Aerospace Metals_General Data and Usage

TO 1-1A-9 NAVAIR 01-1A-9 TM 43-0106TECHNICAL MANUAL ENGINEERING SERIES FOR AIRCRAFT REPAIR AEROSPACE METALS GENERAL DATA AND USAGE FACTORS F09603-99-D-0382 BASIC AND ALL CHANGES HAVE BEEN MERGED TO MAKE THIS A COMPLETE PUBLICATION DISTRIBUTION STATEMENT - Approved for public release; distribution is unlimited. Other requests for this document shall be referred to 542 MSUG/GBMUDE, Robins AFB, GA 31098. Questions concerning technical content shall be referred to 542 SEVSG/GBZR, Robins AFB, GA 31098. Published Under Authority of the Secretary of the Air Force and by Direction of the Chief of the Naval Air Systems Command. 26 FEBRUARY 1999 CHANGE 5 - 27 JUNE 2005 TO 1-1A-9 LIST OF EFFECTIVE PAGES INSERT LATEST CHANGED PAGES. DESTROY SUPERSEDED PAGES. NOTE: The portion of the text affected by the changes is indicated by a vertical line in the margins of the page. Changes to illustrations are indicated by miniature pointing hands. Changes to wiring diagrams are indicated by miniature pointing hands or by shaded areas. A vertical line running the length of a figure in the outer margin of the page indicates that the figure is being added. Dates of issue for original and changed pages are: Original . . . . . . . . . . . . . 0 . . . . . . . . . 26 February 1999 Change. . . . . . . . . . . . . . 1 . . . . . . . . . . . . .25 June 2001 Change. . . . . . . . . . . . . . 2 . . . . . . . . . . . 1 October 2001 Change. . . . . . . . . . . . . . 3 . . . . . . . . . . . . . 26 July 2002 Change. . . . . . . . . . . . . . 4 . . . . . . . . . . 17 January 2003 Change. . . . . . . . . . . . . . 5 . . . . . . . . . . . . .27 June 2005 TOTAL NUMBER OF PAGES IN THIS PUBLICATION IS 288, CONSISTING OF THE FOLLOWING: Page No. *Change No. Page No. *Change No. Page No. *Change No. Title . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5 A. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5 i - vi . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 4 vii Deleted . . . . . . . . . . . . . . . . . . . . . . . . . 4 viii Blank Deleted . . . . . . . . . . . . . . . . . . . 4 1-1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1 1-2 Blank . . . . . . . . . . . . . . . . . . . . . . . . . . 0 2-1 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 0 2-2 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5 2-3 - 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A Change 5 USAF T.O. 1-1A-9 TABLE OF CONTENTS Section Page Section Page I INTRODUCTION..................................................... 1-1 1-1 PURPOSE ............................................. 1-1 II FERROUS 2-1 2-2 2-4 2-7 2-8 2-9 2-11 2-12 2-13 2-14 2-19 2-26 2-29 2-30 2-35 2-41 2-42 2-43 2-48 (STEEL) ALLOYS................................. 2-1 Classification ........................................ 2-1 SAE Numbering System ...................... 2-1 Carbon Steels ........................................ 2-1 Nickel Steels ......................................... 2-2 Chromium Steels .................................. 2-2 Chromium - Nickel Steels.................... 2-2 Chrome - Vanadium Steels .................. 2-3 Chrome - Molybdenum Steels .................................................. 2-3 Principles of Heat Treatment of Steels .................................... 2-3 Hardening ............................................. 2-3 Quenching Procedure ........................... 2-4 Tempering (Drawing) ........................... 2-4 Normalizing........................................... 2-5 Case Hardening .................................... 2-5 Carburizing ........................................... 2-6 Cyaniding .............................................. 2-7 Nitriding................................................ 2-7 Heat Treating Equipment.................... 2-7 Heat Control, Furnace Temperatures Survey and Temperature Measuring Equipment.......................................... 2-8 Furnace Control Instruments Accuracy.................................. 2-8 Salt Bath Control ............................... 2-10 Quenching Tanks and Liquids.............................................. 2-10 Heat Treating Procedures.................. 2-10 Hardness Testing................................ 2-11 Specification Cross Reference.......................................... 2-11 General Heat Treating Temperatures, Composition (Chemical) and Characteristics of Various Steel and Steel Alloy ................ 2-35 Machining of Steels (General) .......................................... 2-60 Machining Corrosion Resisting Steel ..................................... 2-65 Deleted Deleted Deleted Deleted Deleted Deleted Deleted Deleted Deleted Deleted 2-199 2-200 2-201 2-202 2-203 2-216 2-234 2-292 Deleted Deleted Deleted Deleted Deleted Deleted Fabrication of Ferrous Alloys .............................................. 2-121 Steel Surface Finishes...................... 2-130 2-53 2-55 2-58 2-60 2-68 2-73 2-74 2-75 2-81 2-117 2-128 2-131 2-135 2-147 2-152 2-168 2-184 2-186 2-195 III ALUMINUM ALLOYS............................................. 3-1 3-1 Classification ........................................ 3-1 3-4 Commercial and Military Designations ...................................... 3-1 3-8 Mechanical Properties.......................... 3-2 3-16 Physical Properties............................. 3-18 3-17 Heat Treatment of Aluminum Alloys ....................................... 3-18 3-51 Heat Treatment .................................. 3-24 3-56 Heat Treating Equipment.................. 3-24 3-70 Fabrication .......................................... 3-28 3-73 Forming Sheet Metal.......................... 3-28 3-96 Deleted 3-97 Deleted 3-118 Deleted 3-123 Deleted 3-131 Deleted 3-145 Deleted 3-154 Deleted 3-175 Machining............................................ 3-45 3-179 Cutting Tools for Machining Aluminum.................................. 3-45 3-180 Turning................................................ 3-46 3-183 Milling-Aluminum .............................. 3-46 3-189 Shaping and Planing .......................... 3-49 3-195 Tapping................................................ 3-56 3-198 Filing ................................................... 3-56 3-202 Reaming .............................................. 3-57 3-204 Sawing ................................................. 3-57 3-210 Grinding .............................................. 3-58 3-216 Polishing.............................................. 3-58 3-218 Roughing ............................................. 3-58 3-219 Greasing or Oiling .............................. 3-58 3-221 Buffing ................................................ 3-59 3-223 Hardness Testing................................ 3-59 3-226 Non-Destructive Testing/Inspection ........................... 3-59 3-228 Anodizing Process for Inspection of Aluminum Alloy Parts ....................................... 3-59 3-231 Aluminum Alloy Effects on Scratches on Clad Aluminum Alloy .................................... 3-59 3-233 Allowable Defects................................ 3-59 3-234 Harmful Scratches.............................. 3-60 Change 4 i 5-17 Milling ............................ 6-1 6-5 Heat Treatment and Hot Working Temperature of Copper Alloys............................... 5-1 5-11 Hardness Testing....... 5-1 5-1 Classification ......... 5-11 5-34 Joggling ............................. 6-1 6-9 Machining Copper and Copper Alloys ........................... 6-1 6-12 Heat Treating Procedures and Equipment Requirements............... 4-15 4-26 Identification . 5-11 5-28 Draw Forming............................................... 5-1 5-4 General ................................................. HARDNESS TESTING................................................ 5-19 Grinding ................ 5-15 Riveting ................ 8-1 ii Change 4 ..................................................................................... 6-1 6-10 Wrought .................. 5-17 Tapping.....................................................................................................................Continued Section Page Section Page 3-241 3-242 Disposition of Scratches Sheets/Parts . 5-1 5-6 Physical Properties... 7-1 7-5 Specifications .... 5-1 5-5 Military and Commercial Designations ... 4-3 4-22 Grinding and Polishing Safety Practices ............ 5-17 Drilling ...................... 7-5 7-9 Selection of Material for a Cutting Tool ........................................................................................................................................................................ 5-12 5-37 Deleted 5-38 Deleted 5-39 5-40 5-42 5-43 5-45 5-47 5-48 5-51 5-52 5-54 5-57 5-63 5-66 5-69 5-70 Deleted Deleted Deleted Deleted Deleted Soldering .................O..........Beryllium Alloys ...................... 7-6 7-19 Deleted 7-21 Deleted 7-22 Deleted 7-23 Deleted VIII TESTING AND INSPECTION.... 5-11 5-29 Hydraulic Press Forming ....................... 7-1 7-1 General ................................................................. 6-1 6-7 Stress Relief of Copper Alloys ................... 5-11 5-26 Forming Sheet Metal (General) ...... 5-1 5-7 Mechanical Properties.............................................................. 1-1A-9 TABLE OF CONTENTS ....... 4-16 4-29 Heat Treating Magnesium Alloys -(General)... 7-5 7-7 Applications of Tool Steels.............. 3-60 Cleaning of Aluminum Alloy Sheet (Stock).............................. 5-1 5-12 Tensile Testing ....... 4-1 4-13 Safety Requirements for Handling and Fabrication of Magnesium Alloys ..............................................T...................................................................................Copper ................. 4-14 4-24 Deleted 4-25 Heat Treating Safety Practices ........................... 6-11 VII TOOL STEELS............................. 5-6 5-15 Heat Treatment .................... 4-1 4-4 Definitions......................................... 5-19 VI COPPER AND COPPER BASE ALLOYS ............................................................................ 4-2 4-19 Safety Precautions for All Alloys (Including Fire Hazards) ............................. 6-1 6-3 Copper Alloying Elements .......Hammer Forming .......................... 5-11 5-33 Drop ...... 4-1 4-1 Classification . 5-12 5-35 Blanking and Shearing ......................... 6-10 6-15 Solution ............................... 7-6 7-18 Distortion in Tool Steels ................................................... 5-19 Reaming .................................................................................................... 5-1 5-14 Fire Damage ..................... 5-15 Machining and Grinding........................... 7-1 7-6 Class Designations ................................................................................................................................. 7-5 7-16 Heat Treat Data ..................................................................................................................... 5-1 5-13 Non-Destructive Testing ...........................................Heat Treatment Copper Beryllium . 6-1 6-1 Copper and Copper Base Alloys ............. 5-17 Turning................................ 6-11 6-17 Precipitation or Age Hardening ................ 4-19 4-47 Deleted 4-77 Deleted 4-78 Deleted 4-79 Deleted 4-82 Deleted 4-93 Deleted V TITANIUM AND TITANIUM ALLOYS............................................................... 5-11 5-32 Stretch Forming................................... 7-1 7-4 Alloying Elements in Tool Steels ......................... 5-6 5-22 Hydrogen Embrittlement .............................................. 4-16 4-45 Alloy General Characteristic Information......................... 5-17 Machining.............................................................(General) ..... 3-60 IV MAGNESIUM ALLOYS ..... 5-8 5-25 Fabrication .............................. 5-1 5-10 Methods of Identification.... ......................................... 2-64 Change 4 iii ........................ 9-3 9-38 Stress-Relief After Welding . 8-1 Vickers Pyramid Hardness Test .......................... 8-4 Rockwell Hardness Tester ......... 8-14 Chemical Analysis . 1-1A-9 TABLE OF CONTENTS ...................Continued Section Page Section Page 8-1 8-3 8-5 8-8 8-15 8-18 8-20 8-21 8-22 8-24 8-27 8-33 8-34 General ............................................................................................................................................ 3-55 Typical Dust Collectors for Magnesium.................... 8-1 Brinell Hardness Test .............................................................................................O..... 8-14 Spectrochemical Analysis............................................................................................................................... 2-9 Deleted Deleted Stretch Forming.......................................... 9-11 9-68 Description of Methods .................................................... 8-9 Hardness Method... 2-12 Cutting Speeds and Feeds for SAE 1112 Using Standard High Speed Tools .. 9-1 9-11 Tint Test for Determining Coating Removal from Nickel Base and Cobalt Base Alloys ...................................................... 8-9 Tensile Testing ...................... 8-11 LIST OF TABLES Number Title Page Number Title Page 2-1 2-2 2-3 Soaking Periods for Hardening Normalizing and Annealing (Plain Carbon Steel).................. 8-7 Standard Pyramid Diamond Indentor........................................................ 2-61 Conversion of Surface Feet Per Minute (SFM) to Revolutions Per Minute (RPM).................................. 4-22 4-2 4-3 4-4 8-1 8-2 8-3 8-4 8-5 8-6 8-7 Deleted Deleted Deleted Brinell Hardness Tester................... 2-61 2-4 2-5 2-6 Machinability Rating of Various Metals............................................................................................................................................... 9-11 A Supplemental Data .......................................... 8-9 Decarburization Measurement ................................................................................ 8-14 IX HEAT TREATMENT ................................................. 8-6 Vickers Pyramid Hardness Tester .. 2-10 Specification Cross Reference ............ 8-8 Testing with the Scleroscope .................................................. or Precipitation Heat Treatment . 2-135 Head to Alloy Identification Method ....A-1 Glossary ........ 9-1 9-13 Titanium Alloy Parts. 3-20 Drill Designs and Recommended Cutting Angles..... 8-10 Nondestructive Inspection Methods.................. 8-8 Test Specimens ................... Stabilization..................T....................................... 8-4 Shore Scleroscope Hardness Test ...................... 9-3 9-16 Solution.... 8-1 Rockwell Hardness Test................................... 8-8 Shore Scleroscope .................................................... 9-1 9-1 General .............. 8-1 Methods of Hardness Testing.................................................... 8-5 Attachments for Rockwell Tester ....................................... 9-1 9-9 Special Heat Treatment Information ... 9-8 9-59 Local Stress-Relief ................................................... 2-127 Surface Roughness .................GLS 1 LIST OF ILLUSTRATIONS Figure Title Page Figure Title Page 2-1 2-2 2-3 2-4 2-5 3-1 3-2 4-1 Number and Distribution of Thermocouples................... 2-63 Tool Correction Chart ............ . 3-52 Milling ....................................................................................... 3-23 Recommended Maximum Quench Delay............................................... 3-32 Deleted Deleted General Rivet (Alum) Identification Chart ......Speeds and Feeds.......... 2-70 Drilling Speeds for Corrosion Resisting Steel........................................................... 3-25 Reheat Treatment of Alclad Alloys.. 3-52 Tool Angles ............... 2-71 Deleted Deleted Deleted Deleted Deleted Deleted Deleted Deleted Deleted Deleted Deleted Deleted Deleted Deleted Deleted Deleted Deleted Deleted Deleted Deleted Cold Bend Radii (Inside) Carbon/Low Alloy Steels........ 2-136 Designations for Alloy Groups ....................................................................... 3-27 Cold Bend Radii (Inside) for General Applications.................................. 3-29 Maximum Accumulative Reheat Times for Hot Forming Heat Treatable Alloys at Different Temperatures .............................................. 4-7 iv Change 4 .................................................................... 2-65 Suggested Cutting Speeds and Feeds .................. Wrought Alloys (For Immersion Type Quenching)................Continued Number Title Page Number Title Page 2-7 2-8 2-9 2-10 2-11 2-12 2-13 2-14 2-15 2-16 2-17 2-18 2-19 2-20 2-21 2-22 2-23 2-24 2-25 2-26 2-27 2-28 2-29 2-30 2-31 2-32 2-33 2-34 2-35 2-36 2-37 2-38 3-1 3-2 3-3 3-4 3-5 3-6 General Machining Comparison of Corrosion Resisting Steel to Free Machining Screw Stock B1112 ......................... 3-24 Precipitation (Aging) Treating Temperatures............Standard Alloys..................................... 3-1 Aluminum Alloy Designation and Conversions to 4 Digit System ... 2-128 Forging Temperature Ranges for Corrosion Resistant Steel ..Speeds and Feeds ................................................ 3-50 Turning Speeds and Feeds ............................................................................................. 3-45 Shear Strength of Protruding and Flush Head Aluminum Alloy Rivets........ 3-51 Tool Angles .......................... 4-3 Alloy Designation Cross-Reference ...................................... 3-42 General Aluminum Rivet Selection Chart (Rivet Alloy vs Assembly Alloy) .. Inch Pounds .......................Typical............................................ 2-134 Surface Roughness and Lay Symbols ........................................ 2-68 Suggested Milling Cutting Speeds and Feeds................................................................................................ 2-70 Tapping Allowances (Holes Size to Screw Size) .................. 3-54 Thread Constant for Various Standard Thread Forms ............................................................ 3-23 Soaking Time for Solution Treatment of Cast Alloys.........Turning ...... 2-128 Cold Bend Radii (Inside) Corrosion Resistant Steel Alloys...... Alloy Designations to Specifications................................. Times and Conditions ............Milling............................. of Aluminum Alloy Plates and Shapes .................. 2-128 Galvanic Series of Metals and Alloys............... 2-69 Suggested Tool Angles ......... 3-14 Physical Properties ..................................... 3-9 Mechanical Properties ..................O. 3-16 3-7 3-8 3-9 3-10 3-11 3-12 3-13 3-14 3-15 3-16 3-17 3-18 3-19 3-20 3-21 3-22 3-23 3-24 3-25 3-26 3-27 3-28 4-1 4-2 4-3 Heat Treating (Soaking) Temperatures ................................................T..Milling.......... 3-17 Soaking Time for Solution Heat Treatment of All Wrought Products ..................................................................... 3-48 Standard Rivet Hole Sizes with Corresponding Shear and Bearing Areas for Cold Driven Aluminum Alloy Rivets....................... 3-54 Shaping Tool Angles ........................ 3-47 Bearing Properties............. 2-66 Tool Angles .... 3-1 Federal and Military Specifications......... 4-6 Chemical Properties of Magnesium Alloys ......................................................Turning ........ 1-1A-9 LIST OF TABLES ... 3-3 Chemical Composition Nominal and General Use Data 1/ .. 3-53 Shaping and Planing ................................. 3-56 Cross-Reference. Typical. . 7-7 Thermal Treatment for Hardening and Tempering Tool Steel . Stabilization or Precipitation Heat Treatments ........................ 5-18 Angles for Tool Grinding ..... 4-18 Artificial Aging (Precipitation Treatment) ... 4-12 Physical Properties ................................... 9-4 Cross-Index for Stress-Relief Heat Treatments ................ 6-9 Typical Stress-Relief Treatments for Certain Copper Alloys ........................... 7-14 Hardness Conversion Chart ..... 6-11 Standard Machinability Rating of Copper Alloys ............. 5-18 Tool Angles for Alloys ................................................ Loads and Prefix Letters ...................Magnesium and Magnesium Alloy ...........................Typical.......................................................................................... 5-7 Heat Treat...... 7-2 Chemical Composition.................Magnesium Alloy @ 68 oF...... 5-18 Speeds and Feeds for Milling ............................................................................Brass................. Stress Relief and Annealing Temperatures and Times ........... A-13 Table of Weights ................ 4-9 Mechanical Properties Magnesium Alloy Sheet and Plate at Room Temperature .......................................... 8-3 Rockwell Scales............................ 6-2 6-2 6-3 6-4 6-5 6-6 7-1 7-2 7-3 7-4 7-5 7-6 7-7 8-1 8-2 8-3 9-1 9-2 9-3 A-1 A-2 A-3 A-4 A-5 A-6 A-7 A-8 A-9 A-10 A-11 A-12 A-13 Hot Working and Annealing Temperatures for Copper and Wrought Copper Alloys........................ 9-9 Chemical Symbols .A-12 Table of Weights ........... 7-5 Forging......................................... A-13 Table of Weights ....................... 4-13 Solution Heat Treating Temperatures and Holding Times .......Continued Number Title Page Number Title Page 4-4 4-5 4-6 4-7 4-8 4-9 4-10 4-11 4-12 4-13 4-14 4-15 4-16 4-17 4-18 4-19 4-20 4-21 4-22 4-23 4-24 4-25 4-26 4-27 4-28 4-29 4-30 4-31 5-1 5-2 5-3 5-4 5-5 5-6 5-7 5-8 5-9 6-1 Mechanical Properties Magnesium Extrusions and Forgings at Room Temperature ............................... 6-13 Tool Steel Specifications............... 7-5 Tool Steel Hardening and Tempering Temperatures ..........General ........ Tool Steel................ 7-11 Comparison of Tool Steel Properties.................... 9-1 Cross-Index for Solution. 8-12 Typical Heat Treatment Application........................ 5-19 Chemical Composition by Trade Name ........................................ 6-13 Age Hardening Time-Temperature Conditions and Material Temper Designations ................T............................................................................................................................................. A-8 Table of Weights .................................... 5-12 Deleted Turning Speeds for Titanium Alloys.................................. 4-11 Mechanical Properties of Magnesium Alloy Castings at Room Temperatures................A-13 Change 4 v .......................................... Normalizing and Annealing Treatments of Tool and Die Steels ................A-10 Table of Weights ................... 6-12 Typical Engineering Properties......Steel......................................Nickel Chromium Iron Alloy (Inconel) .....Copper ........................... 4-19 Deleted Deleted Deleted Deleted Deleted Deleted Deleted Deleted Deleted Deleted Deleted Deleted Deleted Deleted Deleted Deleted Deleted Deleted Deleted Deleted Deleted Deleted Specification Cross Reference Titanium Alloy ...............Bronze .............................................Tensile Strength Relationship of Carbon and Low Alloy Steels ........ 1-1A-9 LIST OF TABLES ........Aluminum and Aluminum Alloy.........................................A-6 Table of Weights .............O............A-1 Decimal Equivalents .................... 8-10 Approximate Hardness ...........Nickel Copper Alloy........... 7-3 Tool Steel Selection ........................A-2 Engineering Conversion Factors ..... A-12 Table of Weights ......A-12 Table of Weights ................Lead..............A-9 Table of Weights .......... 5-2 Nominal Mechanical Properties at Room Temperature ...................A-11 Table of Weights ..........Typical.......................Iron ....................................................... 5-9 Recommended Minimum CCLD Bend Radii ................................... .......................A-21 Comparative Table of Standard Gages........................ A-18 Metal Bending and Bend Radii Bend Allowances Sheet Metal Bend Allowances Per Degree of Bend Aluminum Alloys..............Zinc ....Continued Number Title Page Number Title Page A-14 A-15 A-16 A-17 Table of Weights .......................................... 1-1A-9 LIST OF TABLES .. A-19 A-18 A-19 A-20 Bend Set Back Chart ................. A-22 Melting Points Approximate.....A-16 Temperature Conversion Chart ........A-17 Standard Bend Radii for 90o Cold Forming-Flat Sheet ...........O...................................T......................A-23 vi Change 4 ...... Change 1 1-1/(1-2 blank) . WELDING. deversif ied uses and new developments of metal products.O. 1-6. LEM. The word ‘‘will’’ is used to express declaration of purpose. PURPOSE. T. 9-238. refer to comparable Army documents. 1-2.. temperatures and other controls for heat treatments. 1-3. sand control.T. d. Deleted 1-7. 1-1A-9 SECTION I INTRODUCTION 1-1. etc. The words ‘‘will’’. Procedures for general foundry practice. it may not include all data required in some instances and further study and citation of this data will be required.O. it shall be interpreted to mean that the requirements are binding. ‘‘should’’ and ‘‘may’’ in this technical manual is as follows: a. gating and risering of both ferrous and non-ferrous castings may be obtained from available commercial handbooks and/or publications. the data applicable to the specif ic item(s) will govern in all cases. It includes such data as specif ication cross reference. If a conf lict exists between this technical manual and the specif ic technical manual(s) or other approved data for a particular weapon. Information on welding aerospace metals is contained in NAVAIR 01-1A-34. ‘‘should’’ and ‘‘may’’. mechanical and physical properties processing instructions for basic corrosion prevention. The use of ‘‘shall’’. The word ‘‘may’’ is used to express an acceptable or suggested means of accomplishment. e. end item. grades. b. a request for assistance should be made to WR-ALC. usage and processing for fabrication and repair. and other information required for general aerospace weapon system repair. If a requirement exists for information not included. ‘‘will’’. c. This is one of a series of technical or engineering technical manuals prepared to assist personnel engaged in the maintenance and repair of Aerospace Weapon Systems and Supporting Equipment (AGE). The word ‘‘should’’ is used to express nonmandatory desired or preferred method of accomplishment. 00-25-252. Due to the many types. approved designation system for alloys and tempers. shall be interpreted as nonmandatory provisions.O. Army Personnel: Wherever the text of this manual refers to other technical orders (T. The information/instruction contained herein are for general use. equipment. This technical manual provides precise data on specif ic metals to assist in selection.C. 1-4. 1-5. Whenever the word ‘‘shall’’ appears. T.’s) for supporting information. forming characteristics. . CARBON STEELS.25% Nickel. An instance of such departure is the steel numbers selected for several of the corrosion --and heat resisting alloys. Steels of this grade are used for the manufacture of articles such as safety wire. TYPE OF STEEL Nickel-Chromium-Molybdenum Steels 1. 1.50 Percent Nickel.50 percent is classed as medium carbon steel.25 percent Molybdenum Chromium Steels Low Chromium Medium Chromium High Chromium Corrosion and Heat Resisting Chromium-Vanadium Steel 0. 0.65% Chromium.25% Molybdenum 0.15 Vanadium Silicon Manganese Steels A Percent Silicon Low Alloy. ‘‘2’’ a nickel steel.25 to 3. and ‘‘3’’ a nickel chromium steel. 0. forging. 0.T.75) and 0. The equivalent SAE numbers range from 1010 to 1030. 2-5. Steel containing carbon in percentages ranging from 0. cable bushing.80-1.50 and 0.75 Percent Nickel.43). 0.40 percent carbon (0.10 to 0. it has been found necessary to depart from this system of identifying the approximate alloy composition of a steel by varying the second and third digits of the number.O.65 percent Chromium Corrosion and Heat Resisting Molybdenum Steels 0.00 percent Chromium. in order to avoid oonfusion. High Tensile Boron Intensified Leaded Steels 43xx 86xx 87xx 93xx NUMERALS (AND DIGITS) 2-2. 0. SAE NUMBERING SYSTEM.80% Chromium. In some instances. Usually the last two or three digits indicate the approximate average carbon content in ‘‘points’’ or hundredths of 1 percent.30 percent is classed as low carbon steel.25 Percent Molybdenum NUMERALS (AND DIGITS) 1xxx 10xx 11xx 13xx 3xxx 31xx 303xx 4xxx 40xx 46xx 48xx 5xxx 50xx 51xxx 52xxx 514xx and 515xx 6xxx 61xx 9xxx 92xx 950 xxBxx xxLxx 2-4. 0. The f irst digit indicates the type to which the steel belongs.25% Molybdenum 3.55% Nickel. 0. etc.50 and 0.20 Chromium 0.30 to 0.55% Nickel.10-0. The basic numerals for the various types of SAE steel are: TYPE OF STEEL Carbon Steels Plain Carbon Free Cutting (Screw Stock) Manganese Steels Nickel Chromium Steels 1. for example ‘‘1’’ indicates a carbon steel. the second digit generally indicates the approximate percentage of the predominant alloying element.80% nickel.20% Molybdenum 0. A numeral index system is used to identify the compositions of the SAE steels.25 percent Molybdenum 3. 2-3. Steel containing carbon in percentages ranging from 0.12% Molybdenum Nickel-Molybdenum Steels 1. Thus ‘‘2340’’ indicates a nickel steel of approximately 3 percent nickel (3. This steel in sheet form is used for secondary structural parts and clamps and in tubular form for moderately stressed structura1 parts.25 Percent Nickel. 1-1A-9 SECTION II FERROUS (STEEL) ALLOYS 2-1.50 Chromium 0.38 to 0. 0. In the case of the simple alloy steels. and where surface hardness is 2-1 . 0. CLASSIFICATION. This steel is especially adaptable for machining. certain nuts. which makes it possible to use numerals that are partially descriptive of the composition of material covered by such numbers. 2-9. are made from SAE 1035 steel. etc. CHROMIUM-NICKEL STEELS.50 to 1. strength.Sulfur (s) or Selenium (Se) added to improve machinability. 321. 301-Chromium and Nickel (approximate 0. b. 304-Carbon (c) lowered to reduce susceptibility to carbide precipitation. 2-8. 316L. SAE 1095 in sheet form is used for making flat springs and in wire form for making coil springs. 302. Chrome-nickel steel containing approximately 18 percent chromium and 8 percent nickel is known as corrosionresistant steel. The following are examples of variations: a. SAE 51335 steel is particularly adaptable for heat-treated forgings which require greater toughness and strength than may be obtained in plain carbon steel. The lowering of the carbon content makes the steel more ductile and less susceptible to uneven stress. and parts such as Woodruff keys. It is usually identified as aisi types 301.25 percent. f. In the fully heat-treated condition it is very hard and will withstand high shear and wear. Both nickel and chromium influence the properties of steel. 303. impact resistance and toughness. 2-7. the basic 18-8 chrome-nickel steel is type 302. d. NICKEL STEELS. d. b. 321-Titanium (Ti) added to reduce/avoid carbide precipitation (stabilized grade). e. while chromium hardens it. 304.5 Nickel) is lowered to increase response to cold working. surface skin. The general proportion is about two and one-half times as much nickel as chromium. 347F or Se. Chromium steel is high in hardness. 2-6. 309-Cr and Ni higher for additional corrosion and scale resistance. Tantalum (Ta). Chromium and nickel in various proportions mixed with steel form the chromenickel steels. The addition of other elements in varying quantities adds to the hardness of this steel. light forgings. h. In plate and sheet form it is used for firewalls. excessive grain growth and the consequent development of brittleness. CHROMIUM STEELS.05 percent is classed as high carbon steel. Chrome-nickel steel is used for machined and forged parts requiring strength. Steel containing carbon in percentage ranging from 0.. 303-Sulfur(s) or Selenium (se) added for improved machining characteristics.45 to 1. and corrosion resistant properties. toughness and shock resistance. i. Parts such as crankshafts and connecting rods are made of SAE 3140 steel. reduces the danger of overheating. 316L-C.TO 1-1A-9 important. The low heat treating temperatures required. It may be used for such articles as the balls and rollers of anti-friction bearings. The alloys are varied to obtain the required mechanical properties for some specific purpose such as improving corrosion resistance or forming machining. Lowers the percentage of carbon that is necessary for hardening. This alloy is still subject to carbide preceipitation from exposure to temperatures 800-1500F range and this shall be considered when it is selected for a specific application. c.lowered for welding applications. j. 302-Basic Type 18 Chromium 8 Nickel. g. The other grades/types have been modified by changing or adding alloying elements to that contained in the basic alloy. e. Certain rod ends. c. however.Added to reduce/ avoid carbide precipitation (stabilized grade). 2-2 Change 5 . 2-10. Lowers the critical temperature ranges (heating and cooling) and permits the use of lower heating temperatures for hardening. It has limited use in aircraft construction. 309. Some benefits derived from the use of nickel as an alloy in steel are as follows: a. 304L-Carbon (c) lowered for welding applications. nickel toughens it. The characteristics depth hardening from the addition of nickel to steel as an alloy results in good mechanical properties after quenching and tempering. welding characteristics. while the nickel content ranges from 1 to 2 percent. but little deformation. etc. 316-Molybdenum (Mo) added to improve corrosion resistance and strength. ductility. 347. 304L. 316. Hardening of nickel alloy steels at moderate rates of cooling has the advantage of lowering the temperature gradients. k. At a given strength (except for very thin sections/parts) the nickel steels provide greatly improve elastic properties. For all ordinary steels in this group the chromium content ranges from 0. reducing internal stress/warpage and permits deeper/ more uniform hardening. 347-Columbium (Cb). The various nickel steels are produced by combinining nickel with carbon steel. The chrome-nickel steels are used for a variety of applications on aircraft and missiles. 347F or Se . At elevated temperatures. the chromium content varies from 0. only 0. If the upper critical temperature is exceeded too much. They are especially adaptable for welding and for this reason are used principally for welded structural parts and assemblies. f langes.15 to 0. brackets. Chrome-vanadium steels when heat-treated have excellent properties such as strength. heat shields/def lectors. heater ducts. in the case of certain steel parts. as be quenching in oil or water. 2-17. 2-15. At ordinary temperatures the iron exists as ‘‘ferrite’’. HARDENING. The temperature at which this change from austenite to ferrite begins to occur on cooling is called the ‘‘upper critical temperature’’ of the steel. 1-1A-9 exhaust stacks. the carbon is dissolved in the iron matrix and the carbide-particles appear only af ter the steel has cooled through its ‘‘critical temperature’’ (see paragraph 2-15). If the cooling is rapid. Molybdenum is very similiar to tungsten in its effect on steel.85 to 1. screens/screening and other miscellaneous items. missiles. and resistance to wear and fatigue.00 percent. the temperature of the steel may be judged approximately by its color. the thickness of the section controls the depth of hardness for a given steel composition. Control of furnace atmosphere. 2-12. nuts. In some instances it is used to replace tungsten in cutting tools. c. studs. in this condition the steel is sof t. however. e. size. At ordinary temperatures. gear structures. The addition of up to 1% molybdenum gives steel a higher tensile strength and elastic limit with only a slight reduction in ductility. 2-16. couplings. and temperature of quenching medium to harden adequately and to avoid cracks. At elevated temperatures. bolts. The accuracy with which temperatures 2-3 . in the form of carbide particles. At times. etc. hinge pins. 2-11. shims.85 percent carbon. Steel that has been heated to its upper critical point will harden completely if rapidly quenched. Chrome-vanadium steel with high carbon content (SAE 6195) is used for ball and roller bearings. determines the hardness and strength of the steel. which condition is associated with high hardness of the steel. an unsatisfactory coarse grain size will be developed in the hardened steel. Control over the rate of heating. Parts fabricated from 4130. specif ically to prevent cracking of thick and irregular sections. the iron matrix exists in a form called ‘‘austenite’’ which is capable of dissolving carbon in solid solution. to prevent scaling and decarburization. clamps.10 percent. The 4130 alloy is used for parts such as engine mounts (reciprocating). as described in the preceding paragraph. Molybdenum in small percentage is used in combination with chromium to form chrome-molybdenum steel. and varies with the carbon content. rivets. the carbide particles are relatively coarse and few. the carbon precipitates as a cloud of very f ine carbide particles. such instruments are not available. viscosity. Successful hardening of steel will largely depend upon the following factors af ter steel has been selected which has harden ability desires: a. b. up to approximately 0. ammunition chutes. however. It can be folded and f lattened without signs of breaking or failure. this steel has important applications in aircraf t. the temperature should be determined by the use of accurate instruments. the heat treat characteristic varies. screws. and in such cases. bolts. the upper critical temperature is lowered with increasing carbon content. CHROME-VANADIUM STEELS. Chrome-vanadium steel with medium high carbon content (SAE 6150) is used to make springs. turn-buckles. and miscellaneous GSE equipment. from 0. Very thick sections may not harden through because of the low rate of cooling at the center. 2-13. PRINCIPLES OF HEAT TREATMENT OF STEELS. A special grade of this steel in sheet form can be cold-formed into intricate shapes. etc. If the rate of cooling is slow..80 to 1. cable.MOLYBDENUM STEELS. The vanadium content of this steel is approximately 0. the nature of these carbide particles. fairing.e. CHROME . the carbon content of steel exists in the form of particles of iron carbide scattered throughout the iron matrix. In bar and rod it is used to fabricate various f ittings.O. are used extensively in the construction of aircraf t. toughness. Correct heat capacity. valve stems/seats.T. In addition to the preceding factors. stiffeners. Thorough and uniform heating through sections to the correct hardening temperatures. and distribution. d. nuts.25percent being used in the chromemolybdenum steels. In wire form it is used for safety wire. i. their number.70 percent carbon the upper critical temperature is raised with increasing carbon content. support brackets for accessories. gun wells. in which carbon is relatively insoluble and precipitates. however.18 percent and the chromium content approximately 1. etc. When heating steel. Molybdenum is a strong alloying element. 2-14. in practice it is necessary to exceed this temperature by/from approximately 28o to 56oC (50o to 100oF) to insure thorough heating of the inside of the piece. 1-1A-9 may be judged by color depends on the experience of the workman. The article should be slightly agitated in the bath to destroy the coating of vapor which might prevent it from cooling rapidly. In addition. QUENCHING PROCEDURE. and then applying pressure. d. 2-21. 2-24. The tendency of steel to warp and crack during the quenching process is diff icult to overcome. Unfortunately. 2-19. as steel in its hardened condition cannot be bent or sprung cold with any degree of safety. Tempering consists in reheating the steel to a temperature below the critical range (usually in the neighborhood of 600 1200oF). however. 2-26.O. and is due to the fact that certain parts of the article cool more rapidly than others. Warped parts must be straightened by f irst heating to below the tempering temperature of the article. The water bath should be approximately 18oC (65oF). This allows the bath to remove the heat of the article rapidly by conduction and convection. and the tendency of heated steel to warp or crack when quenched may be greatly reduced by its use. parts made from high carbon steel will not develop maximum hardness when quenched in oil unless they are quite thin in cross section. Steel that has been hardened by rapid cooling from a point slightly above its critical range is of ten harder than necessary and generally too brittle for most purposes. In certain cases water is used in the quenching of steel for the hardening process. For example. In aircraf t. NOTE Aerators may be used in the Quench Tanks to help dissipate the vapor barrier. It is desirable to retemper the part af ter straightening at the straightening temperature. A 10%. QUENCHING MEDIUM. a bath of water covered by a f ilm of oil is occasionally used. Both the medium and the form of the bath depend largely on the nature of the work to be cooled. thus reducing the tendency to crack due to contraction. This is particularly important where many articles are to be quenched in succession. STRAIGHTENING OF PARTS WARPED IN QUENCHING. and the emissivity or tendency of steel to radiate or emit light. By permitting it to lie on the bottom of the bath it is apt to cool faster on the top side than on the bottom side. 2-25. depending on the severity of the stresses. Operations such as forging and machining may set up internal stresses in steel parts and it is therefore advisable to normalize articles before attempting the hardening process. This pressure should be continued until the piece is cooled. Irregularly shaped sections should be immersed in such a manner that the parts of the greatest section thickness enters the bath f irst. The following recommendations will greatly reduce the warping tendency and should be carefully observed: a. Irregularly shaped parts are particularly susceptible to these conditions although parts of uniform section size are of ten affected in a similar manner. 2-23.T. the character of the scale on the steel. the amount of radiated light within the furnace. A number of liquids may be used for quenching steel. When the steel is plunged through this oil f ilm a thin coating will adhere to it. salt brine (sodium chloride) solution is used when higher cooling rates are desired. Oil is much slower in action than water. 2-18. A 10% salt brine solution is made by dissolving 0. the light in which the work is being done. In order to relieve the stresses and reduce the brittleness or restore ductility the metal is always ‘‘tempered’’. NOTE Alloy steels should never be quenched in water. Whenever the rate of cooling is not uniform. TEMPERING (DRAWING). it is under severe internal stress. it is generally used and is recommended in all cases where it will produce the desired degree of hardness. internal stresses are set up on the metal which may result in warpage or cracking. as extremely cold water is apt to warp or crack the steel and water above this temperature will not produce the required hardness. This reheating causes a coalescence and enlargement of the f ine carbide particles produced 2-4 . a gear wheel or shaf t should be quenched in a verticle position. thus causing it to warp or crack. 2-20. regardless of the number of times it has been previously heated. 2-22. No attempt should be made to straighten hardened steel without heating. b. For many articles such as milling cutters and similar tools. c. retarding the cooling effect of the water slightly. It is important that a suff icient quantity of the medium be provided to allow the metal to be quenched without causing an appreciable change in the temperature of the bath. An article should be quenched in such a manner that all parts will be cooled uniformly and with the least possible distortion.89 pound of salt per gallon of water. An article should never be thrown into quenching media/bath. bending. forming. Surface sof tening is accomplished by heating the surface to just below the temperature 2-5 . tempering temperatures may be approximately determined by color. and nitriding. Normally. The fast quench hardens the steel to the depth that the hardening temperature has penetrated below the surface. c. wear-resistant surface or ‘‘case’’ over a strong. that the surface is rapidly heated to the proper quenching temperature for the steel being treated. 2-32. 2-27. CASE HARDENING. Heating to low temperatures. To increase its ductility by reducing hardness and brittleness. A buff stick consisting of a piece of wood with emery cloth attached is ordinarily used for this purpose. and wires for rope and cable. is to determine temperatures by hardness checks. This is accomplished in the same types of furnaces as are used for hardening and annealing. These colors appear only on the surface and are due to a thin f ilm of oxide which forms on the metal af ter the temperature reaches 232oC (450oF).e. Less ref ined methods are sometimes used for tempering small tools. 2-28. rapid heating will narrow the affected area. Following the application of the heat. 2-30. they must be removed from the furnace and cooled in still air. Treatment of this kind is known as ‘‘case hardening’’. an open f lame of heated iron plate is ordinarily used as the heating medium. Tempering temperatures can also be determined by the use of crayons of known melting point. 1045. and welding. 1040. Normalizing may be accomplished in furnaces used for annealing.O. The above method may be used where exact properties af ter tempering is not too important such as for blacksmith work. Such crayons are commercially available for a wide range of temperatures under the trade name of ‘‘Tempilstiks’’. However. the part is quenched by a spraying of water/oil rapidly. The most desireable method for general aeronautical use. 2-29. as this practice will cause the grain structure to enlarge. However. 1137. tough core. The actual hardness resulting will depend on the rate of cooling from the quenching temperature. In many instances it is desirable to produce a hard. To sof ten the material so that machining. as in soldering. 1140 etc. Steel which has been coldworked is usually annealed so as to increase its ductility. Steel is usually subjected to the annealing process for the following purposes: a. normalizing may be classed as a form of annealing. This treatment may be accomplished in several ways. the surface must be brightened. The optimum soaking time is roughly one-quarter hour per inch of diameter or thickness. Although the color method is convenient. will destroy these properties. NOTE This method is not adapted for surface hardening of parts for use in critical applications. In hardening by this method the shape and size/mass of the part must be considered. forging. NORMALIZING.T. b. If a combination of high strength core and surface is required some of the medium carbon alloy steels can be heat treated and subsequently surface hardened by the f lame method. cyaniding. The desired strength wanted will determine the tempering temperature. As in the case of hardening. When tempering by the color method. can be performed. because surface can be cooled at a faster rate. which is usually water. To ref ine the crystalline structure and remove stresses. piano wire. Prolonged soaking of the metal at high temperatures must be avoided. by applying a reducing f lame (An Oxidizing f lame should never be used) at such a rate. and subsequent adjustments made as necessary to obtain the properties required. The articles are put in the furnace and heated to a point approximately 150o to 225oF above the critical temperature of the steel. f lame hardening will produce surface hardness higher than can be obtained by routine furnace heating and quenching. Most operations will require special adapted spray nozzles to apply the quenching media. the principal ways being carburizing. Surface hardening/sof tening by applying intense heat (such as that produced by an Oxy-Acetylene f lame) can be accomplished on almost any of the medium carbon or alloys steel. a large amount of cold-drawn wire is used in its cold-worked state when very high yield point and tensile strength are desired and relatively low ductility is permissible. 1-1A-9 by drastic quenching. For recommended tempering temperatures see heat treat data for material/composition involved. and thus tends to sof ten the steel. The parts are surface hardened. Flame Hardening/Sof tening. This process also removes stresses due to machining. Af ter the parts have been held at this temperature for a suff icient time for the parts to be heated uniformly throughout. 2-31. as in spring wire. Although involving a slightly different heat treatment.. The length of time required for the soaking temperature will depend upon the mass of metal being treated. i. it should not be used unless adequate facilities for determining temperature are not obtainable. etc. In order to see the tempering colors. liquid. Hardening/Heating.O. the carburizing steels are those containing not more than 0. When pack carburizing. therefore. bone charcoal and charred leather. b. necessary to heat the parts again to the critical temperature of the case and quench them in oil to produce the required hardness. 2-37. carbon travels slowly from the outside toward the inside center. a. in a manner similar to that used for f lame hardening. Of ten it is necessary to apply the heat in short intervals to prevent exceeding the hardening temperature. This method is sometimes used to sof ten material that has been hardened by frame cutting. The induction method of heating can be used to surface harden steels. In some instances the induction method can be used to deep harden. Carburized steel parts are rarely used without subsequent heat treatment. it will absorb carbon from the gas until a carbon content of approximately 0. the proportion of carbon absorbed must decrease from the outside to the inside. and therefore. the carburization progresses more slowly as the carbon content increases during the process. while in contact with a carbon-aceous substance. the parts are quenched in oil. however. The length of time required to produce the desired degree of carburization material used and the temperature to which the metal is subjected. Parts hardened (surface) by this method will be limited to capability and size of loop/coil used to produce the magnetic f ield. For example. It is.1 percent has been attained. the more readily it will absorb. Solid. 2-36. although slow. reduces warpage and is advisable in many cases. 2-40. The amount of carbon absorbed and the thickness of the case obtained increases with time. At elevated temperatures iron can react with gaseous carbon compounds to form iron carbide. and optimum strength and ductility in the core.T. 2-39. intensity of the magnetic f ield. which is the saturation point for the increased temperature. It is apparent that. CARBURIZING. if mild or sof t steel is heated to 732oC (1. the extent will depend on exposure/dwell time. Ref ining the core is accomplished by reheating the parts to a point just above the critical temperature of the steel. depending upon the depth of case desired and the size of the work. 2-35. The air cooling. heated to the proper temperature. Liquid carburizing consists of immersing the parts in a liquid salt bath. The simplest method of carburizing consists of soaking the parts at an elevated temperature while in contact with solid carbonaceous material such as wood charcoal. 1-1A-9 required for hardening and allowing the material to cool (in air) naturally. Capped pipes of mild steel or welded mild steel boxes are useful only as substitutes. this being the saturation point of the steel for the particular temperature. Af ter soaking for a suff icient time to insure uniform heating. 2-34. A soaking period of 10 minutes is generally suff icient. Induction. c. The container should be so placed as to allow the heat to circulate entirely around it. Specif ically. 2-6 . This process is particularly adaptable to certain engine parts. and the size of the part to be treated. and gas carburizing methods are employed. carbonic gases given off by this material will penetrate the steel to an amount proportional to the time and temperature. capped pipes of mild steel. carbon during the carburizing process. The carbon penetrates the steel as in the solid method producing the desired case. By heating steel. Nichrome boxes. Grain size of the core and case is ref ined.20 percent carbon.350oF) in an atmosphere of carbonic gases. Af ter carburizing. The hardening temperature for the high carbon case is well below that of the core. b. or welded mild steel boxes may be used. By increasing the heat to 899oC/(1. Nichrome boxes are most economical for production because they withstand oxidation. The lower the carbon content in the steel. in carburizing. a. which consists of several steps to obtain optimum hardness in the case. The carburizing process may be applied to both plain carbon and alloy steels provided they are within the low carbon range.80 percent has been attained at the surface. the container should be removed and allowed to cool in air or the parts removed from the carburizing compound and quenched in oil or water.650oF) the same steel will absorb carbon from the gas until a carbon content of approximately 1. The furnace must be brought to the carburizing temperature as quickly as possible and held at this heat from 1 to 16 hours. Gas carburizing consists of heating the parts in a retort and subjecting them to a carbonaceous gas such as carbon monoxide or the common fuel gases. 2-38. 2-33. the parts are packed with the carburizing material in a vented steel container to prevent the solid carburizing compound from burning and to retain the carbon monoxide and dioxide gases. The exception is that the heat for hardening is produced by placing the part in a magnetic f ield (electrical) specif ically designed for the purpose. A f inal stress relieving operation is necessary to minimize the hardening stresses produced by the previous treatment. if heated above that temperature. Furnaces and baths shall be of suitable design. at any point. The design and construction of the heating equipment shall be such that the furnace/bath is capable of maintaining within the working zone. The container in which the work and ammonia gas are brought in contact must be airtight and capable of maintaining good circulation and even temperature throughout. combusted gases. quenching.O. When no distortion is permissible in the nitrided part. Various jigs and f ixtures are sometimes needed for controlling quenching and preventing warping. 2-41. MILH-6875 or engineering data for material involved). NITRIDING. one of the essential constituents of which is aluminum. The depth of case obtained by nitriding is about 0. the hardness is rapidly lost and cannot be regained by retreatment. Nitrided surfaces can be reheated to 950oF with out losing any of their hardness. The stress relieving temperature is generally around 350oF. the parts are quenched in water. it is necessary to normalize the steel prior to nitriding to remove all strains resulting from the forging. Only a thin case is obtained by this method and it is. When extreme hardness is desired. for the treatment required in aircraf t work. inert atmosphere or vacuum furnaces. however. The furnace should be of a suitable type and design for the purpose intended and should be capable of maintaining within the working zone a temperature varying not more than + or . The nitriding process does not affect the physical state of the core if the preceding tempering temperature was 950oF or over. This method of case hardening is advantageous due to the fact that a harder case is obtained than by carburizing. Af ter the charge has been brought up to treating/soaking temperature all areas of the working zone shall be within the permissible temperature range specif ied for the steel/alloy being heat treated (See Table 2-3. a temperature varying not more than ±25oF (±14oC) from the required heat treating temperature. as cyanide vapors are extremely poisonous. HEAT TREATING FURNACES/BATHS. however.14oC (25oF) for the desired value. 2-45.T. The process involves the exposing of the parts to ammonia gas or other nitrogenous materials for 20 to 100 hours at 950oF. in some instances. or machining. be supplied by means of a forge or welding torch. Heat may. all decarburized metal must be removed to prevent f laking of the nitrided case. 2-7 .400oF to 1. Immediately af ter removal from the bath. The cyanide bath should be maintained at a temperature to 760oC to 899oC (1. type and construction for purpose intended. 2-46. 2-44. The use of a closed pot and ventilating hood are required for cyaniding. Heat treating furnaces are of many designs and no one size or type perfectly f ills every heat treating requirement. 2-47. with any charge. The case obtained in this manner is due principally to the formation of carbides and nitrides on the surface of the steel. This is accomplished by heating. followed by quenching. Protective and inert atmospheres shall be utilized and circulated as necessary to protect all surfaces of parts comprising the furnace load. 2-43. Steel parts may be surfacehardened by heating while in contact with a cyanid salt. HEAT TREATING EQUIPMENT. protective atmosphere. seldom used in connection with aircraf t construction or repair. Prior to any nitriding treatment. 1-1A-9 c. The work to be hardened is immersed in a bath of molten sodium or potassium cyanide from 30 to 60 minutes. Many engine parts such as cylinder barrels and gears may be treated in this way. the temperature should be carefully held to the lower limit of the range. CYANIDING. FURNACES. The size and quantity of metal to be treated and the various treatments required determine the size and type of furnace most suitable for each individual case. tinning of any surface will prevent it from being nitrided. When a part is to be only partially treated. and molten-lead baths. Equipment necessary for heat treating consists of a suitable means for bringing the metal to the required temperature measuring and controlling device and quenching medium. Nitriding is generally applied to certain special steel alloys. molten-fused salt baths.650oF). and cooling in still air. therefore. The heat treating furnaces/baths are of many designs and no one size or type will perfectly f ill every heat treating requirement.015 inch if heated for 50 hours. however. Cyaniding is. a rapid and economical method of case hardening. and may be used in some instances for relatively unimportant parts. The acceptable heating media for heat treating of steels are air. soaking until uniformly heated. a furnace is necessary. 2-42. will be the control document for heat treating steel material to be used on aerospace equipment. FURNACE TEMPERATURES SURVEY AND TEMPERATURE MEASURING EQUIPMENT. For distribution of test thermocouples. the furnace or bath temperature shall be allowed to stabilize at the potential test temperature. Furnaces/baths shall be equipped with suitable automatic temperature control devices. control. recording and controlling instruments shall be checked at regular intervals. whichever is greater. As a part of the inspection thermocouples should be closely inspected for condition and those severely deteriorated and of doubtful condition should be replaced. 2-49. The furnace control couples shall be corrected for any deviation from the standard electromative force (EMF) temperature chart as determined in calibration of the couples. The initial and succeeding (semi-annual and annual) surveys shall be performed with a standard production type atmosphere. The temperature for check shall be at working temperature with a production load. In the tempering furnaces. it will be necessary to review the involved specif ication or manufacturer’s engineering or design data for the appropriate heat information (temperature. times. Thermocouples shall be properly located in the working zones and adequately protected from contamination by furnace atmospheres by means of suitable protecting tubes. af ter any change is made that may affect operational characteristics. Af ter all the test thermocouples have reached the minimum of the heat treating range. The temperature of all test locations/thermocouples shall be recorded at 5 minute intervals. starting immediately af ter insertion of the test thermocouples in the furnace or bath.T. Heat Treatment of Steel. The initial survey shall be made at the highest and lowest temperatures of the furnace specif ied operating range. a minimum of 9 test thermocouples or 1 per 25 cubic feet. In case of conf lict the Military/Federal Specif ication will be governing factor or the conf lict will be negotiated with the responsible technical/engineering activities for resolution. 1-1A-9 NOTE Specification SAE-AMS-H-6875. whichever is greater. Reading shall be continued for 1/2-hour or more af ter furnace control thermocouple reads within 25oF of original setting. and semi-annually thereaf ter to assure conformance with temperature and control requirement previously cited. Periodic surveys may be made at a convenient temperature within the operating range.O. the required changes shall be made in the furnace and arrangements of the charge. 2-53. atmosphere. an annual survey will be acceptable. A survey shall be made before placing any new furnace in operation. 2-50. 2-52. shall be used for air furnaces except circulating air furnaces used for tempering only. The survey may be waived at the discretion of the authorized inspector or representative provided that the results from previous tests. If the test indicates that conditions are not satisfactory. The accuracy of temperature measuring. not exceeding 3 months or upon request of personnel in charge or authorized (Government) inspector or representatives. show that the temperature and control uniformity is within specif ied limits. see Figure 2-1. FURNACE CONTROL INSTRUMENTS ACCURACY. properly calibrated and arranged. The resulting temperature readings shall be within ±1. their maximum variation shall not exceed ±25oF (14oC) and shall be within the specif ied heat treating temperature range in accordance with Specification SAE-AMS-H-6875 or Table 2-3. 2-51. 2-48. The accuracy of the instrument shall be made by comparison tests with a standardized precision potentiometer type instrument of known (tested) accuracy used with a calibrated thermocouple. For all surveys. A minimum of 9 test thermocouples or 1 per 15 cubic feet. preferably of the potentiometer type to assure adequate control of temperature in all heat-treating zones. 2-54. etc). If instruments are replaced or not used for 3 months they shall be checked before use.0 percent of the temperature indications of the calibrating equipment. The test thermocouple shall be located approximately 3 inches from the installed furnace thermocouple(s). The locations may be surveys. Bath furnaces shall be tested by use of a minimum of 5 test locations or 1 per each 15 cubic feet. HEAT CONTROL. Where furnaces are used only for annealing or stress relieving. using suitable protected multiple or single brake test thermocouples. controlled if required. Where new alloys are involved. 2-8 Change 4 . with the same furnace or bath and same type of load. Temperature measuring and recording instruments used for controlling the furnace shall not be used to read the temperature of the test temperature sensing elements. shall be used. Number and Distribution of Thermocouples 2-9 . 1-1A-9 Figure 2-1.T.O. size and shape of piece to be treated. annealing and hardening where parts are not preheated. Temperatures required for hardening steel are governed by the chemical composition of the steel. parts of heavy cross section should be hardened from the high side of the given temperature range. Suitable tanks must be provided for quenching baths. preferably the potentiometer type. If the center of the section is more that 1/2-inch from the surface. ANNEALING. 2-62. and cooling in air or quenching in oil at approximately 27o to 66oC (80o to 150oF). hardness. handling equipment. SALT BATH CONTROL. The furnace must be brought to the proper temperature gradually. 1-1A-9 2-55. 2-56. Soaking Periods for Hardening Normalizing and Annealing (Plain Carbon Steel) DIAMETER OR THICKNESS INCHES 1 and less Over 1 through 2 Over 2 through 3 Over 3 through 4 Over 4 through 5 Over 5 through 8 TIME OF HEATING TO REQUIRED TEMPERATURE (APPROX) HOURS 3/4 1 1/4 1 3/4 2 1/4 2 3/4 3 1/2 TIME OF HOLDING (APPROX) HOURS 1/2 1/2 3/4 1 1 1 1/2 2-63. The quenching liquids commonly used are as follows: Water at 18oC (65oF). holding at this temperature for approximately the period of time given. temperature given. and grain structure obtained by hardening and the method of tempering. Temperature recording should be of the automatic controlling and recording type. previous treatment. Annealing consists of heating to the applicable temperature. therefore. It applies only to plain carbon and low alloy steels. QUENCHING TANKS AND LIQUIDS. INITIAL FURNACE TEMPERATURES. and the exact temperature should be determined by hardness or tension test for individual pieces. a lower tempering temperature should be used for sections thicker than 1 inch in order to obtain the required tensile strength. For parts of complicated design involving abrupt change of section or sharp corners. 2-64. HEAT TREATING PROCEDURES. unless the furnace atmosphere is such that undue deterioration of the thermocouples will not result. and Fish Oil. In normalizing.) Tempering consists of heating the hardened steel to the applicable temperature holding at this temperature for approximately 1 hour per inch of the thickness of the largest section. Commercial Quenching Oil. The bath will be checked at least once a month. HARDENING. This table is intended to be used as a guide only and should not be construed as being a mandatory requirement. SOAKING PERIODS. The temperature to be used for tempering of steel depends upon the exact chemical composition. 2-57. The f inal tempering temperatures should not be more than 111oC (200oF) below the tempering.T. TEMPERING (DRAWING. the temperature should be at least 260oC (500oF) below the working temperature. the tensile strength at the center will in general be reduced. NOTE Additional Heat Treatment information is discussed in Section IX. 2-58. 2-61. Table 2-1. The tempering temperatures given are only approximate. 2-59.O. Table 2-1 indicates in a general way the effect of size on the time for soaking. The period of soaking is governed by both the size of the section and the nature of the steel. The size of tanks should be suff iciently large to allow the liquids to remain approximately at room temperature. Generally. The bath composition shall be adjusted as frequently as necessary to prevent objectionable attachment of the steel or alloy to be treated and to permit attainment of the desired mechanical properties of the f inished product. the temperature in that zone of the furnace where works is introduced should be at least 149oC (300oF) below the working temperature at the time of insertion of parts of simple design. 2-60. and cooling in the furnace to a temperature not higher than 482oC (900oF). 2-65. Thermocouples should be placed in a suitable protecting tube. The steel 2-10 . The location of these tanks is very important due to the fact that insuff iciently rapid transfer from the furnace to the quenching medium may destroy the effects of the heat treatment in many instances. Circulating pumps and coolers may be used for maintaining approximately constant temperatures where a large amount of quenching is done. and are not approved for Air Force use. Parts may be cooled in the box or furnace to a temperature of approximately 482oC (900oF) then air cool. This treatment produces a coarse grain in some types of steel and may cause excessive distortion. This treatment leaves the alloy in a relatively sof t condition and it is then necessary to condition by heating and quenching. Hardness readings may then be taken on the tubing. will affect the corresponding relation between hardness and tensile strength. It applied only to the plain carbon and low alloy steels not to corrosion-resistant. the tests to determine the relationship between hardness and strength should be made on the actual part. followed by heating and quenching for case hardness. GENERAL. 2-70.O. Therefore. hardness tests may be employed using the equivalent hardness values specif ied in Table 8-3. Alloy may be quenched directly from the carburizing furnace. the following procedure may be used: Short lengths may be cut from the tube. SPECIFICATION CROSS REFERENCE. 1020 steel will require 1 to 3 hours at a carburizing temperature of 899oC (1650oF) for each 1/64 inch of case depth. Each of these methods is discussed in section VIII. Table 2-2 is a cross reference index listing the steel and alloy types and the corresponding Federal. Carburizing consists of heating the steel packed in a carburizing medium. 1-1A-9 may then be removed from the furnace and cooled in still air. The methods of hardness testing in general use are: the Brinell. CARBURIZING. The approximate relationship between the tensile strength and hardness is indicated in Table 8-3. Hardness testing is an important factor in the determination of the results of the heat treatment as well as the condition of the metal before heat treatment and must. to the applicable temperature and holding at this temperature for the necessary period of time to obtain the desired depth of case. Tempering temperatures listed with the individual steels in Table 2-3 are offered as a guide for obtaining desired tensile and yield strength of the entire cross section. 2-68. f irst for core ref inement. 2-67. 2-69. In making hardness measurements on tubular sections. The core treatment outlined above ref ines the grain as well as hardens. 2-11 . required. or the presence of decarburized or porous areas and hard spots. the Rockwell reading will be lower than indicated in the table for the corresponding tensile strength. This may be impractical because every tube size end wall thickness would have a different factor. Rockwell. TENSILE STRENGTH. but tension tests are impractical. stock material meeting the requirements of a military specif ication shall be used for all aeronautical structural items. valve. HARDNESS-TENSILE STRENGTH RELATIONSHIP. 2-73. holding at this temperature for period of time. correction factors must be determined and applied to the observed readings in order to compensate for the roundness and def lection of the tubing under the pressure of the penetrator. Hardness values should be within a range of two points Rockwell or 20 points Brinell or Vickers. be carefully considered in connection with this work. such as buff ing and plating. Vickers. and aeronautical material specif ications for the different conf igurations. in a closed container. Some of the specif ications listed in Table 2-2 are for reference only.T. Military. or tool steels. these surfaces must be adequately removed by grinding before measurements are made. and Shore Scleroscope. magnet. This table is to be used as a guide. As an alternate. Any process which affects the surface. 2-71. When a narrow range of hardness is required. removing from furnace and cooling in still air. A mandrel long enough to extend out both ends of the tube and slightly smaller in diameter than the inner diameter of the tube is then passed through the section and the ends supported in ‘‘V’’ supports on the hardness tester. Normalizing consists of heating the steel to the applicable temperature. Usually there is less distortion in f ine grain steels. Where two or more specif ications cover the same material. 2-72. For cylindrical parts of less than 1 inch in diameter. 2-66. The tensile strength-hardness relationship is quite uniform for parts which are suff iciently large and rigid to permit obtaining a full depression on a f lat surface without def lection of the piece. NORMALIZING. HARDNESS TESTING. When the physical properties are specif ied in terms of tensile strength. therefore. thus producing a hard case and a core hardness of Rockwell B67. Seamless/Welded 2-12 . Billets. Specification Cross Reference COMP/ALLOY DESIGN 1005 FORM/COMMODITY Rod. Welded Rivets Wire (Carbon) Strip (For Small Arms. Bullets) Blooms. steel welding (A/C application) Steel. Welding Rod and Wire (Welding Low Carbon Steel) AMS 5030 FEDERAL MILITARY MIL-R-908. Slabs Bars (General Purpose) Wire Sheet and Strip Sheet and Strip Sheet and Strip Sheet and Strip Tubing. Welding Electrodes. MIL-S-4174 Bars.T. 1016. C1 1 1008 MIL-S-4174 1010 MIL-S-16974 QQ-S-633 QQ-W-461 5047 5040 5042 5044 5050 5053 7225 QQ-W-409 MIL-S-13468 MIL-S-16788 C1 1 MIL-S-13852 QQ-S-698 QQ-S-698 QQ-S-698 MIL-S-11310 MIL-T-16286 C1 A MIL-E-6843 C1 E 6013 5031 MIL-E-6843 C1 E 6013 MIL-E-18193 ty 60 MIL-R-5632 C1 1 5060 QQ-S-633 (Comp C1015-C1019) WW-T-731 Comp A 1015. Seamless (Marine Boiler application) Electrodes. Welding Electrodes. aluminum coated low carbon. Billets. f lat. welding steel and cast iron. Blooms. rod and wire. sheet and strip. Slabs Steel Disks (For Deep Drawn Ammunition items) Tubes.O. 1017. Seamless Tubing. 1-1A-9 Table 2-2. 1018 and 1019 Bar (General Purpose) Bar and Billets Tube. T. Bars. Blooms.O. 1018 and 1019 (Continued) FORM/COMMODITY Tube. Billets. Slabs Tubing (Welded) Tubing Steel Disks (For deep drawn ammunition items) Sheet and Strip Tubing (Seamless and Welded) 5060 QQ-S-633 Comp C1015 QQ-W-409 (Comp 1015 1019 QQ-W-461 MIL-T-3520 MIL-S-13852 MIL-S-7809 QQ-S-640 MIL-S-16974 MIL-S-16974 QQ-S-633 MIL-S-3090 MIL-S-7952 5032 QQ-W-461 QQ-W-414 5045 QQ-S-698 1020 QQ-S-635 QQ-W-409 MIL-T-3520 MIL-S-11310 MIL-S-16788 C1 2 MIL-T-20162 Gr 1 MIL-T-20169 MIL-S-13852 QQ-T-830 Change 1 2-13 . Billets Blooms. Slabs Bars Sheet and Strip Wire (Carbon) Wire Wire (Book Binder) Sheet and Strip Plate (Carbon) Wire (Carbon) Tubing (Automotive) Bars Blooms.Carbon Wire (Carbon) Wire (Carbon) Tubing Steel Disks Plate. Specification Cross Reference .Continued COMP/ALLOY DESIGN 1015. 1017. Mechanical AMS FEDERAL QQ-T-830 MT1015 MILITARY Steel . Slabs 1020 Bars. 1016. Billets. 1-1A-9 Table 2-2. Sheet and Strip (See Corten) Sheet and Strip. T.Continued COMP/ALLOY DESIGN 1022 FORM/COMMODITY Bars and Forgings Plates (Up to 1″) Wire (Carbon) Steel Disk (For deep drawn ammunition items) Bars. Carbon (Bars. Mechanical AMS 5070 FEDERAL QQ-S-633 QQ-S-691. 1-1A-9 Table 2-2.O. C1 1 QQ-S-681. Billet. Billets. Bloom. Plate. Forgings. Bar. C1 2 MIL-S-11310 5075 5077 QQ-W-409 MIL-S-15083 C1 B MIL-S-13852 MIL-S-7952 QQ-S-643 MIL-P-20167 C1 C MIL-S-7809 6354 5080 QQ-S-633 (Bar) MIL-S-20145 Gr N MIL-P-20167 C1 A QQ-S-633 QQ-W-461 MIL-T-5066 MIL-T-5066 1025 Fittings Bars Tubing Tubing Castings Castings Bars Tubing. Blooms. Sheet and Strip (High Str) Sheet. Welded Wire Casting Steel Disks Sheet and Strip Tubing Plate Corten NAX AC 9115 1035 Plate. Seamless Tubing. and Tubings) Ingot Plate Bar Wire (Carbon) 2-14 . Slabs Sheet and Strip Tubing Tubing. Strip Steel. C1 A QQ-W-409 MILITARY MIL-S-11310 MIL-S-13852 MIL-S-16974 QQ-S-640 QQ-S-643 QQ-T-830 MIL-F-20236 ty 1 QQ-S-633 MIL-T-3520 MIL-T-5066 QQ-S-681. Specification Cross Reference . Tubes. Strip Forgings (Naval Ship Board) Plates and Disks (For artillery ammunition cartridge cases) Tubes AMS FEDERAL MILITARY MIL-T-20141 QQ-S-635 MIL-S-16900 5082 MIL-S-3289 QQ-S-691 C1 B QQ-S-691 C1 C QQ-S-741 Gr A QQ-W-409 QQ-S-640 MIL-S-19434. Seamless Plate and Disk Plates (Marine Boiler) Plates (Marine Boiler) Shapes. C1 1 MIL-S-3289 MIL-T-11823 QQ-S-633 QQ-S-635 QQ-S-681.O.Continued COMP/ALLOY DESIGN 1035 (Continued) FORM/COMMODITY Tubes Plate (Carbon) Forgings Tubes. Bar and Plate (Structural) Wire Sheet.T. Bars and Slabs 1045 Tubes (Welded) Bars Wire (Carbon) Ingots Plate Sheets. 1-1A-9 Table 2-2. Seamless Strip Strip (For ammunition cartridge clips) 1050 Bars Plate (Carbon) 2-15 . Strip. Specification Cross Reference . Billets. C1 1 QQ-W-409 MIL-S-11310 MIL-S-16974 MIL-T-4377 QQ-S-633 QQ-W-461 MIL-S-20145 Gr P QQ-S-635 QQ-S-640 MIL-S-303 MIL-S-3039 QQ-S-633 QQ-S-635 MIL-S-20137 1040 Bars Plate (Carbon) Castings Wire Bars Blooms. C1 C5 5085 QQ-S-681 QQ-T-880 MIL-S-20145 Gr R MIL-S-10520 QQ-S-633 MIL-E-18193 (Ty 201) QQ-S-633 MIL-S-16410 comp 3 QQ-W-428 Ty 1 and 2 MIL-S-2839 MIL-S-16788. and Slabs (For Forgings) Bars. Billets.T. Strip 1070-1075 Sheet. Billets. C1 C6 MIL-S-16974 MIL-S-10520 comp 3 QQ-S-640 MIL-S-8143 1055 Ingots Forgings (For Shell Stock) Bars Electrodes 1060 Bar Bars. Spring 5120 (1074) QQ-S-633 QQ-T-580 C1-W1-09 7240 5115 QQ-T-580 FF-W-84 C1 A QQ-S-633 MIL-S-12504 MIL-S-11713 comp 2 1080. (Galvanized) MIL-S-16788 C1 C8 MIL-W-6714 2-16 . Spring Blooms. Blooms. Springs. 1086. 1090 Bars Steel. Specification Cross Reference . Billets. Drawn Metal (Stitching. 1-1A-9 Table 2-2. Strip Wire. Seamless/ Welded AMS FEDERAL MILITARY MIL-S-16788. Billets. Castings Tubing. Spring Steel Tool Washers Wire Bars Steel. Slabs (For Forgings) Wire. Slabs Bars. Strip (SpringTime Fuse) Strip. Billets.Continued COMP/ALLOY DESIGN 1050 (Continued) FORM/COMMODITY Blooms. and Wire Wire. Blooms. Tool Blooms.O. Slabs Forgings Sheet. Slabs. Specification Cross Reference . Square and Flat for Forgings Strip Bars. Slabs Wire.16410 comp 1 1095 Bars Bars. Bars. Forging and Mechanical Tubing Bars Bars Forgings MIL-S-16124. Spring Sheet. Forging and Mechanical Tubing 2-17 . Billet and Slabs MIL-S-16788 MIL-S-46033 MIL-S-17919 MIL-S-16974 5010 1112 Steel. Carbon. C1 1. Carbon Spring. Slabs Steel Bars. Strip Wire (High Carbon) Sheet. comp A 5022 QQ-S-633 MIL-S-10520 5024 1137 Steel . Blooms.Carbon. Wire Wire. Bars.Continued COMP/ALLOY DESIGN 1080.Carbon. Comm Quality Wire. Bars Forging and Mechanical Tubing Bars 5010 5022 QQ-S-633 1117 Steel .O. Billets. Music AMS FEDERAL MILITARY MIL-S-16974 5110 5112 5132 QQ-W-470 QQ-S-633 QQ-W-428 MIL-S-11713 comp 3 QQ-W-470 5121 Strip 5122 Strip 7340 MIL-W-13604 MIL-S-7947 cond A MIL-S-7947 cond H MIL-S-8559 MIL-S.T. 1-1A-9 Table 2-2. Spring (For small arms application) Blooms. Strip Sheet. Strip Springs Wire. Billets. 1090 (Continued) FORM/COMMODITY Blooms. 1086. Round. Bars. Wire Bar Wire 4050 4130 Steel. Specification Cross Reference . Billets 3310 Bars Wire 3316 4037 Bars Bars. Tool Bars. Billets (For carburizing) 3140 Bars Wire (Alloy) Bars. Seamless AMS 5024 FEDERAL QQ-S-633 MILITARY MIL-S-43 MIL-S-16124.O. Forgings (A/C Quality) 2-18 .Continued COMP/ALLOY DESIGN 1137 (Continued) FORM/COMMODITY Bars Bars Tubing. Rods. C1 2 QQ-S-643 QQ-S-624 QQ-W-405 MIL-S-20145 QQ-S-624 QQ-W-405 QQ-S-629 QQ-S-624 QQ-S-629 QQ-W-405 MIL-S-20145 Gr V QQ-S-624 QQ-W-405 QQ-S-624 QQ-W-405 MIL-S-866 QQ-S-624 QQ-W-405 MIL-S-16974 QQ-S-624 QQ-S-405 MIL-S-1393 comp 2 6300 QQ-S-624 QQ-W-405 QQ-T-570 C1 1 6370 QQ-S-624 MIL-S-6758 MIL-S-7397 comp 1 2317 Bars Wire (Alloy) 2330 Ingots Bars Wire (Alloy) Tubing 2340 Bars Tubing Wire (Alloy) Ingots 2515 Bars Wire (Alloy) 3115 Bars Wire (Alloy) Bars.T. Blooms. 1-1A-9 Table 2-2. Seamless AMS 6350 6351 FEDERAL MILITARY MIL-S-18729 MIL-S-16974 6360 6361 6362 6371 QQ-S-626 QQ-S-627 QQ-W-405 QQ-S-624 MIL-T-6736 MIL-S-6731 Tubing. Plates (Commercial Grade) Tubing Bar. Bars. Rods. Forging Stock 6303 6372 6365 MIL-S-18733 MIL-T-6735 cond N MIL-T-6735 MIL-S-16974 . 1-1A-9 Table 2-2. XMDR-2. Welded Tubing. Seamless Bars. Seamless Tubing 17-22-A(V) 4137C0 Mellon 4140 Bar. Sheet Strip (A/C Quality) Bars. Forging.Alternate designation: Unimuch UCX2. Forgings. Seamless Tubing. Specification Cross Reference .O. Billets and Slabs Tubing. Sheet. Blooms. Steel.T. Strip Tubing. Billets Wire (Alloy) QQ-W-405 QQ-S-624 6882 QQ-S-624 QQ-S-626 Specif ication: MIL-S-5626 6381 MIL-S-16974 4150 Bar Bar (For Small arms Weapons Barrels) Bar (Special Bar for AF Bullet Cores and Shot) MIL-S-11595 MR MIL-S-12504 MR 2-19 . Blooms Tubing. Blooms.Continued COMP/ALLOY DESIGN 4130 (Continued) FORM/COMMODITY Plate. Mechanical Plate (Commercial Quality) Sheet. Sheet. Rocoloy. Strips Wire (Alloy) 4135 Bars Plate.2. MX . Sheet and Strip Bar. Nitralloy Type G. Mechanical AMS 6440 6441 FEDERAL MILITARY MIL-S-7420 Ladish D-6-A . Reforging Bar Bar. Forging Stock (Nitriding) 6470 Bar and Forgings MIL-S-6709. Forging and Mechanical Tubing Bars 6418 QQ-S-624 QQ-W-405 MIL-S-16974 MIL-S-21515 MIL-S-7108 6428 QQ-S-627 MIL-E-21515 QQ-S-624 6359 6414 6415 MIL-S-5000 MIL-S-8844 C1 1 64126475 6413 QQ-W-405 MIL-S-20145 Gr U QQ-S-624 MIL-E-8699 2-20 .T. Forging and Tubing Bar. Forging Tubing. Blooms. Billets 4335 (Mod) HyTuf 4615 Bars. Forging and Tubing Bar. 1-1A-9 Table 2-2. Plate and Sheet Wire (Alloy) Bars. Modif ied and ASTM-A355-57T C1 A Nitralloy 4330 Bars and Forgings Stock (Mod) Nitralloy 4337 Bars. Specification Cross Reference . Seamless Wire (Alloy) Ingot 4340 Plate.O. D-6-A-V . Rod. Nitralloy 135 Bar.Alternate designation. Plates.and D-6-A-C.Continued COMP/ALLOY DESIGN 52100 FORM/COMMODITY Bars. Forging. comp A Alternate designations. Sheets and Strips Bar. Forgings Tubing. Forging and Tubing Strip and Sheet Bar. 1-1A-9 Table 2-2.O. Blooms. Specification Cross Reference . Forgings. Blooms. Forging Wire Wire. Billets AMS FEDERAL QQ-W-405 MILITARY MIL-S-866 MIL-S-7493 QQ-S-624 QQ-W-405 MIL-S-16974 6312 6317 QQ-S-624 QQ-S-624C Bars QQ-W-405 MIL-S-18731 QQ-S-624 6448 6450 QQ-W-428 comp D MIL-S-16410 comp 4 MIL-S-20145 Gr Z 6455 7301 QQ-S-627 MIL-W-22826 6270 QQ-S-624 (Bar) QQ-W-405 MIL-S-866 MIL-S-16974 5333 (8615 mod) 6272 QQ-S-624 (Bar) QQ-S-624 QQ-S-627 MIL-S-18731 MIL-S-8503 MIL-S-46033 MIL-S-8503 MIL-S-7493 4617 4620 Bars Bars Wire 4640 Bars. Tubing Bars Bars Sheet and Strip 2-21 .T. Tubing Wire (Alloy) Bars. Billets and Slabs Castings 8617 Bars. Spring Bars.Continued COMP/ALLOY DESIGN 4615 (Continued) FORM/COMMODITY Wire Bars. Forgings. Billets Bars. Wire (Spring) Ingots Sheet. Billets Bars Bars and Forgings Wire (Alloy) 6150 Sheet. Strip Bars Bar Bars. Strip Wire 8615 Bars. Strip (Springs) Springs (Highly Stressed) Sheet. Sheet. Specification Cross Reference .T. Billets Slabs Plate (Commercial Grade) Wire (Alloy) Sheet. Tubing Plates (Commercial Grade) Sheet and Strip Wire Bars. Billets Slabs Plate Tubing. Billets AMS FEDERAL QQ-W-405 QQ-S-624 MILITARY 6274 QQ-S-626 QQ-S-627 QQ-W-405 MIL-S-8690 MIL-S-16974 MIL-S-18728 MIL-T-6732 QQ-S-624 6280 6281 6530 6550 6355 MIL-S-16974 QQ-S-626 QQ-W-405 QQ-S-627 MIL-S-6050 QQ-S-624 MIL-S-16974 QQ-S-626 MIL-T-16690 QQ-W-405 6535 6282 MIL-T-6733 cond N MIL-S-6098 MIL-T-6732 cond N MIL-T-6734 cond N MIL-S-6050 8630 Plate. Forgings. Strip (Hot Rolled) Bars. Seamless Tubing Wire (Alloy) 8735 Tubing. Strip Bars. (Mechanical) 2-22 . Blooms. 1-1A-9 Table 2-2. Blooms. Welded Sheet. Rods. Forgings 8640 Bars Bars. Forgings Tubing Tubing. Seamless Tubing.Continued COMP/ALLOY DESIGN 8617 (Continued) 8620 FORM/COMMODITY Wire Bars Bars.O. Blooms. Strip (A/C Quality) Tubing Bars Bars. Seamless Tubing. Strip. Forgings. and Reforging Stock Bars Bar Wire.O. rods. Strip 9262 Wire. 1-1A-9 Table 2-2.Continued COMP/ALLOY DESIGN 8735 (Continued) FORM/COMMODITY Tubing. C1 6 QQ-W-428 MIL-S-46033 QQ-S-624 QQ-S-627 6260 6265 QQ-W-405 6263 5358 5515 MIL-S-5059 QQ-S-624 (Bar) 9250 9620 Bars. bars and forging stock (A/C quality) Sheet. Forgings 6322 QQ-S-624 6325 6327 6358 6323 QQ-S-626 QQ-W-405 MIL-S-6049 cond C MIL-S-6049 MIL-S-6049 MIL-S-8844 C1 2/3 QQ-S-624 MIL-S-46033 QQ-W-474. Tubings Bar. Sheet and Strip Tubing. Forgings Plate. Forgings Bars Bars. Wire (Spring) Steel. Mechanical Plate (Commercial) Wire (Alloy) Bars. Strip and Plate Bars. Forgings AMS FEDERAL MILITARY MIL-S-6098 6357 6320 MIL-S-18733 MIL-S-6098 MIL-S-6098 8740 Bars.T. Rods. Plate (ST) 2-23 . comp E MIL-S-16410. Specification Cross Reference . Spring Bars. Forgings Bars. comp 5 MIL-S-17919. Rods. Spring Bar Bars Sheet and Strip 9310 Bars. Forgings and Tubing Wire (Alloy) 9315 Type 301 (30301) Bars Casting Prec Invest (S±) Sheet. Forgings Bar. Plate (Full H) Plate.O. Forging Bar Bar. Strip Shape Wire. Reforging Bars. Sheet.Continued COMP/ALLOY DESIGN Type 301 (30301) (Continued) FORM/COMMODITY Sheet. Forging 2-24 . Billets. Castings Wire. Strip Pins. Strip. Sheet. Annealed Castings Plate. C1 1 QQ-S-682 QQ-S-766 MIL-W-17481 7241 5640 5738 MIL-S-862 MIL-S-7720 5641 5642 FF-W-84 C1 C QQ-S-763 (60302) Steel. Forgings Sheet. Plate (1/2 H) Sheet. Specification Cross Reference . Helical 303 Bar.T. Sheet. Strip Plate. Strip. Sheet. Bar and Billets (Reforging Applications) Bars. Plate (1/4 H) Sheet. Cotter Rivets (18CR 8N:) Steel. Strip. 1-1A-9 Table 2-2. Strip Plate. Forging (Swaging) Bar. C1 1 5516 7210 7228 FF-P-386 Type C MIL-S-5059 MIL-S-5059 302 (30302) Bars (CD to 100000 tensile) Bars (CD to 125000 tensile) Bars. Stainless. Forgings MIL-S-5059 comp 302 MIL-S-5059 MIL-S-862 C1 302 MIL-S-7720 5358 QQ-W-423 MIL-S-17509. Strip Wire Lockwashers. (Spring Temper) AMS 5517 FEDERAL MILITARY MIL-S-5059 5518 5519 QQ-S-766 5688 5636 5637 QQ-W-423 comp 502 QQ-S-763 CL 303 QQ-S-763 C1 302 QQ-S-763. Precision Invest Castings. Strip Castings. Sheet. Forging Wire Tubing Bars. Plate 5522 5360 5361 5524 5573 5648 5698 QQ-W-423 5691 5649 QQ-S-763 MIL-S-7720 comp MCR QQ-S-766 MIL-S-867 (C1 III) MIL-S-5059 comp 316 316 Casting. Sand. Mechanical Tubing Bar Plate.T. Mechanical Tubing and Rings Sheet. Investment Casting. Sheet.Continued COMP/ALLOY DESIGN 304 FORM/COMMODITY Tubing Tubing Castings Plate. Forging (Free Machining) 2-25 . Strip Tubing. Forging. Strip Plate Plate. Tubing Wire. Seamless Tubing. Strip. Strip.O. 1-1A-9 Table 2-2. Forgings. Sheet. Centrifugal Sheet. Screen Wire Electrode. Welded AMS 5566 5567 FEDERAL MILITARY MIL-T-6845 MIL-T-8504 MIL-S-867 C1 1 MIL-S-4043 MIL-F-20138 QQ-S-766 5370 5371 5697 5647 QQ-S-763 5511 5639 5697 QQ-S-763 QQ-W-423 MIL-T-5695 QQ-S-763 5560 5565 5652 MIL-T-8506 MIL-S-8506 MIL-S-4043 MIL-S-7720 QQ-W-423 314 Bar. Bar. Forgings Tubing. Specification Cross Reference . Seamless Bar. Welded Bar. Plate Tubing. Forging. Sand Wire Bars. Coated. G347 MIL-T-8606 MIL-S-6721 Type CB + TA) (CB) MIL-T-6737. 1-1A-9 Table 2-2. Reforgings AMS FEDERAL QQ-W-423 MILITARY MIL-P-1144 MIL-S-862 5645 5510 QQ-S-766 5570 MIL-T-8606 T1. Forgings. Welded Drawn 2-26 . Seamless.O. Billets. T 321 MIL-T-7880 QQ-S-763 C1 321 MIL-S-6721. Sand Casting Tubing. Strip Tubing. Cotter Tubing. Sheet. Screen Pins. Flexible Wire.Continued COMP/ALLOY DESIGN 316 (Continued) FORM/COMMODITY Wire Pipe. Seamless Tubing. Welded Tubing. Sheet. Welded. Forgings. Welded. Sheet. Tubing Mechanical Plate. Tubing Castings Sheet. G321 MIL-T-8887 5576 5689 7211 5557 MIL-T-6737 QQ-S-763 MIL-T-8606 QQ-S-682 MIL-T-8808 5559 MIL-T-8606 7229 5646 QQ-S-763 C1 347 MIL-S-867 C1 II 5512 5363 MIL-S-17609 C1 II 5571 MIL-T-8606. Strip Tubing. Forgings Tubing Plate. Seamless Tubing.T. Strip Plate. Hydraulic Tubing. Seamless and Welded Bar. Hydraulic Tubing. Strip Casting. comp T1 321 Bar. Specification Cross Reference . Thin Wall 347 Tube Rivets Bars. Welded Bar. Type 1. Thin Wall Tubing. Strip Tubes. Forgings. Sheet and Strip (Ferrite Modif ied/ controlled) 5614 5609 5504 5505 QQ-S-766 C1 410 Change 1 2-27 . Welded Plate. Sheet. C1 2 MIL-R-5031 QQ-S-766 MIL-T-16286 MIL-T-8808 5362 5613 5612 QQ-S-763 C1 410 410 (51410) Bars. Sheet.Continued COMP/ALLOY DESIGN 347 (Continued) FORM/COMMODITY Tubing. Mechanical Tubing Plate. Hydraulic Tubing. Welded Bars. Seamless (Marine Boiler Application) Tubes. Type 347 MIL-T-7880 5556 5558 QQ-S-682 MIL-T-6737 QQ-S-763 MIL-S-6721 MIL-S-17509. Sheet. 1-1A-9 Table 2-2. Welded Tubing. Hydraulic Casting. Welding Plate. Strip Castings Rods. Flexible Tubing. Forgings. Sheet and Strip Plate. Mechanical Tubing Bars. Specification Cross Reference . Forgings Plate. Mechanical Tubing (Ferrite Controlled Modified) 410-MO 410-MOD 410 410 Bars and Forgings Bars and Forgings. Strip Tubing. sand and Centrif AMS 5575 FEDERAL MILITARY MIL-T-6737.O.T. Forgings Bars 416 (51416F) Bars Bars and Forgings Bars and Billets (Reforging) 420 Bars and Billets (For Reforging) Bars and Forgings (Free Mach) (51420) Bars and Forgings Bars Plate. Billets. C1 440A QQ-S-763. Precision Investment Bars and Forgings Bars and Forgings 2-28 . Seamless Tubing.T. Sand Bars. Forgings. Tubing Castings. C1 440C QQ-S-763. 