A1-F18AC-NFM-200

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A1-F18AC-NFM-200NATOPS FLIGHT MANUAL PERFORMANCE CHARTS NAVY MODEL F/A-18A/B/C/D EQUIPPED WITH F404-GE-400 ENGINES McDonnell Douglas Corporation DISTRIBUTION STATEMENT C. Distribution authorized to U.S. Government agencies only and their contractors to protect publications required for official use or for administrative or operational purposes only, determined on 1 August 2006. Other requests for this document shall be referred to Commander, Naval Air Systems Command (PMA-265), RADM William A. Moffett Bldg, 47123 Buse Rd, Bldg 2272, Patuxent River, MD 20670-1547. DESTRUCTION NOTICE - For unclassified, limited documents, destroy by any method that will prevent disclosure of contents or reconstruction of the document. THIS PUBLICATION SUPPLEMENTS A1-F18AC-NFM-000 NATOPS FLIGHT MANUAL FOR MODEL F/A-18A/B/C/D AIRCRAFT. ISSUED BY AUTHORITY OF THE CHIEF OF NAVAL OPERATIONS AND UNDER THE DIRECTION OF THE COMMANDER, NAVAL AIR SYSTEMS COMMAND. 0801LP1059510 15 JANUARY 1993 CHANGE 7 - 1 AUGUST 2006 A1-F18AC-NFM-200 LIST OF EFFECTIVE PAGES Insert latest changed pages; dispose of superseded pages in accordance with applicable regulations. Dates of issue for original and changed pages: Original ............ 0 ....... 15 Jan 93 Change.............. 1 ....... 15 Jan 94 Change.............. 2 ....... 15 Jan 97 Change.............. 3 .......15 Feb 98 Change.............. 4 ..... 15 May 00 Change.............. 5 ........15 Jul 01 Change.............. 6 ........ 1 Nov 04 Change.............. 7 ........ 1 Aug 06 Total number of pages in this publication is 336 consisting of the following: Page No. #Change No. Title .............................................7 A...................................................7 B...................................................7 C...................................................7 D ..................................................0 E blank........................................0 i ....................................................0 ii ...................................................0 iii ..................................................0 iv 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Change 7 B A1-F18AC-NFM-200 INTERIM CHANGE SUMMARY The following Interim Changes have been cancelled or previously incorporated in this manual: INTERIM CHANGE NUMBER(S) REMARKS/PURPOSE The following Interim Changes have been incorporated in this Change/Revision: INTERIM CHANGE NUMBER REMARKS/PURPOSE 1 Interference Code Numbers. Interim Changes Outstanding - To be maintained by the custodian of this manual: INTERIM CHANGE NUMBER C ORIGINATOR/DATE (or DATE/TIME GROUP) Change 7 PAGES AFFECTED REMARKS/PURPOSE A1-F18AC-NFM-200 SUMMARY OF APPLICABLE TECHNICAL DIRECTIVES Information relating to the following technical directives has been incorporated in this manual. Change Number ECP Number AFC 102 00300 LEX Fence Installation LEX Fence 00285 BRU-33/A Design Change Canted VER Description Visual Identification Effectivity (R)161353 thru 161924 (P)161925 and up Information relating to the following recent technical directives will be incorporated in a future change Change Number ECP Number Description Visual Identification Effectivity D/(E blank) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 3-1* SECTION IV FLIGHT CHARACTERISTICS . . . . . . . . . . . . . . . . . . . . . . . . . . 4-1* SECTION V EMERGENCY PROCEDURES . . . . . . . . . . . . . .A1-F18AC-NFM-200 TABLE OF CONTENTS SECTION TITLE PAGE SECTION I THE AIRCRAFT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Index-1 FOLDOUTS . . . . . . . . . . . . . . 7-1* SECTION VIII WEAPONS SYSTEMS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11-1 APPENDIX . . . . . . . . . . . . . . . . . . . . . 5-1* SECTION VI ALL WEATHER OPERATION. . . . . . . . . . . . . . . . . . . . . . 8-1* SECTION IX FLIGHT CREW COORDINATION . . . . . . . . . . . . . . . . . . . . . 9-1* SECTION X NATOPS EVALUATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Index-1* ALPHABETICAL INDEX (SECTION XI ONLY) . . . . . . . . i . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 2-1* SECTION III NORMAL PROCEDURES . . . . . . . . . . . . . . . . . . . . . . . . . FO-1* * Refer to NATOPS Flight Manual. . . . . . . A1-F18AC-NFM-000. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1-1* SECTION II INDOCTRINATION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 6-1* SECTION VII COMMUNICATION-NAVIGATION EQUIPMENT AND PROCEDURES . . . . . . . . 10-1* SECTION XI PERFORMANCE DATA . . . . . . . . . . . . . . . . . . . . . . . . A-1* ALPHABETICAL INDEX . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . adverse weather or terrain. have your Central Technical Publication Librarian send a revised ADRL report on floppy disk to NAVAIRTECHSERVFAC. then send a letter to Commanding Officer. Once established on automatic distribution for this or any other NAVAIR technical publication. However. or considerations affecting the lives and property of others may require modification of the procedures contained herein.A1-F18AC-NFM-200 FOREWORD SCOPE The NATOPS Flight Manual Performance Charts are issued by the authority of the Chief of Naval Operations and under the direction of Commander. It can not be used to make one time orders of publications from current stock. see ONE TIME ORDERS above. it is not a substitute for sound judgement. order it from stock by sending an electronic DD 1348 requisition IAW NPFC pub 2002D. NAVAIRTECHSERFAC. If your activity does not have a library. PA 19111 requesting assignment of a distribution account number (if necessary) and automatic mailing of future issues of the publication(s) needed. 700 Robbins Avenue. . This manual contains information on performance data and effective operations. . Philadelphia. Naval Air Systems Command in conjunction with the Naval Air Training and Operating Procedures Standardization (NATOPS) Program. APPLICABLE PUBLICATIONS The following applicable publications complement this manual: A1-F18AC-NFM-000 (NATOPS Flight Manual) A1-F18AC-NFM-210 (Performance Data Charts for aircraft with F404-GE-402 engines) A1-F18AC-NFM-500 (Pocket Checklist for aircraft with F404-GE-400 engines) A1-F18AC-NFM-510 (Pocket Checklist for aircraft with F404-GE-402 engines) A1-F18AC-NFM-600 (Servicing Checklist) A1-F18AC-NFM-700 (Functional Checkflight Checklist) A1-F18AC-TAC-000/A1-F18AE-TAC-000 (Volume I Tactical Manual) A1-F18AC-TAC-010/A1-F18AE-TAC-010 (Volume II Tactical Manual) A1-F18AC-TAC-100 (Volume III Tactical Manual) A1-F18AC-TAC-020 (Volume IV Tactical Manual) A1-F18AC-TAC-300 (Tactical Manual Pocket Guide) One Time Orders If this publication is needed on a one time basis (without future updates). Attn: Code 32. your activity must submit an ADRL report on floppy disk at least once every 12 months to update or confirm their automatic distribution requirements. NOTE The ADRL floppy disk can be used only to place an activity on the mailing list for automatic distribution of future issues of the publications. If you have a continuing need for this publication. ii Activities not submitting an ADRL report on floppy disk for more than 12 months may be dropped from distribution of all NAVAIR technical publications. Philadelphia. PA. To get publications from stock. Automatic Distribution (with updates) This publication and changes to it are automatically sent to activities who are established on the Automatic Distribution Requirements List (ADRL) maintained by Naval Air Technical Services Facility (NAVAIRTECHSERVFAC). NOTE HOW TO GET COPIES Each flight crewmember is entitled to personal copies of the NATOPS Flight Manual and appropriate applicable publications. It’s your responsibility to have a complete knowledge of its contents. Read this manual from cover to cover. Compound emergencies. . S. Commanding Officer VFA-125 U.7 series. CA 93245-0125 Attn: F/A-18 Model Manager Autovon: 949-1727 Commercial: (209) 998-1727 Change recommendations of an URGENT nature (safety of flight. NATOPS review conferences are held in accordance with OPNAVINST 3710. Routine change recommendations are submitted directly to the Model Manager on OPNAV Form 3710/6 shown on the next page.7 series.) should be submitted directly to the NATOPS Advisory Group Member in the chain of command by priority message. Naval Air Station Lemoore. The address of the Model Manager of this aircraft is: iii . etc. CHANGE RECOMMENDATIONS Recommended changes to this manual or other NATOPS publications may be submitted by anyone in accordance with OPNAVINST 3710.A1-F18AC-NFM-200 UPDATING THE MANUAL To ensure that the manual contains the latest procedures and information. . It will be held for action of the review conference planned for r to be held at Your change recommendation is reclassified URGENT and forwarded for approval to by my DTG /S/ AIRCRAFT MODEL MANAGER iv .A1-F18AC-NFM-200 NATOPS/TACTICAL CHANGE RECOMMENDATION OPNAV/FORM 3710/6(4-90) S/N 0107-LF-009-7900 DATE TO BE FILLED IN BY ORIGINATOR AND FORWARDED TO MODEL MANAGER FROM (originator) Unit TO (Model Manager) Unit Complete Name of Manual/Checklist Revision Date Change Date Section/Chapter Page Paragraph Recommendation (be specific) r CHECK IF CONTINUED ON BACK Justification Signature Rank Title Address of Unit of Command TO BE FILLED IN BY MODEL MANAGER (Return to Originator) FROM Date TO Reference (a) Your change Recommendation Dated r Your change recommendation dated is acknowledged. at once. This concept was selected for a number of reasons: reader interest increases as the size of a technical publication decreases.. or condition. An operating procedure. but detailed operation and interaction is not provided. a changed procedure. CAUTIONS. ‘‘May’’ and ‘‘need not’’ have been used only when application of a procedure is optional. practice.. MANUAL DEVELOPMENT This NATOPS Flight Manual was prepared using a concept that provides the aircrew with information for operation of the aircraft. The Interim Change Summary page is provided as a record of all interim changes. etc. or as a naval message. AND NOTES The following definitions apply to ‘‘WARNINGS’’. or constructive suggestions for improvement of its content should be submitted by routine or urgent change recommendation. NATOPS FLIGHT MANUAL INTERIM CHANGES NOTE NATOPS Flight Manual Interim Changes are changes or corrections to the NATOPS Flight Manuals promulgated by CNO or NAVAIRSYSCOM. An operating procedure. WORDING The concept of word usage and intended meaning which has been adhered to in preparing this Manual is as follows: ‘‘Shall’’ has been used only when application of a procedure is mandatory. the custodian of the manual should check the updated Interim Change Summary to ascertain that all outstanding interim changes have been either incorporated or canceled. ‘‘Will’’ has been used only to indicate futurity.. as appropriate. never to indicate any degree of requirement for application of a procedure. adjacent to the affected text. practice. or condition. ‘‘CAUTIONS’’. Upon receipt of a change or revision. etc. comprehension increases as the technical complexity decreases. WARNING.A1-F18AC-NFM-200 YOUR RESPONSIBILITY NATOPS Flight Manuals are kept current through an active manual change program. or condition. etc. and ‘‘NOTES’’ found throughout the manual. An operating procedure. Any corrections. Interim Changes are issued either as printed pages. AIRSPEED All airspeeds in this manual are in knots calibrated airspeeds unless stated in other terms. The change symbol identifies the addition of either new information. and accidents decrease as reader interest and comprehension increase. like the one printed next to this paragraph. which may result in damage to equipment if not carefully observed or followed. which may result in injury or death. if not carefully observed or followed. the correction of an error. practice. additions. CHANGE SYMBOLS Revised text is indicated by a black vertical line in either margin of the page. or a rephrasing of the previous material. those not incorporated shall be recorded as outstanding in the section provided. ‘‘Should‘‘ has been used only when application of a procedure is recommended. v . which is essential to emphasize. and no abnormal procedures (Hot Starts. . e. temperature.A1-F18AC-NFM-200 To implement this streamlined concept. almost everything in the manual could be considered a subject for a Note. c. quantity. etc. and Warnings are held to an absolute minimum. except where such use provides the pilot with a value judgement. A careful study of the NATOPS Flight Manual will probably disclose a violation of each rule stated. Caution. The pilot shall be considered to have aboveaverage intelligence and normal (average) common sense. vi f. g. since. Notes. In some cases this is the result of a conscious decision to make an exception to the rule. Notes. No values (pressure. b. Multiple failures (emergencies) are not covered. it only demonstrates the constant attention and skill level that must be maintained to prevent slipping back into the old way of doing things. observance of the following rules was attempted: a. d. . Simple words in preference to more complex or quasi-technical words are used and unnecessary and/or confusing word modifiers are avoided. etc. Only the information required to fly the airplane is provided. the ‘‘Streamlined’’ look is not an accident. or Warning.) are contained in the Normal Procedures Section. No Cautions or Warnings or procedural data are contained in the Descriptive Section. h. Cautions.) which cannot be read in the cockpit are stated. Cautions and Warnings will not be used to emphasize new data. In many cases. it takes constant attention for the NATOPS Flight Manual to keep its lean and simple concept to provide the pilot with the information required. In other words. ...................................................................................................................................................... 11-85 PART 5 ENDURANCE ..................................... 11-238 PART 7 DESCENT ........................A1-F18AC-NFM-200 Section XI SECTION XI PERFORMANCE DATA F404-GE-400 Engines PART 1 STANDARD DATA ................................................................................... 11-298 11-1 ............................................................... 11-38 PART 4 RANGE ................... 11-3 PART 2 TAKEOFF .............................................. 11-23 PART 3 CLIMB ..................................................................................................................................................................................................... 