1-1A-9 Table 2-2. C1 431 QQ-S-763 C1 416 Se (Bar) 414 Bars. Sheet and Strip Wire 431 Bars and Billets (For Reforging) Bars.O.Continued COMP/ALLOY DESIGN 410 (60410) FORM/COMMODITY Casting Investment Casting. Flexible 5591 MIL-T-7880 5615 QQ-S-763 C1 414 MIL-S-862 5610 5610 MIL-S-862 C1 6 MIL-S-862 C1 5 5620 5621 5621 5506 QQ-S-763 C1 420 QQ-S-766 C1 420 QQ-W-423 MIL-S-862 MIL-S-18732 5372 5682 5353 5630 5631 QQ-S-763. Sand Wire Bars Bars. Forgings 431 MOD 440 C 440 A Castings. and Billets (For Reforging) AMS 5350 5351 FEDERAL MILITARY MIL-S-16933 C1 I QQ-W-423 comp 410 MIL-S-861 MIL-S-862 (51410) Tubing. Specification Cross Reference . T. C1 440F MILITARY 17-4 PH Bar Castings . Forgings and Rings Bars (Up to 1 inch) Bars (Up to 1.5 inch) Bars (Up to 1 inch) Bars and Forgings 5720 5721 5722 5723 5724 5729 5538 19-9DX Bars.000 PSI) Castings . Investment Bar and Forging Plate.000 PSI) Castings . Sheet and Strip Plate. Sheet and Strip Change 1 2-29 . Specification Cross Reference COMP/ALLOY DESIGN 440 F 14-4PH 15-7 MO FORM/COMMODITY Bars and Forgings Castings. Sheet and Strip (125000TS. Hot rolled.Welding Castings . Welded 19-9DL Casting Sand (Solution Treated) Plate. Sheet and Strip Sheet and Strip (Precipitation Hardening) Bar and Forgings Tubing.Investment (Heat Treated 130. Sheet and Strip AMS 5632 5340 5657 5520 5643 5342 FEDERAL QQ-S-763. 1-1A-9 Table 2-2.Investment (Heat Treated) Electrode .Investment 5343 5344 5827 5355 5528 5530 5644 5568 5369 5526 5527 MIL-S-25043 17-7 PH Plate.5 inch) Plate. Stress Relieved) Bars (Up to 1.O.Investment (Heat Treated 150. Forgings and Rings Bars (Up to 1 inch) Bars (Up to 1. Covered (Armor applications) Bar Sheet and Strip (Cold rolled) Sheet and Strip (High Temp Annealed) Bar and Forgings Tubing. Coated Wire 5745 5540 5548 AM350 MIL-S-8840 5745 5554 5774 5775 5743 5368 5547 5549 5594 5781 5734 5735 MIL-S-8840 AM355 Bar Castings. 1-1A-9 Table 2-2.O. Forgings.5 inch) AMS 5539 FEDERAL MILITARY 5723 5724 5729 MIL-E-13080 19-9 MOD Electrode. Specification Cross Reference . Welding Electrode. Forgings. Seamless Wire.Continued COMP/ALLOY DESIGN 19-9DX (Continued) FORM/COMMODITY Plate. Mechanical Tubing Bars. Welding.T. Sheet and Strip. Coated Welding A286 Bars. (Hot rolled and Stress Relieved 125. Investment Sheet and Strip Plate (Solution Heat Treated) Plate (Equalized and Over-Tempered) Electrode.000TS) Bars. Mechanical Tubing and Rings 2-30 Change 1 . Forgings. Sheet and Strip Bars. Annealed Plate.T.Continued COMP/ALLOY DESIGN A286 (Continued) FORM/COMMODITY Bars. Sheet and Strip Bars. Mechanical Tubing and Rings (Sol Treated) Bars and Forgings and Mechanical Tubing (Annealed and Precip Treated) Rivets. Forgings.O. Investment Plate. Specification Cross Reference . Mechanical Tubing and Rings 5354 5508 5616 Inconel 600 Wire. Steel (Annealed 1650oF and partially precip treated) AMS 5736 FEDERAL MILITARY 5737 7235 Rene 41 Bars and Forgings (Solution Treated Bars and Forgings (Solution and Precip Treated) Plate Sheet and Strip (Solution Heat Treated) 5712 5713 5545 Greek Ascoloy Castings. Forgings and Rings Tubing. 1-1A-9 Table 2-2. Seamless 5687 5540 5665 5580 5542 QQ-W-390 MIL-N-6840 MIL-N-6710 MIL-T-7840 MIL-N-7786 42 Inconel Alloy X750 Sheet and Strip Change 1 2-31 . T. Alloy Prec Invest Sheet Bar and Forgings Wire HNM WASP Alloy Bars. Prec Invest Casting. Forging. Spring Temper Hastelloy C Castings. C1 12 MIL-S-17759 NONE NONE NONE MISC STANDARDS/SPECIFICATIONS .O. Forgings Hastelloy W Bars and Forgings Wire Hastelloy X Castings. Wire 5668 5698 5699 5388 5389 5530 5750 5755 5786 5390 5536 5754 5798 MIL-N-8550 Cond E JAN-W-562. No 1 Temper Wire. Sand Sheet Bar.Continued COMP/ALLOY DESIGN 42 Inconel Alloy X750 (Continued) FORM/COMMODITY Bars and Forgings AMS 5667 FEDERAL MILITARY Bars and Forgings Inconel X750 Wire. C1 2 MIL-N-18088 MIL-R-5031. C1 1 JAN-W-562.METAL PRODUCTS Steel: Chemical Composition and Hardenability Metal Test Methods Surface Passivation Corrosion Resistant Steel Parts QQP-35 MIL-STD-753 Fed Std 66 Fed Std 151 2-32 Change 1 . 1-1A-9 Table 2-2. Billet. Specification Cross Reference . Missile Space Vehicles and Associated Support Equipment and Facilities Preparation of Test Reports Marking of Aircraf t and Missile Propulsion System Parts. Hose and Tube Lines for Aircraf t. Specification Cross Reference . Nomenclature and Temper Designation for Magnesium Base Alloys Tolerances for Copper and Copper Base Alloy Mill Products Continuous Identification Marking of Iron and Steel Identification Marking of Aluminum Magnesium and Titanium Continuous Identification Marking of Copper and Copper Base Alloy Mill Products FED-STD-146 MIL-STD-775 MIL-STD-1247 MIL-STD-831 MIL-STD-841 MIL-STD-1233 MIL-STD-455 MIL-STD-453 MIL-STD-418 MIL-STD-410 MIL-STD-409 FED-STD-183 FED-STD-184 FED-STD-185 Change 1 2-33 .Continued COMP/ALLOY DESIGN FORM/COMMODITY AMS FEDERAL MILITARY X-Ray Standards for Welding Electrode Qualif ication and Quality Conformance Test Welds Identification of Pipe. 1-1A-9 Table 2-2.O. Fabricated From Critical High Temp Alloys Procedures for Determining Particle Size. Distribution and Packed Density of Powdered Materials Alloy Designation System for Wrought Copper and Copper Alloys Inspection Radiographic Mechanical Tests for Weld Joints Qualification of Inspection Personal Magnetic Particle Alloy.T. Continued COMP/ALLOY DESIGN FORM/COMMODITY AMS FEDERAL FED-STD-187 MILITARY Identification of Pressed Bonds. Seams and Joints Sheet Metal Tolerance for Aluminum Alloy and Magnesium Alloy Wrought Products Heat Treatment of Steels (Aircraf t Practice) Process for Steel Mill Products Preparation for Shipment and Storage Tolerances for Steel and Iron Wrought Products FED-STD-245 SAE-AMS-H-6875 MIL-STD-163 FED-STD-48 2-34 Change 4 .T. Specification Cross Reference .O. 1-1A-9 Table 2-2. Forms. Low Carbon. See supplement data for chemical symbols. Because of the carbon range this metal has increased strength and hardness but reduced cold formability compared with the lowest carbon group. It f inds wide application where carburizing is required. Typical applications are bolts. COMPOSITION RANGE C% Mn% 0.6 P% 0-0.23 Mn% 0. Low Carbon.18-0. Low Carbon. water quench.05 Fe% Balance FORM-SPECIFICATION. air cool.04 S% 0-0. Anneal: 1650oF.American Gas Assoc Class 302.22-0.3-0. For 1650 use 38NH3 & 24CH4 *Gas .2 P% 0-. COMPOSITION (CHEMICAL) AND CHARACTERISTICS OF VARIOUS STEEL AND STEEL ALLOYS.5 HardCase Depth ness Cool 0. GENERAL HEAT TREATING TEMPERATURES.3-0. and other items where cold formability is the primary requisite. Quench in oil (minimum hardness) Water. etc. Anneal: 1600oF. COMPOSITION RANGE C% Mn% 0. Anneal: 1600oF. This material is not generally considered a carburizing type. See Specification Table 2-2.7-0. See Specif ication Table 2-2.05 Balance FORMS. HEAT TREATMENT Normalize: 1650o-1750oF Anneal: 1600o-1650oF Harden: 1650o-1700oF Quench with water.04 S% Fe% 0-.23 0. With this steel no martensite is formed and tempering is not required. 1025. Low Carbon steel of this grade is used for manufacture of such articles as safety wire.05 Fe% Balance FORMS.3-0. HEAT TREATMENT 2-35 . See Specif ication Table 2-2.04 S% 0-0. Hardening: 1575o-1650oF. water or brine quench. it is sometimes used in this manner for larger sections. 1020. cold rolled 68000.13-18 Mn% 0. certain nuts. 1010. automotive parts. etc.05 Fe% Balance FORM-SPECIFICATION. This steel is readily welded by common welding FORMS-SPECIFICATIONS. Tensile: 130. 1-1A-9 2-74. furnace cool. This steel is similar in content and heat treatment requirements to 1020. pipe f langes. furnace cool. Harden: 1650o-1750oF. COMPOSITION RANGE C% Mn% Si% 0. cable bushings and threaded rod ends. Heat treatment is frequently employed to improve machinability.5 2. See specifications Table 2-2. oil.000 psi. use 35NH3d 25CH4 generator gas*.13 0. COMPOSITION RANGE C% 0. it should not be selected where strength is required. 1015.T.04 S% 0-0. bearing races.019 0.08-0.6 P% 0-0. air cool. water quench. cam shaf ts. This material is similar in content and characteristics to 1010. quench in water. or where greater case hardness is needed. Of low tensile value. HEAT TREATMENT Normalize: 1700oF.04 S% 0-0. cool in still air. or brine.5 Fe% Balance Normalize: 1700oF. machinery.28 0.018 62 59 OQ OQ Draw 350 350 For 1560F.000 psi. Tensile strength: hot rolled 67000. cold rolled 80000.3-0. Carburize: 1600oF. oil. Welding is easily accomplished by all common welding methods. Typical applications are case hardened roller chains. CARBO-NITRIDING Temp Time 1560 1650 2. and Brine (maximum hardness). HEAT TREATMENT Normalize: 1650o-1750oF. Yield strength: hot rolled 45000. HEAT TREATMENT Normalize: 1600o-1700oF. Carburize: 1650o-1700oF. It is suitable for welding and brazing. COMPOSITION RANGE C% 8-0.O. See Specification Table 2-2. Yield: 78. electrical equipment. brine.6 P% 0-0. Low Carbon.6 P% 0-0. Tempering: 250o-400oF is optional. 1022. furnace cool.10 0-0. Carburize: 1550oF to 1650oF. however. Harden: 1525o-1600oF. tools and springs.000 psi. cold rolled 79. use low hydrogen electrodes E6015 (thin gauges) and E7015.000 psi. Tensile strength.1-0. cold rolled 92. 30 minutes to 6 hours. furnace cool.32-0.30-1.25-0. annealed or normalized 67.6-0.055 0. 1-1A-9 methods. clutch pedals. furnace cool. Anneal: 1550oF. 1 hour per 1″ of section. 1035. Temper: 1100o-1150oF. but in the annealed or normalized condition it is stronger than plain carbon steel.25 Cu% Mn% 0.6-0. Suitable heat treatment is required to permit machining. COMPOSITION RANGE C% 0. quench in water or oil.25-0.T. Moderate strength is maintained with high toughness up to approximately 800oF. CA-25. Temper: 1150oF for 70.500. Medium Carbon. respectively.15 FORM-SPECIFICATION.05 Ni% 0-0. For heliarc welding use drawn f iller wire of MIL-R-5032.04 Cu% 0-0. Anneal: 1550o-1625oF. yield 80. See Specification Table 2-2. This steel is not heat treatable. Spheroidize: 1250o-1375oF. FORM Sheet.9 P% 0-0.000 psi.75 Ni% 0-0.65 Stress relief anneal 900o-1150oF. but hot formability is excellent. Low Alloy.04 S% 0-0. using the same methods applied to plain carbon steel. Typical applications are gears.000 psi annealed). yield 48. air cool. This steel is selected where higher mechanical properties are needed since it may be further hardened and strenghtened by heat treatment or by cold work. 1 hour per inch of maximum section thickness. Perform spot welding by pulsation method for heavier gauges. use post heat cycle for lighter gauges. For gas welding.) Weldability is very good by all common welding methods.6-0.37-0. is easily formed. hot rolled 54.000 psi. Typical room temperatures: tensile 76. water or oil quench. HEAT TREATMENT SPECIFICATIONS AMS 6354 6440 HEAT TREATMENT Anneal: 1625o-1650oF.8 Zn% 0. welded and machined.05 Fe% Balance Si% 0.04 Cr% 0. 2-36 . air cool. yield 53. f lywheel rings. This alloy cannot be hardened. (Tensile 79.000 and yield 85. furnace cool.15 Fe% Balance HEAT TREATMENT Normalize: 1650oF. ASTM A233 or E60 electrodes are recommended for shielded arc welding.000.000 psi. Normalize: 1650o-1675oF.9 Fe% Balance Mn% 0.12 Cr% 0.5-0. plate.05 Fe% Balance FORM-SPECIFICATION. Harden: 1500o-1575oF. This alloy is readily welded by the usual gas and arc methods with complete freedom from air hardening. Yield strength.000 psi.000 psi. Weldability is excellent and it machines better than carbon steels of the same tensile strengths. air cool. cool in still air.000 psi. Wire. 1040. COMPOSITION RANGE C% 0-0. For tensile 125. crank shaf ts. See Specification Table2-2. NAXAC9115 Low Carbon.2-0.04 S% 0-0. hot rolled 85.5 S% 0-0.25 P% 0-0.2 P% 0-0.17 Mo% 0. CORTEN Low Carbon. COMPOSITION RANGE C% Q 0. (Preheat) Temper at 900oF for 100. Anneal: 1575o-1650oF. Tensile strength. air cool. HEAT TREATMENT Normalize: 1575o-1650oF.35 Si% 0. Normalize: 1575o-1650oF. Stress relief 1150oF. annealed or normalized 47.000 psi temper at 700oF.15-0. Low Alloy. this alloy is 4-6 times more resistant to atmospheric corrosion than plain carbon steel. In addition. high strength welding rods such as ASTM A251. This material is usually in the stress relieved condition.5-0. This steel may be resistance welded to itself or other resistance weldable ferrous alloys. Cold formability is poor. are recommended. Medium Carbon is selected where intermediate mechanical properties are needed and may be further hardened and strengthened by heat treatment or cold work. Brinill 183-201.000 psi. yield strength.44 0. For arc welding.38 Mn% 0. to obtain tensile 100.O.05-0. (Brine or caustic may also be used for quenching. strip. COMPOSITION RANGE C% Mn% Si% 0.000 psi.07-0.75 P% 0.25 S% 0-0.000 psi.9 0-0. 000 psi.6-0. 1055. High Carbon.6-0. Temper: 1100oF for tensile 100.000 psi tensile. Medium Carbon.65 0. 1-1A-9 1045. air cool.000 tensile. Medium Carbon. High Carbon.000 for yield.04 Fe% Balance FORMS-SPECIFICATIONS. water or oil. 1060.000 psi.6-0. HEAT TREATMENT Normalize: 1575o-1675oF. Forgings such as connecting rods. Anneal: 1550o-1600oF.6-0.55 0. Temper: 1250oF for 100. 1070.000 psi tensile.43-0.9 P% 0-0.000 psi.46-0. axle shaf ts and tractor wheels are fabricated from this steel.5 Mn% 0. 99. furnace cool for maximum softness. axles. Welding by the thermit process is satisfactory. as well as for manufacture of springs. High Carbon.05 Fe% Balance FORMS-SPECIFICATION. COMPOSITION RANGE C% Mn% 0. Temper: 1025oF for 139.000 tensile.05 Balance FORMS-SPECIFICATION. This is a medium carbon type steel with high mechanical properties which may be further hardened and strengthened by heat treatment or by cold work.09 P% 0-0. air cool.000 yield.O. water or oil quench. Temper: 1250oF for 100. Harden: 1450o-1550oF.) Harden: 1475o-1550oF. etc. Temper: 1125oF for 130. In addition this alloy is used for f lat springs and wire form as coil springs. Harden: 1475o-1550oF.000 psi. See 1055 for application and characteristics COMPOSITION RANGE C% Mn% 0. HEAT TREATMENT Normalize: 1550o-1650oF. furnace cool (Tensile 90. Temper: 1100oF for 125. steering arms. COMPOSITION RANGE C% 0.05 Fe% Balance FORM-SPECIFICATION. Temper: 1025oF for 125. Temper: 700oF for 150. 1080.000 for yield.000 psi tensile. COMPOSITION RANGE 2-37 .05 Fe% Balance FORM-SPECIFICATION. air cool. 1050. HEAT TREATMENT Normalize: 1525o-1625oF.65-0. HEAT TREATMENT Normalize: 1525o-1625oF.04 S% 0-0. yield 65.9 P% 0-0. quench.000 annealed. 75. 96.000 for yield.000 psi tensile. Harden: 1450o-1550oF. 1080 are in same category) have similiar characteristics and are primarily used where higher carbon is needed to improve wear characteristics for cutting edges. Harden: 1450o-1550oF.9 P% 0-0. Hot Working Temperature: 1550o-1650oF. HEAT TREATMENT Normalize: 1550o-1650oF.75 0. See 1055 for application and characteristics. 1050oF for 125. retard cooling rate to prevent hardness. Anneal: 1550o-1575oF. Temper: 1250oF for 100. yield 95. Temper: 1000oF for 150.04 S% 0-0. Not recommended for welding.60 0. 90.000 tensile.000 psi annealed). See Specification Table 2-2.000 tensile.9 P% 0-0. Anneal: 1450o-1525oF. furnace cool. air cool. See Specification Table 2-2. See Specification Table 2-2.55-0. Not recommended for welding. oil or water quench. Anneal: 1500o-1575oF (Tensile 104. 600oF for 150.T. Temper: 1000oF for tensile 125. 80. yield 54. Hot formality is very good at 1550o-1650oF. See 1055 for applications and characteristics. water or oil quench. COMPOSITION RANGE C% Mn% 0.000 psi. COMPOSITION RANGE C% Mn% 0.50-0.04 S% 0-0. Application is similar to 1045. High Carbon.000 yield. See Specification Table 2-2. Anneal: 1500o-1575oF. 114.000 tensile. Steels of this type (1060.04 S% Fe% 0-0.04 S% 0-0. air cool.000 psi tensile.6-0. Not recommended for welding.000 psi tensile. The high carbon content of this steel causes diff iculties in arc or gas welding processes. 1070.000 psi tensile.000 yield 50.000 yield. Temper: 925oF for 149. See Specification Table 2-2. water or oil quench (Preheat). nuts.000 tensile.000 yield.9-1. It is easy to machine and resulting surface f inish is excellent.5 P% 0-0. Case hardness 65 RC. Speroidize for maximum sof tness when required. In addition these steels are used for f lat spring applications and in wire form as coil springs. furnace cool to 900oF and air cool. 1137. HEAT TREATMENT Normalize: 1650oF. It has good brazing characteristics but is diff icult to weld except with the low hydrogen electrode E6015 (AWS).08-0. 1095.35-1. Temper at 350oF Case depth 0.41-0.04 0. furnace cool (Tensile 68.32-0.9 P% 0-0. See Specification Table 2-2.3 P% S% Fe% 0-0. Anneal: 1425o-1475oF (Tensile 98.39 1.000 psi annealed) furnace cool. COMPOSITION RANGE C% Mn% P% S% Fe% 0. This steel is intended for those uses where easy machining is the primary requirement. COMPOSITION RANGE C% 0. 129. air cool.9 0.000. quench oil.7-0.13 Balance 2-38 . but not for parts subjected to severe stresses and shock.05 Fe% Balance screws. 103. Temper: 800oF for 176.000 psi tensile. Tensile strength cold drawn 83. air cool. Anneal: 1425o-1475oF. HEAT TREATMENT Normalize: 1550o-1650oF. Temper: 900oF for 178. Temper: 1100oF for 143. COMPOSITION RANGE C% Mn% P% S% Fe% 0-0.T. 1112.000 psi tensile.O.04 S% 0-0.000 yield. To reduce annealing time.000 psi tensile. HEAT TREATMENT May be surface hardened by heating in cyanide at 1500o-1650oF.000 yield.04 S% 0-0. FORM-SPECIFICATION. Temper: 1200oF for 129. See Specification Table 2-2. See Specification Table 2-2. Free Cutting.000.000 psi annealed) Harden: 1450oF. 1117.05 Fe% Balance FORM-SPECIFICATION. Harden: 1425o-1500oF. Pot Cool Reheat to 1450oF.000 psi annealed).04 0.12 0.000 yield.000 yield.3-0. Temper: 800oF for 200. air cool.000 yield. Temper: 1100oF for 146.65 0-0. HEAT TREATMENT OIL QUENCH Normalize: 1550o-1650oF. quench in water SINGLE QUENCH AND TEMPER Carburized 1700oF for 8 hours.0-1.6-0. yield 66. Carbon (Free Cutting Steel).000 psi tensile. Anneal: 1475o-1525oF (Tensile 120.045. 113.000 yield. See Specification Table 2-2. Quench in water.13 Balance FORM-SPECIFICATION. followed by single or double quench and draw. tempering is optional. 88. Tensile strength hot rolled bars 65. Preheat and soak at 1500oF to 1650oF and quench in oil or water. 96.000 tensile. It is suited for fabrication of small parts which are to be cyanided or carbonitrided and may be oil quenched af ter case hardening heat treating. which result in some sacrif ice of cold forming properties. This and similar grades are widely used for parts for bolts.23 Balance FORM-SPECIFICATION. Free Cutting.000 yield.000 yield. Anneal: 1575oF.000. Temper: 1100oF for 145.16-0. weldability and forging characteristics.000 tensile. Harden: 1425o-1550oF (oil quench).07-0. High Carbon. Temper: 600oF for 184. 138.000 psi.75-0.13 max 0.88 0.03 Mn% 0. It is characterized by a higher sulphur content than comparable carbon steels.08-0. 1-1A-9 C% Mn% 0. WATER QUENCH Normalize: 1550o-1650oF. 87. This steel is used as the standard for rating the machinability of other steels. 150. See 1055 for applications.000 psi tensile. Temper: 600oF for 213. COMPOSITION RANGE C% 0.2 Mn% 1. yield 52.000 psi tensile. quench with water. Carbon. 113. This material is used where a combination of good machinability and uniform response to heat treatment is needed. Harden: 1450o-1550oF. air cool. nuts. Temper: 900oF for 150.000. reheat to 1450oF to 1550oF.000 psi.2 0.000.000. furnace cool. Nickel Alloy. COMPOSITION RANGE C% Mn% 0. yield 80. Anneal: 1450o-1600oF.000 psi.000 psi. Temper: 975oF for tensile 125.04 0.000 psi 2340. Harden 1525o-1575o. but has greater strength. See Specification Table 2-2.75 Fe% Balance P% 0-0. Temper: 850oF for tensile 125.000 psi 124. 105.000 psi.000 psi yield. OIL QUENCH Temper: 1025oF for tensile 100.35 3. preheat.000 psi 150. Temper: 650oF for tensile 150. yield 100. TYPICAL STRENGTH OF OIL QUENCHED Temper: 1100oF for tensile 100.38-0.000. turnbuckles. Temper: 750oF for tensile 150. HEAT TREATMENT Normalize: 1600o-1700oF.000 psi.000 psi. Harden: 1400o-1550oF. HEAT TREATMENT Normalize: 1600o-1700oF.000 psi. yield psi 83.04 S% Si% 0-0. Anneal: 1425o-1600oF. 132. See Specification Table 2-2.8 Ni% 3. WATER QUENCH Temper: 1100oF for tensile 100. yield 100. Temper: 900oF for tensile 140. air cool.000 psi tensile. air cool Anneal: 1500o-1550oF Harden: 1375o-1525oF Carburize: 1650o-1700oF.000 psi.000 psi.000 psi tensile.04 0. 2515.43 0.000 psi.000 psi. yield 90.9 P% 0-0. COMPOSITION RANGE C% Mn% P% S% Si% Ni% Fe% 15-0.000 psi yield. yield 90.000 psi tensile. f ittings and other pressure containing parts intended principally for low temperature parts. yield 50. This is a heat treatable steel which develops high strength and toughness in moderate sections. It is used in highly stressed bolts.75 FORM-SPECIFICATION.04 0. See Specification Table 2-2. These specif ications cover steel castings for valves. HEAT TREATMENT Normalize: 1600 -1700 F.2-0. TYPICAL STRENGTH OF WATER QUENCHED Temper: 1100 F for tensile 105. yield psi 124. o o o 2330.000 psi. both in composition and response to heat treatment.6-0. This steel may be welded by common welding procedures. 1-1A-9 FORM-SPECIFICATION. temper at 250o-300oF. 164. This metal is similar to 2330.2-0.000 psi. f langes. Tensile strength: 85. Nickel Alloy. Temper: 700oF for 178.25-0.000 psi.O.2-0. Quench with oil. yield psi 100.25-3. COMPOSITION RANGE C% Mn% 0.25 Balance FORM-SPECIFICATION.6 0. Temper: 825oF for tensile 125. It is an oil hardening steel.000. Temper: 800oF for 182.000 psi.000 psi. Temper: 875oF for tensile 125. oil or water quench.35 Ni% 3. Harden: 1400o-1500oF. quench in oil. studs. cool in air. Anneal: 1400o-1500oF.4-0. See Specification Table 2-2.04 S% Si% 0-0.000 psi in annealed condition.28-0.7-0.000 psi. This steel is quite similar to SAE 2512 and 2517. Nickel Alloy.000 psi.35 FORM-SPECIFICATION. furnace cool. Temper: 1200oF-1250oF for tensile 100. 2317. yield psi 88. Nickel Alloy.000.T. etc. HEAT TREATMENT Normalize: 1600oF. yield psi 83.000 psi yield. COMPOSITION RANGE 2-39 .33 0. WATER QUENCH 700oF 900oF 1100oF 190. Temper: 1100oF for 125.04 0.000 psi. yield psi 108. 0il.000 psi.000 psi annealed). Nickel Chrome Alloy. for 8 hours. Temper: 1200oF for tensile 125. See Specification Table 2-2. COMPOSITION RANGE C% 0.13 Cr% 1. HEAT TREATMENT Normalize: 1550o-1700oF Anneal: 1475o-1550oF (Tensile 94. Temper: 700oF for 165. surface hardness combined with high and uniform properties when heat treated.25 P% 0-0. yield 80. It is commonly used in case hardened gears. yield 106.17 0.6 Ni% 4. HEAT TREATMENT Normalize: 1600o-1700oF.11-0. Temper: 900oF for tensile 125.75-5. 1-1A-9 C% Mn% 0. yield 125. This steel has execeptionally high hardenability and is well suited for heavy parts which must have high. yield 178.000.05″. oil quench. air cool.2-0.25-3. Temper: 700oF for tensile 152.08-0.5 Mn% 0. leaf and coil springs and hand tools. COMPOSITION RANGE C% 0.45-0. See Specification Table 2-2.52-0.2-0.000 psi.75 Mn% 0. 3115.95 P% S% Si% 0-0.000 psi. pinions.000 psi. yield 66. yield 86. oil quench.000 psi.05-1.45 P% 0-0.04 0.25 Fe% Balance FORM-SPECIFICATION.8 Balance FORM-SPECIFICATION. See Specification Table 2-2.Chromium Alloy. Temper: 900oF for 138.18-0. shaf ts.35 3.0-1. WATER QUENCH Temper: 1100oF for 116. 125.78 S% 0-0.000 psi. 3310. yield 142. Temper: 300oF for tensile.04 0.12-0. Molydenum Alloy.2 Si% 0.6-0.000 psi. HEAT TREATMENT Normalize: 1625o-1725oF Anneal: 1550o-1600oF Harden: 1425o-1525oF.000 psi.4-1.37-0. Temper: 1200oF for tensile 104.37-0.75 S% 0-0.6 P% 0-0. This steel is used for such parts as gears. This is a medium deep hardening steel capable of developing good strength and toughness when oil quenched. furnace cool to 700oF. Temper: 700oF for Tensile 200. Temper: 1000o for Tensile 14. Cool Slowly Carburize: 1700oF. temper 300oF.T.048 Cr% 0. yield 125.000 psi. COMPOSITION RANGE C% 0.000 psi.04 0-0.4-0. with oil.5-0. Effective case depth 0. Harden: 1475o-1550oF. Steel Nickel Chromium Alloy. etc. oil quench. It is similar to Krupp Nickel Chromium except it contains more nickel.O. Anneal: 1475o-1575oF. Temper: 800oF for Tensile 184.04 S% Si% 0-0. reheat to 1500oF. See Specification Table 2-2. HEAT TREATMENT Normalize: 1650o-1750oF Anneal: 1500oF Quench: 1425o-1525oF.000 psi. 4037. Nickel .37 Mn% 0. air cool.35 FORM-SPECIFICATION.63 Ni% 1.058 Fe% Balance Cr% Fe% 0. PSI.000 psi.000.35 Fe% Balance 3140.45 Ni% 1.025 Si% Ni% 0.000 psi. Quench: 1500oF-1550oF. CORE PROPERTIES 3115 Box cooled 1425oF 3120 3115 Reheated 1475oF 3120 3115 Oil Quenched 1525oF 3120 DRAW TEMP 300oF 300oF 300oF 300oF 300oF 300oF TENSILE KSI 125 155 125 155 125 155 YIELD KSI 88 115 86 115 86 110 FORM-SPECIFICATION.000 psi. yield 105. for tensile 170.000 psi.000 psi.2-0.000 psi.000. COMPOSITION RANGE 2-40 .000 typical for 1/2″ diameter rod. 000 psi annealed).35 S% 0-0. Cool down 20oF per hour to 1100oF.39 Mo% 0.000 psi tensile strength).75-0.0-1.000.2-0.4 Cr% 0. AMS6303 Bar. furnace cool. air cool. 1 inch diameter have tensile strength 87. Normalize: 1600oF.5 Ce% 0-0.6-0. Spherodize: 1400o-1425oF.000 psi.95 0-0. HEAT TREATMENT Harden (austenitize): 1550o-1600oF.2-0.04 Cr% 0. Temper: 850oF for 180. quench in oil. This alloy may be welded by any of the commercial methods in use. 2-41 . yield 122. furnace cool.08-0. hold for 1 hour per inch of thickness. forging stock. Annealed: 1525o-1585oF (tensile 80. 1 hour.3 Mn% P% S% Si% 0.7-0. Temper: 1150oF for tensile 132.5 0. Harden: 1550o-1625oF. hold at this temperature 1 hour for each inch of section thickness. Temper: 975oF for 150. yield 141.9 0-0.25 FORM-SPECIFICATION. It forms and welds readily.95 P% 0-0. etc. Alternate designations are Unimach VC X 2.75 P% S% Si% 0-0. COMPOSITION RANGE C% 0.3 Cr% 1. a temperature of 600oF is generally used. SAE Steels: 8630 and 8730 have similar characteristics.98-1. It is used in turbine rotors.500. Typical usages for this material is in the manufacture of gear shaf ts axles.T. Chromium .000 psi. Temper: 1100oF for 125. hardness BHN 311-321. Machining characteristics are similar to 4140. COMPOSITION RANGE C% 0. cool in air. Anneal: 1450oF. All sections should be so placed as to provide access of air to all surfaces. A welding rod corresponding to 17-22A(S) is available.55-0.000 yield strength.15-0. for each inch of thickness. 6 hours have tensile strength 142.000. See Specification Table 2-2.15 Fe% Balance HEAT TREATMENT Normalize: 1600o-1700oF. quench in oil.35 Cr% 0. air cool.6-0. 1-1A-9 C% 0.9 0. Austenitize Castings:1600o-1650oF.04 FORM-SPECIFICATION. water quench.25-0.2 Mn% 0. This is a high strength.32-0. Post heating or stress relief is recommended.6 S% 0-0.04 FORM-SPECIFICATION. Normalize: (cast) 1900oF. Temper: 1050oF for 150.Molydenum Alloy.4-0. COMPOSITION RANGE C% 0. Temper: 950oF for tensile 163. 4135. Temper: 1025oF for tensile 151.000. Larger sections may be fancooled in order to accelerate cooling.39-0. 4137CO.25 Fe% Balance Ni% Si% 0-0.2 Co% 0. oil quench.000 psi. furnace cool. forging. 17-22A(V).O. HEAT TREATMENT Anneal: 1500o-1600oF.15-0.04 0.05 0.75-1.000.000 tensile psi. yield strength 126.23 Mn% 0.8-1. MX2.C. yield 57.000 tensile psi. and Rocoloy. Oil Quenching requires prior heating to 1750oF.25 Mn% 0.35 Ni% 0-0.000. in which high temperatures are encountered for short periods. 6-12 hours. air cool. 67.35-0.04 0-0. HEAT TREATMENT Normalize: 1700o-1850oF. Chromium Molydenum Alloy.26-0. machine tool parts. quench in oil. Normalize: (wrought) 1600o-1700oF. Annealed bars. furnace cool.800. When pre-heating is required depending upon size of section and type of welding procedure.04 0-0. heat resistant steel with a 1000 hour rupture strength of 1100oF (30.000 psi range.35 Fe% Balance Temper: 1100oF for 125.000-240. 4130. and for components of guided missiles. Temper: 1225oF for 100.95-1.6-0. for oil quench 1575o-1625oF.000 psi.3-0. Structural (Ultra High Strength) Low Alloy. Hardening: 1550o-1650oF. COMPOSITION RANGE C% 0.4 Mo% 0. yield 159.2-0. then air cool. This ultra-high strength steel has yield strength in the 230.79 Mo% 0. A.04 Si% 0.1 hour. Pancake forgings normalized at 1800oF + tempering at 1225oF. Harden: 1550oF.5 Mn% Mo% 0. Anneal: 1525o-1575oF.000 tensile psi.000. See Specification Table 2-2.75 Fe% Balance V% P% 0. It was developed for use in high performances solid rocket motor cases.000. 000 to 220. Stress relieve af ter welding 1250oF.18 . 30 minutes minimum.00 0.000 HEAT TREATMENT Normalize: 1600o-1650oF (air cool) minimum 1 hour.48-0. This metal is used for such items as gears.33 0. SPECIFICATIONS TYPE 4140 AMS 5336 5338 6378 6379 6381 6382 FORM Precision Investment Castings Precision Investment Castings Bars Bars Heavy Wall Tubing Bars. Temper 4 hours to obtain desired strength.2-0. 4 hours.43 0.000 psi 950oF . 2-42 .000 psi 1075oF . This steel is 4330 improved by the addition of vanadium. oil or salt quench at 400oF. wire.28-0. It can be nitrided.000 yield 116. This steel is widely used where the higher strength and higher hardenability of 4340 is not required.000 psi 1175oF .05-0.35 S% 0-0. 4150. CHEMICAL COMPOSITION C% Mn% Si% P% Si% Cr% 0. 950o to 110oF. fast cool to 1235o-1265oF.O. axles. oil quench Temper: 1200oF for tensile 128.00 Ni% 1.10 Fe% Balance SPECIFICATIONS: None FORMS: Sheet. air cool.25 Fe% Balance FORMS-SPECIFICATIONS.000 psi 725oF . Double temper 540o-560oF for two consecutive 2 hour periods with intermediate cooling to room temperature.160. Austenitize: 1700oF for sections less than 1/2 inch 1725oF for sections larger than 1/2 inch. shaf ts. 750o to 950oF.12 Mo% 0. It is highly shock resistant and has better welding characteristics than higher carbon steels. Intermediate stress relieve to restore ductility of formed parts. air cool. air cool.015 Anneal: 1550o-1600oF furnace cool.16 P% 0-0. Spheroidize: Anneal: 1420o-1460oF. connecting rods.14-0. and is primarily used heat treated to a tensile strength between 220 and 240 KSI.35-0. oil quench. Resulting hardness RB95 maximum.19 Fe% Balance V% 0.75-1. 1250oF for 10 minutes. Harden: 1550o-1600oF 30 minutes. 30 minutes. 4 hours.8-0.000 to 160.000 to 140.012 Si% 0.2-0. 20 minutes minimum to 1 hour maximum per inch thickness.38-0.35 Fe% Balance HEAT TREATMENT Normalize: 1600o to 1700oF.00 Mo% 0.000 psi 850oF .53 0. forging. Temper: 200 to 220 KSI. Full anneal at 1525oF to 1575oF furnace cool or cool in ash or lime.040 0-0.040 0. oil quench 75o to 140oF.35 0. Austenitize: 1550o to 1600oF 15 minutes per inch thickness.80-1.000 to 200.100.180. Medium Carbon Chromium . Stock MILITARY COMPOSITION RANGE C% Mn% P% S% Si% Cr% 0. air cool.040 mx 0-0. Chromium-Molybdenun. C% Mn% P% S% Cr% 0.0 0-0. MIL-S5626 HEAT TREATMENT Normalize: 1550o-1650oF Anneal: 1450o-1525oF Harden: 1475o-1525oF. 4140.25 Si% 0.0 0-0. Temper: 220 to 240 KSI.04 0.120.15-0.50 V% 0. pistons. plate. See table below. pins.T.1 Mo% 0.75-1.Molybdenun (Nitriding Grade).140.000 to 180. HEAT TREATMENT Normalize: 1750oF.000 Temper: 1100oF for tensile 150.20-0. See Specification Table 2-2.75-1.040 mx 0. Maximum time in salt 12 minutes. strip. 2 hours.0. hold 14 to 24 hours. DRAW TEMPERATURES 1300oF . Spheroidize: 1400o-1425oF furnace cool. 4 hours. Forgings. bar. Temper: 180 to 200 KSI.22-0.040 0.000 psi SAE 4330 V Mod. Forgings.97-1. Weldability characteristics are good using the Tungsten-arc-inert-gas process.65-2. Temper: normalized condition for machinability 1250oF maximum.000 yield 135. 600o to 750oF.35 0. springs. 1-1A-9 Mo% 0.200.75-1. 04 Fe% Balance LADISH D-6-A. Tubing. air cool. High Carbon.75 1. Steel ultra high strength (Nitriding Grade). then temper to desired hardness. The Rockwell hardness at various temperatures is listed below: Temper: Temper: Temper: Temper: Temper: 400oF. Low Alloy High Strength. This process produces a case of extreme hardness without appreciably changing core tensile strength or yield strength. It is also readily machined. RC28 Anneal: 1500o-1550oF.000 psi. 30 minutes. Available in most wrought forms and forgings.3 0. This steel is used for anti-friction bearings and other parts requiring high heat treated hardness of approximately Rockwell C60. toughness and good wear resistance qualities. This alloy is suitable for hot work die applications and structural material in aircraf t and missiles. at 10oF per hour. It may readily be welded and cold formed in the annealed or spheroidized condition.2-0. air cool + 600oF temper. Austenitize: 1550o-1575oF.T. Rods. COMPOSITION RANGE A1% C5 Cr% Mn% Mo% Si% 0.7 0. Temper: 300o-1275oF. TYPE LADISH D-6-A FORM Condition UP TO 1″ THICK BAR Vacuum remelt by consumable electrode process.O.0 0.000 521000. Stress relieve: 1000o-1250oF one to two hours. Bar. Normalize by slowly heating to 1790o-1810oF.1 1.35 0-0.43 1. HEAT TREATMENT Normalize: 1650o-1700oF air cool Anneal: 1250o-1340oF hold 5 hours. furnace cool. COMPOSITION RANGE C% Cr% Mn% Mo% Ni% Si% V% Fe% 0. Tensile Yield 282.025 Fe% Balance FORMS-SPECIFICATIONS. See Specification Table 2-2.4 0. None.000 has excellent toughness.4-1. Spheroidize: Slow cool (about 5oF per hour) following austenitizing by extended heating at a temperature near the ACM point or by isothermal transformation at 1275oF following austenitizing. Harden: Quench in water from 1425oF-1475oF or quench in oil from 1550o-1600oF. HEAT TREATMENT SPECIFICATIONS TYPE NITRALLOY 135 MOD AMS 5470 FORMS Plates.000 Temper: 800oF for tensile 200.6 0. RC55 800oF. FORMS.46 1.000 yield 186. 6 hours.2-0.38-0. oil quench.4 P% 0-0. hold 8 hours. At strength levels below 220. Sections 1 inch or less in cross sections may be air cooled. Heat to 1430o-1460oF. Af ter nitriding it may be used where high resistance to abrasion and mild corrosion resistance are required. High Chromium Alloy. cool down at 50oF per hour to 1000oF. RC40 1200oF. Austenitize: 1700o-1750oF.45 0. Normalize: 1600o-1650oF.025 0-0. It also can be temper straightened.000 psi 255.04 S% 0-0. forgings stock.5-0. RC48 100oF. It may be heat treated to strength levels up to 300. air cool. This alloy is well suited for case hardening by nitriding.3-1. Normalize 1650oAC 1550oF.95-1.000 psi Nitralloy 135 Mod.0 0.3-0.000 yield 163. MILITARY MIL-S6701 HEAT TREATMENT Anneal: 1450oF. time and temperature depend on hardness desired.55 0. Oil quench sections less than 2 inches thick. Cool to 1320oF at 10oF per hour. 1-1A-9 Temper: 950oF for tensile 180.000 psi it is suitable for elevated temperature applications below 900oF.05 Balance SPECIFICATION. Cool to 1250oF at furnace rate and air cool.22 0. COMPOSITION RANGE C% Cr% Mn% Si% S% P% 0.95-1. air cool.25-0.8 0. It is best machined in the spheroidized annealed condition. Change 1 2-43 . Temper: 1000o-1300oF 1 hour minimum per inch of thickness. and at 240. 30 minutes. RC60 600oF. 000 to 280. 4615. oil quench. welded or brazed parts before austenitizing. furnace cool or cool in ash o o HEAT TREATMENT Normalize: 1675o-1725oF Anneal: 1575o-1625oF Harden: 1425o-1550oF oil quench. hold 8 hours.000 psi unless specif ically approved by design engineer.2-0.4%. 183.45-0. Temper: 550oF for 234. To heat treat for regular machining. maximum 0. water quench sections greater than 3 inches temper 1200oF. oil quench sections less than 3 inches. Tempering range is limited to 400o-600oF preferably no higher than 550oF.7-0. Stress relief parts af ter straightening.35 1.65-2.000. 1 hour of maximum thickness. Austenitize 1475o-1575oF. 6 hours minimum.000. See Specification Table 2-2.0 Mo% Fe% 0. Carburize: 1425o-1550oF 2-44 . 194. 2 hours. Temper: 900oF for tensile 190.000. 4337. Steel Nickel Molybdenum Alloy. yield.04 0.04 0-0.000 psi 90.000-280. yield. etc. Temper: 725oF for tensile 220. This is a high grade carburizing steel for use where reliability and uniformity are required.000 psi yield.85 0. Spheroidize Anneal: 1425oF.54-2.35 0-0. TYPE NITRALLOY 135 MOD FORM Condition BAR 1725oF. 191.000.000 psi In welding the major problem to avoid is loss of aluminum and chromium in the weld area.000 psi yield. machining.9 Ni% 1.04 0. Temper: 500oF for 235.000 psi tensile. which require strict control. normalize condition for improved machinability 125oF maximum. 2 hours per thickness. Temperature should not exceed tempering temp or reduce the tensile strength below 260. This alloy is easily welded by conventional methods using low hydrogen electrode of similar composition. Temper: 400oF for 239. Harden: 1475o-1550oF. the loss of which would prevent subsequent nitriding.000 psi 110.04 0-0. 193. Anneal: 1475o-1575oF. air cool.000 psi 1 1/2 to 3 inches 3 to 5 inches or lime. 142. 4340 Steel Nickel . oil quench.43 0. Normalize.3 Balance FORMS-SPECIFICATIONS.000 psi tensile and subsequently subjected to grinding. 15 minutes for each inch of thickness.000 psi 100.18 0.35%.13-0. good strength. 176. 5 hours.000 psi tensile this steel has been found superior to other common low alloy steels as well as some of the recently developed more complex low alloy steels. No welding shall be performed on this alloy heat treated above 200.000 psi. by special processes.Chromium Molybdenum Alloy.T. Austenitize: 1575o-1625oF.38-0. Cool af ter austenitizing. then heat to 1200oF (maximum 1250oF) for 15-20 hours. LESS THAN 1 1/2 inches 135.2-0. furnace cool or air cool. COMPOSITION RANGE C% Mn% P% S% Si% Ni% 0.000 psi 85. Parts heat treated to 260.000. Resulting hardness should be 229-248 BHN. COMPOSITION RANGE C% Mn% Si% P% S% Cr% 0. It can be heat treated to strength values within a wide range.65-0. 1-1A-9 (NOTE: Temper 50oF minimum above nitriding temperatures). The carbon content of 4337 is minimum 0. machining or straightening should be tempered to 350o-400oF.000. Temper: 1100oF for tensile 150. Temper: 400o-500oF for tensile 260.000 yield. Nitride: 930o-1050oF. 200.000 psi tensile. then furnace cool to 1210oF.000 psi yield. These two alloys are similar except that carbon content differs slightly. Temper. normalize or austenitize.0 Mo% 0.000 psi yield. 4 hours minimum.000 psi tensile.3 Fe% Balance SIZE DIA Tensile Yield 125. HEAT TREATMENT Normalize: 1600 -1700 F. At 260.O. high hardenability and uniformity are characteristics.2-0. It possesses fair formability when annealed and may be welded. Temper: 600oF for 230.000 psi tensile.65 0-0.2-0. 6152. (5) Temper: 450oF. piston pins.04 0.000 psi. Chromium Vanadium Alloy. Steel Nickel Molybdenum Alloy. spline shaf ts.1% Vanadium. (3) Temper: 450oF. Steel Nickel Molybdenum. (3) Reheat: to 1500oF (4) Quench: in agitated oil. Temper: 1000oF for 140 to 160.2-0. (Tensile psi 90.2-0.8 0-0. Anneal: 1500o-1600oF. Spheroidized annealed to 183-241 BHN = 45% 8615. hand tools. (3) Reheat: 1500oF.000 psi. It may be used for average size case hardened automotive parts such as gears. oil quenched. (5) Temper: 300oF.04 0-0.075. Temper: 1200oF for 100.65 0-0.0 Fe% Balance and small distortion in heat treatment. See Specification Table 2-2. differing only in the amount of Vanadium. reheat to 1425o-1475oF quench in oil. Its hardenability characteristics lie between that of plain carbon steel and the high alloy carburized steel. Typical usages are for f lat springs under 1/8 inch thick. agitated oil.38-0.075. 2-45 .2-0. crackshafts.O. (4) Quench: in agitated oil. cold formed.2-0.065 Case hardness: RC59 4640. spline shaf ts. (1) Carburize: 1700oF for 8 hours.000 psi. It is also used for valve springs. Temper: 900oF for 160 to 180. COMPOSITION RANGE C% Mn% P% S% Si% Ni% 0. (2) Pot cool. etc.0 Mo% 0. (1) Carburize: at 1700oF for 8 hours. furnace cool. 1-1A-9 Where case hardening is paramount.04 0-0.17-0. etc. Temper: 800oF for tensile psi 210.35 1. and for coil springs over l/2 inch diameter with same heat treatment. (2) Pot Cool.9 0-0. Steel-Ni-Cr-Mo Alloy. 4620. This steel has excellent machinability at high hardness levels. FORM-SPECIFICATIONS. oil quench.000 psi annealed. Case hardness: RC62 Recommended practices for maximum core toughness: Direct quench from pot. Case depth: 0.65-2. Alloy 6152 contains a minimum of 0.24 0. piston rods.04 0. and drawn at 725o-900oF to 44-48 or 48-52 RC.000 yield psi 137. and 1/8 inch and over hot formed.7-0.35 1. (2) Quench: in agitated oil. Case depth: .3 Fe% Balance FORMS-SPECIFICATIONS.04 0. HEAT TREATMENT Normalize: 1600o-1750oF Anneal: 1450o-1550oF Quench: 1450o-1550oF.0 Mo% 0.6-0. and machine parts. See Specification Table 2-2.000 psi.53 0. It is generally employed for partial stress relief and improved resistance to cracking from grinding operation. These two steels are essentially the same.06 Case hardness: RC58 Single Quench and Temper: (1) Carburize: 1700oF for 8 hours. Tempering 250o-350oF is optional. Temper: 1100oF for tensile psi 150. Its application is primarily gears. HEAT TREATMENT Normalize: 1625o-1750oF.000 psi. Temper: 1100oF for 120 to 140. oil quench. (2) Quench: in agitated oil. COMPOSITION RANGE C% Mn% P% S% Si% Ni% 0.000 yield 58. COMPOSITION RANGE C% Mn% P% S% Si% Cr% 0.) Harden: 1550o-1600oF.48-0.2-3. Temper: 800oF for 180 to 200.T. pump parts.1 V% 0. This is a medium hardenability case steel. This is a triple alloy case-hardening steel with medium hardenability.43 0. Recommend practice for maximum case hardness: Direct quench from pot.000 psi.000 psi.000 yield psi 194.45-0. Case hardness: RC62 Single Quench and Temper: (1) Carburize: 1700oF for 8 hours.35 0.8-1. (3) Temper: at 300oF Case depth: 0. 6150.000 psi.65-2.15 min Fe% Balance HEAT TREATMENT Normalize: 1650o-1750oF Anneal: 1550o-1600oF Quench: (High temperature) 1550oF Quench: (Low temperature) 1425oF Carburize: 1650o-1700oF. Case depth: 0.04 0-0. Temper: 700oF for 200 to 220. 9 0-.4-0.2-0.T.35 0.6 0.6 Mo% 0.9 0-0. at about 100. Harden: 1475o-1575oF.4-0.7 Cr% 0. tensile 2-46 . HEAT TREATMENT Normalize: 1650o-1725oF Anneal: 1575o-1650oF.7-0. Ni-Cr-Mo-Alloy. HEAT TREATMENT Normalize: 1550o-1650oF.35 0. (1) Carburize: 1700oF for 8 hours.3 0.4-0. See Specification Table 2-2.7 Cr% 0.076.04 0-0. Anneal: 1575o-1625oF. (2) Quench: in agitated oil. (3) Temper: 450oF.04 0.25 Fe% Balance FORMS-SPECIFICATIONS.4-0.2 0.13-0. CARBURIZING: For maximum case hardness: Direct quench from pot. Anneal: 1500o-1550oF (Tensile 90. oil quench. It is classed as medium hardenable. (2) Pot cool.35 0.2-0. Direct quench from pot.15-0.6 Mo% 0. See Specification Table 2-2. Case depth: 0. Case depth: 0.15-0. HEAT TREATMENT Normalize: 1600o-1750oF. engine pins.075. and its air hardening af ter welding.23 0. (2) Pot cooled. Steel Ni-Cr-Mo Alloy This steel has characteristics very similar to 4130.7 Cr% 0.4-0.18-0. gears etc. Anneal: 1575o-1650oF.04 0-0.04 0. but develops somewhat greater strength.28-0.050 Case hardness: RC58 Single Quench and Temper.2-0. (5) Temper: 450oF. Steel Ni-Cr-Mo Alloy.075 Case hardness: RC64 Recommended practices for maximum core toughness.15-0.4-0.25 Fe% Balance FORMS-SPECIFICATIONS.33 0. 1-1A-9 It is primarily used for differential pinions. HEAT TREATMENT Psuedo-Carburize 1650o-1700oF. COMPOSITION RANGE C% Mn% P% S% Si% Ni% Cr% 0.04 0. Case depth: 0. Case hardness: RC61.9 0-0. 8620.04 0.000 psi.7-0. Normalize: 1650o-1725oF. reheat 1550oF. box cool. COMPOSITION RANGE C% Mn% P% S% Si% Ni% 0.2-0.6 Mo% 0. transmission gears. Harden: 1474o-1575oF Carburize: 1700oF for 8 hours.4-0. Single Quench and temper: (1) Carburize: 1700oF for 8 hours.7-0. This steel is similar to 8615 and 8617 though stronger.25 Fe% Balance FORMS-SPECIFICATIONS.000 psi.15-0. This steel is very similar to 8615.15-0. 8630. (1) Carburize: 1700oF for 8 hours. (3) Reheat: to 1550oF.500 psi. See Specification Table 2-2. COMPOSITION RANGE C% Mn% P% S% Si% Ni% 0.7-0.000 psi yield 72. (4) Quench: in agitated oil.000 psi yield strength. It is used for aircraf t engine mounts. (5) Temper: 300oF.04 0-0. It is also used in the heat treated condition as chain. See Specification Table 2-2. (3) Temper: 300oF.18 0. cam shaf ts and for good core properties with high surface hardness af ter case hardening. Temper: 300oF for tensile 100.4-0.000 psi yield 94. 8617. Case depth: 0. (3) Reheat: to 1500oF. COMPOSITION RANGE C% Mn% P% S% Si% Ni% 0. (1) Carburize: 1700oF for 8 hours.9 0-0.6 Mo% 0. oil quench. (2) Quench: in agitated oil. It is used for ring gears. Case hardness: RC64. Draw at 300oF Tensile: 128.25 Fe% Balance FORM-SPECIFICATIONS. (4) Quench: in agitated oil.04 0-0. and other aircraf t parts due to good properties when normalized in light sections.O. transmission gears. tool bits. oil quench. joints. Temper: 725oF for tensile 220. It is similar in characteristics to 8630 and 8640 FORMS-SPECIFICATIONS.000 psi yield.2 Cr% 0. Temper: 1100oF for 145.04 1. spline shaf ts. knuckles. See Specification Table 2-2 . yield 66. Anneal: 1525o-1575oF Harden: 1575o-1625oF quench in agitated oil.3 Fe% Balance FORMS-SPECIFICATIONS. piston etc. 130.4-0. oil hardening type.000 psi yield.000 psi yield. rods.2 Cr% --Fe% Balance FORMS-SPECIFICATIONS.43 0. Steel Ni-Cr-Mo.04 0-0.000 psi tensile. HEAT TREATMENT Normalize: 1550o-1650oF.000 psi.04 0-0. 180. reamer bodies.55-0.4-0. drill collars. 4140 has higher strength and ductility and slightly better machinability.4-0.4-0. Temper: 800oF for tensile 210.8-2.35 0. Typical uses. yield 127. 9262. shapes. HEAT TREATMENT Normalize: 1575o-1625oF.4 Fe% Balance FORMS-SPECIFICATION. 205.15-0. Temper: 900oF for tensile 190. yield 107.000 psi.000 psi.2-0.000 psi.000 psi.04 0-0.2-0.4-0. 4140.000 psi yield strength.04 0.65 0. Steel Ni-Cr-Mo.000 psi C% Mn% P% S% Si% 9262 0.04 0-0.6 Mo% 0.000 psi Temper: 800oF for tensile 170. COMPOSITION RANGE C% Mn% P% S% Si% Ni% 0. aircraf t engine studs. tubing COMPOSITION RANGE C% Mn% P% S% Si% Ni% 0. This metal is used for shapes. yield 93. constitutes the only chemical variations in these alloys. tubing. etc.1-0.000 psi.7 Cr% 0.04 0.33-0.65 0. Temper: 700oF for 200.7 Cr% 0. Harden: 1500o-1575oF.04 0-0. These are similar alloy spring steels.4-0. heavy duty bolts. 8640.0 0-0. oil or water quench.000 psi.0 0-0. aircraf t engine bolts.65 -0.04 1.000 psi. axles. propeller shaf ts. Temper: 1000oF for 150. Anneal: 1500o-1575oF (Tensile 103.000.T.38 0.0 0-0.000 psi.3 o C% Mn% P% S% Si% 9261 0.35 0. Typical applications are coil and f lat springs.38-0. Temper: 900oF for tensile 149.000 psi tensile.75-1. core drills.000 psi. COMPOSITION RANGE C% Mn% P% S% Si% Ni% 0.25-0.55-0. Harden: 1475o-1575oF.000 psi annealed) Harden: 1500o-1575oF (Quench in agitated oil) Temper: 1100oF for tensile 160.000 psi tensile. 184. yield 183.O.75-1. 2-47 . COMPOSITION RANGE C% Mn% P% S% Si% 9260 0.0 0-0. The quantities of chromium in each.8-2.2-0.2-0.000 psi tensile.25 Fe% Balance 8740.000 psi.7 Cr% 0. Temper: 1100oF for tensile 131.2-0.0 0-0.04 0-0.000 psi Temper: 775oF for tensile 200. Temper: 700oF for 220.75-1. See Specification Table 2-2. Harden: 1525o-1600oF Oil quench. yield 152. Temper: 800oF for 200. Steel Silicon.8-2. furnace cool. yield 198.000 psi. See Specification Table 2-2. 8735.000 psi yield strength.04 1. 1-1A-9 60. HEAT TREATMENT Normalize: 1600o-1650oF.000 annealed). chisels.6 Mo% 0. Temper: 1200oF for tensile 119.000 psi tensile. bolts. This steel is similar to It may be satisfactorily used for axles.75-1.25 Fe% Balance Fe% Balance o HEAT TREATMENT Normalize: 1575 -1625 F Anneal: 1525o-1525oF.0 0-0.55-0.38-0.75-1.7-1. etc.43 0. See Specification Table 2-2.35 0. 140. 9261.6 Mo% 0.04 0. Steel Ni-Cr-Mo.2 Cr% 0. 9260. etc. Anneal: 1475o-1575oF. Single quench and temper: (1) Carburize: 1700oF for 8 hours. full anneal. See Specification Table 2-2. 2-2. This is a high hardenability case steel. HEAT TREATMENT Anneal: 1950o-2050oF. Cool to 800oF within 3 minutes maximum. possesses superior corrosive resistance.045 0-0.7 0-0. cold work should be followed by stress relieving at 400o-800oF. (3) Temper: 450oF. COMPOSITION RANGE C% Mn% Si% P% Cr% Ni% S% 0.047 inch Case hardness: RC62 Single Quench and Temper: (1) Carburize: 1700oF for 8 hours. Case hardness: RC54. air cool. (2) Quench in agitated oil. yield 280. furnace cool. Recommended practice for maximum case hardness: Direct quench from pot. This alloy can be hardened only by cold work. It is inferior in strength to 301. Case depth: 0.039 inch.025 0.4-0.25 0-2. yield 144.O.1 hour per inch thickness. 36 to 8 hours maximum respectively.35 2.0-8. Maximum tensile strength. (1) Carburize: 1700oF for 8 hours. yield 192.04 17. 1/2 to 2 hours. 1-1A-9 Temper: 1100oF for tensile 165. however.0 Fe% Balance FORMS-SPECIFICATIONS.08-0.05 Fe% Balance FORM-SPECIFICATION.000 psi. Case depth: 0.0 0-0.15 Fe% Balance Type 301. (3) Reheat to 1450oF.T. Steel Austenitic Stainless.047 inch. Steel Austenitic Stainless. COMPOSITION RANGE C% Mn% P% S% Si% Ni% 0. HEAT TREATMENT The heat treatment and resulting strength is similar to that recommended for type 301. Temper: 600oF for tensile 325.000 psi.000 psi. Type 303. water quench. Full anneal is mandatory when. (2) Pot cool. Anneal: 1475o-1575oF.0-19.55 Cr% 1. FORMS-SPECIFICATIONS.000 psi.025 0-0. (4) Quench: in agitated oil. both the case and core have high hardenability. 1/2 hard 150.0 0-0. Type 302.0 0-1. (3) Reheat: to 1450oF.15 0-2. However the presence of these elements 2-48 . (5) Temper: 300oF. except that the temperature range for annealing type 302 ranges between 1925o-2075oF. Case hardness: RC59. This alloy is similar to Type 301 in composition and characteristics.7-0.13 0. (5) Temper: 450oF.000 psi. Case depth: 0. exposed to corrosive media. These varieties of the 18-8 austenitic stainless family contain additions of sulphur and selenium for the purpose of improving machining characteristics. For best results. 9310.0 0-0.03 Cu% 0-0. (4) Quench: in agitated oil.45 Mo% 0. or alternately 600oF. To relieve the elastic characteristics and increase the compressive yield strength of cold worked conditions.0-19.03 17.0 0-1. HEAT TREATMENT Normalize: 1625o-1725oF. 400o-800oF. Temper: 900oF for tensile 214. (3) Temper: 300oF. such as hot chlorides.08-0. full hard 185. (2) Quench: in agitated oil.0 6. which vary only slightly in chromium and nickel and contain no other metallic alloying element. Type 303Se.000. which may lead to stress corrosion cracking. Steel Austenitic Stainless.047 inch Case hardness: RC62. This type of steel is used particularly for carburized parts having thick sections such as bearing races.000. This alloy may be strengthened to an exceptional degree by cold work. etc.2-0.0 Ni% 8. 1/4 hard 125. heavy duty gears etc. Steel Ni Cr-Mo (Electric Furnace Steel). To obtain maximum core toughness: Direct quench from pot.000 psi.000 psi.95-3. It is generally used in the annealed conditions COMPOSITION RANGE C% Mn% Si% P% S% Cr% 0.0-1.0-10. (2) Pot cool. Case depth: 0. See Specification Table 2-2. This steel belongs to the sub-family of 18-8 steels. since it is a high alloy. (1) Carburize: at 1700oF for 8 hours. Af ter forming in order to prevent stress cracking. See Specification Table.08-0. 1-1A-9 tend to decrease formability and corrosion resistance. Type 303 Se is superior to 303 in these respects.04 19.18 17. 2-49 .0 1.50 P% 0.0 Balance Max 0. To restore ductility af ter embrittlement has occurred. It possesses high resistance to scaling and carburizing and is used for parts and welded assemblies requiring corrosion and oxidation resistance to 2000oF. Steel-Austenitic Stainless. air cool up to 0.0 8.0 11.T.35 19.0 1.04 Mn% 1.04 0.0 0.0 10. 1/2 hour per inch of thickness.0 0. These metals are available as castings under the designations CF-8 and CF-3 respectively. This is a non-heat-treatable stainless steel generally used in the annealed condition. Steel Austenitic Stainless.03 2.12 Cr% Cu% 23.15 2.50 19. 10 minutes.0 1. This alloy can only be hardened by cold work.0 0. The cast form of 303Se is also known as CF-16F. Stress relief and best corrosion resistance to high temperatures properties is achieved by f inal annealing at 1900oF minimum.0 0.17 0.08 2.0-22.75 0. Castings: 2000o-2100oF. 30 minutes minimum. Bars. cool to 800oF maximum within 3 minutes.0 1. Welding is not generally recommended.5 18.04 0. This alloy may be hardened only by cold work.12 17.0 10.0 0. See Specification Table 2-2. forgings: 1900o-1950oF. anneal 1900o-1950oF for 10-60 minutes.03 20. Sheet.5 0.35 C Mn Si P S Cr Ni Mo Cu Iron TYPE 304 PERCENT MIN MAX 18.0 Balance 0. depending on section thickness.064 thickness.08 carbon (maximum) and type 304L with 0.0 HEAT TREATMENT Anneal or solution treat: 1900 -2050 F.O.0 Balance HEAT TREATMENT Same as types 303 and 303Se. HEAT TREATMENT Anneal (solution treat) 1900o-2100oF using rapid air cooling for sheet and light plate and water quench for heavier sections.065 inch and thicker.0 0. tubing: 1900o-1950oF. COMPOSITION RANGE o o Si% 1.5 0.0 0. COMPOSITION RANGE C% 0.0 0. These steels are subject to carbide precipitation when subjected to temperature over 800oF. Welding may be readily accomplished by all common methods.04 0. ALLOY TYPE 303 PERCENT Min C Mn Si P S Cr Ni Mo Cu Se Iron (Fe) .7-2.03% maximum carbon.5 TYPE 303Se PERCENT Min .0-25. Type 304L.0-2. This alloy may be hardened only by cold work.0 8.03 Fe% Balance FORM-SPECIFICATION.0 0.5 0. It is subject to embrittlement af ter long time exposure to temperature in the 1200o-1600oF range.0 Mo% Ni% 0.0 8. water quench.15 2.15 Balance Max 0. water Quench 0. TYPE 314. Type 304. This steel is produced in two grades.0 11. type 304 with 0. They have properties similar to Type 302 but the corrosion resistance is slightly higher.03 20.0 0.0 8.3 S% 0.5 TYPE 304L PERCENT MIN MAX 0. air cool or quench. These alloys have better corrosion resistance than 30302 or 30304 types.000 89 100.04 0-0. Steel Austenitic Stainless.0 0-0. This may be hardened only by cold work. 1/2 to 2 hours. Wrought products are readily formable and weldable. the possibility of intergranular precipitation and of the associated intergranular corrosion is reduced.0 0. Stress relieve af ter fabrication 1300oF. minimum. yield 45.000 89 PLATE ANNEALED SHEET ANNEALED WIRE ANNEALED 0. 1-1A-9 TYPE 314 FORMS CONDITION THICKNESSIN Tensile Yield Hardness RB BAR ANNEALED 1 IN DIA 100.This is one of the two stabilized 18-8 steels Since titanium FORMS-SPECIFICATIONS.0 0-0.010 245.000 psi.000 ------------- TYPE 316 and 317. tensile 90. Castings 1950o-2100oF.08 1. Stabilizing anneal for service 900o-1500oF.0 0-0. type 321 is used primarily either for parts fabricated by welding without postweld annealing or for service at 800o-1500oF.5 Iron% Balance forms a carbide of low solid solubility.002 to 0.0-2.000-70.O.0 0-1.000 psi.5 Ti% Cu% *6XC-0. This steel is available in all wrought forms.0 Mo% 2.04 0-0.5 Cu% 0-0. Steel Austenitic Stainless.000 89 95.25-2.5 Iron (Fe)% Balance FORMS-SPECIFICATIONS.0-19. Stabilize for high temperature service 1625o1675oF. 2-50 . See Specification Table 2-2.03 17.010 HARD DRAWN 0.000 ------------- 100. CORROSION RANGE C% Mn% Si% P% S% Cr% 0-0. HEAT TREATMENT Full anneal 1750o-1850oF.0-20.000 35.000 50.03 16. stress relieve 400o-500oF. 2 hours minimum for plate.08 0-2.000275. two hours minimum for plate furnace cool or air cool. water or oil quench or air cool. In annealed condition.000 230. HEAT TREATMENT Anneal wrought products 1850o-2150oF.T. (Cast Alloy) but CF 12M castings should be quenched from above 2000oF.000260.000 50.000 50.0-14. heat to 1500o-1650oF one hour per inch thickness.0 Ni% Mo% 8. * 6 times columbian content. TYPE 321.0-13. For sheet alloys.0 Ni% 11. Therefore. 1 hour per inch in thickness. Low side of temperature range is used for CF 8M.4-1. Welding rods and castings are not produced in this type. See Specification Table 2-2. This alloy may be hardened only by cold work. COMPOSITION RANGE C% Mn% Si% P% S% Cr% 0-. annealing temperature 1950oF.7 0-0.002 to 0. Castings are also weldable.000-130. air cool or quench depending on section size. and the metal arc method is most of ten used. Fusions welding of this alloy is comparable to type 304L. similar workability and machinability.10 11. will cause precipitation and reduce the resistance to intergranular attack. 2-51 . Corrosion resistance of this alloy is similar to Type 302.5-1.0 Ni% 9. 1-1A-9 TYPE 321 TENSILE .5 Cb1% *10XC-1. Full anneal castings 1900o-2000oF 30 minutes minimum. Type 420 has higher mechanical properties. Stainless type 416 has similar mechanical properties. 98. Tensile strength in annealed condition 117.15 1. Best performance is obtained if heat treated or cold worked to 180-240 BHN.04 0-0.06 0.YIELD FORM CONDITION THICKNESS IN Tensile Yield SHEET. Type 347 is used principally for parts fabricated by welding without postweld annealing. or for long service between 800o-1500oF.0 Mo% 0-0. Alloy may be hardened only by cold work.T. TYPES 403.6 0.5 Ni% 1. HEAT TREATMENT Full anneal wrought products 1800o-1900oF. See Specification Table 2-2.0-19. corrosion resistance is not as good as the 300 series stainless.08 0-2. COMPOSITION RANGE C% Mn% P% S% Si% Cr% 0. cool rapidly. STRIP ANNEAL -90000 35000 PLATE -85000 30000 ALL 85000 35000 BAR ANN+CD 1 INCH 95000 60000 WIRE SOFT TEMPER 0. HEAT TREATMENT Annealing: 1200o-1300oF. 410.0 Fe% Balance Mo% Si% 0.0 0-0. This steel is subject to carbide precipitation at temperatures in excess of 2150oF.0 14.O. 115. It should be passivated.25 0. COMPOSITION RANGE C% Mn% Si% P% S% Cr% 0-0.0 0. workability and resistance to corrosion. COMPOSITION RANGE C% Mn% P% S% Si% Cr% 0. This is a free machining type of alloy. 416. TYPES 347 and 348. Stress relieve af ter fabrication 1300oF.1 Iron (Fe%) Balance Welding.000 psi.5-13. At this temperature columbian carbides are going in to solid solution and subsequent rapid cooling. It is magnetic in the hardened condition and is not normally used in the annealed condition. 1 hour per inch of thickness 2 hours minimum for plate.000 yield. 1 hour per inch thickness. It has better machinability but less weldability.15 0-1. FORMS-SPECIFICATIONS. however. This steel has good resistance to weather and water.000 psi. Steel Austenitic Stainless is the second of two stabilized 18-8 steels (see type 321 for other). 2 hours minimum for plate. Postweld annealing is not required.25-2. Steel-Martensitic Stainless. furnace cool or air cool.04 0-0. Since columbian forms a carbide of very low solubility. specifying only the total of both elements. although a stress relief is recommended.03 0-0.03 17.0 0-0. however it has a greater tendency to pitting corrosion and attacks in streaks. Hardening: 1800o-1900oF.0-13.000 yield.062 115000 85000 0. Heavy sections may crack during welding or subsequent heating. Stabilizing anneal for service 800o-1500oF. Columbian is usually associated with the similar element tantalum which is included in the columbian analysis. followed by heating to 1200oF. Intergranular corrosion is absent in this steel unless it is overheated to above 2150oF. Therefore. the possibility of intergranular precipitation and of the associated intergranular corrosion are practically eliminated. 1500o-1650oF. Tensile strength in annealed cold drawn 130.5 Fe% Balance FORMS-SPECIFICATIONS. Steel Martensitic Stainless.50 95000 65000 Full anneal or stabilizing anneal will eliminate sensitized conditions. See Specification Table 2-2.6 *10 Times Columbian Content. A stabilizing anneal will restore the corrosion resistance.15 1. Type 414.08-0. 1075oF for 120.04 Ni% 1.2 1. air cool to room temperature. temper 550o±25oF for 2 hours. TYPE 431.03 15. Tempering between 600o-1000oF is not generally recommended due to reduced ductility and corrosion resistance.000 psi.000 Tensile and Yield 90. air cool. temper at a temperature not lower than 1100oF. Harden: 1700o-1850oF.3-0.000 psi. HT-115 (115. In the fully annealed condition formability of this alloy almost equals the 1/4 hard austenitic stainless steels.0-17. Heavy sections should be preheated at 1250oF. HEAT TREATMENT Full anneal 1550 -1650 F one hour per inch of thickness. See Specification Table 2-2. temper 1200o±25oF for 2 hours. or austenitize 1850o±25oF for 30 minutes.Tensile 100.000 psi. (3) Tempered and Drawn . depending on section size. air cool. HT-175 (175.000 psi. 2-52 Change 1 .04 0-0. Subcritical anneal 1300o-1350oF.Tensile 75.0 Ni% 0-0. Steel Martensitic Stainless. It machines best in conditions having approximately 225 BHN. yield 40. oil quench from furnace. Steel Martensitic Stainless.000 psi.000 Yield PSI) Heat Cond A material to 1850o-1950oF. furnace cool 50oF per hour to 1100oF.5 Fe% Balance FORMS-SPECIFICATIONS. HT-125 (125. helium) or vacuum in the furnace working zones.000 psi.000 psi. Tensile . Temper: Temper: Temper: 400o-1300oF. COMPOSITION RANGE C% Mn% Si% P% 0.0 TYPE 420. HEAT TREATMENT Anneal: 1500o-1650oF. CAUTION S% Cr% 0. Temper: range. 575o-600oF for 180. Weldability is poor except by use of low-hydrogen electrodes.03 Fe% Balance Cr% 12. Avoid 700o-1075oF temper 1300oF for 100.000 psi.4 0-1.5 Mo% 0-0. air cool. Materials in the solutiontreated condition (not more than 2 percent segregated ferrite or austenite in the microstructure) may be hardened by the following treat treatment. HEAT TREATMENT Type 431 steel must be protected from contamination at furnace temperature by dry inert atmosphere (organ.Tensile 110. (2) Heat Treated . Shearing type operations such as blanking and punching are not recommended.000 PSI) Heat Cond A material to 1800o-1900oF for 30 minutes. Parts shall be transferred from furnace working zones to the oil bath within a 30-second interval prior to quenching.000 psi. furnace cool (50oF per hour) to 1100oF.25-2. yield 85. o o Avoid tempering or holding within range from 700o to 1100oF. See Specification Table 2-2.0 0-0.0-14.000 tensile) Austenitize at 1850o±25oF for 30 minutes. yield 85. air cool. See Specification Table 2-2. marquench into salt bath at 400oF. quickly transfer from furnace to oil quench to bath at not over 100oF. quickly transfer from furnace to oil quenching bath at not over 100oF followed by refrigeration at 100oF±10oF for 2 hours. quench in oil from furnace temper at a temperature not higher than 700oF.T. temper 1200o±25oF for 2 hours. Austenitize 1800o-1850oF oil quench. 3 hours minimum.0 0.5 Si% P% S% 0-1. cool rapidly.0 1.0 FORMS-SPECIFICATIONS. refrigerate at 100o±10oF for 2 hours.000 psi. HT-200 CONDITION Austenitize at 1850o±25oF for 30 minutes. This is a medium carbon grade of martensitic stainless which in the past has been intensively used in the cutlery industry. Temper 400o1500oF. oil and quench. This alloy is suitable for highly stressed parts in corrosive environment. except that air or salt bath furnaces may be employed for tempering operations. It has recently proved satisfactory for air weapon application where its high strength permits heat treatment for tensile strength up to 240.000 Tensile and 135. COMPOSITION RANGE C% Mn% 0.Yield strength is as follows: (1) Annealed . tempering at 550oF±25oF for 2 hours. 3 hours minimum.O. and f inal temper at 550o±25oF for 2 hours. temper 550oF for 2 hours. 1-1A-9 FORMS-SPECIFICATION. This stainless steel possesses good corrosion resistance. Solution anneal 1925o-1975oF.00 6. From condition A to Condition H900(RH-C 40/47) 900o ± 10oF. Age condition A to condition TH1050. Steel Martensitic Stainless.0 max 1.75 max 1.0 0.03 16. Condition RH950 .6-0. 1735o to 1765oF.240 to 250 KSI ultimate.45 Ni% 3. COMPOSITION RANGE A% 0. 4 hours. Condition H1125(RH-C 30/37) 1125o ± 10oF.10-0. SPECIFICATION: See MIL-S-25043.03 max Cu% 3. Condition H975(RH-C 36/43) 975o ± 10oF. 1-1/2 Change 3 2-53 . air cool.75 Fe% Balance FORMS-SPECIFICATIONS.95 1. TYPE 440A. HEAT TREATMENT Condition A.125 to 145 KSI ultimate 75 to 100 KSI yield. air cool.T.0-5.2 1. 4 hours.0 1.75-0.0 S% 0.0 max 0.0-5. Condition CH900 . air cool. air cool. + 940o to 960oF.0 0.0 1.95-1. 4 hours.50-1.180 to 200 KSI ultimate 150 to 185 KSI yield. valves. Age condition C of cold rolled sheet or cold drawn wire to condition CH 900.12 P% 0. 4 hours. 1 hour.0 max SPECIFICATION: MIL-S-81506 HEAT TREATMENT To condition A-1900o±25oF 30 minutes.5-17. 230 to 240 KSI yield. Temper: 300o-800oF.200 to 215 KSI ultimate 180 to 190 KSI yield. may be machined and formed in its annealed condition. air cool. air cool. Steel.75 Fe% Balance C% Mn% Si% P% S% Cr% Mo% 440C 0. COMPOSITION RANGE C% Mn% Si% P% S% 440A 0. Condition H1025(RH-C 35/42) 1025o ± 10oF.0-18. 10 minutes. 4 hours. 4 hours.0 Iron Balance hour. 440B. Condition H950(RH-C 37/44) 950o ± 10oF.0 max Fe% Balance Si% 1.04 0.0-5.0-8.0 0.130 to 150 KSI ultimate.200 to 215 KSI ultimate 175 to 185 KSI yield. 550C. 890o to 910oF for 1 hour.0 Mn% 1.0 max 0. Steel Martensitic Stainless (Precipitation Hardening). 17-7PH.03 16. 4 hours.07 max 0.0 0.0 Si% 1. hold at 50o to 60oF 1/2 hour (condition TO) + 1040o to 1060oF.5 S% . etc. air cool to 50o to 60oF within 1 hour. 1-1/2 hour. Condition T . Condition RH1050 . This stainless steel possesses high strength and good corrosion and oxidation resistance up to 600oF. 30 minutes per inch of thickness. therefore they are grouped since heat treatment requirements are the same.04 max 0. HEAT TREATMENT Anneal: 1550o to 1650oF. Condition A . 1-1A-9 17-4PH.75 max Balance C% Mn% Si% P% S% Cr% Mo% 440B 0.04 max Cr% 15. COMPOSITION RANGE C% Cb% 0. Condition H1075(RH-C 31/39) 1075o ± 10oF. yield 260. Age condition A to condition RH 950. Precipitation Hardening.0-18.0 C% 0.000 psi. These steels are similar except for carbon range. 55 KSI yield. air cool. Condition H1100(RH-C 32/38) 1100o ± 10oF.030 Mn% Ni% 1. air cool or oil quench below 90oF. air cool. 1375o to 1425oF. air cool.045 Cr% 16. Harden: 1850o-1950oF. Condition C . 4 hours.04 0. and is used up to temperatures of 800oF. Martensitic Stainless.0-18. See Specification Table 2-2.O. Condition H1000(RH-C 35/42) 1000o ± 10oF. refrigerate (condition A 1750o) to -90o to -110oF 8 hours (condition R100). air cool. 4 hours.15-0. 4 hours. 440C. Condition H925(RH-C 38/45) 925o ± 10oF.0-18. Condition H1150(RH-C 28/37) 1150o ± 10oF. air cool.000 psi. air cool. 1 hour.03 max Cr% Mo% Fe% 16. 440A. These steels are used for cutlery.0 P% 0. cool rapidly. tensile 270. Condition H1050(RH-C 33/40) 1050o ± 10oF. air cool.015 S% 1. 1800o-1850oF. Age cold worked alloy. hardness.265 KSI ultimate.000 psi. hardness RC40. plate. 1 hour.T. TYPICAL PROPERTIES FOR VARIOUS CONDITIONS: Condition A . yield 275. 8 hours (condition R100) + 940o to 960oF.125 to 145 KSI ultimate. This alloy (sheet) is similar to PH 15-7 MO except it has slightly lower tensile and yield strength but considerable higher toughness and superior welding characteristics.180 KSI ultimate. 1 hour. hardness RC50.annealed C cold worker. sheet cold rolled or wire cold drawn to condition CH 900. 8 hours + age 1 hour.sheet.130 to 150 KSI ultimate. Condition A . Condition SRH 950 .0 Condition CH900 . CHEMICAL CONDITION C% Mn% 0. 15-7-MO. hardness 28-30. 125 KSI yield. 30 minutes air cool. by heating 890o -910oF for 1 hour. 1-1A-9 440B. water quench.000 psi. In general this alloy is unstable during exposure to temperatures exceeding 500oF.AMS 5520. hardness RC45. tensile 280. air cool. hardness RC46-48. SPECIFICATION . hardness RC38.0 1.1765oF. Welding is not recommended. Higher toughness may be obtained by annealing af ter welding and then heat treating. The heat treatment is identical to 17-7PH and other properties are identical or similar to 17-7PH. air cool. MECHANICAL PROPERTIES TYPICAL Condition A .0 0. 1925o-1975oF.50 Fe% Balance Al% 0. hold at 50o . Age condition A to SRH conditions.03 Cr% 14.220 KSI ultimate.02-0-05 1. Age condition A to condition TH1050. air cool (condition A 1750) ±90o to 110oF. hardness RC40-45.50-15. FORMS . 75-90 KSI yield. Age condition C. 190 yield. but can be hardened to a limited extent by cold working or hot cold working.O. 65 KSI yield. 19-9 DL 19-9 DX.50 Fe% Rem HEAT TREATMENT Condition A. Condition C . Bar and forgings solution anneal 1925o1975oF.50-9. RH1050.0-3. 440C. air cool.0 Ni% 7. 10 minutes (austenite conditioning).200 KSI ultimate. 30 minutes per inch thickness. 1-1/2 hour.1060oF. Aging at 940o-960oF or 1040o-1060oF is generally used with the higher temperature giving somewhat lower strength but af ter better toughness. COMPOSITION RANGE C% Mn% Si% P% 0.60oF within 1 hour. 1735o . In chemical composition 19-9DL contains columbium which was replaced by a higher molybdenum and titanium conten in 19-9DX. air cool.0-16.sheet and strip. 1 hour.60oF. bars and forgings. etc.000 psi.150 KSI ultimate. air cool to 50o . 1/2 hour (condition T) + 1040o . This general welding characteristics is similar to 17-7 PH. 3 minutes per 0.75 Mo% 2. 890o-910oF or 1040o1060oF.4 Ni% 6. 170200 KSI yield. 200225 KSI yield.0-3. FORMS AND CONDITIONS . This alloy is a further development of 17-7PH alloy and due to molybdenum content it can be heat treated to high strength at room and elevated temperature (up to 1000oF). TH and RH conditions are also used with difference f inal age hardening temperatures. 180 KSI yield. Condition T .50 S% 0.75-1.09 1. Steel Martensitic Stainless. however. Solution anneal sheet and strip.0 0. RB100 max. 190 KSI yield hardness RC40. 1-1/2 hour (austenite conditioning).220 KSI ultimate.available .1 inch thickness. Condition RH950 . such as TH1150.75-1. Age condition A to condition RH 950. Condition R100 . yield 270. This alloy is subject to salt stress corrosion. CHEMICAL COMPOSITION OF 19-9DL: 2-54 . early test indicate it is superior in this respect to 17-7PH and PH 15-7 MO.0 Si% Ph% 1. tensile 285. 55-65 KSI yield. HEAT TREATMENT Anneal to Condition A. These stainless steels are not heat treatable. which is a common characteristic of precipitation hardening stainless steels.50-7. 1375o to 1425oF.50 Me% 2.0 Cr% 13.190 to 210 KSI ultimate. Condition TH1050 . 1685o 1715oF. strip. Condition SRH1050 . air cool. 260 yield.225 to 240 KSI ultimate. hardness 90-100.0 A1% 0. PH 14-8 MO. air cool and within 1 hour cool to 100oF.000 psi. condition C. AMS 5657. 00 1. 1300o to 1450oF 1 to 2 hours. Double age condition L to condition DA.0-5. 2000oF.040 0. 1650o to 1800oF (1/2 to 1 hour) rapid air cool.35 0.10-0. Steel . Age to condition SCT 1000. 1850o to 1900oF. plate 3/4 hour inch. oil or water quench.002 . Homogenize sand and shell mold castings. 3/4 hour minimum.T. 3 hours minimum. Sheet/strip.0-17. Solution Treat: Same as anneal.80 0.0 1. Steel . It has a low FORM-SPECIFICATION TABLE 2-2. 3 hours minimum Age to 2-55 .Age Hardening stainless This alloy combines high strength at temperatures up to 850oF with the corrosive resistance of stainless steel.75-1. hold 3 hour minimum. 975o to 1025oF.50 Balance HEAT TREATMENT Bar and forgings. This is a precipitation hardening austenitic steel. The expansion on aging from condition H to set amounts to 0. air cool up to 1 inch thick.030 18.04 0-0. 3/4 hour minimum per inch of thickness. followed by rapid cooling.Age Hardening Stainless.25-2.08-0. It is also applied to cold worked materials immediately af ter working to prevent stress cracking. Age condition SCT 850.O.10-0. 1 hour minimum per inch. 1200o to 1400oF. 3/4 hour minimum per inch.25 0-0. HEAT TREATMENT Anneal to condition H for maximum formability and stability. Stress relief: 1175o to 1225oF (4 hours) air cool.0 Ni% Mo% W% Ti% Cu% Fe% 8.75-1. NOTE Intergranular corrosion may occur in certain environments unless annealed at 1800oF.0-21.1900o to 1950oF.25 N% 0.0 1. Corrosion resistance of this alloy is slightly lower than that of AM-350. In the solution annealed condition it has a Brinell hardness of 201 maximum. Age to condition SCT 1000 975o to 1025oF. 1/2 to 1 hour minimum. Allowance must also be made for growth which will result from heat treating. Anneal to Condition L: 1685o-1735oF ---Sheet and strip.35 0. with high rupture and creep properties in the 1000o1400oand not prone to overage at these temperatures. Avoid higher temperatures to prevent resolution and precipitation of carbides. Age: Bar and forgings. air cool. 3 hours. FORM-SPECIFICATIONS. cool to 100oF. if not subsequently severely cold formed.28-0. hold 3 hours minimum + 850o to 1050oF.5-1.75 0. Anneal to condition L .75 1.0-21. 2 hours. 3/4 hour per inch. This alloy differs from AM-350 by a lower chromium and a higher carbon content.50 Fe% Balance CHEMICAL COMPOSITION 19-9DX: C% Mn% Si% Ph% S% Cr% 0. cool to -100oF. HEAT TREATMENT Anneal to condition H . oil or water quench. 1950o to 2050o.80 0.12 0. HNM. 3 hours. 2-4 hours.875oF. air cool to 80oF maximum + 1000o to 1050oF.50 0. Steel .03 16. This alloy is one of a series of age hardening steels which combines high strength at temperatures up to 800oF and higher with the corrosion resistance of stainless steels. 1350o-1400oF.13 Fe% Balance condition SCT 850o. casting 1575o to 1625oF.75 0.35 0.Age Hardening Stainless. 8 hours minimum. COMPOSITION RANGE C% Mn% Si% P% S% Cr% 0.07-0. 825o to 875oF.030 18. rapid air cool to 80oF. 3 hours. section above 1 inch.0-11.040 0. Resulting should be approximately RC38 Subzero cool and age condition L to condition SCT. Bar should not be annealed to condition H unless subsequently subjected to forgings.28-0. AM-355.0-11.1685o to 1735oF. air cool.40-0. Subzero cool and age condition L to condition SCT. Condition H plate. Castings. See Specification Table 2-2. oil water quench. air cool to 80oF and heat to 825o 875oF. air cool.0-1. should be equalized before annealing to condition L and aging to condition SCT. 825o . rapid air cool to 80oF. 1 hour minimum per inch thickness. 1350o 1400oF. air cool to 80oF.0. rapid air cool. 1-1A-9 C% Mn% Si% Ph% Si% Cr% 0.5-3.004 inch per inch. It possesses good formability in the high temperature annealed condition. Double age either condition H or condition-L to condition DA. water quench: sheet and welded tubing.5 0-0.0 Ni% 4.0-1. Thoroughly degreased and cleaned prior to annealing to avoid harmful surface reactions and to facilitate subsequent pickling. per inch of thickness. Anneal to condition H: Plate and forgings at 1925o-1975oF. 825o to 875oF.0 Mo% 2.0 Ni% Mo% W% Cb+Ta Ti% Cu% 8. Equalize and age bar for best machineability.35 0. AM-350.30-0. This treatment is applied to hot worked or hot cold worked material for service up to 1300oF. oil or water quench.30-0.75 0. Bar forgings and tubing.50 0. 1800o to 2150oF (1/2 to 1 hour) rapid air cool.0-1. 850o to 1050oF for 3 hours minimum. At a temperature of 1200oF a tensile of 145. Sections 5/8 inches thick may be air cooled. This alloy was developed as a replacement for 1625-6 alloy and contains less nickel.40 P% 0-0.5 6.Chromium . This alloy has a good combination of tensile and creep rupture properties up to 1500oF at high stresses and is used for some parts of aircraf t gas turbines. aircraft structural. however. FORM Condition Solution Treat 2050oF 30 minutes oil quench 116. SPECIFICATION. shaf ts and gears. This material is very susceptible to work hardening. Solution treat 2125o-2175oF. None. Age 1300oF. 2-56 .06 15. 30 minutes.03 S% .000 Tensile PSI Yield PSI Hardness BHN RB RC 192 302 87. engine components. None.0 0.000 and yield of 100. SPECIFICATION.25 Ti% 3.5 5.5 0.07 15. the lower nickel content is balanced by additional manganese which allows an increase in the nitrogen content that can be retained during melting.0 14-0-17.Nickel Chromium Stainless (Austenitic).025 FORM.30 18. however brazing may be successfully accomplished by use of orayacetylene torch and furnace methods.25 0. depending on section size.5 0.5-8.000 BAR Solution Treat 2050oF 30 minutes Water quench 145.25 0. At a temperature of 1200oF a tensile of 145.0-7. 2 to 8 hours.000 Solution Treat 15 minutes air cool 106. Bar. air cool.25 25. machining requirements are similar requiring heavy positive feeds and sharp cutting tools.5 3.000 92.0 V% 0.5 9.000 90.Nickel . COMPOSITION RANGE A1% B% C% Cr% Mn% 0. Solution treat 2125o-2175oF. and is suitable for transformer parts. Steel .5 0.0-17. depending on section size. air cool.Iron .000 psi is obtained.5 33 V57. using an alloy conforming to specif ication AMS 4755.000 55.30-0.000 56. HEAT TREATMENT Anneal 1700o-2300oF.25 S% 0.T.Alloy. air cool.000 and yield of 100. Cold work (about 20% reduction) and age (bar up to1/2 inch) 1200oF-1300oF 2 to 8 hours. water or oil quench. non-magnetic bolts. See Specification Table 2-2. 16 hours. Cold work (about 20% reduction) and age (bar up to 1-1/2 inch) 1200o-1300oF. COMPOSITION RANGE AM355 C% Cr% Mn% Ni% P% Si% S% Iron 0. HEAT TREATMENT Anneal 2000o-2150oF. HEAT TREATMENT Anneal 1700o-2300oF.000 SHEET Solution Treat 2050oF air cool & age 1300oF.025 Mo% Ni% Si% 1. forging.O. Welding is not recommended. 16 hrs 133. 1-1A-9 magnetic permeability. water or oil quench. However.0 0-1. The optimum solution treatment for best properties af ter aging is approximately 2050oF. FORM. COMPOSITION RANGE C% Cr% Mn% Mo% Ni% Si% 0-.000 psi is obtained. water quench.008 0. Steel . Forging. Bar.03 Iron (Fe) Balance P% 0.0 N% 0.025 Balance FORM-SPECIFICATIONS.55 Iron Balance 16-15-6. It is somewhat inferior to regular 18cr-8ni stainless types. O. GMR-235.5 Cr% Iron% Mn% Ni% 19. GMR-235 and GMR-235D are nickel based alloys precipitation hardening.0-12.40-0.0 0-2.000 psi. This alloy may be air melted or air cast. It is used as gas turbine blades and rotors within the heat range 1200o-1700oF. 1 hour. Available as castings and investment castings.08 0. Age 1400oF for 16 hours.0 0-1.5 12.5 0-1. Solution treatment for thick sections 2200o2275oF.0 1. Aging 1400oF 4 hours air cool af ter solution treating.000 83.5 1. HEAT TREATMENT Stress relief: 1575o-1625oF. COMPOSITION RANGE C% Cr% C1% Ta% Iron% Mn% Mo% 0.03-0. Steel Cobalt Base . has excellent castability and foundry characteristics. buckets and vanes. forging and wire. COMPOSITION RANGE Tensile Yield RC 147. TYPE V36 SPECIFICATION. The best creep rupture properties are in the 1300o-1500oF range. cool rapidly 279. 2 hours. Solution treat 2170o2200oF 1 hour minimum.0 0-0.0 0-1. Steel.04 Cobalt Balance 2-57 .0-22.T. Nickel Base Corrosive Resistant Alloy.5-4. rapid air cool.03 Balance SPECIFICATION.000 --Sol Treat +60%.Chromium-Nickel-Alloy. Haynes Alloy No 152. 151.0 Si% Ti% W% P% S% Cobalt% 0-1.0-26. high temperature alloys developed for investment cast gas turbine wheels. HEAT TREATMENT This alloy is primarily solid solution hardened and only small strength increases can be obtained by aging.25-0. Rockwell As cast.5 0-5.5-2.5 0-0. The composition with maximum aluminum and titanium content is designated GMR235D.0 0-1.hardening alloy for service at 1300o-1800oF where strength and corrosion resistance is important. cool rapidly 166. FORMS. Stress relieve cold worked alloy 900oF.0 0-1.03 0-0.0 0.2 3.5-2.33 24. CF 239.5-2. Age hardening: Above 1200oF susceptible to age hardening which increases alloy strength but causes loss in ductility.05-0.5 20.000 25 W152. This is a solid solution .0 1.0-21. None.5 Ni% Si% W% S% P% Cobalt 19.0 Si% 0-0. Hardenability. Chief ly furnished in sheet. FORMS. Tensile Strength: As cast. Used for guide vanes in gas turbines.03 0-0. water quench.000 --This material is generally used in the ‘‘as cast’’ condition. Primary use has been f irst-stage turbine vanes.000 127. They are similar to Hastelloy R-235 but contain more aluminum. bar. It is used for investment cast parts requiring high stress rupture properties at elevated temperatures.0 P% 0-0.000 248. RC38.0-2. af ter burner parts and high temperature springs. As-Cast hardness at room temperature RC33.0-13.04 S% 0-0. Cobalt Base Corrosion Resistant Alloy. but creep rupture properties are somewhat lower than the ‘‘as cast’’ alloy.03 Balance SPECIFICATION. COMPOSITION RANGE B% C% 0.5 0-0. This treatment reduces tensile properties below 1400oF and lowers creep rupture strength.4-0. 2 hours. COMPOSITION RANGE C% Cr% C1+TA Iron% Mn% Ni% 0.5 W% 10. Cobalt Chromium Tungsten Corrosion Resistant Alloy. None. air cool. This is a casting alloy generally used in the ‘‘as-cast’’condition. 1-1A-9 SUPPER ALLOYS H/L V36. Available in ‘‘as cast condition’’.0 1. operating above 1400oF. Alternate Designations. tensile strength 125. HAYNES ALLOY NO. PWA 653. results in higher tensile properties than ‘‘as cast’’ material. None. HEAT TREATMENT FORM Condition SHEET Sol Treat 15 min 2250oF+ age Sol Treat +20%.0-21. but may be supplied in billet. solution treat at 1950o-2000oF hold at temperature for 30 minutes and air cool. None. TYPE HASTELLOY ALLOY R-235 SPECIFICATIONS.000 95. Then heat to 2025o-2075oF.0 0-0.0 0. Steel Nickel Chromium Stainless Alloy. It has good properties up to 1300oF.0-21. hold at temperature for 30 minutes and cool in still air. Material treated at higher solution temperature (2200oF) is subject to strain-age cracking.2 17.3 2.2 12.03 Ni% Balance SPECIFICATION.0 0-0.5 . To obtain maximum room and high temperature tensile strength or short time rupture strength.3 0-0.5 9. air cool. COMPOSITION RANGE A1% C% Cr% C1%+Ta% Cu% Mn% 0. Nickel Base Corrosion Resistant Alloy.0-55.5 Balance GMR-235D MAX 3. furnace cool.0 4.000 95.1 0.0 3.25-2. None.25 4.6 2.0 0.75 0-0. 20oF per hour to 1150oF air cool or 1325oF 8 hours.60 2.5 0.0 50.O.0-4. Single age anneal alloy at 1325oF 16 hours. It is readily welded in either the annealed or aged condition. furnace cool. 5 hours from the ‘‘as cast’’ condition improves the stress rupture life of the alloy. bars and forgings 1800o-1900oF. water quench. This alloy is readily fabricated and welded in the solution treated condition.5 Balance MIN MAX 3. It possesses high strength up to 1800oF with good resistance to oxidation and overaging in high temperature service.0 0 0. For heavier sections (of both alloys) temperatures should be increased to 2150oF.50 Mo% Ni% Si% Ti% S% Iron 2.25 0-0. Strip.1 8.0-11.05 0. Then age at 1385o-1415oF hold at temperature for 16 hours and air cool. except that GMR235 is available in cast form. FORMS. Solution treat sheet at 1725oF. Investment Castings.0-17. 100oF per hour to 1150oF.0 0-2. Max psi RC-Max SHEET Sol Treat 1975oF Water Quench 0. Max psi Yield.0 17.1 14.75-2. FORMS.0 0.5 5. the latter is preferred for highest strength up to 1300oF. Bar and Wire HEAT TREATMENT FORM Condition Thickness-in Tensile. Tensile 115. None. Sheet. HEAT TREATMENT Solution treatment 2050oF 1 to 3 hours. 1-1A-9 GMR-235 % MIN A1 B C Cr Co Iron Mn Mo Si Ti Ni 2.000 27 Sol Treat 2200oF Water Quench 0. Double age anneal alloy at 1325oF 8 hours. These alloys precipitation harden rapidly during air cooling and aging treatments are usually unnecessary. Strip. air cool (GMR 235) Solution treatment 2100oF 2 hours.25 6. Bar.16 14.021 150.5-5.5 6.0 0. Both of 2-58 . air cool (GMR-235D).0 Mn% Mo% Si% Ti% P% S% 0-0.4-1.1 17. Solution treat rods.5 0 1.1 0.25 4.0 0 0.0 0 0 3.01 0-0. 2 to 4 hours. water quench.2 14.75 0-0. COMPOSITION RANGE A1% B% C% Cr% Co% Iron% 1.0 0 4. air cool. HEAT TREATMENT Both single age and double age treatments may be employed.000 psi.1 0.75 0-0. This is a relatively new alloy and heat treatment and fabrication procedures are still under development. hold 8 hours. To obtain maximum long time stress-rupture life.5-6. Somewhat higher creep rupture properties are obtained at the higher temperatures.5 0.000 25 INCONEL ALLOY 718.T. Form This material is available in wrought form only. Aging at 1800oF.03 Balance SPECIFICATION. 15 minutes. slow response to age-hardening and good ductility from 1200o-1400oF.1 4.009 0-0.000 psi yield 90.05 0.5 0-0.0 0. ‘‘As-Cast’’ room temperatures hardness for both alloys is RC36 maximum. however.70 150. solution treat at 2175o 2225oF. HASTELLOY ALLOY R-235. air cool.3-1. Sheet. This is a nickel base aluminum-titanium precipitation hardening alloy. Plate. Final heat treatment af ter fabrication of sheet and bar depends upon properties desired.0 Balance Balance Solution treatment 1950o-2000oF 1/2 hour. Distortion is comparatively low if material is subsequently solution treated and water quenched.015 Ni% Balance Zr% 0-0.75-3. cool to 1200oF in 4 seconds maximum + 1400oF. Start and f inish should be made on metal tab of the same thickness using an inert gas atmosphere of 2 helium to 1 argon.01 Co% Iron% 10.5 18.2 S% 0-0.000 *Furnace cool at temperature reduction of 100oF per hour to 1150oF hold 8 hours air cool. ** Furnace cool at temperature reduction of 20oF per hour to 1150oF air cool.g. Highly Alloyed Nickel Base Corrosion Resistant.06-0.0 0-5. Following the torch with a water spray reduces the hardness and produces maximum ductility in the weld and heat affected zones. TYPE INCONEL ALLOY 718 FORM Condition HOT ROLLED BAR 0. It can be formed and also welded in the annealed condition.000 RC43 2150oF water quenched 130. Plate. solution treat 2150oF 30 minutes + 1650oF 4 hours. If cooled at a slower rate than specif ied.0-12. Bar. COMPOSITION RANGE C% Mn% Si% Cr% Ti% A1% 0.000 Age 1325oF 16 hour 193. water quench or cool from 2150o to 1200oF in 4 seconds maximum. This is a nickel base investment casting alloy which is strengthened by addition of cobalt. It also has superior creep resistance.03-0. This alloy has higher elevated temperature tensile and stress-rupture strength than most wrought cobalt or nickel based alloys. Solution treat. This alloy may be fusion welded if copper and gas backing with a tight hold down is used.0 0-0.5 B% 0-0.75 B% 0-025-0.5-1.0500 IN DIA Anneal 1800 F 1 hour 8 hour* o + + 8 hour** 204. 1950o-2000oF 4 to 6 hours.0-16. Castings.06 SPECIFICATIONS. fatigue strength and high oxidation resistance.0 0-0. aluminum and titanium. TYPE RENE 41 Co% Cu% 17.000 hardening results and forming becomes diff icult.1 Cr% 14. Strip.8 Mo% 9.0-3.5-6.12 0-0. Best machinability is obtained in the fully aged condition af ter either oil or water quenching from solution treating temperature. This alloy possesses exceptional mechanical properties at temperatures up to 1800oF. Wire. Solution treat 1950o-2150oF 30 minutes.T.75 Iron Mn% Mo% Si% 0-4. 2-59 . Final aging 1385o-1415oF 16 hours air cool. age FORM Condition Tensile Yield Rockwell Hardness ALL 2150oF air cooled 195. Bars.0-20.000 173. Welding is generally not recommended.0-10.0 Ni% Balance Thickness .0 SPECIFICATIONS: None FORMS: Sheet. UDIMET 700.000 65.75-4. Nickel Base Heat Treatable Stainless Alloy. Hardens by aging and cold working.500 211.035 C% 0. Nickel Base Corrosion Resistant Alloy. It has high creep strength and excellent oxidation resistance in the high temperature range 1500o-1800oF combined with good room temperature strength.in Tensile PSI Yield PSI 0. Billets. Forgings HEAT TREATMENT Solution annealing for castings 2075o-2125oF 2 hours air cool. 16 hours.000 160.0-20.1 Ti% 2. air cool. RENE 41. quench or air cool.0 0-0. Hardenability: Alloy must be water quenched to retain sof t solution treated conditions.O.3 1. Intermediate aging 1535o-1565oF 24 hours air cool. in less than 4 seconds from 2150oF to 1200oF. COMPOSITION RANGE A1% 3.0 3. 1-1A-9 these double age treatments appear to give the same results.5 0-0. None FORMS. e. Solution annealing for forgings 2125o-2175oF 4 hours air cool.000 174.15 4.000 154. HEAT TREATMENT For maximum formability 1950o-2150oF 30 minutes. Heat treat for good ductility and high creep rupture strength.000 RB93 NICROTUNG. Heat treatment for high short time strength: Solution treat 1950oF 30 minutes. fully heat treat solution treat. 2-77.0 9.0-8. air cool and 1526oF. are as follows: a. Nickel-Cobalt-Chromium Corrosion Resistant Alloy. 2-75. The term cutting feed is used to express the axial distance the tool moves in each revolution. side clearance. The structure of the steel to be machined. tool. For a known diameter and surface feet per minute (SFM) be used for an operation. 1-1A-9 COMPOSITION RANGE A1% B% C% Cr% Co% 3. Corrosion resistance is good and resistance to oxidation under repeated heating and cooling is very good. which is assigned a machinability rating of 100%.0 0-0. front clearance. and soluble or emulsif iable oils. Where stress rupture strength above 1562oF is not the important property. air cool. HEAT TREATMENT For maximum stress-rupture life in range 1560o1740oF. the cutting action is the same. Bar. d. the width. select the type of operation. MACHINING OF STEELS (GENERAL).0 Mo% 4. 8-16 degrees. Recommended cutting f luids for steels are lard oil. The cutting tool angles (back rake. and side rake) are highly important in the machining of metals. Regardless of the material of which the cutting tool is made.08-0. None FORMS.2-4. The cutting speeds listed in Table 2-4 are approximate speeds using high-speed steel tools.75 W% 7.9-1.2 Cr% 13. 16 hours.08 0. 8 hours. These speeds are based on SAE 1112 steel.5-5. 12-22 degrees. Back rake angle.08 Ni% Balance e. refer to Table 2-6 for recommended checks. Side clearance angle.02-0. the cast alloys at twice the speed of high-speed steel. depth or diameter of cut and obtain the recommended cutting speed for SAE 1112 from Table 2-3 then refer to Table 2-4 for the percent rating of the metal to be machined. The capacity and rigidity of the machine Cutting f luids. 2-80.8 Mn% 0-1. For tool corrections when improper machining on an operation is encountered. and double age as follows: Solution treat 2102oF 4 hours.0-22. Strip. COMPOSITION RANGE A1% 4. air cool. Side rake angle. and a f ine feed for f inishing operations. but tensile strength. Double age 1922oF.T. and are to be used only as a basis from which proper speeds for a particular part may be calculated. Investment castings. The range of values based on general practice for the machining of steel and steel alloys.O.02-0. 8-13 degrees. air cool.75-4. and also acts as a lubricant giving better cutting action and surface f inish. c. c.75 0. SPECIFICATIONS. the feed remains the same for different cutting tool steels. and the sintered carbides at twice that of the cast alloys. and multiply the SFM value from Table 2-5 by the rating in Table 2-4. NIMONIC 105. and only the speed is changed. A course feed is usually used for roughing operations. d. the corresponding revolution per minute (RPM) can be obtained from Table 2-5. HEAT TREATMENT Heat treatment is not recommended for this alloy. Approximate cutting feeds are listed in Table 2-3. elongation and impact strength up to 1292oF is desired. This alloy has excellent resistance to creep at very high temperatures. 2-79. The carbon-steel tool cuts at low speed.0-13.0 Co% Cu% 18. 2-78. Front clearance angle. mineral oils. b. The use of a proper coolant (cutting f luid) of ten results in an increase of cutting speed for the same tool life.5-16. In order to obtain an approximate starting speed for different steels. The main difference is the cutting speed.5 Ti% 0. 2-60 . the following heat treatment is recommended.75-4. Cutting condition with respect to feeds and speeds. The highspeed tool cuts at twice the speed of carbon-steel. 4 hours. 16 hours. Solution treat 2104oF. It is designed for use as turbine blades and rotors used in gas turbines. None FORMS. This material has ‘‘as-cast’’ hardness of RC38-40.0 Ti% 3.5 Zr% 0. air cool. Age 1562oF. 10-15 degrees.0 S1% 0-1.0-11. The result is the recommended surface feet per minute (SFM) for the cutting operation. sulphurized oils. Sheet.5 Ni% Balance SPECIFICATION. In general. There are f ive basic factors affecting machinability as related to steel: a. b.13 11.0 C% 0-0. Design composition and hardness of the cutting tool.5 Iron% 0-1. 2-76. 0025 0.750 1.0025 0.0055 0.500 0.250 Under 1/2″ Over 1/2″ Width Width Width Width Table 2-4.125 0.0015 0. IN.0018 0.187 0.007 0.007 0.250 0.500 2.062 0. Width Width Width Width Width 0.000 1. Cutting Speeds and Feeds for SAE 1112 Using Standard High Speed Tools TOOL NAME Form Circular or Dovetail SIZE OF HOLE.0045 Twist Drills 0.250 0.000 2.006 0.0025 0.000 1.0020 0.T.010 0./REV 0.125 0.500 1.010 0.008 0. IN.005 0.O.500 SURFACE FPM 165 160 160 155 150 105 105 115 115 120 FEED IN.0045 0.250 Depth Depth Depth Depth Over 25 Pitch 15 to 25 Pitch Less than 15 Pitch 0.007 0.007 0.008 0.0012 0.0065 0.500 Box Tools Blade 165 160 155 150 30-40 20-30 15-20 150 140 135 130 145 145 165 175 180 190 Threading and Tapping Hollow Mills 0. 1-1A-9 Table 2-3.250 0.002 0.125 0. 0.062 0.375 0.003 Reamers Cut Off Machinability Rating of Various Metals SAE DESIGNATION 1010 1015 1020 1022 1025 1035 1040 1045 1050 1055 1060 RATING % 50 50 65 70 65 65 60 60 50 55 60 BRINELL HARDNESS 131-170 131-170 137-174 159-192 116-126 174-217 179-229 179-229 179-229 192-197 183-201 2-61 .0065 0. -- WIDTH OR DEPTH OF CUT.187 0. T.O.Continued SAE DESIGNATION 1070 1080 1095 1112 1117 1137 2317 2330 2340 2515 3115 3140 3310 4037 4130 4135 4137 4140 4150 4337 4340 4615 4620 4640 5210 6150 8615 8617 8620 8630 8640 8735 8740 9260 9262 9310 RATING % 45 45 42 100 85 70 55 50 45 30 65 55 40 65 65 64 60 66 50 50 45 65 62 55 30 50 67 63 60 65 60 55 60 45 45 40 BRINELL HARDNESS 183-241 192-229 197-248 179-229 143-179 187-229 174-217 179-229 187-241 179-229 143-174 187-229 170-229 170-229 187-229 170-229 187-229 179-197 187-235 187-241 187-241 174-217 152-179 187-235 183-229 197 170-217 170-217 170-217 179-229 179-229 179-229 179-229 187-255 187-255 207-217 2-62 . Machinability Rating of Various Metals . 1-1A-9 Table 2-4. T. Conversion of Surface Feet Per Minute (SFM) To Revolutions Per Minute (RPM) DIAMETER IN INCHES 1/16 1/8 3/16 1/4 5/16 3/8 7/16 1/2 9/16 5/8 11/16 3/4 13/16 7/8 15/16 1 1 1/8 1 1/4 1 3/8 1 1/2 1 5/8 1 3/4 1 7/8 2 2 1/4 2 1/2 2 3/4 3 DIAMETER IN INCHES 1/16 1/8 3/16 1/4 5/16 3/8 120 7334 3667 2445 1833 1467 1222 130 7945 3973 2648 1986 1589 1324 140 8556 4278 2852 2139 1711 1436 10 611 306 204 153 122 102 87 76 68 61 56 51 47 44 41 38 34 31 28 25 24 22 20 19 17 15 14 13 15 917 458 306 229 183 153 131 115 102 92 83 76 71 65 61 57 51 46 42 38 35 33 31 29 25 23 21 19 20 1222 611 407 306 244 204 175 153 136 122 111 102 94 87 81 76 68 61 56 51 47 44 41 38 34 31 28 25 25 1528 764 509 383 306 255 218 191 170 153 139 127 118 109 102 96 85 76 69 64 59 55 51 48 42 38 35 32 30 1823 917 611 458 367 306 262 229 204 183 167 153 141 131 122 115 102 92 83 76 70 65 61 57 51 46 42 38 SURFACE FEET PER MINUTE 40 2445 1222 815 611 489 407 349 306 272 244 222 203 188 175 163 153 136 122 111 102 94 87 81 76 68 61 56 51 50 3056 1528 1019 764 611 509 437 382 340 306 278 255 235 218 204 191 170 153 139 127 117 109 102 95 85 76 69 64 60 3667 1833 1222 917 733 611 524 458 407 267 333 306 282 262 244 229 204 183 167 153 141 131 122 115 102 92 83 76 70 4278 2139 1426 1070 856 713 611 535 475 428 389 357 329 306 285 267 238 214 194 178 165 153 143 134 119 107 97 89 80 4889 2445 1630 1222 978 815 698 611 543 489 444 407 376 349 326 306 272 244 222 204 188 175 163 153 136 122 111 102 90 5500 2750 1833 1375 1100 917 786 688 611 550 500 458 423 393 367 344 306 275 250 229 212 196 183 172 153 137 125 115 100 6111 3056 2037 1528 1222 1010 873 764 679 611 556 509 470 436 407 382 340 306 278 255 235 218 204 191 170 153 139 127 110 6722 3361 2241 1681 1345 1120 960 840 747 672 611 560 517 480 448 420 373 336 306 280 259 240 224 210 187 168 153 140 SURFACE FEET PER MINUTE 150 9167 4584 3056 2292 1833 1528 160 9778 4889 3259 2445 1956 1630 170 10390 5195 3463 2597 2078 1732 180 11000 5500 3667 2750 2200 1833 190 11612 5806 3871 2903 2322 1935 200 12223 6111 4074 3056 2445 2037 225 13751 6875 4584 3438 2750 2292 250 15279 7639 5093 3820 3056 2546 270 16807 8403 5602 4202 3361 2801 300 18334 9167 6112 4584 3667 3056 2-63 .O. 1-1A-9 Table 2-5. Feed (increase feed if too light a feed has tendency to rub rather than cut) 6. TOOL CHATTER Check: 1.T.O. Tool load (vary side cutting edge angle to correct improper load) 7. Tool overhand (reduce to minimum) 2. Tool clearance (be sure end cutting edge angle is suff icient) 5.) 2-64 . Chip breaker (widen breaker if chips are too tight. 170 1484 1299 1154 1039 945 866 799 742 693 649 577 519 472 433 400 371 346 325 289 260 236 216 180 1572 1375 1222 1100 1000 917 846 786 733 688 611 550 500 458 423 393 367 344 306 275 250 229 190 1659 1451 1290 1161 1056 968 893 829 774 726 645 581 528 484 447 415 387 363 323 290 264 242 200 1746 1528 1358 1222 1111 1019 940 873 815 764 679 611 556 509 470 437 407 382 340 306 278 255 225 1964 1719 1528 1375 1250 1146 1058 982 917 859 764 688 625 573 529 491 458 430 382 344 313 286 250 2183 1910 1698 1528 1389 1273 1175 1091 1019 955 849 764 694 637 588 546 509 477 424 382 347 318 270 2401 2101 1867 1681 1528 1401 1293 1200 1120 1050 934 840 764 700 646 600 560 525 467 420 382 350 300 2619 2292 2037 1833 1667 1528 1410 1310 1222 1146 1019 917 833 764 705 655 611 573 509 458 417 382 Tool Correction Chart A. Work Support (eliminate vibration) 3. 1-1A-9 DIAMETER IN INCHES 7/16 1/2 9/16 5/8 11/16 3/4 13/16 7/8 15/16 1 1 1/8 1 1/4 1 3/8 1 1/2 1 5/8 1 3/4 1 7/8 2 2 1/4 2 1/2 2 3/4 3 120 1048 917 815 733 667 611 564 524 489 458 407 367 333 306 282 262 244 229 204 183 167 153 130 1135 993 883 794 722 662 611 567 530 497 441 397 361 331 306 284 265 248 221 199 181 166 140 1222 1070 951 856 778 713 658 611 570 535 475 428 389 357 329 306 285 267 233 214 194 178 SURFACE FEET PER MINUTE 150 1310 1146 1019 917 833 764 705 655 611 573 509 458 417 382 353 327 306 287 255 229 208 191 160 1397 1222 1086 978 889 815 752 698 652 611 543 489 444 407 376 349 326 306 272 244 222 204 Table 2-6. Nose radius (too large a radius may cause chatter) 4. Speed (Low and excessive speeds cause tool wear) 3. The modif ied alloys which are usually Table 2-7. Nose radius (decrease size) D. are more diff icult to machine than the carbon steels and most other metals.’’ This table is only intended as a starting point and is not intended to replace any information accumulated through experience or other available data. Coolant (Heating and cooling of tip may cause chipping) C.Continued B. especially the 18-8 grades. designated by a suff ix to type number such as 430 F or Se. CHIPPING OF CUTTING EDGE Check: 1. their chemical content is modif ied by adding selenium (Se) and sulfur (S). the same general methods are used with modif ication/compensation for the individual characteristics of each type or grade. The corrosion resisting steels. RAPID TOOL WEAR Check: 1. General Machining Comparison of Corrosion Resisting Steel To Free Machining Screw Stock B1112 GRADE/TYPE Group I 430F 416 420F 303 MACHINABILITY RATING 80% 75% 70% 65% GRADE/TYPE Group III 420 431 440 442 446 347 MACHINABILITY RATING 45% 45% 45% 45% 45% 40-45% 40% 40% 40% 40% Group II 403 410 430 440F 55% 50% 50% 50% Group IV 302 304 309 316 2-65 . Relief angles (clearance may not be suff icient) 4. For comparison and as a general guide to the machining characteristics of free machining screw stock grade B1112 as an 100% machinable ‘‘norm. Tool Correction Chart . MACHINING CORROSION RESISTING STEEL.T. UNSATISFACTORY FINISH Check: 1. 2-82. 1-1A-9 Table 2-6. Edge sharpness (Hone or chamber slightly) 2. Exceptions are types 416 and 303. 2-83. To improve machining characteristics of some types. Nose radius (too large a nose radius mats f inish) 2-81. Speed (Increase) 4. Feed (Increase) 2. Speed (rough f inishes can be eliminated by increasing speed) 2. Chip Breaker (widen breaker if tight chip causes chipping) 3.O. Even though they are more diff icult to machine. use slow speeds and heavy feed to reduce effect of work hardening. To overcome these problems requires control of speeds.040 0.020-0. smooth. b. cutting tools. 2-86. 2-87. etc. Prior to attempting local manufacture of cutting tools. Suggested Cutting Speeds and Feeds ALLOY TYPE/GRADE 302. 304. for cutting corrosion resisting steel: a. use Tungsten Carbides. 309.015 0. Tools for turning the corrosion steels should be ground with a heavy side rake clearance for maximum cut freedom.T. The upper surface of the tool should be f inished with a f ine wheel or hand stoned to prevent galling. Grind tools with generous lip rake and with ample side and front clearance.008-0. galling and stringing. In machining of the corrosion resisting steels. Select tools of proper alloy/type and keep cutting edges sharp. Avoid riding of tool on work and intermittent cutting when possible. Avoid overheating cutting tool when grinding to prevent surface and stress cracking. c. from an economic standpoint. Do not allow tools to become dull to prevent surface hardening from rubbing and hard spots which are diff icult to remove.PER MIN 20-40 50-80 40-60 90-110 150-200 OPER Rough Finish Rough Finish Rough TOOL MATERIAL High Speed Steel High Speed Steel TungstenCobalt TungstenCobalt Carbide 2-66 . facilities/equipment must be available to properly heat treat. NOTE Some types of tool steel are available in raw stock in accordance with Federal Specif ications. use Tungsten-Cobalt Type T5 (18-42-8) and Tungsten-Cobalt Type T4. and heat treated. 1-1A-9 2-84. For chip disposal or breakage a chip grove is usually necessary except with the free machining grades. Support cutting tool rigidly near work to prevent lash and other diff iculty from use of heavy cutting feeds. The following is a recommended guide for selection of tools: a. (18-41) and Molybdenum-Tungsten Type M3 (6-63).030 CUTTING SPEED SURFACE FT.008-0. For general machining and short runs use high speed tool steels such as Tungsten Type T1 Table 2-8.. diff iculty will be experienced from seizing. d. Speeds are critical in machining stainless. TURNING OF THE CORROSION RESISTING STEELS. see paragraph 7-4. free of burrs. b. g. Cutting Tools for Machining Corrosion Resisting Steels. the chip breakage is a safety precaution to prevent diff iculty and hazards in breaking the expelled cutting..010-0. Selection of cutting tool is important for machining stainless due to tough machining characteristics.015 0. etc. c.020-0. it is usually advisable to obtain most cutting tools pref inished to size. and lubricants. 2-85. Cutting tool of these alloys can be used at approximately 100% faster speeds than the Tungsten-Cobalt type.O. In addition. 316 FEED INCH 1/ 0. 314. nicks and scratches. f. e. Apply proper lubricant/coolant to cutting tool to prevent overheating. For medium runs at approximately 25% higher speed. For long production runs at high speed. The following general practices are recommended for shaping/grinding cutting tools. 310. select speed about 50% slower than those used for carbon steels as a starting point. In general. equipment.040 0. In addition. 015 430F.020-0.005-0.010-0.030 0.015-0.PER MIN 150-300 20-40 OPER Finish Rough TOOL MATERIAL Carbide High Speed Steel High Speed Steel TungstenCobalt TungstenCobalt Carbide Carbide High Speed Steel High Speed Steel TungstenCobalt TungstenCobalt Carbide Carbide High Speed Steel High Speed Steel TungstenCobalt 420. 347.018 0.030 0.015-0. 1-1A-9 Table 2-8.040 0.008-0.T.018 0.008-0. Suggested Cutting Speeds and Feeds .015-0.018 CUTTING SPEED SURFACE FT. 321 0.015-0.018 0. 440.040 0.040 0.005-0.015 0.005-0.015-0. 431.015 420F 303 0. 442.O.008-0. 416 0.005-0.050 0.008-0.Continued ALLOY TYPE/GRADE FEED INCH 1/ 0. 446.015-0.050 55-90 40-80 100-130 165-220 165-330 30-60 75-120 60-105 135-180 225-300 225-450 25-55 65-105 50-90 Finish Rough Finish Rough Finish Rough Finish Rough Finish Rough Finish Rough Finish Rough 2-67 .015 0.040 0. T.015 CUTTING SPEED SURFACE FT. Suggested Cutting Speeds and Feeds . Feeds for smaller sizes should be reduced proportionally to size of material being turned.030 0. 2-68 .PER MIN 100-155 175-240 195-350 OPER Finish Rough Finish TOOL MATERIAL TungstenCobalt Carbide Carbide NOTE: 1/ Feeds cited are based on turning 1 inch stock or larger.O. Another factor requiring consideration in machining stainless is high co-eff icient of thermal expansion which will necessitate adjusting (slacking off) centers as material heats up.005-0. 1-1A-9 Table 2-8. 2-88.015 0. The sof ter condition of stainless is not necessarily the easiest to cut.Continued ALLOY TYPE/GRADE FEED INCH 1/ 0.010-0.Turning NOTE In grinding chip breakers.005-0. Table 2-9. allow for chip to clear work or rough f inish will result. Tool Angles . It is generally preferable that material be moderately hardened (Brinell 200-240) for best machining. 020 to 0.005 0.006 0. however. care should be taken to avoid unnecessary weakening of support for cutting edge. 440.002-0. 2-69 . in grinding the lands. 2-95. grade. 442.T. controlling of heat build-up is of utmost importance to meet dimensional requirements. 446 302. 304.025) with clearance (3o-10o primary angular) behind cutting lip to reduce frictional heat resulting from rubbing. 420. Once cutting is started. CAUTION Before starting operation/equipment. 17-7PH. Suggested Milling Cutting Speeds and Feeds ALLOY TYPE/GRADE 301.006 SPEED SFPM 35-70 30-95 35-90 35-70 50-100 50-130 35-80 TOOL MATERIAL High Speed Steel High Speed Steel High Speed Steel High Speed Steel High Speed Steel High Speed Steel High Speed Steel 403-410. and f low of coolant/lubrication. The information in these tables is only provided as a starting point. Cutter lands should be ground to narrow width (0. High speed tool steel is used for most milling on stainless. As a further measure against rubbing.008 0. successively on alternate sides and half the bottom. material hardness. FEED INCH 1/ 0. etc. angles. 430 440F 303 430F. Cutters for Milling. 316. In close tolerance work. The recommended cutting speeds. However more power and rigid support of tool is required to accomplish cutting due to inherent strength and toughness of the various stainless alloys. This problem can be controlled in most cases by adjusting cutting speeds. 347. tool angles. carefully check for proper set up. and use of proper lubricants in adequate quantities. The use of helical cutter minimizes vibration and chatter especially when cutter/cut exceeds 1 inch. 2-90. such as cemented carbides. The recommended cutting speeds.002-0. In milling the corrosion resisting steel. Naturally the continuous operation will depend on satisfactory operation of equipment and other factors.002-0. 2-93. method of grinding. Heat conduction of the chromium-nickel grades is about 50% slower than the carbon steels. 17-4PH. 2-94. 314. 416 420F 1/ Use heavy feeds for rough cuts and light feeds for f inishing. tools. capacity of equipment and cost of tooling for specif ic uses requires consideration. The other grades are used under certain conditions.008 0. The exact amounts the land is ground will depend on diameter of cutter. However.008 0. tool angles and feeds for turning corrosion resisting steel are cited in Tables 2-8 and 2-9. or as a guide. 2-91. safety. MILLING CORROSION RESISTING STEEL.002-0. 431.002-0. All the standard cutter designs used for cutting carbon steel can be used to cut stainless but preferred design is those with helical (spiral) teeth. 2-92. On side cutter. diff iculty will be experienced from heat build-up. 310. 1-1A-9 2-89. running condition of equipment. Chip removal and loading of cutter can be aided when milling slots by staggering teeth to cut Table 2-10. a secondary clearance of 6o-12o starting at the back of the land is recommended. it should be carried to completion to avoid the effects of changes in metal temperature. The same general procedures/equipment are used in working stainless as those used with carbon steel.002-0. 321.O. angular clearance of 3o to 10o to avoid frictional heat and rubbing is recommended. and feeds for milling are cited in tables 2-10 and 2-11.002-0.007 0. 309. rigid support of work and cutters. and to prevent seizing of chips to cutting edges. Lubrication for Drilling Stainless. 2-98. Special types are used for drilling grades (420. 446 SPEED SFPM (APPROX) 20 40 30 35 60 20 30 40 80 50 75 95 40 60 NOTE Do not let drill ride on work to prevent work hardening and heat damage to drill. 2-99. Lubrication for Milling. 316. and feed per revolution should be 0.005 for holes up to 1/2 2-70 .Milling TOOL ANGLES Rake Radial 1/ Rake Axial 1/ Clearance Land Width TOOL MATERIAL HIGH SPEED STEEL CEMENTED CARBIDE/C 10 -20 4 -8 o o o o ALLOY Use lower angle Use lower angle Approximately same Approximately same 30o-50o 1/64″-1/16″ 1/ Saws. 410 416. When drilling the free machining 400 series grades the angle is reduced to 118o-130o. 2-102. The webb support for the point should be as heavy as possible. Drill point/tips for use with the chromium-nickel grades are usually ground with 135o-140o (included) angle and 8o-15o lip clearance. 310 303 309. Table 2-12. etc. it is advisable to leave suff icient stock to insure that cutting will occur behind the work hardening surface resulting from drilling. are sometimes used with rake angle as low as 0 degrees. The lubrication of milling cutter is very important to control generation of heat which is considerable in cutting all grades of stainless. DRILLING CORROSION RESISTING STEEL. The recommended lubrication for general use and light drilling is soluble oil. 2-97. Speeds used for drilling the corrosion resisting steels should be closely controlled to prevent hardening of metal and excessive drill damage from heat. Due to the work hardening characteristics of the corrosion resisting steel.. 1-1A-9 Table 2-11. Utilization of adequate lubrication/ coolant is of utmost importance in drilling stainless due to poor heat conduction of this material. Drilling Speeds for Corrosion Resisting Steel GRADE TYPE 301. 430F 420 AB & C 442.O.007 inch. thinning of the webb at the point will relieve point pressure. The sulphurized oils diluted to desired viscosity with paraff in oil are usually satisfactory. 440. These spiral f luted reamers are used to help alleviate chatter and chip removal that are associated with the straight f luted reamers.) that are abrasive due to high carbon content. REAMING CORROSION RESISTING STEEL. The cutting oils used should be applied in large quantities directly on the cutter and zone of cut. see Table 2-12. 304. 2-101. The recommended material to be lef t for reaming is 0. and miscellaneous prof ile cutters. Drills for use with the corrosion resisting steels are prepared with different cutting angles than used with carbon steel. 420F. Suggested Tool Angles . High speed steel drills are commonly used for drilling stainless.003-0. 347 403. however. sulphurized mineral or fatty oils. etc. 321. Speeds for drilling the high carbon types are usually reduced 25-50%o in comparison to the other grades.003-0. On larger diameter drills use chip curling grooves to help expel and prevent chip accumulation in area of hole being drilled. The recommended reamer for the corrosion resisting steels is the spiral f luted type which is made from high speed steel/carbide tipped. For general illustration of point designs see Figure 3-2. 2-96. 302. For suggested drilling speed using high speed steel drill bits.T. form relieved cutters. 2-100. and for heavy work. 1342±0. better results can sometimes be obtained by modif ication of taps (in shop) as required and by use of two f luted type Table 2-13. Lands are narrowed by removing about half the threading area from each land. 347. 416.100 SFPM. 442. 431. and for 309. Cutting edges are relieved by grinding a 2o5 radial taper on each land.010 for reamers up to 1 inch diameter.1100±0. 302. 0. 316.1380 0. TAPPING CORROSION RESISTING STEEL. 0.O. Tapping Allowances (Hole Size to Screw Size) THREAD/SCREW SIZE 4-40 MAJOR DIA. 2-103. For instance modif ication of taps can be accomplished by grinding longitudinal grooves along the lands.0960-41 THREAD DEPTH PERCENT 95 90 80 71 49 95 83 72 54 97 77 65 96 87 69 57 6-32 0. The portion removed should trail the foremost cutting edge.1250-1/8″ 0.1360-29 0.012 inch) to reduce rubbing and frictional heat. 440F and 303 --35 .1144±0. Conventional or standard type taps are used with stainless. however.1405-28 2-71 . Also.T. b.1160-32 6-40 0. omission of cutting edges on alternate threads and relieving cutting edges will reduce binding and frictional drag.0860-44 0.1065-36 0. 304.0871±0.0890-43 0. provide additional clearance for chips and compensate for the swelling which is encountered with the sof ter temper material.1640 0. cutting edge should be ground to have positive hook/rake 15o-20o for sof ter material and 10o-15o for harder material.1200-31 8-32 0. These modif ications will also aid in distribution of lubrication to cutting area. 2-105.1285-30 0. The recommended speed for reaming types 301. Trial should be conducted to determine best cutting for indivldua1 operations.0100.0810-46 0.0035 0.0995-39 0. 440.75 surface feet per minute.1040-37 0. 1-1A-9 inch and 0. 403 and 410 is 20 .005-0. for 430F. 420F. 2-104. The land should be ground with a clearance of 4o-7o (and width should not be reduced below 0.1100-35 0.004 0.002 DRILL SIZE DECIMAL & NR 0. 310. Reamers for cutting stainless should have a 26o-30o starting chamfer with a slight lead angle behind the chamfer of 1o-2o for about 1/8-3/16 inch on the land to reduce initial shock of cutting. taps for small holes. 430. o c.1120 MINOR DIA.004 0. Speeds for reaming will vary according to type of material being cut. 426 20-60 SFPM.827-45 0. The modif ication is usually accomplished as follows: a. Longitudinal grooves are ground down the center of each land about 1/3 to 1/2 thread depth and 1/3 to 1/2 approximately of land width.1380 0. 321.1130-33 0. 4579±0. Due to high strength and poorer cutting quality of the stainless series steels. Tapping Allowances (Hole Size to Screw Size) .4531-29/64″ 0. 75% thread depth is generally used as maximum 2-72 . holes for tapping are usually made as large as possible consistent with f it specif ied by drawing or other data.2143±0.2090-4 1/4-24 0.1960-9 2031-13/64″ 0.2500 0.1593±0.3750 0.1850-13 0.2500 0.002 0.1990-8 0. and on through holes.2010±0.O.003 DRILL SIZE DECIMAL & NR 0.T.3320-Q 0. it may extend over 3 or 4 threads 2-107.3125 0.4687-15/32″ 2-106.3390-R 1/2-24 0.002 0.1695-18 THREAD DEPTH PERCENT 93 83 71 59 50 100 96 87 78 63 100 86 75 68 88 80 67 95 86 75 65 86 70 66 86 57 1/4-20 0.1610-20 0.1935-10 0.2770-J 3/8-24 0.2500 0. the tap basically should have a taper/chamfer of about 9o with center line on the starting end to facilitate entry into hole. 0. In addition to the above.003 0.Continued THREAD/SCREW SIZE 10-32 MAJOR DIA.1900 MINOR DIA.2090-4 0.2610-G 0.2708±0.0032 0.3281-2 1/64″ 0. The taper should be held short (1st thread) for blind holes.2090-4 0.1562-5/32″ 0. Actually due to the higher strength of this material less thread area or engagement is required in comparison to most other metals.2193±0.1875-3/16″ 0.1660-19 0.2130-3 0.2656-17/64″ 0. 1-1A-9 Table 2-13.3278±0. 0.2720-1 0.2187-7/32″ 5/16-24 0.5000 0.003 0. Due to the above and the fact that less cutting is required.2130-3 1/4-28 0.1520-24 0.005 0. 062 inch. and for light work.O. 2-112. Oil f low/application should be applied before tapping commences to prevent initial congestion of cuttings. the blade should not be allowed to drag/ride on the return stroke.T. a light grade cutting oil. especially with the 300 series types to prevent work hardening. The teeth per inch for saw blades average 8-12 and speed of saw travel usually ranges from 50-100 feet per minute depending on type and temper of material being cut. aids in chip removal. SAWING. With the power hack saw. tubing. Power hack saws are used for heavy cross-cutting section bars. tubing material is run at slightly higher speed. etc. Hack saws (mechanical drive). Pages 2-75 through 2-120 deleted. However. speeds range from 100-125 feet per minute for material under 0. Figures 2-2 and 2-3 deleted. 2-116. The decreased thread depth also reduces tendency to gall and seize.062 and 60-100 FPM for thickness over 0. The lubricant serves to prevent overheating as well as lubrication. The deeper cuts are used to get under work hardened surface resulting from previous cut (stroke). 2-111. Band saws are well suited for low speed (straight line/contour) sawing of stainless/corrosion resisting steel within prescribed limitation. The 18-8 (300 series) are usually tapped at 10-25 SFPM except for the free machining types which are tapped at 15-30 SFPM. Lubrication for Tapping. 2-114. The teeth area should be of wavy construction to increase width of cut area to prevent binding. As general guide. 1-1A-9 unless otherwise specif ied. etc. and effect of swelling in sof t material. deeper cuts are made at relatively low speed. Higher percentages of thread depth are necessary in material when stock is not thick enough to permit the required number of thread. Band Sawing. temper. the friction cutting method may be employed. 2-115. Lubricants should not be used. etc. As with cutting other metal. Coolant/lubrication is essential to prevent excess blade damage from heat. the band saw velocity ranges from 5000 FPM for cutting f lat 1/32 inch material to about 10. Change 1 2-73/(2-74 blank) . saw selection. Lubrication recommended is soluble oil/water mixed about 1 part oil to 4 parts water for heavy work. speeds usually vary with the physical properties. Heavy pressure to maintain cut is not usually necessary. The hack saw blade should be lightly lubricated with lard oil/other cutting oil for best results. rates range from about 100 FPM for light gauge to 15-18 FPM for 1/2 inch material. The lubrications recommended for tapping are sulphurized mineral oils with paraff in and lard oil. Tapping speeds used for stainless should be slower than those used for carbon steel. Tables 2-14 through 2-33 deleted. Saw blades must be kept in sharp condition for effective low speed sawing. 2-108. The straight-chromium 400 series generally is tapped at 15-25 SFPM. tap wear. Feed for this method can be considerably higher than is used for slow speed cutting. In utilizing the friction method. except the free machining grades.000 FPM for 1/2 inch and 14. Pressure should be just suff icient to create proper heating and sof tening at cut point without forcing the saw. 2-109. of type/grade being cut. power required to drive tap. Tapping Speeds Corrosion Resisting Steel.000 for 1 inch material. Saw teeth per inch varies from 18 for material below 1/ 8 inch thick to 10 per inch for thicknesses over 1/2 inch. 2-110. 2-113. Hack saws (hand) for cutting corrosion resisting steel should be of high speed steel with approximately 32 teeth per inch for light work and approximately 24 teeth per inch for heavy work. The saw manufacturer’s recommendations should be followed for cutting speed. Paragraph 2-117 through 2-227 deleted. For tapping allowances of some size screws/bolts see Table 2-13. For faster cutting with the band saw. which are tapped at 15-35 SFPM.. and if applied under pressure. . Personnel assigned to accomplish designs. 2-231. The information furnished in this section is provided as a guide to aid personnel engaged in the use and application of the ferrous alloys. beat treat. 2-237. experimentation trial and further study will be required. Due to varied usage of steel products. (Deleted) (Deleted) (Deleted) (Deleted) (Deleted) (Deleted) reading. etc. application and fabrication must be well trained in fundamentals of metal forming practices. e. The following general rules should be employed in handling and forming: 2-234. In many instances. c. painting. analysis. welding. Method to be used for fabrication. 1-1A-9 2-228. properties. etc. assembly. blue print Change 1 2-121 . corrosion control. Also.O.. Corrosion resistance to certain chemicals/ environments. Fatigue properties under cyclic loads. The section of steel for design or application to equipment and component is usually based on the following: a. in accordance with scope of relation to fabrication process. machining.. 2-236. plating. forming. details and rules related will not f it every application. b. FABRICATION OF FERROUS ALLOYS. heat treat. riveting. i. machining. 2-232. Temperatures to which part will be subjected.T.e. these personnel must keep constantly abreast of advancing processes for maximum eff iciency/prof iciency. 2-233. 2-229. welding. Strength and weight requirement of part/ equipment to be fabricated. 2-230. d. etc. 2-235. For long production runs. and material from which dies are made. etc. free of nicks. b. are essential to successfully draw form steel.. Sheared or cut edges shall be sanded. When in doubt inquire. remove all cutting lubrication. plating or painting process. CAUTION Machines rated for carbon steel shall not be used over 60% of rated capacity when cutting. other approved material and good cleaning procedures. prior to any heat treat. sheared/sawed strips and blank shall be handled with care to prevent cutting and other parts of the body. Blank hold down pressure and drawing rings.O. Polished sheet material should be protected when forming to prevent die tool marking. 1-1A-9 a. high chromium steel is recommended to manufacture drawing dies because of wear resistance and hardness. 2-239. The use of heat treated formed sheet metal parts on aerospace craf t are usually an exception in part due to above and most materials are used in the normalized or annealed condition. etc. If parts show presence of above. forming or machining stainless steel unless approved by responsible engineering activity. Control of die design. f iled. Hold down pressure should be suff icient to prevent wrinkling of material. with bare hands af ter cleaning and subsequent to heat treating/ passivation because f inger prints will cause carburization and pitting of surface. Some diff iculty will be encountered from warping due to treat treating and precautions must be taken when forming the material to prevent sporadic or uneven stress in the work piece. increase radius by one thickness or more until diff iculty does not exist. etc. etc.. Sheet. grain. rust. b. especially corrosion resistant steel. or bend cracking. The removal of rough and sharp edges is also recommended prior to accomplishing other machining operations to reduce hazards in handling. For recommended General Bend Radii for use on Aerospace weapon/equipment (see Table 2-34 for Low Carbon/low alloy steel and Table 2-35 for Corrosion Resistant Steel. Finish of die-all scratches and surface roughness should be removed. BENDING (SINGLE CURVATURE). g. Form material across the grain when possible using correct or specif ied bend radii. 2-238. The bending of most steel sheet and thin bar stock can be readily accomplished provided that equipment with adequate bending and cutting capacity is available and if the materials are formed in the sof t condition/lower temper range. degreasing. or polished prior to forming. In utilizing Table 2-34 and Table 2-35 it is recommended that in practice bend area be checked for strain. d. f. Radii used for forming or bending. lathes. Observe load capacity of equipment such as brakes. c. parts will require jigs or close control during the heating and cooling phase of heat treatment. Hardwood and phenolic can be used in some cases for piece production where draws are shallow.) 2-240. 2-242. Surfaces of material. usually equal to 3-6 times thickness of material depending on specif ic requirements. rolls. shears. high carbon. mills. The heat treatable alloys are usually formed in the annealed or normalized condition and heat treated if required/ specif ied af ter forming.T. Other details. on: Successful drawing of steel will depend a. shall be used when specif ied. etc. pickling. drills. inspection requirements. due to possible fatigue or stress corrosion failure. Kirksite/case zinc alloy can be used with drop hammer hydraulic press if the draw is not severe. burrs and foreign material. etc. and the severity of draw. Springback allowance will vary according to the type and temper of material being formed. ways. Also. when heated. e. but not to the extent that would prevent f low of the metal into 2-122 . In addition to above. CAUTION Avoid handling parts. The use of sharp bend radii on parts for aeronautical application shall be avoided and other application where the parts will be subjected to f lexing (cycle) or concentrated stresses. foreign particles. Tool and equipment shall be maintained smooth. Use moderate radii. 2-241. presses. tape. These surfaces can be protected using non-corrosive paper. Also provide bend relief in corner when required. shall be protected from scratching. Af ter forming/machining is completed. shall be checked for alignment tolerances.. periodically/ each set-up. c.. For medium and short production runs. DRAW FORMING. especially f inished sheet. dies. by cleaning. etc. Drawing using a hydraulic powered press in lieu of a cam operated or toggle type press is usually the most satisfactory. e. or as desired. The preheating tends to reduce work hardening and the requirement for intermediate annealing during the drawing operation. size requirement must be considered. Excessive distortion may result from f inal annealing af ter last draw. Drawing Speed . 2-244. such as obtained by pickling (dull surface) improves control of metal under hold down pads and the holding lubricants.. Af ter size is determined by trial. Other compounds such as tallow. The ram pressure suff icient to cause the material to stretch and wrap to contour of the die form blank is applied perpendicular to the blank (see Figure 2-4). lubrication. In instances where draws exceed 22-25% annealing is recommended af ter completion of the drawing operation followed by descaling and passivation (stainless). It is recommended that part be cleaned and annealed following each draw. the blank should be f iled/polished to prevent cracking in wrinkle/stress areas. Drawing rings radii should be 4-8 times metal thickness and smoothly polished. mixture of mineral oil and sof t soap. f iling. using a very ductile material to determine blank size and stress areas prior to starting the forming operation is recommended. When trimming. One heavy bodied lubricant used is lard oil. STRETCH FORMING. 2-247. the majority of drawings will occur on wider portions of the rectangle away from the corners. which will damage the surface. clearance (drawing) should be increased when clearance is increased. Lubricant . The surface condition of the blank also has an effect on drawing. other foreign material. the radius of the vertical corner should be approximately 10% of the width.O. 1-1A-9 the female portion of the die. h. Parts should be cleaned removing all lubrication and other contaminate prior to annealing and desealed af ter annealing. Trial.Compounds used should be of heavy consistency capable of withstanding high temperature and restating pressure necessary to form material. 416. sheet or strip. before heating or annealing and upon completion of forming or drawing operation. Restriking on f inal stage die to remove distortion af ter f inal anneal is permissible without further heat treatment.430. is stretched beyond the elastic limit until permanent set will take with a minimum amount of springback. sulfur (one pound of sulfur to 1 gallon of oil) to which lithopone is added in equal parts until consistency equals 600W engine grease. The stretch forming is usually accomplished by gripping ends of material (blank) and applying force by a separate ram carrying the forming die.Generally a speed of 2055 feed per minute is satisfactory.Generally punch clearance should be about 1 1/4 to 1 1/2 times thickness for the initial draws. 2-246. consideration must be given to the fact that on rectangular parts. Temper-drawing should be started with annealed/normalized material and intermediate annealing accomplished as required. g. the f irst operation should be a moderate draw with punch diameter equal to 60% of blanks diameter and reduction of 15-25%. especially where free f lowing drawing methods are used (without hold down). Failure to clean the parts will result in pitting and carburization. On the other hand. The second and subsequent draws should be made with punches about 20%. the roughened surface may be less desirable because of greater friction. by reducing the severity of the last draw or restriking af ter f inal annealing on last stage die for the purpose of removing distortion. d. CAUTION Parts shall be cleaned of all contaminates. A slightly roughened surface.. and when reduction exceeds 8-15% on each following draw. The requirement for annealing (intermediate) usually is needed af ter reduction exceeds 30-35% for stainless/20-25% carbon steel on the initial draw. Blank size and preparation . 446) can be improved by preheating dies and blanks. When forming involves more than one draw. This problem can be overcome in most instances. To overcome this problem. and about 1 1/8 to 1 1/4 times for the following draws. Where facilities are available. Clearance between punch and die .T. Stretch forming is a process where material. 2-243. This method of forming is 2-123 . f.A good practice is to use minimum size required to meet dimensional size of parts and for hold down. 2-245. 442. handling hazard and surface friction which hinders f low of metal into die. etc. powdered graphite mixed to thin paste with lightweight oil can be used. cold forming of some steels (primarily straight chromium stainless such as 410. If parts show signs of galling. Those steels that have low yield strengths in the sof t/annealed condition. and curved pan shaped parts containing f lat areas. are more economical than permanent dies. beads. The trimming of edges and removal of nicks and scratches is important to prevent starting points for concentrated stress. Normally. because less pressure is required to form metal and springback is lower. The rubber pad hydraulic press is used to form relatively f lat parts having f langes. It is recommended that additional rubber be supplemented in the form of sheets (usuually l/2 . rings. deburred. 2-251. DROP HAMMER FORMING. another method of alignment and holding of blank must be utilized. clamping pressure is suff icient to hold part. or carbon steel. kirksite/ zinc cast alloy. facilities are provided to apply pressure at a uniform rate.T. 2-250. Form blocks are usually manufactured from steel. reverse curves. another aid that may be necessary is to anneal material between die stages and intermediately for single stage die forming. The work is accomplished by setting the form block on the lower press plate or bed. 2-254. Manual spinning is usually accomplished on a lathe specif ically adapted and f itted for that purpose. wooden mallet to remove wrinkles. drop hammer forming is accomplished without benef it of hold down. and as the hydraulic pressure (applied by a ram to the head) increases. under tension loads. the rubber envelopes the form block forcing the blank to conform to the form block contour or shape. CAUTION Parts should be cleaned prior to annealing to protect f inish. spinning tools are the roller or round nose type designed in such a manner that high pressure can be applied without bending. such as shallow dishing. The direction of major tension (stretch) and direction of grain is also important. and tools are of proper design. The sheet metal blank should be cut to size (allow suff icient material to form f lange). Form blocks for spinning are usually made of phenolic. 2-252. and some types of hard molding plastic with high impact strength. hardness. In many instances.’’ which prevent slippage of blank when pressure is applied. Af ter the block is prepared and placed on the plate. hardness of 70-80 durometers) over the form block and blank to prevent damaging the rubber press pad. These dies can be rapidly produced. etc. etc. for piece production from phenolic and hardwood. Normally. and hard forming such as bumping hammer. the rubber pad f illed press head is lowered or closed over the block. SPINNING.O.. stiffners. The form for forming f langes on ribs. Annealing of the part at intervals also aids the operator when manual spinning. The metal is slowly forced in shape by controlling the impact of blows. and low rates of work hardening are the best grades for spinning. Forming dics/blocks for general production are made from kirksite/zinc. which. Where local design of tools are 2-124 . it will be necessary to use a combination of hand forming shrinking/stretching using supplemental machinery and pressing to complete forming by this method. can be melted and recast. To successfully complete forming operations. Lubrication aids in uniform distribution of stress and the lubricant shall be applied uniformly to work piece to avoid distortion which could result from unequal friction when material is sliding across the forming die during stretching. supplemental equipment. Dies for drop hammer forming are usually made by casting metals such as kirksite. and the blank is placed on the block. and radius. alloy. In some cases. hard wood. 2-249. should be undercut approximately 2-8 degrees depending on the alloy. 1-1A-9 usually limited to parts with large radii of curvature and shallow depth.1 inch. The blank is held in place on the block by locating pins (holes are drilled through the blank and into the form block for the insertion of the locating pins). The design of form blocks for hydropress forming requires compensation for springback. Care should be taken to remove all traces of zinc that may be picked up from kirksite forming dies. lightening holes. would tear. phenolic (mechanical grades). and f iled prior to pressing. it is necessary to use drawings. The main requirements are that required speed be maintained without vibration. as failure to remove the zinc will result in penetration of the steel (stainless) when treated and will cause cracking. intermediate annealing and 2-3 or more stage spinning blocks are used. It is recommended in forming that the major tension be transverse to the direction of grain. and for very light drawing of pan shaped parts having large radii. If tooling holes are not allowed. 2-253. 2-248. 2 or 3 stage dies. such as tool steel for long production runs. and can be reinforced at selected points of wear by facing with harder material. To overcome work hardening problems. These holes are referred to as ‘‘tooling holes. Some types and kinds of plastic with good hardness and high impact strengths are also used. the case is not as hard as obtained with other carburizing steels. and free of nicks. and have good drawing qualities. This group of steels is used where cold formability is the main requirement. The basic advantages of this group is high strength coupled with fair ductility and abrasion resistance. Plain Carbon Steel . However.125 inches thick. This series is not used where great strength is required. 2-263. is a carburizing grade with extremely high strength core.chromium alloys. and heat treated af ter fabrication. and to assure clean. 2500 Series Nickel Steel. 2-256. 2-261. and normalized condition. Double shear should be used when possible to minimize off balance condition and load. it is important that shear action be incorporated to equalize and reduce load. 1100 Series Steel. 2-262. SHEARING AND BLANKING. To prevent damage to shear. PLAIN CARBON AND ALLOY STEELS. annealed. Punches and dies should be maintained in clean sharp condition and lubricated by swabbing or spraying material to be punched with lightweight lube oil to prevent galling and to aid in keeping punch/die clean.1030 through 1050. Plain Carbon Steels . 2-257. BLANKING AND PUNCHING. This group of steels have good impact strength and require close control of heat treatment practices to obtain the required strength and ductility. Type D2.T.SAE 1016 through lO30. 4100 Series Chromium . This group of steels is commonly known as the carburizing or case hardening grades. Where only one shear is available.006 could be used for general shearing of sheet stock up to 0. The addition of manganese improves machining qualities but reduces the cold formability characteristics. This series of steels is characterized by good wear resistance and tough core and surface. Excessive blade clearance should be avoided to prevent work hardening of cut area which increases susceptibility to stress corrosion and burring. This steel is more diff icult to handle in fabrication and heat treatment than lower nickel . 2-267. 4000 Series Molybdenum Steels. NOTE These grades not currently being produced. such as 1040 are of ten cold drawn to required physical properties for use without heat treatment. The higher carbon groups. NOTE These grades not currently being produced. This group (medium carbon types) is used where higher mechanical properties are required. used for wire and rod for cold upsetting applications. 2-269. blades or knives must be maintained in sharp condition. This group is easily fabricated by forging 2-259. 3100. 2-264. Also. hardened to Rockwell C40-50. The main use of these steels is for screw stock. clearance between shear blades should be approximately one-twentieth (5%) thickness of material to be cut. The strength and hardness of these grades will vary according to carbon content and amount of cold work. Alloys 1030 . Blanking and punching requires close control of die clearance.O. The major use is in the manufacture of forgings. This group is widely used for forged stock. 2300 Series Nickel Alloy Steels. Listed for reference only. In designing dies and punches. This material is normally machined in the forged. The 3300 series is used primarily in the form of forgings and bars which are required to meet rigid mechanical properties. shearing action of punch/blanking die. response to heat treatment. 1-1A-9 required. clean. and is heat treated before use in partically every application. 2-258. Lubrication such as lightweight engine oil or soap should be applied at regular intervals to prevent galling and to clean blades for prolonged shear blade life.Molybdenum Steels.1035 are 2-125 . This series almost without exception. a clearance of 0. and 3300 Series Nickel Chromium steels. 2-260. and high wear resistance.005 to 0. accurate cuts. Plain Carbon Steels . Steels in this group are generally used where easy machining is the primary requirement. This alloy group is used where wear resistance resulting from high carbon content is needed. 3200.1055 through 1095. 1300 Series Alloy Steel. Alloy Steels . Clearance for blanking and punching should be 5% of thickness and closely controlled for all gauges. 2-255. This series has good working properties. 2-266. such as bolts. raw material for manufacture is obtainable under QQ-T-570. The lower carbon and manganese types are used for most cold formed parts. GENERAL FABRICATING CHARACTERISTICS. This steel is used for parts requiring a high strength core and good wear resistance.1006 through 1015. 2-265. The addition of nickel has very little effect on machinability and greatly increases elasticity and strength. 2-268. 1-1A-9 and rolling.O. The straight chromium grades such as 410.Molybdenum Steels.. These steels have approximately the same characteristics as the 4300 series steele. 442.Chromium . 304. 2-275. The use of sharp radii shall be avoided where parts are subjected to f lexing or concentrated stresses due to possible fatigue or stress corrosion failure. 2-271. if required. shall be considered. Recommended bend radii for use with stainless is shown in Table 2-35. more power is required to form these types than is required for carbon steel because of higher tensile strengths and the fact that yield strength increases rapidly during forming or bending. 304 and 305) have forming characteristics superior to plain carbon steel because of the wide spread between tensile and yield strength. This steel is used for structural. machined and forged parts over 1/2 inch thick. internal stresses produced should be relieved and loss in strength regained by normalizing. 2-283. and are stable at high temperatures. Draw Forming. Some types (302. and stablized grades 321 and 347. 304. the severity of the forming operation must be reduced to compensate for the prehardened material.e. 304. etc.e. 305. Forming and welding operations are accomplished utilizing annealed material. It is usually obtained in the normalized condition. a radius equal to 3 times the thickness is recommended. and 446 react similar to carbon steel and are somewhat less ductile than the 300 series stainless. welding of the f inished parts. The most common types of corrosion resistant steel used for drop hammer forming are 301. This grade has very good cold forming characteristics. especially if using type 301. 430. Yield strengths are also higher which means that more power is required for bending and forming. it may crack. 2-272. 302. 410. However. and 9900 Series Steels. The fabrication of stainless steel requires the use of modif ied procedures in comparison to those used for carbon steels. 430. 2-284. 2-277. i. 4300 Series Nickel . 8600. bar. 302. generally have good forming and drawing qualities. These steels are characterized by their high impact strength and resistance to fatigue.4 hours. based on a 50% reduction. 321. 305. 431. a shape 8 inches in diameter and 4 inches in depth could be drawn in one operation. The corrosion resisting series. 8700. The tensile strength are higher than carbon steel and consequently will stand higher loads before rupture. and heat treated or normalized af ter these operations are completed. rod and tubing. and hardness should not exceed Rockwell B90. They are easy to forge and machine.. 2-282. This grade is used extensively in aircraf t construction in the form of sheet. Af ter welding and cold forming. The condition of material for best forming should be annealed.T. In the normalized condition. 416. 2-274. If this material is not relieved in 2 . 347. The 301. 2-276. The strains set up by severe reductions (above 45% with chromium-nickel types and 20% with straight chromium types) should be relieved by annealing immediately af ter the operation is completed. Drop Hammer Forming. The beat drawing grades are of the 18-8 series. Forming Sheet Stock. 302. i. 2-270. 2-279.. Forgings are always normalized or heat treated af ter fabrication. Preparation for machining or forming must be by a suitable annealing cycle. It is possible to form some type (301 and 302) in 1/4 and 1/2 hard condition. types 301. 2-281. However. Because of the ductility factor of this series drawing and forming should be limited to 20 -25% reduction. and higher elongation. and naturally will vary according to the type of material being formed. 9300. Stainless steels should be annealed for draw forming. 4140 Series Steel. 2-126 . 9700. 4130 sheet (MIL-S-18729 can be cold bent in the annealed condition to an angle of 180o with a radius equal to the thickness of the sheet. These steels are used to meet conditions in which other alloy steels have insuff icient strength. 316. CORROSION RESISTANT (STAINLESS) AND HEAT RESISTANT STEELS. 9800. 305 and 316 types can be drawn based on a reduction of 35 to 50%. 2-273. 4130 Grade Steel. Springback allowance should be about 2 to 3 times the amount allowed for carbon steel. 301 work hardens more rapidly and is subject to strain cracking. 2-280. 2-278. 8000 Series Molybdemum Steels. In selecting the type for drawing. T. Stretch Forming 2-127 . 1-1A-9 Figure 2-4.O. 304 309.050 2T 2T 3T 2T 3T 0.0.250 1 1/2T 2T 2T --1 1/2T 2T Forging Temperature Ranges For Corrosion Resistant Steel TYPE/GRADE 301 302 303 304 305 308 316 321 374 PREHEAT oF 1500-1600 1500-1600 1500-1600 1500-1600 1500-1600 1500-1600 1500-1600 1500-1600 1500-1600 FORGING TEMPERATURE oF STARTING FINISHING 2050-2200 2050-2200 2050-2200 2050-2200 2100-2200 2100-2200 2150-2250 2100-2200 2100-2200 1600-1700 1600-1700 1700-1800 1600-1700 1600-1700 1600-1700 1600-1700 1600-1700 1650-1750 HEAT TREATED SEE HEAT TREAT DATA FOR ANNEALING AND STRESS RELIEF. SEE TABLE 2-3.187 2T 2T 3T 2T 3T Cold Bend Radii (Inside) Corrosion Resistant Steel Alloys Sheet Thickness = T (Inches) Alloy 201. 321.016 2T 2T 2T 3T 3T 0.025 2T 2 1/2T 2 1/2T 2 1/2T 2 1/2T 0. 0.032 2T 2T 3T 3T 3T 0.012 .0.040 2T 2 1/2T 3T 2 1/2T 3T 0.051 . 302 305. 347 405. 1-1A-9 Table 2-34.190 .020 2T 3T 3T 3T 3T Table 2-35. 2-128 .090 1T 1 1/2T 2T 3T 4-5T 1T 1 1/2T 0. Sheet Thickness = T (Inches) Alloy Temper 1020/1025 4130 Annealed 4130 Normalized 8630 Annealed 8630 Normalized 0. 430 17-7PH Temper Annealed 1/4 Hard 1/2 Hard 3/4 Hard Hard Annealed Annealed Table 2-36.125 2T 2T 3T 2T 3T 0. 202 301. Cold Bend Radii (Inside) Carbon/Low Alloy Steels Temper.T.0. 0. 310 316.063 2T 2T 3T 2T 3T 0.O. 410.051 1-2T 1-2T 2T 2T 3-4T 1T 1T 0. See Heat Treat Data Table 2-3 for temperatures. Spinning. The use of temperatures higher than those cited above should be avoided to prevent subjection of material to the carbide precipitation heat zone. ductility. 1-1A-9 Table 2-36. Hot Forming. See Heat Treat Data Table 2-3 for temperatures.O. The best grades for spinning are those that have low yield strength in sof t/annealed condition and low rate of work hardening such as 304. Hot forming is used to form shapes in stainless that cannot be accomplished by cold forming and for forging parts economically. Forging Temperature Ranges For Corrosion Resistant Steel . The straight chromium grades respond to spinning similar to carbon steel. The air hardening grades in tempers other than annealed may crack from thermal shock upon loading into a hot furnace. Diff iculty and variations depend on individual characteristics of grade to be worked. i. it is important that temperature be closely controlled.. especially with the air hardening grades. however.T. In either case. 2-289. Hot forming by methods other than forging is accomplished at somewhat lower temperatures. hardness and reaction to cold working. 2-287. The reaction of these metals to hot forming in similar to carbon steels. Upon heating to 800o-900oF. this is accomplished by fully annealing. Spinning procedures for stainless are similar to those used for other metals. 403. The straight chromium (type 400 series) are more responsive to hot forming than the chromium-nickel grades. Shears and other equipment rated for carbon steel should not be used above 50 . 305. The unstabilized chromium-nickel grades may be formed at temperatures up to 800oF and the extra low carbon grades up to 1000oF. CAUTION Difference in temper of raw material will result in variation of preheating. f inished parts should be relieved of residual stress and carbide precipitation which affects corrosion resistance. Shearing and Blanking. Shearing and blanking of corrosion resisting steels as with other fabrication processes requires more power in comparison to shearing carbon steel and most other metals. 2-286.e. 1400-1500 1400-1500 1400-1500 1400-1500 1400-1500 1400-1500 1400-1500 1900-2100 1900-2100 2050-2200 2100-2250 2000-2100 2050-2150 1950-2100 1600-1700 1600-1700 1600-1700 1600-1700 1600-1700 1600-1700 1950-2100 These grades shall be promptly annealed after forging because they air harden intently if allowed to cool from forging temperatures.70% of rated capacity when cutting stainless. more power is required. 2-285. Also. In using heat for forming. their tensile strength is 2-129 . ultimate strength. Mild warming above 200oF improves performance of the straight chromium grades. 410 and 416. yield strength. 2-288.Continued TYPE/GRADE PREHEAT oF FORGING TEMPERATURE oF STARTING FINISHING HEAT TREATED AIR HARDENING 403 410 414 416 420 431 440 NON-HARDENING 405 430 442 446 1400-1500 1400-1500 1400-1500 1400-1500 1900-2100 1900-2100 1900-2000 1800-2000 1750-1850 1350-1450 1300-1400 1300-1500 Post annealing required. Grades 403.T. 410 is accomplished in two temperature ranges as follows: a. Proper safety precautions should be observed in the event any welding or soldering operations are required 2-130 . or by metal spraying over similar or dissimiliar metal parts. parts shall be fully annealed under controlled conditions by heating to 1550oF and holding.Iron. forming and perforating of the item has been completed. which will be painted prior to being placed in service unless other wise specif ied by specif ications MIL-F-7179. 2-294.O. 42C2-1-7. chromium. Porous coatings of the more noble metals such as silver. the 1400o-1500oF temperature is below the scaling limit and very close to being below the scaling limit for type 430. platinum. zinc. nickel.g. wear resistance. e. zinc includes all zinc parts such as castings as well as zinc coated parts. The following galvanic series table and dissimiliar metal def inition in accordance with MS33586 are for use as a guide in the selection of the most suitable plating for parts subject to uses where galvanic corrosion would be a prime factor. b. This temperature is recommended in view of the following: a. silver. nickel and chromium plating are used. nickel. It is usually specif ied when there is a need for surface characteristics that the basic metal does not possess. other than organic f inishes. and graphite. Metal plating is a process where an item is coated with one or more thin layers of some other metal. applied by hot dipping. 2-292. For types 442 and 446. 2-293. cobalt. the recommended temperature for forming is 1400o 1500oF. and aluminum and their alloys (Including the aluminum alloys in Group I). nickel plate. CADMIUM PLATING (QQ-P-416). Metals classif ied in the same group are considered similar to one another and materials classif ied in different groups are considered dissimilar to one another. GROUP I . chromium plate. STEEL SURFACE FINISHES. rhodium and rhodium alloys.1575o F. 5356. copper. and silver plating are the most commonly used. stainless steels.Magnesium and its alloys. the plating shall be applied af ter all machining. Aluminum alloys 5052. tin plate. The type of plated coatings is generally dependent on the characteristics desired. nuts and washers which are component parts of assemblies. Unless otherwise specif ied. and buildup of worn parts. titaniam. whether the zinc is electro deposited. Forming at this temperature is somewhat easier because strength is low and ductility is higher. and 446 be hot formed.Copper. The most commonly used types of plating are: Cadmium plate. For processing instructions. chromium. c. 2-295. For appearance. bolts. For protection against corrosion when appearance is unimportant. 2-290. GROUP II . slowly cooling to 1100oF (at approximately 50oF per hour) and then cooling in air. refer to T. When it is required that the non-hardening grades 430. Forming of the air hardening grades type 403. The advantage of forming at this temperature is that parts can be stress relieved at 1350o . GROUP III . d. Low temperature forming up to 1400oF. This is the type of f inishes generally used on ferrous parts. and phosphate coatings. TYPES OF PLATING. NOTE The above groups do not apply to standard attaching parts such as rivets. copper plate..Cadmium. The thickness of the plated coating is important since its protective value is primarily dependent on its thickness. 2-291. b. High temperature forming at 1525o . For hardness. or other approved data. 442. tend to accelerate the corrosion of steel. b. lead.1450oF to restore strength uniformity. 2-296. GROUP IV . for the purpose of aircraf t and aircraf t parts construction are separated into four groups in accordance with MS33586. and scaling is held at a minimum. 5056. DEFINITION OF DISSIMILIAR METALS. 1-1A-9 lowered considerably and at the same time ductility begins to increase. The four groups are as follows: a. platinum and gold. Heating these grades above 1600oF promotes grain growth which can only be corrected by cold working. welding. Effectiveness of most other metallic coatings depends on their ability to provide envelope or anodic protection.O. Dissimiliar metals and alloys. and 410 are not subject to loss of corrosion resistance due to the forming of intergranular carbides at grain boundaries. and tin and their alloys (except stainless steels). 6061 and 6063. gold. The metal/material referred to in the groups is the metal on the surface of the part. zinc plate. either cadmium or zinc coatings is usually used. Upon completion of forming at this temperature. brazing. The primary purpose of cadmium plating is to retard or prevent surface corrosion of parts. In 2-299. such as mild steel with unplated corrosion resisting steel. Heavy chromium electro deposits (0-1-10 MILS) are of ten used to salvage under machine parts. brazing. All steel parts having a hardness of Rockwell C40 (180. Unless otherwise specif ied. d. refer to QQ-Z325. Unless otherwise specif ied. Parts in functional contact where gouging or binding may be a factor or where corrosion might interfere with normal functions. Zinc shall be deposited directly on the basic metal without a preliminary plating of other metal. 2-298. forming and perforating have been completed. c. to relieve residual tensile caused by machining. d. plating is intended for wear and abrasion resistance. Hydrogen embrittlement relief shall be in accordance with blue prints and /or applicable specief ications. This coating is of two classes. grinding or cold forming. except in the case of parts made from corrosion resisting steels on which a preliminary plating of nickel is permissible. plating is intended for decorative plating. brazing. Parts shall not be reworked f lexed or subjected to any form of stress loads af ter placing and prior to the hydrogen embrittlement relief treatment.T. Zinc plating (Type 1) should not be used in the following applications: a.000 PSI or above shall not be plated. All steel parts having an ultimate tensile strength of 220. welding. Parts which in service are subjected to a temperature of 700oF or higher.000 PSI or above should be shotpeened prior to electro plating. the plating shall be applied af ter all machining. brazing. 2-297. welding. Class I. as required.000 PSI) and higher shall be baked at 375o± 25oF for 3 hours minimum af ter plating for hydrogen embrittlement relief.O. a low embrittlement cadmium plating bath shall be used. All steel parts having a tensile strength of 180. To restore dimensions. for wear resistance and corrosion protection. The general requirements for nickel plating are specif ied in QQ-N-290. To minimize the effect of dissimilar metal contacts. The primary purpose of zinc coatings is to retard or prevent the formation of corrosion products on exposed surfaces. all steel parts shall be given a stress relief at 375o ±25F(191o ± 14C) for 3 hours or more prior to cleaning and plating. c. Unless otherwise specif ied.000oF and other coating would not be adequate or suitable. Federal Specif ications QQ-P-416 should be used for cadmium plate requirements. welding. All plated parts which are designed for unlimited life under dynamic loads shall be shot peened in accordance with military Specif ication MIL-S- 2-131 . Critical parts should be magnaf luxed af ter plating.000 PSI or above shall not be electro plated without specif ic approval of the procuring service or responsible engineering activity. b. and Class II. Parts in contact with structural fabric structure. the plating shall be applied af ter all basic metal heat treatments and mechanical operations such as machining. unless otherwise specif ied. Grounding contacts where the increased electrical resistance of zinc plated surfaces would be objectional. Zinc Plating (QQ-Z-325). For additional information. Surfaces where free circulation of air does not exist and condensation of moisture is likely to occur. 1-1A-9 on cadmium plated parts because of danger from toxic vapors during such operations. Nickel shall be used for the following application only in accordance with MIL-S-5002: a. and Class lI. Nickel Plating (QQ-N-290). e. the plating shall be applied af ter all base metal heat treatments and mechanical operations such as machining. Class I. This coating is divided into two classes. Chromium Plating (QQ-C-320). As an undercoat for other functional coatings. Cadmium coatings should not be used on parts subjected to temperatures of 450oF or higher. Steel parts having a hardness of Rockwell C40 and higher shall be baked at 375o ± 25F for 3 hours or more and within eight (8) hours af ter plating to provide embrittlement relief. intended for use as a decorative coating. b. All parts having a hardness greater than Rockwell C40 and higher shall be baked at 375o ± 25oF for 3 hours af ter plating for hydrogen embrittlement relief. When permission is granted. CAUTION Chromium and nickel electro deposits severely reduce the fatigue strength of high strength steels. Where temperatures do not exceed 1. All steel having an ultimate strength of 220. addition high strength steels are susceptible to detrimental hydrogen embrittlement when electro plated. forming and perforating have been completed. forming and perforating on the article have been completed. For complete information pertaining to silver plating. 2-304. Plated parts below Rockwell C40 hardness and subject to static loads or designed for limited life under dynamic loads. Intended Use. When a plating is required it shall be in accordance with specif ication MIL-S-5002A or other approved technical engineering data. Silver plating shall be of the following types and grades: a. Phosphate Coating (MIL-P-16232). 0. such as nickel and chromium or combinations thereof. forming. The description of phosphate coatings herein is specif ied as ‘‘heavy’’coatings. 2-301. refer to MIL-P-16232. af ter shot peening and plating. but shall be treated by any method approved by the contracting agency. For the different classes of coatings and required supplemental treatments. Silver is of ten used as an antisieze and for preventing fretting corrosion at elevated temperatures.010 .for corrosion protection of nonferrous base metal. b. 2-302. Type m.for articles such as terminals which are to be soldered. Hardened parts which have been heat treated at less than 375oF shall not be heated as noted above.O. normally obtained from silver-cyanide plating solutions operated without the use of brighteners. or combinations thereof. 2-305. Grade B. Without supplementary tarnishresistant treatment. d. refer to Federal Specif ication QQ-S365. Plated parts below Rockwell C40 hardness which are designed for unlimited life under dynamic loads shall be shot peened in accordance with specif ication MIL-S-13165 prior to plating. All parts with a hardness of Rockwell C40 (180. Semi-Bright. b. brazing. friction and electrical load.210oF for 15 minutes (embrittlement relief). This coating should be applied af ter all machining. protective coating and easy solderability are of prime importance. Type II.0005 . Type ‘‘Z’’ (Zinc) coatings should not be used in contact with alkaline materials or temperature in excess of 200oF. On ferrous surfaces. Type ‘‘M’’ shall be baked at 210 . e. Sometimes obtained by polishing or by use of ‘‘brighteners’’. The following applications of thicknesses are for information purposes only: a. All steel parts subject to constant f lexure or impact having a Rockwell hardness of RC40 or greater shall be heated at 375o ±25oF for 3 hours for stress relief prior to cleaning and plating. need not be shot peened prior to plating or baked af ter plating.0005 to 0. With supplementary tarnish resistant treatment (chromate treated). Parts having a hardness of Rockwell C40 or higher shall be given a suitable heat treat stress relief prior to plating and shall be baked subsequent to coating as follows: a.0005 . phosphate coatings should be used with a suitable supplementary treatment. Light phosphate coatings used as a paint base are covered by specif ication TT-C-490. 2-303. any type is acceptable.001inch. c. Except for special purpose applications. Semi-lustrous deposits normally obtained from silver-cyanide plating solutions operated with brightener. steel parts plated with hard coating. Tin plating is used where a neat appearance. Af ter all base-metal heat treatments and mechanical operations such as machining. 2-306. welding.for electrical contacts. Grade A. Deposits without luster. Where a plating is required. Silver Plating (QQ-S-635).0003 . Matte.for increasing the electrical conductivity of base metals. 0. Tin Plating (QQ-T-425). welding and heat treatment have been completed. Type ‘‘Z’’ shall be baked at 200o . the total plated thickness shall not be less than 0.T. d. high electrical conductivity and good bearing properties.if the type is not specif ied. It is extensively used as an undercoating for nickel and chromium plating. forming and perforating of the article have been completed. Type ‘‘M’’ (Manganese) coatings are resistant to alkaline environments and should not be exposed to temperatures in excess of 250oF. Bright. 0. SURFACE TREATMENTS FOR CORROSION AND HEAT-RESISTING STEELS AND ALLOYS.000 PSI). shall be processed as follows in accordance with MIL-S-5002A: a. 0. 1-1A-9 13165 prior to plating. Silver plating (electro deposits) has high chemical and oxidation resistance.225 F for 1 hour. Unless otherwise specif ied. o o e. b. shall be baked at 375o ±25oF for 3 hours for hydrogen embrittlement relief. 2-300. b. Type I. The base metal for tinplate shall be low carbon cold steel. the shot peening shall 2-132 . c. Normally the corrosion-resisting and heat resisting alloys are unplated unless a coating is necessary to minimize the effect of dissimiliar metal contacts. depending on pressure. Vapor deposited coating’s are applied by exposing the base metal to a heated vaporized metallic coating such as cadmium and aluminum in a high vacuum. The foreign materials are removed from stainless to provide for uniform surface contact with oxidizing agents (Air or Acid) which forms the protective f ilm or passive surface. NOTE Af ter the parts are passivated they shall be handled the minimum necessary consistant with packaging. The protective f ilm formation is inherent with the stainless steels in normal air when they are clean. Vapor-deposited coatings can be obtained by processes in which a volatile compound of the coating is reduced or thermally decomposed upon the heated surface of the base metal. TYPES OF PROCESS I II III TEMPERATURE TIME (Minutes Minimum) 30 20 10 70-90 120-130 145-155 For parts made of ferritic or austenitic stainless use process Type I. In addition the times and temperatures shall be selected according to the alloy involved. For parts made of martensitic stainless steel. in specif ication MIL-C-8837. or other abrupt changes of section size where stresses will be concentrated. Af ter plating. use process Type II or III. Af ter cleaning the parts will be passivated by immersing in a solution of 2025% (Volume) nitric acid (Sp.T. Vapor deposited coatings are used to provide good corrosion resistance for steel and eliminate sources of hydrogen embrittlement. Parts for installations in high temperature areas shall not be handled with bare hands because f inger prints will cause carburization and pitting of surface when heated. which might contaminate the passivation solution and be a detriment to the passivation treatment shall be removed. or above. Unless otherwise specif ied. 2-308.5 2.O. 2-307. as damage to parts may occur. or above. oil.5% (Weight) sodium dichromate with process times and temperatures as follows: CAUTION Excessive time shall not be used. the shot peening shall be accomplished on all surfaces for which the coating is required and all immediately adjacent surfaces when they contain notches. The process is primarily a cleaning operation which removes the contamination and speeds up the formation of the protective (invisible) oxide f ilm which would occur naturally but slower in the presence of oxygen in a normal atmosphere. all grease. The stainless steels are usually passivated af ter fabricating into parts to remove surface contaminates. The metal coating forms by condensation of the vaporized coating metal on all exposed surfaces of the base metal. Within 15 minutes af ter above treatment. shall be baked at 375o ±25oF for not less than three (3) hours af ter plating. 2-309. Prior to accomplishing the passivation treatments the parts shall be cleaned.gr 1. thoroughly rinse in hot water (140oF .160oF). which may cause discoloration or corrosive attack af ter the parts are placed in use. 2-310. MECHANICAL-SURFACE FINISH. 2-311.42) plus 1. the parts shall be baked at 375o± 25oF for not less than three (3) hours. 1-1A-9 be accomplished on all surfaces for which the coating is required and on all immediately adjacent surfaces when they contain notches. In this case af ter the f ilm has formed the material is placed in a condition approaching that of maximum corrosion resistance. II or III. Plated parts which have a hardness of Rockwell C40.6% sodium dichromate (by weight) at 140 . The following paragraphs are concerned with mechanical surface f inish of the geometrical irregularities of surfaces of solid materials and established classif ication for various degrees of roughness and 2-133 . cadmium vacuum deposited. and are designed for unlimited life under dynamic loads. Plated parts which have a hardness of Rockwell C40. d. wax. Within 1 hour af ter hot water rinse. Any areas to which oxygen contact is prevented by contaminants or other means tends to remain activated and subject to corrosion attack. assembly/installation. Specif ic requirements for coating. VAPOR DEPOSITED COATING. f illets or other abrupt changes of section size where stresses will be concentrated. Surfaces will be considered suff iciently clean when a wetted surface is free of water breaks. PASSIVATION OF STAINLESS STEELS. and are subject to static loads or designed for limited life under dynamic loads or combination thereof. shall be shot peened in accordance with specif ication MIL-S13165 prior to plating. c. and rinse thoroughly with water and dry. f illets. and for coating. aluminum vacuum deposited. are cited in specif ication MIL-C23217A. immerse in an agueous solution containing 4 .160oF for 30 minutes. The surface chosen (unless already designated) for a specif ic application will be determined by its required function.7178 Cadmium Aluminum . Prof ilometers and other instruments used to measure surface height if calibrated in RMS (Root Mean Square) average will read approximately 11% higher on a given surface than those calibrated for arithmetic average.T6 Aluminum .T. For all other surfaces the f inish resulting from the machining method required to obtain dimensional accuracy is generally satisfactory.5052 Aluminum . etc.3003 Aluminum .Cathodic (Most Noble) 2-134 . such as the surfaces produced by machining and abrading (abrasive honing. Also associated with roughness high is roughness width. The values cited are microinches.6061 Clad Aluminum . Figure 2-5 shows the meaning of each symbol def ined. *When waviness width value is required.000063 inches average deviation from mean.7075 . Galvanic Series of Metals and Alloys CORRODED END . Waviness height rating (when required) may be specif ied in inches as the vertical distance from peaks to valleys of the waves. Designation of Surface Finish. grinding.T6 Steel or Iron Lead Tin Nickel (active) Inconel (active) Brass Copper Bronze Titanium Monel Silver Solder Nickel (Passive) Inconel (Passive) Silver Graphite Gold Platinum Protected End . f iling. Table 2-37.O. whereas waviness width is the distance in inches from peak to peak of the waves.2024 .T6 Aluminum .2017 .T6 Aluminum . for example 63 = 63 Microinches or 0. The symbol used to designate surface irregularities is the check mark as shown below.) The roughness height ratings are specif ied in microinches as the arithmetic average of the absolute deviations from the mean surface. the value may be placed to the right of the waviness height value. 2-313.7075 Clad Aluminum . Surface f inish should be specif ied for production parts only on those surfaces which must be under functional control. usually specif ied in inches and the maximum permissible spacing of surface irregularities.T4 Aluminum . is placed immediately below the right-hand extension. 2-312. Table 2-38 gives the typical normal ranges of surface roughness of functional parts. As the arithmetic average of the absolute diviations from the mean surface.6061 . when required. sanding. The surface roughness of a part is a measurement rating of the f inely spaced irregularities. 1-1A-9 waviness. **Roughness width cutoff value.2014 .ANODIC (LEAST NOBLE) Magnesium Magnesium Alloys Zinc Aluminum .2024 Clad Aluminum . 1-1A-9 Figure 2-5. Surface Roughness 2-135 .T.O. 1-1A-9 Table 2-38. Surface Roughness and Lay Symbols 2-136 .T.O. thermal and electrical conductivity. designated by this system except that the 4 digit number is pref ixed by an X.. 1-1A-9 SECTION III ALUMINUM ALLOYS 3-1. Designations for Alloy Groups OLD 2S 3S 4S 11S 14S R301 Core 17S A17S 18S 24S 19S 32S 50S 52S 56S 61S 62S 63S MA15 -72S 75S 78S 79S NEW 1100 3003 3004 2011 2014 2017 2117 2018 2024 2219 4032 5050 5052 5056 6061 6062 6063 7050 7475 7072 7075 7178 7079 MAJOR ALLOYING ELEMENT None (Aluminum 99. 3-3. i. 525. 758.9 which are 3-1 .00% minimum..00X) Manganese Manganese Copper Copper Copper Copper (Special control of impurities) Copper Copper Copper Silicon Magnesium Magnesium Magnesium Magnesium & Silicon Magnesium & Silicon Magnesium & Silicon Zinc Zinc Zinc Zinc Zinc Zinc 1XXX .O. The major alloy element for each type is indicated by the f irst digit (see Table 3-1) i. 243.. The common forms are casting. The present system utilized to identify aluminum alloys is the 4 digit designation system. hex. Table 3-1. CLASSIFICATION. sheet.Magnesium and Silicon 7XXX . etc.Magnesium 6XXX ..Other element 9XXX .Unused series The second digit of the destination indicates modif ication in impurity limits.. corrosion resistance to the atmosphere and many varieties of chemicals. Aluminum Alloy Designation and Conversions to 4 Digit System 3-2.. The above factors plus the fact that some alloys of this material can be formed in a sof t condition and heat treated to a temper comparable to structural steel make it very adaptable for fabricating various aircraf t and missile parts.e..Silicon 5XXX . etc. If the second digit is 0 it indicates that there is no special control on the impurities. Aluminum alloys are produced and used in many shapes and forms.. See Table 3-1 for complete listing.. COMMERCIAL AND MILITARY DESIGNATIONS. angles (extruded and rolled or drawn). channels and forgings. 3-6. The inherent advantages of this material are lightweight.).T.. indicate same purity with special control on one or more impurities. plate. assigned consecutively as needed indicates special control of one individual impurity.. also.. 3-4. rod (round.Mangenese 4XXX ..... Experimental alloys are.40% minimum aluminum without special control on individual impurities and 1140.. bar.Zinc 8XXX . while numbers 1 .e. The last two of the four digits in alloy groups 2XXX through 8XXX have no special significance except that they serve to designate the alloy by its former number. Table 3-2. Although most aluminum alloys contain several alloying elements only one group the 6XXX designate more than one alloying element.00% of minimum and greater 2XXX . etc. 3-5.. 2XXX indicates an aluminum alloy in which copper is the main alloying element.Aluminum 99.. 1240 etc. ref lectivity for radiant energy of all wave lengths and ease of fabrication. Thus 1040 indicates 99.Copper 3XXX . 1XXX indicates aluminum of 99.. T.O. 1-1A-9 NOTE Cladding which is a sacrif icial aluminum coating applied to an aluminum alloy core for the purpose of increasing corrosion resistance is designated as alclad 2024, alclad 2014, alclad 7075, etc. 3-7. Aluminum alloys for military use are identif ied by military and federal specif ications which are comparable to commercial specif ications and designations. The following table is a general list of the commonly used military and federal specif ications according to the commercial designation and forms of material. 3-8. MECHANICAL PROPERTIES. Prior to presenting factual data on mechanical properties the tempers (hardness) and methods of designation should be explained. For nominal mechanical properties see Table 3-4. 3-9. The tempers of aluminum alloys are produced essentially by three methods. These methods are cold working (strain hardening), heat treatment and a combination of the two. The various alloys of aluminum are either classed as heattreatable or non-heat-treatable. Alloys 1100, 3003, alclad 3003, 3004, alclad 3004, 5050 and 5052 are classed as nonheat-treatable. The tempers of these alloys are designated by symbols H1, H2, H3, H4, F & O. 3-10. A second number added to the above indicates the degree of strain hardening-actual temper. Example: 2=1/4 hard (2/8) - H12, H22, H32 4=1/2 hard (4/8) - H14, H24, H34 6=3/4 hard (6/8) - H16, H26, H36 8=Full Hard (8/8) - H18, H28, H38 As previously pointed out the above tempers designation symbols are hyphen (-dash) suff ixed to the 4 digit alloy designation. Example: 1000-H12, 5052-H24, 3004-H34 etc. The general symbols used for the nonheat-treatable alloys are as follows: -F As fabricated -O Annealed -H21 Strain hardened only -H2 Strain hardened then partial annealed -H3 Strain hardened then stabilized NOTE Attempt should not be made to alter the temper characteristics of the ‘‘H’’ series of aluminum alloys other than in emergencies. This shall be limited to annealing operation only. 3-11. Alloys alclad 2014, 2024, alclad 2024, 6061, 7075, alclad 7075 and 7178 are classed as heat treatable. The mechanical properties of these alloys is improved by heat treatment or by a combination of heat treatment and strain hardening. The tempers for these alloys is designated by symbols, W, T, T2, T3, T4, T5, T6, T7, T8, T9, T10, F and O. Following is a summary of these symbols. -F As fabricated -O Annealed -W Solution heat treated - unstable temper -T Treated to produce stable tempers other than -F or -O -T2 Annealed (cast products only) -T3 Solution heat treated and then cold worked -T4 Solution heat treated -T5 Artif icially aged only -T6 Solution heat treated and then artif icially aged -T7 Solution heat treated and stabilized -T8 Solution heat treated, cold worked and then artif icially aged -T9 Solution heat treated, artif icially aged, and then cold worked -T10 Artif icially aged and then cold worked Added numbers to the above denotes a modif ication of standard tempers. Example: The numeral ‘‘6’’ following ‘‘T3’’ indicates a different amount of cold work then used in ‘‘T3’’ such as 2024-T36. The numbers added to indicate modif ication or signif icant alternation of the standard temper are arbitrarily assigned and specif ication for the alloy should be utilized to determine specif ic data. 3-12. The following standard modif ication digits have been assigned for wrought products in all alloys: TX-51 - Stress-Relieved by Stretching: Applies to products which are stress-relieved by stretching the following amounts af ter solution heat treatment: Plate Rod, Bar and Shapes 1 1/2 to 3% permanent set 1 to 3% permanent set Applies directly to plate and rolled or cold f inishes rod and bar. These products receive no further straightening af ter stretching. Applies to extruded rod, bar and shapes which receive minor straightening af ter stretching to comply with standard tolerances. -TX510 - Applies to extruded rod, bar and shapes which receive no further straightening af ter stretching. -TX511 - Applies to extruded rod, bar and shapes which receive minor straightening af ter stretching to comply with standard tolerances. 3-2 T.O. 1-1A-9 Table 3-3. Federal and Military Specifications ALLOY 1100 FORM (COMMODITY) Bars Rolled Bar, rod, wire and shapes, rolled or drawn Sheet and Plate Tubing AMS 4102 4001B,4003B 4062C - FEDERAL QQ-A-411, QQ-A-225/1 QQ-A-411, QQ-A-225/1 QQ-A-561, QQ-A-250/1 WW-T-783 (Old), WW-T700/1 QQ-A-365, QQ-A-225/3 QQ-A-261, QQ-A-200/2 QQ-A-266, QQ-A-225/4 QQ-A-367 (See QQ-A-367 & 367-1) QQ-A-255, QQ-A-250/3 MILITARY MIL-A-148 MIL-A-12545 MIL-A-799 - * Extrusion (Impact) 1360 2011 2014 Wrought Product Bar and Rod Bar, Rod and Shapes Extruded Bar, Rod and Shapes Rolled or Drawn Forgings Extrusions (Impact) Alclad 2014 2017 Plate and Sheet Bar, Rod, Wire and Shapes, Rolled or Drawn WIRE - ROD FORGINGS 2018 2020 2024 Forgings Sheet and Plate Bar, Rod and Shapes Extruded Bar, Rod and Shapes Rolled or Drawn 2024 Plate and Sheet 4153A 4121B 4134A,4135H MIL-A-12545 4118 QQ-A-351, QQ-A-225/5 QQ-A-430 QQ-A-367 MIL-W-7986 4140 QQ-A-367 QQ-A-250/16 MIL-A-8882 4152 QQ-A-267, QQ-A-200/3 4120 4035 4037 QQ-A-225/6, QQ-A-268 QQ-A-355, QQ-A-250/4 3-3 T.O. 1-1A-9 Table 3-3. Federal and Military Specifications - Continued ALLOY Alclad 2024 FORM (COMMODITY) Sheet and Plate AMS 4040 4041 4042 4086 4087 4088 4130 4142 FEDERAL QQ-A-362, QQ-A-250/5 MILITARY 2024 Tube Drawn WW-T-785 (Old), WW-T-700/3 QQ-A-367 QQ-A-367 MIL-A-8720 2025 2218 2219 Forgings Forgings Plate and Sheet Sheet and Plate Sheet and Plate, Alclad Extrusions 4031 4090 4094 4095 4096 4162 4163 QQ-A-250/30 3003 Bar, Rod, Shapes Extruded Bar, Rod, Wire and Shapes Rolled or Drawn Plate and Sheet Tube Drawn 4006 4008 4065 4067 4145 4114 4015 4016 4017 4070 4071 4182 QQ-A-200/1, New QQ-A-357, Old QQ-A-225/2 (New) QQ-A-356 (Old) QQ-A-359, QQ-A-250/2 WW-T-786 (Old) WW-T-700/3 QQ-A-367 QQ-A-225/7 (New) QQ-A-315 (Old) QQ-A-318 QQ-A-250/8 WW-T-787 (Old), WW-T-700/4 MIL-C-915 (Ships) 4032 5052 5052 Forgings Bar, Rod, Wire and Shapes Drawn Plate and Sheet Tube, Drawn 5056 Bar, Rod and Wire Rolled or Drawn 3-4 T.O. 1-1A-9 Table 3-3. Federal and Military Specifications - Continued ALLOY 5056 (Cont) FORM (COMMODITY) Bar, Rod, ShapesExtruded Plate Sheet Wire Rod Welding Rod AMS FEDERAL QQ-A-200/7 QQ-A-250/9 MILITARY MIL-C-6136 MIL-W-7986 QQ-R-566 C1 FS-RA156 QQ-A-200/4 (New) QQ-A-250/8 (New) QQ-A-250/7 (New) 4018 4019 4150 QQ-A-270 QQ-A-225/8 (New) QQ-A-325 (Old) 4127 4025 4026 4027 4080 4082 4081 4021 4022 4023 4155 4091 4092 4093 MIL-T-7081 4156 QQ-A-200/9 (New) QQ-A-274 (Old) QQ-A-270 (Old) QQ-A-200/8 (New) QQ-A-367d-1 QQ-A-327 QQ-A-250/11 (New) WW-T-789/WW-T-700/6 MIL-T-7081 MIL-A-19005 MIL-A-87001 MIL-A-17358 MIL-A-19070 MIL-A-17357 5083 Bar, Rod and Shapes Plate and Sheet 5086 5154 6061 Plate and Sheet Plate and Sheet Bar, Rod and Shapes Extruded Bar, Rod and Shapes Rolled or Drawn 6061 Forgings Plate and Sheet Tube, Drawn Tube, Hydraulic Alclad 6061 Sheet and Plate 6062 Bar, Rod and Shapes Extruded Tube, Drawn Tube, Hydraulic 6063 6066 Bar, Rod and Shapes Extruded Bar, Rod and Shapes Extruded 3-5 T.O. 1-1A-9 Table 3-3. Federal and Military Specifications - Continued ALLOY 6151 7050 FORM (COMMODITY) Forgings Plate Extrusion AMS 4125 4050 4201 4340 4341 4342 4107 4108 4154 FEDERAL QQ-A-367 MILITARY Die Forging Hand Forging 7075 Bar, Rod and Shapes Extruded Bar, Rod, Shapes and Wire, Rolled or Drawn Forgings Extrusions (Impact) Plate and Sheet Alclad 7075 MIL-A-46118D (Armor) QQ-A-225/11 QQ-A-277 QQ-A-225/9 QQ-A-282 QQ-A-367 MIL-A-12545 QQ-A-283 QQ-A-250/12 QQ-A-287 QQ-A-250/13 QQ-A-250/13 MIL-A-8902 MIL-A-11352 4122 4139 4170 4044 4045 4048 4049 Plate and Sheet Plate and Sheet Alclad one side 7076 7079 Forgings Forgings Plate and Sheet Plate and Sheet Alclad one side 4137 4138 QQ-A-367 QQ-A-367 QQ-A-250/17 QQ-A-250/18 7475 Sheet and Plate Rod 4207 4202 MIL-A-63547 4158 4051 4052 QQ-A-250/14 MIL-A-9186 MIL-A-9180 MIL-A-11267 (ORD) 7178 Bar and Shapes Extruded Plate and Sheet 8280 Sheet 3-6 3% 99.T.O.75% 99. Federal and Military Specifications .0% 43 108 A108 113 122 A132 142 195 B195 214 220 319 355 356 XB216 43 108 113 122 142 195 B214 XB216 220 319 355 FORM (COMMODITY) Ingot AMS FEDERAL QQ-A-451 MILITARY Foundry Ingot QQ-A-371 Foundry Ingot QQ-A-371 Foundry Ingot Sand Castings Sand Castings Sand Castings Sand Castings Sand Castings Sand Castings Sand Castings Sand Castings Sand Castings Sand Castings Sand Castings 4240 4210 4212 4214 4217 QQ-A-601 QQ-A-601 QQ-A-601 4222 4230 4231 QQ-A-601 QQ-A-601 QQ-A-601 QQ-A-601 QQ-A-601 QQ-A-601 QQ-A-601 MIL-A-10937 (ORD) MIL-A-10936 (ORD) 356 A612 ML 43 A108 Sand Castings Sand Castings Sand Castings Permanent Mold Castings Permanent Mold Castings MIL-A-10936 (ORD) MIL-A-25450 USAF QQ-A-596 QQ-A-596 3-7 .5% 99. 1-1A-9 Table 3-3.Continued ALLOY 99. Chemical composition nominal plus general use data are given in Table 3-4 and nominal mechanical properties at room temperature are given in Table 3-5. 1-1A-9 Table 3-3.T. The following two digit . 3-13.Applies to products solution heat treated by the user which attain mechanical properties different from those of the -T4 temper.* -T62 . -TX53 .T temper designations have been assigned for wrought products in all alloys: -T42 .Stress-Relieved by Compressing: Applies to products which are stress-relieved by compressing af ter solution heat treatment.O. 6063-T42 and 6463-T42. 3-15. 6101-T62. Federal and Military Specifications . 3-14.Applies to products solution heat-treated and artif icially aged by the user which attain mechanical properties different from those of the -T6 temper. For additional information on heat treating aluminum alloys. The values cited are general and intended for use as comparisons values.Continued ALLOY 113 122 A132 B195 XB216 319 355 356 750 ML 13 43 218 360 A360 380 A380 FORM (COMMODITY) Permanent Mold Castings Permanent Mold Castings Permanent Mold Castings Permanent Mold Castings Permanent Mold Castings Permanent Mold Castings Permanent Mold Castings Permanent Mold Castings Permanent Mold Castings Permanent Mold Castings Die Castings Die Castings Die Castings Die Castings Die Castings Die Castings Die Castings AMS FEDERAL QQ-A-596 QQ-A-596 QQ-A-596 MILITARY 4282 4283 QQ-A-596 MIL-A-10935 (ORD) QQ-A-596 4280 4281 4284 4286 4275 4290 QQ-A-596 QQ-A-596 QQ-A-596 QQ-A-591 QQ-A-591 QQ-A-591 MIL-A-15153 Ships MIL-A-15153 Ships MIL-A-15153 Ships MIL-A-15153 Ships MIL-A-15153 Ships 4290 QQ-A-591 QQ-A-591 QQ-A-591 4291 QQ-A-591 Misc STANDARD/SPECIFICATIONS -TX52 . 6062-T62.* *Exceptions not conforming to these def initions are 4032-T62. 3-8 . see paragraph 3-22. For specif ic values the specif ication for the alloy should be utilized.Stress-Relieved by Thermal Treatment. 25 REM X X X 3-9 .5 0.10 0. formability and weldability. Popular sheet alloy for aircraf t similar to 2014.05 99.03 --- -0.05 -- -- -- 99.25 -0. readily welded and brazed. electrical conductivity. corrosion resistant.45 X 2014 0.60 X X Electrical conductor Good corrosion resistance.10 0.O.05 -- 0.10 99.0 X X 1145 0.25 REM X X X High strength alloy. Electric resistance weldability excellent fusion weldability limited.% ALLOY SI CU MN MG CR ZN AL FLAT AND COILED SHEET PLATE SHAPES RODS AND BARS TUBE PIPE CHARACTERISTICS EC 1060 -0. 1100 1.20 0.45 99.4 0. X X Excellent formability.6 1.5 0.Table 3-4. 1-1A-9 2024 0.03 -0. Chemical Composition Nominal and General Use Data 1/ 1 NOMINAL COMPOSITION . T.8 4.55 0.0 0.05 -0.8 0.10 0.05 0.5 0.5 4. Excellent formability combined with high electrical and thermal conductivity and corrosion resistant. Similar to 3003 in strength.05 REM X X X Strutural uses requiring high strength up to 600 degrees F.25 1.1 6.2 -3004 0.O.3-10 ALLOY SI CU MN 2219 0.Continued 1 NOMINAL COMPOSITION .20 1. Chemical Composition Nominal and General Use Data 1/ . high resistance to corrosion.40 0. Stronger than 1100 and 3003 with fair workability and good corrosion resistance.10 REM X X X X 1. Stronger than 1100 with good weldability and formability.10 0.4 0. 1-1A-9 Table 3-4. Good anodizing characteristics. and corrosion resistance.40 0.3 3003 0.25 REM X X 1.20 0. high strength weldments.8 0.10 0. Good anodizing strength.2 5005 0.6 0.25 REM X X . formability and resistance to corrosion.25 REM X X 0.0 -- 0.10 T.20 0.30 0.20 5050 0.01 - 0.2 0. -- 0.% MG CR ZN AL FLAT AND COILED SHEET PLATE SHAPES RODS AND BARS X TUBE PIPE CHARACTERISTICS 0. formability. weldability. Good corrosion resistance and f inishing characteristics.8 5. Chemical Composition Nominal and General Use Data 1/ .10 0. 1-1A-9 High strength and corrosion resistance.10 2.5 3. 5083 0.10 0. T.25 REM X 5154 5254 0.8 2.12 0.45 0.5 0. weldability and corrosion resistance. Good strength and excellent weldability.45 0.07 0.45 0.40 0.40 0.5 0. Good strength.7 0.20 REM REM X X X 5357 0.0 -- -- REM X 5454 0. X High weld joint efficiency with basic good strength and resistance combined with good formability.25 0. 5456 3-11 0.10 0.25 0.10 0.01 3.3 -- -- REM X X .5 0. Excellent bright finishing characteristics.25 0.% ALLOY SI CU MN MG CR ZN AL FLAT AND COILED SHEET PLATE SHAPES RODS AND BARS TUBE PIPE CHARACTERISTICS 5052 0.20 0.40 0.Continued 1 NOMINAL COMPOSITION .Table 3-4.20 0.3 1.15 0. weldable.10 REM X X Highest strength of non-heat-treatable alloys.8 4.10 0.2 0.O.05 0.25 REM X X X Excellent strength at elevated temperature (150 -300 F) plus weldability. 10 0.0 .4 0.% MG CR ZN AL FLAT AND COILED SHEET PLATE SHAPES RODS AND BARS TUBE PIPE CHARACTERISTICS 1.10 0.Continued 1 NOMINAL COMPOSITION .25 REM 1.10 T.25 5652 6061 0. Good weldability and formability. Good bright finishing characteristics.6 -- -- REM REM X X Superior bright finish when anodized.15 6063 0.25 REM X 1.0 0. Good workability with moderate strength. 1-1A-9 Table 3-4. good formability and corrosion resistance. X X X Best weldability of heat treatable alloys.6 .6 .25 0.25 REM X X .08 0.25 REM X X 0.15 6062 0.25 0.3-12 ALLOY SI CU MN 5457 5557 0. Chemical Composition Nominal and General Use Data 1/ .5 0. X Excellent strength with good finishing characteristics and corrosion resistance.0 . 2.3 0. Good weldability with formability better than 6061.20 0.06 0.O.25 0.7 0. X Good finishing characteristics and resistance to corrosion. Electric resistance weldability but limited fusion weldability.Table 3-4.3 5.25 2.2 3.1 5.5 .3 6.2 4.Continued 1 NOMINAL COMPOSITION . 2/ Extra high strength and hardness.25 - 6.O. Chemical Composition Nominal and General Use Data 1/ . 7075 0. good exfoliation corrosion resistance good stress-corrosion cracking resistance.2 REM X X X High tensile properties. High strength alloy for a/c applications.7 . however it is notch sensitive.7 REM X X SI = Silicon MN = Manganese CR = Chromium AL = Aluminum CU = Copper MG = Magnesium ZN = Zinc T.05 1.6 REM X X X 7079 0. Similar to 7075 but maximum strength in thick sections. Specif ication Should Be Utilized When Specif ic Data Required.6 .30 2.0 0.3 . toughness up to 300 degrees F resistance to stresscorrosion cracking.8 REM X X 7475 0.6 0.T73 Is Completely Resistant To Stress Corrosion Cracking.50 1. 3-13 2/ 7075 .5 0.% ALLOY SI CU MN MG CR ZN AL FLAT AND COILED SHEET PLATE SHAPES RODS AND BARS X TUBE PIPE CHARACTERISTICS 7050 - 2.03 2.3 - 2. Aerospace applications requiring high strength. .3 REM X 7178 2.30 2.30 . 1-1A-9 1/ Nominal Composition Does Not Include All Alloying Elements That May Pertain. 000 20.000 40.000 37.000 26.000 18. 1-1A-9 Table 3-5.000 42.000 18.000 18.000 25.000 18.000 15.000 35.T351 2219-T37 2219-T62 2219T81.000 41.000 11.000 19.000 25.000 16.000 47.000 2024-0 2024-T3 2024-T36 2024-T4 Alclad 2024-0 Alclad 2024-T3 Alclad 2024-T36 Alclad 2024-T4 Alclad 2024-T81 Alclad 2024-T86 2219-0 2219-T42 2219T31.000 52.000 6.000 41.000 14.000 70.000 46.000 18.000 16.000 10.000 29.000 20.000 38.000 41.000 14.000 10.000 50.000 16.000 27. Sheet Specimen (1/16 in.000 51.000 24. Thick) 35 12 9 6 5 30 10 8 5 4 20 10 9 5 5 21 20 22 10 20 18 13 20 20 18 11 19 6 6 18 20 17 11 10 1 10 30 11 8 6 5 Brinell Hardness 500-kg Load 10 MMM Ball 23 28 32 38 44 28 35 40 47 55 45 52 63 70 77 ----47 120 130 120 --------96 110 113 123 128 28 36 41 46 51 Shearing Strength PSI 9.000 11.000 63.000 12.000 22.000 21.000 37.000 36.000 53.000 70.000 68.000 61.000 60.000 64.000 23.O.000 27.000 57.000 45.000 10.000 15.000 17.000 36.000 72.000 29.000 41.000 Elongation.T851 2219-T87 5005-0 5005-H32 5005-H34 5005-H36 5005-H38 3-14 .000 11.000 18.000 42. Mechanical Properties .000 65.000 42.000 69.000 21.000 65.000 57.000 66.T.000 31.000 66.000 52.000 27.000 20.000 25.000 17.000 12.000 29.000 13.000 20.000 40.000 60.000 16.000 18.000 60.000 --33.000 37.000 26.000 33.000 27.000 57.000 22.Typical Alloy and Temper 1100-0 1100-H12 1100-H14 1100-H16 1100-H18 3003-0 3003-H12 3003-H14 3003-H16 3003-H18 Alclad 3003 3004-0 3004-H32 3004-H34 3004-H36 3004-H38 Alclad 3004 Alclad Alclad Alclad Alclad 2014-0 2014-T3 2014-T4 2014-T6 Tensile Strength PSI 13.000 67.000 17.000 11.000 21.000 11.2%) PSI 5.000 37.000 40.000 25.000 40.000 26.000 26.000 41. Per Cent in 2 in.000 Yield Strength (Offset= 0.000 16.000 37.000 11.000 15.000 6.000 40.000 14.000 41.000 42.000 24.000 68. 000 21.000 67.000 22.000 18.000 74.000 12.000 29.000 26.000 7.000 63.O.000 39.000 36.000 28.000 73.000 28.000 30.000 30.T7452 7075-0 7075-T6 Alclad 7075-0 Alclad 7075-T6 A1clad 7079-T6 7178-0 7178-T6 7079-T6 7475-T7351 Tensile Strength PSI 21.000 8.Continued Alloy and Temper 5050-0 5050-H32 5050-H34 5050-H36 5050-H38 5052-0 5052-H32 5052-H34 5052-H36 5052-H38 5154-0 5154-H112 5154-H32 5154-H34 5154-H36 5154-H38 5357-0 5357-H32 5357-H34 5357-H36 5357-H38 6061-0 6061-T4 6061-T6 7050-T74.000 32.000 24.000 21.000 39.000 18.000 --22. T7451.000 24.000 31.000 13.000 28.T.000 40.000 65.000 83.000 --22.000 33.000 Elongation.000 28.000 32.2%) PSI 8.000 40.000 17.000 24.000 22.000 76.000 12.Typical .000 21.000 38.000 24.000 23.000 46.000 19.000 -- -- 3-15 .000 15.000 32.000 18.000 28. 1-1A-9 Table 3-5. Mechanical Properties .000 72.000 13.000 19.000 35.000 17.000 21.000 17.000 33.000 17.000 35.000 20.000 14.000 19. Thick) 24 9 8 7 6 25 12 10 8 7 27 25 15 13 12 10 25 9 8 7 6 25 22 12 13 17 11 17 11 10 6 14 Brinell Hardness 500-kg Load 10 MMM Ball 36 46 53 58 63 47 60 68 73 77 58 63 67 78 83 87 32 40 45 51 55 30 65 95 142 60 150 --- Shearing Strength PSI 15.000 22.000 35.000 35.000 30.000 70.000 22. Per Cent in 2 in.000 33.000 18.000 60.000 20.000 25.000 30.000 37.000 73. Sheet Specimen (1/16 in.000 15.000 35.000 62.000 72.000 Yield Strength (Offset= 0.000 26.000 45.000 42.000 48.000 83.000 26.000 25.000 48.000 45.000 42. T6 7050 7075-0 7075-T6 7475 BRASS Copper Monel Nickel Steel(low alloy) Steel(18.180 890-1175 -1981 --2645 2800 2500-2650 449 787 40 30 50 30 44 50 50 35 35 43 43 45 40 45 -30 46 26-43 100 4 16 3-15 2-4 15 30 3-16 . APPROX MELTING RANGE DEGREES F ELECTRICAL CONDUCTIVITY % COMPARE TO COPPER STANDARD 59 57 50 1100-0 1100-H18 3003-0 3003-H12 3003-H14 3003-H18 3004-0 3004-H38 2014-0 2024-0 2024-T3 2219 5050-0 5050-H38 5052-0 5052-H38 5357-0 5357-H38 6061-0 6061-T4.322 0.102 0.215 2.210 1. 1-1A-9 Table 3-6.319 0.3 7.810 1010-1190 1.200 1.190-1.69 2.73 0.92 7.258 950-1.190-1.80 2.8 8.180 935-1.200 890-1175 890-1.100 0.318 0.100-1.080-1.1 0.O.098 1.70 2.84 2.83 2.098 0.94 8.099 1.68 2.4-8.84 7.102 0.265 0.101 0.IN.165-1.283 0.71 0.282 0.101 0.210 42 41 40 2.205 42 42 50 2.80 8.205 1.160-1.80 2.319 0.276-0.8 7.72 0.165-1.77 2.6-7.097 0.101 0.70 2. Physical Properties-Standard Alloys ALLOY SPECIFIC GRAVITY WEIGHTS PER CU.304-0.8 8.097 0.098 0.T.8 stainless) Tin Zinc 2.098 1. 1-1A-9 Table 3-7. 7475 880-970 FORGINGS ALLOYS 2014 2017 2018 FORGINGS 2025 4032 6151 6061 7075 925-950 925-950 940-970 950-970 940-970 950-980 960-1010 360-890 7075 Other temperatures may be required for certain sections and conditions. Heat Treating (Soaking) Temperatures ALLOY DESIGNATION WROUGHT ALLOYS Except forgings alloys 2014 2017 2117 2024 2219 6061 6062 6066 7050 7075 (rolled or drawn) 7075 (Extruded) 7075 (Sheet . 7079 820-840 7079-W 7079 Other temperatures may be required for certain sections and conditions.T.051 in thickness or less) 7178 (rolled or drawn) 7178 (Extruded) *7079 SOLUTION HEAT TREAT TEMPERATURE (DEGREES F) TEMPER 925-945 925-945 925-950 910-930 985-1005 960-1010 960-1010 960-980 880-900 860-930 860-880 910-930 860-930 860-880 820-840 2014-T4 2017-T4 2117-T4 2024-W 2219-T4 6061-T4 6062-T4 6066-T4 7050-W 7075-W 7075-W 7075-W 7178-W 7178-W 7079-W 7475-W 2014-T4 2017-T4 2018-T4 2025-T4 4032-T4 6151-T4 6061-T4 7075-W *7079 Other temperature may be required for certain sections and conditions.O. SAND CAST ALLOYS 122 142 195 220 319 355 356 930-960 950-980 940-970 800-820 920-950 960-990 980-1010 T4 T4 T4 T4 T4 T4 T4 3-17 . corresponding to a specific gravity of 271. GENERAL. Further aging (overaging) causes the strength to decline until a stable condition is obtained. PHYSICAL PROPERTIES. Heat Treatment of wrought aluminum alloy parts. Data for standard alloys are shown in Table 3-6. Other alloys. 3-20. extrusions and similar items. During this hardening and strengthening operation the alloying constituents in solid solution precipitate out. and 7178 require solution heat treatment and aging (precipitation heat treatment) for specific length of time at a definite temperature (see Table 3-11). is one-tenth of a pound per cubic inch (see Table 36). They are known as solution and precipitation heat treatment. Upon standing at room temperature the hardening constituent in excess of that which is soluble at room temperature precipitates. Heat Treating (Soaking) Temperatures . Artificial aged alloys are usually slightly “overages” to increase their resistance to corrosion. Immediately after quenching. 3-19. temperature and times. Natural aging alloys can be artificially aged. This is in effect a method where the molecules of the aluminum and alloying elements are realigned to increase the strength and hardness of some aluminum alloys. because it consists of a supersaturated solid solution of the hardening agent. If utilized it should be limited to clad sheet. 3-22. NOTE SAE-AMS-2770. the alloy is in an unstable condition. refer to latest issues of SAE-AMS-2770 & SAE-AMS-2771. As precipitation progresses.TO 1-1A-9 Table 3-7. Heat Treatment of aluminum alloy castings.Continued SOLUTION HEAT TREAT TEMPERATURE (DEGREES F) ALLOY DESIGNATION 40E Solution heat treatment not required. This is done to reduce their susceptibility to intergranular corrosion caused by under-aging. 7075. The strengthening of the material is due to the uniform alignment or formation of the molecule structure of the aluminum and alloying element. There are two types of heat treatment applicable to aluminum alloys. Some alloys such as 2017 and 2024 develop their full mechanical properties as a result of solution heat treatment followed by 96 hours (natural precipitation) aging at room temperature. PRECIPITATION (AGE) HARDENING. 3-16. it is then quenched rapidly in cold water to retain this condition. Artificial aging consists of heating aluminum alloy to a specific temperature and holding for a specified length of time. will be the control documents for heat treatment of Aluminum Alloys used on aerospace equipment.098 pounds per cubic inch. 3-21. For aging treatment. It has been found that those alloying elements which increase the strength and hardness are more soluble in 3-18 Change 5 . see Table 3-11. HEAT TREATMENT OF ALUMINUM ALLOYS. The precipitate is in the form of extremely fine particles which due to their “keying” action. For complete description of aluminum alloy heat treat requirements. Commercially pure aluminum weights 0. however. including its alloys. 3-17. 3-18. Solution heat treatment is a process where the alloying elements enter into solid solution in the aluminum at critical temperatures. To complete the solution often the metal is held at high temperatures for sufficient time. The approximate weight for aluminum. especially the high copper content alloys. greatly increase their strength. it increases the susceptibility of the material to intergranular corrosion. the strength of the material increases until the maximum is reached. PERMANENT MOLD CAST ALLOYS 122 A132 142 B195 355 356 TEMPER 930-960 940-970 950-980 935-965 960-990 980-1010 T4 T4 T4 T4 T4 T4 solid aluminum at high temperature than at low. NOTE Additional Heat Treatment information is discussed in Section IX. such as 2014. & SAE-AMS-2771. This phase of heat treatment consists of aging material previously subjected to solution heat treatments by natural (occurs at room temperature) or artificial aging. 3-33. With clad materials. extrusions. Solution heat treatment should be held to the minimum time required to obtain the desired physical properties. 3-32. 3-27. SOLUTION HEAT TREATMENT. The soaking temperature required is selected to put all of the soluble elements into solid solution. The temperature for heat treating is usually chosen as high as possible without danger of exceeding the melting point of any element of the alloy. See Table 3-12 for the recommended reheat-treatment times. A general guide to use is approximately one hour for each inch of cross-sectional thickness. This is necessary to obtain the maximum improvement in mechanical properties. 3-29. prolonged heating may defeat the purpose of the cladding by excessive diffusion of copper and other soluble elements into the cladding. Large forgings and heavy sections can be quenched in (150° . This is caused by re-precipitation along grain boundaries and in certain slip planes. The one used depends upon the item. For specific quench delay see Table 3-10. QUENCHING. 3-24. In many instances the above will require sample testing to determine the exact solution time. STRAIGHTENING OF PARTS AFTER SOLUTION HEAT TREATMENTS. and usually a severely blistered surface. If the maximum specified temperature is exceeded eutectic melting will occur. such as heavy forgings.TO 1-1A-9 previously 3-23. Principal reasons for using this method is to minimize distortion and to alleviate quench cracking. tubing and small fairing are normally quenched in cold water. For the recommended approximate soaking time for various alloys see Table 3-8. For clad sheet the number of solution heat-treatment is limited due to the increased diffusion of the core and cladding. (see specifications SAE-AMS-2770 & SAE-AMS2771). Allowing the metal to cool before quenching promotes intergranular corrosion and slightly affects the hardness. There are three methods employed for quenching. 3-31. alloy and properties desired. 3-36. The oxidation can be retarded by using either sodium or potassium fluoborate during the heating cycle.180°F) or boiling water. 3-35. The soaking period will vary from 10 minutes for thin sheet to approximately 12 hours for the thicker materials. The heating time commonly called the “soaking time” required to bring about solution increases with the thickness of the section or part to be heat treated. The consequence will be inferior physical properties. To obtain optimum physical properties of aluminum alloys. The temperature before quenching should be 85°F or less. Small articles made from sheet. The bare heat-treatable alloys can be solution heat treated repeatedly without harmful effects other than high temperature oxidation. As pointed out it is necessary that solution heat treatment of aluminum alloys be accomplished within close limits in reference to temperature control and quenching. It will be necessary to straighten some parts after heat treating due to warping produced by the process. 3-30. Spraying Quenching. The hot water quench will also reduce residual stresses which improves resistance to stress corrosion cracking. This type of quench is used to minimize distortion and cracking which are produced by the unequal temperatures obtained during produced by the unequal temperatures obtained during the quenching operation. rapid quenching is required. 3-34. 3-25. Sufficient cold water should be circulated within the quenching tanks to keep the temperature rise under 20°F. Water sprays are used to quench parts formed from alclad sheet and large sections of most alloys. RE-SOLUTION HEAT TREATMENT. 3-28. It is recommended that thermocouple be placed in the coldest part of the load to determine the period required to bring the load to the correct temperature (soaking temperature). 3-26. The basic purpose of quenching is to prevent the immediate re-precipitation of the soluble constituents after heating to solid solution. In the case of thick material the controlling factor would be when the center (core) reached the minimum temperature. These Change 5 3-19 . The time at temperature (soaking time) is measured from the time the metal reaches the minimum limit of the temperature range. The recommended time interval between removal from the heat and immersion is 10 seconds or less. This system is not usually used to quench bare 2017 and 2024 due to the effect on their corrosion resistance. The parts quenched by this media should pass the test for corrosion required for the item involved. Cold Water Quenching. maximum strength will not be obtained. If the temperature of heat treatment is low. Hot Water Quenching. This type of quench will insure good resistance to corrosion and particularly important when heat-treating 2017 and 2024. Heating Time. These may be stored in refrigerators which ensure that the rivet temperature does not rise above minus 10oF.O. The same conditions apply for these rivets as for the 2017 (D) except heat treat at 920oF ± 10oF. These do not require heat treatment.T. or 30 minutes in a molten salt bath and quench in water. item A and 3-1. item D for head identif ication. b. d. their temperature will be maintained at minus 10oF or below by being carried in refrigerated boxes. install as received. and 2024. A temperature of 32oF or below will delay or retard natural aging for approximately 24 hours. See Figure 3-1. item E for head identif ication. See Figure 3-1. HEAT TREATMENT OF RIVETS. item B for identif ication. CAUTION Rivets which have been anodically oxide coated should not be reheattreated in direct contact with molten salts more than 5 times. item DD for head identif ication. 7050 (E) Rivets. 1-1A-9 parts are usually straightened by restriking or forming. Heat treat prior to installation by heating to 940oF ± 10oF for 30 minutes in a circulating air furnace. D/DD Rivets. install as received. f. 3-20 Change 2 . 1100 and 5056 Rivets. e. a. The rivet is identif ied by a dimple in the center of the head (see Figure 3-1. 2017 or 2017-T4 (D) Rivets. The heat-treatable alloys commonly used for rivets are 2117. It is noted the D rivets may also be used in the age hardened condition. It is desirable to place these parts in refrigeration immediately af ter quenching to retard natural aging until such time straightening is accomplished. When the rivets are transported. c. Rivets held at minus 10oF or below can be retained for use indef initely. If either time is exceeded reheat treatment is required. 1 hour in still air furnace. 2117 Rivets. 2024-0 or 2024-T4 (DD) Rivets. 2017. Head to Alloy Identification Method 3-37. See Figure 3-1. If supplied in T-4 temper no further treatment is required. lower temperatures will delay the aging longer. item AD for head identif ication). These rivets must be driven within 20 minutes af ter quenching or refrigerate at 32oF or lower which will delay the aging time 24 hours. These do not require heat treatment. Figure 3-1. See Figure 3-1. These rivets can be reheat treated a maximum of three times.) When the above is encountered it is usually necessary to anneal the part one or more times at progressive stages of the forming operation. 1-1A-9 (1) Quality control shall be responsible for periodically checking the temperature of each refrigerator and for prohibiting the use of rivets in any box when the temperature becomes excessive. The 3003 alloy is annealed by heating to 775oF at a relatively rapid rate and holding at the minimum soaking period necessary to attain temperature uniformity and then cool as cited above. 3-40.930oF temperature more than 3 times. (2) Each refrigerator shall have the rivets removed and be thoroughly cleaned at least once every six months. Material is then cooled at a rate of no greater than 50oF per hour until the temperature is 500oF or below. b. Alternate 7075 annealing methods: (1) If forming is to be accomplished immediately af ter annealing. During prolonged forming or stamping operations the metal becomes strain hardened (commonly called ‘‘work hardened’’ and upon the performance of additional work it will split or crack. reheating to 450oF. 3-39. no attempt should be made to shorten the annealing cycle because the soluble constituents go into solution as the temperature is increased. or heat to 910o . 1/2 hour maximum. (3) Rivets which remain out of refrigeration for 30 minutes or more shall be reheat treated. (2) If alloy is to be stored for an extended period before forming.700oF. When fully annealing. air cool. d. CAUTION Annealed aluminum parts shall not be used for parts or f ittings on aircraf t or missiles unless specif ied by drawings or other approved engineering data.750oF holding for approximately 2 hours. metal. holding at this temperature for 6 hours and then cooling to room temperature. Partial annealing of heat-treated material.775oF.T. A tag or placard that denotes the next cleaning date shall be attached to each refrigerator. 3-42. heat to 670o . Aluminum alloys are annealed to remove the effects of solution heat treatment and strain hardening. (3) Intermediate anneal during cold working of ‘‘O’’ condition material. 2 hours. Time at temperature. When heat-treated materials are annealed as specif ied for annealing of the work-hardened alloys. If the material is then cooled rapidly the soluble constituents remain in solution and the material does not attain fully annealed mechanical properties. and cooling in air or in the furnace. Annealing and subsequent forming of material previously heat treated should be avoided if conditions and time permit. Annealing is utilized to help facilitate cold working. Annealing temperature shall not exceed 775oF to prevent excess oxidation and grain growth. This factor will vary depending upon the type of anneal (partial or full). c. Annealing of Work-Hardened Alloys. the effect of heat-treatment is reduced considerably. The partially annealed Change 1 3-21 . hold at this temperature for 4 hours and then cool in air.930oF until uniform temperature is attained. Alloy 7075 is fully annealed by heating to 775oF 850oF (higher temperature utilized for material having smaller amount of cold work). thickness. The recommended method is to repeat the solution heat treatment and immediately perform the forming or drawing operation. Castings are annealed by heating to 650o . heat to 670oF .O. diffusion and discoloration. A part shall not be annealed using the 910o . ANNEALING. cool as desired. method of furnace charging and similar factors. All of these alloys except 3003 are annealed by heating to 650oF and no higher than 775oF. These alloys (except 7075) are annealed by heating to 775oF for not less than 1 hour and most instances 2-3 hours. cool in air. and cooling to room temperature. cool in air. Parts work hardened during fabrication are annealed at various stages of the forming operation so that complicated shapes can be formed. Annealing of heat-treated alloys (wrought). Annealing of cast alloys. Avoid excessive time at temperature to prevent growth. Recommended times and temperatures for annealing various alloys are as follows: a. but not completely. holding at temperature until uniform temperature has been established throughout the furnace load. if the part is to be successfully completed. reheat to 450oF. especially when annealing clad alloys. cooling in air. heat to 775oF. soaking for 2 hours at temperature. The purpose of such annealing are for the relief of stresses and attainment of dimensional stability. 2-3 hours. 3-41. 3-38. Rate of cooling below 500oF is not restricted. in order to help prevent diffusion of the cladding. recommend that “O” fully annealed material be utilized. Metal Specification and the mechanical property requirements of the applicable material specification. Suggested soaking periods are given in Tables 3-8 and 3-9 for the common alloys. 3-46. QUENCHING. 7079 forgings are generally quenched in water at temperatures less than 100°F to obtain optimum mechanical properties. The mixing of different thicknesses of clad material when charging heat-treatment furnaces will be avoided. 3-45. In case of conflict the correct Military/Federal specification will be the governing factor. Heat-treating operations will be performed on the complete individual part or piece of material never on a portion only. NOTE Parts formed that are unavoidably distorted should be reformed immediately after quenching.TO 1-1A-9 material is only to be utilized when moderate but not secure operations are to be performed. In some cases sample testing will be required to ascertain that specified properties are developed. This is desirable from the point of view of reducing stress corrosion susceptibility. The load should be held within the heat-treatment range (after the coldest part has reached the minimum of the range) for a sufficient time to insure that specified properties will be developed. Heat treating temperatures and times. Individual pieces of materials or parts should be racked or supported to prevent distorting if possible and permit free access to the heating and quenching medium. If difficulty is experienced with forming partially annealed material. and 7075 are quenched in water at temperatures in excess. 3-22 Change 5 . 3-48. 2117. The hot water quench lowers the residual stresses considerably. When heat treating clad sheet material. Wrought alloy products must be quenched by total immersion in water or by a drastic spray quench. however a hot water quench (180°F) should be used whenever possible providing the lower strength associated with the quench is satisfactory. Aluminum alloy should be heat treated at the temperature given in Table 3-7. To effectively obtain the desired qualities in aluminum alloys it is necessary that the interval between removing the charge from the furnace and immersion in the quenching water be maintained at the absolute minimum (See Table 3-10). 2017. To prevent distortion it is necessary in some cases to provide jig and fixture support for complex contoured (formed) parts. 3-44. 3-43. This should be accomplished in such a manner that will produce the utmost uniformity. especially in the case where very thin to thick materials are involved. 3-47. Maximum quench delay for immersion quenching is shown by Table 3-10. of 100°F. Forgings of 2014. The above is necessary to maintain the form of the material involved and to facilitate heating to the specified temperature and quenching rapidly. In instances where new alloys are involved it will be necessary to consult the specification for the alloys. the jig used shall be so constructed that it will not restrict the contact required with the heating medium of the part being treated. Wrought alloy products may be quenched using high velocity. the size and spacing of the load will be arranged to permit raising to the heat treatment temperature range in the minimum time. high volume jets of cold water where the parts are effectively flushed in a specially constructed chamber provided that the parts will pass the test for corrosion set forth in Specifications SAE-AMS-2770 & SAE-AMS-2771. However. Specifications SAEAMS-2770 & SAE-AMS-2771 or the manufacturer for the appropriate heat treat data. Charging of furnace and baths. 001 1. Table 3-9.3.250 .501 and under .500 . spacers.126 0.0. However.017 0.2. should be quenched by dumping into cold water. 3-50. Small parts such as rivets.T. fasteners.0. CAUTION Rivets.0.000 .500 .063 .500 . Soaking Time for Solution Heat Treatment of All Wrought Products THICKNESS (INCHES) (MIN.1.251 0. etc.021 0.501 2.2.500 . washers and other small parts which have been anodically oxidecoated should not be heat treated indirect contact with molten salts or more than 5 times by this medium.000 SALT MIN 10 10 15 20 25 30 35 45 60 90 105 120 150 165 180 SOAKING TIME (MINUTES) BATH AIR FURNACE MAX (Alclad Only) MIN MAX (Alclad) 15 20 25 30 45 40 45 55 70 100 115 130 160 175 190 20 20 25 30 35 40 50 60 90 120 150 180 210 240 270 25 30 35 40 45 50 60 70 100 130 160 190 220 250 280 3-49. washers.O. Forgings should be quenched by total immersion in water at no more than 180oF. THICKNESS OF THE HEAVIEST SECTION) 0.064 0.0. fasteners.125 .090 .032 .0. NOTE Quench delay time begins at the instant furnace door begins to open or at the instant any portion of a load emerges from a salt bath and when last portion of the load is immersed in the (water) quench tank.091 0.033 0.000 .3. Castings and forgings quenching.016 0.000 .0.501 1. if conditions warrant castings or forgings may be quenched by complete immersion in cold water.1.4. Forgings and impact extrusion supplied in T41 or T61 should be quenched in boiling water. 1-1A-9 Table 3-8.. Casting should be quenched by total immersion in water at 150o to 212oF. The maximum quench delay may be exceeded (usually conf ined to large sections or loads) if temperature will be above 775oF when quenched.020 .0.501 3.001 3.001 2. Soaking Time for Solution Treatment of Cast Alloys ALLOY SAND CAST ALLOYS 122 142 195 S195 (105) 220 319 355 356 PERMANENT MOLD CAST ALLOYS 122 A132 142 B195 355 356 TIME (HOURS) 6-18 2-10 6-18 6-24 12-24 6-18 6-18 6-18 6-18 6-18 2-10 4-12 6-18 6-18 3-23 . but they are usually more economical to operate. NOMINAL THICKNESS (INCHES) up to 0. Air furnaces are ideal for precipitation (aging). This method is adaptable for solution heat treating small parts. but well below the annealing temperature.032 to 0. 3-59. strength and condition of the material required. HEAT TREATMENT. the advantages are usually conf ined to solution heat treatment only. The initial cost of these type furnaces is higher than for the salt bath types. Air furnaces used for heat treatment of aluminum alloy should be of the recirculating air type. and decomposition of the sodium nitrate which when dissolved in quenching water forms a compound that attacks aluminum alloys. The above are heated by gas. HEAT TREATING EQUIPMENT.031 0.016 0. Annealing or solution heat treating will remove any properties developed as a result of cold working the material. 3-56. cleaner and more f lexible. 3-55. The above advantages may be completely nullif ied by the slower quench caused by the necessary arrangement of equipment. 3-54. The heated air in this type furnace is recirculated at high velocities to obtain a rapid heating cycle and uniform temperatures. Precipitation heat treatment of many aluminum alloys is necessary to obtain the required properties. They are liquid baths and controlled atmosphere. The addition of potassium dichromate (approximately 1/2 ounce per hundred pounds of nitrate) tends to inhibit the attack. Mechanical properties obtained from precipitation (aging) are dependent on the amount of cold work present in the material at the time of aging. af ter solution heat treatment will result in tensile and yield strength well above those obtained by room temperature aging. Hollow core casting or parts where the salts are likely to be diff icult or impossible to remove should not be treated by bath salt. Either method has certain advantages over the other and it generally is advisable to weigh the advantages desired and consider environmental conditions. Associated advantages are uniform temperature without excess danger of high temperature oxidation and faster heating which reduces the time required to bring the load to temperature. Conditions T-81 or T-86 would necessitate a cold work percentage of approximately 1% for T-81 and 6% for T-86 af ter solution heat treated and prior to aging. 3-58. The salt bathe method has certain advantages over the air furnace. provided the material is not cold worked prior to aging. The higher strength conditions can only be obtained by a controlled amount of cold work prior to aging. 3-60.O. Wrought Alloys (For Immersion Type Quenching) stretch or roll the material in order to produce these conditions. However. Heating of some aluminum alloys bare or alclad at an elevated temperature. electricity and oil regardless of the method utilized it must be demonstrated that satisfactory results are obtained and the material is not injured.017 to 0.091 0. The products of combustion must be excluded from the furnace atmosphere to help avoid high temp oxidation and atmosphere contamination. 3-57. AIR FURNACES. The selection of material for various uses will therefore be governed by. These furnaces are also used for solution heat treating. f ire and explosion hazards.T. This is due to the amount and types of equipment necessary to 3-24 . However. large thin sections and missed loads. Field accomplishment of the cold work required to produce the higher strength conditions is considered impractical. Recommended Maximum Quench Delay.091 and over 3-51. 3-53. The above will also apply to alloy 2024. SALT BATHS. this process will reduce the elongation factor of the material and increase resistance to forming. thermal treatments and annealing. Equipment and heating media used are divided into two distinct groups. Therefore. MAXIMUM TIME (SECONDS) 5 7 10 15 3-52. most forming operations should be performed prior to this stage of treatment. PRECIPITATION (ARTIFICIAL AGE) HEAT TREATMENT. the severity of the cold work to be performed. safer. 1-1A-9 Table 3-10. Subsequent heat treatment and aging of annealed material or aging of solution heat treated material will result in T-6 condition. Plate 7475-W.81/2 18 16 11-13 11-13 7-9 8 .25 hours 340-360 room room 7475-T6 7475-T61 5-14 96 Minimum 96 Minimum 2014-T6 2014-T4 2017-T6 Change 1 3-25 .as quenched 2017 .12 17-20 17-19 35-37 96 71/2 .O. 6-8 hours 240-260 240-260 440-460 2017-T4 2117-T4 2024-T4 6061-T4 6061-T6 2020-T6 2024-T6 1-T62 2024-T6 2024-T81 2024-T86 2014-T6 1-T62 2014-T6 2219-T81/T851 2219-T62 2219-T4 6066-T6 6061-T6 7050-T74 7075-T6 7178-T6 6063-T5 71/2 .as quenched(w) 2024 . Times and Conditions ALLOY & TEMPER OR COND BEFORE AGING WROUGHT ALLOYS (EXCLUDING FORGINGS) 2017 .as quenched(w) 3/ 6061 . Precipitation (Aging) Treating Temperatures.as quenched(w) 96 96 96 96 AGING TIME (HOURS)2/ AGING TEMP (DEGREES F)2/ TEMPER AFTER AGING room room room room 340-360 310-360 370-380 370-380 370-380 370-380 305-330 305-330 350 375 room 340-360 340-360 250 followed by 350.as quenched 250 250 followed by 315.as quenched(w) 2117 .as quenched(w) 6061-T4 2020-W 2024-T4 1-T42 2024-T4 (Alternate for sheet) 2024-T3 2024-T36 2014-T4 1-T42 2014-T4 (Alternate for Plate) 2219-T31/T351 2219-T4 2219-W 6066-T4 6061-T4 7050-W 7075-W 1/ 7178-W 6063-F 7079 . 1-1A-9 Table 3-11.81/2 6-8 22 Minimum 22 Minimum 1-2 5 days at room temperature following 48 hours at 230250 degrees F 24-25 3-5 7475-W. Sheet FORGING ALLOYS 2014-T4 2014 . 3-3.T.81/2 71/2 . 1-1A-9 Table 3-11.O. for 0. in thicknesses less than 0.Continued ALLOY & TEMPER OR COND BEFORE AGING 2018-T4 2025-T4 4032-T4 6151-T4 7075-W X7079 AGING TIME (HOURS)2/ 4-12 6-14 4-12 4-12 22 Minimum 5 days at room temperature followed by 48 hours at 230-250 degrees F 1-3 1-3 1-4 96 Minimum 1-6 1-6 1-6 6-12 9-11 21 days 1-3 1-8 1-6 1-6 1-6 14-18 AGING TEMP (DEGREES F)2/ 330-350 330-350 330-350 330-350 230-260 TEMPER AFTER AGING 2018-T6 2025-T6 4032-T6 6151-T6 7075-T6 X7079-T6 SAND CAST ALLOYS 142-T41 195-T4 S195-T4 220-W 319-T4 335-T4 356-T4 356-F 40 40PERMANENT MOLD CAST ALLOYS 142-T41 B195-T4 319-T4 355-T4 356-T4 A132-T45 400-450 300-320 300-330 300-320 300-320 300-350 142-T61 B195-T6 319-T6 355-T6 356-T6 A132-T65 400-450 300-320 300-320 room 300-320 300-320 300-320 430-450 345-365 room 142-T61 142-T6 S195-T6 220-T4 319-T6 335-T6 356-T6 356-T6 40-E 40-E 1/ Alternate aging treatment for 7075-W sheet only. 2/ Time is soak time af ter recorder is at temperature.) 3-26 Change 1 . 3/ The 96 hour minimum aging time required for each alloy listed with temper designation W is not necessary if artif icial aging is to be employed to obtain tempers other than that derived from room temperature aging. Times and Conditions . or load may be allowed to cool between the two steps of the treatment. The temperature may be raised directly from the lower to the higher temperature. Precipitation (Aging) Treating Temperatures. then heat 315o-335oF for 3-4 hours. (For example.T. natural aging (96 hours) to achieve the -T4 or -T42 temper for 2014 alloy is not necessary prior to artif icial aging to obtain a -T6 or -T62 temper.500 inch: Heat at 230o250oF for 3-4 hours.500 inch thickness or less. Add 1/2 hour for each additional 1/2 inch of thickness. the f irst heat treatment of material purchased in the heat treated condition is a reheat treatment. unless separate load thermocouples are employed. Furnace equipment shall be installed with the necessary furnace control.T.Temperature uniformity in a salt bath may be determined by use of a temperature sensing element enclosed in a suitable protected tube. Furnace temperature survey. A minimum of 9 test locations within the furnace load area should be checked. For all surveys. periodic surveys shall be made as outlined for the initial survey. the air and metal (load) temperature at any point in the working or soaking area shall not exceed the maximum soaking temperature (see Table 3-7) for the specif ic alloy being heat treated. The design and construction of the furnaces and baths should be such that during the recovery and soaking period. The temperature of all test locations should be determined at 5 to 10 minute intervals af ter insertion of the temperature sensing elements in the furnace. The maximum variation indicated by reading from the various locations in the load zone shall not exceed 20oF and no reading shall be outside the heat treating range specif ied for the materials involved. The monthly survey should be made at one operating temperature for solution treatment and one for precipitation heat treatment. Upon bringing a change to temperature. 3-62. For salt bath the same as above except one test location for each 40 cubic feet of air volume. and recording instruments to assure and maintain accurate control. Furnace thermocouple and sensing element should be replaced periodically. There should be a minimum of 9 test locations with at least one for each 40 cubic feet of heat treating volume. Nitrate charged salt baths should not be used to heat-treat aluminum alloys types 5056 and 220 due to the fact that the bath compound will attack the alloy. temperature measuring. 3-68. The temperature sensing element should be held in one position until thermal equilibrium has been substantially reached and reading made. 3-61. Other size furnaces should be checked with a ratio of test locations in accordance with those previously cited. 3-66. Temperature Control and Uniformity. Af ter all temperature sensing elements have reached equilibrium. one in the center and one for each 25 cubic feet of air furnace volume up to the maximum of 400 cubic feet. 3-64. Salt Bath Testing . 1-1A-9 Table 3-12. Good temperature control is essential to produce the exacting temper requirements for superior quality material. Upon the initial installation and af ter each change is made in the furnace which might affect the operational characteristics a temperature survey should be made. A monthly survey should be made af ter the initial survey. to record actual metal temperatures. 3-63.125 and less over 0. Insofar as this chart is concerned annealing and precipitation treatments are not considered heat treatments. Therefore. Reheat Treatment of Alclad Alloys THICKNESS (INCHES) MAXIMUM NO. The temperatures should be checked at the maximum and minimum required for solution and precipitation heat treatment for which the furnace is to be used. Temperature measuring instruments used for furnace control shall not be used to read the temperature of the test temperature sensing elements. OF REHEAT TREATMENT PERMISSIBLE 1 2 0. 3-27 .O. Temperature readings should be taken for a suff icient length of time af ter thermal equilibrium to determine the recurring temperature pattern. 40 test locations are recommended. The temperature sensing element should then be placed in a new location and the procedure repeated. the furnace and the load should be controllable with ±5oF of the required temperature range. the maximum temperature variation of all elements shall not exceed 20oF and at no time af ter equilibrium is reached should the temperature readings be outside the solution heat treating or precipitation range being surveyed. This is necessary due to oxidation and deterioration of the elements. These operations should be repeated until the temperature in all parts of the bath have been determined. 3-67.125 NOTE Heat treatment of a previously heattreated material is classif ied as a reheat treatment. the furnaces should be allowed to heat to point of stabilization before commencing the survey. Salt baths must be operated with caution to prevent explosions as any water on the material being treated is instantly transformed to steam upon imersion in the salt bath. one in each corner. 3-65. However. e.O. 3-75. The most common problems encountered in practice are springback and cracking within the bend area. 7178. NSN 7510-00-537-6928 (Black). At this point it should be explained that a substantial amount of the diff iculties encountered in heating aluminum alloys is due to improper or inadequate temperature control and circulation of heating medium. 1-1A-9 3-69. The forming operation should be performed as soon af ter quenching as possible.T. 3-72. 2. clean and free of rust and other foreign matter. the material adjacent to the other surface of the bend is under tension and the length is increased due to stretching and the material adjacent to and on the inner surface is under compression and the length is decreased. 7075. 3-74. FABRICATION.5% for material in the range of 0.063 . rough edges of material being formed or forming equipment and bending parallel to direction of grain f low.187 inch and 1. burrs and sharp edges. Provide clean area.7510-00-537-6930 (Yellow). especially on clad materials. c. The nominal cladding thickness is 4% of composite thickness for material under 0. then fabricators should proceed with additional caution and if needed.. For the approximate bend radius to use in bending various thicknesses and types of aluminum see Table 3-13. The formability varies considerably with alloy and temper. tools and work area should be kept smooth. 3-78. thickness and alloy in the range of ‘‘formable’’ material. The following general rules should be employed in the handling and forming operation: a. The clad coating referenced is usually a sacrif icial corrosion resisting aluminum alloy coating sandwiched metalurgically to an alloyed core material. GENERAL. in view of the natural aging that occurs at room temperature on all the heat treatable alloys. The thickness of the coating will depend on the thickness of the sheet or plate. using approximately the same procedures as those used for common steel except that care must be taken to prevent scratching. e. FORMING SHEET METAL. Alloyed aluminum (2024. should seek assistance of engineering or laboratory metallurgists. It can be fabricated into a variety of shapes by conventional methods. Specif ic application usually depends on the shape. For intricate forming operations it is necessary to use annealed (Con‘‘O’’) material and f inal strength developed by heat treating af ter the forming has been accomplished. which is much more formable than the fully heat-treated temper.063 inch. The lower the temperature the longer the delay to a point where maximum delay is obtained. Scratching will make forming more diff icult plus it provides an easy path for corrosion attack. Heat-treated alloys can also be formed at room temperature immediately af ter quenching (‘‘W’’temper). b. strength and temper of the alloy. All shop equipment. 3-28 . If tighter bend radii is required. Use only straight and smooth forming dies or brake leafs of the correct radius which are free of nicks. The natural aging can be delayed to a certain extent by placing the part in a cold storage area of 32o or lower. free of chips.188 inch and thicker. d. Use pencil. Problems associated with bend cracking are usually a result of improper bend radii. 3-76. The forming of aluminum (1100) is relatively easy. Sheared or cut edges shall be sanded and f iled or polished. etc. Form material across the direction of grain f low when possible. 3-79.) are more diff icult to form.5% for material 0. grit and dirt and other foreign material. f. BENDING. bar or rod. This portion is intended to provide some of the information required to fabricate the various aluminum products into parts and assemblies. Aircraf t Marking. Provide clean smooth (rust free) and adaptable forming equipment. 3-73. Specif ication MIL-P-83953. The part is then aged to develop full strength. When diff iculties arise the function of these units should be checked prior to performing other system test. and 7510-00-537-6935 (Red). Upon bending sheet metal. the material at the bends f lows or deforms i. 3-77. Diff iculties encountered with springback are most commonly associated with bending of the 3-71. Actual practice may reveal that a larger or a smaller radius may be used in some instances.0. and extensive control is required to prevent scratching and radii cracking. Material should be of the correct temper. 3-80. Aluminum is one of the most workable of all the common metals. Do not mark on any metal surface to be used as a structural component with a graphite pencil or any type of sharp pointed instrument. The preceeding will necessitate that the mechanic be well trained to cope with the variables associated with this material especially when the end use of the item is an aircraf t or a missile. 3-70. prior to bending or forming. Bending is classif ied as single curvature forming. 16 0.03 0.02 0.06 0.03 0.1875 3T 3T 5T 3T 3T 1. Avoid reducing radii to the point that grain separation or bend cracking results.187 0.03 0.250 0.187 0.5T 4T 4T 4T 6T 6T 0.03 0.06 0.250 0.160 0.09 0.03 0.5-4T 4T 4T 3T 5T 5T --0.03 0.040 0. The amount of overforming utilized will depend on the temper and the alloy.06 0.06 0.06 0.19 0.5T -0.09 -2T 2T 0. 1-1A-9 stronger alloys.250 31/2T 41/2T 6T 4T 4T 1.016 0.5T 4-6T 6T 6T 6T 6-8T 6-8T 8T -0.5-1.5T 2T 2T 1T 1T 11/2T 2T 2T 2T 0.02 0.5-1.03 0. Springback problem associated with this material can be overcome to a certain degree by overforming.03 0.063 0.T81 2024-T4 2024-T3 2014-T3 7075-T6 7178-T6 7050-T7 7475 0.125 0.06 0 2T 2T 0.03 0 0.250 0.5T 0.03 0.44 1-2T 3T 3T 11/2T 11/2T 2T 3T 5T 5T 3-29 .5T 2T 2T 1T 1T 2T 2T 21/2T 21/2T 0. especially those having high yield strength.5-2.03 0.06 0. required.03 0.06 0.03 0.160 0.O.06 0.03 0.250 0. the sof ter the material the less springback compensation Table 3-13.125 0.250 0.032 0.312 0. Other means of reducing springback is to bend the material in the sof t condition (Condition ‘‘O’’) or immediately af ter quenching and reducing the thickness or the radius if allowed.1875 0.06 0.T.03 0.064 2T 2T 3T 2T 2T 1-2T 3.03 0-1T 2-3.5-1.5-2.06 0.03 0.06 0.03 0.03 0.5T 21/2T 21/2T 11/2T 11/2T 21/2T 21/2T 4T 4T 0.125 21/2T 21/2T 4T 2T 2T 1-2T 4-6T 5T 5T 5T 6T 6T --0.06 2T 2T 2T 0.06 0.03 0.03 0. Cold Bend Radii (Inside) for General Applications Alloy and Temper 0.06 0.03 0.06 --- Sheet Thickness = T (Inches) 0.5T 5-7T 6T 6T 6T 9-10T 9-10T 9T -9.032 2T 2T 2T 2T 2T 0-1T 2.03 0.06 0.03 0.016 1100-0 3003-0 5052-0 6061-0 2014-0 2219-0 7075-0 7178-0 1100-H12 3003-H12 5052-H32 1100-H16 3003-H16 5052-H36 1100-H18 3003-H18 5052-H38 6061-T4 6061-T6 2219-T4 2219-T62.03 0.06 0.1875 0.187 0. kirksite and plastic for medium or short run production. f inish of die. the material is formed in the annealed ‘‘O’’temper. Most of the common alloys are formed in the annealed condition. The design of foam block for hydropress forming require compensation for springback even through the material normally used is Condition ‘‘O’’ or annealed.T. Selection of a system or condition of material to be utilized will require experimentation and the subsequent utilization of the system that gives the best results. The press forming operations are usually accomplished by setting the form block (normally male) on the lower press platen and placing a prepared sheet metal blank on the block. the non-heat treatable alloys can only be annealed to relieve the effect of work hardening. Normal practice is to under cut the form block 2-7o depending on the alloy and radii of the form block. which is limited to AMA level repair facilities. 3-82. Stretch forming is usually accomplished by gripping two opposite edges f ixed vises and stretching by moving a ram carrying the form block against the sheet. material allowance on blank. kirksite and some types of hard setting molding plastic have been used successfully as form blocks to press sheet metal parts such as ribs. to prevent shif ting of blank when the pressure is applied (the sheet metal blank should be cut to size and edges deburred prior to pressing). Draw forming is accomplished by forcing the male die and the metal blank into the female die. Condition ‘‘O’’ material of the heat treatable alloys can be heat treated af ter drawing to obtain higher strength and to relieve the effect of work hardening. elongation factor of material. heat treated and reformed. shape of blank. 3-85. and phenolic and hardwood for piece production. such as contoured skin. HYDRAULIC PRESS FORMING. radii of die forming surfaces. As previously stated the material should be reformed as fast as possible af ter heat treatment. Results will depend on die design. DROP HAMMER FORMING. The rubber sheet used should have a shore hardness of 50-80 durometers. where the shape is not too deep or where narrow width material is used. 3-87. 3-86. fans. DRAW FORMING. surface clearance between punch and female die. to eliminate distortion resulting from heat treatment. The blank is located on the block with locating pins. The disadvantage is high cost of initial equipment. Also. Material used for stretch forming should be limited to alloys with fairly high elongation and good spread between yield and tensile strength. Because of the work hardening resulting from each draw.O. temper. spars. The drop hammer can be used to form deep pan shaped and beaded type parts. The surface of kirksite dies used without plastic insert should be smooth to prevent galling and scratching of the aluminum surface. The rubber pad hydropress can be utilized to form many varieties of parts from aluminum and its alloys with relative ease. This material should not be annealed if high strength is the major requirement. In severe conditions an intermediate anneal is sometimes used. In some instances the material is formed immediately af ter heat treating and quenching. the condition of the material is more uniform than that obtained by hand forming. However. The advantage is uniform contoured parts at faster speed than can be obtained by hand forming with a yoder hammer or other means. some types of large radii contoured parts can be formed with a combination of hand forming and pressing operations. blank hold down pressure. beads and lightening holes. Drawing of very deep shells require more experimentation and the utilization of a succession of limit draws. Stretch forming is normally restricted to relatively large parts with large radii of curvature and shallow depth. 3-84. 1-1A-9 3-81. STRETCH FORMING. For the deeper curved shapes. the form block forcing the blank to conform to the form blocks contour. However. masonite. Kirksite with a plastic surface insert is satisfactory for male and female dies. When forming deep pans and complicated shaped parts it is 3-30 . and lubricant. drawing speed. The recommended material to manufacture drawing dies is hardened tool steel for large scale production. 3-83. shape of part being formed. It is recommended that additional rubber be supplemented in the form of sheets when performing the above to prevent damage to the rubber press pad. The ram pressure being suff icient to cause the material to stretch and wrap to the contour of the form block. etc. It is possible to stretch form the heat treatable alloys in tempers T4 or T6. Optium results usually requires experimentation and adjustment of one or more of these factors. Phenolic. This process involves stretching a sheet or strip to just beyond the elastic limit where permanent set will take place with a minimum amount of springback. Generally mechanical press either single or double action and hydraulic presses are used to perform the drawing operation. Draw forming is def ined as a method where a male die (punch) and a female die is used to form a sheet blank into a hollow shell. The rubber pad f illed press head is then lowered or closed over the form block and the rubber envelope. reduction in successive draws must be less. This type forming is usually limited to relatively f lat parts having f langes. Normally most aluminum alloys can be sheared 1/2 inch and less in thickness except for the harder alloys i. Equal formability will be obtained with shorter periods of heating in most cases and the minimum times should be used. 7075-T6 and 7178-T6. 7178. The inside joggle radii should be approximately the same as used for straight bending. The above will naturally require that tooling used be designed to handle the thickness of material to be cut. Frequent checks should be made using an accurate contact pyrometer. These alloys have a tendency to crack in the vicinity of the cut especially if the sheer blades are dull or nicked. HOT-FORMING. 3-90. size of cut and the relationship of the width of the cut to sheet thickness. Correct clearance between shear blades is important for good shearing. tallow or ordinary soap can be used as a lubricant. The higher the temperature the easier formed. For this reason mass production of parts is impractical. 3-91.T. Spinning is an art and makes exacting demands upon the skill and experience of the mechanic performing the operation. When the capacity of shear is doubtful the shear manufacturer should be consulted. 1100. etc. An intermediate anneal is sometimes used to relieve the hardened condition (cold work) resulting from the forming operation.) and approximately four times the depth for the higher strength alloys (7075. 3-94. 3-88. 3-31 .e. 6061. Hot forming is not generally recommended. annealed material should be used with heat treatment to follow.. Aluminum soap. Forming by spinning is a fairly simple process. 3-92. 1-1A-9 of ten necessary to use drawings rings. JOGGLING. The losses in strength as a result of re-heating at the temperature cited by this table will not exceed 5%. Hot forming is used in some instances when spinning the heavier gauge materials and harder alloys. 2014. Normal clearance is from one-tenth to oneeighth the sheet thickness. Joggle run out or length as a normal rule should be three times the depth of the joggle for the medium strength alloys (2024. 3-93. the disc is molded to the form block by applying pressure with a spinning stick or tool. condition of material. type of shear or knife blades. it is sometimes used where it is not possible to form an article by other methods. Other alloys can be used where the shape to be spun is not excessively deep or where the spinning is done in stages and intermediate annealing is utilized to remove the effect of strain hardening (work hardening) resulting from the spinning operation.. it can be used to advantages where only a few parts are required and to assist in the removal of buckles and wrinkles in drawn shell shaped objects. 7079 etc). Actual formability will depend on the temperature that various alloys are heated. 5052. SPINNING. however. Excessively high temperature shall not be used. Accomplishment shall not be attempted unless adequate facilities are available to control temperature requirements. Accurate shearing will be affected by the thickness of material. Blade life will be prolonged by occasionally lubricating. an aluminum disc (circle) is placed in a lathe in conjunction with a form block usually made of hardwood. as the disc and form block are revolved. Too little clearance will quickly dull or otherwise damage the blades or knives. or even to fold between blades. A joggle is an offset formed to provide for an overlap of a sheet or angle which is projecting in the same plain. too much will cause the material to be burred. pads or 2-3 stage dies. Table 3-14 cites the recommended times and temperature (accumulative) for the various alloys. adjustment and sharpness of blades. as considerable loss in strength and corrosion resistance will occur. The best adapted materials for spinning are the sof ter alloys i. 3-89. It should be understood that this table cited the maximum accumulative times at cited temperature. Where deep and tight joggles are required. 3003. However. BLANKING AND SHEARING. etc.e.O. 3-95. Tables 3-15 through 3-16 deleted. Paragraphs 3-96 through 3-155 deleted. Maximum Accumulative Reheat Times for Hot Forming Heat Treatable Alloys at Different Temperatures ALLOY 2014-T6 2024-T81 2024-T86 6061-T6 7075-T6 450oF To Temp 5 Min 5 Min 5 Min No 425oF To Temp 15 Min 15 Min 15 Min No Temp No No 400oF 5-15 Min 30 Min 30 Min 30 Min 5-10 Min No No 375oF 30-60 Min 1 Hr 1 Hr 1-2 Hrs 30-60 Min No No 350oF 2-4 Hrs 2-4 Hrs 2-4 Hrs 8-10 Hrs 1-2 Hrs No No 325oF 8-10 Hrs ----5-100 Hrs 2-4 Hrs No No 300oF 20-50 H 20-40 H 10-20 H 100-200 H 10-12 H No No *2014-T4. However. 1-1A-9 Table 3-14. Pages 3-33 through 3-38 deleted. 2024-T3 No * These materials should not be hot formed unless subsequently artif icially aged. The essential factors requiring control are die clearance. The shearing principle is primarily the same as that encountered with the squaring shear. Suitable lubricants are engine oil. Blanking is usually accomplished utilizing a blanking die in almost any type of punch press equipment.T. the method of grinding punch dies will vary according to the results required and in such manner that will reduce load on equipment. Commonly two or more high points are ground on die to keep side thrust on the punch at a minimum. Lubrication is essential in blanking operations. BLANKING.O. 3-32 Change 1 . shearing edge lead. 2014-T3 No *2024-T4. and stripping action. kerosene and lard oil which are normally used in mixed form. . Rivets in aluminum alloys 1100(A). The rivets used in USAF Weapon System structures require that the alloys and shapes be closely controlled by specif ication/standards. The most common alloys utilized are aluminum because the structure alloys are normally aluminum. Typical advantages of this method of mechanical fastening are simplicity of application. sizes. 1-1A-9 3-156. 3-157. Deleted. RIVETING. If for some reason it is necessary to determine if a rivet has been heat treated this may be done by Rockwell Hardness testing. Test by supporting rivets in a vee block and hardness reading taken with a 1/16 inch ball 60 kilogram load . discontinue use. The customary procedure (unless only a few rivets are involved) is to place the rivets under refrigeration immediately af ter heat treatment The time the rivets may be used will depend on refrigeration equipment available. for general rivets used on AF weapons systems. In addition some of the aluminum rivet characteristics can be changed by heat treating which facilitates application (see paragraph 3-37. due to some alloys having superior properties they have been selected as standard. 3-163. Riveting is the most common method of assembling components fabricated from aluminum. Cooling rivets +0-10oF and below will retard natural aging to the extent that the rivets may be retained for use indef initely. hishear. These rivets are presently classif ied as solid shank. All of the aluminum alloys could be used to manufacture rivets. Deleted. 3-166. low cost.T.O. however. lengths and types. 3-160. easily inspected (X Ray and other type equipment not required. If inspection reveals that rivets are cracked. Rivets in alloy 2017 and 2024 should be driven immediately af ter quenching with a maximum delay of 20 minutes or refrigerated to delay aging. alloys. 2117(AD) are used in the condition received Alloys 2017(D) and 2024(DD) of ten referred to as ‘‘Ice Box Rivets’’ require heat treatment prior to use (see paragraph 3-43). 3-167. 5056(B). Cooling to 32oF will retard natural aging to the extent that the rivets may be driven up to 24 hours. 3-159. 3-161. identif ication. and in many cases lighter weight. Deleted. blind (structural-non-structural) explosive/ chemical expanded. Deleted. consistent joint uniformity. Deleted. remove defective rivets and obtain reheat treated rivets prior to continuing the assembly operation. Deleted.) 3-164. 3-158. They are available in a variety of shapes. Rivets utilized with extended driving time should be closely inspected af ter upsetting for cracks. (3-39 blank)/3-40 Change 1 . etc. 3-165. 3-162.). A hardness of over 75 will indicate a heat treated rivet.. See Table 3-17 for alloys head. MS/AN standard cross references. to assure structural integrity and uniformity. Ps=ultimate shear strength (pounds). Theoretical rivets holes should be completed i. The formula Ps = Sb AC can be used to determine failure in bearing strength. The salt from the bath will contaminate cracks and crevices of the assembly and complete removal can not be assured.750 1.pitch is the distance between the center of two adjacent rivets on the same gauge line. A=cross sectional (area of the driven rivet. Sb = specif ied ultimate bearing strength of the plate (psi) and AC = projected crushing area (bearing area) of rivet. material separation and buckling which weakens the structural strength of the rivet joint. The rivet hole should be drilled. Ts=ultimate tensile strength (pounds). 3-172. To overcome these problems requires that holes be pilot drilled end reamed to size at time rivet is to be installed.003 for thin sheet and up to about 0. reamed to size.e.O. drilled. A=diameter of hole (inch) and Tp=thickness of plate. Shear strength (ultimate) of a driven rivet can be determined by the formula Ps=SsAN. and corrosion attack of rivets and material af ter equipment is placed in service/use.) before starting to rivet assembly.000 inch thick material) required to insert rivet without forcing. chips removed that may lodge or be trapped in between surface of metal and treated (anodized etc. D=pitch of the rivets (inch) . 3-169. 1-1A-9 CAUTION Heat treatment and most other operations requiring use of heat will be accomplished prior to installing rivets. PT = specif ied ultimate tensile strength of the plate (psi). 3-168. Ss=specif ied shear strength of the driven rivet (psi). (2) prevents 3-41 . deburred. since heating af ter rivets are installed will cause warping and possible corrosion if salt bath is used. normally equal to hole cross section (square inch) and N=number of shear planes. Unless otherwise specif ied rivets should be selected that have comparable strength and alloy as material being assembled. Ps = ultimate bearing strength of the joints (lbs).. Rivet hole preparation is one of the key factors in controlling successful upsetting of rivet head. punched/reamed to size that allows the minimum clearance (apprximately 0. For shear strength of protruding and f lush head rivets see Table 3-19. The following tables are provided as a general guide for selection of rivet alloy vs assembly alloy. 3-171. This method has a twofold purpose: (1) allows easy insertion of rivets.020 for 0. The load required to cause tensile failure of a plate in a rivet joint can be determined by the formula Ts=P+ (D-A) Tp. This is an important factor in preventing corrosion from dissimilar metal contact and to assure structurely sound assemblies. The above cannot always be accomplished especially where the assembly is large and requires the application of a large amount of rivets due to hole tolerance and variations in holding clamping/pressures. 3-170. Rivet Selection. or diameter (sq in) see table 3-20 for typical bearing properties of aluminum alloy plates and shapes.T. O. 1-1A-9 elongation of rivet holes and resulting weakening of rivet joint.T. Two methods for coating rivets and improving protection of hole surfaces from corrosion are: General Rivet (Alum) Identification Chart OLD AN/ STD AN456 USAF460 SUPERSEDING MS STD FORM MATERIAL See AN470 See MS20601 See MS20601 Same Same 1100 5056 2117 2017 2024 HEAD AND NUMERICAL IDENT CODE CONDITION HEAT TREAT MS20470 See MS20601 Brazier Head Solid Modified 1000 Flush Head Blind Type II Class 2 Protruding Head Type II Class I Blind Same Same Universal Head Solid USAF461 See MS20600 USAF463 NAF1195 AN470 See MS20600 See MS20600 MS20470 A-Plain B-Raised Cross AD-Dimple D-Raised Dot DD-Raised Dash B AD M B AD M B F F T-4 T-4 T-4 F T-4 F T-4 F No No No Yes Yes No No No No No No No MS20600 Protruding Head-Blind Type II. Class 2 Protruding Head Blind Chemically Expanded Type I. 3-173. Class I. Styles A & B o 5056 2117 Monel 5056 2117 Monel 5056 MS20601 MS20602 2017 D T-4 No 3-42 . chromate primer or other approved material. Class I 100 Flash Head Blind Type II. Rivet holes drilled/reamed af ter assembly is started should be treated by coating with zinc Table 3-17. T. etc. General Rivet (Alum) Identification Chart .Continued OLD AN/ STD SUPERSEDING MS STD FORM MATERIAL 5056 2117 HEAD AND NUMERICAL IDENT CODE B AD CONDITION HEAT TREAT MS20604 Universal Head Blind Class I Non Struct F T-4 No No No Monel M or MP (MP = Monel Plated) MS20605 100o Flash Head Blind Class 2.O. For other information on rivets see T. Non Struct 5056 2117 B AD F T-4 No No No Monel M or MP (MP = Monel Plated) 5056 2117 B AD F T-4 MS20606 Modified Trusshead Blind Class 3 Non-Struct No No No Monel M or MP (MP = Monel Plated) 1010 Recessed Triangle Annealed C-None CW Annealed Raised Dots Class A Annealed MS20613 Universal Head Solid No 302 MS20615 Universal Head Solid Copper Monel No No No NOTE: Copper. specif ication.O. For special rivets see manufacturing drawing. steel. and monel listed for information purposes only. 1-1A-8/1-1A-1. 1-1A-9 Table 3-17. data. 3-43 . Copper 302/304 A A No No Monel AN441 AN442 AN450 Use MS20435 Use MS20470 MS20450 See AN435 See AN70+ MS20470 Countersunk & oval tubular 1006/ 1010/ 1015 Copper 2117 Brass MONEL AN455 MS20470 Brazier Head Solid Superseded by Universal. 1-1A-9 Table 3-17. A T-4 Grade B A No No No No 3-44 .T. See AN470 Blank/ None C-None AD-None B-None M-None A No Note: Listed for Reference only. AN427 MS20427 Countersunk 100o 1006/ 1010 Copper 302/304 Monel M AN430 AN435 MS20470 MS20435 Round Head Solid 1006 A A A No No No Round Head replaced by universal See AN470 + M520470 A No NOTE: Listed for Reference only. General Rivet (Alum) Identification Chart .O.Continued OLD AN/ STD AN426 SUPERSEDING MS STD FORM MATERIAL 1100 5056 2117 2017 2024 HEAD AND NUMERICAL IDENT CODE A-Plain B-Raised Cross AD-Dimple D-Raised Dot DD-Raised Dashes Recessed Triangle C-None FRecessed Dash M-None Head Ident Recessed Triangle C-None F-Head Ident None M-None CONDITION HEAT TREAT MS20426 Countersunk 100o F F T-4 T-4 T-4 No No No Yes Yes NOTE: See paragraph 3-44 for heat treat data. ) see MIL-HDBK-5. strength. 3-174. heat treatability. Dipping rivet in zinc chromate primer and installing while still wet.H16 and H18. The resistance encountered in cutting alminum alloys is low in comparison to other metals. 2024. b. moderate feeds and depths of cut. factors. 7075 and 7178 5052 and magnesium alloys. General Aluminum Rivet Selection Chart (Rivet Alloy vs Assembly Alloy) Rivet Alloy 1100 2117-T4 (AD) Assembly Alloy 1100. Rigid support of tool near cutting edge to minimize clatter and vibration. 2014. because it does not break as easily as the other types. d. e. 2017. 5052 3003 . Secure clamping of work to machine to avoid distortion or slippage. In fact most of the aluminum alloys will machine approximately 10 times faster than steel. CUTTING TOOLS FOR MACHINING ALUMINUM. weight. 1-1A-9 Table 3-18.’s 11A-8 and 1-1A-1. There are four general types of tool steel material that can be used to machine aluminum. corrosion resistance. b.O. 3-176.. grinding and maintaining tools for cutting aluminum: 3-45 . machining. cutting compound or coolants to prevent overheating. For additional information on rivets (strengths. a.H16 and H-18. d. 2017. The higher speeds utilized for machining aluminum requires: a. physical form (cast or wrought) and temper. 3003. Apply lubricant/coolant in large quantities to tool when cutting. smooth. 7075. etc. feeds. wire edges and scratches. Keep cutting edges of tools sharp. c. Design tools (grind tool) so that chips and cuttings are expelled away from the work piece. 3-177. 6061. 6061.. 2024. 3004. Use of proper lubricant. taps. High carbon tool steel is adequate for machining a small number of parts or where cutting speed required is relatively low. etc. etc. They should be selected in accordance with availability and scope of job to be accomplished. This factor combined with other properties. Stock material is 2017-T4 (D). The following is a suggested guide for selection of tools: a.. 5052 . etc. 5052. c. Brass (free machining) is the only other material with comparable machining properties. required to effectively accomplish a specif ic task. Allow more space for chips to be formed and expelled from tool than allowed for steel. 3-179. Machines be free of vibration and lost motion. The purpose of this section is to provide a general guide for selection of tools.e. The more ductile or sof ter the alloy the more rake required.O. The amount of rake required will depend on composition. 2024T4 (DD) 5056-H32 (B) a. The tools used for machining aluminum will normally require more rake side-top and operation at higher/feeds than used for steel. speeds. This material will exceed the performance of some of the other types of tools when used for fragile tools such as drills. MACHINING. free of burrs.T. makes aluminum a preferred material in many instances for fabrication of parts by machining. The following general practices are recommended for shaf ing. Spraying holes with primer af ter drilling and immediately preceding installation of rivet. etc. T. tools etc. Due to various circumstances personnel familiar with machining steel products are required to machine aluminum without proper training/information on speeds. Personnel accomplishing the work should be properly trained in machining aluminum as with other types of metals. i. and 7178 2014. 3-175. b. AZ31B. Use high machining speeds. warpage/distortion and to provide adequate lubrication to cutting tool. 3-178. Tool alloys should be selected for milling aluminum as follows: a. Recommend top rake angles of 12o . In practice it will be found that some machining operations can be performed dry.20o and front clearances of 4o . reasonable cost. All the various classes (T1. collet or faceplate. Sof t liners may be used between work and machine jaw faces to prevent jaw teeth from damaging/marring work piece. (1) Availability.8o grind face concave (slightly) and so that corner adjacent to work will lead opposite corner by 4o . lard oil such as Specif ication C-O-376 or mineral oil. b. For heavy cutting especially when speeds are low. b. 3-183. The carbide tools have been known to last thirty times longer than high speed tool steel. Where climb milling/high speeds are utilized.12o or as required for best results. Nick tooth cutters are used when reduction in size of chips is required. c. Where long production runs are involved cemented carbide (solid or tipped) tools give better service. TURNING. Sturdy construction of tools and holders is essential to minimize vibration/chatter at the high speeds aluminum alloys are machined. 3-182. carbide tipped tools are recommended for extended runs. This will normally clear as the speed is increased. T2.T. Class T1 (18-4-1) general purpose type is the most widely used. Long rods/ stock should be supported by ball or roller bearing tailstock centers which are more satisfactory than solid or f ixed centers in resisting thrusts from centrifugal force and thermal expansion. The tooling for milling should be selected according to the operation and duration/size of job to be performed. 3-185. The carbide tools are also recommended for cutting high silicon content alloys. 3-180. T3.90o are used with top rake angles of 6o . NOTE Parting tools should have less top rake than turning tools. Normal cutting of 75o . 3-184. c. To properly perform the turning operation f irmly attach the work to the machine (lathe) chuck. (2) Heat resistance (will retain cutting edge up to about 950oF dull red).O. Because of the brittleness of the cemented carbide tool the cutting angle should be greater than those recommended for high carbon/high speed steels. The cutters should have fewer teeth and should be ground with more top and side rake than those used for milling steels. Milling of aluminum alloys should be accomplished at high cutter speeds.10o. (3) Permits use of large rake angle required. The work should be held in the best manner to minimize distortion from chuck or centrifugal force action during the turning operation. Tool projection in relation to work should be set at or slightly above work piece center line. High speed tool steel is the most common type used for machining except on the higher silicon alloys. When cutters with large helix angles are used it is of ten necessary that two interlocking cutters of opposite helixes be employed to alleviate axial thrust. The reason for the higher cutter speeds is that at low speeds the cutters will have a tendency to load and gum. Specif ication VV-O-241 is recommended. For production runs of extended duration high speed steel is recommended. d. Solid-tooth cutters with large helix angles are used where free-cutting tools are required.ALUMINUM. The recommended cutting f luids are the soluble oil emulsion which combine the functions of cooling and lubricating for general purpose use.) may be used for machining aluminum. The limitations will usually depend on the machine and type cutters used. 1-1A-9 obtainable in accordance with Federal Specif ication QQ-T-580 where required for local fabrication of high carbon tools etc. Tables 3-22 and 3-23 cite suggested turning speeds. Tool projection (or set) should be slightly above center line (CL) of the work. 3-46 . Federal Specif ication QQ-T-590 applies to stock material. Most operations can be accomplished with spiral cutters. Diamond tipped tools should only be used for light f inishing cute or special f inishing operations. tool angles and feeds. MILLING . 3-181. When it is necessary that work be held by clamping from inside diameter outward the tightness of jaws should be checked frequently to be sure that work is not being released as a result of thermal expansion. etc. For short runs high carbon steel is normally satisfactory. 000 0.753 0.460 2.984 0.000 0.360 3/8 3.090 1.000 lbs per square inch.000 0.0984 0.O.018 0.000 3-47 .032 0.020 1/16 0.970 4.760 1.964 0.040 0.250 Double shear rivet strength correction factor (resulting from use in thin plates and shapes) SIZE OF RIVETS Sheet Thick Inch 0. FSU = 38 KSI 2024-T31.110 3. Sheet thickness (in) 0. Single shear rivet strength correction factor (resulting from use in thin plates and shapes).510 3.0996 1.025 0.996 1.996 1.016 0. FSU = 34 KSI 2017-T3.0964 0.090 0.996 1.280 3.980 0.045 0.190 0.T.125 0.290 2.036 0.050 0. FSU = 41 KSI 1/16 99 106 120 135 145 3/32 203 217 297 275 296 1/8 363 388 442 494 531 5/32 556 596 675 755 815 3/16 802 862 977 1.100 0. FSU = 30 KSI 2017-T31.980 0.160 0.964 0. 1-1A-9 Table 3-19.063 0.972 1.792 3/32 1/8 5/32 3/16 1/4 5/16 3/8 0.000 0.972 1.000 0.450 4.800 FSU = Average Shear Strength of alloy in specif ied temper.688 0.016 0.000 0.970 3.000 0.180 1/4 1.018 0.996 1.450 1. Shear Strength of Protruding and Flush Head Aluminum Alloy Rivets.972 1.071 0.964 0.120 5/16 2.974 0.980 0.970 2. Inch Pounds Size of Rivet(In Dia) Alloy + driven temper 5056 FSU = 28 KSI 2117-T321.020 0.550 1.080 0. KSI = 1000 lbs square inch example: 34 KSI = 34.964 0. 000 0.Continued 0.883 0.000 12.987 1.857 0.160 0.0 3003 .000 19.000 34.935 0.000 0.831 0.688 0.896 0.H16 3003 .000 26.125 0.870 0.100 0.000 21.922 0.857 0.000 0.050 0.935 1.987 1.000 36.190 0.036 0.H14 1100 .000 23.974 1. of Aluminum Alloy Plates and Shapes Edge Distance = 1.040 sheet.000 16.000 23.996 = 388 0. Inch Pounds .961 1.000 21.000 38.000 38.883 0.5 X Rivet Diameter Alloy 1100 .000 27.000 0.000 0.714 0.H16 1100 .H18 3003 .250 0.045 0.000 28.974 1.H12 1100 .071 0.922 0.688 0.000 27.000 Ultimate Strength 27.996 2328 3492 3492 386.448 corrected shear pounds Table 3-20.714 0.000 29.714 0.792 0.688 0.090 0. Example: Rivet diameter 1/8 (alloy 2117 .0 1100 .000 0.000 33.870 0.740 0.080 0.T3) installed in 0.883 0.000 23.896 0.792 0.000 32. Shear Strength of Protruding and Flush Head Aluminum Alloy Rivets.000 Note: Values (lbs) of shear strength should be multiplied by the correction factor whenever the D/T = rivet diameter/plates sheet or shape thickness ratio is large enough to require correction.935 0.000 42.792 0.000 46.063 0.032 0.961 1.835 0. Bearing Properties.818 0. shear factor is 388 lbs correction factor 0. 1-1A-9 Table 3-19.T.974 0.792 0.000 24.818 0.000 0.688 0.000 22.000 32.831 0.818 0.740 0.000 Ultimate Strength 21.025 0.000 38.740 0.000 Edge Distance = 2.974 1.919 0.000 34.000 22.753 0.870 0.000 24.948 0.000 3-48 .935 0.000 18.000 31.0X X Rivet Diameter Yield Strength 12.O.000 15.040 0.H12 3003 .H18 Yield Strength 10. Typical.000 34. 000 102.T3 Alclad 2024-T-3 2024 .000 84. size. for milling aluminum. kind of tool material.T6 Alclad 7075-T6 Yield Strength 56. Secure clamping of work is re-emphasized especially when heavy cutting feeds are to be used.000 122.000 Ultimate Strength 93. contour and tool angles.000 73.000 Ultimate Strength 118.000 47.018 inch).000 72.T6 2024 . The best combination of cutting speeds. clamping method and type material being worked. Finishing tool shall be used with f ine feeds only due to the additional side and top rake (f inish cut should not exceed 0.T6 7075 .000 58.000 82.T4 6061 . mixture of 50-50 lard-oil and soluble oil.000 139. Milling cutters should be inclined to work and beveled on leading corner (least bevel for f inish cuts) to minimize clatter. 1-1A-9 Table 3-20.000 115. Recommended cutting compounds are kerosene.000 101.000 54.Continued Edge Distance = 1.000 107. The slower cutting speeds can be overcome to some extent by securely anchoring the work to the machine and using heavy rough cutting feeds. The cutting f luids for milling aluminum should combine cooling and lubrication properties. Coolant lubrication should be applied under pressure (atomized spray if available) in large quantities to tool and work. The recommended cutting f luids are water base cutting f luids such as soluble oils and emulsions.000 80.000 156. condition of machine. SHAPING AND PLANING.H34 5052 . 3-189.000 91.000 78. feed and cut for a given job will depend on design of tool/cutter. 3-190.000 71.000 29.000 66.000 42.O. The tools used for rough cut should be (round nose) of heavy construction and properly ground to operate eff iciently. tool angles and feeds.H32 5052 . Bearing Properties. 3-188.000 144.000 100.H38 6061 . Tables 3-26 and 3-27 cite suggested turning speeds. Typical.000 34. 3-187.000 94.000 50.000 114.000 96.000 61.000 59.000 105.T.000 3-186.000 74.000 30.000 47.5 X Rivet Diameter Alloy 2014 .000 86.000 60.000 46. 3-191.000 64. Finish tool should have more top rake and an extra large amount of side rake.000 127.T36 Alclad 2024-T36 5052 .000 85.000 62.T4 2014 .000 56. of Aluminum Alloy Plates and Shapes .000 123. Tables 3-24 and 3-25 cite suggested speeds.000 110.000 96.000 41.000 74. Rough cut tools should be ground with moderate amount of rake to provide maximum cutting edge support.000 94.000 Edge Distance = 2.0 5052 . Most cutting operations by shaping and planning can be accomplished without cutting f luids.000 56. 3-49 .000 133. mixed 1 part to 15 for high speeds and 1 part to 30 for low speed cutting.H36 5052 .000 37.0X X Rivet Diameter Yield Strength 64.000 69.000 54. The speed at which aluminum alloys can be cut by planing and shaping is somewhat slower in comparison to other machining methods.000 129. however f ine f inishing can be improved by lubrication. due to equipment design and limitations.000 64. machine power.000 25. 1-1A-9 Table 3-21. Standard type twist drills may be used satisfactorily for many drilling operations in aluminum alloys. Spiral Angle: 24o . Standard Rivet Hole Sizes with Corresponding Shear and Bearing Areas for Cold Driven Aluminum Alloy Rivets 3-192. 3-50 Change 3 . especially in deep hole drilling operations. better results can be obtained with improved designed drills where sof t material and drilling of thick material or deep holes are involved. Drill press.28o for thin stock and medium depth holes up to 6 times drill diameters. However.T.48o for deep holes over 6 times drill diameter.140o for general work and 90o 120o for high silicon. These drills are usually designed having more spiral twists per inch (see f igure 3-2). The following is a general guide for the selection of drills and recommended speeds: a. type alloy and machine/drill motor to be utilized. Generally a drill for a given job should be selected according to the thickness. 24o . Point Angle: 118o . 3-193.O. The additional spiral twist gives more worm action or force to drill causing the drill to cut/feed faster and is helpful in removing chips. DRILLING ALUMINUM ALLOY. 220.1300 700 . 214.8000 At Minimum vibration 0.0.T. 43 0. T6. H38 T4.2500 0.008 Maximum 0.010 Maximum 0.1500 0. HIGH SILICON SERIES 0. Turning Speeds and Feeds ALLOY TYPE AND TEMPER Sof t Series. 122 HARD SERIES 0.004 Finish 5052-H34. 1-1A-9 Table 3-22.0. 212 750.040 Maximum 1500 .200 Maximum 400 .0.007 .002 . 113 138. 132.010 Maximum Rough Finish Rough At minimum vibration 600 Maximum 0.0.7000 6000 .020 Maximum 500 .120 Maximum 0.007 . A132.250 Maximum 0.1600 FEED.250 Maximum 0.020 600 Maximum 0.020 Maximum Not recommended 0. 2024-T3 7075-T6.004 0.020 Rough Plain high carbon/high speed Plain high carbon/high speed Carbide Carbide Diamond tipped Diamond tipped Plain high carbon/high speed Plain high carbon/high speed Carbide Carbide 108. IN.002 .020 Finish Rough 0. etc. 319. H14 CUT INCHES CUTTING SPEED FPM 700 .005 Rough Finish Finish only Diamond 0.3500 0./REV OPER TOOL MATERIAL Plain high carbon/high speed Plain high carbon/high speed Carbide Carbide 0.012 Maximum 0.020 Maximum 600 Maximum 0. 1100 All temp 5052-H12.050 Maximum Rough 0.650 0.O.010 Maximum 0.015 Finish 2011-2024-0 5056-0-6061-0 7075-0. 356 0. H36.004 Maximum Rough Finish 3-51 .0.002 .002 .006 Maximum 0.004 Finish 4032.200 Maximum 0.1000 500 .0.020 Maximum 0.120 Maximum 500 .004 . 333.010 Maximum 4000 .0. 7178T6 6061-T4. 004 .2000 Ft/minutes 10 Maximum FEED Inches per tooth 0.020 Finish Rough Finish Rough Finish 3-52 .0-025 0.O.0.Turning TOOL ANGLES Cutting Angles Top Rake Side Rake Front Clear Side Clear PLAIN HIGH CARBON/HIGH SPEED 30o .200 Maximum 0.0.06 .250 Maximum CUTTER SPEED Ft/minutes 700 .004 .025 OPER TOOL MATERIAL Rough High carbon/ High Speed ″ ″ ″ Carbide Tipped ″ ″ ″ ″ ″ Soft Hard Hard Soft Sof t 0. 1-1A-9 Table 3-22.15000 10 Maximum 10 Maximum 10 Maximum 20 Maximum 20 Maximum 0.10o 6o .005 . IN.88o 10o .20o 7o .50o 30o . Turning Speeds and Feeds .0o 0o .10o 7o .006 At minimum vibration Table 3-23. CARBIDE 52o .020 Maximum 0.0.1500 4000 Maximum 3000 ./REV OPER Rough TOOL MATERIAL Diamond tipped Diamond tipped 0.53o 10o .020 Maximum 5000 Maximum 500 .003 Finish Tool Angles .10o DIAMOND 74o .Continued ALLOY TYPE AND TEMPER etc CUT INCHES CUTTING SPEED FPM NOT RECOMMENDED FEED. 0.0.005 .025 0.025 0.T.0.32o 5o .80o 0o.020 0.005 .0.6o Nose Radii 0.005 .15000 3000 .10o Table 3-24.Speeds and Feeds ALLOY Temper Soft CUT Inches 0.300 Maximum 0.10o 6o .020 Maximum 0.0.001 .10 --- Milling . e. prior to operating. The drilling of thin material normally does not require coolant/lubrication however adequate lubrication is essential to drill life and hole quality when drilling holes of 1/4 inch depth or more.140o Spiral Angle: 0o . Helix Tooth Spacing 10o .002.016.035 in/rev for drills over 1 1/4 inch diameter. i.Continued ALLOY Hard Hard CUT 0. Feed also may be determined by the formular feeds = square root of drill diameter (inches) divided by 60 feet = Drill diameter (IN) + 0. Table 3-25.004 .20o Speed f t/min up to 1500 Feed inches/revolution 0. feed should be slightly less. Due to variables involved no set factors can be given. Tool Angles . Consult safety off icer when in doubt about the safety of an operation. Milling . safety goggles shall be worn when grinding/ drilling. Work shall be securely clamped to prevent slippage.004 .0. 3-194.020 Maximum CUTTER SPEED 3000 . c.250 Maximum 0. factors given for drill press should be used as a guide. with high speed drills and up to 2000 f t/min with carbide tipped drills.Milling TOOL ANGLES Cutting Angle Top Rake Clearance HIGH CARBON/HIGH SPEED 48o .0.020 0. However.12o Secondary 68o . 0.004-0. b.15o CARBIDE 3o .0.016 to 0. Soluble oil emulsions and lard oil mixtures are satisfactory for general drilling.004 .12o Secondary 10o ..50o Course .020 in/rev for 3/8 . Feed should be adjusted in accordance with speed of motor to prevent tip heating and also to satisfy operation/operator.7o Primary 7o . 12o for silicone alloys Speed: 600 f t/min.20o Approximately 1 tooth per inch of diameter. 3-53 . The lubrication should be applied by forced feed spray/f low where possible and the drill should be withdrawn at intervals to be sure lubricant f lows to the drill tip (f ill holes completely) when drill is withdrawn.67o 20o .28o Lip Clearance (lip relief): 15o .Speeds and Feeds .97o 10o .1 1/4 inch diameter and 0.T. When using carbide tipped drill.35o 3o . Point Angle: 118o .O. WARNING When operating any machinery all safety precautions must be observed. Feed: 0. Machinery shall be inspected to insure that safety guards are in place/ for safe operation etc.006 .7o Primary 7o .15000 4000 .0. Portable Drills Electric/Air Driven.15000 20 Maximum 20 Maximum FEED 0.012 inch per revolution for drills 3/8 inch diameter. 1-1A-9 Table 3-24.020 OPER Rough Finish TOOL MATERIAL Carbide Tipped ″ ″ Lip Clearance (lip relief): 17o for sof t alloys 15o for medium and hard alloys.Suff icient for chip Clearance. Lathe/screw-machine. 375 OPER Rough Finish Rough Finish TOOL MATERIAL High Carbon/ High Speed High Carbon/ High Speed High Carbon/ High Speed High Carbon/ High Speed Shaping Tool Angles OPERATION ROUGH FINISH Top rake Bottom Clear Side Rake Side Clear Cutting Angle 19o .60o 7o .0.0.9o 8o .10o 43o .100 0.031 0.0.020 .10o 30o .O.9o 0o .0o 64o .008 . Shaping and Planing-Speeds and Feeds METHOD Shaping Shaping Planing Planing CUT INCHES 1/4 Maximum 0.0.52o 7o .40o 50o .71o 30o .050 .37o TOOL MATERIAL HIGH CARBON/HIGH SPEED HIGH CARBON/HIGH SPEED HIGH CARBON/HIGH SPEED HIGH CARBON/HIGH SPEED HIGH CARBON/HIGH SPEED HIGH CARBON/HIGH SPEED 3-54 .0.018 CUTTING SPEED Maximum speed of RAM Maximum speed of RAM Maximum speed of Table Maximum speed of Table Table 3-27. FEED (INCHES) 0.0.156 0.014 3/8 Maximum 0.094 .T.005 .005 . 1-1A-9 Table 3-26. O.T. 1-1A-9 Figure 3-2. Drill Designs and Recommended Cutting Angles 3-55 . 8500 0. The following procedures and tools are recommended for tapping aluminum alloys: a. etc. Tool Angles: Spiral f lute-grind a lead spiral extending one full thread beyond chamfer on straight f luted tap. 3-196. The f ile is of ten adjusted until force or motion applied is parallel to the work piece for best results. Spiral f luted taps for cutting right-handed threads should have a right-hand spiral of about 40o angle with a generous back off taper and highly polished f lutes. Lightly double cut f iles having tooth spacing of 14 . Hand f iles of the single cut type having milled teeth usually give the best results for f iling aluminum.O. The use of the ‘‘Gun Tap’’ is therefore limited to tapping holes which have room for the cuttings ahead of the tool. TAPPING. 3-198.0200 0. 3-200. 1-1A-9 Table 3-28.7500 0.006 inches per inch larger than standard for the same thread in steel or in accordance with the following. For f inish f iling a long angle mill f ile (single) (cut) with tooth spacing of 14-24 teeth per inch with side rake angle of 45o to 55o is recommended. The cuttings generated are large and have a tendency to powder. With this type tap the major portion of cutting occurs at the spiral end and curls ahead of the tap.7395 0. white lead.005 X tap diameter)-thread per inch C = Thread constant for various thread forms and percentages of thread depth required as given in Table 3-28. pack and clog between f ile teeth. This spiral pointed tap should not be used for cutting tapered thread or for bottoming taps. The main consideration in f ile design/ selection for aluminum is to provide ample chip space clearance.9600 0.9000 0. b. cutter area (included angles).6960 0.T.0886 1.1042 1. o 75% 0. back rake 4 .9605 0. FILING.8o. In absence of the preferred f ile the same effect can be obtained using standard mill cut f iles by adjusting angle of f iling incidence to the metal worked. Straight f luted tape can be used but have a tendency to clog and tear the threads during the tapping operation. A good general purpose f ile is the curved tooth type (of ten called ‘‘vixen’’) having about ten deeply cut teeth per inch.Pointed or ‘‘Gun Taps’’ (straight f luted except they have a short spiral on the starting end) cut aluminum more freely than the other types. The taps used for threading aluminum alloys should be of the spiral f luted type for best results. c. Tapping Allowance: Drill diameter for general tapping should be from 0. Thread Constant for Various Standard Thread Forms PERCENT OF FULL THREAD DESIRED THREAD FORM American Std Course Series C = Whitworth C = British Ass’n Std C = Amer Std 60o Stub C = Amer Std Sq C = Amer Std 10 modified Sq Sq C = 3-195.005 to 0.9000 e. Cutting Speed: 40 to 130 feet/minute use lower speed for hard alloys and higher speed for sof t alloys. f.9743 0. User should be 3-56 .7830 0. cutting angel 40o to 45o. 3-197.6525 0.0245 0.8500 90% 1. for semi-blind use spiral pointed (gun taps).8000 85% 1. 2 f lute 36o to 72o and 3 f lutes 24oto 48o.20 per inch can be used for light duty rough cutting and f inishing when working the harder alloys. top rake 45o to 50o. d.9000 0.0800 0. 3-199. C Drill Diameter = (1.7500 80% 1. To overcome clogging problem chip space is increased.1526 1. Tap Type Selection: For blind holes and bottoming use spiral f luted.1691 1. It can be used for heavy and f inish cuts. Spiral . Lubrication: For high speed tapping use lard oil/mineral oil and for hand tapping a more viscous lubricant is recommended such as heavy grease/oil. grooves are cut deeper and teeth are cut with generous side and top rake. Thread Type: Rounded or f lattened (turn coated) thread contour for general use. and for hole through work use spiral pointed (gun taps). To make gun tap and spiral f lute tap should be 28o to 40o.0392 1.8000 0. The use of chalk or talc on f ile will help prevent clogging. heat treated alloys. Lubricants and coolants. 3-203.O. Also the f lexible back type of saw with teeth hardened to the bottom of the gullet is used for heavy work.T. Clogged f iles can be cleaned by wire brushing.005 . Blades having as many as 14 teeth per inch are satisfactory for thin materials. The top blade supports are placed slightly in advance of those below the tables and the blade should be allowed to vibrate freely to eliminate excessive saw breakage. 3-208.500 to 5. The desired feed in inches/revolution is 0. Band Saws. Quiet smooth cutting band saws usually produce smooth burnished surfaces accompanied by excessive heat and consequently decreased blade life.solid. The sof ter alloys require appreciably more blade set than do the harder.0. Curved or copying cuts are made with band saws. A good and simple general rule to follow when sawing aluminum is that the spacing of the teeth on band saws for aluminum should be as coarse as is consistent with the thickness of the material being sawed. 3-209. Special routing machines are available which cut varied prof iles from aluminum sheet or plate rapidly and eff iciently. 3-201. e. Tool type: Straight/spiral with 10o spiral f lute and solid teeth. Hack saw blades of the wavyset type are well suited for cutting aluminum by hand. Hack Saws. as far as practicable to saws for aluminum. SAWING. c. Machine f iling using rotary f iles (miniature milling cutters having spiralled sharp teeth with smooth deeply cut f lutes) are operated at high speed. clearance angle primary 4o to 7o. As a general rule. The teeth should be coarse (about 14 teeth per inch) with deep polished f lute and spiral notched design. This amount of hook. For hand feeds the top rake must be reduced considerably to avoid overfeeding. Usually an alternate side rake of about 15o and a top rake or ‘‘hook’’ of 10o to 20o proves quite satisfactory. Power hacksaws and hand saws require a cutting lubricant for most operations involving thick sections. The wavy set type of blade having 5 to 15 teeth per inch has suff icient chip space to avoid clogging and binding on aluminum alloys. REAMING. The band saw blades must be well supported by side rollers and back support both immediately below the saw table and about 2 or 3 inches above the work. The rotary f iles are operated up to 10. CAUTION Wear goggles or face shield when f iling with rotary f iles to protect eyes.003 to 0. secondary angle 15o to 20o. light weight machine oil.000 feet per minute. 3-207. o 3-204.000 RPM for small diameter and to 2. Files shall be kept clean and free of rust. For extremely f ine work a jewelers blade may be used. 3-202. Finish reamers should be maintained with exceptionally keen cutting edges and highly polished f lutes for smooth work. high blade speed are desirable with a speed range from 1.350.015 inch diameter (reaming allowance). Cutting f luids: Soluble oil/mixture of kerosene and lard oil. 1-1A-9 careful not to drag f ile across work on back stroke as with any f illing operation. Holes to be f inished by reaming should be drilled suff iciently under-size to assure positive cutting rather than scraping and swedging (indication of oversize drilled holes and improper feed is the projection of a lip around hole diameter af ter the reaming operation is accomplished). requires a power feed and securely clamped work. Band saw blades of spring temper steel having a tooth spacing from 4 to 11 teeth per inch and with amply radiused gullets are recommended for aluminum alloys. a noisy band saw is cutting more eff iciently than the saw that cuts quietly. 3-206. Tool material: High carbon steel for general use. the restricted chip space requires the use of coarser tooth spacing of about four teeth per inch to avoid clogging and binding. 3-57 . cutting angle 84o to 90o. It should be emphasized that the same principles which govern the shape of cutting tools for aluminum should be applied. b.010. For heavy sections the saw teeth should be fairly coarse with a slight set and a slight amount of front rake. In any type of work. Clearance and rake angles: Top rake 5o to 8 . high speed steel/or carbide tipped for durability and continued production jobs. The following procedures and tools are recommended for reaming aluminum alloys: a. but for best results the spiral f luted reamers are recommended .000 maximum peripheral feet/min for the larger diameter. Generally most of the different type reamers may be used for aluminum. however. expansion or adjustable. 3-205. The spiral should be opposite to the rotation to prevent reamer from feeding and hogging into the hole. Hole to be reamed should be undersize 0. tapered hole should be somewhat slower about 300 . Machine speed and hole reaming allowance: Cutting speeds up to 400 f t/min for straight holes. Soluble oil d. for subsequent polishing procedures. The grinding characteristics of the various aluminum alloys vary in many instances. The preliminary f inishing or roughing process usually employs a f lexible aluminum oxide paper disc. the f ine grindings of aluminum must be strained from the compound before reusing in order to prevent deep scratches on the f inished surface. Rough grinding operations are usually performed by use of resin bonded wheels of medium hardeners and grit sizes of 24 to 30. Soluble oil emulsions of the proportions of 30 or 40 to 1 are most suitable. since their greater resistance to cutting or grinding generates a considerable amount of heat which may cause warping and damage to the material. 3-216. particularly in their sof ter tempers have a tendency to clog the wheels and do not f inish to as bright and smooth a surface as the harder materials. these are the wheel speed. gives it a smooth lustrous f inish. 3-214. GRINDING. faced with suitable abrasives. For f inish work. 3-212.100 grit abrasives are for this process and are set in an adhesive in accordance with standard practice. such as crystalon. 3-58 . a sof t silicon carbide wheel of 30 to 40 grit in a vitrif ied bond have proven to be very satisfactory.000 feet per minute have given good results. Aluminum and its alloys are polished in the same manner as other metals. 14 to No. buff ing and coloring. Also the aluminum abrasives from No. Heating is also reduced by small applications of tallow or a tallow oil mixture.T. faster wheel speeds would cause heating or ridging of the sof t metal surface. Roughing is not required on smooth undented or unscratched surfaces. scratches or abrasion on the metal resulting from previous handling and operations. Excess aluminum pick-up on the wheels as results from overheating will cause deep scratches in the metal. 3-218. however.000 feet per minute. The various operations covered under the polishing category include roughing. greasing or oiling. A wide selection of lubricants exists. This is a ref ined or gentle roughing procedure for f inishing aluminum surfaces. POLISHING. Polishing is the act of removing marks. A grinding compound of soluble cutting oil and water works well. The peripheral speed of these discs runs around 6. Common alloys. but a lower wheel-to-metal pressure is used for aluminum. 3-219. These operations are brief ly described in the following paragraph. Caution should be taken in selecting the proper grade of each commercial make of wheel. carborundum and natalon. Experience has revealed in most cases it is more convenient and adaptable to use the f luid type lubricant applied freely through a recycling system directly to the blade and work stock. Special care should be exercised when grinding castings and wrought alloy products that have been heat treated. 1-1A-9 cutting compounds and neutral mineral-base lubricating oils applied to the sides of the blade aid in minimizing friction and gullet clogging. 3-211. Generous applications of stick grease are recommended to prevent clogging of the grinding wheels during rough grinding. ROUGHING. 3-213. Usually 50 . 3-217.000 FPM are used. 3-210. used to prepare aluminum surfaces having deep scratches gouges or unusually rough surfaces. peripheral speeds of about 6. Experienced operators have proven that their own good judgement is a determining factor as to the correct wheel and work speeds. work speed and grinding compound. while copious quantities of a low viscosity coolant type grinding compound are essential and recommended for f inish grinding. 3-220. Once the grinding wheel has been selected there are three variables that affect the quality of a f inish. it must be understood that a more gentle cutting action or f iner abrasives are used for polishing aluminum than used for steel. plus a light coat of tallow or beeswax lubricant to prevent excessive heating. 3-215. a semi f lexible bonded muslin or canvas wheel. Stick type lubricants should be applied very frequently. 36 have been found to be satisfactory for rough grindings. The harder free-cutting aluminum alloys may be ground satisfactorily with free cutting commercial silicon carbide grinding wheels. Application is visually employed by a sof t wheel faced with 100 to 200 grit aluminum oxide emery. Lubricants and Coolants. However. by the application of proper machining procedures. GREASING OR OILING. Greasing or oiling is a necessary operation in f inishing coatings and other fabricated work which has been marred by previous operations.O. Polishing or f inishing aluminum and most of its alloys. ranging from tallow or grease stick to kerosene-thinned mineral base lubricating oil. Here again. This is a term used to describe the preliminary f inishing operation or process. Light applications of heavy grease or paraff in wax will provide ample lubrication for some work. wheel speeds of about 6. ANODIZING PROCESS FOR INSPECTION OF ALUMINUM ALLOY PARTS. attempts have been made to remove scratches from aircraf t skin by sanding. 3-226. the thread count of the buff. The purpose of the following information on the effects of scratches on aluminum alloys is to assist in eliminating controversy in depots and f ield inspection. nicking or scratching. polishing and f iling. 3-231. In case of doubt strip f ilm from part and reanodize. NON-DESTRUCTIVE TESTING/INSPECTION. nicks and notches be removed by sanding. regarding serviceability of aluminum alloy. Metal hardness can be measured accurately by the Brinell. This 3-59 . Many factors. which is applied to the face of the wheel. Hardness is the resistance of a metal to deformation by scratching penetration or indentation. divide the applied load in kilograms by the spherical area of the impression in square millimeters. (2) The presence of small corroded areas will not materially affect the strength of clad unless the corroded pitted area extends through the cladding down to or into the bare metal Clean corroded areas thoroughly by authorized methods (See Paragraph 3-242). method of inspection is not acceptable for inspection of parts subject to internal defects. or polishing resulting in removal of much of the cladding material and causing decrease in strength and corrosion resistance. abraded or discolored from the stand point of corrosion resistance and fatigue strength. Parts inspected by this method shall be limited to sheet stock and surface defect of forgings. 1-1A-9 3-221. buff ing. can be anodized for the inspection of defects as cited in Specif ication MILI-8474. This is a term used to describe a f inishing procedure employed to obtain a smooth high luster on an aluminum surface. 3-229. The Brinell technique is usually used to obtain the hardness of aluminum and aluminum alloys.e. skin and aircraf t structural parts which have been scratched. turned at a peripheral speed of 7. Before any fabrication commences it is necessary that all scratches. 3-225. ALLOWABLE DEFECTS. The parts are examined visually for indications of cracks. In some instances. HARDNESS TESTING. the pressure applied to the buff against the work. have been disposed of due to lack of knowledge by inspection personnel as to the effect of various depth scratches on the strength and corrosion resistance of the clad alloy. etc. Hardness value of aluminum alloy is tested by applying a load of 500 kilograms to a ball ten millimeters in diameter for 30 seconds. Insuff icient rinsing in cold water af ter anodizing produces stains which may be confused with defects.T. serviceable aluminum alloy parts and sheets. To obtain the hardness value of a material. the buff ing compound used. 3-222. and is usually a good indication of strength. Rockwell or Vickers Process. The following surface defects are those which do not affect the strength or corrosion resistance. forging laps or other defects. 3-233. the speed of the buff or wheel and the skill and experience of the operator must be considered in obtaining a satisfactory and quality type f inish. Parts for which anodic coating is applicable in accordance with MIL-A-8625 Type I. NOTE For additional general information on inspection and testing see Section VIII of this technical order.O. i. BUFFING. BRINELL HARDNESS.000 FPM. sheet. Aluminum and aluminum alloys are susceptible to stress risers resulting from notching. (3) Stains are not grounds for rejection since they affect neither the strength nor the corrosion resistance. These wheels usually consist of muslin discs sewed together. 3-232. such as tripole powder mixed with a grease binder. ALUMINUM ALLOY EFFECTS ON SCRATCHES ON CLAD ALUMINUM ALLOY. (1) Scratches which penetrate the surface layer of clad aluminum alloy sheets or parts but do not extend beneath the cladding are not serious or detrimental. inclusion in castings and forging or any part subject to internal stress. 3-223. such as. a. If the indications do not reappear the defects shall be considered absent and part should not be rejected for that reason. This hardness value is obtained by applying a load through a ball indenter and measuring the permanent impression in the material. 3-227. 3-224. Also. A very close visual inspection is required of all raw material prior to any forming or machining operations. This high luster f inish is obtained by use of a f ine abrasive. 3-228. Defects are indicated by darkening of cracked or void areas af ter the anodic treatment. 3-230. Parts (air weapon) shall be closely inspected as cited and they do not meet specif ied requirement shall be condemned and replaced as directed. wet or moist. b. Serviceable portions of damaged sheets will be used in the manufacture of smaller parts and assemblies. Alkali Cleaning Solution. it has been found convenient (on clad material) to use a ‘‘spot’’ test to determine whether or not a scratch extends through the cladding. Stubborn or exceptionally oily sheets may be cleaned by using solvent. 3-240. Composition of solution is 4 to 6 oz of cleaner specif ication MIL-C5543 to one gallon of water. Assemblies fabricated from clad aluminum-alloy sheets will not be rejected by inspection personnel. 3-242. Only that portion of sheet that is scratched and otherwise damaged beyond serviceability will be administratively condemned. Caution will be exercised to make sure that all of the caustic solution is removed from the sheet by thorough rinsing. Scratches resulting from the normal handling and processing of clad aluminum-alloy sheet rarely extend through the cladding and penetrate the core. Type II. soaking. The material is cleaned by immersing in the solution (as prepared by instructions cited in paragraph 3-245) for 4-6 minutes. 3-241. 3-234. 3-237. The caustic solution will be prepared fresh for each series of tests to be made. Refer to T. and allowing it to react for 5 minutes. 3-243. Type II. Care wi11 be taken not to use excessive amounts of the caustic solution for the same reason and it is preferable that only one drop be used for each test. Material or equipment that would scratch or abrade the surface shall not be used. in water) on a portion of the scratch. a. Also material shall not be stored af ter solvent cleaning and prior to alkaline cleaning. or other suitable solvent. 3-238. 3-236. When making the ‘‘spot’’ test to determine whether a scratch extends to the core. 00-85A23-1 for packaging and storage. so that the caustic solution will react properly. since the caustic solution is very corrosive to aluminum and aluminum alloys. Scratches which extend through the cladding and penetrate the core material act as notches and create stress concentrations which will cause fatigue failure if the part is highly stressed or subjected to repeated small stress reversals.O. If a black residue remains in the base of the scratch at the spot tested. it indicates that the scratch extends to the core. the sheet area will be cleaned and degreased with solvent Federal Specif ication P-D-680. Since it is very diff icult to measure the depth of a scratch on a sheet without cross sectioning the sheet. On alloys except 7075 and 7178 the ‘‘spot’’ test is made by placing a drop of caustic solution (10% by weight of sodium hydroxide. it indicates that the scratch does not penetrate through the cladding. unless solvent is completely removed from the surfaces of the metal. Before making the ‘‘spot’’ test. Scratches or abrasions which penetrate the cladding will not affect corrosion resistance. Federal Specif ication P-D-680. 3-60 . INSPECTION. before cleaning with alkali solution. sheets so scratched may utilized for non-stressed applications. 1-1A-9 CAUTION No attempt will be made to remove scratches or other surface defects by sanding or buff ing since the protective layer of cladding will be removed by such operations. thoroughly rinsing in water (fresh tap) and then completely drying. unless the defect is of suff icient depth to adversely affect the mechanical properties or cover suff icient area to impair the corrosion resistance of the assembly. CLEANING OF ALUMINUM ALLOY SHEET (STOCK). 3-235. and the spot allowed to dry.T. For alloys 7075 and 7178 a drop of 10% cadmium chloride solution will produce a dark discolorationm within two minutes if the scratch penetrates the clad. The caustic solution will then be rinsed off the sheet with water. NaOH. HARMFUL SCRATCHES. scrubbing and wiping. The cleaning will be accomplished by brushing. 3-244.O. The cadmium chloride applied as above will not cause 2024 to discolor within two minutes. It is then easier to determine whether the residue which remains is black or white. DISPOSITION OF SCRATCHED SHEETS/PARTS. All scratched clad aluminum-alloy sheets wi11 be utilized to the fullest extent. However. If no black color is visible and only a white residue remains in the base of the scratch. it is advisable for comparison purposes to spot test an adjacent area in which there are no scratches. 3-239. Solvent Cleaning. Never pile/store material while damp. TEST FOR DEPTH OF SCRATCHES. 3-61 . Specif ication MIL-C-38334. Fill the task 1/2 to 2/3 full of water. Prepare the solution in the following manner: a. 3-245. Specif ication MIL-C-25769. size of the part and the amount of solution circulated. 3-247. acid resisting gloves.15 Sp). or with a mop. c. or brush. Type II. b. Corrosion Removal and Treatment of Aluminum Sheets When Immersion Is Not Practical. Diluted solution of sodium dichromate (Na2Cr2 O7) 12 to 14 ounces per gallon of water. Add tap water to balance-up solution loss. b. d. Corrosion Removal. Corrosion is removed by immersing the sheet in the following acid cleaning solution: CAUTION When using acid solution wear approved clothing. 3-251. 3-248. contact local safety off icer a. c. shall be added to the rinse water as a corrosion inhibitor. 3-246. Agitate thoroughly with wooden paddle to insure proper mixture. Clean the tank thoroughly before preparing a new solution. Add not more than one pound of cleaner at a time. Do not allow solution to dry before rinsing as less effective cleaning will result. Heavily soiled areas. Maintain solution in the following manner: a. b. To remove corrosion products use a metal conditioner and brightener. b. Rinse thoroughly with a spray or stream of water. The surface shall be cleaned with water base cleaner. a. 1-1A-9 9 gallons of water. aprons/ coveralls. CAUTION Do not use strong alkali solution because it will etch the aluminum. Af ter removing from the acid. A light detectable stain is desired on corroded areas. c. Nitric-Hydrof luoric Acid Cleaning. f lush thoroughly with water immediately. Prepare a new solution when contamination impares the cleaning ability of the solution. Dissolve the contents of two 5-pound packages in 10 gallons of water. NOTE The sheet will stain when rinsed with sodium dichromate. Parts shall then be completely dried by blasting with compressed air or other approved method. 3-250. Use water heated to a temperature of 170oF (77oC). Corrosion Removal from Aluminum Alloy Sheets. Preparation. If solution is splashed into eyes. 1/2 pint technical hydrof luoric acid (48oHF) (1. Stir with a wooden paddle until fully dissolved. 3-249. Make addition as required to maintain the active alkali concentration between 4 and 6 oz alkaline cleaner for each gallon of water added and stir thoroughly. Dissolve four 5-pound packages in 50 gallons of water (a 55 gallon drum is suitable for this purpose). If the stain is dark reduce the amount of sodium dichromate added to rinse water.T. Add water to operating level and stir thoroughly with a wooden paddle or other means.5o Be). One half hour or less should be suff icient. the parts shall be washed in fresh hot or cold running water for a suff icient length of time to thoroughly remove the acid. Lightly soiled areas. The solution shall consist of 1 gallon technical nitric acid (58-62% HNO3) (39. Apply the solution by spraying. face shields or respirator. Parts shall be immersed for 3 to 5 minutes in cold acid (50o . For special instructions.O. Application. The rinsing time depends upon the freshness of the solution.105oF). Carefully dissolve the alkaline cleaner. Allow to remain on the surface for several minutes while agitating with a brush. sponge. and then report to dispensary. The stronger the solution the darker the stain. To speed drying the surface may be blown dry with warm clean air (140oF maximum).T. accidentally contacts the skin or eyes. acetone or other combustible materials. For special instructions contact local safety off icer. Keep the surface wet with the solution until a coating is formed which may take from 1 to 5 minutes depending on the surface condition of the metal. 3-62 . 3-252. aprons/coveralls. NOTE Do not permit excess conversion coating to dry on the metal surface because the residue is diff icult to f lush off with water. d. A clear Specif ication MIL-C-5541 coating is available (reference QPL 5541) and should be used when a bright metal f inish is desired. Insure that all traces of brightener have been removed (shown by no foaming or bubbles while rinsing). When using brightener at high ambient temperature (above 80oF) leave brightener on for shorter periods of time. allow approximately 5 to 10 minutes from application of brightener before rinsing. not in lead. Prepare the brightening solution by mixing Specif ication MIL-C-38334 compound with an equal amount of water. Apply the conversion coating (light) by using a f iber bristle brush or a clean. face shields or respirator. e. Fire may result. If solution is splashed into eyes. f lush thoroughly with water immediately.O. d. Conversion coating is a toxic chemical and requires use of rubber gloves by personnel during its application. c. acid resistant gloves. Depending on the ambient temperature and amount of corrosion deposits present. Rinse the brightener from the surface (using approximately 50 gallons of water per minute. a. . and then report to dispensary. Rinse with clear water. Apply enough diluted brightener to completely cover the area being treated with a nonmetallic bristle brush. Mix in accordance with manufacturers instructions. WARNING . Most solutions conforming to Specif ication MIL-C-5541 leave a stain. 1-1A-9 WARNING When using acid solution wear approved clothing. Chromate Conversion Coating Specif ication MIL-C-5541. sof t cloth. Do not permit Specif ication MIL-C5541 material to contact paint thinner. If acid. Material in storage shall not be treated with this material more than one time. a. Allow the surface to air dry. CAUTION Metal conditioner and brightener is for use only on aluminum alloys. Consult a physician if eyes are affected or if skin is burned. Mix the solution in a stainless steel. b. or sponge the area with a clean. Do not leave brightener on the surface longer than necessary to dissolve the corrosion. b. frequently rinsing the cloth in clear water. rubber or plastic container. moist cloth. c. Thorough rinsing is required. Agitate the brightener by scrubbing with a non-metallic bristle brush. in a rubber pail. f lush immediately with plenty of clear water. for aluminum alloys. copper alloy or glass. Aluminum alloys which are treated with Specif ication MIL-C- 38334 shall be treated with Specif ication MIL-C5541. and it shall not be used just for the sake of improving the appearance of material. brush.. It is recommended that a test panel be prepared and subjected to complete cleaning/ treating procedure before applying material to a sheet.T. 3-254. MIL-E-7729 or ‘‘Magic Marker’’ manufactured by Speeddry Products Inc. and Storage of Aluminum Alloy Sheets and Plates Refer to T. A felt tip pen may also be used. an AF Form 50A will be attached to each sheet with a statement that. CAUTION Avoid brushing or rubbing the newly applied chemical conversion coating. Anodizing is the anodic process of treating aluminum alloys. The anodizing method is preferrable to chemical f ilms on aluminum parts where facilities are available. The marking may be applied with Black paint Specif ication TT-L-50. For Packaging. When clear material is being used. been cleaned and treated for corrosion in accordance with T. . . Packing.O. or immersion as specif ied by QPL-5541. no control of discoloration is necessary. ‘‘This material has 3-63/(3-64 blank) . temper and type or grade. . They are extreme f ire hazards if allowed to dry otherwise.Y. . or ‘‘Equal’’. size/thickness. 00-85A-23-1. a thin f ilm of artif icially produced oxide is formed on the surface of the metal by electrochemical reaction. 1-1A-9 Section III. These chemical f ilms are substitutes that may be used in lieu of anodic f ilms. and TO 42C2-1-7 gives the anodizing process.’’ If original markings are removed as a result of the cleaning and treatment process.. For process procedures applying to chemical f ilms. and may be applied by spray. N.O. refer to Technical Orders 1-1-8 and 1-1-2. the material shall be remarked (staggered) at each end and in the middle with the Specif ication. Af ter the procedures cited in paragraphs 3-252 through 3-263 have been complied with. 3-255. Richmond Hill. Military Specif ication MIL-C-5541 lists the requirements for corrosion protection and paint base of aluminum by the use of chemical f ilm. 1-1A-9 WARNING Any absorbent material used in applying or wiping up MIL-C-5541 material shall be rinsed in water before discarding. . Military Specif ication MILA-8625 lists the requirements of aluminum anodizing. . The test panel shall be used to determine the dwell time of MIL-C-5541 material.O. since it is sof t and can be easily rubbed off the surface before completely drying. ANODIC COATINGS FOR ALUMINUM. . NOTE A light (just visible to the naked eye) evenly dispersed conversion coating is all that is required. 3-253. date . . but rather a gradual yielding when the metal is stressed above the proportional limit. The yield point in magnesium is not reached abruptly. The hardness of a metal can be accurately measured using the Brinell on Rockwell process of testing. Hardness is the resistance of a metal to plastic deformation from penetration. For example: Alloy Designation AZ92A would consist of 9% (mean value) aluminum and 2% (mean value) zinc as the major alloying elements. The hyphenated suff ix symbol which follows an alloy designation denotes the condition of temper. The degree of hardness is usually a good indication of the metals strength. M Manganese. measured in pounds per square inch. 4-7. followed by the respective digital percentages of these elements. Chemically bare magnesium is resistant to attack by alkalis. 1-1A-9 SECTION IV MAGNESIUM ALLOYS 4-1. DEFINITIONS. The suffix ‘‘A’’ indicates this is the f irst qualif ied alloy of this type. (arranged in decreasing percentage order. solution and precipitation heat treat and stabilization treating. Adequate protection of the metal against unfavorable conditions can be maintained generally. The percentage is rounded off to the nearest whole number or if a tolerance range of the alloy is specif ied. 4-3.T. rods. It is susceptible to attack by salts and by galvanic corrosion from contact with dissimilar metals and other materials. Mechanical includes cold rolling. 4-4. One exception to the use of the suff ix letter is that an ‘‘X’’ denotes that impurity content is controlled to a low limit. TEMPER is the condition produced in the alloy by mechanically or thermally treating it to alter its mechanical properties. of stress. E Rare Earth. They are suitable for varied stress and non-stress aerospace applications.74. 4-12. H Thorium. HARDNESS. PHYSICAL PROPERTIES. 4-6. has a specif ic gravity of 1. TEMPER DESIGNATION SYSTEM. in its pure state. amines. 4-5 and 4-6 lists the nominal yield strengths of various alloys. (heat 4-2. tubing. The letters designate the major alloying elements. two or three digit number designation in that order. The yield strength is that point 4-1 . cold working. TENSILE STRENGTH. ELONGATION is the linear stretch of a material during tensile loading measured before and af ter rupture. i. by using proper surface f inish (See paragraph 4-93) and assembly protection. the mean of the range (rounded off to nearest whole number) is used. SHEAR STRENGTH is the maximum amount (in pounds per square inch) in cross sectional stress that a material will sustain before permanent deformation or rupture occurs. The useful tensile strength of a metal is the maximum stress it can sustain in tension or compression without permanent deformation. The weight for an equal volume of magnesium is approximately two-thirds of that for aluminum and one-f if th of that for steel. Z Zinc. Magnesium alloys are produced and used in many shapes and forms. is a two letter. 4-10. at which permanent deformation results from material failure. The chemical property constituents of the various alloys are listed in Table 4-3. 4-5 and 4-6 list the nominal hardness of various magnesium alloys. Brinell hardness testing is explained in Section VIII of this manual. denotes the latest qualif ied revision of the alloy.. See paragraph 412 for temper designations. lightweight. In magnesium it is the increase in distance which occurs when stretch is applied between two gage marks placed 2 inches apart on the test specimen. CHEMICAL PROPERTIES. or scratching. thermal includes annealing. phenols. Tensile and yield strengths decrease at elevated temperatures. weighing . sheets and plate and forgings. Similar data for magnesium alloys are included in Table 4-6 as well as other physical property information. 4-5.O. Some of the letters used to designate various alloying elements are: A Aluminum. extruded bars. esters and most oils. Their inherent strength. Af ter rupture the two pieces are f itted together and remeasured. castings.. A suff ix letter following the percentage digits. 4-9. Tables 4-4. shock and vibration resistance are factors which make their use advantageous. Magnesium. The data in Tables 4-4. The current system used to identify magnesium alloys. aldehydes. 4-11. etc.063 pounds per cubic inch. alcohols. The elongation is the percentile difference of the amount of stretch in ratio to the original 2 inches. chromic and hydrof luoric acids and many organic chemicals including hydrocarbons. indentation.e. or in alphabetical order if the elements are of equal amounts). K Zirconium. CLASSIFICATION. 4-8. -AC As-Cast -F As-fabricated -O Annealed -W Solution heat treated . it is mandatory that all such actions be made according to the requirements and WARNING Magnesium thorium alloys shall be handled. For example: Stirring alloy melt of 5% thorium content resulted in 0. 00-110N-4. See T. to the H1.e. both of these areas must be considered. HZ32. must be disposed of in accordance with AEC Standards for Protection Against Radiation 10 CFR Part 20. These symbols and their meanings are listed below: (Heat treating itself is discussed in subsequent paragraphs of this section of the manual). 4-14. 6. MAGNESIUM-THORIUM ALLOYS (HK31.00-110N-4 4-16. through applicable disposal procedures.O. the size of stacks should be limited to 1000 cubic feet with an aisle width not less than one-half the stack’s height. ZH62) are mildly radioactive but are within the safe limits set by the Atomic Energy Commission (AEC) and represent no hazard to personnel under normal conditions. As an alternative the ashes or scrap may be turned over to an AEC licensed scrap dealer. cold worked and then artif icially aged -T9 Solution heat treated. Use of local exhaust reduced thorium concentrations to well within acceptable 1imits . 4-17. H3 symbols indicate the degree of strain hardening. artif icially aged and then cold worked -T10 Artif icially aged and then cold worked -H1 Strain hardened only -H2 Strain hardened and partially annealed -H3 Strain hardened and stabilized Added suff ix digits 2. the body one foot away from the alloy for an entire 40 hour work week. 1-1A-9 treat or strain hardening). to rage and processing of thorium containing alloys. If ventilation is such that the visible fumes f low away from the welder. providing such fumes are not permitted to accumulate in the immediate vicinity. SAFETY REQUIREMENTS FOR HANDLING AND FABRICATION OF MAGNESIUM ALLOYS. An alternate practice involves use of ventilated welder’s hood.1 mg/m3 of air were found in the breathing zone.O.. 4-18. 8. 2=1/4 hard. One is the fact some alloys contain thorium. the ashes which will then contain the thorium. if there is not suff icient room ventilation to control contamination of the general atmosphere. ZH42. it is adequate.035 mg/m3. can be expected to control any health hazards that might result from f ine dust in grinding the low thorium content alloys.1 milligram per cubic meter (mg/m3) of thorium in air is a safe limit for continuous atmospheric exposure and is readily met in processing magnesium alloys containing up to 10% thorium. followed to avoid f ire hazards. In welding these alloys without local exhaust.O. Only long exposure to f ine dust or fumes need cause concern as to radioactive toxicity of magnesium-thorium. Thorium containing scrap and wet grinding sludge may be disposed of by burning providing an AEC ammendment is secured for the basic AEC license. a radioactive element (e. i.T. H2. HM31A) and the other is the low melting point/ rapid oxidation (f ire hazard) characteristics of the metal. HM31. The corresponding AEC permissible safe limits are 1500 mr/week for the hands and 300 mr/week for the whole body. There are two special major areas of safety precautions to observe in proceeding of magnesium alloys other than general shop safety practices. Despite the relative safety present in the handling.008 to 0. standard of 0. 4-15. and 8=full hard. 4-13. Where the application of heat is to be made to a thorium alloy. Radiation surveys have shown that exposure of workers handling the referenced thorium alloys is well within the safe limits set by the AEC. the exposure would be 168 millirems (mr) to the hands and 72 mr to the whole body. 4=1/2 hard. For indoor storage of thorium alloy sheets and plates. Assuming hand contact.. HM21A. Normal dust control precautions. Such storage is within the normal recommendations for f ire safety.g. These are maximum values which probably would not be approached in actual practice. A 4-2 .unstable temper -T Treated to produce stable tempers other than for -O -T2 Annealed (cast products only) -T3 Solution heat treated and then cold worked -T4 Solution heat treated -T5 Artif icially aged only -T6 Solution heat treated and then artif icially aged -T7 Solution heat treated and stabilized -T8 Solution heat treated. stored and disposed of in accordance with T. HM21. 4. concentrations of thorium above the tentative limit of 0.002 mg/m3 atmospheric contamination and grinding air alloy of 3% thorium content gave thorium contamination in the breathing zone ranging from 0. 6=3/4 hard. HK31A. to which the alloy has been processed. If burned. O. Shapes Forgings Sand Castings Permanent Mold Castings Permanent Mold Castings Die Castings Die Castings Sand Castings Permanent Mold Castings Sand Castings 4375 4376 4377 __ __ __ __ 4350 4358 4350 __ 4420. 4422 4424 __ __ __ 4360 __ __ __ 4490 __ 4437 __ 4434 AZ31C AZ61A AZ63A QQ-M-56 QQ-M-56 QQ-M-55 ____ AZ80A AZ81A AZ91A AZ91B AZ91C AZ92A QQ-M-31 QQ-M-40 QQ-M-56 QQ-M-55 QQ-M-55 QQ-M-38 QQ-M-38 QQ-M-56 QQ-M-55 QQ-M-56 MIL-C19163 4-3 . Shapes Forgings Extruded Tubes Sheet and Plate Sheet and Plate Sheet and Plate Welding Rod Extruded Bars. Use heavy feeds to produce thick chips. During machining operations. Alloy Designation to Specifications ALLOY AM100A AZ31B FED SPEC QQ-M-56 QQ-M-55 QQ-M-31 QQ-M-40 WW-T-825 QQ-M-44 QQ-M-44 QQ-M-44 ____ ____ ____ QQ-M-31 QQ-M-40 WW-T-825 MIL SPEC __ __ __ __ __ __ __ __ MIL-R6944 __ __ __ __ __ __ MIL-R6944 MIL-C19163 MIL-C19163 MIL-C19163 MIL-R6944 ___ ___ ___ ___ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ HNBK 502 52 510 52 510 510 510 __ __ __ __ 520 530 520 __ 50 50 __ __ 523 532 505 505 __ 501 501 504 __ 500 SAE AMS 4483 ASTM (ASME) B80 B199 B107 B91 B217 B90 B90 B90 B260 B107 B217 B90 B107 B91 B217 B260 B80 B80 B199 B260 B107 B91 B80 B199 B199 B94 B94 B80 B199 B80 USE Sand Casting Permanent Mold Casting Extruded Bars. Rods. Rods. 4-21. 4-20. Keep all cutting tools sharp and ground with adequate relief and clearance angles b. certain precautions should be taken during working of it. 1-1A-9 restrictions of the 00-100 series technical orders. Shapes Extruded Tubes Sheet and Plate Extruded Bars. temperature. observance of the following rules will control any potential f ire hazard: a. These precautions are noted in the following paragraphs on safety precautions. 4-19. Cross-Reference. Shapes Forgings Extruded Tubes Welding Rod Sand Castings Sand Castings Permanent Mold Castings Welding Rod Extruded Bars.T. as applicable. Rods. SAFETY PRECAUTIONS FOR ALL ALLOYS (INCLUDING FIRE HAZARDS). Since magnesium will ignite and burn f iercely when heated to a point near its melting Table 4-1. As previously stated. the normal precautions taken in the shop processing of magnesium will suff ice for safe handling of thorium alloys. Machining Safety Rules. and AEC regulations. Rods. Cross-Reference. 4441 __ 4442 __ __ 4445 4384 4385 ASTM (ASME) B199 B260 B80 B80 B199 B80 B199 B260 B80 B90 USE Permanent Mold Castings Welding Rod Sand Castings Sand Castings Permanent Mold Castings Sand Castings Permanent Mold Castings Welding Rod Sand Castings Sheet and Plate EK30A EK41A QQ-M-56 QQ-M-56 QQ-M-55 EZ33A QQ-M-56 QQ-M-55 ____ QQ-M-56 ____ HK31A* * HK21A* ____ QQ-M-40 ____ ____ ____ __ __ __ __ __ __ __ 522 533 522 51 __ __ __ 53 534 __ __ 508 __ __ __ 4390 4388 4389 4447 __ _ _ _ _ _ _ _ _ _ _ B260 __ B90 B107 __ B80 B80 B107 __ B217 B90 B260 __ __ B91 B90 __ __ B80 __ Welding Rod Forgings Sheet and Plate Extruded Bars. Shapes Sand Castings Sand Castings Extruded Bars.Continued ALLOY AZ92A (Cont) FED SPEC QQ-M-55 ____ MIL SPEC MIL-C19163 MIL-R6944 ___ ___ ___ ___ ___ MIL-R6944 ___ MIL-M26075 MIL-M26075 MIL-R6944 ___ MIL-M8917 MIL-H8916 MIL-H8916 ___ MIL-M45207 ___ ___ ___ ___ MIL-R6944 ___ ___ ___ ___ ___ ___ ___ MIL-M46039 HNBK 503 __ __ __ __ 506 506 __ 507 507 SAE AMS 4484 __ __ 4440. Shapes Forgings Extruded Tubes Sheet and Plate Welding Rod Sand Castings Permanent Mold Castings Forgings Sheet and Plate Sand Castings Sand Castings Sand Castings Extrusions HM31A* HZ32A* KIA MIA QQ-M-56 QQ-M-56 QQ-M-31 QQ-M-40 WW-T-825 QQ-M-44 ____ QQ-M-56 QQ-M-55 QQ-M-40 ____ QQ-M-56 ____ QQ-M-56 ____ QE22A TA54A ZE10A ZE41A ZH42* ZH62* ZK21A __ __ __ __ __ __ 4438 4387 4-4 . Shapes Extruded Bars. Alloy Designation to Specifications .O.T. 1-1A-9 Table 4-1. Rods. Rods. Rods. T.O. 1-1A-9 Table 4-1. Cross-Reference, Alloy Designation to Specifications - Continued ALLOY ZK51A ZK60A ZK60B ZK61A FED SPEC QQ-M-56 QQ-M-31 QQ-M-40 WW-T-825 ____ QQ-M-56 MIL SPEC ___ ___ ___ ___ MIL-M26696 ___ HNBK 509 524 __ 524 __ 513 SAE AMS 4443 4352 4362 4352 __ 4444 ASTM (ASME) B80 B107 B91 B217 __ B80 USE Sand Castings Extruded Bars, Rods, Shapes Forgings Extruded Tubes Extruded Bars, Rods, Shapes Sand Castings *These alloys contain radioactive thorium element. See paragraph 4-15 for precautionary instructions. MISC SPECIFICATION MIL-M-3171 Magnesium alloy, processes for corrosion protection of SAE-AMS-M-6857 Magnesium alloy castings, heat treatment of Change 4 4-5 T.O. 1-1A-9 Table 4-2. Alloy Designation Cross-Reference NEW DESIGNATOR AZ63A MIA MIB MIA MIA MIA A292A AZ92A AM100A AZ91A AZ31B AZ31B AZ31B AZ31B AZ61A AZ61A AZ61A AZ80A AZ80A ZK60A EX41A EZ33A TA54A FORMER DOW REVERE H M M M M M C C G R FS-1 FS-1 FS-1 FS-1 J-1 J-1 J-1 0-1 0-1 __ __ __ __ FORMER AMERICAN MAGNESIUM AM265 AM3S AM403 AM3S AM3S AM3S AM260 AM260 AM240 AM263 AM52S AM52S AM52S AM52S AMC57S AMC57S AMC57S AMC58S AMC58S AMA76S AMA130 AMA131 AM65S FORMER * MILITARY ____ AN-M-26 AN-M-30 AN-T-73 AN-M-22 AN-M-30 ____ ____ ____ AN-M-16 AN-M-27 AN-T-72 ____ AN-M-29 AN-M-24 AN-T-71 AN-M-20 AN-M-25 AN-M-21 ____ ____ ____ ____ NEW FEDERAL QQ-M-56 QQ-M-31 QQ-M-56 WW-T-825 QQ-M-40 QQ-M-44 QQ-M-56 QQ-M-55 QQ-M-55 QQ-M-38 QQ-M-31 WW-T-825 ____ QQ-M-44 QQ-M-31 WW-T-825 QQ-M-40 QQ-M-31 QQ-M-40 QQ-M-31 ____ ____ QQ-M-40 USE Castings, Sand Extruded Bars, Rods, Shapes Castings, Sand Extruded Tube Forgings Sheet Castings, Sand Castings, Perm Mold Castings, Perm Mold Castings, Die Extruded Bar, Rod, Shape Extruded Tube Forgings Sheet Extruded Bar, Rod, Shape Extruded Tubes Forgings Extruded Bar, Rod, Shape Forgings Extruded Bar, Rod, Shape Castings, Perm Mold Castings, Perm Mold Forgings NOTES: *These ‘‘AN’’ Specif ications have been superseded by the listed Federal Specif ications. 4-6 Table 4-3. Chemical Properties of Magnesium Alloys ALLOY AL MN ZINC ZIRCONIUM RARE EARTH ----------------------2-3.0 3.0-5.0 2.5-4.0 ------0.1mx ----1.8-2.5 --0.120.22 THORIUM SI CU NICKEL MG FORMS AM100A AZ31B(1)(2) AZ31C AZ63A(2) AZ80A AZ81A AZ91A AZ91A AZ91B AZ91C AZ92A EK30A EK41A EZ33A HK31A* HM21A* HM31A* HZ32A* KIA MIA(1) QE22A(3) TA54A(4) ZE10A 9.3-10.7 2.5-3.5 2.4-3.6 5.3-6.7 7.8-9.2 7.0-8.1 8.1-9.3 8.1-9.7 8.3-9.7 8.1-9.3 8.3-9.7 --------------------3.0-4.0 --- 0.10 0.20 0.15 0.15 0.12 0.13 0.13 0.13 0.13 0.13 0.10 ------0.15mx 0.45-1.1 1.2mn ----1.2 --0.20 --- 0.30max 0.6-1.4 0.5-1.5 2.5-3.5 0.2-0.8 0.40-1.0 0.4-1.0 0.4-1.0 0.4-1.0 0.4-1.0 1.6-2.4 0.3 max 0.3 2.0-3.1 0.3mx ----1.7-2.5 ------0.3mx 1.0-1.5 ----------------------0.20 min 0.4-1.0 0.5-1.0 0.4-1.0 ----0.5-1.0 0.4-1.0 --0.4-1.0 ----- ----------------------------2.5-4.0 1.5-2.5 2.5-3.5 2.5-4.0 ----------- 0.30 0.10 0.10 0.10 0.30 0.30 0.30 0.50 0.50 0.30 0.30 ------- 0.10 0.05 0.10 0.05 0.25 0.10 0.10 0.10 0.30 0.10 0.25 0.10 0.10 0.10 0.10 0.01 0.005 0.03 0.005 0.01 0.01 0.01 0.03 0.03 0.01 0.01 0.01 0.01 0.01 0.01 ----0.01 --0.01 0.01 0.01 --- Bal Bal Bal Bal Bal Bal Bal Bal Bal Bal Bal Bal Bal Bal Bal Bal Bal Bal Bal Bal Bal Bal Bal Castings, sand, perm mold Extruded Bars, rods, shapes tubes = sheets Same Castings, sand and perm mold Extruded bars, rods, shapes, forgings Castings, sands and perm mold Castings, perm mold Castings, Die Castings, Die Castings, sand and perm mold Same Castings, sand only Castings, sand and perm mold Castings, Sand/Sheet Plate Castings, Sand/Sheet/Plate Forgings, Sheet/Plate Extruded Bars/Rods/Shapes Castings, Sand Castings, Sand Extruded Bars, rods, shapes tube-sheets-forgings Castings, sand Forgings Sheet and Plate --------0.10 --0.30 --- ----0.10 --0.05 0.10 0.05 --- T.O. 1-1A-9 4-7 4-8 ALLOY AL MN ZINC ZE41A ZH42* ZH62A* ZK20A ZK51A ZK60A ZK60B ----------------------------4.25 3.0-4.5 5.2-6.2 2.0-2.6 3.6-5.5 4.8-6.2 4.8-6.8 T.O. 1-1A-9 Table 4-3. Chemical Properties of Magnesium Alloys - Continued ZIRCONIUM RARE EARTH 1.25 ------------- THORIUM SI CU NICKEL MG FORMS 0.5 0.5 0.5-1.0 0.45mn 0.5-1.0 0.45 0.45 --1.5-2.5 1.4-2.2 --------- --------------- ----0.10 --0.10 --0.10 ----0.01 --0.01 --0.01 Bal Bal Bal Bal Bal Ba1 Bal Castings, Sand Castings, Sand Castings, Sand Extrusions Castings, Sand Extruded Bars/Rods/Shapes Tube-Forgings Same *NOTE: These alloys contain radioactive thorium. See paragraph 4-15 (1) Calcium, AZ31B, 0.04---MIA, 0.4.0.14 (2) Iron, AZ31B, 0.005---AZ61A, 0.005---AZ63A, 0.005. (3) Silver, QE22A, 2.5-3.0 (4) Tin, TA54A, 4.6-6.0 Table 4-4. Mechanical Properties Magnesium Extrusions and Forgings at Room Temperature - Typical ALLOY & C0ND FORM DIEMN (DIA THICKNESS: WALL THKNESS - IN’S) CROSS SECTIONAL AREA (INCHES) MIN TENSILE STR (1000PSI) MIN TEN YLD STR (1000PSI) MIN ELONGAtion (2″ %) 7 7 7 7 8 8 9 7 7 9 8 6 4 4 4 2 4 MIN SHEAR STR (1000PSI) HARDNESS (BRINELL) AZ31B-F and AZ31C-F Bars, Rods, shapes Hollow shapes AZ61A-F Bars, rods, shapes Hollow shapes AZ80A-F Bars, Rods, shapes 0.249 and under 0.250-1.499 0.500-2.499 2.500-4.999 All dimensions 0.249 and under 0.250-1.499 0.250-4.999 All dimensions 0.249 and under 0.250-1.499 1.500-2.499 2.500-4.999 0.249 and under 0.250-2.499 2.500-4.999 Not applicable 0.249 and under 0.250-1.499 1.500-2.499 2.500-4.999 All dimensions All dimensions All dimensions All dimensions All dimensions All All All All All All All All All All All All All All All All areas areas areas areas areas areas areas areas areas areas areas areas areas areas areas areas 35 35 34 32 32 38 39 40 36 43 43 43 42 47 48 45 37 30 32 32 29 28 43 43 40 45 46 21 22 22 20 16 21 24 22 16 28 28 28 27 30 33 30 26 not not not not not 31 31 28 36 38 req req req req req 17 17 17 -17 -18 -18 19 19 19 --21 -- -49 --49 -60 -60 60 60 60 60 82 82 82 T-5 Same HM31A-T5* MIA-F Bars, rods, shapes Bars, rods, shapes Under 4.000 All All All All All areas areas areas areas areas Hollow shapes ZK60A-F Bars, rods, shapes Hollow shapes Bars, rods, shapes Hollow shapes 2 3 2 2 2 5 4 5 4 4 -15 15 -15 22 22 -22 22 44 44 44 44 44 75 75 -82 82 4.999 and under 5.000-29.999 All areas 4.999 and under All areas T5 T.O. 1-1A-9 4-9 250 0. Mechanical Properties Magnesium Extrusions and Forgings at Room Temperature .050-0.IN’S) CROSS SECTIONAL AREA (INCHES) MIN TENSILE STR (1000PSI) MIN TEN YLD STR (1000PSI) MIN ELONGAtion (2″ %) MIN SHEAR STR (1000PSI) HARDNESS (BRINELL) EXTRUDED TUBES 0.500 0. 1-1A-9 Table 4-4.050-0.4-10 ALLOY & C0ND FORM AZ31B-F and AZ31C-F AZ61A-F MIA-F ZK60A-F ZK60A-T5 AZ31B-F AZ61A-F AZ80A-F AZ80A-T5 T6 MIA IA54A-F ZK60A-T5 T.250 Not applicable Not applicable Not applicable Not applicable DIE FORGINGS 28 40 46 46 -28 38 38 2 5 5 4 ----- 42 75 75 82 34 38 42 42 50 (typ) 30 36 42 19 22 26 28 34 (typ) 18 22 26 6 6 5 2 5 (typ) 3 7 7 17 19 20 20 -14 --- 55 55 69 72 72 47 --- NOTE: This alloy contains radioactive elements.O.500 0.050-0.500 Not applicable 32 16 8 -46 0. .050-0.Continued DIEMN (DIA THICKNESS: WALL THKNESS .Typical .050-0. See paragraph 4-15 for precautions. 125 0.501-1.001-1.000 0.188 0.001-3.000 0.000 1.000 0.250 0.500 0.Table 4-5.016-0.501-0.750 0.016-0.250 0.500 0.251-2.250 0.250 0.016-0.016-0.500 0.064 0.Typical ALLOY & COND AZ31B-F AZ31B-H10 -H11 -H23 -H24 DIMENSION THICKNESS (INCHES) All gauges 0.500 0. 1-1A-9 * Contains radioactive thorium element.000 1.251-0.060 0.500 0.250 0.000 All gauges 0.189-0.001-3.250 0. See paragraph 4-19 for precautionary data.060 0.064 0.751-1. 4-11 .251-0.016-0.065-0.016-0.000 1.500 0.251-1.250 MINIMUM** TENSILE STRENGTH (1000PSI) 35 (typical) 30 32 39 39 39 39 37 37 37 37 35 32 32 32 30 32 30 30 30 29 34 31 34 33 31 32 30 29 33 (typ) 35 (typ) 30 30 29 36 34 31 MINIMUM** TENSILE YIELD STR (1000PSI) 19 (typical) 12 12 25 25 29 29 24 22 25 23 22 18 15 15 15 15 16 16 15 14 26 22 25 25 18 21 19 18 18 (typ) 26 (typ) 18 15 12 25 22 20 MIN ELONGATION (2″--%) MINIMUM SHEAR STRENGTH (1000PSI) -----18 18 -----17 17 -------21 21 20 20 ---- HARDNESS (BRINELL) USE Tooling Plate Standard Plate Standard Plate and Sheet Standard Sheet and Plate Spec Sheet and Plate Same Same Same Spec Sheet and Plate Spec Sheet and Plate Same Same Same Tread plate Sheet Sheet Sheet Sheet Sheet Sheet Sheet Sheet Sheet Sheet Sheet Sheet and and and and Plate Plate Plate Plate 12 (typical) 10 12 4 4 4 4 10 10 8 8 8 12 12 12 10 8 12 12 12 12 4 4 4 4 4 6 6 6 17 (typ) 7 (typ) 15 15 12 4 4 4 -H26 -0 AZ31C-F HK31A-0* --73 73 -----56 56 --52 ----57 57 --- -H24* (typ) (typ) (typ) (typ) HM21A-T8 MIA-O H ZE10-0 H24 17 (typ) 7 (typ) 48 54 Sheet and Plate Sheet and Plate Sheet and Plate T.016-0. ** Values given are all minimum unless otherwise noted beside value.061-0.061-0. Mechanical Properties Magnesium Alloy Sheet and Plate at Room Temperature .000 0.126-0.125 0.065-0.000 All Gauges All gauges 0.O.000 1.063 0.016-0.001-2.126-0.251-0.501-1.501-2.251-0.251-0.016-0.501-1.250 0. 8 21 20 --23 --24 22 26 HARDNESS (Brinell) 54 52 69 69 50 55 55 73 55 52 55 -73 65 63 80 84 45 45 50 50 55 57 --62 --70 65 68 AM100A-F -T4 -T6 -T61 AZ63A-F -T4 -T5 -T6 AZ81A-T4 AZ91C-F -T4 -T5 -T6 AZ92A-F -T4 -T5 -T6 EK30A-T6 EK41A-T5 -T6 EZ33A-T5 HK31A-T6* HZ32A-T5* KIA-F QE22A-T6 ZE41A-T5 ZH42-T51* ZH42-T4* ZH62A-T5 ZK51A-T5 ZK61A-T6 22 40 40 40 29 40 30 40 40 24 40 23 40 24 40 26 40 23 23 25 23 30 29 24 35 28 32.0 40 39 20 34 34 34 24 34 24 34 34 18 34 23 34 20 34 20 34 20 20 22 20 27 27 24 35 28 -35 35 34 39 DIE CASTINGS AZ91A-F AZ91B-F 33 33 --22 22 --3 3 --20 20 67 67 NOTE: *This alloy contains radioactive thorium element.T.5 12 4 8 5 -6 2 -4 7 2 3 7 -7 -3 1 6 -1 2 -1 2 4 4 14 2 2. Mechanical Properties of Magnesium Alloy Castings at Room Temperatures ALLOY & COND TENSILE STRENGTH (1000 PSI) TYPE MIN TENSILE STRENGTH YIELD (1000 PSI) TYPE MIN 12 13 16 22 14 14 16 19 14 14 14 12 19 14 14 17 21 16 16 18 15 15 14 6 25 19 21.5 11 2 5 2 10 1 2 3 1 3 3 8 7 14 2 2.6 -22 24 26 10 10 15 17 10 10 10 16 10 10 10 12 16 10 10 11 18 14 14 16 14 13 13 6 25 19 --22 20 26 TYPICAL ELONGATION IN 2″--% TYPE MIN 2 10 4 1 6 12 4 5 12 2. See paragraph 4-19 precautionary instructions.6 35.7 19.5 --5 5 5 SHEAR STRENGTH (1000 PSI) 18 20 21 21 16 17 17 19 17 16 17 -19 16 17 16 20 18 18.5 4.5 33. 1-1A-9 Table 4-6.4 19.O. 4-12 . 0 29.065 0.065 MELTING RANGEoF 867-1101 867-1101 867-1101 1116-1169 977-1145 850-1130 850-1130 850-1130 914-1130 914-1132 875-1105 875-1105 875-1105 875-1105 830-1100 830-1100 830-1100 1100-1184 1193 1193 1010-1189 1092-1204 1100-1195 1121-1202 1026-1198 1200 -1100-1200 1180 1180 -1020-1185 968-1175 968-1175 968-1175 1145 ELECTRICAL CONDUCTIVITY (IACS) 11.066 0.065 0.5 34.81 1.9 12.065 0. covered.0 24. g.81 1.77 1.066 0. Machine the metal dry whenever possible.5 9.3 18.79 1.5 11.645 0.83 1.065 0.82 1.86 1.065 0.0 31. If chips should become ignited.066 0.0 22.064 0.067 0. e.6 15.066 0.5 12.80 1.79 1.81 1.5 -28. Store magnesium chips in clean.83 1.066 0.064 0.065 0.065 0. 1-1A-9 Table 4-7.0 26.065 0.065 0.066 0.1 11. If a coolant is def initely required use a mineral oil. Keep an adequate supply of a recommended magnesium f ire extinguisher within reach of the operators.83 1.067 0.6 12.0 30. c.81 1. Physical Properties Magnesium Alloy @68oF ALLOY & COND SPECIFIC GRAVITY 1.83 1.063 0. Do not allow chips to accumulate on machines or operator’s clothing.065 0.064 0.O. avoiding f ine feeds and keeping speeds below 500 700 surface feet per minute during turning and boring.83 1. extinguish them as follows: 4-13 .83 1.065 0.76 1. Keep work areas clean.5 9. non-combustible containers where they will remain dry.81 1.066 0.065 0.065 0.066 0.0 -- AM100A-F -T4 -T6 AZ31B and AZ31C AZ61A AZ63A-F -T4 -T6 AZ80A AZ81A AZ91A-AZ91B AZ91C-F -T4 -T6 AZ92A-AC -T4 -T6 EK30A EK41A-T5 -T6 EZ33A HK31A-T6 HM21A HM-31A-F HM32A MI-A TA54A ZE10A ZH42 ZH62A ZK21A ZK51A ZK60A-F -T5 ZK60B ZK61A NOTE: Percentage conductivity of annealed copper at 68oF (international annealed copper standard).82 1.81 1.82 1.0 12.066 0.87 1.81 1.0 25. f.3 13.8 10.066 0.80 1.066 0. plainly labeled.065 0.3 10.83 1.76 1.066 0.T.83 1.065 0.81 1. Machinists should not wear textured or fuzzy clothing and chips and sawdust should not be allowed to accumulate in cuffs or pockets.0 26.9 11. Do not permit tools to rub on the work af ter a cut has been made.81 1.81 1.067 0.3 27.80 DENSITY LBS/CU in 0. d.77 1.80 1.9 26.0 26.80 1.0 10.2 12.5 --23.86 1.81 1. detail B is used with booth type portable grinding and polishing where the dust passes through the grate with the air being circulated into a liquid spray which removes the dust. Keeping the cutting speed below 700 feet per minute will greatly reduce the f ire possibilities even with a dull or poorly designed tool and f ine feeds. The sludge will burn with intense heat. Alternately. This may be done by spreading it on a layer of f ire brick or hard burned paving brick to a maximum depth of 3″ to 4″. completely clean the entire collector systems. Do not grind sparking material on these grinders unless the magnesium dust has been completely removed from the equipment system. a one or two inch layer of powder can be spread on the f loor or surface nearby and the burning metal transferred to it. In addition. In addition a suitable devise should be installed in the system that will insure the collector system is in full operation and has changed the air in the ducts. 4-14 . 4-23. A method of rendering magnesium sludge chemically inactive and non-combustible by reacting it with a 5% solution of ferrous chloride (Fe C122H2O) is detailed in the National Fire Protection Association’s Bulletin No. detail C. The clothing of operators should be smooth and f ire retardant without pockets and cuffs. If such accumulation is evident the collector system is not operating properly and must be checked and repaired. (1) Cover with a layer of G-1 or Met-L-X powder. Keep dust from accumulating on surrounding f loors. Fire control is the same as detailed in paragraph 4-21 for machine chips. Any dust escaping the hood should be kept swept up and properly disposed of. windows. The dust produced during grinding and polishing of magnesium must be removed immediately from the working area with a properly designed wet type dust collection system. the hood design and the oil pan combine to afford a satisfactory dust collection. Clean. etc. 4-22. During grinding and polishing operations a proper dust collection system must be used. Standards for Magnesium. If chrome pickled magnesium is to be ground. Maintain adequate supplies of plainly labeled approved f ire extinguishing powder and suitable dispensing tools readily available to operators.O. c. (2) Actively burning f ires on combustible surfaces should be covered with a 1/2 inch layer or more of extinguishing powder. dull. On individual grinders for small scale work. several times before the grinder begins running. clean dry sand. b. Periodically and no less than once a month. 1-1A-9 WARNING Water or any of the common liquid or foam type extinguishers will intensify a magnesium chip f ire and may cause an explosion and shall not be used. Design the booth to catch all the dust possible. e. as shown in Figure 4-1. Therefore. the grinding wheel or belt must be replaced prior to grinding of any other metal. chipped or improperly designed tools. then the entire mass shoveled into an iron container or onto a piece of iron plate. Small collectors as shown in Figure 4-1. then placing a combustible material on top of it and burning the entire lot. 48. air exhaust blower and liquid level controller should be electrically water connected so cessation or failure of the dust collector operation will shut the grinder off. The grinder-to-collector ducts should be short and straight. Do not store or allow to even partially dry since it is extremely f lammable. The grinder’s power supply. then add more powder as required. f. The collector portrayed in Figure 4-1. Figure 4-1 illustrates acceptable type collectors. (3) High cutting speeds. etc. The following specif ic safety rules pertain to the grinding and polishing of magnesium: a. graphite powder. extremely f ine feeds. tool dwell on work af ter feed is stopped. dry unrusted cast iron chips. The self opening vents illustrated prevent hydrogen collection during shut down. Proper systems precipitate the magnesium dust by a heavy spray of water and must be so designed that dust or sludge cannot accumulate and dry out to a f lammable state. a safe location must be used. Dispose of grinding sludge as soon as it is removed from the equipment. talc and pitch may also be used.. All clothing should be easy to remove and kept free of dust accumulations. benches.T. therefore. detail A serving one or two grinders are the best. or tool hitting a steel or iron insert increase the chances of chip ignition. sparks may result. GRINDING AND POLISHING SAFETY PRACTICES. dust and air-dust mixtures must not be allowed to accumulate within spark range. Magnesium grinding should be done on equipment set aside and labeled for that purpose. d. Caps should be worn. tool rub. Dry type f ilter collectors or central collector systems which carry the dust through long dry ducts should not be used for magnesium. Inspect and clean the grinder to collector ducts daily or move frequently if the volume of collection is high. a small f ire should be removed from the furnace. proceed as follows: a. personnel must not enter such clouds or any area where there is reason to believe the safe level is exceeded unless wearing a gas mask with an acid gas canister containing a dust f iller. Analysis of atmosphere in the worker’s breathing zone will be accomplished to assure personnel safety. the powder can be applied to the burning parts with a shovel (assuming the furnace door can be opened safely). then shut the fan off. The furnace door should be kept closed during this action and until a def inite temperature drop below 700oF is evident. when needed. Remove parts not burning with long handled hooks. Connect the gas feed line to this port. Metal Fyr Powder of the Fyr Fyter Company is the same material. Use furnace equipment having two sets of temperature controls. 4-26. Provide approved f ire extinguishing equipment. if safe and good quality workmanship is to result. Shut off all power. Running the furnace circulating fans for about 1 minute af ter the gas is f irst introduced will assist in gas dispersal. open the feed line valve to provide about 2 lbs/minute (depending on furnace size and number of gas cylinders) and maintain gas f low until furnace temperature drops to 700oF indicating the f ire is out. a gauge pressure of 15-30 psi will deliver 1-2 lbs of BF3 per minute. The cylinders should be weight checked for contents every 6 months.O. This is an effective gaseous means of extinguishing magnesium f ires in heat treating furnaces. Five parts per million by volume of air or more are usually present in visible clouds of material resulting from the release of the gas to atmosphere. Using 10 feet of hose and feed of pipe. and C f ires shall not be used. on a suitable dolly. as evidenced by excessive furnace temperature and omission of a light colored smoke. WARNING Water and other extinguishers for Class A. pumps have been constructed which can throw 75-100 lbs/ minute onto the f ire through a 30 foot hose and nozzle. The gas is introduced into the furnace from a storage cylinder through an entry port preferably located near f loor level. Deleted. Heat treating of magnesium alloys requires the exercising of certain def inite rules. The cylinders may be permanently connected or brought to the furnace. Begin f ire extinguishing procedures using one of the following methods: (1) G-1 Powder Method. Notify f ire marshal control crew at once. (2) Boron Trif luoride (BF3) Gas Method.T. The gas cylinder used should be f itted with a Monel needle valve and a ‘‘tee’’ for attaching a 0-160 psi pressure gauge. e. b. A suitable gas transfer system uses a 5/16″ f lexible bronze hose to carry the gas to the furnace where it enters through a 1/4″ steel pipe entry port. c. dumped into an iron container and then extinguished by covering with G-1 powder which is a graphite base powder of the Pyrene CO2 Company. 4-25. Therefore. Paper bags f illed with the powder can be used if the f ire is so located that such bags can be thrown in effectively. f. Load the furnace with castings of one identical alloy only. HEAT TREATING SAFETY PRACTICES. operating independently of each other. WARNING Boron trif luoride vapor or gas is toxic in the proportion of more than 1 part per million by volume of air when exposures are prolonged or frequently repeated. the furnace load should be allowed to cool with the door open. Standardize checking procedures and adjustments of all equipment and of operating cycles. b. If a f ire should occur for any reason. c. d. For the handling of large quantities of G-1 powder. In large furnaces or with f ires of high intensity. This gas does not require heating in order to f low. Use SO2 (Sulfur Dioxide) atmosphere to control oxidation. Af ter all burning parts have been Change 1 4-15 . Where it can be safely done. 1-1A-9 4-24. B. Use the recommended time and temperature operating ranges at all times. fuel and SO2 feed lines to the furnace. covered with the powder. The following rules should be closely followed: a. Insure the castings are clean. approximately.5% solution of silver nitrate. it is more expensive than trif luoride. Pure magnesium will melt at approximately 1202oF. NOTE SAE-AMS-M-6857. This material has been successfully used to extinguish magnesium heat treat furnace f ires. the gas must be heated to f low freely. and observing the reaction for 1 minute.5g. The cylinder outlet should be f itted with a special valve and gauge to control gas f low. 1-1A-9 (3) Boron Trichloride (BCL3) Gaseous Method. Of f irst importance in the heat processing of these alloys is a clear understanding of the characteristics of the metal relative to heat. whether a light metal is magnesium or not can be generally determined by a simple test consisting of placing the test metal in contact with an 0. it indicates it is aluminum free alloy. However. if necessary. If this agent must be used. Therefore. If a greyish iridescent coating forms the alloy contains aluminum. Workmen should not occupy areas where noticeable vapors are present unless wearing a gas mask with an acid gas canister containing a dust f ilter. will be the control for heat treatment of magnesium alloy castings used on aerospace equipment. Certain alloys such as AZ63A Type 1. during any heating of alloy items. In the case of these two 4-16 Change 4 . Flexible 5/8″ ID neoprene hose may be used to connect the cylinder to a steel pipe for insertion into the furnace port. If the metal assumes a very bright brassy coating. the liquid is corrosive and the fumes irritating with a health hazard similar to hydrochloric acid fumes. 4-29. IDENTIFICATION OF ALLOY. according to their element constituency. Otherwise its use in extinguishing a furnace f ire is similar to the procedures for boron trif luoride. or AZ92A Type 1.04% of boron trif luoride. The solution should be freshly prepared and the test operator familiar with the colors of chemical treatment. refer to latest issue of SAE-AMS-M-6857.GENERAL. 1). Positive identif ication of an alloy. Formation of a black deposit of metallic silver on the metal indicates magnesium or high-magnesium alloy. . Type I Specif ication MIL-M-3171 (Commercially known as DOW No. by grinding or f iling a clean area on the surface. They must be brought up to heat treating temperature slowly enough to prevent this. there are several factors involved with its use which makes it less preferred than boron trif luoride. PRECAUTIONS DURING HEATING. 4-30. Prior to the test the metal should be thoroughly cleaned down to the base metal. the liquid containing cylinders should be heated with infrared lights to provide the heat necessary to insure adequate gas f low. Then immerse the metal in a chrome pickle chemical solution. these include: ten times more concentration than the 0. are subject to eutectic melting of some of its elements if heated too rapidly. Additional Heat Treatment information is discussed in Section IX. particularly during solution heat treating. The metal is easily burned and overheating will also cause formation of molten pools within it. The solution is made by dissolving 0. HEAT TREATING MAGNESIUM ALLOYS . 4-28. of water. 4-27. For complete description of magnesium alloy castings heat treat requirements. can only be determined by laboratory analysis. Heat Treatment of Magnesium Alloy Castings. . either condition resulting in ruining of the metal.O. The alloys melting points range from 830oF to 1204oF. However.T. The solution is made in the proportions of 24 ounces sodium dichromate and 24 f luid ounces concentrated nitric acid to enough water to make one gallon. specif ied temperature maximums must be closely adhered to. from a constituency standpoint. of silver nitrate in 100 ml. hangers. The temperature of all test locations should be determined at 5 to 10 minute intervals af ter insertion of the temperature sensing elements in the furnace. direct heating element radiation or f lame impingement on the articles being treated. The temperature control shall be capable of maintaining a given temperature to within ± 10o F at any point in the working zone. carbon dioxide or other satisfactory oxidation inhibitor shall be used when heating to 750oF and over. af ter the charge has been brought up to this temperature. A minimum of 9 test locations within the furnace load area should be checked. a protective atmosphere containing suff icient sulphur dioxide. 4-37. The monthly survey should consist of one test for a solution heat treat temperature and one test for a precipitation heat treat temperature. of 9 test locations required regardless of the volume. 4-34. maintain and record the furnace temperatures. it is mandatory that suitable support be provided for articles being processed to prevent warping. A monthly survey should be made af ter the initial survey. 4-32. Furnaces used for solution heat treatment shall be of the air chamber type with forced air circulation. In an oxidizing atmosphere. since the alloys tend to become plastic at high heat treat temperatures. Suitable jigs. The thermocouple and sensing elements should be replaced periodically because of the in-service incurred effects of oxidation and deterioration. to record actual metal temperatures. This will be above the variation expected but shall not be more than 10oF above the maximum heat treat temperature of the alloy being processed. their concentration percentage in the furnace atmosphere should be periodically checked for correct amounts. 4-31. f ixtures. For all surveys. 4-38. To prevent such occurrences. These devices shall be interconnected with a manual reset control. 4-35. HEAT TREATING EQUIPMENT. The holding periods given are for castings up to 2 inches thick. temperature measuring and recording instrument equipment to assure complete and accurate control. this characteristic can result in ignition and f ierce burning. Solution for heat treating of magnesium alloyed articles is accomplished by heating at an elevated temperature in an air furnace for a specif ic length of time (holding period). 4-39. 1-1A-9 examples. One in each corner. one for each 40 cubic feet of heat treating volume with a minimum. Table 4-8 below lists the recommended soaking and holding time for solution heat treating alloys. The safety measures def ined in paragraph 4-1 must be rigidly practiced. one in the center and one for each 25 cubic feet of furnace volume up to the maximum of 400 cubic feet. Upon initial furnace installation and af ter any maintenance on the furnace or its equipment which might affect its operational characteristics. is that it is subject to excessive surface oxidation at 750oF and higher temperatures. electricity or oil. the furnaces should be allowed to heat to a point stabilization before taking any readings.O. 4-36. ventilators and other equipment shall be used in processing the articles. a temperature survey shall be made to test its capability of maintaining the minimum and maximum temperatures required for the various treatments it will be used for. a periodic survey should be made. HEAT TREATMENT SOLUTION. Pyrometers used with the automatic control system to indicate. There shall also be protective devices to shut off the heat source in case of circulation air stoppage. unless separate load thermocouples are employed. The maximum temperature variation of all elements shall not exceed 20oF and shall not exceed the solution or precipitation heat treating range at any time af ter equilibrium is reached. When oxidation inhibitors are used. These requirements and those of other pertinent specif ications and instructions should be consulted and strictly adhered to in processing the metal. using the test criteria of the initial survey. racks. should preferably be of the potentiometer type. trays. The particular requirements for various alloys are detailed in paragraph 4-46 in this section. AZ92A (Type 2). AZ91C and QE22A sand castings and AM100A permanent mold castings 4-17 . An additional and no less important characteristic of the metal relative to heat treatment. 4-33. during which certain alloying elements enter into uniform solid solution. In addition. Items thicker than 2 inches will require longer periods. The furnaces shall be installed with the necessary control. Heating provisions can be gas. The safety cut-outs shall be set as close as practicable above the maximum solution heat treating temperature for the alloy being treated. Each furnace used shall be equipped with a separate manual reset safety cut-out which will turn off the heat source in the event of any malfunction or failure of the regular automatic controls. Their design must be such as to make impossible. no less than two hours should be consumed in bringing them from 640oF to treating temperature.T. Furnace control temperature measuring instruments shall not be used as test instruments during any survey. Precipitation heat treatment or artif icial aging of alloys is accomplished at temperature lower than those of the solution treatment. since elements of the alloy subject to melting points lower then the alloy itself can go into solution. Distortion is not a particular problem during precipitation or stabilization treatment or annealing. The same general procedure of heating to temperature. (generally referred to as charging the furnace). In the case of complicated formed parts. carbon dioxide or other satisfactory oxidation inhibitor shall be used when solution heat treating at 750oF and over. it is good practice to handle magnesium alloy articles with care at all times under elevated heat conditions. holding for a time and cooling to room temperature is used as in the other two types. improve the ductility. When applied to a solution treat treated alloy. soaked or held at that temperature for a specif ied time and cooled to room temperature. and/or ref ine the grain structure. Individual pieces should be racked or supported to prevent distorting without interfering with the free f low of the heated atmosphere around the article. The alloy is heated to the proper temperature. 4-40. Suggested aging treatments for various alloys are as cited in Table 4-9. Since magnesium castings are subject to excessive surface oxidation at temperatures of 750oF and over. Stabilization heat treating an alloy increases its creep strength and retards growth at service encountered elevated temperatures. Placing of articles to be treated in the furnace.T. 1-1A-9 may be charged into the furnace which is at the heat treating temperature. 4-41. it may be necessary to utilize a specially contoured 4-18 . The whole casting must be heat treated. The desired effects are gained by controlling the temperature. Distortion or warping can occur due to the semi-plastic qualities of the alloys at the furnace elevated temperatures during solution heat treat. sof ten the material for forming. not just part of it. Avoid excessive time at temperature to prevent unwanted grain growth. Actually stabilization treatment is a high temperature aging treatment accomplished quickly rather than allowing an alloy to age naturally over a period of time. Conversely. generally resulting from forming operations.O. However. Table 4-8. should not be done in a haphazard fashion. Solution Heat Treating Temperatures and Holding Times ALLOY AM100A AZ63A (Type 1) AZ63A (Type 2)* AZ81A AZ91C AZ92A (Type 1) AZ92A (Type 2) HK31A QE22A** ZK61A TEMPERATURE RANGE 790-800 720-730 (F to T4) 720-740 (F to T4) 770-785 770-785 760-770 775-785 1045-1055 970-990 925-935 or 895-905 TIME PERIOD(HRS) 16-24 10-14 10-14 16-24 16-24 16-24 14-22 2 4-8 2 10 MAX TEMP oF 810 734 745 785 785 775 785 1060 1000 935 935 * Contains calcium. HEAT TREATING PROCEDURES. Annealing of magnesium alloys is accomplished to relieve internal stresses. it increases the alloy’s yield strength. no attempt should be made to shorten the time at temperature and over all annealing time by increasing the temperature. 4-43. only the temperature and time elements are different. ** Quench in 150oF water bath within 30 seconds af ter opening of furnace. a protective atmosphere containing suff icient sulphur dioxide. 4-42. hold time and cooling medium exposure. O. cool in still air or oven. Aging increases basic yield strength and hardness and decreases toughness and elongation. French . AM100-A . Table 4-9.Used in low cost extruded bars. Cooling af ter treating is accomplished in either still or blast air.5% SO2 atmosphere 20 hours at 790oF.Use in general purpose extrusions with good properties. solid 1120oF. structural sections and tubing with moderate mechanical properties and high elongation sheet and plate. a. Hot working temperature is 450 . depending upon the alloy. Foreign equivalents are: British DTD 120A Sheet. Hot working temperature 350o750oF. Anneal Change 1 4-19 .T. Others are aged from T4 condition. hard rolled sheet = 300oF for 60 minutes. Annealing temperature 650oF. high resistance to corrosion. shapes. Rarely used in sheet form. b. yield strength and elongation. In the following paragraphs are brief summaries of the general characteristics of the various alloys. Stress relief of extrusions and annealed sheet = 500oF for 15 minutes. ALLOY GENERAL CHARACTERISTIC INFORMATION. 1-1A-9 jig or f ixture to adequately protect the design contour of the item at high temperatures. Electron AZ31. F3 and T8. cool in still air. shortness temperature above 780oF. The water should be at 150oF temperature. Completely artif icial age 5 hours at 450oF.SOC Gen Air Magnesium. Artificial Aging (Precipitation Treatment) ALLOY & TEMPER AM100A-T6 AM100A-T5* AZ63A-T6 AZ63A-T5* AZ91C-T6 AZ92A-T6 (Type 1) AZ92A-T6 (Type 2) AZ92A-T5* (Type 2) EZ33A-T5* HK31A-T6 HZ32A-T5* QE22A-T6 ZH62A-T5* ZK51A-T5* ZK61A-T5* ZK61A-T6 AGING TREATMENT 5 hours at 450oF or 24 hours at 400oF 5 hours at 450oF 5 hours at 425oF or 5 hours at 450oF 4 hours at 500oF or 5 hours at 450oF 16 hours at 335oF or 4 hours at 420oF 4 hours at 500oF or 5 hours at 425oF 5 hours at 450oF or 16 hours at 400oF or 20 hours at 350oF 5 hours at 450oF 2 hours at 650oF or 5 hours at 420oF or 5 hours at 420oF 16 hours at 400oF 16 hours at 600oF 8 hours at 400oF 2 hours at 625oF or 16 hours at 350oF 8 hours at 424oF or 12 hours at 350oF 48 hours at 300oF 48 hours at 265oF *T5 is aged from as-cast condition. 4-44.800oF. good formability and strength. good weldability. The one exception is alloy QE22A which is water quenched. German and Italian. press forgings with good mechanical properties. rods. 4-45. intermediate cost. AZ31B and C .Used in pressure tight sand end permanent mold castings with good combination of tensile strength. Solution heat treat in 0. c. AZ61A . 1351350 forgings. Liquid temperature 1170oF. 4-46. Partially artif icial aging -12 hours at 325oF. cool in strong air blast. Used as pressure tight sand casting alloy. H23 sheet may be stress relieved af ter welding at 650oF for 1 hour or 675oF for 20 minutes. Age for 16 hours at 400oF. 16 hours at 780oF. Stabilize at 300oF at 4 hours and cool in air. AZ63A . Good strength at 300o . HK31A . Has high tensile and yield strengths. EK30A .O. Hot work at 850oF 1100oF Anneal at 850oF.Used in sand casting for elevated temperature applications. Solution heat treat at 1060oF maximum 16 hours then cool in air or with fan. k.Used in sand castings for good strength properties with best ductility and toughness. Heat treatable.1000oF.500oF.5% SO2. n.used for die castings generally. Foreign equivalents are British BS 1351 (forgings) BS 1354 (extrusions). AZ91B . Heat treat annealed sheet extrusions and forgings 15 minutes at 500oF rolled sheet 400oF for 15 minutes. Table 4-11. Deleted. Shortness temperatures are above 750oF. d.Used for extruded and press forged products. Solution heat treat sand castings by loading into a 1050oF furnace and holding for 2 hours. 4 hours and air cool.Used in pressure tight sand and permanent mold castings. Good salt water anti-corrosion properties. 500oF for 15 minutes. German AZ855 Helium or Argon-arc weldable using AZ92A welding rod or may be resistance welded. Solution heat treat at 740oF in a 0. Cool in strong air blast. Superior modulus of elasticity particularly at elevated temperatures. Foreign equivalents are Elektron AZG. Heat treat forgings (T5)450oF for 16 hours. Resistance welding is also satisfactory. forgings 500o F for 15 minutes. Stabilize for 4 hours at 500oF. Stress relieve af ter welding. usable at 650oF and above. Hot work at 700oF . Solution heat treat 20 hours at 760oF in an atmosphere of 0. HM31A . l.Used in extruded bars. Exposure to temperatures through 600oF for periods of 1000 hours caused practically no change in short time room and elevated temperature properties. shapes and tubing for elevated temperature service. Equal to AX63A in salt water corrosion resistance. Table 4-10. annealing temperature 725oF. Forgeign equivalent British ZRE1. Artif icial aging is done at 420oF for 14 hours. British DTD59A(as cast)and DTD-289 (heat treated). extruded and artif icially aged 400oF for 60 minutes. AZ81A . Age at 400oF then air cool. Hot working temperature 600-750oF. cool in air or by fan. Shortness temperature above 775oF. 2 hours at 665oF and 10 hours at 775oF may be used. Anneal at 750oF. German AZM. HM21A . 5 hours at 450oF. AZ92A . T-7 condition. Has excellent weld and forming characteristics in sheet/plate form and retains good strength up to 650oF. f.Used in sand or permanent mold castings for good strength. Heat treat: T-4 condition.500oF.T. EZ33A . Age at 420oF for 5 hours. pressure tightness and toughness. AZ91C is used for pressure tight sand and permanent mold castings having high tensile and weld strength. T-6 has good yield strength and. 4-20 Change 1 . air cool. o. Cool in air or oven. AZ80A . Stabilizing treatment 500oF. Good impact resistance in T-4 temper. j. g. good strength sand and permanent mold castings where temperatures may reach 500oF in use. i. Foreign equivalents are British 1351 (forgings). Solution heat treat 775oF for 18 hours.5%SO2atmosphere for 10 hours then cool in air. e. AZ91C . Foreign equivalents are Elektron AZ91 and British DTD136A.Used sheet. Age at 400oF 16 hours.Used in sand castings for elevated temperature use up to 650oF and sheet and plate applications. Sheet may be resistance welded.AZ91A . excellent ductility. Solution heat treat at 1060oF maximum 16 hours then cool in air by fan. ductility. plate and forgings. Aging is done at 450oF for 5 hours and cooled in air or furnace. m.AZ91B . 1-1A-9 650oF. h. Deleted. AZ91A. Readily castable with low micro-shrinkage tendency. To prevent germination (grain growth) an alternate heat treat of 775oF for 6 hours. Hot working temperature is 800o to 1050oF. Stress relief: as extruded.is also die cast alloy but has higher impurity content. EK41A .Used for pressure tight. then cool in air. then fan or air cool. cool in air blast and then age at 400oF for 4 hours. rods. Has good strength properties in temperature range 300o. pressure tight.Casting alloy with comparatively low strength has excellent damping characteristics. q. Solution heat treat at 925o . u. Foreign equivalent . Hot work at 500o . Foreign equivalent is German ZW6. Quench in 150oF water bath.905o F for 10 hours. w. The alloy is a precipitation hardening one from the as-cast condition and requires no solution heat treatment.Used as a wrought alloy for extruded shapes and press forgings. y. ZK60A . Foreign equivalents are British BS1352 (forgings) and German AM503. Anneal 400oF. ZK51A . Heat treat for 12 hours at 350oF.British RZ5. hard rolled sheet at 400oF in 60 minutes. More ductility and better shock resistance may be obtained by overaging at temperatures such as 750oF. aa. ZE10A . 16 hours at 350oF air cool. T4 condition 750oF for 24 hours. TA54A . air cool. in 15 minutes. No stress relief required af ter welding. r. ZK61A . Age 2 hours at 625oF.Used in sand castings for aircraf t engines and airframe structures where high Paragraphs 4-47 through 4-51 deleted.Used for sand castings. rod. Has high strength and good ductility characteristics.900oF. ZE41A .O. weldable alloy. v.Used for low cost. z. Hot work at 560o .A good strength.Used for wrought products and provides for moderate mechanical properties with excellent weldability. ZH42A . Hot work at 600o-750oF. moderate strength sheet and plate.Best hammer forging alloy. ZH62A . corrosion resistance and hot formability. Stress relieve annealed sheet at 500oF. Change 1 4-21 . Age at 300oF for 24 hours. Solution heat treat at 970o-990oF 4 to 8 hours.Used for high yield strength. Resistance welding also satisfactory. It is of properties for medium and long range exposure at temperatures above 500oF and is pressure tight. Foreign equivalent is British T26. good ductility. For T51 condition treat at 480oF for 24 hours. Good weldability using shielded arc and AZ61A or AZ92A. HZ32A . x. s. Foreign equivalent is British Z52.Castings have high yield strength at elevated temperatures. 1-1A-9 p. air cool. sand castings. Heat treat at 480oF for 12 hours.T. and extrusions at 500oF in 15 minutes.Used as a high strength good ductility structural alloy at normal temperatures and has the highest yield strength of any alloy except ZK61A-T6.Casting Alloy. ZK21A . Shortness temperature is 950oF.An alloy of moderate strength for extrusion fabrication. Anneal at 700oF. AZ61A or EX33A rod is preferred for welding. Maximum hardness is developed at 480oF in 24 hours.935oF for 2 hours or 895o . MIA .1000oF. t. strength at room temperatures and moderate longtime creep resistance at temperatures up to 480oF are required. where temperatures are below 200oF. KIQA . QE22A . Pages 4-23 through 4-43/(4-44 blank) deleted. . Typical Dust Collectors for Magnesium 4-22 Change 1 Paragraphs 4-52 through 4-95 deleted. Tables 4-12 through 4-31 deleted. 1-1A-9 Figure 4-1. Figures 4-2 through 4-4 deleted.T.O. Rockwell or Vickers Technique. 5-12. The useful strength of a metal is the maximum load which can be applied without permanent deformation.T. reference will be made to Table 5-1. MILITARY AND COMMERCIAL DESIGNATIONS. Pure titanium is commonly known as unalloyed. its uses are limited to end items not requiring the higher strengths obtained from the heat treatable alloys.O. joined. and readily dissolves carbon. Titanium is non-magnetic. and is usually a good indication of strength. titanium is a very active metal and readily dissolves carbon. 5-4. close visual inspection is required of all raw stock prior to any forming or machining operations. or scratching. formed. Electrical resistivities of titanium are similar to those of corrosion-resistant steel. 5-9. 5-7. All scratches. For this reason. Methods of distinguishing titanium alloys from other metals are simple and def inite. before fabrication. 5-3. It can be cast. and notching. Operations involving titanium requiring the application of heat in excess of 800oF must be performed in a closely controlled atmosphere by methods explained in future paragraphs. oxygen and nitrogen. Therefore. As previously pointed out. 5-2. by sanding and polishing. nicks and notches must be removed. To positively identify the various alloys. The modulus of elasticity is somewhat more than half that of the alloy steels and the coeff icient of expansion is less than half that of austenitic stainless steels. a chemical or spectographic analysis is necessary. This factor is commonly called yield strength. PHYSICAL PROPERTIES. 1-1A-9 SECTION V TITANIUM AND TITANIUM ALLOYS 5-1. diff iculties encountered in the fabrication of parts. Compared to other materials. The density of titanium is intermediate to aluminum and steel. All three elements tend to harden the metal. One quick method is to contact the titanium with a grinding wheel. MECHANICAL PROPERTIES. 5-5. nicking. indentation. the melting point of titanium is higher than that of any of the other construction materials currently in use. This variation in mechanical properties is the cause of 5-1 . in pounds per square inch. 5-6. This leaves a dark line similar in appearance to a pencil mark. GENERAL. Limited physical properties are available on the titanium compositions covered by existing military specif ications. Unalloyed titanium cannot be heat treated. This property can be measured accurately by the Brinell. The most pronounced effects are obtained from oxygen and nitrogen. For the selection of the proper class and form of stock required for a particular purpose. In the case of titanium the yield strength is the most important factor and is therefore used by industry to designate the various types of unalloyed titanium. Hardness is the resistance of a metal to plastic deformation by penetration. HARDNESS TESTING. 5-11. For this reason. Titanium and titanium alloys are highly susceptible to stress risers resulting from scratching. The hardness to be expected from the various alloys and unalloyed titanium is listed in Table 5-2. METHODS OF IDENTIFICATION. Also. and nitrogen. or any application of heat in excess of 800oF. 5-10. at which complete failure occurs. There are presently two military specif ications in existence (See Table 5-1) covering alloyed and unalloyed titanium in classes established to designate various chemical compositions. 5-13. TENSILE TESTING. Titanium is a very active metal. The nominal mechanical properties are listed in Table 5-2. oxygen. any heating process must be performed in a closely controlled atmosphere to prevent the absorption of oxygen and nitrogen to a point of brittleness. NON-DESTRUCTIVE TESTING. and machined with relative ease as compared to the various alloy grades. identif ication can be accomplished by moistening the titanium and marking the surface with a piece of glass. This results in a pure white trace ending in a brilliant white burst. heat treatment. CLASSIFICATION. Titanium is produced in pure form as well as in various alloys. The control of these elements causes considerable diff iculty in obtaining correct mechanical properties during the fabrication of titanium. oxygen and nitrogen having the most pronounced effect. The tensile strength of a metal is that load. 5-8. since the absorption of small amounts of oxygen or nitrogen makes vast changes in the characteristics of this metal during welding. COMP. Ti-75A A55. HA-1970. COMP. Strip Plate Forgings 70KS1 (A70.5Sn (A110AT) Sheet Strip. 0. MST-40. MST70 RS70. 2 MIL-T-9046 Type II. RS-40. MST 5AL2. 100A) Sheet Strip Plate Bars.T. Ti-75A. MST 55 RS55. COMP. Strip Plate Sheet. HA-1950. E A-110AT. A MIL-T-9047 Comp. B MIL-T-9046 Type I. A A70. NA2-7123B MIL-T-9046 Type I. NA2-7126G A70. T1-5AL2.O. HA5137. B MIL-T-9047 Comp. Plate Bars and Forgings 5AL-2. Strip Plate Sheet. COMP. COMP. MST 5AL-2. MST70 RS70. C MIL-T-9046 Type II. T1-65A.01 014. COMP. D MIL-T-9046 Type II. A A-40. STRIP PLATE Tubing Welded Tubing Seamless 55KS1 (A55.5Sn EL1 Sheet Strip Plate 4910 MIL-T-9046 Type II. Forgings and Forging Stock 4901 4921 4902 4941 4942 4900 MIL-T-9046 Type I. HA1940. 55A ALPHA TITANIUM ALLOY 5AL-2. HA5137.5Sn. COMP.5Sn. RS110C. Ti-5AL-2. C MIL-F-83142 Comp. 65A) Yield Sheet. Ti-55A A40. 75A) Yield 70KS1 (A70. NA2-7149A 4926 4966 4909 Bars and Forgings 5AL-SZr-5Sn Sheet.5Sn. HA-1970. Specification Cross Reference Titanium Alloys Comp/Alloy Designation Form/Commodity Specification Data AMS Military 1 Other 2 COMMERCIALLY PURE (UNALLOYED) 40KS1 (A-40 55A) YIELD SHEET. COMP. Strip Plate 4924 7AL-12Zr 7AL-2Cb-1Ta 5-2 Change 1 . 1-1A-9 Table 5-1. 3 MIL-T-9046 Type II. COMP. 1 MIL-T-9046 Type I.NA2-71269 A-110AT. RS110C.5Sn. COMP. COMP. RS110A. Strip. MST 6AL-4V.T. Ti-3AL 3MO-IV. RS120A.01002 MST 4AL-3MO-IV. Ti-13V-11C4-3AL 11. F MIL-T-9047 Comp. Strip Plate Forgings 4AL-3Mo-IV Sheet. MST 8Mn. Strip. 14 MIL-T-9047 Comp. B C110M. Plate (Solution and Pretreated) 6AL-4V (C120AV) Sheet. RS115. Plate Sheet.5 Mo-6Zr- MIL-T-9047 Comp. C C-120AV. 12 MIL-T-9046 Type III COMP. 5 4972 4973 BETA TITANIUM ALLOYS 13V-11Cr-3AL Forgings Bars and Forgings 13. HA6510. R120B. Plate Bars and Forgings Bars. LB0170-110 Change 1 5-3 .5V-11Cr-3AL (B120VCA) Plate. 13 4908 MIL-T-9046 Type III. COMP. A MIL-T-83142 Comp. MST 13V-11Cr-3AL. Plate 4912 4977 4917 MIL-F-83142 Comp. Strip. Ti-8Mn. TI-6AL-4V. Rings Forgings (Solution heat treated and stabilized) 4915 (Single ann’1) MIL-T-9046 Type II. 12 B-120VCA. LB-0170-104 4913 4911 MIL-T-9046 Type III.O. 1-1A-9 Comp/Alloy Designation Form/Commodity Specification Data AMS Military 1 Other 2 8AL-1MO-IV Sheet. 0. Sheet and Strips Solution Heat Treated Bars and Forgings Bars and Wire (Solution Heat Treated) 8Mn (C110M) Sheet. Strip. 6 C120AV. F 4956 C120AV. COMP. MST-6AL-4V. Specification Cross Reference Titanium Alloys . Welding Forgings 6AL-4VEL1 Sheet.O. B 4973 (Ann’1) 4979 (H. LB0170-110.) MIL-T-83142 Comp. 0. F MIL-T-9047 Comp.) Forgings 7AL-4Mo (C135MO) Sheet. D 4930 MIL-T-9047 Comp. HA-7146.Continued Comp/Alloy Designation Form/Commodity Specification Data AMS Military 1 Other 2 Bars and Forgings Bars and Forgings (Solution & Precipitation Heat Treated) Extrusions Wire.01037 4965 4935 4954 MIL-F-83142 COMP. Plate Bars and Forgings Forgings Wire. MST-6AL-4V. Plate Bars and Forgings 4970 (H. 7 MIL-F-83142 Comp. COMP. Strip. MST 7AL4MO. Ti-6AL-4V. 9 C135MO. TI-6AL-4V. 6 MIL-T-9046 Type III. HA6510. 9 MIL-T-9046 Type III. Welding (Extra low intertital environment controlled) 6AL-6V-2Sn Forgings Sheet. RS120A. LB0170-147 C120AV MIL-F-83142 Comp. COMP. RS 135. LB0170-122 5-4 .T.T. Plate Bars and Forgings 4928 MIL-T-9047 Comp.T. 1-1A-9 Table 5-1. Strip. Strip. HA6510. RS120A. E MIL-T-9046 COMP. 8 4918 MIL-T-9046 Type III. Ti-7AL-4MO. Strip.T. For designation beginning with LB or NA (example LB170-110 or NA2-7123B) NORTH AMERICAN AVIATION INC. 1-1A-9 Table 5-1.A-40) CRUCIBLE STEEL CO. For designation beginning with A. e. C (example . COMP.T. Validate any difference and assure that selected specif ication material(s) will comply with end item specif ication requirements before specifying or using. 2 Change 4 5-5 . B.O. f. For designation beginning with RS (example RS-40) REPUBLIC STEEL CO.Continued Comp/Alloy Designation Form/Commodity Specification Data AMS Military 1 Other 2 7AL-4Mo (C135MO) (Cont) 6AL-2SN4Zr-2Mo Forgings MIL-F-83142 Comp.) 4976 (Ann’1) MIL-T-9047 Comp. b. d. 13 MIL-T-9046 Type III. c. For designation beginning with T1 (example T1-8Mn) TITANIUM METAL CORP. The following manufactures names apply to designations listed under other: a. G 4979 (H. Specification Cross Reference Titanium Alloys .01015) CONVAIR OR GENERAL DYNAMICS CORP. 14 MISCELLANEOUS SPECIFICATIONS Heat Treatment of Titanium and Titanium Alloys 1 SAE-AMS-H81200 There may be controlled requirements applicable to some specif ications listed in the same alloy type or series. g. For designation beginning with HA (example HA-1940) HARVEY ALUMINUM CO. For designation beginning with 0. Plate Bars and Forgings 6AL-2Sn4Zr-6Mo Bars and Forgings MIL-T-9047 Comp. II Sheet. For designation beginning with MST (example MST-70) REACTIVE METAL CORP.0 (example 0. 5-6 Change 4 . inert atmospheres or vacuum shall be used as necessary to protect all parts (titanium or titanium alloy). inert atmosphere. 1-1A-9 5-14. FIRE DAMAGE. combusted gases. Heat Treatment of Titanium and Titanium Alloys. Additional Heat Treatment information is discussed in Section IX. an overtemperatured condition is indicated by the formation of an oxide coating and can be easily detected by a light green to white color. However. A majority of the titanium alloys can be effectively heat treated to strengthen. nitrogen and oxygen. the affected parts will be removed and replaced with serviceable parts. which comprise the furnace load to prevent reaction with the elements hydrogen. HEAT TREATMENT . alloys used on aerospace equipment. 5-16. However. For complete description of titanium heat treat requirements.T.O. Fire damage to titanium and titanium alloys becomes critical above 1000oF due to the absorption of oxygen and nitrogen from the air which causes surface hardening to a point of brittleness. protective atmosphere.GENERAL. The heating media for accomplishing the heat treatment can be air. will be the control document for heat treatment of titanium and titanium . etc. or vacuum furnace. protective. carbon. . refer to latest issue of SAE-AMS-H-81200. NOTE SAE-AMS-H-81200. 5-15.. If this indication is apparent following f ire damage to titanium aircraf t parts. anneal and stress relieve. 0 5.0 10.5SN) Comp B (5AL-2.2% Off set) 1000 psi Min Tensil Str (Ultimate min) 1000 psi MATERIAL TYPE MIL-T-9046 1/ TYPE I.0 170 125 8 5 10 10 10 155 145 160 160 160 170 160 170 170 170 5.2% Off set) 1000 psi Min Tensil Str (Ultimate min) 1000 psi Elong % in 2 in Rock well Hardness SOLUTION TREATED AND AGED Yield Str Tensil Elong % in 2 in ANNEALED CONDITION Yield Str (0. Comp A (Unalloyed 40 ksi) Comp B (Unalloyed 70 ksi) Comp C (Unalloyed 65 ksi) TYPE II. 4V) Class 7 (5AL.5Sn) Class 3 (3AL. B and C are classif ied as commerically pure. 15Cr.0 Not recommended C36 C36 C38 NOTE 1/ Comp A. 1-1A-9 5-7 .5Fe.5SnE11) Comp C (5AL-5Zr-5Sn) Comp D (7AL-23Zr) Comp E (7AL-2Cb-1Ta) Comp F (8AL-1Mo-IV) TYPE III. 4V) Class 6 (6AL. Nominal Mechanical Properties at Room Temperature SOLUTION TREATED CONDITION Elong % in 2 in Rock well Hardness Yield Str (0.0 8. Class 1 (Unalloyed) Class 2 (5AL. T.O.Table 5-2. Comp A (8Mn) Comp B (4AL-3Mo-IV) Comp C (6AL-4C) Comp D (6AL-4V-EL1) Comp E (6AL-6V-2Sn) Comp F (7AL-4Mo) TYPE IV. 2Mo) Class 5 (6AL.0 5. 5Cr) Class 4 (2Fe.5Mo) 40-65 70-95 55-80 110 95 110 120 110 135 110 115 120 120 140 135 120 70 110 130 120 120 130 135 50 80 65 120 100 120 130 115 145 120 125 130 130 150 145 125 80 115-120 140 130 130 140 145 20 15 18 10 8-10 10 10 10 8-10 10 10 8 10 10 10 10 15 10 10 15 8 10 10 B88 C23 B95 C35 C35 C35 C38 Not recommended 130 150 160 160 160 120 C23 C36 C36 C36 C40 C39 145 150 160 160 5 5 150 160 160 175 5. 2Cr. 2. 1.0 8. Comp A (5AL-2. 1. Comp A (13V-11Cr-3A1) MIL-T-9047. can only be hardened/strengthened by cold work. For the recommended soaking periods and temperatures see Table 5-3. the material shall be held within temperature range for suff icient time. For aging. for the necessary aging to take place and to insure that specif ied properties are developed. 5-22. 5-20. 5-19. and inert gas furnaces which control the atmosphere to 1% or less of oxygen and nitrogen combined. NOTE Avoid direct f lame impengement to prevent severe localized oxidation and contamination. Quench delay time begins when furnace doors begin to open and ends when the last corner of the load is immersed. etc. Also avoid contact with scale or dirt. CAUTION Cracked ammonia or hydrogen shall not be used as a protective atmosphere for titanium and titanium alloys in any heat treating operations. Excessive heat treat soaking periods ahall be avoided to prevent diffusion of oxygen hydrogen and nitrogen. Quenching from solution heat treating for temperature wrought titanium alloys.091 nominal thickness and 7 seconds for 0. This type of embrittlement. Wrought alloys should be fully quenched by air cooling from the aging temperature. NOTE All heat treating operations shall be performed uniformly on the whole part. For general use. This is associated with a decrease in impact strength at temperatures below 200oF and a shif t in the temperature range where the change from ductile to brittle occurs. which is similar to the embrittlement of steel. The same applies for stress relieving except the time at temperature will depend on section size plus amount of cold work hardening present in the material. but at high temperatures where surface oxidation (above 1000oF) is signif icant. welding. 5-17. only becomes evident above a certain strength level. or unalloyed titanium. With alpha-beta alloys. With extremely large loads or long lengths quench delay may be exceeded if performance test indicates that all parts comply with specif ication requirements. 5-18. The quenching baths shall be located and arranged to permit rapid transfer of the load from the furnace to the bath. The brittle layer must be removed by mechanical or chemical means prior to forming or application in stressed components. Air-chamber furnaces are more f lexible and economical for large volumes of work and for low temperature heat treatments. The water shall be of suff icient volume or circulation or both so that the water temperature upon completion of the quenching operation will not be more than 100oF. Furnaces which have given satisiactory results are vacuum furnaces capable of supplying pressures of one micron or less. HYDROGEN EMBRITTLEMENT. AGING AND STRESS RELIEVING. work hardening. Solution heat treating and aging the alpha-beta alloys to high strength levels increases sensitivity to hydrogen embrittlement. a muff le furnace utilizing external heating gives more protection. For recommended temperatures and times see Table 5-3. Oxygen and nitrogen diffusion will take the form of a hard brittle surface layer which is diff icult to distinguish from the base metal. Stress relief and annealing are the only heat treatments applicable to these alloys. 5-23. shall be by total immersion in water. The soaking period for heat treatment of titanium alloys shall be the minimum necesaary to develop the required mechanical properties. Scaling (oxidation) of titanium and titanium alloys starts at about 900oF. especially if gas heated. embrittlement is found at slow speeds of testing and under constant or ‘‘sustained’’ loads as demonstrated by tests on notched specimens. Heating to temperatures 5-8 . Maximum quench delay for immersion-type quenching shall be 4 seconds for wrought alloys up to 0. 5-24. 5-21. The commercially pure. electric furnaces are preferred since heating can be accomplished internally or externally with a minimum of contamination. Hydrogen is readily absorbed from pickling.091 and over. The minimum soaking period (when unknown) shall be determined by teat samples run prior to heat treating the f iniahed material or part. depending on section size. The material is also quenched by air cooling from the stress relieving temperature. Alternately direct resistance heating may be used where extremely short heat up cycle on nearly f inished parts is required to minimize surface oxidation.T. except for alloy 3AL-13V-11Cr less than 2 inches thick. which maybe air cooled.. Light scaling which forms from exposure to temperatures up to 1000oF has little or no detrimental effect on mechanical properties. Hydrogen embrittlement is a major problem with titanium and titanium alloys. Hydrogen embrittlement in the basically pure and alpha alloys is evident by a reduction in ductility and a slight increase in strength.O. These processes of heat treatment are employed to remove residual stress resulting from grinding. etc. never on a portion thereof. 1-1A-9 above 1000oF under oxidizing conditions results in severe surface scaling as well as diffusion of oxygen. cleaning and scale removal solution at room temperature and from the atmosphere at elevated temperatures. 25Fe-2. 1-1A-9 3A1-13V-11Cr 12/ 1A1-8V-5Fe 13/ 900-1000 1000-1100 1/4-60 1/4-60 1430-1470 1200-1300 1/4-1 1/2-1 1/2 1375-1425 1375-1470 30-90 15-60 880-920 925-1000 2-60 1-3 5-9 . Stress Relief and Annealing Temperatures and Times STRESS RELIEF TEMP oF MATERIAL STRESS RELIEF TIME HOURS ANNEALING TEMP oF ANNEALING TIME HOURS HEAT TREATING TEMP oF H.75Cr 7/ 8/ 5A1-1.5Sn 5A1-5Zr-5Sn 7A1-12Zr 7A1-2Cb-1Ta 2/ 8A1-1Mo-1V 1/ Alpha-Beta Alloys 8Mn 3/ 1000-1100 900 800 1/2-1 2-4 8 1000-1300 1 1/2-2 Hardened only by cold work 1080-1125 1100-1300 1275-1325 1000-1200 1285-1315 1-2 1/2-3/4 1/2-3/4 1/3-3/4 1/2 1335-1550 1335-1550 1630-1670 1630-1670 1430-1470 1/4-4 1/4-1 1/4-1 1/4-1 8 Hardened only by cold work 950-1000 800-1000 960-990 --- 1/2-2 1/2-15 3-5 --1/2-2 1/2 1/2-8 1/2-2 1/2-2 1/2-50 1/2-3 1/2-8 1/2-50 1250-1300 1175-1200 1360-1400 1250-1350 1250-1300 1225-1250 1425-1650 1180-1200 1275-1550 1300-1500 1425-1450 1275-1550 1 1/2 1/16-1/2 1/2-1 1/2 2-24 2-4 1/3-2 4-24 1/2-8 2-3 1-8 1/2-8 1420-1480 1620-1660 1350-1550 1650-1700 1670-1730 1575-1675 1675-1275 1650-1750 1360-1400 Not recommended 5-25 10-30 Not recommended 60-120 10-20 10-60 30-120 5-25 30-60 30-90 875-925 910-940 900-1000 950-1050 960-990 875-1175 975-1175 6-10 6-12 6-10 4-8 4-6 4-8 4-8 900-950 960-990 4-6 3-5 2Fe-2Cr-2Mo 4/ 2. B and C Alpha Alloys 5A1-2.5V 4A1-4Mn 4A1-3Mo-1V 6/ 7/ 5/ 1250-1350 900-1100 1000-1100 1100-1200 900-1200 1000-1100 900-1300 900-1200 5A1-1.T. SOAKING TIME MINUTES 14/ AGING TEMP oF AGING SOAKING TIME HOURS Unalloyed Commercially Pure Comp A. Heat Treat.5A1-16V 3A1-2.5Fe-4Cr-1.O.Table 5-3.2Mo 9/ 6A1-4V 7/ 10/ 5/ 6A1-6V-2Sn 9/ 15/ 7A1-4Mo 11/ 6A1-4V (low o) 10/ 5/ Beta Alloy Not recommended T. For bar and forging anneal.T. also. 5/ For 100 % stress relief. Bar and Forgings: Duplex anneal 1650-1850.15 hours. heat treat at 1000oF for 15 minutes. 14/ Longer soaking times may be necessary for specif ic forgings.O. Air cool may be used for lower ductility requirements. Stress relieve at temperature cited during aging. furnace cool at a rate of 50oF per hour maximum to 800oF. 8/ Anneal sheet at temperature for 20 minutes. air cool. heat at 1300oF-1500oF for 1/2-2 hours. 7/ Slow cool to 1000o-1050oF maximum from upper annealing temperature.5-10 MATERIAL T. Triplex anneal. 1000oF . For bar hold at anneal temperature 2 hours. + 1375.5 hours. heat at 1275o-1325oF for 2 hours. 12/ Solution heat treatment recommended for annealing.1 hour and 950oF . For hydrogen removal by vacuum annealing. 1 hour.1/2 hour. 15/ Age at 1050o-1150oF air cool for best combination of mechanical properties and termal stability.Continued STRESS RELIEF TEMP oF STRESS RELIEF TIME HOURS ANNEALING TEMP oF ANNEALING TIME HOURS HEAT TREATING TEMP oF H. 11/ Furnace cool from annealing temp (1425o-1450oF) to 1000o-1050oF maximum at 300oF per hour (maximum) for maximum formability. Mill anneal + 1435oF.5 hours.50 hours or 1200oF .5 hours or 1100oF . Soaking time shall be measured from the time all furnace control instruments indicate recovery to the required (minimum) process range. 6/ Furnace cool at 300oF maximum from anneal temperature for maximum formability. Stress Relief and Annealing Temperatures and Times . 850oF . 10/ For sheet anneal. 9/ Air cool from annealing temperature. 1-1A-9 Table 5-3. 5 minutes air cool. If aging not employed. formability may be improved by holding at annealing temperature 24 hours. .1/2 hour. SOAKING TIME MINUTES 14/ AGING TEMP oF AGING SOAKING TIME HOURS 1/ Sheet: Regular anneal furnace cool Duplex anneal. For maximum creep properties (af ter lowering from upper annealing) temperature hold at 1050o for 24 hours. Aging time will depend on strength level required/desired. heat 1300o-1350oF. at 900oF . then furnace cool to 1100oF maximum. 15 minutes air cool. 4/ Stress relief may be accomplished at 800oF . For 50 % relief. 3/ Anneal furncee cool at 300oF per hour maximum to 1000oF to 1050oF. Shorter times are satisfactory when soak time is accurately determined by thermocouples attached to the load. 13/ Furance cool from upper anneallng temperature at 300oF per hour maximum to 900oF. 2/ Bar Duplex anneal: Mill anneal + 1000o-1200oF. Mill anneal + 1850oF. 8-24 hours air cool. 1/2-6 hours air cool. 15 minutes air cool. Heat Treat. 1 hour air cool + 1000o-1100oF. 1000oF . Usually a stress relief operation at 1000oF for 20 minutes is necessary. Deep draw forming should not be attempted unless adequate equipment and facilities are available.T. requires that pressure plates and dies be made somewhat thicker than in normal practice. 5-27. ductile iron or laminated steel dies are usually necessary. Actual practice may reveal that smaller bend radii can be used. This operation is performed at room temperature and should be done at a very slow rate. Many parts can be formed at room temperature on the hydropress if f lange clips. The forming of material requiring tight bends or small radii necessitates the application of heat in the range of 500oF. it provides additional rigidity for forming. STRETCH FORMING. loading until plastic deformation begins. This extra pad of rubber serves two purposes: First. Z-sections and channels and to stretch form skins so that they will f it the contour of the airplane fuselage. 1-1A-9 5-25. Tooling for hydropress form blocks. FORMING SHEET METAL-GENERAL. BENDING. DRAW FORMING. If long runs are anticipated. hat sections. The heat should be applied for only short periods of time to avoid excessive oxygen and nitrogen contamination which causes embrittlement. Drop-hammer forming of titanium has been very successful and has been accomplished both at room and at elevated temperatures. if elevated temperature forming is to be used. The press is then closed. All blanks for stretch-forming should have the edges polished to remove any notch effects. a f inished part requiring no hand work is obtained. then a restrike operation. it is recommended that form blocks be made from a good grade of hot-work tool steel due to the galling action of titanium at elevated temperatures. Spring back is equivalent to that of 1/4 hard 18-8 stainless steel. HYDRAULIC PRESS FORMING. For this procedure. the rubber pad envelops the form block forcing the sheet metal blank to conform to its contour. 5-26. 5-11 . stress-relieve at 1000oF for 20 minutes. 5-29. wedges and hinge-type dies are used. As the ram is lowered. the best results have been obtained by warning the female die to a temperature of 200o to 300oF to remove the chill and heating the blank to a temperature of 800o 1000oF for 10 to 15 minutes. 5-32. DROP-HAMMER FORMING. and lightening holes. then a rubber pad 70 to 80 Durometer hardness is placed on top. The forming of the unalloyed titantum can be accomplished at room temperature using approximately the same procedures as those extablished for 18-8 stainless steel. Stretch forming has been used on titanium primarily to bend angles.O.025 inch of sheared edges should be removed. This will require that facilities be maintained for heating and controlling temperatures of the blanks to be formed and the dies used in the forming operation. The current equipment available was designed for material of uniform quality and considerable work is required for adaptation to form titanium. 5-30. Approximately 0. In most instances. The part is then struck and set in the die. When cold forming is employed. The basic diff iculties encountered are sheet thickness. it is usually desirable to partially form the parts. 5-31. The above factors combined with high yield strength. The factors which require control are the compensation for springback and the bend radii. For approximate cold bend radii of sheet titanium see Table 5-4. direction of grain f low and f latness. This type of forming is accomplished by gripping the section to be formed in knurled jaws. Hot forming for severely contoured parts or when only low-forming pressures are available is accomplished between 600oF and 800oF. the form block is heated to the required temperature. 5-28. Springback is comparable to that of hard stainless steel when formed at room temperature. it protects the press-contained rubber from the hot form block. FABRICATION. then wrapping the part around a female die. A male form block is set on the lower press platen and the blank held in place on the block by locating pins. then f inish form. high tensile strength and low uniform elongation of commercial titanium alloys makes forming diff icult. The bend radii will depend on the type of material or alloy and whether forming is accomplished hot or cold. In drop-hammer forming. 5-33. If long runs are to be made. Rubber pad hydropress forming can be accomplished either hot or cold depending on the type tooling employed and the press pressures used. Straight-Edge Bending of titanium using power brake on hand forming equipment can be accomplished to a limited degree using the methods developed for stainless steel. and second. beads. the blank positioned and covered with powdered or shredded asbestos. property variations. Kirksite is satisfactory for male and female dies where only a few parts are required. A press-contained rubber pad (45 to 55 Shore Durometer hardness and about 8 inches thick) is located over the form block and blank. This type of forming is used on parts that are predominately f lat and have f langes. 1Mo-1V) Type III .160 bend radii (minimum).025 inch of the sheared.125 inch in thickness have been sheared on 1/2 inch capacity f lat bed shears designed for steel.070 to 0. blanked.5T 5T -4.5T 3T 3.187 2T 2. Materials up to 0. Cold joggling . Type II.5T 4. Pages 5-13 through 5-14 deleted. and the alloys compare to 1/2 hard 18-8 stainless steel. Joggle run-out should be the determining factors whether joggles are formed hot or cold. 5-34. Joggles should be formed hot where a ratio of joggle run-out to joggle depth is less than 8. 1-1A-9 Table 5-4.5T 4. JOGGLING.5T 3T 2.070 & under thickness over 0.5T 5T 5T -5T 3. Before any forming or other operations are performed 0.040 = 0. The joggle die corner radius should not be less than 3T-8T. the shear designer should be consulted.O. b. BLANKING AND SHEARING.Commercially Pure Comp A (unalloyed 40.5T 4.040 MIL-T-9046. These operations compare to those of 18-8 stainless steel in the 1/4 hard condition for commercially pure.000 psi) Comp C (unalloyed 55. Composition A. If this capacity is to be exceeded. Minimum joggle run-outs should be as follows: Hot joggling .Alpha Titanium Alloy Comp A (5AL02. would require a bend radii of 4 x 0. or nibbed edges should be removed to prevent stress risers that will cause a tear in the part during forming operations.four times the joggle depth.5Sn) Comp B (5AL-2.eight times the joggle depth. Paragraphs 5-38 through 5-42 deleted.5T 4T 5T 5T --3-5T 1/ T = Thickness of material.Alpha-Beta Comp A (8Mn) Comp B (4AL-3Mo-1V) Comp C (6AL-4V) Comp D (6AL-4V) Comp E (6AL-6V-2Sn) Comp F (7AL-4Mo) Type IV .5T 2T 4T 4T 4. 5-12 Change 2 . Recommended Minimum CCLD Bend Radii TYPE/COMP Type I . 5-37. 5-35. sawed. The force required for titanium and its alloys is greater and the dies wear faster.000 psi) Comp B (unalloyed 70.1.T.5T --3T 2. Joggling of titanium can be accomplished without any particular diff iculty provided the following rules are adhered to: a.Beta Comp A (13V-11Cr-3AL) MINIMUM BEND RADIUS (90 DEGREE BEND) 1/ 0. c. 5-36. Deleted.5T 4.5Sn EL1) Comp C (5AL-5Zr-5Sn) Comp D (7AL-12Zr) Comp E (7AL-2Cb-1Ta) Comp F (8AL. Example: A piece of 0.000 psi) Type II . by precoating with a thin f ilm of silver.T. Change 1 5-15/(5-16 blank) . 5-45. Deleted. dimpling can be accomplished at temperatures of 500oF to 700oF. Deleted. 5-44. the above mentioned method will probably be replaced in most cases with rivets of the high shear series. The resultant f ilm should be made wet with either a 60% tin-40% lead or a 50%-50% tin and lead solder. and shear rivet NAS-2406 through NAS-2412. Riveting of titanium can be accomplished using conventional equipment with rivets manufactured from commercially pure material. however. When it is necessary to have f lush-head rivets. This can be accomplished by heating the chloride salts-coated titanium in an atmosphere controlled furnace as previously mentioned in paragraph 5-18. RIVETING. it is important that the time and temperature be held to a minimum. pin rivets such as NAS1806 through NAS1816. SOLDERING. 5-50. 1-1A-9 5-43. 5-49. 5-46. Table 5-5 deleted. it is necessary to take precautions to avoid galvanic corrosion when titanium is riveted to other metals. Due to diff iculties involved. i.. Limited information is available on soldering.O. Better results can be obtained by using the squeeze method rather than the rivet gun and bucking bar. Other types of rivets such as high strength aluminum. 5-47. copper or tin from their chloride salts.e. As with other metals. Deleted. This can be accomplished by coating the titanium with zinc chromate primer Specif ication MIL-P-8585. Since the deposited f ilm may dissolve in the liquid solder and dewet the surface. stainless steel and monel are also used to join titanium. tension rivet NAS-2006 through NAS-2010. The driving time is increased about 65% over that required for high strength aluminum rivets. 5-48. It is possible to successfully solder titanium where little strength is required. Deleted. the rivet holes require close tolerances to insure good gripping. . MACHINING AND GRINDING. and f inish. Point angle. 118o and 140o should be tried on large jobs to determine the angle that will give the best result. the piece being cut will be pulled into the cutter. so the following information is only intended as a guide. but 90o. For tool grinding information see Table 5-9.. See Table 5-8 for recommended speed and feeds. 5-62. 5-59. 0. Commercially pure and alloy titanium is not diff icult to turn.005 to 0. may be used when carbide is not available. carbide tools may give better results when dry. use of a good cutting f luid that emphasizes cooling rather than lubrication. Tables 5-6 and 5-7 show suggested turning speeds. unalloyed titanium machines similarly to 18-8 stainless steel.O. Considering the type of tool which is required in milling operations. and the results are not as satisfactory with carbide as they are with castalloy tools. This may damage the cutter or the work piece. The cutter machines the thinnest portion of the chip as it leaves the cut. Additional information on drills may be obtained from NAS907. 5-63. 5-64. As with other materials.T. the use of sharp tools is very important. The cutting speed should be 50 to 60 FPM for the pure grade of titanium and 30 to 50 FPM for alloy grades. Commercially pure. MACHINING. sharp and proper tools. slow speeds and heavy feeds. 5-60. Carbide tools such as metal carbides C91 and Carboloy 44A and other similar types give the best results for turning titanium. Low speeds and heavy positive feeds are required. The same water-base cutting f luids used for turning are recommended for milling. 5-65. The recommended cutting f luids are waterbase cutting f luids such as soluble oils or chemical type f luids. That is. This will reduce the danger of chipping the tool. DRILLING. This damages the cutting edge and the tool fails rapidly. Lantung. For effective milling. The diff iculty encountered is that chips remain tightly welded to the cutter’s edge at the end of cut or during the portion of the revolution that it does not cut. however. 5-53. and for face milling the teeth should emerge from the cut in the same direction that the work is fed. Variations in actual practice will depend on the type of work. etc. 5-61. 1-1A-9 5-51.002 to 0. All work should be accomplished with live centers since galling or seizing will occur on dead centers. One method that can be utilized to relieve this diff iculty to a great extent is climb milling. This should be done since the cutter usually fails because of chipping. Rexalloy. Thus. it can be readily seen that this type of machining is more diff icult than turning. the drill is removed from the hole at intervals to remove the chips.009 inch for 1/4 to 1/2 inch diameter drills. the area of contact between chip and tool is at a minimum when the chip is removed at the start of the next cutting portion of the revolution. Cast alloy tools such as Stellite. MILLING. Sliding contact. The machine used for climb milling should be in good condition because if there is any lost motion in the feed mechanism of the table. tool angles and feeds. The unsupported portion of the drill should be as short as possible to provide maximum rigidity and to prevent drill running. or when the high speed steels. 5-58. TURNING. The basic requirements are: rigid machine setups. and riding of the tool on the work must be avoided. 5-57.005 inch for smaller drills. To select the appropriate tool material it is advisable to try both cast alloy and carbide tools to determine the better of the two for large milling jobs. 5-56. Drilling of titanium can be accomplished successfully with ordinary high speed steel drills. 5-52. All holes should be drilled without pilot holes if possible. the work feed should move in the same direction as the cutting teeth. Tool sharpness is again emphasized because a nick or a seized chip on a tool increases temperature and will cause rapid tool failures. 5-55. Helix angle 28o to 35o and lip relief 10o. The cutting f luids recommended are sulfurized and chlorinated coolants for drills with diameters of less than 1/4 inch and mixtures of mineral oil or soluble oil with water for hole sizes larger than 1/4 inch diameter. 90o for drills 1/4 inch diameter and larger and 140o for drills 1/8 inch diameter or less. As the cutter starts the next machining portion the chips are knocked off. Since titanium has a tendency to gall and seize on other metals. In drilling deep holes. Cobalt-type high speed steels give the best results of the many types available. 5-17 . 5-54. The increase in cutting speeds (20 to 30%) possible by using carbide rather than cast (all alloy tools) does not always compensate for the additional tool grinding cost. are not satisfactory. Feeds should be 0. intermittent drilling is recommended. but the alloy grades are somewhat harder. equipment. chip removal is one of the principal problems and the appearance of the chip is an indication of the sharpness and correct grinding of the drill. 5 Mo MILITARY MIL-T-9047C Class 1 CUTTING SPEED FPM 250-300 150-170 170-200 120-160 30-60 50-80 FEED. 4V 4A1. 1.040 inch 5o . 1.008-0.5 Cr.5 Fe 1.5Fe. 4. 4V 4A1.004-0. Tool Angles for Alloys TOOL ANGLES Back Rake Side Rake Side Cutting Edge Angle End Cutting Edge Angle Relief Nose Radius 0o 6 o CARBIDE HIGH SPEED STEEL 5o Pos 5 .007 0.5Cr 1.003-0.O. and 6 Class 7 110-150 20-40 40-70 0.004-0. 1.15o 5o 5o 0.004-0.005 inch to 0. 4.15o 5o .010 TOOL MATERIAL Carbide Hi-Speed Steel Cast Allloy Carbide Bi-Speed Steel Cast Alloy Classes 2.008 0.006 0.005-0.004-0. 2. 2Cr. Table 5-7. 6A1. 5Cr 2Fe.004-0.004-0.008 0.004-0. 2Mo. 5. 1. Speeds and Feeds for Milling TYPE Unalloyed 70.000 PSI 5A1. 3. 4Mn 5A1. 3.T.010 0.008 Carbide Cast Alloy 5-18 .015 0. Turning Speeds for Titanium Alloys TYPE Unalloyed 70.5Mo MILITARY MIL-T-9047C Class 1 Class 2.012 0.005-0.020 0. 4Mn 5A1.15o 5o 5o 0.15 o o CAST ALLOY 5 Pos 5o .004-0.010 inch 6o 6o 6o 0.010-0. 5CR 2Fe.008 0.000 PSI 5A1. Cr 2 Mo 6A1.5Sn 3A1.008 Carbide Hi-Speed Steel Cast Alloy NOTE: For cutting forging skin speed 1/4 of that above and feeds about 1/2. 1-1A-9 Table 5-6. in/rev 0.010 inch Table 5-8. 5. 6 MILLING SPEED FPM 160-180 120-140 80-120 80-100 FEED.005-0.5 Sn 3A1. IPT -IN INCHES 0.008 0. 2.008 TOOL MATERIAL Carbide Cast Alloy Carbide Cast Alloy Class 7 70-110 70-90 0.004-0.007 0. sulfurized mineral. 5-69. Grinding of titanium is different from grinding steel in that the abrasive grain of the wheel wears or is dissolved by a surface reaction.008 inch are satisfactory. 1500-2000 SFPM and table feeds of 400 to 500 inches per minute with down feed of 0. Cutting f luid.05 inch cross feed for highest grinding ratios. diff iculties involved can be minimized by reducing the thread to 55 or 65% from the standard 78%. 1-1A-9 Table 5-9. Cutting speed: 40 to 50 FPM for unalloyed and 20 to 30 FPM for the alloy grades. A straight-f luted reamer can be used. the hole to be reamed should be drilled with a sharp drill. Specif ication VV-O283. lower wheel speeds and the use of aluminum oxide or sof t bonded silicone carbide wheels employing wet grinding methods are recommended. Angles for Tool Grinding ANGLES Axial Rake Radial Rake Corner Angle End Cutting Edge Angle Relief CAST ALLOY TOOL 0o 0o 30o 6o 12o CARBIDE TOOL 0o 0o 60o 6o 6-10o c.005 to 0. In the attempt to tap titanium. 3 f luted in sizes greater than 1/4-20. cutting. The removal of larger amounts lessens the degree of concentricity. Due to the galling and seizing that are characteristic of titanium. smaller amounts should be removed. Grade 1. 5-67. Recommended wheel speeds are. 2 f luted in sizes 1/4-20 or 1ess. TAPPING. however. GRINDING. 5-19/(5-20 blank) . b. REAMING. Active cutting oil such as oil. The following are procedures and material recommended for tapping titanium: a.001 inch maximum per pass and using 0. Another problem will be the smear of titanium.T.O. 5-66. Feeds should increase in proportion to the size of the hole. Speeds of 40-200 FPM and feeds of 0. Power equipment should be used when possible and a hole to be tapped should be drilled with a sharp drill to prevent excessive hardening of the hole wall. Chip removal is one of the problems that will require considerable attention in an effort to tap titanium. Build up from smear will cause the tap to freeze or bind in the hole. These problems can be alleviated to some extent by the use of an active cutting f luid such as sulphurized and chlorinated oil. tapping is one of the more diff icult machining operations. As with tapping operations. 5-68. but spiral-f luted reamers with carbide tips usually produce the best results. Preparation of the hole to be reamed and the type of reamer used is the keynote to successful reaming operations. 5-70. The essential requirements for grinding are the selection and use of grinding f luids and abrasive wheels. Type of Tap: Gun or spiral point. rather than wheel wear which is caused by breakage. If the degree of concentricity is an important factor. these factors depend on the size of the hole. To overcome this problem. . corrosion resistance. ALUMINUM . The two principal copper base alloys are brass and bronze. WROUGHT-COPPER-BERYLLIUM ALLOYS.Added to copper principally as a deoxidizer and in some bronzes to improve spring properties. BERYLLIUM .O. hot working. These alloys are of high strength and corrosion resistance. 6-5. Table 6-3 below gives a list of typical stress relief treatments commonly used in industry. During production and fabrication.Added to copper for higher strength without loss of ductility. containing zinc and tin respectively. and precipitation hardening. The temperatures commonly used for heating. and should be used as representing average stress relieving temperatures. 6-4. ductile and corrosion resistant. 6-2. Berryllium-coppers are widely used for tools where nonsparking qualities are desired. 6-1 . The beryllium copper alloys are frequently used due to their ability to respond to precipitation or age hardening treatments and other benef icial characteristics. malleable.Added to copper in amounts up to 1% to form a machinable. It is added to brasses or bronzes in amounts of 0. HEAT TREATMENT AND NOT WORKING TEMPERATURE OF COPPER ALLOYS. 6-9. MACHINING COPPER AND COPPER ALLOYS.90%.Added to copper along with aluminum in some aluminum bronzes and with manganese in some manganese bronzes. Free cutting brass is one of the most easily machined metals and serves as a standard for machinability ratings of copper alloys. . STRESS RELIEF OF COPPER ALLOYS. They are ductile. hot working and annealing af ter cold working are given in table 6-2. Most of the commercial coppers are ref ined to a purity of 99. stress relief for solution treatment. high strength hardness. and has an electrical conductivity of 20%. Small amounts are used as deoxidizers.Added to copper to form a series of alloys known as bronzes. CHEMICAL COMPOSITION. IRON . corrosion resistant and have colors ranging from pink to yellow.Added to copper to form a series of age hardenable alloys. NICKEL . This table is listed in terms of chemical composition percents.T. Bronzes are a quality spring material. copper alloys may be heated for homogenizing. it is the strongest of the copper base alloys 6-8. minimum copper plus silver. Some of the characteristics are. TIN .Added to copper as a predominating alloy element to form a series known as aluminum bronzes. COPPER AND COPPER BASE ALLOYS. with the corresponding specif ication and common trade names.The chemical composition of the copper alloys (listed by commercial trade name) is listed in table 6-1.Added to copper to form the copper silicon series having high corrosion resistance combined with strength and superior welding qualities. COPPER ALLOYING ELEMENTS. good electrical and thermal conductivity. PHOSPHOROUS . They have excellent corrosion resistance. In the fully treated condition. 6-3. Alloy designations for wrought copper and copper alloys are listed in table 6-1. good wear resistance. MANGANESE . non-magnetic qualities and very good fatigue strength. as the major alloying element. NOTE Additional Heat Treatment information is discussed in Section IX.Added to copper to form a series of alloys known as brasses. LEAD . 1-1A-9 SECTION VI COPPER AND COPPER BASE ALLOYS 6-1. and are strong. high-conductivity copper rod. SILICON .Added primarily as a desulfurizing and de-gassifying element for alloys containing nickel. ZINC . The following table gives the machinability ratings and recommended speeds and feeds for use with high speed steel tools. 6-6.5 to 4% to improve machinability and in the range of 2 -4% to improve bearing properties. 6-10. 6-7. Class FS-RCu-1 QQ-W-343 WW-T-799 QQ-C-502 QQ-C-825 QQ-C-502 QQ-C-825 QQ-A-673. 102 MIL-W-85C MIL-W-6712A Oxygen free copper.O. comp 1 QQ-W-321. Electrolyte Tough pitch copper. 104 105 110 Oxygen free with silver. 95% Commercial bronze.T. 101 SPECIFICATION FEDERAL QQ-A-673. 128 130 170 172 210 220 230 Fire refined tough pitch with silver. Fire refined tough pitch with silver. comp 2 QQ-B-613. Beryllium Copper Gilding. Chemical Composition by Trade Name COPPER ALLOY NO. comp 4 QQ-W-321 comp 3 WW-P-351 Grade A WW-T-791 Grade 1 MIL-W-85C MIL-W-6712 MIL-W-3318 MIL-W-6712 MILITARY MIL-W-85C TRADE NAME Oxygen free certif ied copper. Type I QQ-C-502 QQ-C-825 QQ-C-576 QQ-C-502 QQ-C-576 QQ-C-502 QQ-C-576 QQ-C-530 QQ-C-533 QQ-W-321. comp 4 QQ-B-626. type II QQ-C-502 QQ-C-576 QQ-W-343 WW-P-377 QQ-A-673 Type II QQ-C-502 QQ-C-825 QQ-C-576 QQ-R-571. 85% 6-2 . Oxygen free with silver. 1-1A-9 Table 6-1. 90% Red Brass. T. 65% (rod and wire) 274 Yellow brass 63% 6-3 . 66% (Sheet) 268 270 Yellow brass. 240 SPECIFICATION FEDERAL QQ-B-591 QQ-B-613 comp 3 QQ-B-626 comp 3 QQ-B-650 comp D QQ-W-321 comp 4 QQ-B-613 comp 2 and 11 QQ-B-626 comp 2 and 11 QQ-B-650 comp C QQ-W-321 comp 6 MILITARY TRADE NAME Low Brass.O. 80% JAN-W-472 *MIL-S-22499 MIL-T-6945 comp II MIL-T-20219 Cartridge brass. 1-1A-9 Table 6-1. 70% 260 *Laminated Shim Stock 261 262 Same as 260 QQ-B-613 comp 11 QQ-B-626 comp 11 QQ-B-613 comp 1 and 11 QQ-B-626 comp 1 and 11 QQ-B-613 comp 11 QQ-B-626 comp 11 QQ-W-321 comp 7 QQ-B-613 comp 11 QQ-B-626 comp 11 QQ-W-321 comp 8 Yellow brass. Chemical Composition by Trade Name .Continued COPPER ALLOY NO. Chemical Composition by Trade Name . Class FS-RW-1 QQ-W-343 WW-P-377 QQ-C-502 QQ-C-825 QQ-C-576 QQ-W-343 QQ-C-502 QQ-C-825 QQ-C-576 QQ-C-502 QQ-C-825 QQ-C-576 QQ-C-502 QQ-C-576 WW-P-377 WW-T-797 WW-T-799 MIL-W-85C Electrolytic Touch pitch anneal resist copper MIL-T-6945 comp III MILITARY TRADE NAME Muntz metal.T. 60% 298 330 Brazing Alloy Low leaded brass 331 110 111 114 Tough pitch with silver 116 Tough pitch with silver 120 Phosphorous deoxidized low residual phosphorus copper 6-4 .Continued COPPER ALLOY NO. 280 SPECIFICATION FEDERAL QQ-B-613 comp 11 QQ-B-626 comp 11 WW-P-351 Grade C WW-T-791 Grade 3 QQ-B-650 comp A QQ-B-613 comp 11 QQ-B-626 Comp 11 WW-P-351 Grade B WW-T-791 Grade 2 QQ-B-613 comp 11 QQ-B-626 comp 11 QQ-R-571.O. 1-1A-9 Table 6-1. Chemical Composition by Trade Name .T. 121 122 SPECIFICATION FEDERAL QQ-C-502 QQ-C-576 QQ-A-674. 1-1A-9 Table 6-1.O.Continued COPPER ALLOY NO. Type III QQ-C-502 QQ-C-576 WW-P-377 WW-T-797 QQ-C-502 QQ-C-576 QQ-C-502 QQ-C-576 QQ-C-502 QQ-C-576 QQ-B-613 comp 11 QQ-B-626 comp 11 QQ-B-613 comp 11 QQ-B-626 comp 11 QQ-B-613 comp 11 QQ-B-626 comp 11 QQ-B-613 comp 11 and 24 QQ-B-626 comp 11 and 24 QQ-B-613 comp 11 QQ-B-626 comp 11 QQ-B-613 comp 11 QQ-B-626 comp 11 QQ-B-613 comp 11 QQ-B-626 comp 11 Fire refined tough pitch copper Fire refined tough pitch with silver High leaded brass Phosphorus deoxidized high residual phosphorus copper MILITARY TRADE NAME 122 123 125 127 332 340 Medium leaded brass 641/2% 335 Low leaded brass 342 High leaded brass 641/2% 344 347 348 6-5 . Phosphorized Naval Brass. Antimonial Admiralty.O. Arsenical Admiralty. arsenical MILITARY TRADE NAME Medium leaded brass 62% 353 Extra High leaded brass 356 Extra High leaded brass 370 Free cutting muntz metal 360 Free cutting brass 377 443 444 445 462 Forging brass Admiralty. 631/2% 464 Naval Brass 465 6-6 . 1-1A-9 Table 6-1.Continued COPPER ALLOY NO. Chemical Composition by Trade Name . 350 SPECIFICATION FEDERAL QQ-B-613 comp 11 QQ-B-626 comp 11 QQ-B-613 comp 11 QQ-B-626 comp 11 QQ-B-613 comp 11 QQ-B-626 comp 11 and 22 QQ-B-613 comp 11 QQ-B-626 comp 11 QQ-B-613 comp 11 QQ-B-626 comp 11 and 22 QQ-B-626 comp 21 WW-T-756 WW-T-756 WW-T-756 QQ-B-626 comp 11 QQ-B-637 comp 4 QQ-B-613 comp 11 QQ-B-626 comp 11 QQ-B-637 comp 1 QQ-B-613 comp 11 QQ-B-626 comp 11 QQ-B-637 comp 1 MIL-W-6712 MIL-T-6945 comp 1 MIL-W-6712 MIL-T-6945 comp 1 Naval brass.T. O. class FS-RCuSm -2 QQ-R-571 Class FS-RCu Sm-2 QQ-R-571 Class FS-Rcu Sm-2 QQ-B-750 Comp D QQ-B-750 QQ-C-450 comp 3 QQ-C-450 comp 4 MIL-B-13501 MIL-W-6712 MIL-T-6945 comp 1 MIL-W-6712 MIL-T-6945 comp 1 MILITARY MIL-W-6712 MIL-T-6945 comp 1 MIL-W-6712 MIL-T-6945 Naval Brass. 1-1A-9 Table 6-1. 466 SPECIFICATION FEDERAL QQ-B-613 comp 11 QQ-B-626 comp 11 QQ-B-637 comp 1 QQ-B-613 comp 11 QQ-B-626 comp 11 QQ-B-637 comp 1 QQ-R-571 Class FS-RWZn-1 QQ-B 650 comp B QQ-B-626 comp 11 QQ-B-637 comp 2 QQ-B-626 comp 1 QQ-B-637 comp 3 QQ-B-750 comp A QQ-W-401 QQ-R-571.Continued COPPER ALLOY NO. High leaded 510 Phosphor Bronze A 518 Phosphor bronze 521 Phosphor Bronze C 524 544 606 612 Phosphor Bronze D Phosphor Bronze B-2 6-7 . welding and brazing rod Brazing Alloy Naval Brass. antimonial 467 470 472 482 Naval brass.T. phosphorized TRADE NAME Naval Brass. medium leaded 485 Naval Brass. Chemical Composition by Trade Name . Low Fuming Silicon Brass Copper Nickel 30% Low silicon bronze B MILITARY TRADE NAME Aluminum Bronze D 622 651 655 656 High Silicon Bronze A 658 661 670 675 680 681 692 715 735 745 6-8 . 1-1A-9 Table 6-1.O. Chemical Composition by Trade Name .Continued COPPER ALLOY NO. 614 618 SPECIFICATION FEDERAL QQ-C-450 comp 5 MIL-W-6712 MIL-R-18818 MIL-RUA1-2 MIL-R-18818 class MIL-RCA-B QQ-C-591 comp B QQ-C-591 comp A QQ-R-571 Class FS-RCuS1 MIL-T-8231 MIL-E13191 class MIL-EcuSi-A MIL-E-13191 class MIL-ECuSi-A QQ-C-591 comp D QQ-B-728 Class B QQ-B-728 Class A QQ-R-571 Class FS-RCu-Zn-3 QQ-R-571 class FS-RCuZn-2 QQ-C-591 Comp E QQ-R-571 Class FS-RCuNi QQ-C-585 comp 6 QQ-C-585 comp 5 QQ-C-586 comp 5 QQ-W-340 comp 5 Nickel Silver 65-10 Manganese Bronze B Manganese Bronze A Bronze Low Fuming (Nickel) Bronze.T. 5 Zn 90 Cu.5 Cu. 35 Zn.T. 35 Zn 60 Cu. commercially pure Gilding Metal Commercial Bronze Red Brass Low Brass Cartridge Brass Yellow Brass Muntz Metal Leaded Commercial Bronze Low Leaded Brass Medium Leaded Brass CHEMICAL COMPOSITION 99. 40 Zn 89 Cu. 1 Pb HOT WORKING TEMP oF 1300 to 1650 1300 to 1650 1400 to 1600 1450 to 1650 1450 to 1650 1350 to 1550 (a) 1150 to 1450 (a) (a) (a) ANNEALING TEMP o F 700 to 1200 800 to 1450 800 to 1450 800 to 1350 800 to 1300 800 to 1300 800 to 1300 800 to 1100 800 to 1200 800 to 1300 800 to 1200 6-9 .5 Pb 64. 15 Zn 80 Cu. 1-1A-9 Table 6-1.25 Zn. 34. 1.93 Cu 95 Cu.75 Pb 64.5 Cu. 30 Zn 65 Cu. 752 SPECIFICATION FEDERAL QQ-C-585 comp 1 QQ-C-586 comp 1 QQ-W-340 comp 1 QQ-C-586 comp 3 QQ-W-340 comp 3 QQ-C-585 comp 7 QQ-C-585 comp 2 QQ-C-586 comp 2 QQ-W-340 comp 2 QQ-C-586 comp 4 QQ-W-340 comp 4 Table 6-2. 20 Zn 70 Cu. 0. Chemical Composition by Trade Name . Hot Working and Annealing Temperatures for Copper and Wrought Copper Alloys MILITARY TRADE NAME Nickel Silver 65-18 764 766 770 Nickel Silver 55-18 794 COMMERCIAL DESIGNATION Copper.Continued COPPER ALLOY NO. 9.5 Zn. 10 Zn 85 Cu.O. 4 Zn.1 Pb 60 Cu. 30 Ni 65 Cu.5 Cu. 5 Cu. 18 Ni 55 Cu. Z al 95 Cu.Continued COMMERCIAL DESIGNATION High Leaded Brass Extra High Leaded Brass Free Cutting Brass Leaded Muntz Metal Free Cutting Muntz Metal Forging Brass Architectural Bronze Admiralty Naval Brass Leaded Naval Brass Manganese Bronze Aluminum Brass Phosphor Bronze ‘‘A’’ Phosphor Bronze ‘‘C’’ Phosphor Bronze ‘‘D’’ Phosphor Bronze ‘‘E’’ Cupro-Nickel 30% Nickel Silver 18% (A) Nickel Silver 18% (B) High-Silicon Bronze (A) Low Silicon Bronze (b) CHEMICAL COMPOSITION 62.75 Pb 62. 35. 37.5 Mn HOT WORKING TEMP oF (a) (a) 1300 to 1450 1150 to 1450 1150 to 1450 1200 to 1500 1200 to 1400 1200 to 1500 1200 to 1400 1200 to 1450 ANNEALING TEMP o F 800 to 1100 800 to 1100 800 to 1100 800 to 1100 800 to 1100 800 to 1100 800 to 1100 800 to 1100 800 to 1100 800 to 1100 1250 to 1450 1450 to 1550 (a) (a) (a) 1450 to 1600 1700 to 2000 (a) (a) 1300 to 1650 1300 to 1650 800 to 1100 800 to 1100 900 to 1250 900 to 1250 900 to 1250 900 to 1200 1200 to 1600 1100 to 1500 1100 to 1400 900 to 1300 900 to 1250 (a) These alloys are usually hot extruded af ter casting. 1.7 Zn 96. Specif ication QQ-C-530 and 172.5 Zn. 3 Si. 1.5 Zn. 6-11. 0. HEAT TREATING PROCEDURES AND EQUIPMENT REQUIREMENTS. 1-1A-9 Table 6-2. 39. 2 Si. 35 Zn. 0. 38 Zn.5 Zn.75 Sn 58. 3Mn.75 Sn 60 Cu.5 Cu. 8 Sn 90 Cu.5 Cu. 3 Pb 60 Cu.5 Cu. Hot Working and Annealing Temperatures for Copper and Wrought Copper Alloys .25 Sn 70 Cu.5 Pb 61. 28 Zn. 1 Sn 60 Cu. Typical Engineering properties of alloys 170. 2. 1. 1Fe 76. 22Zn. 1. 10 Sn 98. 2 Pb 57 Cu. 38. 5 Sn 92 Cu. 5 Pb 60.8 Cu.O. 3 Pb 71 Cu.T.2 Zn 1 Sn. 39. 40 Zn. 6-12.Cu. Specif ication QQ-C-533 are cited in Table 6-5. 1. 35. 0. 17 Zn.75 Zn. 27 Zn.5 Mn. 1.75 Cu. 18 Ni 94. Cu. 39.25 Zn. 6-10 .5 Zn. further hot working is uncommon. 18 ZN . 6-14. For parts less than 1/2 inch in thickness. Molten salt baths shall not be used because of corrosive attack of beryllium alloys by the molten salts at solution heat treatment temperatures. Insuff icient time will make it impossible to achieve maximum strength af ter precipitation hardening.37 ZN 60 CU .5 Sn 90 Cu .O. HOURS 1/2 1 1 1 1 1/2 1 1 1 1 1 1 Change 4 6-11 .1 SN 85 Cu .10 Zn 80 Cu . In addition. PRECIPITATION OR AGE HARDENING. or precipitation heat treatment. or ± 5oF for aging.T. Typical Stress-Relief Treatments for Certain Copper Alloys ALLOY COMPOSITION Copper. cold working requirements demand intermediate sof tening (annealing) treatment. forming operations and then precipitation heat treating. numbers 170.40 ZN 70 Cu . continuous or induction types. Some oxidation will occur as a result of the annealing temperatures and it should be removed by pickling or other suitable cleaning process.10 Sn TEMP oF 300 400 500 500 475 375 575 475 475 475 375 375 TIME. brazing or other fabrication operations or when. refer to the latest issue of SAE-AMS-H-7199. For complete description of heat treat requirements for these alloys.30 Ni 64 Cu . 172 and 175. the temperature in working zone shall not vary above the maximum or below the minimum specif ied for the alloy being treated. The furnace alloy shall be capable of maintaining a temperature in working zone with a normal load. Test sample should be used to determine specif ic time or if laboratory facilities are available an examination of microstructure will conf irm the adequacy of the time selected. Normally solution heat treatment is not required because the material is furnished in a condition suitable for accomplishing Table 6-3. 1-1A-9 NOTE SAE-AMS-H-7199. while excessive time may cause grain growth with attendant harmful possibilities.18 Ni 95 Cu .20 ZN 70 Cu . commercially pure 90 Cu . 6-15. Heat Treatment of Wrought Copper-Beryllium Alloys. The actual changes can be controlled by the time and temperature of hardening.29 ZN .30 ZN 63 CU . Once the parts are brought up to temperature it is recommended that material be held at temperature for 1 hour per inch of thickness. with either controlled gas atmosphere or air (static or forced). Appreciable changes can be produced in both mechanical and physical by this treatment. will be the control document for heat treatment of wrought copper-beryllium alloy. The solution heat treatment temperatures for alloys 170 and 172 shall be 1425o to 1460oF. The time the material is held at the temperature will determine the potential properties of the material. gas or oil. Table 6-6 gives times and temperatures for obtaining various tempers. Air atmosphere furnaces shall not be used when the loss of material due to excessive scaling is detrimental to the f inished part. An agitated quench should be used. 1/6-1/2 hour may be suff icient. SOLUTION HEAT TREATMENT COPPER-BERYLLIUM. used in the chamber. 6-13. 6-17. Process for (Copper Alloy numbers 170. The part/material should be rapidly (10 seconds or under) quenched in water from the annealing temperature. 6-16. of ± 20oF for solution heat treatment.15 Ni 70 Cu . during the holding portion of the treatment cycles (See Table 6-6). An exception is when the material has been rendered unsuitable for precipitation or age hardening as result of welding. Furnaces for solution heat treating of copper-beryllium items/parts may be heated by electricity. 172 and 175). 020 0.020 0.035 0.015 0.020 * Table based on machining characteristics in comparison to this alloy.005 to to to to to to to to to to to to to to to 0.040 0.020 0.015 to 0.035 0. INCH FINISHING FEED.020 0.020 0.005 0.005 to 0.015 0.020 0.015 0.003 0.015 0.015 150 to 300 150 to 300 150 to 300 150 to 300 150 to 300 75 75 75 75 75 75 75 75 to to to to to to to to 150 150 150 150 150 150 150 150 0.005 to 0.003 0.003 0.035 0.005 0.040 0.005 0.006 0.015 0.015 0.003 0.015 0.040 0.015 0.005 0. 85% Low Brass.040 0.015 0.040 0.015 to 0.006 0.020 0.006 0.015 0.015 0.005 to 0.015 0.035 0.015 0.005 0.006 0.006 0.020 0.015 to 0.006 0.035 0.035 0.035 0.015 to 0. Standard Machinability Rating of Copper Alloys ALLOY DESIGNATION MACHINABILITY RATING 80 80 60 70 90 100 80 70 90 30 30 40 30 30 50 50 30 60 60 20 20 20 20 20 20 20 20 SURFACE SPEED FEET PER MINUTE 300 300 300 300 300 300 300 300 300 300 150 150 150 150 150 to to to to to to to to to to to to to to to 700 700 700 700 700 700 700 700 700 700 300 300 300 300 300 ROUGHING FEED.015 0.040 0.005 0.020 0.015 0. INCH Leaded Copper Leaded Commercial Bronze Low Leaded Brass Medium Leaded Brass High Leaded Brass Free Cutting Brass* Forging Brass Leaded Naval Brass Architectural Bronze Red Brass.020 0.015 0.015 0.005 0.003 0.003 0.015 0.040 0.020 0.005 to 0.020 0.006 0.005 0.003 0.035 0.015 to to to to to to to to to to to to to to to 0.015 0.005 0.015 0. 6-12 .015 0.015 0.015 0.003 0.015 0. 80% Muntz Metal Naval Brass Manganese Bronze (A) Leaded Nickel Silver.015 0.015 0.005 0.020 0.020 0.015 0.020 0.O. 12% Leaded Nickel Silver 18% High Silicon Bronze (A) Leaded Silicon Bronze (d) Aluminum Silicon Bronze Electrolytic Tough pitch copper Commercial Bronze Phosphor Bronze Nickel Silver Cupro-Nickel Aluminum Bronze Beryllium Copper Chromium Copper 0.040 0.003 0.T.020 0.015 0.003 0.035 0.015 0.005 to 0.020 0.015 to 0.035 0. 1-1A-9 Table 6-4.006 0.005 to to to to to to to to 0.006 0.006 0.015 0.005 0.015 to to to to to to to to 0. Age Hardening Time-Temperature Conditions and Material Temper Designations MATERIAL FORM TEMPER DESIGNATION BEFORE AGE HARDENING A 1/4 H 1/2 H H A H H AGE HARDENING TIME TEMP HRS. Table 6-6.T.000 60-80.000 35-60 10-35 5-25 2-8 4-10 3-6 2-5 1-4 30-35 31-36 32-38 35-39 34-38 35-39 39-43 41-46 B45. Sheet or Strip Forgings Rod and Bar 3/4 Inch or Less Over 3/4 Inch Wire AT 1/4 HT 1/2 HT HT AT HT HT 600 ± 5 600 ± 5 600 ± 5 A 1/4 H 1/2 H 3/4 H 3 2 1-1/2 1 600 600 600 600 ± ± ± ± 5 5 5 5 AT 1/4 HT 1/2 HT 3/4 HT NOTE: For additional data see Specification SAE-AMS-H-7199.000 110-135.000 load cycles. Change 4 6-13/(6-14 blank) .000 160-195.000.2% OFFSET % ELONGATION IN 2 INCHES FATIGUE (1) STRENGTH KSI ROCKWELL HARDNESS ELECTRICAL CONDUCTIVITY % OF 1 ACS 17-19 16-18 15-17 15-17 22-25 22-25 22-25 22-25 A.000 55-70.O.78 B68-90 B88-96 B96-102 C36-MIN C38-MIN C39-MIN C40-MIN (1) Based on 100. (oF) 3 2-1/2 2 2 3 2 3 600 600 600 600 ± ± ± ± 5 5 5 5 TEMPER DESIGNATION AFTER AGE HARDENING Plate.000 90-112.000 165-205.000 100-125.Annealed 1/4 Hard 1/2 Hard Hard AT 1/4 HT 1/2 HT HT 60-78 75-88 85-100 100-120 165-190 175-200 785-210 190-215 28-36. Typical Engineering Properties TENSILE STRENGTH KSI YIELD STRENGTH 0. 1-1A-9 Table 6-5. . 7-5. It improves the deep hardening and elevated temperature properties of steel. Silicon is added to shock resisting and hot work steels to improve their impact characteristics and hardenability. dependent upon its intended use. square. molybdenum 7-1 .This element forms stable carbides and has considerable effect on the hardenability of steels.Carbon is the most important single element in tool steel.One of the most important features of tungsten steels is their high red hardness. 4 . c. i. (See Table 7-2.9% in tungsten . and present and past classif ication of the tool steels.80% the addition of chromium produced a marked increase in the hardenability (depth of hardness) of steels. acts as an intensif ier. drill rods. f. and QQ-S-780. hexagonal. Changing the carbon content a specif ic amount will change the physical properties a greater degree than the same amount of any other element. CARBON . COBALT .molybdenum high speed steels. (round. In amounts of 1/4 to 1% it acts as a deoxidizer. (round. MANGANESE . QQ-S779. Addition of 5 to 8% increase the red hardness of these steels. or rectangular). Undissolved vanadium carbides inhibit grain growth and reduce hardenability. it acts as a deoxidizer and desulfurizer. Machine ability decreases as chromium increases. Dissolved carbides increase hardenability. and 14 .) a. TUNGSTEN . e. chemical composition table. and forged shapes. 7-2. Table 7-1 lists these specif ications. which means they hold good cutting edges. Tool steels are produced and used in a variety of forms. h. It is used in only a few applications and only in small amounts. It is added to high speed and hot working steels to resist grain growth and help maintain their hardness at elevated temperatures.O. square. CHROMIUM . QQ-S-778. d. Army Specif ication 57-108A was superseded by three Army Ordnance Specif ications. Tungsten content is usually 5 . VANADIUM .This element is present in all steels. MOLYBDENUM . 1-1A-9 SECTION VII TOOL STEELS 7-1. QQ-T-580 and QQ-T-590 respectively. SILICON .12% in heat resisting tool steels. In amounts of less than 1/2%. Vanadium is also used as a deoxidizer. Small amounts of chromium toughens the steel (greater impact strength). f lats. or octaganal). Tool steels are essential to the fabrication of aircraf t parts. Degree of hardness of tool steel quenched from a suitable temperature is a function of carbon content alone. 7-3. ALLOYING ELEMENTS IN TOOL STEELS. It is therefore necessary to provide guidance in the handling of these important metals.Nickel makes the steel more ductile. Tungsten steels are f ine grained and high strength. The more common forms are bars. SPECIFICATIONS. The armed services procure tool steels under three different Federal Specif ications. 7-4.T. and increases its strength.Cobalt is sometimes used in high speed tools. NICKEL .In amounts up to 1.This element is present in all steels. In amounts greater than 15% it gives steel air hardening tendencies. The addition of 5 to 15% chromium imparts hardening qualities to the steel. b. A degree of red hardness and resistance to wear and abrasion results from the addition of chromium to steel. It is added to plain carbon tool steels to make them f ine grained and tough.Always used in conjunction with other alloying elements. It has a graphitizing inf luence and usually requires the addition of carbide stabilizing elements such as molybdenum and chromium. In intermediate amounts it is necessary to have other alloying agents present with manganese because of its tendency to make the steel brittle. g. GENERAL. which were then superseded by Federal Specif ication’s QQ-T-570.20% in straight tungsten high speed steel. O.QQ-T-778 57-108A ----------QQ-S-00778 (Army) -----QQ-S-00778 (Army) QQ-S-00778 (Army) QQ-S-00778 (Army) QQ-S-00778 (Army) CLASSIFICATION A1 A2 A3 A4/A5 B1 B1 FS-W3-10 C1 -----C2 C3 FS-D5 -----D1 -----FS-H12 -----FS-H21 FS-T1 FS-T2 FS-T4 FS-T5 T6 FS-T7 FS-T8 FS-M1 FS-M2 FS-M3 -----F1 -----F3 FS-M34 B4 B3 ----------FS-L7 -----FS-S1 FS-S2 FS-S5 FS-W5 W1-.Special purpose. low alloy types F . 1-1A-9 D .80 Carbon W1-. Tool Steel Specifications SAE DESIGNATION FEDERAL SPECIFICATION NUMBER CLASS W1-08 W1-09 W1-10 W1-12 W2-09 W2-10 W3-10 A2 A6 D2 D3 D5 D7 F3 H11 H12 H13 H21 T1 T2 T3 T4 T5 T6 T7 T8 M1 M2 M3 M4 M-10 M15 M30 M34 01 02 06 L6 L7 T15 S1 S2 S5 W5 SUPERSEDED SPECIFICATION NUMBER 57-108A 57-108A 57-108A 57-108A 57-108A 57-108A QQ-S-00779 (Army) 57-108A -----57-108A 57-108A QQ-S-00778 (Army) -----57-108A -----QQ-S-00778 (Army) -----QQ-S-00778 (Army) QQ-S-00780 (Army) QQ-S-00780 (Army) -----QQ-S-00780 (Army) QQ-S-00780 (Army) MIL-S-15046 (Ships) QQ-S-00780 (Army) QQ-S-00780 (Army) QQ-S-00780 (Army) QQ-S-00780 (Army) QQ-S-00780 (Army) -----57-108A -----57-108A QQ-S-00780 (Army) 57-108A.90 Carbon W1-1.0 Carbon VV A2 A6 D2 D3 D5 D7 F3 H11 H12 H13 H21 T1 T2 T3 T4 T5 T6 T7 T8 M1 M2 M3 M4 M10 M15 M30 M34 01 02 06 L6 L7 T15 S1 S2 S5 W5 QQ-T-580 QQ-T-580 QQ-T-580 QQ-T-580 QQ-T-580 QQ-T-580 QQ-T-580 QQ-T-570 QQ-T-570 QQ-T-570 QQ-T-570 QQ-T-570 QQ-T-570 QQ-T-570 QQ-T-570 QQ-T-570 QQ-T-570 QQ-T-570 QQ-T-590 QQ-T-590 QQ-T-590 QQ-T-590 QQ-T-590 QQ-T-590 QQ-T-590 QQ-T-590 QQ-T-590 QQ-T-590 QQ-T-590 QQ-T-590 QQ-T-590 QQ-T-590 QQ-T-590 QQ-T-590 QQ-T-570 QQ-T-570 QQ-T-570 QQ-T-570 QQ-T-570 QQ-T-590 QQ-T-570 QQ-T-570 QQ-T-570 QQ-T-570 7-2 .T.0 Carbon V W3-1.2 Carbon W2-.Carbon tungsten tool steels Table 7-1.Molybdenum Base types L .9 Carbon V W2-1.High carbon-high chromium types H .0 Carbon W1-1.Hot work tool steels T .High speed tool steels M . 20 0.90-1.75 1.60 2.60 2.00 Carbon VV A2-5% Chromium A6-Maganese D2 D3 D5 D7 F3 H11 H12 H-13 H21 T1 T2 T3 T4 C 0.10-0.40 0.40 0.20-0.95-1.80-1.35 0.75 17.20 0.25-18.50 0.70-1.00 3.90 0.5-3.50 0.15-2.50 3.50 3.30-0.O.60 2.10 0.35 0.10 0.40 0.50 max 0.20 0.0 13.90-1.10-0.30-0.90-3.20-0.40 SI 0.10 0.70-1.00 1.90 Carbon W1-1.50 3.75 1.00-1.40 0.15-0.95 0.15-0.40 0.025 0.15-0.35 0.30-0.10 0.80-2.025 0.10 0.0 13.60-0.70-1.40 0.20 CU 0.20-0.40 0.35 0.70-1.013.45 0.10 0.15 0.20 0.15-0.755.20-0.35 1.40 0.00 Carbon-V W3-1.25-1.50 0.00 0.85-0.15-0.10-0.10 0.15 0.030 0.30-0.30 1.95-1.75 8.40 CHEMICAL C0MPOSITION.40 0.15 0.10 0.15-0.50 0.85-0.25-1.30 0.50 0.20-0.20-0.80 0.20-0.35 0.00 4.40 0.65-0.15-0.025 0.10-0.75-4.80 MN 0.20-0.15-0.5 T.20 0.030 0.20 0.80 0.35-0.50-19.30-0.75 1.75-0.20 0.50 1.50 0.755.5 0.50 0.35 0.25-1.90-1.50 0.30-0.5 13.40 0.20-0.95-1.20 0.0-1.45 0.75 7-3 .901.10-0.25-18.30-0.40 0.20 P 0.20-0.20 0.30-0.24-0.25-1.10-1.00 17.20 11.20 0.00 17.755.20 0.20-0.15 0.75 1.50 0.35 0.0 11.40 0.Table 7-2.20 0.50 0.20 0.50 4.15 0.20-0.50 0.80-1.20-0.20 0.15-0.70-0.75 0.15-0. Chemical Composition.75 1.20-0.80-1.30-0.35 0.35 0.8-4.40 2.20 0.30 0.45-0.00 17.00-2.30-0. 1-1A-9 4.10-0.75 3.40 0.35 0.15 0.75 5.7 0.50 0.40 0.20 0.80-1.20 0.4 0.20 Carbon W2-.85 1.10-0.70-0.35 0.30-0.15 0.15 0.70-1.030 0.10 0.75-4.50 3.75 10.80 Carbon W1-.15 0.75-4.35 0.35 0. PERCENT (TABLE II) CR V MO W 0.65-0.15 0.10 0.0 11.85 0.05 0.15 0.50 .10 1.35 0.15 4.40 0.20 0.30-0.80 2.40 0.025 0.40 0.15 CO NI 0.50 0.10-1.80-2.95-1.40 0.50 4.25-0.20 3.25 max 4.00 0.20 0.10 0.20-0.75-4.20 0.15 0.90 Carbon-V W2-1.25 5.40 0.50-19.10 0.80 0.0 11.35 0.35 0.00 Carbon W1-1. Tool Steel SAE DESIGNATION W1-.40-1.80-1.40-1.10 0.95 0. 95-1.25-14.20-0.50 0.0 0.30 0.75 4.75-5.50 3.30 1.40 0.50 3.50-6.20-0.00 0.50 1.75-4.20 4.45-0.25 max 0.15-0.25 3.30 0.755.50-2.505.00 3.75-4.60 0.75-6.50-6.40 0.30-0.70-0.50 10.20-0.40 0.25 1.85 0.75 3.95 0.85-0.40 0.40 0.00-5.75-4.30 0.20-0.10 1.40 0.35-1.50 CO 7.00-13.95 1.25 3.55 0.85-0.40 0.50 4.50 0.50-4.20-0.70-1.30 1.00 2.20-0.80-1.00-1.75-9.00 9.75-3.20-0.30-0.40 0.35 0.50 13.20-0.20-0.50-0.00 7.25 4.40 0.85 0.15-1.20-0.75 5.75 1.20-0.75 1.25 0.40 0.40 0.50 1.20-0.00 8.25 4.40 0.75-4.20-0.40 0.20-0.40 0.30-0.75 1.45 0.75 4.85-0.40 0.20 0.25-1.90-1.20-0.50-1.20 1.40 0.75-0.90-4.76 0.75-0.50 12.50-5.78-0.65-0. PERCENT (TABLE II) CR V MO W 3.00-4.20 2.30-0.80-2.30 max 0.20-0.60 0.30-1.20-0. Chemical Composition.40 0.25 0.30 0.90-2.20-0. 1-1A-9 Table 7-2.85 0.25-0.40 0.75-9.25 3.00-6.35 1.40 0.75 0.25-0.80-1.20-0.00 18.25 1.75-0.0-3.85 1.50-19.20 0.40 CHEMICAL C0MPOSITION.80-2.40 0.85 5.60 0.75 4.55 0.75 8.50-14.50 4.75 NI CU P 4.15-0.35 T.30-0.00-9.25 0.40 0.25 MN 0.00 1.00 0.50 4.85 0.20-0.50 4.20-0.60-0.92 0.40 0.35-3.255.05-1.30 0.40-0.30-2.75 3.25 13.55 0.20 1.70-1.50 7.80 0.45 0.25 13.60-2.7-4 SAE DESIGNATION T5 T6 T7 T8 M1 M2 M3 M4 M10 M15 M30 M34 01 02 06 L6 L7 T15 S1 S2 S5 W5 C 0.75-4.20-0.45-0.88 1.50-4.80 0.20 6.50 3.20-0.25-1.50-5.95 1.40 1.25-1.30 1.20-0.85 0.35 0.30-2.75 0.30 0.10-0.60 0.70-1.25 .50 7.40-0.Continued SI 0.25-6.40-1.75-5.70-1.O.75-4.40-0.80-2.20-0.40 0.00 0.60 17.50-5.50 1.80-2.40 0.20 0.30 1.40 0.20-0.75 5.20-0.40 0.40 1.20-0.80-2.20-0.75 3.00-1.25 1.60 1.25 4.65-0.50-21.20-0.90 0.25 0.20-0.85-0.75-9.00-4.00-1.40-0.30 0.00 0.40 0.60 0.75-4.40 0.75-4.05 1.50-1.77-0.40 0.75-0.40 0. Tool Steel .20-0. transformer grade Paper. A2 A2. Oil 2225oF.0. Selection is usually based more on previous experience or applications than on an engineering or metallurgical analysis. AIS14140 W1. oil hardening types A . copper and magnesium alloys Carbon and alloy steels. The majority of tool steel applications can be divided into a small number of groups: cutting.Cold work tool steels. and high wear resistance. The selection of material for a cutting tool depends on several factors: the metal being machined. Most 7-5 .000 W1. not reinforced TOTAL QUANTITY OF PARTS TO BE MADE 1. A2 Table 7-3 is listed for use as a guide reference in the selection of tool steel types for specif ic applications. lathe tools. Rockwell C52max Electrical sheet.0016 . In battering tools.000 10. shearing. D2 W1 01 01. high toughness is most important. 0.0006 . forging. Oil 1875 F. forming. cutting tools require high hardness.0005 . AIS14140 W1. extrusion.0011 . Forming tools must possess high wear resistance or high toughness and strength.0.000 100. machining practice. D2 D2 D2 W1. 01.0. Oil 1550 F. taps. 1-1A-9 Table 7-3. high resistance to the sof tening effect of heat.0021 0. coolant to be used. D2 A2. W .0025 0.0014 0.Shock resisting tool steels O . A2 01.0014 .0005 . Oil 1750oF. Oil 2350 F. Forming tools include draw. Oil 1600 F.Water hardening tool steels S . Oil 1775 F. A2 W1.0014 .Cold work tool steels. A2. Shearing tools require high wear resistance and fair toughness. IN/IN W O L F S A D T M 7-6.0. etc. ferritic stainless Stainless steel.0. Shearing tools include shears. broaches. Table 7-4. punches. air hardening types 7-7. A2 01. A2 A2 A2 W1 01 W1. D2 A2. nature of cutting operation.0024 0. austenitic Spring steel. 01.0025 0.0015 0. Tool Steel Selection MATERIAL TO BE CUT Aluminum.0.O. etc. Battering tools include chisels and all forms of shock tools. blanking and trimming dies.0. and similar sof t material Plastic sheet. hardened. size and design of tool. hobs. condition of the machine tool. and cost of tool material. A2 W1. Water 1450 F.0.0. APPLICATIONS OF TOOL STEELS.0017 . rolling and battering.0024 CLASS DESIGNATIONS. cold heading and die casting dies. drawing.T. 7-9. Oil o o o o o o TEMPERING TREATMENT 300oF 300 F 300 F 300 F 500oF 500 F 500 F 1050 F 1025oF o o o o o o SIZE CHANGE. Tool Steel Hardening and Tempering Temperatures STEEL HARDENING TREATMENT 1450oF.0010 . 7-8.0021 0. gaskets. Cutting tools include drills.0005 0. SELECTION OF MATERIAL FOR A CUTTING TOOL. High speed drills should possess high strength and toughness. M2. 7-18. 7-12.T. T7. Material for reamers should be of high hardness and abrasion resistance. M2. The M3 and M15 and T15 classes possess greater abrasion resistance than the lowervanadium grades. such as M1. and test samples should be checked prior to use. the cobalt high speed steels should be used. 1-1A-9 7-10.050 inch sheet materials are shown in following table. 7-13. the two main types being volume change or change in geometrical form. M15 or T15 may be justif ied. such as T6. T8 and T15 are advantageous for operations like milling cutters and prehardened forging die blocks. M10 and T1. Certain special purpose steels in each class. 7-19. These tables are listed for use as a guide only. and also dependent on specif ic tempering and heat treatments. and annealing of tool and die steels. This table does not cover all operations. Recommended punch and die material for blanking parts from 0. M10 and T1. NOTE Additional Heat Treatment information is discussed in Section IX. Classes T1 and M1 are used for tools subject to shock. The thermal treatments listed in table 7-5 cover the generally used treatments for the forgings. Volume change is def ined as expansion or contraction and geometric change is def ined as changes in curvature or angular relations. normalizing. M2 and M10 make up nearly 90% of the general purpose high speed steels. while M2 and M10 are generally used where tools require less toughness and more abrasion resistance. notably M1. 7-15. HEAT TREAT DATA. Material for taps is generally of the M1. 7-14. If a very close tolerance is required for a f inished tool. As the hardness of the workpiece increases beyond Rockwell C35. Deleted Deleted Deleted Deleted Deleted 7-6 Change 1 . M2 or M10 types.O. 7-17. High speed cutting tools are usually manufactured from the class ‘‘T’’ or class ‘‘M’’ alloys. 7-23. specif ic data covering this item should be obtained from a detailed source. 7-16. In tapping heat-resisting alloys or steels harder than Rockwell C35. The thermal treatments listed in table 7-7 cover the usual ranges of temperatures for hardening and tempering tool and die steels. Distortion is a general term encompassing all dimensional changes. and is a sample table intended for use as a guide only. T1. Table 7-4 shows an approximate range of size changes depending upon the type of tool steel. DISTORTION IN TOOL STEELS. Milling cutters are usually made from the high speed steels. 7-22. 7-20. Four classes. M1. 7-21. 7-11. 84-94 1500 1400-1450 W1 (0.0C) 1450 1500 1450 1550 1400-1450 75 159-202 84-94 A2 1600 1650 DO NOT NORMALIZE 1550-1600 40 202-229 94-98 A6 D2 1200-1300 1650 1850 2000 1850 2000 1850 2000 2050 2125 1800 2000 1650 DO NOT NORMALIZE DO NOT NORMALIZE 1600-1650 40 248 207-255 102 95-102 D3 1650 1650 DO NOT NORMALIZE 1600-1650 50 212-255 96-102 D5 1650 1650 DO NOT NORMALIZE 1600-1650 40 207-255 95-102 Change 1 7-7 D7 1650 1800 DO NOT NORMALIZE 1600-1650 50 235-262 99-103 T.0C) 1450 1500 1450 1550 1400-1450 75 159-202 84-94 W3 (1.Table 7-5. APPROX.0C) 1450 1500 1450 1550 1400-1450 75 159-202 84-94 W1 (1. 1-1A-9 F3 1550 1600 DO NOT NORMALIZE 1475 50 235 99 .8C) HEAT SLOWLY TO 1450 START FORGING AT 1800 1950 1800 1950 1800 1900 1800 1900 1800 1900 1800 1900 1800 1900 1850 2000 DO NOT FORGE BELOW 1500 NORMALIZING/b HEAT SLOWLY TO 1450 HOLD AT TEMPERATURE ANNEALING/c MAX RATE OF COOLING F/HR 75 BRINELL HARDNESS APPROX.2C) 1450 1500 1450 1625 1400-1450 75 159-202 84-94 W2 (0.O. 159-202 ROCKWELL B. Normalizing and Annealing Treatments of Tool and Die Steels FORGING/a SAE DESIGNATION W1 (0.9C) 1450 1500 1450 1500 1375-1425 75 159-202 84-94 W2 (1.9C) 1450 1500 1450 1500 1375-1425 75 159-202 84-94 W1 (1. Forging. 1-1A-9 Table 7-5. ROCKWELL B. Normalizing and Annealing Treatments of Tool and Die Steels . 1650 DO NOT NORMALIZE 1550-1600 50 192-229 92-98 1650 DO NOT NORMALIZE 1600-1650 50 192-229 92-98 1650 DO NOT NORMALIZE 1550-1600 50 192-229 92-98 1650 DO NOT NORMALIZE 1600-1650 50 202-235 94-99 1750 DO NOT NORMALIZE 1600-1650 50 217-255 96-102 1750 DO NOT NORMALIZE 1600-1650 50 223-255 97-102 1750 1750 DO NOT NORMALIZE DO NOT NORMALIZE 1650 1600-1650 50 50 229-255 98-102 1800 DO NOT NORMALIZE 1600-1650 50 248-293 102-106 1700 DO NOT NORMALIZE 1600-1650 50 248-293 102-106 1700 DO NOT NORMALIZE 1550-1625 50 217-250 96-102 1750 DO NOT NORMALIZE 1600-1650 50 229-255 98-102 1700 DO NOT NORMALIZE 1525-1600 50 207-248 95-102 1700 DO NOT NORMALIZE 1550-1625 50 217-248 96-102 .7-8 Change 1 SAE DESIGNATION HEAT SLOWLY TO H11 1650 1950 2100 1950 2100 1950 2100 2000 2150 1950 2100 2000 2150 2025 2000 2150 2000 2150 1950 2150 1950 2150 2000 2150 1900 2050 1950 2100 H12 1650 H13 1650 H21 1600 T1 1600 T2 1600 T3 T4 1925 1600 T5 1600 T6 1600 T7 1600 T8 1600 M1 1500 M2 1500 T.Continued FORGING/a START FORGING AT DO NOT FORGE BELOW NORMALIZING/b HEAT SLOWLY TO HOLD AT TEMPERATURE ANNEALING/c MAX RATE OF COOLING F/HR BRINELL HARDNESS APPROX. APPROX. Forging.O. 1-1A-9 S1 1500 1600 DO NOT NORMALIZE 1450-1500 50 192-235 92-99 .Table 7-5. Forging. ROCKWELL B.Continued FORGING/a SAE DESIGNATION HEAT SLOWLY TO START FORGING AT DO NOT FORGE BELOW NORMALIZING/b HEAT SLOWLY TO HOLD AT TEMPERATURE ANNEALING/c MAX RATE OF COOLING F/HR BRINELL HARDNESS APPROX. M3 1500 2000 2150 2000 2150 1900 2100 1900 2100 1900 2100 1900 2100 1750 1900 1750 1900 1750 1900 1800 2000 1800 2000 2000 2100 1800 2000 1700 DO NOT NORMALIZE 1550-1625 50 223-255 97-102 M4 1500 1700 DO NOT NORMALIZE 1550-1625 50 229-255 98-102 M10 1400 1700 DO NOT NORMALIZE 1600-1650 50 235-262 99-103 M15 1400 1700 DO NOT NORMALIZE 1600-1650 50 235-262 99-103 M30 1400 1600 DO NOT NORMALIZE 1600-1650 50 235-262 99-103 M34 1400 1600 DO NOT NORMALIZE 1600-1650 50 235-262 99-103 01 1500 1550 1500 1600 1425-1475 50 183-212 90-96 02 1500 1550 1500 1550 1375-1425 50 183-212 90-96 06 1500 1500 1500 1625 1425-1275 50 183-212 90-96 L6 1500 1600 1550 1650 1400-1450 50 183-212 90-96 L7 1500 1550 1550 1650 1450-1500 50 174-212 88-96 T15 1500 1600 DO NOT NORMALIZE 1600-1650 35 241-269 100-104 Change 1 7-9 T. APPROX.O. Normalizing and Annealing Treatments of Tool and Die Steels . The purpose of normalizing af ter forging is to ref ine the grain structure and to produce a uniform structure throughout the forging. 192-229 ROCKWELL B. the higher side of which should be used for large sections and heavy or rapid reductions. APPROX. the time of soaking at forging temperature increases proportionately. With the very high alloy steels. as the alloy content of the steel increases. The temperature at which to start forging is given as a range. to about 4 hours for heavy sections and large furnace charges of high alloy steel. 92-98 1650 1600 1500 1600 1400-1450 50 192-229 92-98 1500 DO NOT NORMALIZE 1400-1425 50 192-212 92-96 a. Either furnace cooling or burying in an insulating medium such as lime. it becomes more necessary to cool slowly from the forging temperature. Normalizing should not be confused with low temperature (about 1200F) annealing used for the relief of redisual stresses resulting from heavy machining. Forging. and the lower side for smaller sections and lighter reductions. and the lower limit for smaller sections. Cooling from the normalizing temperatures is done in still air.O. as the alloy content increases. such as high speed or air hardening steels. Likewise. varies from about 15 minutes for a small section to about 1 hour for larger sizes. c. The annealing temperature is given as a range. The temperature varies from about 1 hour for light sections and small furnace charges of carbon or low alloy steel. .Continued FORGING/a START FORGING AT DO NOT FORGE BELOW 1600 NORMALIZING/b HEAT SLOWLY TO 1500HOLD AT TEMPERATURE 1400-1450 ANNEALING/c MAX RATE OF COOLING F/HR 50 BRINELL HARDNESS APPROX. The length of time the steel is held af ter being uniformly heated through at the normalizing temperature.7-10 Change 1 SAE DESIGNATION S2 HEAT SLOWLY TO 1500 1900 2100 1900 2050 1700 1900 S5 1500 W5 1200 T. the upper limit of which should be used for large sections. or silocel is satisfactory. b. Normalizing and Annealing Treatments of Tool and Die Steels . this slow cooling is imperative in order to prevent cracking and to leave the steel in a semi-sof t condition. 1-1A-9 Table 7-5. mica. bending and forming. Table 7-6. Thermal Treatment for Hardening and Tempering Tool Steel . 1-1A-9 7-11 .O.General CLASS W1-08 W1-09 W1-10 W1-12 W2-09 W2-10 W3-10 A2 A6 D2 D3 D5 D7 F3 H-11 H12 H13 H21 T1 T2 T3 T4 T5 QUENCH MEDIUM Water Water Water Water Water Water Water Air Air Air Oil Air Air Water Air Oil-Air Air Oil-Air Oil-AirSalt Oil-AirSalt Oil-Air Oil-AirSalt Oil-AirSalt PREHEAT TEMPERATURE F -a -a -a -a -a -a -a 1200-1300 1200-1300 1200-1300 1200-1300 1200-1300 1200-1300 -a 1450-1500 1450-1500 1400-1450 1500-1550 1500-1550 1500-1550 1500-1550 1500-1550 1500-1550 HARDENING TEMPERATURE RANGE F 1420-1450 1420-1450 1420-1450 1420-1500 1420-1500 1420-1500 1420-1500 1725-1775 1525-1600 1800-1875 1750-1800 1800-1875 1850-1950 1550 1825-1875 1800-1900 1825-1575 2100-2150 2300-2375 2300-2375 2275-2325 2300-2375 2300-2400 HARDNESS AFTER QUENCHING ROCKWELL C 65-67 65-67 65-67 65-67 65-67 65-67 65-67 61-63 60 61-63 62-64 60-62 63-65 62-66 53-55 53-55 53-55 50-52 63-65 63-65 TEMPERING TEMPERATURE RANGE F 350-525 350-525 350-525 350-525 350-525 350-525 350-525 400-700 HARDNESS AFTER TEMPERING ROCKWELL C 65-56 65-56 65-56 65-56 65-56 65-56 65-56 60-57 DECARBURIZATION (PREVENTION OF DURING HEAT TREATMENT) -b -b -b -b -b -b -b -c 400-700 400-700 400-700 300-500 850-1000 300-500 1000-1100 1000-1100 1000-1100 950-1150 1025-1100 1025-1100 1000-1050 60-58 62-58 59-57 65-63 62-58 66-62 51-43 51-43 51-43 50-47 65-63 63-65 67-60 65-63 65-63 -c -c -c -c -c -c -c -c -c -c -c -c -c -c 63-65 63-65 1026-1100 1050-1100 T. O. Thermal Treatment for Hardening and Tempering Tool Steel . 1-1A-9 Table 7-6.Continued PREHEAT TEMPERATURE F 1600 1600 1500-1550 1400-1500 1450-1500 1450-1500 1450-1500 1400 1400 1400 1400 HARDENING TEMPERATURE RANGE F 2350 2325 2300-2375 2150-2250 2175-2250 2150-2225 2150-2225 2220 2220 2220 2220 1450-1500 1420-1450 1450-1500 1500-1600 1525-1550 2250-2300 1650-1800 HARDNESS AFTER QUENCHING ROCKWELL C 60-65 60-65 63-65 63-65 63-65 63-65 63-65 60-65 60-65 60-65 60-65 63-65 63-65 63-65 62-64 63-65 65-66 57-59 TEMPERING TEMPERATURE RANGE F 1000-1100 1000-1100 1025-1100 1025-1100 1025-1075 1025-1075 1025-1075 1000-1100 1000-1100 1000-1100 1000-1100 300-800 375-500 300-800 400-800 350-500 1025-1100 300-1000 HARDNESS AFTER TEMPERING ROCKWELL C 65-60 65-60 65-63 65-63 65-63 65-63 65-63 65-60 65-60 65-60 65-60 62-50 62-57 63-50 62-48 62-60 66-68 57-45 DECARBURIZATION (PREVENTION OF DURING HEAT TREATMENT) -c -c -c -c -c -c -c -c -c -c -c -b -b -b -b -b -c -c 1500-1600 1200-1300 .7-12 CLASS T6 T7 T8 M1 M2 M3 M4 M10 M15 M30 M34 01 02 06 L6 L7 T15 S1 QUENCH MEDIUM Oil Oil Oil-AirSalt Oil-AirSalt Oil-AirSalt Oil-AirSalt Oil-AirSalt Oil Oil Oil Oil Oil Oil Oil Oil Oil Oil-Air Oil -a -a -a -a -a T.General . General . Furnace atmosphere dew point is considered a reliable method of measuring and controlling this equilibrium.O. preheating at 1050o to 1200o is recommended. Thermal Treatment for Hardening and Tempering Tool Steel . T. b. the furnace atmosphere should be in equilibrium with the carbon content of the steel being treated. c. In the latter case.Continued CLASS S2 S5 QUENCH MEDIUM Water-oil Water Oil PREHEAT TEMPERATURE F -A HARDENING TEMPERATURE RANGE F 1550-1575 1660-1625 1550-1600 1600-1675 HARDNESS AFTER QUENCHING ROCKWELL C 60-62 58-60 60-62 58-60 65-66 TEMPERING TEMPERATURE RANGE F 300-500 300-500 300-650 300-650 300-400 HARDNESS AFTER TEMPERING ROCKWELL C 60-54 58-54 60-54 58-54 62-65 DECARBURIZATION (PREVENTION OF DURING HEAT TREATMENT) -b -b -b -b -b W5 Water 1100-1200 1400-1550 a. For large tools and tools having intricate sections. Use moderately oxidizing atmosphere in furnace or a suitable neutral salt bath. Use protective pack from which volatile matter has been removed.Table 7-6. carefully balanced neutral salt bath or atmosphere controlled furnaces. 1-1A-9 7-13 . 1-1A-9 Table 7-7. Comparison of Tool Steel Properties CLASS NON DEFORMING PROPERTIES TOUGHNESS RESISTANCE TO SOFTENING EFFECT OF HEAT Poor Poor Poor Poor Poor Poor Poor Fair Poor Fair Fair Fair Fair Poor Good Good Good Good Good Good Good Best Best Good Good Best Good Good Good Good Good Good Good Good Poor WEAR RESISTANCE MACHINE ABILITY W1-08 W1-09 W1-10 W1-12 W2-09 W2-10 W3-10 A2 A6 D2 D3 D5 D7 F3 H11 Hl2 Hl3 H21 T1 T2 T3 T4 T5 T6 T7 T8 M1 M2 M3 M4 M10 M15 M30 M34 01 Poor Poor Poor Poor Poor Poor Poor Best Good Best Good Best Best Poor Good Good Good Good Good Good Good Good Good Good Good Good Good Good Good Good Good Good Good Good Good Good Good Good Good Good Good Good Fair Fair Fair Poor Fair Poor Poor Good Good Good Good Poor Poor Poor Poor Poor Fair Poor Poor Poor Poor Poor Poor Poor Poor Poor Poor Fair Fair Fair Good Good Fair Good Good Good Good Best Best Best Best Best Fair Fair Fair Fair Good Good Good Good Good Best Best Good Good Good Best Best Best Best Best Best Good Best Best Best Best Best Best Best Fair Fair Poor Poor Poor Poor Fair Fair Fair Fair Fair Fair Fair Fair Fair Fair Fair Fair Fair Fair Fair Fair Fair Fair Fair Fair Fair Good 7-14 .O.T. O.T. Comparison of Tool Steel Properties .Continued CLASS NON DEFORMING PROPERTIES TOUGHNESS RESISTANCE TO SOFTENING EFFECT OF HEAT Poor Poor Poor Poor Best Fair Fair Poor Poor WEAR RESISTANCE MACHINE ABILITY 02 06 L6 L7 T15 S1 S2 S5 W5 Good Fair Fair Fair Good Fair W-Poor O-Fair W-Poor O-Fair Poor Fair Fair Fair Fair Poor Good Best Good Good Good Good Fair Good Best Fair Fair Fair Fair Good Best Fair Fair Fair Fair Good Best Best 7-15/(7-16 blank) . 1-1A-9 Table 7-7. T.O. 1-1A-9 SECTION VIII TESTING AND INSPECTION HARDNESS TESTING 8-1. GENERAL. d. A release mechanism with micrometer eyepiece for calculating the area of the impression. 8-7. Making The Brinell Test. The test is preformed as follows: a. Prepare the sample by f iling, grinding, and polishing to remove all scratches and variations that may affect the reading. b. Place the sample on the anvil of the machine and elevate until the hardened ball contacts the surface to be tested. c. Apply the load by pumping handle. NOTE A load of 3,000 kilograms is required for steel, while 500 kilograms is used when testing the sof ter metals, such as aluminum alloy, brass, and bronze. Normally, the load should be applied for 30 seconds. Although this period may be increased to 1 minute for extremely hard steels, in order to produce equilibrium. d. Release the pressure and measure the area of impression with the calibrated microscope. e. Calculate the Brinell number, completing the test. 8-8. ROCKWELL HARDNESS TEST. The Rockwell hardness test is based on the degree of penetration of a specif ically designed indentor into a material under a given static load. The indentor/penetrator used may be either a diamond or hardened steel ball. The diamond indentor called a ‘‘brale’’ is precision ground and polished and the shape is spheroconica. The steel ball for normal use is 1/16 inch diameter, however, other larger diameter steel balls such as 1/8, 1/4 or 1/2 inch may be used for testing sof t metals. The selection of the ball is based on the hardness range of the type of materia1 to be tested. 8-9. The Rockwell machine/tester for accomplishing the hardness test applies two loads to obtain the controlled penetration and indicates results on a graduated dial (see Figure 8-2). A minor load of 10 kilograms is f irst applied to seat the penetrator in the surface of the test specimen. The actual penetration is then produced by applying a major 8-2. Hardness testing is used to determine the results of heat treatment as well as the state of the metal prior to heat treatment. Its application in determining the approximate tensile strength of the material by use of a hardness-tensile strength table is very limited and should only be used in the case of ferrous (steel) alloys. Table 8-1 should be used only as a conversion table for converting the various hardness values from one type of test to another, and should not be used as an indication of tensile strength for alloys other than ferrous. In addition, it should be realized that values given in Table 8-1 are only approximate. Whenever a specif ic type of hardness test is given in a drawing, specif ication, etc., necessary hardness readings should be made by that test whenever possible, rather than by other means, and a conversion made. In obtaining hardness values, precaution must be taken to assure removal of cladding and decarburized surface layers from area to be tested. 8-3. METHODS OF HARDNESS TESTING. 8-4. The methods of hardness testing in general use are: Brinell, Rockwell, Vickers (British), Tukon and Shore scleroscope. 8-5. BRINELL HARDNESS TEST. This test consists of pressing a hardened steel ball into a f lat surface of the metal being tested by the application of a known pressure. The impression made by the ball is measured by means of a microscope with a micrometer eyepiece. The Brinell ‘‘number’’ is obtained by dividing the load in kilograms by the area of the spherical impression made by the ball, measured in square millimeters. The thickness of all samples used for testing must be suff icient to prevent bulging on the under side. 8-6. Brinell Tester. The Brinell tester (Figure 81) consists of the following major parts: a. An elevating screw and anvil for bringing the sample into contact with the ball. b. A manually operated hydraulic pump for applying the pressure to the hardened steel ball, which is mounted on its actuating member. c. A pressure gage for determining the applied pressure. 8-1 T.O. 1-1A-9 load, subsequently, releasing and then reading hardness number from the dial. The dial reading is related to the depth of penetration, load and the penetrator used. The shallower the penetration, the higher the hardness value number for given indentor and load. The normal major load is 150 kilograms (‘‘C’’ Scale) when using the diamond penetrator and 100 kilograms (‘‘B’’Scale) when using a 1/16 inch steel ball. A hardness value indicated by a number alone is incomplete. The number must be pref ixed with a letter to indicate the load and indentor used to obtain the number. There is a variety of combinations of indentors and loads used to obtain a hardness value in accordance with hardness range of various material. The combinations are listed in Table 8-2 which is based on Specif ication ASTM E-18. 8-10. Review of Table 8-2 will reveal that the Red Dial Numerals ‘‘B’’ scale are used for steel ball indentors regardless of size of ball or load and Black Figure ‘‘C’’ scales are used for the diamond penetrator. When the readings fall below the hardness value, C20 (B98) the material is considered too sof t for the diamond cone and 1/16 inch or larger hardened ball should be used. The diamond cone must be used for all hard materials (those above 100 on the ‘‘B’’scale) as the steel ball may be deformed by the test. If in doubt about the hardness of a material start with the diamond penetrator and switch to the steel ball if the material is below C20-C22. 8-11. Rockwell Test Procedure: The procedure for making the Rockwell test is outlined as follows: (See Figure 8-2 for machine illustrations.) a. Prepare the sample by removing (f ile, grind and polish) scale, oxide f ilms, pits, variations and foreign material that may affect the reading. The surface should be f lat, of one thickness and no bludge should be opposite the indentation. NOTE Do not perform test closer than 1/8″ from edge of specimen to assure accurate reading. b. Select the proper anvil and penetrator and place proper weight on the weight pan. c. Check trip lever for proper location. Lever should be located in the OFF LOAD position. d. Place the test specimen on the anvil and by turning the hand wheel, raise it slowly (do not crash) until contact is made with the penetrator. On the older model continue turning until pointer of the indicator has made three revolutions and is within f ive divisions (plus or minus) of the upright position. On the newer model af ter contact, continue turning hand wheel until the small pointer is nearly vertical and slightly to right of the dot. Then watching the long pointer, raise specimen until long pointer is approximately upright within three degrees (plus or minus) of C-0. K the C=+3 degrees position is overshot, lower the specimen and start over. When the pointer is within three divisions of C-0, set dial to zero. Af ter this step is complete, the minor load has been applied. e. Apply the major load by tripping the trip lever. Trip the lever, do not push. f. When the trip lever comes to rest and there is no further movement of pointer, return lever to the original position and read the hardness number indicated by the dial. When dial pointer indicates a fraction, use next lower whole number for the reading. 8-12. All hardness tests should be made on a single thickness to obtain accurate results. In testing curved specimens, the concave side should face the indentor; if reversed, an inaccurate reading will result due to f latening of the piece on the anvil. Specimens that do not balance on the anvil because of overhang should be properly supported to obtain accurate readings and to prevent damaging the penetrator. Also to obtain a true indication of hardness of a given part, several readings (3-6 is usually suff icient) at different points should be taken and averaged. If it is necessary to determine the condition of the interior, parts should be cut by some method that does not appreciably change the temper/ condition, such as using a water-cooled saw-off wheel. When testing clad material; the clad coat shall be removed. Specimen samples of clad and other materials should be provided when possible. It is not desirable to accomplish the test on the f inished part. 8-2 T.O. 1-1A-9 Table 8-1. Hardness Conversion Chart 8-3 T.O. 1-1A-9 working order before making any test. The table on which the Rockwell tester is mounted must be rigid and not subject to any vibration if accurate results are to be obtained. 8-14. The accuracy of the Rockwell hardness tester should be checked regularly. Test blocks are available for testing all ranges of hardness. If the error in the tester is more than ±2 hardness numbers, it should be re-calibrated. The dashpot should be checked or oil and properly adjusted for completion of travel. The ball indentor and diameter should also be checked regularly for bluntness and chipping and replaced as required. 8-15. VICKERS PYRAMID HARDNESS TEST. The Vickers pyramid hardness test(Figure 8-4) covers a normal range of loading from 2.5 to 127.5 kilograms. However, for special applications such as the hardness testing of thin, sof t materials, loads as low as 50 to 100 grams may be used. This test is made by pressing a square base diamond indentor into a f lat surface of the metal being tested by the application of known pressure. The indentation lef t by the indentor is a square, the diagonal of which remains the hardness of the metal. The diagonal of the square impression is measured by a microscope which reads directly to 0.001 millimeters on a large micrometer drum. With the standard pyramidal diamond indentor (Figure 8-5) having an angle of 136o between opposite face of the pyramid, the pyramidal hardness number is determined by dividing the applied load in kilograms by the pyramidal area of the impression in square millimeters by the formula, Hardness 1.854 applied load in kilograms square of the diagonal of impression or from correlation tables accompanying the tester. Rapid readings may be taken by means of three knife edges in the f ield of the eye-piece. The f irst knife edge is f ixed; the second knife is movable through a micrometric screw connected to a counter. The third knife edge, moved by means of a special screw, may be used if rapid reading of values to specif ied limits is desired. This method of testing is highly f lexible and permits testing for very high hardness values. In the Amsler-Vickers variation of this hardness tester the surface of the material to be tested, at which the indentor contacts may be thrown on a ground-glass screen directly in front of the operator, allowing the length of the diagonals to be read directly. Figure 8-1. Brinell Hardness Tester 8-13. The Rockwell testers are equipped with various anvils and indentors. Typical anvils and attachments are shown in Figure 8-3. The anvil(s) should be properly selected to accomplish the job. The tester should also be properly set and in good 8-4 Rockwell Hardness Tester 8-5 . 1-1A-9 Figure 8-2.T.O. the speed of rotation being controlled by a piston and dashpot of oil. Table for supporting the metal to be tested. View the impression of the indentation in the form of a square in the f ield shown by the eyepiece. c. The load is fully applied. the whole is rotated by a weight attached to a f lexible cable. weight and drum. e. f. Swing the microscope (10) into place until locked. 1-1A-9 Figure 8-3. A medium-power compound microscope for measuring the indentation across the diagonal of a square. Attachments for Rockwell Tester 8-16. c. A frame containing a control in which a plunger moves up and down vertically under the inf luence of a cam which applies and releases the test load. 8-17. The cam is mounted on a drum and when the starting handle is depressed. Depress the load trip level (8) applying the load. f. b. d. Place the test piece (6) on the testing table (5) and turn the table elevating wheel (1) until the indentor (7) fails to contact the metal being tested. Vickers Tester. drum and weight to their original positions. The Vickers tester consists of the following major parts: a.T. returns the cam. A lever with a 20 to 1 ratio through which a load is applied through a rod to an indentor at the end of a tube moving up and down in a vertical position. the indentor is automatically released. Lower the testing table by reversing the table elevating wheel. 8-6 . a. A foot pedal. The test is applied as follows (See f igure 8-4): CAUTION Sudden contact of the indentor and the material under test should be avoided to prevent possible injury to the diamond point. Prepare the sample by smooth grinding or polishing to remove all scratches and variations that may affect the readability of the indentation. Making The Vickers Test. which when depressed. The tripper also released the lever for load applications.O. the time being determined by the rate at which oil is allowed to bleed out of the dashpot. Elevate the indentor by turning the wheel. which supports the beam during the return of the cam. A tripper. e. b. d. The mechanism provides for a slow and diminishing rate of application for the last portion of the load. The duration of the load application is f ixed by the manufacturers at 10 to 30 seconds. thus cocking the mechanism and preparing the instrument for another test. T. 1-1A-9 Figure 8-4. Vickers Pyramid Hardness Tester 8-7 .O. while the micrometer-controlled knife edge is adjusted to correspond to the minimum hardness or larger dimension. A base. 8-8 .T. by means of the centering screws (13) to a point where it touches the lef t hand f ixed knife edge. Figure 8-5. If the right hand corner of the impression appears between the second and third knife edges. h. Standard Pyramid Diamond Indentor g. The Shore scleroscope is not a precision instrument as the others discussed in preceding paragraphs. SHORE SCLEROSCOPE HARDNESS TEST. Adjust the right hand movable knife edge by means of the micrometric screw connected to the counter until it touches the right hand corner of the impression. the material has the proper hardness for the range desired. Bring the lef t corner of the impression. The Scleroscope Tester. the height of the rebound must be measured directly on the scale of the machine. mounted to the base and containing the cylindrical diamond point hammer. Testing hardness with the scleroscope consists of dropping a diamond tipped hammer upon the test specimen from a def inite height and measuring the rebound produced.O. provided with leveling screws. 1-1A-9 8-18. 8-19. while on another the amount is indicated on a dial. It is used to give approximate values for comparative hardness readings. A vertical glass tube. This is moved by means of special screws to correspond to the smaller dimension or maximum hardness. end a clamping arrangement to hold the sample to be tested. it is only necessary when taking readings to set the f ixed knife edge to the lef t hand corner of the impression in the usual way. Where specif ied hardness limits are desired the third knife edge is used. The counter (15) will then show an ocular reading which is transposed to the Vickers pyramid numeral by use of correlation tables accompanying the tester. When the settings of the second and third knife edges are made. Figure 8-6. Shore Scleroscope b. The tester (Figure 8-6) consists of the following major parts: a. In one type of tester. In this technical order. The type R1 test specimen is circular in cross section and is used for bars. For this test. visible through the glass tube. When an extensometer is required to determine elastic properties.60%). Diameter of the reduced section may be smaller at center than at ends. dimensions C and L may be modif ied. a.T. 8-20. For more detailed information. Effective decarburization is any measurable loss of carbon content which results in mechanical properties below the minimum acceptable specif ications for hardened materials. The tensile strength shall be determined by dividing the maximum load on the specimen during a tension test by the original crosssectional area of the specimen. (See Figure 8-7. For the purpose of tensile testing implied by this technical order this type of setting would apply to determining the mechanical properties desired in a material. refer to Federal Test Method Standard No. b. (1) The ends of the reduced section shall not differ in width by more than 0. 8-21. publications giving detailed measurements must be consulted. hardness and chemical.O. only the hardness method is covered. Prepare the test specimen as described for the Brinell and Rockwell tests in preceding paragraphs and clamp it on the base. for determining the height of the rebound. 1-1A-9 c. c. (3) When material is over 2 inches thick. (See f igure 8-6). TESTING WITH THE SCLEROSCOPE. When precise measurements are required. Decarburization is the loss of carbon at the surface of ferrous materials which have been heated for fabricating. Raise the hammer (5) by squeezing and releasing the bulb (6) d. or when heated to modify mechanical properties. The microscopic method is suff iciently accurate for most annealed and hot rolled material for small amounts of decarburization in high carbon (over 0. high hardness steels. and castings. 8-23. etc. (2) The ends of the specimen shall be symmetrical with the center line of the reduced section within 0. TENSILE TESTING. The hardness method is insensitive in this case. and an average reading taken to reduce visual error. A suction heat and bulb for lif ting and releasing the hammer. Level the instrument by means of the adjusting screws (1). 8-22. welding. DECARBURIZATION MEASUREMENT.. R4.) This does not exclude the use of other test specimens for special materials or forms of material.10 inch. c. and R5 are circular in cross-section and are used for material of dimensions insuff icient for type R1. e. 8-9 . The most common methods used to measure decarburization are microscopic. e. R3. A scale. The test is made as follows: a. b. the following test specimens are listed. forgings. Release the hammer by again squeezing the bulb and observing its rebound. 151. plates. Several tests should be made at different points of a specimen. heavy-walled tubing. This is done by raising the lever (3) inserting the sample and exerting the pressure on the clamping shoe (4). shapes. The terms tension test and compression test are usually taken to refer to tests in which a prepared specimen is subjected to a gradually increasing load applied axially until failure occurs . machine to 3/4 inch or use type R1 test specimen. In all cases the percentage of elongation shall be based on dimension G. d. and recourse must be taken to chemical analysis. rods. A magnif ier hammer with a larger contact area is supplied for use with extremely sof t metals. Types R2.004 inch. The level position is determined by means of the plumb rod (2). Difference shall not exceed 1% of diameter at ends. The f ile method is of ten suitable for detecting decarburization of hardened materials during shop processing. Decarburization of base metal that will not harden to RC60 can not be detected by this method unless specially prepared f iles are used. These steps should be ground at pre-determined depths below the surfaces. The step grind procedure is essentially the same as the taper grind. a shallow taper is ground through the case.T.O. 8-24. Base metals expected to harden above RC60 and found to be f ile sof t are probably decarburized. and of suff icient areas to allow several hardness readings on each f lat. it is recommended that it be hardened by quenching from heating equipment under conditions which avoid further change in carbon distribution. For the taper grind procedure. 8-25. The extent and severity of any decarburization detected by this method should be verif ied by either of the other methods. 8-26. except that hardness 8-10 . HARDNESS METHOD. readings are made on steps which are known distances below the surface. Taper or Step Grind . Rockwell Scales. but not for accurate measurement. and hardness measurements are made along the surface. 1-1A-9 Table 8-2.The specimen containing the surface on which decarburization is to be measured is prepared so that it can be manipulated on a Rockwell superf icial or Vickers hardness tester. The angle is chosen so that readings spaced equal distances apart will represent the hardness at the desired increments below the surface of the case. Loads and Prefix Letters SCALE PREFIX LETTERS A B* C* D E F G H K L M P R S V INDENTOR/PENETRATOR Diamond 1/16 in Steel Ball Diamond Diamond 1/8 in Ball 1/16 in Ball 1/16 in Ball 1/8 in Ball 1/8 in Ball 1/4 in Ball 1/4 in Ball 1/4 in Ball 1/2 in Ball 1/2 in Ball 1/2 in Ball MAJOR LOAD KILOGRAMS 60 100 150 100 100 60 150 60 150 60 100 150 60 100 150 DIAL NUMBERS Black Red Black Black Red Red Red Red Red Red Red Red Red Red Red * Most Commonly Used Scales. If the specimen is not in the hardened condition. 1-1A-9 Figure 8-7. Test Specimens 8-11 .O.T. 2 99.T.5 100. Approximate Hardness .4 113.6 119.4 116.3 120.9 102.4 109.8 120.8 100.2 115.8 116.6 115.8 107.3 112.9 117.1 108.1 111.7 109.O.8 113.9 110.0 104.2 119.0 114.5 98.5 110.3 130.10mm Ball Steel Ball 717 701 686 671 656 642 628 613 600 584 574 561 548 536 524 512 500 488 476 464 453 442 430 419 408 398 387 377 367 357 347 337 327 318 309 301 294 286 279 272 265 259 253 247 241 235 230 225 Tensile Strength 1000 lb per sq in.7 102.9 283 273 264 256 246 237 231 221 215 208 201 194 188 181 176 170 165 160 155 150 147 142 139 136 132 129 126 123 120 118 115 112 110 107 8-12 .2 101. 1-1A-9 Table 8-3.1 106.5 107.7 105.5 117.1 118.Tensile Strength Relationship of Carbon and Low Alloy Steels Rockwell C 150 Kg Load 67 66 65 64 63 62 61 60 59 58 57 56 55 54 53 52 51 50 49 48 47 46 45 44 43 42 41 40 39 38 37 36 35 34 33 32 31 30 29 28 27 26 25 24 23 22 21 20 B 100 Kg Load 1/16 Ball Vickers Diamond Pyramid 50 Kg Load 918 884 852 822 793 765 740 717 694 672 650 630 611 592 573 556 539 523 508 493 479 465 452 440 428 417 406 396 386 376 367 357 348 339 330 321 312 304 296 288 281 274 267 261 255 250 245 240 Tungsten Carbide Ball 820 796 774 753 732 711 693 675 657 639 621 604 588 571 554 538 523 508 494 479 465 452 440 427 415 405 394 385 375 365 356 346 337 329 319 310 302 293 286 278 271 264 258 252 246 241 236 231 Brinell3 300 Kg Load .4 105. 121.7 112. 6 91.8 91.1 97.5 94.5 84.10mm Ball Steel Ball 220 215 210 206 201 197 193 190 186 183 180 177 174 171 168 165 162 160 158 154 150 145 140 136 131 127 122 117 113 108 104 100 96 92 87 83 79 76 72 68 64 60 57 53 50 Tensile Strength 1000 lb per sq in.5 79 77.2 90. 1-1A-9 Table 8-3.2 95.5 76 74 72 70 68 66 64 61 58 55 51 47 44 39 35 30 24 20 11 0 Vickers Diamond Pyramid 50 Kg Load 235 231 227 223 219 215 211 207 203 199 196 192 189 186 183 179 177 173 171 167 162 157 153 149 143 139 135 129 125 120 116 112 108 104 99 95 91 88 84 80 76 72 69 65 62 Tungsten Carbide Ball 226 222 218 214 210 206 202 199 195 191 187 184 180 177 174 171 169 165 163 159 153 148 144 140 134 130 126 120 116 111 107 104 100 95 91 86 83 80 76 72 67 64 61 57 54 Brinell3 300 Kg Load .7 89 88.4 92. Approximate Hardness . 104 103 102 100 99 97 95 93 91 90 89 88 87 85 84 83 82 81 80 78 76 74 72 70 68 66 64 62 60 58 56 54 52 50 48 46 44 42 40 38 36 34 32 30 28 8-13 .5 87 86 85.5 96.5 83.Tensile Strength Relationship of Carbon and Low Alloy Steels .3 87.9 94.O.1 93.T.2 82 80.3 89.Continued Rockwell C 150 Kg Load 19 18 17 16 15 14 13 12 11 10 9 8 7 6 5 4 3 2 1 0 B 100 Kg Load 1/16 Ball 98.9 96. A discontinuity will interrupt this f ield. NONDESTRUCTIVE INSPECTION METHODS. Any marked change in acoustic properties. Cutting speeds in all machining operations shall be such that no burning takes place to cause alteration of the chemical composition of the test metal. interpretation of the radiograph will indicate defects or damage.O. Method 112. All penetrant inspections shall be accomplished in accordance with T. CHEMICAL ANALYSIS. Examination of the ref lections on a cathode ray tube will reveal discontinuities in the material. Discontinuities are visible due to color contrast between the magnetic particles and the background surface. such as a f law or interface in the material. Magnetic particle inspection is accomplished by inducing a magnetic f ield into the material being inspected. The pulser in the ultrasonic instrument sends an electrical impulse to a piezoelectric material in the search unit (transducer). An eddy current is the circulating electrical current induced in a conductor by an alternating magnetic f ield. Method III. Magnetic particle inspection is used to detect discontinuities in ferromagnetic materials. 8-31. 33B-1-1 and MIL-STD-410. Eddy current inspection is used to detect discontinuities in materials that are conductors of electricity. Samples shall be so selected as to be representative of the entire quantity of metal under inspection. Discontinuities in the material being tested cause variations in the induced eddy current.O. It is accomplished by treating the inspection area with a f luid (penetrant) that penetrates the surface discontinuity. The result of spectrochemical analysis shall be determined to the number of decimal places shown in the chemical requirements for the material.T.I of Federal Method Standard 151A is the controlling document for chemical analysis. All ultrasonic inspections shall be accomplished in accordance with T. 8-32. 1-1A-9 8-27. Chemical analysis methods are those in which the elements present in metals are determined by the use of reagents in solution. Spectrochemical analysis includes all methods in which measurements of electromagnetic radiations produced by a sample metal are employed to determine the chemical composition. SPECTROCHEMICAL ANALYSIS. ref lects the sound back to the transducer. All eddy current inspections shall be in accordance with T.O. MIL-STD-453. creating north and south poles which will attract magnetic particles applied to the material. Drilling.O. All radiographic inspections shall be accomplished in accordance with T. Only f luorescent penetrants are approved for Air Force use. and MIL-STD-410. 8-34. The transducer changes the electrical impulse into mechanical vibrations (sound) and transmits them into the material being inspected. Discontinuities are visible due to color contrast between the penetrant drawn out and the background surface. or other lubricants. The test coil measures the variations which reveal discontinuities in the material. milling and other machining operations for sample metal shall be performed without the use of water. 8-28. 8-30. oil. and cutting speeds shall be such that no burning takes place to cause alternation of the chemical composition of the test metal. Surplus penetrant remaining on the surface is removed and an absorbent material (developer) is applied to the surface.O.1 of Federal Test Method Standard 151A governs this type of analysis. and MIL-STD-410. Radiographic inspection will show internal and external structural details of all types of parts and materials. by combustion methods. 8-33. Penetrant inspection is a nondestructive inspection method that is used to detect discontinuities open to the surface of nonporous material. 33B-1-1. MIL-I-8950. It is accomplished by passing penetrating radiation (usually X or gamma rays) through the part or assembly being inspected to expose a f ilm. Sample metal from any piece shall be such that it represents as nearly as possible the metal of the entire piece. All penetrant inspection materials shall conform to MIL-I-25135.O. 33B-1-1 and MIL-STD-410. 8-29. 33B-1-1. 8-14 . or by other none-mission methods. principally iron and steel. Af ter developing. The developer acts as a blotter and draws some of the penetrant from the discontinuity to the surface. Ultrasonic inspection uses a high frequency sound wave to detect discontinuities in materials. All magnetic particle inspections shall be accomplished in accordance with T. 33B-1-1 and MIL-STD-410. which is produced by a small test coil in contact with or close to the material being inspected. 9-12. number of parts. 9-8. Loading and unloading a cold oven is possible without further lowering the temperature. 9-11. with tolerances included for practical use. Parts that are prone to distortion during heat treatment shall be properly supported and temperature raised gradually by steps. 9-5. All cadmium plate shall be stripped from parts (SPOP 21) and cadmium plated detail parts shall be removed from assemblies prior to subjecting the part or assemblies to any furnace temperature in excess of 500oF (260oC). At temperatures above 500oF (260oC). martensitic stainless steel. Cycles with A suff ix are recommended for this purpose. A cold oven is def ined as any oven where the temperature is not over 500oF (260oC). GENERAL. Some typical material applications are listed in Table 9-1 for general guidance only. Cooling of these parts shall also be done gradually. Inconel 713 (PWA 655) Cobalt alloys: Stellite 31 (AMS 5382). as AMS 6322 and AMS 6415. 9-10. 9-4. stress alloying of molten cadmium will occur with potentially harmful results on the base materials. Heat parts and an uncoated. 459-2 6. However. c. Optimum temperatures are given for each cycle. Controlled atmosphere ovens are not required for heat treatment operations unless specif ied for a particular part. 5A STR STR STR STR 456 457 458-1. 1A Type* STR SPOP No. as Type 410 (AMS 5504 and AMS 5613) and Greek Ascoloy (AMS 5508 and AMS 5616) Aluminum Inconel X Nickel alloys: B-1900 (PWA 663 and PWA 1455). Time required at each specif ied temperature begins only af ter all sections of parts have reached that temperature. 4A 5. 455-1. Coat f ixturing at part contact points and threaded details with PMC 2264 boron nitride coating prior to installing part and before heat treatment. Remove coating from parts using applicable stripping procedure. MAR-M509 (PWA 647) Greek Ascoloy (AMS 5508 and AMS 5616) (martensitic stainless steel) 2 3 4. Parts that are not prone to distortion during heat treatment may be loaded into and withdrawn from a hot oven. 9-6.O. SPECIAL HEAT TREATMENT INFORMATION.T. 9-3. vapor blasted test panel of the same material as the parts at 1075o ±25oF (579o ±14oC) for 45 to 75 minutes in air. Typical Heat Treatment Application Cycle No. WI-52 (PWA 653). 1. it is best to hold to basic temperatures listed. Temperature and time are the most critical factors in heat treatment. Cycle for which an alloy type is listed may not necessarily be specif ied for that material. 1-1A-9 SECTION IX HEAT TREATMENT 9-1. CADMIUM PLATED PARTS. A uniform color match between the part and the test piece will indicate complete removal of the coating. 9-2. Table 9-1. 9-9. 9-7. 6A STR 460-1. and furnace input capacities. 455-2 Possible Alloy Application Low alloy steel. 458-2 459-1. 460-2 9-1 . TINT TEST FOR DETERMINING COATING REMOVAL FROM NICKEL BASE AND COBALT BASE ALLOYS. Perform test as follows: a. b. Furnace operator shall make allowance for size of part. HASTELLOY X (AMS 5536. as AMS 5596. as AMS 5660 and AMS 5661 HASTELLOY X (nickel alloy) Nickel alloy: HASTELLOY X (AMS 5536 and AMS 5754) Cobalt alloys: STELLITE 31 (AMS5382). AMS 5706. AMS 5706. 465 466 467 468 470 480 481 Possible Alloy Application Waspaloy. AMS 5707. AMS 5731. HASTELLOY W Cobalt alloys: STELLITE 31 (AMS 5382). 12A 13 14 15 17 20 21 Type* STR STR STR STR PRE STR STR PRE PRE SOL SOL SPOP No. AMS 5772. as AMS 5525. and PWA 1042). L-605 (AMS 5537 and AMS 5759) Nickel alloys: Inconel 600 (AMS 5540 and AMS 5665). AMS 5754. Haynes 188 (AMS 5608. and AMS 5663 17-7PH (stainless steel . as AMS 5544. HASTELLOY N. as Types 310. and AMS 5663 22 STR 482 101 102 103 104 105 106 SOL SOL STA PRE SOL SOL 761 762 763 764 765 766 9-2 . and AMS 5709 Waspaloy (nickel alloy). AMS 5662. Nimonic 75 (PWA 673) (nickel alloy). AMS 5707. Haynes 188 (AMS 5608. AMS 5708.austenite conditioning). AMS 5662. Udimet 700 Inconel 600 (nickel alloy). as AMS 5596. 316. and AMS 5709 Inconel 718 (nickel alloy). welded with AMS 5680 (Type 347 stainless steel) A-286 (modif ied Tinidur) stainless steel. as AMS 5544. and AMS 5707 Waspaloy (nickel alloy). and AMS 5737 Incoloy 901 (nickel alloy). Type 430 (ferritic stainless steel). and 347 Titanium Inconel 718 (nickel alloy). AMS 5732. as AMS 5596. 7 8 9 11 12. AMS 5772. Inconel 625 (AMS 5599 and AMS 5666). 461 455-3 459-3 464 471.O. 1-1A-9 Table 9-1.T. and PWA 1042). AMS 5706. welded with Type 430 f iller metal Type 430 (ferritic stainless steel). as AMS 5596. and AMS 5707 Waspaloy (nickel alloy). stainless steel. AMS 5662. AMS 5706. as AMS 5544.Continued Cycle No. and PWA 1038). Typical Heat Treatment Application . L-605 (AMS 5537 and AMS 5759). and AMS 5663 Inconel 718 (nickel alloy. AMS 5708. 321. MAR-M509 (PWA 647) Waspaloy (nickel alloy). 4930.. oil mist. SPS 27. Inconel X-750. TITANIUM ALLOY PARTS. 9-16. 4935. OR PRECIPITATION HEAT TREATMENT. SOLUTION. a. or PS 240) at 180o to 200oF (82o to 93oC) for 1 to 4 minutes maximum. 1262). etc. 9-14. SPS 12. Refer to Section V. then dip rinse in cold water. SPS 25. and any other contaminants by wiping with a clean. Rinse in hot PMC 1737 deionized water at 150o to 200oF (66o to 93oC). Air dry. hard. The thin. blue-gray oxide coating sometimes occurring on titanium alloy surfaces and unaffected by this cleaning procedure is harmless in this respect and may be disregarded. Otherwise. 4954. SPS 7. 1215.Continued Cycle No.T. . f ingerprints. grease. 1-1A-9 Table 9-1. Typical Heat Treatment Application . and AMS 5663. Parts fabricated of these titanium alloys may be stress-relieved in air only to 1015o±15oF (546o±8oC). do not use compressed air. 10 Type* PRE SPOP No. At any higher temperatures. Protect eyes and skin from contact. See Cycles 1 and 1A. NOTE Parts shall be immersed only long enough to obtain optimum results. and breathing passages. provide adequate ventilation. dust. AMS 5670. c. WARNING Alkaline rust remover causes burns. such as dirt. Pressure rinse over tank with cold water. NOTE AMS 4901 and 4921 are the only commercially pure titanium material types used widely in the fabrication of P&W engine parts.O. lint-free cloth dampened with methyl ethyl ketone TT-M-261 or acetone O-A-51. AMS 5662. and wear protective clothing. Soak in alkaline rust remover (SPS 2. SPS 5. WARNING Methyl ethyl ketone (MEK) is f lammable and harmful to eyes. e. 4928. Virtually all other titanium materials used are titanium alloys and are subject to these instructions. certain impurities that may be present on the parts during the heating cycle could cause stress alloying of the parts. All titanium alloy parts shall be cleaned by the following procedure prior to stress-relief. 4956. as AMS 5598. Immediately af ter completing step d. protect the parts from all contamination. NOTE Since only light f ilms of oil or grease will be removed by the cleaning solution. 4967. d. and AMS 5671 * PRE = Precipitation SOL = Solution STA = Stabilization STR = Stress-relief 9-13. as AMS 5596. Type 6A1-4V Titanium Alloy Parts (AMS 4911. Keep ignition sources away. b. it is essential that as much surface contamination as possible be removed before immersing parts into the cleaning solution. and PWA 1213. 9-3 . 767 Possible Alloy Application Nickel alloys: Inconel 718. CLEANING. 9-15. dirt. Use clean white gloves for all handling. GENERAL. . Cover parts with clear plastic sheet or store them in clear plastic bags until furnace or other operation is begun. following with a cold water pressure rinse. an inert atmosphere shall be used regardless of any contrary instructions stipulated in a particular repair. for solution make-up. Remove any visible concentrations of oil. STABILIZATION. skin. 471 465 468 470 480 481 761 762 763 764 765 766 767 Peak Temp. 9-18. or precipitation heat treatment is applied to a given part. (3) In retort furnace. as necessary. type of heat treatment. and maximum temperature are listed in Table 9-2. Precipitation heat treatment is a selected temperature and duration that produces benef icial hardening in certain alloys. GENERAL. (4) In pit furnace. by shutting off heat and maintaining atmospheric f low rates. by removing parts from furnace and cooling in room temperature still air. by removing retort from furnace and fan cooling. It does not mean to quench in a liquid. Cross-Index for Solution. AIR COOL OR FASTER is def ined as cooling not less than 40oF (22oC) per minute to 1100oF (593oC) and not less than 15oF (8oC) from 1100o to 1000oF (538oC). 9-21. When a sequence of solution. (1) In vacuum furnace. AIR COOL is def ined as rate of cooling of part obtained by removing that part from furnace at prescribed temperature and allowing it to cool in room temperature still air. Replication and metallurgical examination may be necessary to verify whether f ixturing and cooling rate are adequate to obtain desired microstructure and prevent cracking. a. (2) In protective atmosphere furnace. by cycle or SPOP number. 12 12A 15 17 20 21 101 102 103 104 105 106 107 Type Precipitation Precipitation Precipitation Precipitation Solution Solution Solution Solution Stabilization Precipitation Solution Solution Precipitation SPOP No. The cooling cycle. 9-4 . Solution heat treatment Cycles 20 and 21 are used for various HASTELLOY X parts. are thus precipitated into the grain boundaries of parts fabricated of HASTELLOY X material and subjected for long periods to temperatures of 1200o to 1700oF (649o to 927oC). therefore. Table 9-2. stabilization. Long-time exposure to high temperature engine operating environment causes precipitation of carbides into the grain boundaries. b. The solution treatment dissolves these carbides and puts them back into metallic solution. by force cooling in protective atmosphere. Stabilization heat treatment is maintaining a part at a selected temperature long enough to rearrange the atoms into an improved structure.O. particularly chromium carbides. or Precipitation Heat Treatments Cycle No. various temperatures are used. It is sometimes referred to as Aging. Stabilization. SPOP number. 9-19. Solution heat treatment of material (particularly HASTELLOY X) is performed to improve ductility and weldability prior to resizing and repair. shall be rapid enough to maintain carbides or precipitation hardeners in solution. Carbides. The expressions AIR COOL and AIR COOL OR FASTER mean that parts shall be cooled quickly enough to prevent metal structure changes that can happen in certain alloys if cooling is too slow. oF(oC)* 1350 1350 1325 1450 2050 2150 1825 1825 1550 1400 1750 1750 1325 (732) (732) (718) (788) (1121) (1177) (996) (996) (843) (760) (954) (954) (718) * (disregarding tolerance) 9-23. Circulating fans may be used. or Age Hardening. Def inition has been broadened to include the following situations. Cycle number. 9-22. but f ixturing may be required if distortion is a problem. The f inal condition obtained is a combined effect of this sequence. 1-1A-9 9-17. 9-20. Reference to these cycles will be made in the repair instructions..T. However. and temperature raised and lowered stepwise. Hydrogen cleaning removes oxides from all surfaces. Step cycles shall not be used for solution heat treatments. The benef icial properties derived from this lower temperature treatment could be lost permanently if subjected to a temperature higher than 1800oF (982oC). or air are acceptable atmospheres. Heat part to 2150o ±25oF (1177o ±14oC) and hold for 7 to 10 minutes. including those diff icult to clean mechanically. The specif ic cycle required will be included in the repair procedure. unless otherwise directed by a specif ic repair procedure. CAUTION Do not use this cycle for solution heat treating PWA 1038 HASTELLOY X material. for stress-relief. and to some extent. Air cool or faster. 1-1A-9 NOTE These cycles apply only to the repair of HASTELLOY X parts that require using one of the following solution heat treatments. argon. NOTE Hydrogen. Parts that are susceptible to distortion during heat treatment shall be adequately supported. however. Perform as follows: NOTE This is a short-term precipitation (aging) heat treatment for INCONEL 718 or other part material specif ied in engine publication. Perform as follows: manufacture. Air cool or faster. a. The benef icial properties derived from this lower temperature treatment could be lost permanently if subjected to a temperature higher than 1800oF (982oC).O. The Suff ix A following a cycle number indicates a stepwise cycle. when solution treating is to be followed by weld repair that requires complete prior removal of oxides. 9-27. This material was solution treated at 1950oF (1066oC) at its 9-5 . or air are acceptable atmospheres. argon. stabilization. Refer to cautions in solution heat treat cycles. This material was solution treated at 1950oF (1066oC) at its manufacture. 9-24. CYCLE 21 (SPOP 481). b. For other HASTELLOY alloys. The following solution. NOTE Hydrogen. 9-25. CYCLE 12 (SPOP 471). or precipitation heat treatment cycles apply primarily to certain age-hardenable alloys such as WASPALOY and INCONEL materials. hydrogen is preferred because of its characteristic and benef icial cleaning action over the entire part. NOTE These cycles apply only when specif ically invoked in repair procedures in engine publications. solution heat treat shall be performed in accordance with Cycle 20 (SPOP 480). Heat part to 2050o ±25oF (1121o ±14oC) and hold for 7 to 10 minutes. and to some extent. b. from the inside of cracks to be welded. when solution treating is to be followed by weld repair that requires complete prior removal of oxides. Hydrogen cleaning removes oxides from all surfaces including those diff icult to clean mechanically.T. from the inside of cracks to be welded. Perform as follows: CAUTION Do not use this cycle for solution heat treating PWA 1038 HASTELLOY X material. a. and to dissolve precipitated carbides and intermetallics (hardeners). CYCLE 20 (SPOP 480). For regular Hastelloy material. hydrogen is preferred because of its characteristic and benef icial cleaning action over the entire part. solution heat treat shall be performed per this cycle unless otherwise directed by a specif ic repair procedure. 9-26. Air cool to room temperature. Remove retort from furnace and cool with forced argon to 1000oF (538oC) in no longer than 18 minutes. 9-28. or vacuum. e. Heat to 1825o ±25oF (996o ±14oC) using lower thermocouple for controlling. a. 9-30. Place part in cold oven. Air is an acceptable atmosphere. b. Hold at 1350oF (732oC) for 4 hours. Heat to 600oF (316oC) and hold for 30 minutes. b. g. Cool to 1200o ±15oF (649o ±8oC) at approximately 100oF (56oC) per hour. including cool-down time from 1350oF (732oC). Hold at temperature for 2 hours unless otherwise specified. Place part in oven and heat to 1350o±15oF (732o±8oC). CYCLE 102 (SPOP 762). CYCLE 17 (SPOP 470). c. including cool-down time from 1350oF (732oC). Purge retort at approximately 150 CFH argon until dew point reaches -40oF (-40oC) or lower at retort exhaust. or a blend of hydrogen and argon. are acceptable atmospheres. NOTE This is a solution heat treatment using an argon atmosphere. Increase to 1000oF (538oC) and hold for 30 minutes. Hold at temperature for a total of 3 hours.O. Perform as follows: NOTE This is a short-term precipitation (aging) heat treatment for INCONEL 718 or other part material specif ied in engine publication. c. Heat part to 1325o ±25oF (718o ±14oC) and hold for 4 hours. c. a. Hold at temperature for a total of 3 hours.T. CYCLE 12A (SPOP 465). 9-31. a. Heat part to 1325o ±15oF (718o ±8oC) and hold for 14 hours. Place part with thermocouples in retort. d. Cool to 500oF (260oC) at a rate equivalent to air cool. Increase to 1350o ±15oF (732o ±8oC) and hold for 4 hours. b. and seal retort. Heat part to 1450o ±15oF (788o ±8oC) and hold for 4 hours. c. Cool to 1200o ±15oF (649o ±8oC) at approximately 100oF (56oC) per hour. 9-32. d. then complete cooling with argon or air. Perform as follows: CAUTION Heating or cooling rate between 1000oF (538oC) and 1850oF (1010oC) shall be at least 40oF (22oC) per minute to prevent cracking and to control aging characteristics. b. 1-1A-9 a. Air cool to room temperature. a. d. Insert retort into furnace. f. Perform as follows: 9-6 . CYCLE 15 (SPOP 468). Perform as follows: NOTE Hydrogen. 9-29. Cool at a rate equivalent to air cool. Perform as follows: NOTE Heating and cooling rates are optional. Increase to 1200oF (649oC) and hold for 30 minutes. Air cool. Increase to 800oF (427oC) and hold for 30 minutes. d. Do not exceed 1850oF (1010oC) on higher thermocouple. b. CYCLE 101 (SPOP 761). e. argon. h. NOTE Furnace may initially be set higher than 1850oF (1010oC). using lower thermocouple for controlling. NOTE Furnace may initially be set higher than 1775oF (968oC). c. Perform as follows: 9-7 . a. c. CYCLE 106 (SPOP 766). in order to satisfy cooling rate requirement. Perform as follows: CAUTION Heating or cooling rate between 1000oF (538oC) and 1775oF (968oC) shall be at least 40oF (22oC) per minute to prevent cracking and to control aging characteristics. Insert retort into furnace. Place part in cold furnace. d. Perform as follows: b. b. b.T. 9-34. 9-36.3oC) for 4 hours. at retort exhaust. Cool at required rate using forced argon.O. Air cool. argon. in furnace. Purge retort at approximately 150 CFH argon until dew point reaches -40oF (-40oC) or lower. Hold at temperature for 2 hours unless otherwise specified. or vacuum. a. Heat to 1750o ±25oF (954o ± 14oC). e. Place part in cold furnace. d. NOTE This is a solution heat treatment using vacuum. c. Place part with thermocouples in retort. c. a. b. NOTE This is a precipitation heat treatment using air. . CYCLE 105 (SPOP 765). Do not exceed 1850oF (1010oC) on higher thermocouple. 1-1A-9 CAUTION Heating or cooling rate between 1000oF (538oC) and 1850oF (1010oC) shall be at least 40oF (22oC) per minute to prevent cracking and to control aging characteristics. then complete cooling with argon or air. Do not exceed 1775oF (968oC) on higher thermocouple. 9-35.010 torr range or lower. Evacuate to 0. NOTE This is a solution heat treatment using an argon atmosphere. Heat to 1825o ±25oF (996o ±14oC) using lower thermocouple for controlling. Furnace system shall provide for argon forced cooling. with thermocouples. a. CYCLE 104 (SPOP 764). and seal retort. . Perform as follows: NOTE This is a stabilization heat treatment using air. CYCLE 103 (SPOP 763). argon. Static leak rate shall not exceed 50 microns per hour.009 torr or lower. Heat cycle shall be completed in the 0. NOTE Furnace may initially be set higher than 1850oF (1010oC). or vacuum. Place part. Remove retort from furnace and cool with forced argon to 1000oF (538oC) in no longer than 16 minutes.3oC) for 16 hours. 9-33. Heat to 1400o ±15oF (760o ±8. Air cool. Hold at temperature for 1 hour unless otherwise specif ied. Heat to 1550o ±15oF (843o ±8. Heat to 1325o ±15oF (718o ±8. NOTE On certain parts. Furnace cool at a rate not to exceed 100oF (56 C) per hour to 1150o ±15oF (621o ±8. c. Heat to 1750o ±25oF (954o ±14oC). CAUTION The required stress-relief (Cycle 1 or 1A) af ter welding or brazing Type 410 or Greek Ascoloy materials eliminates the brittleness in the joint areas. experience has indicated that stress-relief is not required. The Suff ix A following a cycle number indicates a stepwise cycle. GENERAL.O. as necessary. Place part in cold furnace. Do not exceed 1775oF (968oC) on higher thermocouple. NOTE Parts may require a cycle different from one of the following. . Evacuate to 0.T. This will result in cycle being included in specif ic repair procedure. d.3oC). To avoid cracking. 9-39. This permissible omission will be included in appropriate manual repair section for such parts. 9-41. 9-40. Heat cycle shall be completed in the 0.3oC) for 8 hours. Static leak rate shall not exceed 0. and temperature raised and lowered stepwise. Reference to these cycles will be made. in order to satisfy cooling rate requirement. a.05 torr per hour. NOTE Local stress-relief of engine parts following minor repairs is authorized only if procedure has been developed to be compatible with applicable parts. NOTE This is a solution heat treatment using vacuum. . Perform as follows: NOTE This is a precipitation heat treatment using air or argon. c. 1-1A-9 CAUTION Heating or cooling rate between 1000oF (538oC) and 1775oF (968oC) shall be at least 40oF (22oC) per minute to prevent cracking and to control aging characteristics. Air cool. material. o . 9-38. STRESS-RELIEF AFTER WELDING. Furnace system shall provide for argon forced cooling. parts shall be handled carefully until stress-relief is accomplished. NOTE Furnace may initially be set higher than 1775oF (968oC). and is approved by the cognizant engineering authority. d. CYCLE 107 (SPOP 767). b. and operating environment. a. Parts that are susceptible to distortion during heat treatment shall be adequately supported. Hold at temperature for 1 hour unless otherwise specif ied. SPOP number. in furnace. size. Cool at required rate using forced argon. The following stress-relief cycles are used throughout manual for various parts. using lower thermocouple for controlling. .010 torr range or lower. hold for 8 hours. Parts that have been repaired by fusion welding shall ordinarily be stressrelieved.009 torr or lower. by cycle or SPOP number. with thermocouples. b. Cycle number. 9-8 . 9-37. Place part. and maximum temperature are listed in Table 16-3. Cross-Index for Stress-Relief Heat Treatments Cycle No. e. Cool to 500oF (260oC) not faster than 100oF (56 C) every 15 minutes. 455-1 455-2 456 457 458-1 458-2 459-1 459-2 460-1 460-2 461 455-3 459-3 464 466 467 482 Peak Temp. c. 9-43. CYCLE 5 (SPOP 459-1). CYCLE 1 (SPOP 455-1). f. 9-44. c. Increase to 1015o ±15oF (546o ±8oC) and hold for 2 hours.T. 1 1A 2 3 4 4A 5 5A 6 6A 7 8 9 11 13 14 22 SPOP No. Heat part to 1600o±25oF (871o ±14oC) and hold for 2 hours. 9-46. d. Perform as follows: a. 9-45. temperature may be raised and cooled gradually in accordance with Cycle 4A. Heat to 600oF (316oC) and hold for 30 minutes. e. o b. b. CYCLE 2 (SPOP 456). Heat to 600oF (316oC) and hold for 30 minutes. b. d. Increase to 1100oF (593oC) and hold for 30 minutes. 9-47. 9-48. CYCLE 4 (SPOP 458-1). Heat part to 350o ±10oF (177o ±6oC) and hold for 1 hour. Put part in cold oven. Cool to 500oF (260oC) not faster than 100oF o (56 C) every 15 minutes. CYCLE 4A (SPOP 458-2). Heat to 600oF (316oC) and hold for 30 minutes. Increase to 800oF (427oC) and hold for 30 minutes. Increase to 1300oF ±25oF (704o ±15oC) and hold for 2 hours. 9-9 . Perform as follows: a. Increase to 900o ±15o(482o ±8oC) and hold for 4 hours.. Increase to 800oF (427oC) and hold for 30 minutes. d. Heat part to 1015oF ±15oF (546o ±8oC) and hold for 2 hours.O. Perform as follows: Put part in cold oven. 1-1A-9 Table 9-3. a. Put part in cold oven. Other cycles are permissible provided stressrelief requirement of 1300o ±25oF (704o ±14oC) for 2 hours is met. use Cycle 1A as an alternate. CYCLE 3 (SPOP 457). NOTE To minimize distortion. NOTE To minimize distortion. oF(oC)* 1015 1015 350 900 1300 1300 1600 1600 1050 1050 1500 1010 1600 1150 1400 1500 1800 (546) (546) (177) (482) (704) (704) (871) (871) (566) (566) (816) (543) (871) (621) (760) (816) (982) * (disregarding tolerance) 9-42. Heat part to 1300o ±25oF (704o ±14oC) and hold for 2 hours. CYCLE 1A (SPOP 455-2). Cool to 500oF (260oC) not faster than 100oF (56oC) every 15 minutes. Other cycles are permissible provided stress-relief requirement of 1015o ±15oF (546o ±8oC) for 2 hours is met. c. Increase to 1050o ±15oF (566o ±8oC) and hold for 2 hours. Perform as follows: a. Other cycles are permissable provided stress-relief requirement of 1600o ±25oF (871o ±14oC) for 2 hours is met. b. 9-10 . c. Air cool. CYCLE 6 (SPOP 460-1). NOTE A protective atmosphere is suggested. c. Air cool.5 microns mercury. b. Increase to 1000oF (538oC) and hold for 30 minutes. Previously designated Cycle 10. CYCLE 22 (SPOP 482). Cool to 500oF (260oC) not faster than 100oF (56 C) every 15 minutes. Perform as follows: CAUTION . Increase to 800oF (427oC) and hold for 30 minutes. b. CYCLE 7 (SPOP 461). e. temperature may be raised and lowered gradually in accordance with Cycle 5A. Cool to 500oF (260oC) not faster than 100oF (56 C) every 15 minutes. Heat part to 1150o ±15oF (621o ±8oC) and hold for 1 hour. Furnace cool at a rate of 50oF (28oC) per hour to 1100o (593oC). Increase to 1300oF (704oC) and hold for 30 minutes. Heat to 600oF (316oC) and hold for 30 minutes. Put part in cold oven. Heat to 600oF (316oC) and hold for 30 minutes. Perform as follows: a. 9-57. b. CYCLE 13 (SPOP 466). Heat part to 1500oF ±25oF (815o±14oC) and hold for 4 hours. CYCLE 9 (SPOP 459-3).T. 9-58. a vacuum of 0. CYCLE 6A (SPOP 460-2). e. CYCLE 8 (SPOP 455-3). Increase to 1010oF (543o±8oC) and hold for 30 minutes. CYCLE 5A (SPOP 459-2). Heat part to 1500o ±25oF (816o ±14oC) and hold for 30 minutes. Other cycles are permissible provided stressrelief requirement of 1050o ±15oF (566o ±8oC) for 2 hours is met. 9-53. air or argon may be used. or shorter heat treatment at higher temperature may be required by engine publication for certain parts. Perform as follows: a. NOTE To minimize distortion. Heat part to 1050o ±15oF (566o ±8oC) for 2 hours. CYCLE 14 (SPOP 467). Heat part to 1600o ±25oF (871o ±14oC) and hold for 1 hour. o c. Heat to 700oF (371oC) and hold for 30 minutes. Perform as follows: a. 9-51. Put part in cold oven. 9-49. or argon or helium with a dew point no higher than -60oF (-51oC) shall be used. Increase to 800oF (427oC) and hold for 30 minutes. Put part in cold oven. NOTE For materials other than titanium. d. 1-1A-9 NOTE To minimize distortion. b. Longer heat treatment at specif ied temperature. maximum.O. b. then air cool or faster. Increase to 1600o ±25oF (871o ±14oC) and hold for 2 hours. CYCLE 11 (SPOP 464). Perform as follows: a. e. d. Cool to 500oF (260oC) not faster than 100oF (56 C) every 15 minutes. o a. f. or faster. o 9-54. temperature may be raised and lowered gradually in accordance with Cycle 6A. 9-52. Heat part to 1400o ±25oF (760o ±14oC) in air and hold for 2 hours. . d. 9-56. For titanium parts. 9-55. 9-50. Air cool. Local stress-relief methods are def ined in the following paragraphs. Heat part to 1800o ±25oF (982o ±14oC) and hold for 1 hour. or replacement of small detail parts. and part blended to original contour. hydrogen is preferable because of its cleaning action on oxides and impurities diff icult to clean mechanically. NOTE Hydrogen. unless otherwise specif ied in applicable engine technical orders. Following the cycle. a. 9-62. Heaters consist of nichrome wire elements insulated with ceramic f iber and contained within a f lexible wire jacket. usually without disassembly. LOCAL STRESS-RELIEF. c. 9-59. CAUTION Thermocouples shall not be tack welded to titanium parts. Resistance blankets and quartz lamps can be used to 1350oF (732oC). GENERAL. which will produce electrical arcing. temperature requirement. as within cracks or cavities. Typical applications include small weld repair of holes or bosses. Local stress-relief is the application of a heat treatment cycle. Temperature can be controlled by pulsing lamp on and off. These components are woven into a thermal blanket. thermocouples are broken or ground off.O. Elaborate f ixturing is avoided when stress-relieving minor areas of large components. and accessibility. door assemblies. local stressrelief provides signif icant cost and time savings. 9-60. Choice of method depends upon size and shape of joint. Approval for local stress-relief is governed in part by accessibility. 9-68. Supplementary f lexible heaters may be added to ensure that adjacent parts do not conduct heat away in such a manner as to make heat distribution non-uniform. Exhaust gases can produce harmful surface reaction. 9-69. Induction. Radiant lamp provides intense infrared heat. Local stress-relief is especially useful when applied to parts on a mounted or partly disassembled engine. 9-11 . however. 9-61. using a portable heating system. 9-64. Thermocouples shall be located every 2 inches of area that is to be stressrelieved. Stress-relief duration and temperature shall be the same as for a corresponding furnace heat treat. part conf iguration. Typical applications include inlet guide vanes. 9-65. this step may be omitted for thin sheet metal parts. vacuum. argon. 1-1A-9 CAUTION Parts shall be thoroughly cleaned before entering oven.T. Coils shall be insulated from metal contact. Place part in cold oven. which shall be held in close contact with surface to be stress-relieved. induction heaters and radiant gas burners can be used to 1825oF (996oC). Resistance Induction Quartz lamp CAUTION Gas burner shall not be used to stress-relieve titanium parts. 9-67. and conf iguration and material of part. when heat treatment is to be followed by weld repair. Besides avoiding disassembly. which can be easily directed toward part being stress-relieved. with a water-cooled copper induction coil of suff icient number of turns to be positioned over entire area to be heat treated. Gas burner radiant heater. b. 9-71. 9-70. c. accessory housing. or air are acceptable atmospheres. to a part that has been weld repaired. DESCRIPTION OF METHODS. 9-63. such as a welded patch. Requirements include a high frequency generator. exhaust struts. intermediate cases. Quartz Lamp. d. however. Temperature prof ile shall be monitored with tack welded thermocouples to provide accurate readout for manual or automatic control during heat treat cycle. and thrust reversers. Resistance. b. 9-66. Typical local stress-relief methods include the following: a. Radiant gas burners are fueled with a mixture of air and natural gas. Heat treat of several areas can be accomplished simultaneously. Good heating patterns and temperature control are permitted by using as burners. Radiant Gas Burner. Exhaust gases can produce harmful surface reaction.T.O. 9-12 . 9-72. 1-1A-9 CAUTION Gas burner shall not be used to stress-relieve titanium parts. O. 13 51 18 33 56 4 83 5 35 48 55 20 6 58 17 24 27 -29 66 68 63 9 64 31 32 79 72 2 67 1 49 53 77 26 36 57 82 3 71 12 25 80 42 ELEMENT SYMBOL ATOMIC NO.T. 60 10 28 7 76 8 46 15 78 84 19 59 91 8 86 75 45 37 44 62 21 34 14 47 11 38 16 73 52 65 81 90 69 50 22 74 92 23 54 70 39 30 40 Aluminum Al Antimony Sb Argon A Arsenic As Barium Ba Beryllium Be Bismuth Bi Boron B Bromine Br Cadmium Cd Cesium Cs Calcium Ca Carbon C Cerium Ce Chlorine Cl Chromium Cr Cobalt Co Columbium (Niobium) Cb(Nb) Copper Cu Dysprosium Dy Erbium Er Europium Eu Fluorine F Gadolinium Gd Gallium Ga Germanium Ge Gold Au Hafnium Hf Helium He Holmium Ho Hydrogen H Indium In Iodine I Iridium Ir Iron Fe Krypton Kr Lanthanum La Lead Pb Lithium Li Lutecium Lu Magnesium Mg Manganese Mn Mercury Hg Molybdenum Mo Neodymium Nd Neon Ne Nickel Ni Nitrogen N Osmium Os Oxygen O Palladium Pd Phosphorus P Platinum Pt Polonium Po Potassium K Praseodymium Pr Protactinium Pa Radium Ra Radon(radium emanation) Rn Rhemium Re Rhodium Rh Rubedium Rb Ruthenium Ru Samarium Sm Scandium Sc Selenium Se Silicon Si Silver Ag Sodium Na Strontium Sr Sulphur S Tantalum Ta Tellurium Te Terbium Tb Thallium Tl Thorium Th Thulium Tm Tin Sn Titanium Ti Tungsten W Uranium U Vanadium V Xenon Xe Ytterbium Yb Yttrium Yo Zinc Zn Zirconium Zr A-1 . 1-1A-9 APPENDIX A SUPPLEMENTAL DATA Table A-1. Chemical Symbols ELEMENT SYMBOL ATOMIC NO. 021 0.85 65 0.076771 0. 1.104 0.096 0.035433 0.5 39 38 2.129921 1/64 0.127952 0.073 0.082877 0.033464 0.35 42 3/32 2.098 0.7 36 2.95 5/64 47 2.032 0.086614 0.5 53 1.9 64 63 0.4 41 2.086 0. OR LTR 80 79 DECIMALS OF AN INCH 0.125984 0. OR LTR 51 DECIMALS OF AN INCH 0.15 56 3/64 1.033 0.O.0935 0.75 50 1.080708 0.04 0.02 0.037401 0.055 0.024 0.035 0.1015 0.125 0.110236 0.15 44 2.102362 0.1065 0.042 0.85 49 1.1 2.0 60 59 1.05 46 45 2.0135 0.090551 0.074803 0.088582 0.089 0.041 0.25 30 3.2 1.4 1.07874 0.55 74 0.0 2.116 0.037 0.8 34 33 2.75 7/64 35 2.114173 0.094488 0.0785 0.067 0.0995 0.057086 0.8 67 66 0.7 70 69 0.25 1.068897 0.3 A-2 .0225 0.07 0.0465 0.018 0.023622 0.025 0.106299 0.09375 0.113 0.078125 0.070866 0.059055 0.015625 0.1 1/8 3.092519 0.055118 0.T.031496 0.052 0.021653 0.3 55 1.95 62 61 1.041338 0.7 DRILL SIZE NO. DRILL SIZE NO.03937 0.039 0.6 37 2.096456 0.036 0.9 32 3.098425 0.2 3.45 40 2.0 31 3.1285 0.043307 0.0595 INCH Mm.2 2.066929 0.9 48 1.65 71 0.02925 0.084645 0.11 0.076 0.0145 0.35 54 1.11811 0.45 1.4 78 77 0.25 43 2.049212 0.12 0.082 0.027559 0.6 73 72 0.75 68 1/32 0.072834 0.046875 0.3 2.1 1.111 0.05 58 57 1.019685 0.108267 0.081 0.047244 0.043 0.5 76 75 0.045275 0.03125 0.038 0.051181 0.15748 0.122047 0.029527 0.031 0.109375 0.026 0.8 1. Decimal Equivalents INCH Mm.02559 0. 1-1A-9 Table A-2.053149 0.028 0.016 0. 8 7.149606 0.161417 0.263779 0.234375 0.181102 0.062992 0.246062 0.4 DRILL SIZE NO.0 O 8.8 12 11 4.240157 0.177 0.154 0.242 0.302 0.27559 0.191 0.322834 0.2 19 4.265625 0.159 0.55 1.15748 0.147 0.0 J 7.272 0. 1-1A-9 Table A-2.161 0.192913 0.318897 0.234 0.18 0.257 0.259842 0.25 A-3 .7 4.165354 0.1405 0. Decimal Equivalents .0 21 20 4.203125 0.2 5 5.T. OR LTR 29 DECIMALS OF AN INCH 0.2 7.199 0.204724 0.1875 0.303149 0.137795 0.277 0.185 0.305117 0.3 18 11/64 17 4.255905 0.279527 0.635 0.173228 0.238 0.144 0.1 4.1 7 13/64 6 5.187007 0.206692 INCH Mm.5 F 6.291338 0.285432 0.141732 0.295 0. 3.31496 0.136 0.9 I 7.266 0.171875 0.166 0.1 K 9/32 7.246 0.7 26 3.6 DRILL SIZE NO.5 28 9/64 A 15/64 6.283464 0.1935 0.19685 0.9 10 9 5.323 3.307086 0.173 0.2 P E 52 1.6 N 7.8 24 3.271653 0. 1.316 0.167322 0.281 0.299212 0.1695 0.177165 0.06496 0.0625 0.204 0.65 3.157 0.Continued INCH 1/16 Mm.3 1/4 6.2 D 6.145669 0.200787 0.153543 0.9 23 5/32 22 4.287401 0.251968 0.75 H 6.6 27 3.6 G 6.196 0.1495 0.296875 0.0 B 6.5 19/64 7.7 17/64 6.0 8 5.140625 0.4 16 4.25 0.9 5/16 8.4 M 7.188976 0.4 6.189 0.3 L 7.133858 0.201 0.267716 0.25 4.28125 0.O.169291 0.8 6.185039 0.248031 0.23622 0.75 3/16 4.75 25 3.295275 0.2055 0.265747 0.182 0.29 0.147637 0.75 7.5 15 4.25 7.15625 0.061023 0.311023 0.261 0.6 14 13 4.3125 0.244094 0.1 8.25 6.152 0. OR LTR DECIMALS OF AN INCH 0.7 7.1 C 6. 5 0.4 3 5.6 9.O.344487 0.362204 0.368 0.2 9.3 U 9.35433 0.728345 0.216535 0.389763 0.209 0.4 Q 8.5 31/32 25.0 61/64 24.75 9.3 DRILL SIZE NO.5 27/64 11. Decimal Equivalents .828125 0.3937 0.8 S 23/32 18.86614 0.Continued INCH Mm.5 55/64 22.82677 0.383857 0.859375 0.5 25/32 20.531495 INCH Mm.370078 0.4 9.7874 0.7 11/32 8.875 0.34375 0.71875 0.0 X Y 13/32 Z 10.953125 0.96875 0.75 1 5.348 0. OR LTR 4 DECIMALS OF AN INCH 0.0 63/64 1 A-4 .338582 0.413 0.385826 0.228 0.5 1/2 13.0 51/64 20.0 3/4 49/64 19.232283 0.359375 0.375 0.90625 0.0 53/64 27/32 21.377 0.964565 0.0 29/32 59/64 23.358 0.0 5.9375 0.4375 0.94488 0.5 7/32 5.377952 0.5 13/16 21.364172 0.7 9. 5.220472 0.890625 0.9 25/64 10.51181 0.413385 0.452755 0.0 7/16 11.6 2 5.T.515625 0.339 0.0 31/64 12.9 9.374015 0.326771 0.5 8.74803 0.208661 0.796875 0.984375 1.5 57/64 23.212598 0.386 0.75 8.5 29/64 15/32 12.366141 0.358267 0.21875 0.484375 0.7 5.1 23/64 9.328125 0.765625 0.221 0.925195 0.5 3/8 V 9.421875 0.846455 0.390625 0.78125 0.492125 0.46875 0.346456 0.98425 0.324802 0.885825 0.84375 0.5 47/64 19.332 0.6 R 8.47244 0.25 8.350393 0.0 T 9. 1-1A-9 Table A-2.40625 0.8 5.397 0.5 15/16 24.226377 0.5 21/64 8.8 W 9.767715 0.224409 0.90551 0.807085 0.53125 0.228346 0.9 8.213 0.43307 0.404 0.342519 0.25 9.334645 0.330708 0.381889 0.75 0.734375 0.921875 0.8125 0.453125 0.3 DRILL SIZE NO. OR LTR DECIMALS OF AN INCH 0. 8.0 7/8 22.0 33/64 17/32 13. T.O. 1-1A-9 Table A-2. Decimal Equivalents - Continued INCH 35/64 Mm. 14.0 DRILL SIZE NO. OR LTR DECIMALS OF AN INCH 0.546875 0.55118 0.5625 0.570865 0.578125 0.59055 0.59375 0.609375 0.610235 0.625 0.62992 0.640625 0.649605 0.65625 0.66929 0.671875 0.6875 0.688975 0.703125 0.70866 INCH Mm. DRILL SIZE NO. OR LTR DECIMALS OF AN INCH 9/16 14.5 37/64 15.0 19/32 39/64 15.5 5/8 16.0 41/64 16.5 21/32 17.0 43/64 11/16 17.5 45/64 18.0 A-5 T.O. 1-1A-9 Table A-3. Engineering Conversion Factors LENGTH 1 1 1 1 1 1 1 1 inch = 2.54 Centimeters = 0.0833 Foot = 0.0278 Yard foot = 0.305 Meter = 0.333 Yard yard = 0.914 Meter = 3 Feet Rod = 16 1/2 Feet = 5 1/2 Yards Mile = 1.609 Kilometers = 5280 Feet = 1760 Yards Centimeter = 0.3937 Inch = 0.0328 Foot Meter = 39.37 Inches = 3.281 Feet = 1.094 Yards Kilometer = 1000 Meters = 3280.83 Feet = 1093.61 Yards = 0.62137 Mile AREA 1 1 1 1 1 1 1 1 1 Sq. Inch = 6.452 Sq. Centimeters Sq. Foot = 144 Sq. Inches = 929.032 Sq. Centimeters Sq. Yard = 1296 Sq. Inches = 9 Sq. Feet = 0.836 Sq. Meter Sq. Rod = 272 1/4 Sq Feet = 30 1/4 Sq. Yards Acre = 43,560 Sq. Feet = 160 Sq. Rods Sq. Mile = 640 Acres Sq. Centimeter = 0.155 Sq. Inch Sq. Meter = 1550 Sq. Inches = 10.764 Sq. Feet = 1.196 Sq. Yards Sq. Kilometer = 0.3861 Sq. Miles = 247.104 Acres VOLUME 1 1 1 1 1 1 1 Cu. Inch = 16.39 Cu. Centimeters = 0.00433 Gallons* Cu. Foot = 1728 Cu. Inches = 7.48 Gallons* = 28.317 Liters = 0.037 Cu. Yards Cu. Yard = 27 Cu. Feet = 0.7646 Cu. Meter = 202 Gallons* Cu. Centimeter = 0.001 Liter = 0.061 Cu. Inch Cu. Meter = 35.31 Cu. Feet = 1.308 Cu. Yards = 264.2 Gallons* Quart* = 0.25 Gallons* = 57.75 Cu. Inches = 0.946 Liter = 2 Pints* Gallon* = 0.832702 Imperial Gallon = 231 Cu. Inches = 0.1377 Cu. Feet = 3.785 Liters = 3785 Cu. Centimeters 1 Gallon, Imperial = 1.20091 U.S. Gallons 1 Barrel (Std.) = 31 1/2 Gallons 1 Barrel (Oil) = 42 Gallons *U.S. Measure WEIGHT 1 1 1 1 1 1 1 Ounce = 16 Drams = 437.5 Grains = 0.0625 Pound = 28.35 Grams = 0.9155 Ounce (Troy) Pound = 16 0unces = 453.593 Grams = 0.453593 Kilogram Ton (Short) = 2000 Pounds = 907.185 Kilograms = 0.892857 Long Ton = 0.907185 Metric Ton Ton (Metric) = 2204.62 Pounds = 0.98421 Long Ton = 1.10231 Short Tons Ton (Long) = 2240 Pounds = 1016.05 Kilograms = 1.120 Short Tons = 1.01605 Metric Tons Gram = 15.43235 Grains = 0.001 Kilogram Kilogram = 2.20462 Pounds COMPOUND UNITS 1 1 1 1 gram per square millimeter kilogram per square millimeter kilogram per square centimeter kilogram per square meter = = = = = 1.422 pounds per square inch 1.422.32 pounds per square inch 14.2232 pounds per square inch 0.2048 pound per square foot 1.8433 pounds per square yard A-6 T.O. 1-1A-9 Table A-3. Engineering Conversion Factors - Continued COMPOUND UNITS (Cont) 1 1 1 1 1 1 1 1 1 1 1 kilogram meter kilogram per meter pound per square inch pound per square foot pound per square foot pound per cubic inch pound per cubic foot kilogram per cubic meter foot per second meter per second meter per second = = = = = = = = = = = 7.2330 foot pounds 0.6720 pound per foot 0.07031 kilogram per square centimeter 0.0004882 kilogram per square centimeter 0.006944 pound per square inch 27679.7 kilograms per cubic meter 16.0184 kilograms per cubic meter 0.06243 pound per cubic foot 0.30480 meter per second 3.28083 feet per second 2.23693 miles per hour MULTIPLES Circumference of Circle Area of Circle Area of Triangle Surface of Sphere Volume of Sphere Area of Hexagon Area of Octagon ENGINEERING UNITS 1 Horsepower = 33,000 foot pounds per minute 550 foot pounds per second 746 watts 0.746 kilowatts 1 Horsepower Hour = 0.746 Kilowatt hours 1,980,000 foot pounds 2,545 heat units (B.T.U) 1 Kilowatt = 1,000 watts 1.34 horsepower 737.3 foot pounds per second 44.240 foot pounds per minute 56.9 heat units (B.T.U) per minute 1 kilowatt Hour = 1,000 watt hours 1.34 horsepower hours 2,655,220 foot pounds 3,412 heat units (B.T.U) 1 British Thermal Unit = 1,055 watt seconds 778 foot pounds 0.000293 kilowatt hour 0.000393 horsepower hour 1 Watt = 1 joule per second 0.00134 horsepower 3.3412 heat units (B.T.U.) per hour 0.7373 foot pounds per second 44.24 foot pounds per minute = Diameter X 3.1416 = Square of Diameter X 0.7854, or Square of Radius X 3.1416, or Square of Circumference X 0.07958 = Base X one-half altitude = Circumference X diameter, or Square of diameter X 3.1416 = Surface X one-sixth diameter, or Cube of diameter X 0.5236 = Square of Diameter of Inscribed Circle X 0.866 = Square of Diameter of Inscribed Circle X 0.828 A-7 T.O. 1-1A-9 The following weights are approximate and variations must be expected in practice. Table A-4. Bars-Flat Size Lbs Per Linear Ft 1/2 x 1 .......................................0.578 1/2 x 2 .......................................1.174 3/4 x 2 .......................................1.7604 3/4 x 3 .......................................2.6408 1 x 2 ..........................................2.3472 1 x 3 ..........................................3.5208 1 1/2 x 2 ....................................3.5208 1 3/4 x 3 1/2..............................7.1883 2 x 3 ..........................................7.0416 2 3/4 x 4 ..................................12.9096 3 x 4 ........................................14.350 Bars-Hexagon Size Lbs Per Linear Ft 3/8 .............................................0.147 7/16 ...........................................0.20 1/2 .............................................0.262 9/16 ...........................................0.331 5/8 .............................................0.409 3/4 .............................................0.639 1 ................................................1.047 1 1/4 ..........................................1.620 1 1/2 ..........................................2.340 Rods-Round Size Lbs Per Linear Ft 3/16 ...........................................0.032 1/4 .............................................0.058 5/16 ...........................................0.090 3/8 .............................................0.129 7/16 ...........................................0.176 1/2 .............................................0.230 9/16 ...........................................0.291 5/8 .............................................0.360 11/14 .........................................0.435 3/4 .............................................0.518 13/16 .........................................0.608 7/8 .............................................0.705 15/16 .........................................0.809 1 ................................................0.921 1 1/4 ..........................................1.439 1 3/8 ..........................................1.741 1 1/2 ..........................................2.072 1 3/4 ..........................................2.820 2 ................................................3.683 2 1/2 ..........................................5.755 2 3/4 ..........................................6.964 3 ................................................8.287 3 1/2 ........................................11.550 4 ..............................................15.200 Sheets Thickness Lbs Per Sq Ft .0126 .........................................0.1797 .016 ...........................................0.2253 .020 ...........................................0.2817 .0253 .........................................0.3570 .032 ...........................................0.4501 .0359 .........................................0.5055 Table of Weights - Aluminum and Aluminum Alloy .0403 .........................................0.5676 .0508 .........................................0.7158 .0641 .........................................0.9026 .0808 .........................................1.1382 .0907 .........................................1.2781 .128 ...........................................1.8099 .156 ...........................................2.202 .1875 .........................................2.6481 .250 ...........................................3.5215 .375 ...........................................5.2822 .500 ...........................................7.212 Tubing-Round Size Lbs Per Linear Ft 1/4 x .028 ..................................0.025 1/4 x .032 ..................................0.027 1/4 x .035 ..................................0.03 1/4 x .049 ..................................0.036 1/4 x .058 ..................................0.044 1/4 x .065 ..................................0.047 5/16 x .025 ................................0.027 5/16 x .028 ................................0.032 5/16 x .035 ................................0.039 5/16 x .065 ................................0.061 3/8 x .025 ..................................0.033 3/8 x .028 ..................................0.037 3/8 x .035 ..................................0.0435 3/8 x .042 ..................................0.053 3/8 x .049 ..................................0.063 7/16 x .035 ................................0.054 7/16 x .049 ................................0.075 1/2 x .032 ..................................0.056 1/2 x .035 ..................................0.063 1/2 x .042 ..................................0.073 1/2 x .049 ..................................0.086 1/2 x .065 ..................................0.11 9/16 x .032 ................................0.067 5/8 x .035 ..................................0.08 5/8 x .042 ..................................0.093 5/8 x .049 ..................................0.11 5/8 x .058 ..................................0.13 5/8 x .065 ..................................0.14 11/16 x .049 ..............................0.105 3/4 x .035 ..................................0.096 3/4 x .049 ..................................0.1245 3/4 x .058 ..................................0.15 3/4 x .065 ..................................0.17 3/4 x .083 ..................................0.21 13/16 x .032 ..............................0.095 13/16 x .049 ..............................0.13 7/8 x .028 ..................................0.09 7/8 x .035 ..................................0.11 7/8 x .049 ..................................0.16 15/16 x .032 ..............................0.11 15/16 x .049 ..............................0.17 15/16 x .083 ..............................0.27 1 x .032 .....................................0.12 1 x .035 .....................................0.13 1 x .042 .....................................0.16 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 2 1 2 2 2 2 2 2 x .049 .....................................0.18 x .058 .....................................0.210 x .065 .....................................0.23 x .083 .....................................0.29 1/16 x .032.............................0.13 1/16 x .083 .............................0.31 1/8 x .035..............................0.15 1/8 x .049..............................0.20 1/8 x .058..............................0.24 1/8 x .065..............................0.27 3/16 x .083 .............................0.35 1/4 x .035..............................0.16 1/4 x .049..............................0.2134 1/4 x .058..............................0.27 1/4 x .065..............................0.30 1/4 x .083..............................0.37 5/16 x .083 .............................0.39 3/8 x .032..............................0.17 3/8 x .049..............................0.25 3/8 x .058..............................0.29 3/8 x .065..............................0.33 3/8 x .083..............................0.41 3/8 x .120..............................0.58 7/16 x .095 .............................0.48 1/2 x .035..............................0.19 1/2 x .049..............................0.27 1/2 x .058..............................0.32 1/2 x .065..............................0.36 1/2 x .083..............................0.45 5/8 x .065..............................0.39 5/8 x .125..............................0.72 11/14 x .095...........................0.58 3/4 x .035 ...............................0.23 3/4 x .049 ...............................0.32 3/4 x .065 ...............................0.3934 3/4 x .083 ...............................0.53 3/4 x .125 ...............................0.79 x .042 .....................................0.29 7/8 x .049 ...............................0.34 x .049 .....................................0.36 x .065 .....................................0.48 x .083 .....................................0.61 x .125 .....................................0.92 1/4 x .025 ...............................0.2052 1/2 x .065 ...............................0.61 Tubing-Streamline Size Lbs Per Linear Ft 1.500 x .250 x .020...................0.082 1.500 x .375 x .020...................0.085 1.625 x .375 x .025...................0.115 1.875 x .375 x .035...................0.16 2.00 x .875 x .049....................0.27 2.01563 x .375 x .025...............0.12 2.625 x .375 x .035...................0.22 3.00 x .375 x .035....................0.25 3.125 x .375 x .032...................0.25 3.350 x 1.50 x .065...................0.61 4.0625 x 1.71 x .065.................0.73 A-8 T.O. 1-1A-9 Table A-5. Bars-Flat Size Lbs Per Linear Ft 1/8 x 1/2 ............................. 0.238 1/8 x 3/4 ............................. 0.358 1/8 x 1 ................................ 0.475 1/8 x 1 3/4.......................... 0.815 1/8 x 2 ................................ 0.935 6/32 x 1 .............................. 0.625 3/16 x 3/4 ........................... 0.535 3/16 x 1 .............................. 0.715 3/16 x 1 1/4 ........................ 0.895 3/16 x 1 1/2 ........................ 1.00 3/16 x 1 3/4 ........................ 1.175 3/16 x 2 .............................. 1.385 3/16 x 2 1/2 ........................ 1.785 3/16 x 3 .............................. 2.055 1/4 x 1 ................................ 0.9575 1/4 x 1 1/8.......................... 1.075 1/4 x 1 1/4.......................... 1.185 1/4 x 1 3/4.......................... 1.585 1/4 x 2 ................................ 1.885 1/4 x 2 1/2.......................... 2.375 1/4 x 3 ................................ 2.815 1/4 x 6 ................................ 5.65 5/16 x 3/4 ........................... 0.957 5/16 x 1 .............................. 1.075 5/16 x 1 1/4 ........................ 1.475 5/16 x 1 1/2 ........................ 1.975 5/16 x 1 3/4 ........................ 2.075 5/16 x 2 .............................. 2.375 5/16 x 2 1/2 ........................ 3.075 5/16 x 3 .............................. 3.875 5/16 x 4 .............................. 5.125 5/16 x 6 .............................. 8.75 3/8 x 1 ................................ 1.285 3/8 x 1 1/4.......................... 1.575 3/8 x 1 1/2.......................... 2.00 3/8 x 1 3/4.......................... 2.275 3/8 x 2 ................................ 2.675 3/8 x 2 1/2.......................... 3.475 3/8 x 3 ................................ 4.175 3/8 x 4 ................................ 5.725 3/8 x 6 ................................ 8.325 1/2 x 1 ................................ 1.795 1/2 x 1 1/2.......................... 2.685 1/2 x 2 ................................ 3.675 1/2 x 2 1/2.......................... 4.675 1/2 x 3 ................................ 5.675 1/2 x 4 ................................ 7.705 1/2 x 6 .............................. 11.10 5/8 x 1 ................................ 2.156 5/8 x 2 ................................ 4.250 3/4 x 1 ................................ 2.875 3/4 x 2 ................................ 5.750 7/8 x 2 1/2.......................... 8.325 1 x 1 1/4 ............................. 4.525 1 x 2 ................................... 7.705 Bars-Hexagon Size Lbs Per Linear Ft 3/16 .................................... 0.1123 1/4 ...................................... 0.1997 5/16 .................................... 0.3120 Table of Weights - Brass 13/16 .................................. 1.913 7/8 ...................................... 2.218 18/14 .................................. 2.546 1 ......................................... 2.897 1 1/8 ................................... 3.667 1 3/14 ................................. 4.086 1 1/4 ................................... 4.527 1 5/16 ................................. 4.991 1 3/8 ................................... 5.478 1 7/16 ................................. 5.987 1 1/2 ................................... 6.519 1 9/16 ................................. 7.073 1 5/8 ................................... 7.651 1 11/16 ............................... 8.250 1 3/4 ................................... 8.873 1 13/14 ............................... 9.518 1 7/8 ................................. 10.19 1 15/16 ............................. 10.88 2 ....................................... 11.59 2 1/4 ................................. 14.67 2 1/2 ................................. 18.11 2 3/4 ................................. 21.91 2 7/8 ................................. 23.95 3 ....................................... 26.08 3 1/2 ................................. 36.75 4 ....................................... 46.93 5 ....................................... 74.25 6 ..................................... 108.25 Sheet Thickness Lbs Per Sq Ft .0031 .................................. 0.1393 .0035 .................................. 0.1564 .004 .................................... 0.1756 .0045 .................................. 0.1972 .005 .................................... 0.2214 .0056 .................................. 0.2486 .0063 .................................. 0.2792 .0071 .................................. 0.3135 .008 .................................... 0.3521 .0089 .................................. 0.3953 .010 .................................... 0.4439 .0113 .................................. 0.4985 .0126 .................................. 0.5598 .0142 .................................. 0.6286 .0159 .................................. 0.7059 .0179 .................................. 0.7927 .0201 .................................. 0.8901 .0226 .................................. 0.9995 .0253 .................................. 1.122 .0285 .................................. 1.260 .032 .................................... 1.415 .0359 .................................. 1.589 .0403 .................................. 1.785 .0453 .................................. 2.004 .0508 .................................. 2.251 .0571 .................................. 2.527 .0641 .................................. 2.838 .072 .................................... 3.187 .0808 .................................. 3.578 .0907 .................................. 4.018 .1019 .................................. 4.512 .1144 .................................. 5.067 3/8 ...................................... 0.4493 7/16 .................................... 0.6115 1/2 ...................................... 0.7987 9/16 .................................... 1.001 5/8 ...................................... 1.248 11/16 .................................. 1.510 3/4 ...................................... 1.797 12/16 .................................. 2.109 7/8 ...................................... 2.446 15/16 .................................. 2.808 1 ......................................... 3.195 1 1/8 ................................... 4.043 1 3/16 ................................. 4.505 1 1/4 ................................... 4.992 1 5/16 ................................. 5.503 1 3/8 ................................... 6.040 1 1/2 ................................... 7.188 1 9/16 ................................. 7.800 1 5/8 ................................... 8.436 1 11/14 ............................... 9.097 1 3/4 ................................... 9.784 1 13/16 ............................. 10.50 1 7/8 ................................. 11.23 1 15/16 ............................. 11.99 2 ....................................... 12.78 2 1/2 ................................. 19.97 3 ....................................... 26.41 Bars-Square Size Lbs Per Linear Ft 3/16 .................................... 0.1297 1/4 ...................................... 0.2306 9/16 .................................... 0.3602 3/8 ...................................... 0.5188 7/16 .................................... 0.7061 1/2 ...................................... 0.9222 5/8 ...................................... 1.441 3/4 ...................................... 2.075 1 ......................................... 3.689 1 1/4 ................................... 5.764 1 1/2 ................................... 8.300 2 ....................................... 14.76 Rods-Round Size Lbs Per Linear Ft 1/16 .................................... 0.01132 3/32 .................................... 0.03625 1/8 ...................................... 0.04527 6/32 .................................... 0.0915 3/16 .................................... 0.1019 7/32 .................................... 0.1475 1/4 ...................................... 0.1811 9/32 .................................... 0.2375 9/14 .................................... 0.2829 11/32 .................................. 0.3480 3/8 ...................................... 0.4074 28/64 .................................. 0.4185 12/32 .................................. 0.4866 7/16 .................................... 0.5546 1/2 ...................................... 0.7243 9/16 .................................... 0.9167 5/8 ...................................... 1.132 11/14 .................................. 1.369 3/4 ...................................... 1.630 A-9 ............ 0.....................0001146 ................... 0......703 1 1/8 x .................... 0.......09547 .................000002884 .......4096 .................. 0...............................7154 9/16 ...........0201 ...0002898 ............8...... 10.....964 1 3/4 x .....................248 2 1/4 x ................................609 1 x ....1443 ... 0....032 ..935 1 1/2 x .............. 1-1A-9 Table A-5.......0113 ............... 0..................................... 0..025 ......065 .2043 ................460 .010 . 0...................058 ......032 . 0..... 0..............4024 1/2 ..1443 .................................................................590 1 5/8 x . 0......... 1...............312 7/8 x ..............................0............... 0.......065 ....05 4 .9983 5/8 ............11...........6102 7/8 x ...0001823 ....0003655 .......065 .... 0........1285 .....267 1 7/8 x ...1. 1.........800 1 1/4 x ...............................4839 ...............................3249 ..... 0...............032 .188 1/2 x ............3648 ................... 0............127 3/8 x ...2576 ...................... 0.................. 0.......... 1.........................................12........ 5..........................162 ...........862 1 1/8 ......................................00 Tubing-Round Size Lbs Per Linear Ft 1/8 x ......0800 ........ 1...681 1 1/4 x ..... 0. 0....729 2 x .. 12.3044 ......................................035 ................162 3/8 x ............................................981 1 3/8 x ............. 0.......8857 ............17.... 1.004 .049 ....16 ...003715 .....162 .........1..................233 7/14 x ..020 ...... 5....... 0... 0.......2..... 0.02994 .......5552 . 0..2576 ..........002 ................................0........ 0...........................................889 7/8 .3..............610 13/14 .......... 0...........032 ............................353 3/4 .................0179 ....049 ......0....... 0..............1819 .........................50 .....0071 ............................................ 0.....00 ............................065 ........ 0...0....052 1/4 x ...............0.0.421 3/4 x ..................... 0....1........0...................................1204 .............40 .........................0285 ..................................032 ..........1............397 7/8 x . 0.2294 .......0031 .........0226 ...0010 .........6....032 .......... 0..... 0..... 0.... 1...........007449 .................78 Sheet Thickness Lbs Per Sq Ft ..........................391 1 x .............0253 ...............1914 .. 0....0.0.75 .....1819 ..032 ...7888 9/16 ............ 0............... 0...... 0...................................065 ................ 0..0907 ....... 0.........028 .....468 Table of Weights ................................. 0.............. 0.......................0. 0..2..............06004 ..................... 6.047 ................45 2 1/8 .......41 .......... 0..... 0............035 ..004 .................................................................................065 ....... 0.................................... 0.......01883 .02375 .............5........................004684 ...................... 0....... 0.........232 3/4 ........................ 0...........................00009092 .............035 1 1/4 .....133 1/2 x .....4096 .................................... 0......114 5/16 x ........................... 0.....035 ....266 3/4 x ...0045 .............. 2.....................998 2 1/2 x ..............032 ...............................002946 ....0508 ............O.................. 0.......................... 0.....0142 .07571 . 0........................................88 3 ............. 0...0005812 .........04471 3/16 .........001469 ..........0571 ...1788 9/16 .........39 ..0089 ............. 0...............Brass .....049 .......763 2 ..042 .......173 1/2 x ............0126 ........035 2 x ......002336 .......104 3/8 x ....... 11..............049 .....04761 ......35.081 1/4 x . 1..75 3 1/2 ..............75 ............ 0...3648 ...............14 ..............643 2 3/8 x ..............410 1 7/14 .................................1019 ................ 0..................00004535 ............. 0..............065 ........ 0........893 1 5/8 x .......471 1 3/8 ..01184 ..........................049 ........455 2 1/4 x ..........Continued .5.................891 1 1/4 x ......0359 . 0......1285 .......028 ..........913 1 1/2 ..220 5/8 x .. 0..........00007210 .049 ..752 1 3/8 x ........... 20.........4.........92 2 1/2 ......... 0.............................001165 ....049 ........... 6.690 ...........................058 ......................4406 ..544 1 1/2 x .....451 1 1/4 x .........................................032 .....210 3/4 x ..................................155 Rods-Round Size Lbs Per Linear Ft 1/8 .285 1 1/4 x .......................00005718 ......1875...........3081 3/8 ..049 ................ 1.............032 .. 0....0002299 .................................................. 0............. 0.........358 1 x .......0453 ... 16.132 1 1/8 x ..... 0............ 0.........012 .................0........034 3/16 x .... 1.008 ..065 .......... 0.......3............................................0009241 .065 .....191 1 . 14............0............020 ........622 1 3/16 ..........2414 ...................................... 0................................134 ....................... 0...200 Wire Size Lbs Per Linear Ft ...438 1 3/4 ....3838 ....................032 ........................0159 .......175 ........... 0...............................0159 ................08 1 5/8 x ....032 ......049 ..............0.......................404 1 1/8 x .....01493 .......065 ... 6...173 1 3/4 x . 0....... 0.......118 11/16 ........... 0.0...........................049 .. Table of Weights ...................2794 3/8 .775 1 .......065 ........010 .....065 .....057 ...1................636 1 3/4 x .....0007328 ............0................................032 ...0063 .................................797 1 1/8 x ......81 .................................... 9....0...................032 ..............460 .........................................1006 1/4 .......049 .................. 0.............035 .............................0004609 ............ 8... 0.......................008 ............................................. 0..................................................................... 1......................4.......005907 .................. 0...................065 ............0254 ...112 3/8 x ..............15 ..567 1 x .....095 .. 0........37 Shim Stock Thickness No...........................................543 1 3/8 x .072 ............3249 ....... 4........6039 1/2 .....1537 1 1/4 x ...............035 ...................00002852 Table A-6.................1.......................875 3 x ..............................024 1/8 x .....115 A-10 . 0....................T.610 1 1/8 x ...................00003596 ......4437 7/16 ............ 0....................032 .............2893 ................................................03776 ........................0056 ...028 ..9275 2 1/2 x .......................716 1 1/8 x ..... ..........0201 ..................831 2 7/8 x ..................................45.Bronze Bars-Hexagon Size Lbs Per Linear Ft 5/16 ..... 0...... 0.....796 2 x ........ 1.............010 ..... Of Ozs Per Sq Ft ................................................................... 0.. 0.0035 ....... 0........................823 1 1/2 x ...389 .....25...009393 .................................................................001853 ..........................................006 .1144 .........012 ................................1518 ......0403 ......049 ............................. 0............ 0.................... 18...0001446 ...... 7......................2893 ........9054 5/8 ............005 .2043 ..........032 ........ 0.......0641 .......2294 ......... 0..........7006 ...........032 .................................1..............065 ......................................... 0....................072 ......049 .... 0........035 ................. 0..............327 5/8 x ......... 1.............327 5/8 x ......... 9................ ..........9646 1/4 x 2 ....076 1/4 x ..202 7/16 x .......................................065 .........................3......134 ..............0............035 ........838 1 1/8 x ......362 3/4 x .........042 ....0......0.....................6602 .......................1...........0.....18..1...........648 1 5/16 x ...........198 1/2 x .......158 7/16 x ...1.....488 3/4 x ................030 1 1/8 ...032 ...........0..................0....042 .................049 ..................0.........194 3/8 x ................................035 ............................1.....0....035 ...0950 ..049 .......................058 .......0....005 ..................0...134 ..............29 1 1/16 x ............929 1/4 x 3 ..............1........................0.12..0....452 7/8 x ..553 1 1/8 x ..................705 7/8 ............049 .....447 3/8 x 2 .................033 1/8 x ................0808 .........................083 ..............................3....0.....049 ............180 5/16 x ...0..1....................894 1/2 x 3/4 .......453 1 1/4 x ......................028 ....................................................1..825 ........517 1 1/4 x ...032 ...........0...............106 3/8 x ..020 .......083 ................065 .304 3/4 x .........489 1 x ...........................006 ...0.......596 9/16 x ...........0..................................................................0..............0.....................9.....................065 3/16 x ............182 1/2 x .0......0.........0..................0.0.............1...........049 ...............737 11/14 x .........................Copper Bars-Flat Size Lbs Per Linear Ft 1/16 x 3/4 ...........0641 .....................................................................065 .................................028 .........................................0....................835 1 1/4 ..............0452 .035 ...0...0.......058 ......2...............0...0..................6567 ..........................075 3/16 x .......0.4823 1/8 x 2 .................083 ....................................................................................................170 ..492 7/8 x .......................4799 .......................035 ...645 9/16 x ............0403 .................0....042 ............0....................0...........................0..............146 9/22 x ...1946 ...245 3/8 x ........044 3/16 x .............035 ....00 13/16 x .......675 Rods-Round Size Lbs Per Linear Ft 1/4 .......065 .032 ....025 .0..............................................................032 .0226 ..................110 5/16 x ....0359 .............0..........049 ...........049 ............0..134 3/8 x .0........411 1 x ........................................0....776 Table of Weights .................................0...........065 ........................032 ........065 .................095 ..............................2.............5827 ...........295 3/8 x ......1...0......0359 .................920 3/4 x ......032 ...........022 ..............................474 1 1/4 x .....0...................................118 3/8 x .....032 ..............5...443 5/8 x .......1...032 ...812 3/4 x ...........................0......0.........27.................929 5/8 x 1 1/2.........................0808 .....................035 ..........410 ..........403 1 1/16 x ...002 ....................331 1 x ......567 1 x ..................02 7/8 x .....................0.................065 .............Bronze .....139 5/16 x ....580 1/2 ...................0..1...498 1 5/16 x ............................9644 .....................3493 ..................................0....................2959 3/8 .Continued ...................554 1/2 x ...............................................641 1 1/8 x ......065 ........0.132 1/4 x .........083 7/22 x ........0.................8637 .......................0.377 1 x ................547 5/8 x ..................042 ...............0.......0...........894 1/4 x 4 ........4.425 1 1/8 x .......0.......7576 5/8 ....................................T........................0.161 1/2 x ...............................1434 ....12 2 1/2 ...............049 .0..............................0201 .......0..... 1-1A-9 Table A-6.....................................0...............................0........049 ......................312 1/2 x ...........................0...320 1 ...344 1/2 x ...........120 1/4 x ....0........................035 .120 ........................................................................ Table Of Weights ..............058 .042 .......................673 3/4 x ..032 ..............026 1/8 x ..............................1.........0..065 ..........2............................................3.............................................2......234 1/2 x .739 1 x ....459 A-11 ..........................576 7/8 x ....049 .......035 ..........109 .....0.............298 5/8 x .072 .......................................0.....085 1/4 x ..2..................196 3/8 x .........2.......0............0...042 ...........251 5/8 x ............0............0907 ...27 Sheet Thickness Lbs Per Sq Ft ..........................0......025 ......0........028 ...0..035 .........032 ......036 1/8 x ................035 ...032 .......122 3/16 x ...............................................716 1 1/4 x .289 7/8 x ..........................542 3/4 x ....................0.......042 ..............125 .............9646 1/4 x 1 .325 7/16 x .1894 9/16 ..297 1 x .........0.....................4261 7/16 .........................................266 9/16 x .................269 1/2 x ................................0....306 9/16 x .....0...........058 ...901 7/8 x .......0126 ....0..............9296 ...........................184 3/4 .....035 ..........0...............158 5/16 x .106 1/4 x ......0............................225 9/16 x ..........9427 Tubing-Round Size Lbs Per Linear Ft 1/8 x .............4....028 ................6....................120 ......................0..................065 ...................735 1 1/2 ........1..582 .425 1/2 x 1 ...0......................937 1 1/4 x ......418 3/4 x .....................................042 ..............0508 ..........................042 .........................281 2 ................................0..088 5/16 x ...............2...............042 ................3...........134 .................0...........0641 ..............................................042 ....................O................032 ...............2914 ...............................03 1 1/4 x ................................704 5/8 x ...........119 5/16 x ...........0.......0...............343 5/8 x ....010 ....049 ..................238 .....0.....3.........................................................171 7/16 x .......042 .....220 3/4 x ......0......328 7/8 x .030 1/8 x ......................120 ......032 ...............049 .......028 .0....0........1.............................................................................055 3/16 x ..................032 .........758 1 3/8 x ..0...........1...........................10 1 x ........095 ...................0907 ..........................032 ..........................0.........0...............097 5/16 x ....0......0.......................................................003 ................................5....................0....028 .......................025 .......... .........................092 1/4 x ......148 ........................061 3/16 x .049 ........759 1 3/16 x .................818 1 3/4 ...1...........0.....................0............231 5/8 x ...................396 13/16 x .....028 ...049 .......0.............065 ......0.................049 .........................0.....050 ........0403 ............0142 ..280 3/4 x ....3...1...........438 1 1/8 x .......0.035 .0.........042 ............858 3/8 x 1 ......98 1 5/16 x ...................025 ........3........028 ............120 ...............................032 ....................028 ................0......0159 ...045 3/16 x ....0.....1809 1/8 x 1 .................0......120 .............049 ......032 ..662 ........7367 ...........567 Table A-7........145 3/8 x ..........0..0.......170 3/8 x ........................1285 .......2312 .........295 1/2 x ......1..................................0......032 ..........................0....0.0.........120 .0571 .........................0.......042 ...1.0.......0.............................207 9/16 x .....................7353 .................................0.025 ..246 3/4 x .120 .0...0............0...........4625 ...................94 3 ..028 ............1.......0..................2......1285 ..........................032 ........0................148 ........0453 .......0.....0253 ...........358 7/8 x ....3................1........................0.......6407 .......0..............................997 .0........0.........232 7/16 x .. ..40 1/8 x 3/4 x 3/4........065 ....................Magnesium and Magnesium Alloy 2 x 3 .......................Iron Angle Size Lbs Per Linear Ft 1 1/16 x 1 x 1......1..........434 5/8 x .....570 3/8 x .................................................6 5/16 x 3 x 3................... Bars-Flat Size Lbs Per Linear Ft 1/2 x 1 .......625 ...........0188 ...........148 ..049 ..........042 .......1..........3....5329 .036 3/8 x ........20........1...........064 .........412 1 .........80 ..........................................16 3/16 x 1 1/4 x 1 1/4 ........037 3/16 ..........129 1/2 ........................ Table of Weights ..75 .......0186 .....4........630 1/16 ................1....757 .049 ......................................0438 ..................................20.........1.................................50.......135 3/4 x 3 ......1......375 ..................0188 ..................................0.....2...............620 5/8 x ..0.....058 3/8 ................0.....................0253 ..0 ...............044 Sheet Thickness Lbs Per Sq Ft 1/32 ..................1.................................0625 ...40.....3.........................0..........1..............................020 ...........1....202 1/4 x ...............................4 .................050 ........................................65 3/16 x 1 x 1..............................................................................510 Rods-Round Size Lbs Per Linear Ft 3/16 .5.....1....745 1/2 x ..............................................................00 ........597 1/2 x .........0..7.........939 5/8 x ........2576 .......0....571 1/2 x ....372 1/2 x 2 ........................................................0...............095 ...................................065 ................Lead ........................................072 ...0.......065 ........1. of Ft Per Lb .........55 .............63.0781 .........31....674 1 1/4 ................12 3/16 x 2 x 2 1/2.............1 ....................1.......4.....................156 ....0......148 .............................................1................................24..0...........6 ..............................513 1 x 3 ...2 .5.................23 1/8 x 1 3/4 x 1 3/4 ..............T.......290 1 3/4 x 3 1/2.........937 7/8 x .......25 ...........................037 ..148 ...10 Table A-10..........21 ..........042 ...............049 ........75 3/16 x 2 1/2 x 2 1/2 ..............20 Wire Size No.......................4.125 .......................................75 ..723 ....0.......................042 ...837 x .1...........700 1 x 2 ...2 .........6....065 ................0..3.......431 7/8 x ..........135 1/2 x .4 Sheet-Galvanized Thickness Lbs Per Sq Ft ....148 ...............73 Table A-8..........................0.........................0375 ..............0...095 7/16 .....2.781 ......................03 .................................7685 ..1875 .....530 x .......................................................0359 ....0156 ........44 1/8 x 2 x 2..............1................................................6377 ............2....31 1/4 x .........................................................0...............1563 Sheet-Terne Plate Size Lbs Per Sq Ft ........1.............0............................4....022 ........10..........0..............................19 1/4 x 2 1/2 x 2 1/2 .032 ...............2...............1.........................884 7/8 x .....9603 .............1..........203........535 2 3/4 x 4 .......... 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 3/8 x ......................................0.............................2.........4.........0625 ................90 5/8 x 6 x 6.................0................................0.........................0...........93 2 3/4 x ..........065 ....1..........................500 ..669 3/4 x .......7 .516.....................80..............766 x ..................065 .................59 1/8 x 1 x 1...2795 ........ Table of Weights ...............2...2.................................263 3/4 .........................050 ..07 3 x ..................................720 Table of Weights ...........................042 ................032 .0.............0938 ..............0......................1............................128..........0.......213 5/8 ....................320 3 x 4 ......0438 ....6........2.........................6 5/16 x 2 1/2 x 3...021 1/4 ............042 ..0....................083 A-12 .8....9...............................62 .....865 1/2 x .......049 ........1..........043 1 1/2 .......4......256...3..065 ...........................088 7/8 x .659 1 1 1 1 1 1 1 1 1 1 2 2 2 2 2 2 2 2 2 Table Of Weights .1............035 ....0................406 .2 .....332 3/4 x ............323.............0...058 ...812 3/16 ............0........................................................0313 ........238 5/8 x ........2........................025 ..1...1........................1.....................................035 ........717 7/8 x .....................083 ...............2....163 x ....032 ...........032 .............7 .................................0.............80 3/16 x 1 1/2 x 2.............11...............50 ................................67 ..014 3/4 x ............92 1/4 x 1 1/2 x 1 1/2 ....2...............................00 .1 3/8 x 1 1/2 x 1 1/2 ...............................523 3/8 x .....826......2...............209 7/16 x ...032 ............1019 ......................................0.042 .......0375 .1.....1......9 .................250 ....5.........0403 ..........2 Sheet-Black Thickness Lbs Per Sq Ft ...............1...................................756 3/4 x 2 .......6................................065 ....270 1 1/2 x 2 ............................................1.........................................035..............9064 ...................................906 .......................1.............0..............35 3/8 x 2 1/2 x 2 1/2 ............049 ..........15.............0907 .........3......34 1/4 x 2 x 2...85 .1...........0156 .......66 .............................790 3/8 x ........................................25 3/52 ..025 ..............................................240 Bars-Hexagon Size Lbs Per Linear Ft 3/8 ........................169 9/16 ...148 ..............0625 .................025 ...681 3/8 x ............................3.......0..125 ..2..................032 ..........................2.....4..1285 ....050 .................................049 .....6...............0........................1....109 x ...........................0156 ...0.56 ...7.3................................................................0508 .......049 .....0................095 ........0...............................809 5/8 x ............156 .....936 x ............984 3/4 x ..........................156 ............1...........Continued 2 1/2 x ................032 ....178 Table A-9..1.................5.......0........48 3/16 x 1 1/2 x 1 1/2 ..Copper ...................................80 1/8 x 1 1/2 x 1 1/2 ....0...............................07 1/4 x 1 1/4 x 1 1/4 .......656 ................................1................. 1-1A-9 Table A-7.1..............................032 .......093 .................................1....................2.1...............873 3/4 x .................................................2........0.............1....9 1/4 x 4 x 4.........................................84..........031 1/8 .058 ..............0808 ..O.00 x ............................10 1/4 x 3 x 3........032 .3...........120 ...106 5/8 x ...017 1/2 x .. ......76 .........59 3 .......828 1 1/2 x .....................94 .............167 ...........285 3/8 ........6..........................0.............................................1................................425 2 1/2 ...................44 ...... 1-1A-9 Table A-10.....0............897 1 3/8 x .......1....250 ..............049 ....................................................1...106 3/4 .................2.............................0..........0......182 3/16 ........0.....0...4.037 ...............0.......1.0....3.....139 5/16 x .....................26 2 1/4 x .1.............156 ...................0.1.......................................................343 7/8 x .............035 ............................................................156 .................058 ....065 ..........0......0.............4...................366 ..0..................28 2 x ..65 ............0........................172 Table of Weights ..........................035 ...........................531 Table of Weights .....................................0..............................................Nickel Copper Alloy Thickness Lbs Per Sq Ft ........................0.........424 3/4 x ....................1451 ..........385 2 1/2 ......650 Table A-11.....................................2125 1/8 x 3/4 ..............0.........................0......................84 3 1/4 x .....0......................593 1 1/4 .........................418 ..............0...0..4....728 3/4 ....................0............. 7/16 ............393 1 x ........................553 2 .0............................................0...4...........035 .......................139 3/8 x ......927 1 3/8 ..................................................Nickel Chromium Iron Alloy (Inconel) .........188 3/8 x ..84 ............375 .850 1/8 x 2 1/2....12.............................638 1/8 x 1/2 .............0...........028 ...........................191 1/2 x .................0641 ..........1......................................270 ......800 Sheets Thickness Lbs Per Sq Ft ...........................................................028 ...........405 ........11..0......797 1 1/2 ...........761 3/4 .........1.319 2 ......638 1/8 x 2 ...319 3/4 .............065 .......292 3/4 x .............91 .......0................................1814 ........................428 1/2 ...................5........32 Table of Weights ..............................0...0............................0............Magnesium and Magnesium Alloy .0..................0...........1875 ............................3......0508 .................55 1 1/2 ..............0.............065 ...........4.......................1..................1594 1 ........065 .........818 2 ..................................065 ...........597 1 1/2 x .........................409 1/2 ..............................................1................0................................................552 7/8 x ............................................2..756 1 1/2 .........334 13/16 ...............065 ...........11 ...1.......543 1 x ....257 1/2 x ..3......................250 .....................190 3/16 ..1...........0....72 ...212 1 1/2 .......O........065 ..................................................................1................088 1/4 x ..035 ......035 .....................................462 ..........065 ......113 3/8 x .....1.......................................043 ..................018 ....0..........849 2 ...................454 15/16 ......................................................1.3258 .........0................0........0......................2............1............058 .........................................................................636 1 x ...........519 7/8 x ..............................0............299 1/2 x .0403 ....1875 ............5..............0............6....................................217 3/8 x ...T. Rods-Round Size Lbs Per Linear Ft 1/4 ........522 1 .............016 .......................0......................049 .....1..................19.3188 1/8 x 1 ..................................................0....1158 .....................................................................................................044 1 1/4 ..............028 .......................400 3/4 x ...480 3 ....0.......40 2 1/2 x ...27 A-13 ......................122 1 1/2 ..............0907 ................0..........4..0............969 1 3/4 x ...0..................................0.......0.5........058 ..........0..0.757 1 3/8 x ..0..........125 .........651 2 1/2 ............09 1 3/4 x ...0.....................46 2 1/4 x ..14 ...113 1/4 x ................................28 2 1/2 ........................................06 1/8 x 3 ..1............................................11 2 x ......0........1.......0................................75 1 .............188 5/8 ...0126 ..........................0......065 ..0.........................................................................0..........................093 ..........708 1 1/4 x ..058 ..................................1............329 5/8 x .........2...0...148 3/16 ....018 .309 3/8 .....................0...................................Steel 3/16 3/16 3/16 3/16 3/16 3/16 3/16 3/16 x x x x x x x x 1/2 .............065 .........................18........................478 1 ................638 1 1/4 ....049 ..................450 4 ......................................956 2 ....................9...........................................0.......0..................0.....................392 7/8 ...049 ..........0......... Rods-Round Size Lbs Per Linear Ft 1/4 .425 1/8 x 1 1/2...........22 ...................39 ......................................188 3/8 x ......049 ..15 .....071 1/4 x .............049 ...................................120 .................................150 5/16 x ..............0....................1........................1.......................1..0.........................290 .............1.0....988 1 1/2 x ......91 Size 1/14 1/14 1/14 1/14 1/14 1/14 x x x x x x 1/14 x 3 .032 .....582 ......049 .065 .............................................................11...............................................0253 .........................65 2 1/2 x .......065 .472 7/8 x .........035 .....................0..........0........................0..............38 Table A-12......025 .................1.....0.................................329 5/8 x ..........0....1.......035 .........027 Sheets Table A-13................0.............................0.........................6...................2..280 3/4 ................049 ............049 ....1..............................................................049 ..............032 ............823 ...........0625 ...049 .058 .091 5/16 x ......0.......236 1/2 x ........0..............686 1 1/4 x ......................................203 Sheets Thickness Lbs Per Sq Ft ...128 ...............049 .......733 .........710 2 3/4 ....0.0...0808 ...................................912 1 1/4 ..................................0.............7...... Bars-Flat Lbs Per Linear Ft 1/2 ..............468 3/4 x .......................0.............125 ......................025 .......................................Continued 1 3/4 ..............................0............................................................113 5/16 x .86 ........348 Table of Weights ....035 ..................230 ...........0359 .638 1 .................114 1/2 ............708 ...............................................0..................56 ...........12 Tubing Size Lbs Per Linear Ft 1/4 x ............................049 ...0....340 3 1/2 ..178 2 1/2 ..232 11/16 .........0.....613 1 x ..........8.....065 ..049 ......................0.037 .............................0....065 .................049 .........................065 ....1..........020 ........1...............0.......500 ....050 ...........032 ..... .........212 5/16 .............62 1 3/4 ............................................0.................91 7/8 .2.......850 1/4 x 1 1/4.......0375 ..................................................................511 1/2 ..70 1/4 x 2 1/2....094 7/32 ...........80 1/2 x 4 1/2.4...........94 1 1/16 .........................2......................211 5/16 ..........55 4 ..39 5/16 x 2 1/2 ......................049 1 7/16 ...........20 1/2 x 3 ..........24.............0.......................................377 ..........................................................65 1/2 x 5 .......13........................................................1......................................................3.................80 1 x 2 1/2 ....19 3/8 x 3 .............020 ..............125 .................................20 3/4 x 5 ................042 A-14 .....9..............5..043 11/16 ..........................................20 1/2 x 3 ...............21 3 1/2 ........................................................03 3 1/4 ................428 1 1/2 ....1....0.................19 3/8 x 1/2 ...........................3.............................................2795 ......4................................40 1/2 x 2 1/2..........32.....6.................................3...................8 8 ...........2.............................................................1...............0.......376 7/16 ...........46 3/8 x 4 .......................................13 1/4 x 3 ....06 5/16 x 1 1/4 ..................50 1 1 1 1 1 2 2 2 2 3 Table of Weights .....425 1/4 x 3/4 ............50 5/8 x 6 ..........2................120 1/4 ......15 11/16 ......................................58 1 ..20..............6.........21........20...........................................................................T....2..................................00 x 3 ....................6377 .................................0..................1...........1.................3....044 15/16 ......12......................73 1 1/4 .............638 3/8 x 1 ................12......2...........................261 11/22 .............8..80 Bars-Hexagon Size Lbs Per Linear Ft 1/4 ...............................5.................1.......44 5/8 x 4 ................O..................195 5/16 ........19 3 ............................9 Sheets Thickness Lbs Per Sq Ft ....................5...................................2.....80.............................................................15......0..............06 2 1/2 ...8...........................1...................................................................25 13/16 ...57 1 1/2 ................30......................................73 9/16 .......0625 .....................................347 1 ............0..........7....................40 3/4 ........................28.................10.....................................................20.............................00 1 x 6 ......................................................60 1 x 5 .........55 3/8 x 2 1/2..............................5549 .................................023 1/8 ..................5...............49 1/4 x 2 .1......4......................................42................7........2....8.008 1 5/8 .............17.........................60 2 1/4 .........................531 3/16 x 3/4 ...................518 1 1/2 .......75 1/4 x 4 ...................................13 1/2 x 1 1/2...........................................7................71 3 3/4 ....015 1 1/8 ......................15.............................92 5/16 x 3 ...............010 3/32 .76 5 1/2 .........5........................2...................................................................0.............1......0..............8344 .........13.........................41 2 .................................56 1/2 ...........33 5/16 x 1 1/2 ........5......................33 1 1/8 .....................13 5/16 x 2 1/4 ................................................0156 ...........................................025 ........................250 .................60 Rods-Rounds Size Lbs Per Linear Ft 1/16 ...........................128 1/4 ......5............850 9/16 ..................10 1/2 x 3 1/2.....857 1 3/8 ........................................................502 13/16 ...............5329 ...........................................................................37.73 4 1/2 .....................................6............................................65 1/2 x 1 .................................86 5/16 x 2 ................................66......022 ......................670 1 1/16 ..........................................................................................25 1/2 x 3 ......... 1/4 x 1/2 .........0....0............................................................................5.....................................................................167 9/32 ...................1.............8..................................78 6 .2.06 1/4 x 1 1/2...913 7/8 ..................1...................................................0...........2........7..303 1 1/4 ...............................00 2 ......................................0................1..............................050 .....................................10 3/4 x 2 1/2..75 3/4 x 6 ...4.....3.............0..6.......................2.17...............................................................................6...........................................28 3/8 x 1 1/4...................................14........68 2 1/4 ..20 5/8 x 2 ..........................0.....................636 1/4 x 1 ........1..........2.............................................1............4............66 13/16 ...3.............1..........50 x 2 1/2 .......380 1 3/16 ..................1......................0.......13 7 ..25..........03125 ............0...96..........................2............17.1...07 1 3/8 ......................0.....................................................................0.................10............................................1875 .065 3/16 .3.................28 1/4 x 1 3/4..........478 7/16 .....0...........3...............1.........91 3/8 x 2 ................1..............................0781 ......................................313 1 5/16 .............093 ....78 Bars-Square Size Lbs Per Linear Ft 1/8 ................................................................................................................................27..........766 1 1/4 ....................10...16................................262 3/4 ...170..................10........69 2 3/4 ..............................0.......................40 1 1/4 x 2 ....................7...0.........31 5/8 x 3 .............0...........1.....................70 1/2 x 1 1/4....52 2 5/16 .................................................................................Steel ........1..6...15....................................55 3/4 x 1 1/2..30 1 x 2 .......75 3/4 x 1 ...............54........Continued 5/32 ......316 3/8 .07 5 ..............332 3/8 .12............................29 3/8 .......................................................................................................................................95 1/2 x 4 ...172 1 3/8 .....50 x 4 ...................8.3.........5...............13....................0...........0........9............328 3/4 ............2.............55 1/2 x 2 .............6....................................... 1-1A-9 Table A-13.................40.............................................10..........................................4........044 .....................................................25...................051 1 3/4 ......2......................0...219 Tubing-Round 1/4 x 3 .........38 3/4 x 3 .....43 7/16 .......7...0...7..388 2 ........5........1....40 x 4 ......................................5.............156 .............053 3/16 .....603 1 ......8952 .......83 3/8 x 3 1/2.........1........6851 ..............50 1/2 x 6 .10...........................................00 1/2 x 2 ............38 5/8 x 3 1/2...............3............................................20 1 x 4 .......0...60 1 5/16 ....................................................................25 3 ..........130.........650 1 3/4 .1.............40 1 1/8 .........................................2.....85 3/4 x 2 ...........3.......109 ....5.........................66 5/16 x 2 3/4 ...50 1 x 3 .....................................................................1........................................1096 ....................845 5/8 ......25 5/8 x 2 1/2................................11...........0.........6..........................797 5/16 x 1 .......4557 .....................1....668 9/16 .............................................................28 2 3/8 .....0...1928 ..........................................................55 3/16 x 1/2 ......59 3/8 x 1 1/2.............3...........2.......................................0..........0..0....................21 2 1/2 ...........10..........0.................................178 1 7/8 ........30 1/2 x 5 ..763 7/8 ...............................2..............................................................0.....17............10 3/8 x 6 .......651 1/2 ...........65 3/4 x 4 ................076 5/8 .............93 5/8 ...........................................................................59 5/16 x 1 3/4 ................3................................4............. .............................255 7/8 x ....120 .........1875............065 ........................................................4105 9/16 x ......0.........065 .......1.................................1037 3/8 x ..........095 .........8066 13/14 x .......9873 15/16 x ....0.....................120 .............361 1 1/2 x ......058 .......035 .............595 1 5/16 x .............................2204 3/8 x ..........................2437 11/14 x ..............................095 ............0........042 .........0..0.1.....6465 11/14 x ..........2.........................0..............9227 1 1/8 x ..............035 .....0................................0..........287 1 3/16 x .............028 .........6932 1 3/8 x ..919 1/4 x ............................2838 7/16 x ...035 ..............................................058 ...........0.......................................134 ......................1.......299 15/16 x ...............169 3/4 x ............................1410 1/2 x ...................120 ..............095 .........9697 5/8 x ...028 .............095 ....3011 5/8 x ................083 ...............................2150 3/8 x .......... Size Lbs Per Linear Ft 3/16 x ..............................0...0..083 ...035 .......065 ............083 ..................058 .........035 ..........0......767 1/2 x ......049 ................083 ............3991 13/16 x .....1....058 .0.........0.......2684 9/16 x ....0.............1270 3/8 x .........2586 3/8 x ...049 .....3650 1 1/4 x ............................2030 7/16 x .......065 ...0....0569 1/4 x ...120 ........049 .......407 x ...................0........................................035 .......120 .......................049 ..515 1/4 x ...............................035 ......9546 7/8 x .............................9518 1 7/16 x .................1.0......2...0........0...............867 x ........0...........8271 1/4 x ..028 ......035 ..........4972 1 x .............0.500 1 1/4 x ..........095...................049 ...058 ..0.035 ............501 x ..171 1 1/4 x ........049 ......................6603 1 1/8 x ..............6404 3/4 x ...........083 ............1.....4318 7/8 x ..............0..126 13/16 x .........0.....1..........3338 11/14 x .................095 ........1..............035 .................8566 11/16 x ...0...0.........065 ................................1875 ....5004 1 3/8 x .......................931 x .120 ..614 3/4 x ..2903 13/16 x ..........1......0663 1/4 x ....................................095 .................035 ...........................................065 .0.....035 ........3883 5/8 x ......................1969 9/16 x ..5952 1 3/16 x ........................0..095 .........3139 7/16 x .....6484 1 x ..................0......083 ...0...125 ...........................................................049........0....083 ........6005 3/4 x .0...................1..........0...035 ..................083 ..1.............058 ..0.0........834 1/4 x ..........6279 1 1/4 x .......049...........1736 1/2 x ...120 ......0850 5/16 x ..........1......5470 1 1/2 x ..............049 .............058 ..................1....028 .........4070 1 1/8 x ........0...........447 1 1/4 x .................095 .........1.0......0.............1............095 .....035 ...065 ........120 ...............038 9/16 x ......527 1 3/8 x .................0....0.........058 ...058 ............1.065 ..........035 .125 ..............3509 5/8 x .......1036 5/16 x ......028 ..............................1575 5/16 x ......065 ..................................0...........095 ..1.......0...............0...0..................5372 5/8 x ...5829 1 x .065 ..065 ...028 ........065 ........1.........0..................065 ...........7804 1/8 x ...065 .................124 7/8 x ..0.....367 1 1/4 x ..9085 1 3/8 x ..................095 ......4.......0......................049 .........065 ......184 1/4 x .....1.............4645 15/16 x ....1.........................0......................049 .....065 ...049 ..1704 3/8 x .........3603 1 x .727 1/4 x .035 ................0...1875 .2......4317 11/14 x ......0....044 1 1/8 x .......3017 1/2 x ....035 ........................0...............................2530 7/8 x ...065 ...035 .....0....................0.058 ..........057 1/8 x .035 ...0..............0...........1..........804 7/8 x .......049 ..567 1/4 x .....1..........6051 15/16 x ...............035 ......4537 1 1/4 x .....5184 7/8 x ....0..1378 5/16 x .0...............1....2157 3/4 x .............120 ..........................095 ....0...7784 1 3/16 x ......085 1/8 x ..............698 x ...0..028 ..........5617 7/8 x ...................677 3/4 x ................125 11/16 x .0.................212 13/16 x .....065 ...0.............0............................... 1-1A-9 Table A-13.......234 1 5/16 x .........120 ...095 .............................095 ...................035 ...............0.....7912 9/16 x .....2...0....095..058 ........................049 .........8892 3/4 x ..................................125 ...........................................................8218 1 1/4 x ....1...095 .....049 .............083 ........1......0.........095 ..................9219 13/16 x .....049 .......2......3693 1/2 x .................................................0...................095 .095 .........................2052 1/2 x ..0........065..049 .........1051 1/4 x ...................3665 3/4 x ..................065 ........0....049 .............................0...065 .1.............0.................107 1 3/16 x .........0..083 .0...049 ...........................1......Steel ..................................058 ...4304 1 3/16 x ...........607 1 7/16 x ......0.....................047 3/4 x ..Continued 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 2 2 2 2 2 2 2 2 2 2 2 2 2 2 2 2 2 2 2 2 2 2 2 2 2 1/2 x ..........082 5/8 x ................216 13/16 x ..................0....1........120 ...................................................................020 x .....626 1/8 x .........1................2..........2583 7/16 x ....................1............095 ................049 ....1....3471 1/2 x ................058 ........3837 1 1/16 x ...8150 1 3/8 x ...............................0.......279 1/8 x ....0..................2..247 15/16 x .................1..............1..049 ............2735 1/2 x ...1..255 1/2 x ........0............0...2203 5/8 x .........................0...............0.049 ........................480 5/8 x ......................................................8923 A-15 ...........1.....058 .551 5/8 x .424 1/2 x ........1223 7/16 x ..0......0...058 ...151 1/4 x .......4738 5/8 x ................................0...429 1/8 x ......5056 7/8 x ......626 9/16 x .....2.340 x .......0..0......040 ........0.................5625 1 1/8 x ....065 ...0............0...120 ............0............1875 ..0........0..0...................1............0....7338 x ...........1................741 7/8 x ...........................4282 3/4 x .1188 1/4 x ...7351 1 1/8 x .......0..049....................1.....095.................9173 1 x .............9666 15/16 x ..............125 ....087 3/4 x ........0.......2670 3/4 x .....................095 ...................095 .......065 .....144 1 3/8 x ...........0..0.....095...............065 .....0.............................120....035 ...1783 5/8 x .....049 ....0803 1/4 x ....487 5/8 x ..035 ....................0................3370 15/16 x ..................................7567 1 x .....................................................0.......9951 1/2 x .4669 Table of Weights .2..7585 1 1/2 x ....5298 1 1/16 x .8120 1 x .............065 ...035 .........................6917 1 1/8 x ..0..................049 .............083 ..1....0............034 1 1/4 x ..........0.0.................035 .......476 3/4 x ......167 3/4 x ...O..........028 ...............0..058 ..........2...........3450 9/16 x ...7376 1 1/4 x .............3......127 1 1/16 x .0.........028 ............049 ......6605 1 5/16 x .3137 7/8 x .120 ......1.............5906 3/4 x .........T...4750 3/4 x .........................6639 3/4 x .......8239 5/8 x .................2904 1 x ..............8651 1 5/16 x ...049 ...1.........927 11/16 x .............1..3.............1.........................1283 5/16 x ...........1....1962 3/8 x .................1716 5/16 x .............028 .4770 1 5/16 x ......2..............................095 ............................0............0476 3/16 x .....1.....................................1.0.................................049 ...................065 ...........................0...............................................065 ............1...........1........065 .........126 3/8 x ........................................................0.......1.......058 ..............065................083 ....0.......................0......................083 .......7259 1 7/16 x ...0.....................058 ..................................120 ........083 ...............................................................................049 ...................................2358 1/2 x ......049 ........0.120 ......................065 ..............365 5/8 x ....065..........0.....0...0...1503 7/16 x .........0..........0......7906 7/8 x .083 ......356 1/4 x ..................................................058 .................028 ................202 x .1..049 ........................0......... ....602 3/8 x .........065................7338 3...................87 A-16 .............687 3/4 x ............4629. Sheet Thickness Lbs Per Sq Ft ..5 .........080 ..............7585 2 2 2 2 2 2 2 2 2 2 2 2 2 3 3 3 3 3 Table of Weights ...166.058.....386 x ....010 ..........125 ..... ..........278 x .......375 x .........................58................921 x .1..29 2.697 x ..........26....................058..................00 x .....691 3/4 x ...87 .............................169 2...101 ...............................120 .....874 x ............0..........311 3/8 x ..........786 x ..O.....1.............944 x .049.......047 ...........3........306...................1 .....................049 ...7 ..................................15625..065...........083....095 ..................... .....6279 1................994 x ...2 ...........2218....035 .............98 ..111...............2936........2...............0............1 ..4.........035....1285 .....515 3.......2..647 3/4 x .............438 1/2 x ......................................1..016 .........035..............91....045 ...071 .......689 1/2 x .........109 ..........2 ..............2.....0.994 x ...2 ...................................0641 ..049 ........0..234...................................024 ...........................025 .120 ...........1.......049.0.0...70 x ......156...........................2.............................058 .2..............3 Table A-14.8923 2................................020 .....018 .........215 x ......383..............032 ........011 .0508 ...........599........3..............854 x ...3 ........362 Wire Thickness No.......95...............68 .....1....6 ...0907 .......................71 ...2............................................3749......25 .140 1/2 x ...1465.........................................2................... .............. ..040 ........128. 3/8 x ..... .047 x .6932 2.........................501 x ........58 .........67 Table of Weights ...289...................0..................72.......Zinc ....................4537 1........367 3/4 x ......1875......2...........2604......... .......937....58 ................................9 .........013 ..067 x 1...............8892 2.............650... ...............047 x ......726 x 1....054 ..98 ..........14.281 1/2 x .7..............065 ................083 ......5004 1..136 x ..........223....167 3/4 x ....................049....5937 2..................T............125 ................1............278 x ....0....................20 ........................823 x ..035................151 3....... ..095 ..32 ...........049.......................................0625 ...............478....386 x ..........5858..........................36....... of Ft Per Lb .045 ......1...11 .......................047 1/2 x ...........45.......3..04 .......................118 ...065 .... .....................162 ...................035.................3.......035......049 .748 x 1..........22....083 .....21875 x ...3.......145........095 .031 ...............Steel .......7338 3..........................781 x ..............................1......0508 .........991 3/4 x .1....1.095 .........1.8239 2...................127 Tubing-Streamline Size Lbs Per Linear Ft 1......1157................994 x .............................366.Continued ..0............049...........................9 .......0..707 x ......028 .... ...875 x ....3 .........................854 x ..018 ...............5.......014 .70 x .386 x .....1913..................................................... .3.............120 .......................120 ..032 ..563 x ....012 ....067 x 1.......0.......887 1/2 x ..........................036 ......008 ............120 .362 3/4 x ........006 ....0....009 .....................049.....9 .........3 ..... 10415... 1-1A-9 Table A-13.......................047 2.......182..041 ......... 1-1A-9 Table A-15.O. Temperature Conversion Chart A-17 .T. O.T. 1-1A-9 Table A-16. Standard Bend Radii for 90o Cold Forming-Flat Sheet A-18 . 00745 0.01080 0.T. 1-1A-9 Table A-16.040 0.00951 0.00454 0.00576 0.00412 0.00943 0.00213 0.00908 0.00352 0.00200 0.00258 0.022 0.00188 0.00195 0.00957 0.00671 0.00094 0.00739 0.01058 0.01105 0.00691 0.00644 0.00834 0.00377 0.00135 0.00473 0.00561 0.00312 0.00467 0.01017 0.01025 0.00086 0.00486 0.00535 0.00562 0.00358 0.00234 0.00304 0.00733 0.00780 0.00507 0.00971 0.00452 0.00808 0.00527 0.00431 0.00800 0.00584 0.01012 0.00372 0.00421 0.00582 0.00802 0.00072 0.00367 0.01005 0.00540 0.00888 0.00235 0.051 0.01030 0.01179 Bend Allowance per One Degree A-19 .00180 0.00630 0.01065 0.00515 0.00725 0.01133 0.01126 0.00842 0.Continued Table A-17.00812 0.00917 0.00616 0. Metal Bending and Bend Radii Bend Allowances Sheet Metal Bend Allowances Per Degree of Bend Aluminum Alloys Stock Thickness BEND RADIUS 1/32 1/16 3/32 1/8 5/32 3/16 7/32 1/4 9/32 5/16 11/32 3/8 13/32 7/16 15/32 1/2 17/32 9/16 19/32 0.00976 0.00636 0.01051 0.091 0.01083 0.00507 0.00867 0.00570 0.00249 0.01072 0.00966 0.00344 0.187 0.00699 0.00997 0.00079 0.00903 0.00418 0.00322 0.01051 0.00963 0.128 0.00104 0.00290 0.00911 0.00289 0.00670 0.00854 0.00787 0.00857 0.00758 0.00590 0.00126 0.00595 0.00834 0.00255 0.00779 0.00149 0.00639 0.00679 0.00297 0.00794 0.00154 0.00476 0.00406 0.00209 0.00921 0.00309 0.00862 0.01073 0.00398 0. Standard Bend Radii for 90o Cold Forming-Flat Sheet .00693 0.00530 0.00481 0.O.00268 0.00461 0.064 0.00616 0.00753 0.00125 0.00748 0.00140 0.00649 0.00848 0.00704 0.00624 0.00685 0.00263 0.00203 0.00426 0.00243 0.00521 0.032 0.00725 0.00364 0.00896 0.00998 0.01020 0.00317 0.00398 0.00159 0.00180 0.00889 0.00943 0.00343 0. 01160 0.01269 0.01276 0.01407 0.01129 0.01238 0.01230 0.051 0.022 0.01214 0.064 Aluminum opposite 1/8 in column ‘‘Bend Radius’’.01245 0.00268 in this case) by the number of degrees of the desired bend angle: 0.064 aluminum alloy. A-20 .064 0.01338 0.01324 0.01268 0.032 0.T.00268 x 50 = 0.01189 0.01183 0.01235 0.01347 0. Bend Radius = 1/8.091 0.01283 0. 1-1A-9 Table A-17.01301 0.01289 0.01322 0.01170 0.01248 0.187 0.01216 0.01378 0. Multiply this bend allowance (0.01139 0.O.01291 0.01344 0.040 0.1340 = total bend allowance to be added to the length of the straight sides of the part to determine the total length of the material needed.01397 0.01175 0.01332 0. Bend Angle = 50o Find bend allowance for 1o in column for 0.01114 0.01107 0.01193 0. Metal Bending and Bend Radii Bend Allowances Sheet Metal Bend Allowances Per Degree of Bend Aluminum Alloys Continued Stock Thickness BEND RADIUS 5/8 21/32 11/16 23/32 3/4 0.01121 0.01357 0.128 0.01223 0.01351 0.01161 0.01298 0.01453 Bend Allowance per One Degree Example: To determine bend allowance Given: Stock = 0. 1-1A-9 Table A-18.O. Bend Set Back Chart A-21 .T. 040303 Birmingham Wire (B.192 . 5. phosphor bronze.G. Used for bare wire of brass. galvanized.1620 .072 .064 .0673 .0991 . crucible spring steel.3147 .B. Zinc gage for sheet zinc only.) Used in England for iron and steel sheets and hoops.) ----------.) .464 .S.G. spring steel wire. Browne & Sharpe Gage (B.5883 . This is a gage based on the weight per square foot of sheets rather than on thickness.3938 .212 . seamless steel. ---------------------------------------------160 150 140 130 120 110 100 90 80 70 60 50 45 40 36 32 0000000 000000 00000 0000 000 00 0 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 A-22 .204307 . seamless copper. copper.0540 .0625 .050821 .380 .1570 .104 .454 . Other gages in use: Trenton Iron Company Gage.W.T.W.1196 . aluminum.1793 . German silver.G. hot-rolled sheet steel.5416 . blue annealed sof t steel.S.0800 . brazed brass and brazed copper tubing.&S. and for all wires and aluminum sheets in England.S.080 .) Also known as U.1644 .289297 .W.1345 .) Also known as Birmingham. THICKNESS IN DECIMALS OF AN INCH United States Standard (Revised) U. phosphor bronze. Steel Wire.238 . zinc and copper (not for copper telephone or telegraph wire).4305 .S.3310 . iron or steel.072 .1981 .400 .G.2500 .516500 . and for boiler tubes.1350 . and with limited usage for copper sheets. cold-rolled monel metal.S.162023 .1113 .3532 . Birmingham Wire Gage (B.144285 .0598 .134 .2804 . United States Standard (Revised) (U.G.180 .) .1205 . 1-1A-9 Table A-19. Gage Number United States Steel Wire (STL.116 .101897 . Birmingham Metal Gage-in England for brass sheets. sheets of copper.425 . Used for iron and steel telephone and telegraph wire and strip steel.257627 . British Imperial Standard Wire Gage (I. hot-rolled monel metal.1250 .203 .300 .460000 .148 .) ------. hoop steel.220 .G) .3964 . Standard for Steel and Iron Sheets and Plates Gages.0882 .0699 .0720 .G. It is used for commercial iron and steel sheets and plates including planished. stainless steel and aluminum tubes. 2.2253 .2830 .) Also known as American or American Wire Gages.500 .432 . ---------------------------------------------.229423 .S.G.348 .045257 .3065 .0749 .2070 .276 .2092 .1398 .080808 . Comparative Table of Standard Gages 1.0495 Browne & Sharpe (B. round-edged f lat wire.2242 .4615 . United States Steel Wire Gage (STL.284 .372 . Standard Birmingham Sheet and Hoop Gage (B. Roebling.5000 . Also for seamless brass.058 . Used for bare wire of galvanized. aluminum and German silver.) Also known as British Imperial Wire or English Legal Standard Gages. Also for rods of brass.S.324861 .O.064084 .G.065 .500 .2625 .1920 .049 Thickness Approx.057068 .0556 . 3.2437 .109 .W.095 .176 .3625 . 6.252 . Stubs or Studs Iron Wire Gages. phosphor bronze and aluminum.324 .1483 .1770 .G.300 . Twist Drill and Steel Wire Gage for twist drill and steel drill rods.0625 . bright basic tinned or copper coated.4900 .W.048 Standard Birmingham Sheet and Hoop (B.2391 .4452 .181940 .) Also known as: National Wire.0785 .& S.2225 . 4. cold-rolled sheet steel.1494 .071962 .114423 . and for insulated wire of aluminum and copper. steel bands.W.S.409642 .364796 .0915 .580000 .S.0897 .6666 .1943 .259 .G.128490 .160 .092 . Standard Sheet Metal or U. Washburn and Moen Gages.083 .0475 British Imperial Standard Wire (I. Not used for telephone and telegraph wire.120 .S.056 .165 .G.232 .6250 . American Steel and Wire Company’s music wire gage.128 .1055 . steel plate.1046 . brass. American Steel and Wire Company. black annealed.0538 .090742 .0478 Weight Oz/Sq Ft.1764 . black sheet iron. Also resistance wire of German silver and other alloys. Standard Steel Wire.144 .) or (N. tinned and terne plates. Used for bare copper telephone wires in the U.340 . 015625 .0061 . 28 24 22 20 18 16 14 12 11 10 9 8 7 6.018 .017900 .02204 .0164 .0060 ----------- Weight Oz/Sq Ft.032 .014 .0108 .0052 .0064 . Comparative Table of Standard Gages .02782 .03125 .0128 .0110 .005615 .0239 .025 .0132 .031961 .028462 .0148 .0181 .007950 .G.G.009 .0299 .0092 .040 .0090 .) .G) .0048 .010 .W.011257 .0162 .0118 .0230 .G.0043 .25 4 ----------- 19 20 21 22 23 24 25 26 27 28 29 30 31 32 33 34 35 36 37 38 39 40 Table A-20.0392 .0076 .03175 .5 5 4.0140 .005000 .036 .5 4.0075 .0090 .0116 .0120 .0410 .0104 .0179 .0105 .042 .0173 .012641 .0258 .018 .0080 .022 .020101 .T.G.025346 .0077 .004 --------------------- Thickness Approx.) .) .S.010025 .028 . Gage Number United States Steel Wire (STL.0124 .0209 .) .014195 . .0135 .0038 Browne & Sharpe (B.S.0349 .032 .003531 .0095 .0150 .G.0084 . Melting Points Approximate ELEMENTS C ALUMINUM ANTIMONY BARIUM BERYLIUM BISMUTH CADMIUM CALCIUM CARBON CHROMIUM COBALT COPPER GOLD IRON LEAD LITHIUM MAGNESIUM MANGANESE MERCURY MOLYBDENUM 660 631 850 1350 271 321 810 3500 1765 1480 1083 1063 1535 327 186 651 1260 -39 2620 DEGREES F 1220 1167 1562 2462 520 610 1490 6332 3209 2696 1981 1945 2795 621 367 1204 2300 -38 4748 A-23 .007080 .022 .008 .0418 .0087 .0149 .0060 .0329 .003144 Birmingham Wire (B.0098 .006305 .012 .0286 .01745 .020 .007 .02476 .W.0070 British Imperial Standard Wire (I.0067 .0054 .Continued THICKNESS IN DECIMALS OF AN INCH United States Standard (Revised) U.004453 .0204 .0348 .028 .005 .S.O.0075 .0100 .0082 .01961 .0136 .0359 .003965 .015941 . 1-1A-9 Table A-19.& S.0068 .016 .5 6 5.035890 .022572 .020 .0440 .0139 .0123 .013 .0048 Standard Birmingham Sheet and Hoop (B.0069 .024 .008928 .0097 .W.035 .0269 .0085 .0164 . 1-1A-9 Table A-20.O.Continued ELEMENTS C NICKEL PHOSPHOROUS (YELLOW) PLATINUM SILICON SILVER TIN TUNGSTEN VANADIUM ZINC 1446 44 1773 1420 961 232 3400 1710 420 DEGREES F 2635 111 3223 2588 1761 449 6152 3110 787 A-24 . Melting Points Approximate .T. Glossary 1 . electrical. a metal is not designated an ‘‘alloy’’ based on elements incidental to its manufacture.17oC (0oF). oxygen. It forms when the metal solidif ies and remains a solution until it cools to about 732oC (1350oF). ANODIC OXIDE COATING--A thin f ilm of aluminum oxide formed on the surface of aluminum and aluminum alloy parts by electro-chemical means. ductility and formability. toughness. AIR COOLING/QUENCHING--Cooling from an elevated temperature in air. manganese. AMORPHOUS--Non-crystalline. nitrogen and hydrogen are incidental to the manufacture of plain carbon steel. Aging is a process in which the trend is toward restoration of real equilibrium and away from an unstable condition induced by a prior operation. (f) Produce a def inite micro-structure. Brittleness is caused by the absorption of hydrogen into the metal from the acid solutions (also called hydrogen embrittlement). and only a portion of the austenite is preserved by rapid cooling. AS CAST--Condition of a casting as it leaves the mold with no heat treatment. this degree of rapidity is impracticable. iron. AUSTENITE--A solid solution of iron carbide in gamma iron. ALLOY--A mixture with metallic properties composed of two or more elements of which at least one is a metal. For example. still or forced. (d) Ref ine crystalline structure. It does not become an ‘‘alloy steel’’ until the elements are increased beyond regular composition or until other elements (metal) are added in signif icant amounts for a specif ic purpose. ANNEALING--Generally it is a controlled heating procedure which leads to maximum sof tness. (c) Af ter ductility. ANNEALING FULL--A controlled heating procedure which leads to maximum sof tness. The term refers only to the ability of the material to harden in air and does not imply any def inite analysis or composition. ISOTHERMAL--Heating of a ferritic steel to a austenitic structure (fully or partial) followed by cooling to and holding at a temperature that causes transformation of the austenite to a relatively sof t ferrite and carbide structure. However. ALLOY ELEMENTS--Chemical elements comprising an alloy. Addition of certain alloying elements such as nickel and manganese perserves austenite below .T.O. carbon. (b) Induce sof tness. magnetic. (b) Specif ically the formation of a new phase by cooling a solid solution to super saturated state and allowing the super saturated solution to partially return to equilibrium by the formation of a less concentrated solid solution and a new phase. Theoretically the solution would remain if the iron or steel were cooled instantaneously from a bright red heat to atmospheric temperature. Hardening of the material occurs simply by cooling in air from above critical temperature. AIR HARDENING--An alloy which does not require quenching from a high temperature to harden. or physical properties. phosphorus. AGING--(a) Generally any change in properties with time which occurs at relatively low temperature (room or elevated) af ter a f inal heat treatment of a cold marking operation. sulphur. ductility and formability. (e) Remove gases. clean and electroplate. ANNEALING. usually limited to the metallic elements added to modify the basic metal properties. silicon. The annealing procedure is utilized for the following: (a) Remove stresses. but in practice. 1-1A-9 GLOSSARY A ACID BRITTLENESS--Brittleness of steel resulting from use of acid solutions to remove scale. CASE--The surface layer of an iron-base alloy which has been made substantially harder than the interior by the process of case hardening. 1-1A-9 GLOSSARY . if of lighter gage. or to an approximate rectangular cross-section of equivalent area. also called closed annealing or pot annealing. BASE METAL--The metal to which other elements are added to form an alloy possessing specif ic properties. The sheets have a bluishblack appearance. BINARY ALLOY--An alloy containing two elements. The process is one of rapid oxidation primarily of silicon and carbon. BESSEMER PROCESS--A process for making steel by blowing air through molten pig iron contained in a suitable vessel. The sheets. BRITTLENESS--Brittleness is the property of a material which permits little bending or deformation without fracture. or perhaps by the segregation of elements already present in the metal.O. Glossary 2 . BRIGHT ANNEALING--A process of annealing. Billets are classif ied as semi-f inished products for re-rolling or forging. usually at a sub-critical temperature. usually with reducing gases. BLUE BRITTLENESS--Brittleness occurring in steel when in the temperature range of 149o to 371oC (300o to 700oF). CARBURIZING (CEMENTATION)--Adding carbon to the surface of iron-base alloys by heating the metal below its melting point in contact with carbonaceous solids. BOX ANNEALING--Sof tening steel by heating it. BLUE ANNEALING--A process of annealing sheets af ter rolling. BILLET--An ingot or bloom that has been reduced through rolling or hammering to an approximate square ranging from 1 1/2 inches square to 6 inches square. cyaniding. are allowed to cool slowly af ter the hot rolling. or nitriding. if fairly heavy. BLACK ANNEALING--A process of box annealing of sheets prior to tinning whereby a black color is imparted to the surface of the product. in a suitable closed metal box or pot to protect it from oxidation. by the penetration of gases such as oxygen into the metal with consequent reactions. they are passed singly through an open furnace for heating to the proper annealing temperature. liquids.Continued B BARK--The decarburized skin or layer just beneath the scale found af ter heating steel in an oxidizing atmosphere. CASE HARDENING--A heat treatment of a combination of heat treatments in which the surface layer of an iron-base alloy is made substantially harder than the interior by altering its composition by carburizing. Brittleness and hardness are closely associated. apart from minor impurities. such that surface oxidation is reduced to a minimum. C CARBON FREE--Metals and alloys which are practically free from carbon. BURNING--The heating of a metal to temperatures suff iciently close to the melting point to cause permanent injury. as is usually the case. or gases. employing a slow heating and cooling cycle. BUTT-WELD--The welding of two abutting edges. thereby yielding a relatively bright surface.T. Such injury may be caused by the melting of the more fusible constituents. or when cold af ter being worked within this temperature range. strip. This method produces a case almost as hard as nitriding at a time factor of slightly longer than required for cyaniding. D DECALESCENCE--When a piece of steel is heated. Also. CYANIDING--Surface hardening by carbon and nitrogen absorption of an iron-base alloy article or portion of it by heating at a suitable temperature in contact with a cyanide salt. At the point of decalesence. sheets. followed by quenching. specif ic term usually applies to reducing metal temperature in a gaseous environment rather than quenching in a liquid. COLD DRAWING--The permanent deformation of metal below its recrystallization temperature. It is the halting in the temperature range that is termed decalescence. At this point the rise in temperature suddenly halts due to the fact that the metal absorbs the heat necessary for the change of state. COOLING--Any decrease in temperature.O.350oF). The values so obtained are merely comparative between different materials tested by the same method. Af ter this halt the temperature will continue its normal rate of increase.Continued C (Cont) CHAPMANIZING--A process for hardening steel by bubbling ammonia through a cyaniding salt bath and holding the f inished part in the gas stream. however. CONVERSION COATING (CHEMICAL)--A f ilm intentionally produced on a metal by subjection to a selected chemical solution for the purpose of providing improved corrosion resistance or to improve the adhesion of subsequently applied organic coating. but primarily to promote transformation of austenite.325oF and 1. and tin plate. CORE--The interior portion of an iron-base alloy which is substantially sof ter than the surface layer as the result of case hardening. COLD WORKING--Plastic deformation of a metal at a temperature low enough to insure strain hardening. COLD TREATING--Cooling to sub-zero temperature for various purposes. the carbon and iron are forming a solid solution and the steel is passing from its annealed condition into its hardened condition. CHARPY IMPACT--An impact test made by measuring in a Charpy machine the energy required to fracture a standard notched specimen in bending. This process is frequently applied in f inishing rounds. Glossary 3 . The decarburized area is sometimes referred to as the bark. that portion of a forging removed by trepanning. by drawing the bay through one or more dies. COLD ROLLING--The permanent deformation of metal below its recrystallization temperature by rolling. the temperature rises uniformly until it reaches a point between 718oC and 732oC (1. DECARBURIZATION--The removal of carbon (usually refers to the surface of solid steel) by the (normally oxidizing) action of media which reacts with carbon. the inner part of a rolled section of rimmed steel as distinct from the rimmed portion or rim. 1-1A-9 GLOSSARY . a body of sand or other material placed in a mold to produce a cavity in a casting.T. (e) Flake -Internal f issures (cracks or clef ts) in large steel forgings or large (MASS) rolled shapes. (d) Fin (Flash) .a rough projection on a casting caused by the mold breaking or being washed by the molten metal. solidify at different temperatures. Very f ine blisters are called pinhead or pepper blisters.Continued D (Cont) DEFECTS IN METALS--Damage occurring to metal during manufacture/fabrication process. (l) Ductility the ability of a metal to withstand plastic deformation without rupture.’’ (f) Ghost .a surface defect appearing as a seam caused from folding over hot metal. (see acid brittleness). which may result in premature failure. In a factured surface or test piece. is held in pockets. EXFOLIATION--The cracking or f laking off of the outer layer of an object. (k) Segregation a mixture of compounds and elements. 1-1A-9 GLOSSARY . The above terms measure ductility and since they are comparative. considerable experience is required for proper evaluation of material for the purpose intended. If very f ine. ELONGATION--The amount of permanent extension at any stage in any process which continuously elongates a body. usually produced by blowholes which have become oxidized. (b) Blow hole . (h) Pipe . EQUALIZING--Intermediate heat treatment (special) which assists in developing desired properties.(Ferrite ghost) a faint band of ferrite. EMBRITTLEMENT--Loss of ductility of a metal.a cavity formed in metal (especially ingots) during solidif ication of the last portion of liquid metal causes the cavity or pipe. f ins.a defect in metal produced by gas bubbles either on the surface or formed beneath the surface. when cooled from the molten state. (c) Bursts -ruptures made in forging or rolling. primary use is for equalizing/relieving stresses resulting from cold working. Ductility is usually determined by tension test using a standard test (2″ gauge length) specimen. or occuring where the skin from a blowhole has partly burned away and is not welded. The test specimen is loaded in tension to rupture. Above this limit failure occurs by the generation and growth of cracks until fracture results in the remaining section. EUTECTIC ALLOY--An alloy which has a lower melting point than neighboring compositions. (g) Lap . or sharp corners and then rolling or forging. (j) Seam .a thin f in of metal formed at the side of a forging or weld where a small portion of the metal is forced out between the edges of the forging or welding case. Some typical defects are as follows: (a) Blister .a crack on the surface of metal which has been closed but not welded. Glossary 4 . The specimen is then assembled and measured for length and diameter at the fracture. (i) Scab . a seam may be called a hair crack or hair seam. ENDURANCE LIMIT--The highest unit stress at which a material can be subjected to a very large number of repetitions of loading and still show no evidence of failure.O. they appear as sizable areas of silvery brightness and coarser grain size than their surroundings. them into the surface. EXPOSURE--Heating to or subjecting to an elevating temperature or environment for a certain period of time. E ELASTIC LIMIT--The elastic limit of a material is the greatest load per unit area which will not produce a measurable permanent deformation af ter complete release of load.T. which. ENDURANCE RATIO--The ratio of the endurance limit for cycles of reversed f lexural stress to the tensile strength.a hole produced during the solidif ication of metal by evolved gas which in falling to escape. but not welding. DUCTILITY--The property that permits permanent deformation before fracture by stress in tension. More then one eutectic composition may occur in a given alloy system. The increase in length is expressed as per cent elongation and the decrease in diameter as per cent reduction of area. Sometimes known as ‘‘chrome checks’’ and ‘‘hairline cracks. the process of revealing structual details by the preferential attack of reagents on a metal surface. upon solidif ication they arrange themselves in a geometric pattern. FERRITE--A solution in which alpha iron is the solvent. in various proportions. The relative position within a group sometimes changes with external conditions. segregations. G GALVANIC SERIES--A list of metals and alloys arranged in order of their relative potentials in a given environment.. FORGING STRAINS--Elastic strains resulting from forging or from cooling from the temperature. The galvanic series indicates the tendency of the serval metals and alloys to set up galvanic corrosion. FATIGUE LIMIT--Usually used as synonymous with endurance limit. approximate depth of carburized or decarburized surface area. FLAME HARDENING--A process of hardening a ferrous alloy by heating it above the transformation range by means of a high-temperature f lame and then cooling as required.T.Continued E (Cont) ETCHING--Attack of metals structure by reagents. They usually consist of bismuth. (c) Deep-etching is a form of macro-etching in which the sample with regular cut surface may be immersed in hot hydrocloric acid (50% acqueous solution) and then examined for major defects such as inclusions. Glossary 5 . When metal is in molten state. However. and iron only as an impurity. GRAIN GROWTH--An increase in the grain size of metal. (b) Macro-etching is for the examination of the sample under a low power magnifying glass or by unaided eye. FUSIBLE ALLOYS--A group of nonferrous alloys which melt at relatively low temperatures.O. The fracture is then examined by eye or with the aid of a low former magnifying glass. etc. The test specimen is broken by any method that will produce a clean sharp fracture. a good polish is necessary. pipes bursts and f lakes. lead. F FATIGUE--The phenomenon of the progressive fracture of a metal by means of a crack which spreads under repeated cycles of stress. FRACTURE TESTING--A test used to determine type of structure. the atoms have no uniform grouping. GRAINS--Individual crystals in metal. FORMING--To shape or fashion with hand/tools or by a shape or mold. etc. but it is only rarely that changes occur from group to group. High polishing for this purpose is not absolutely essential. and which is characterized by a body centered cubic crystal structure. and defects such as seams. A trained/ experienced observer will determine grain size. carbon content and the presence of internal defects. FULLY HARDENED--Applies generally to the maximum hardness obtainable. 1-1A-9 GLOSSARY . applies to materials that are hardened by a strain and/or age hardening process). however. (a) Micro . In metallography. the presence of inclusions of dirty steel. cracks. FILLET--A concave junction of two surfaces usually perpendicular. cracks. tin.etching is for the examination of the sample under a microscope and for this purpose the sample must be very carefully polished (by an experienced person) prior to etching. (In particular. involving the heating and cooling of a metal or alloy in the solid state for the purpose of obtaining certain desirable conditions or properties. shape. See Section VIII for typical testing methods. water. HARDENING--Hardening accomplished by heating the metal to a specif ied temperature. The test results are usually directly related to tensile and yield strength of the metal involved. See Charpy Impact and Izod Impact. or cutting action. inclusions. HEAT TINTING--Heating a specimen with a suitable surface in air for the purpose of developing the structure by oxidizing or otherwise affecting the different constituents. usually oxides. HEAT TREATMENT--An operation. M MACHINABILITY--The cutting characteristic of metal and resulting surface f inish using standard cutting tools and coolant/lubricants. INDUCTION HARDENING--A process of hardening a ferrous alloy by heating above the transformation range by means of electrical induction and then cooling as required. This constituent has a lower melting point than the iron and the result can be that steel may crack during hot working. HOT SHORTNESS--Brittleness in metal when hot. penetration. maximum tensile strength. silicates. indentation. The standard machinability ratings are usually based on comparison to SAE 1112/Aisi B 1112 Bessemer screw stock which is rated at 100% machinability. An exception would be case hardness. There are various factors that effect the machinability of a metal such as hardness. Glossary 6 . HYDROGEN EMBRITTLEMENT--See Acid Brittleness. type. This treatment produces a f ine grain structure. then rapidly cooling by quenching in oil. The results are usually expressed in terms of energy absorbed or number of blows (of a given intensity) required to break the specimen. or combination of operations. alloy constituents. and such which are mechanically held during solidif ication or which are formed by subsequent reaction of the solid metal. structure. HARDNESS TESTING--Test used to determine the ability of a metal to resist penetration.O. condition of tool and coolant. Heating and cooling for the sole purpose of mechanical working are excluded from the meaning of this definition. I IMPACT TEST--A test in which one or more blows are suddenly applied to a specimen. extreme hardness. The wearing qualities of a material are in part dependent upon its hardness. 1-1A-9 GLOSSARY .T. HOMOGENIZING--Annealing or soaking at very high temperatures in order to reduce alloy segregation by diffusion. or brine. and minimum ductility. Hardness and strength are properties which are closely related for wrought alloys. HARDNESS--Hardness refers to the ability of a material to resist abrasion.Continued H HARDENABILITY--The ability of an alloy to harden fully throughout the entire section thickness either by cold working or heat treatment. sulphides. In iron when sulphur is in excess of the manganese necessary to combine with it to form manganese sulphide the excess sulphur combines with the iron to form iron sulphide. The maximum thickness at which this may be accomplished can be used as a measure of hardenability. grain size. INCLUSION--Particles of impurities. O. MECHANICAL WORKING--Subjecting metal to pressure exerted by rolls. MARTENSITE--It is the decomposition product which results from very rapid cooling of austenite. thus impairing the properties of the metal. NORMALIZING--Heating iron-base alloys to approximately 55oC (100oF) above the critical temperature range. followed by cooling to below that range in still air at ordinary temperatures. P PATENTING--Heating iron-base alloys above the critical temperature range followed by cooling below that range in air. the faster it must be cooled to obtain martensite. O OVERHEATING--Heating to such high temperatures that the grains have become coarse. yield strength. The stress in pounds per square inch is divided by the elongation in fractions of an inch for each inch of the original gage length of the specimen. MALLEABILITY--Malleability is the property of a material which enables it to be hammered. bending. or a molten mixture of nitrate or nitrites maintained at a temperature usually between 427o-566oC (800-1050oF). or hammers. rolled. or to affect the structure and therefore the mechanical and physical properties. MECHANICAL HARDNESS--See Hardness. tensile strength. This treatment is applied to wire and to medium or high carbon steel as a treatment to precede further wire drawing. cracks or seams in steel parts at or very close to the surface. Nitriding is conducted at a temperature usually in the range 502o-538oC (935o-1000oF) and produces surface hardening of the metal without quenching.depending on the carbon content of the steel and the properties required of the f inished product. and fatigue limit. Malleability refers to compression deformation as contrasted with ductility where the deformation is tensile. 1-1A-9 GLOSSARY . Glossary 7 . The lower the carbon content of the steel. forging. elastic and inelastic. to change its form. MECHANICAL TESTING--Testing methods by which mechanical properties are determined. within the limit of elasticity. This process is used to remove stresses caused by machining. or that involve the relationship between stress and strain. and welding. The test is accomplished by magnetizing the part with equipment specially designed for the purpose and applying magnetic powder. or in molten lead. MODULUS OF ELASTICITY--The ratio.Continued M (Cont) MAGNA FLUX TESTING--A method of inspection used to detect/locate defects such as cavities. MARTEMPERING--This is a method of hardening steel by quenching from the austenitizing temperature into a medium at a temperature in the upper part of or slightly above the martensite range and holding it in the medium until temperature is substantially uniform throughout the alloy is then allowed to cool in air through the martensite range. N NITRIDING--Adding nitrogen to iron-base alloys by heating the metal in contact with ammonia gas or other suitable nitrogenous material. for example. presses. or to be pressed into various shapes without fracture. MECHANICAL PROPERTIES--Those properties that reveal the reaction. wet or dry. of the stress in the corresponding strain. Flaws are then indicated by the powder clinging to them (see Section VIII for additional data). of a material to an applied force.T. welding. water 18oC (65oF). but this usage is not recommended. air. followed by coolings desired. also called ‘‘contraction of area. coeff icient of thermal expansion. QUENCHING MEDIA--Quenching media are liquids or gases in which metals are cooled by immersion. SENSITIZING--Developing a condition in stainless steels. This term has of ten been used to describe mechanical properties. This term is also inadvisedly used to mean the determination of the mechanical properties. R RECALESCENCE--When steel is slowly cooled from a point above the critical temperature. PROOF STRESS--The proof stress of a material is that load per unit area which a material is capable of withstanding without resulting in a permanent deformation of more than a specif ied amount per unit of gage length af ter complete release of load. 1-1A-9 GLOSSARY . At this time. Q QUENCHING--Rapid cooling by immersion in liquids or gases. electrical conductivity.O. This treatment is commonly applied to sheet and wire and the temperatures generally used are from 549o to 649oC (1020o to 1200oF). machine oil. POTENTIOMETER--Potentiometer 1s an instrument used to measure thermocouple voltage by balancing a known battery voltage against it.Continued P (Cont) PHYSICAL PROPERTIES--Those properties exclusive of those described under mechanical properties. This change is the opposite of decalescence and is termed recalescence.’’ REFINING TEMPERATURE OR HEAT--A temperature employed in case hardening to ref ine the case and core. Glossary 8 . for example. f ish oil. It is usually stated as a percentage of the original area. PYROMETER--An instrument for measuring temperature. e.T. the cooling proceeds at a uniform rate until the piece reaches a point between 677o and 704oC (1.300oF). the cooling is noticeably arrested and the metal actually rises in temperature as the change of state again takes place. which is susceptible to intergranular corrosion. PROCESS ANNEALING--Heating iron-base alloys to a temperature below or close to the lower limit of the critical temperature range. PROPORTIONAL LIMIT--The proportional limit of a material is the load per unit area beyond which the increases in strain cease to be directly proportional to the increases in atress. engine oil. PHYSICAL TESTING--Testing methods by which physical properties are determined.g.250o and 1. Some of the more common are brine (10 percent sodium chloride solution). S SCALE--A coating of metallic oxide that forms on heated metal. PICKLING--Removing scale from steel by immersion in a diluted acid bath. and commercial quenching oil.. The f irst quench is from a high temperature to ref ine the core and the second quench is from a lower temperature to further ref ine and harden the case. REDUCTION OF AREA--The difference between the original cross-sectional area and that of the smallest area at the point of rupture. The condition is usually formed by heating the steel above 800oF and cooling slowly. PLASTIC DEFORMATION--The permanent change in size or shape of a material under stress. paraff in base petroleum oil. density. THERMOCOUPLE--Thermocouple consists of a pair of wires of dissimilar metals connected at both ends. usually followed by relatively slow cooling. SPALLING--The cracking and f laking of small particles of metal from the surface. Glossary 9 . TENSION--That force tending to increase the dimension of a body in the direction of the force. blooms. When the two junctions are subjected to different temperatures an electric potential is set up between them. TOLERANCES--Slight deviations in dimensions or weight or both. 1-1A-9 GLOSSARY . T TEMPERING (ALSO TERMED DRAWING)--Reheating hardened steel to some temperature below the lower critical temperature. heat treating. and hence. (b) In the case of small objects of high carbon steels. SPHEROIDIZING--Any process of heating and cooling steel that produces a rounded or globular form of carbide. the spheroidizing result is achieved more rapidly by prolonged heating to temperatures alternately within and slightly below the critical temperature range. followed by any desired rate of cooling. holding at heat from 1 to 4 hours.Continued S (Cont) SHEETS COLD ROLLED--The f lat products resulting from cold rolling of sheets previously produced by hot rolling.T. It is computed from the maximum load carried during a tension test and the original cross-sectional area of the specimen. This voltage is almost in direct proportion to the temperature difference. SPHEROIDAL OR SPHEROIDIZED CEMETITE--The globular condition of iron carbide resulting from a spheroidizing treatment. welding or machining. SOAKING--Holding steel at an elevated temperature for the attainment of uniform temperature throughout the piece. the term ‘‘tempering’’ is preferred.O. The initial structure may be either pearlitic or martensitic. STRESS--The internal load per unit area. without material affecting other properties. Although the terms ‘‘tempering’’ and ‘‘drawing’’ are practically synonymous as used in commercial practice. (c) Tool steel is generally spheroidized by heating to a temperature of 749o-804oC (1380o-1480oF) for carbon steels and higher for many alloy tool steels. and cooling slowly in the furnace. The voltage measuring instrument is usually calibrated in oC or oF. SHEETS HOT ROLLED--The f lat-rolled products resulting from reducing sheet bars on a sheet mill. a voltage measuring instrument inserted in the circuit will measure temperature. or slabs. The anneal is accomplished at rather low temperatures for the primary purposes of reducing residual stresses. SOLIDIFICATION RANGE--The temperature range through which metal freezes or solidif ies. STRAIN--The elongation per unit length. V VISCOSITY--Viscosity is the resistance offered by a f luid to relative motion of its parts. The spheroidizing methods generally used are: (a) Prolonged heating at a temperature just below the lower critical temperature. TENSILE STRENGTH--The tensile strength is the maximum load per unit area which a material is capable of withstanding before failure. STRESS-RELIEF--This is annealing process which removes or reduces residual stresses retained af ter forming. and billets on a continuous strip-sheet mill. allowable in the various products. O. Glossary 10 . YIELD STRENGTH--Stress arbitrarily def ined as the stress at which the material has a specif ied permanent set (the value of 0. particularly cold working. Y YIELD POINT--The load per unit of original cross section at which a marked increase in deformation occurs without increase in load. 1-1A-9 GLOSSARY .Continued W WIRE--The product obtained by drawing rods through a series of dies. YOUNG’S MODULUS--See Modulus of Elasticity. WORK HARDNESS--Hardness developed in metal resulting from mechanical working.T.2% is widely accepted). 1-1A-9 NAVAIR 01-1A-9 TM 43-0106 By Order of the Secretaries of the U. SCHOOMAKER General. requirements for TM 43-0106. JUMPER General. MARTIN General. Usaf Chief of Staff GREGORY S.S.O. DISTRIBUTION: To be distributed in accordance with Initial Distribution Number (IDN) 340867. AFMC Army authentication for this publication includes the basic dated 26 February 1999 through Change 5 dated 27 June 2005. Air Force: Official: SANDRA R. RILEY Administrative Assistant to the Secretary of the Army 0514409 PETER J. .S.T. Army and U. United States Army Chief of Staff JOHN P. USAF Commander. . . 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