11-229 PART 6 IN-FLIGHT REFUELING ................................ 11-258 PART 9 MISSION PLANNING.................................................................................................................................................................................................. 11-262 PART 10 EMERGENCY OPERATION ........................................................................................................................................... 11-239 PART 8 LANDING...................................................................................................................................... the density altitude will be lower than the pressure altitude. . Consequently. GLOSSARY OF TERMS Indicated Airspeed Indicated airspeed (IAS) is the pitot static airspeed indicator reading. True Airspeed True Airspeed (TAS) is the aircraft speed over the ground in no-wind conditions. as installed in the aircraft. fuel flows and fuel used quantities will be approximately 1% lower. True airspeed is EAS corrected for density altitude. without correction for system errors. atmospheric pressure. there is no significant difference between using JP-5 or JP-8. All reference to gallons is U. U. When conditions are standard. This is a theoretical plane where air pressure (corrected to 15°C) is equal to 29. Density Ratio Density ratio is a single factor representation of a combination of temperature and pressure altitude. Nosewheel Lift-off speed is the speed at which the nosewheel lifts off the ground. Equivalent Airspeed Equivalent airspeed (EAS) is calibrated airspeed corrected for adiabatic compressible flow for the particular altitude. EAS is equal to CAS at sea level in standard air.S. and using JP-5 fuel. if the temperature is above standard.92 inches of mercury (Hg). If the temperature is below standard. Calibrated Airspeed Calibrated airspeed (CAS) is indicated airspeed corrected for static source error. The indicated pressure altitude may not be the actual height above sea level due to variations in temperature. Combat Ceiling Combat ceiling is the altitude where the rate of climb is 500 feet per minute at either military (MIL) or maximum afterburner (MAX AB) rated power. lapse rate. standard day. pressure altitude and density altitude are the same. Unless noted otherwise.S. 1962 conditions and/or provisions to correct for non-standard temperatures. gallons. . 11-2 Pressure Altitude Pressure Altitude is the vertical distance from the standard datum. Density Altitude Density altitude is pressure altitude corrected for temperature. the density altitude will be higher than the pressure altitude. Takeoff Speed Takeoff speed is the speed at which the main gear lifts off the ground. When using JP-4 fuel.Section XI A1-F18AC-NFM-200 INTRODUCTION Nosewheel Lift-Off Speed This section is divided into parts 1 thru 10 to present performance data in proper sequence for preflight planning. All data are based on flight test or the contractor’s estimate. and errors on the sensed pressure. .. Angle of Attack Conversion .. The basic aircraft is defined as an F/A 18 configured with wingtip AIM-9 missiles and has a Drag Index equal to zero (DI=0)............................... Interference drag develops between stores on adjacent wing and fuselage stations... As drag information is obtained it is entered on a Drag Computation Form (figure 11-1)....... Stall Speeds ...... TABLE OF CONTENTS Charts Sample Drag Computation... the basic store drag and the interference drag........ 11-7 11-8 11-10 11-12 11-13 11-14 11-15 11-17 11-19 11-21 11-22 DRAG INDEX SYSTEM Cruise....... Summary of Store Drag Index Numbers ... Airspeed Conversion ...... Basic store drag is the drag count assigned to specific stores and their associated suspension equipment........ The magnitude of this drag is a function of the distance between stores..... Two types of drag must be accounted for when determining the total drag index with external stores................................................ interference drag increases as the distance between stores decreases. Standard Atmosphere Table... climb.......... and as angle of attack decreases.... The basic aircraft configured with LEX fences has a Drag Index equal to six (DI=6.......... Interference Code Numbers..Section XI Part 1 A1-F18AC-NFM-200 PART 1 ......... Altimeter Position Error Correction..6 Mach... range......STANDARD DATA F404-GE-400 angle of attack. endurance...... as airspeed increases above 0.... and aircraft SAMPLE PROBLEM The following sample problem is presented to demonstrate the method of computing both types of drag... Airspeed Position Error Correction ... Station Store Load 1 Wingtip AIM-9 2 (2) VER mounted Mk-83 LD 3 330 gallon fuel tank 4 FLIR 5 330 gallon fuel tank 6 LDT 7 330 gallon fuel tank 8 (2) VER mounted Mk-83 LD 9 Wingtip AIM-9 11-3 ............ and descent charts contained in this section are presented in a drag index format....... Total drag at various Mach numbers and dash angle of attack is calculated for the following interdiction mission store loading. In general................. airspeed....0) for the F/A 18B/D. Interference Code Number To Interference Drag Index Number Conversion.......0) for the F/A 18A/C and one (DI=1.. Temperature Conversion ....... Before using the charts a total drag index figure (drag count) for the specific aircraft configuration must be determined... . The interference DI is a function of Mach number and either cruise AOA (greater than approximately 2. These code numbers are used to compute an approximate interference drag index. The interference drag index is presented as a function of total interference code number and dash angle of attack or cruise angle of attack (figure 11-4). To calculate an interference DI number it is first necessary to obtain the interference code number corresponding to loadings which produce interference drag. the dash angle of attack chart is used. Using the example station 2 load (pylon.4). For example.Section XI Part 1 A1-F18AC-NFM-200 Determining the Basic Store Drag Sample Problem Basic store drag is the additional drag imposed when external stores are carried. The interference code numbers for the other stations producing interference drag can also be found in the table.5). The total of the drag on all stations is the basic store drag index (for the interdiction load example. For the sample problem considered. the basic store drag index is 28.9. Cruise AOA Mach number C.5° or lower). Dash AOA Interference DI number 14 . Only the loadings that generate interference drag are given an interference code. DI = 132. 11-4 .85 30 14 . VER. A. and (2) MK-83 LD).4 gives the interference drag indexes shown on the drag computation form (figure 11-1). The individual code numbers are then summed to obtain a total interference code number for the configuration (for the interdiction load example. The interference DI charts (figure 11-4) are used to convert the configuration total interference code number to a DI number. Interference code number B. Wing tip mounted missiles and stores on the centerline station do not produce interference drag.85 41 Determining Interference Drag Because of the large combination of stores which can be carried. The drag for each of the other stations (including fuselage stations) is similarly found and recorded in the Drag Computation Form (figure 11-1). AIRSPEED CONVERSION CHART The Airspeed Conversion chart (figure 11-7) provides a means of converting calibrated airspeed to true Mach number and true airspeed. The total interference code number of 12. Cruise AOA Interference DI number D.5. The drag index values for selected stores in the inventory are presented in figure 11-2.5°) or dash AOA (approximately 2. Interference code number E. total interference code = 12. Dash AOA Mach number F. a table of interference drag code numbers (figure 11-3) has been devised to aid in computing interference drag while carrying any combination of external stores. the two VER mounted MK-83 LD on the outboard station pylon produce interference drag with the 330 gallon fuel tank on the inboard pylon station. using the sample configuration. The interference code number representing this drag equals 3. the standby altimeter can be used. Mach Number (sheet 2) A. Altitude correction (∆H) D. 1. Indicated airspeed B. 20. Altitude reflector C.490 Ft. if a malfunction of the ADC occurs. 19. True Mach Number Enter the applicable chart with the indicated Mach number or indicated airspeed. these readings must be corrected by means of the Altimeter Position Error Correction chart (figure 11-9.000 feet and 40. However. sheets 1 and 2 ) provides a direct-reading conversion from indicated airspeed to calibrated airspeed and from indicated Mach number to true Mach number.000 Ft. Project vertically upward to intercept the applicable altitude curve.000 feet.000 feet and for indicated Mach numbers up to 1. Indicated Airspeed (sheet 1) USE A. However. Calibrated airspeed 500 Kt.A1-F18AC-NFM-200 Section XI Part 1 AIRSPEED POSITION ERROR CORRECTION CHARTS ALTIMETER POSITION ERROR CORRECTION CHARTS Under normal conditions. Indicated Mach number B.0 Sample Problem 1. Apply ∆H to the assigned altitude and fly assigned altitude +∆H. position error must be applied to the cockpit standby indication. Altitude C. Assigned altitude C.000 Ft. then horizontally left to read the altitude correction (∆H). 20. Indicated Mach number B.7 Mach at altitudes of sea level. 11-5 .1 20. If the ADC fails in flight. 510 Kt. the air data computer (ADC) compensates for the static source position error. -510 Ft. Sample Problem Under normal operating conditions. Assigned altitude +∆H(B+C) 1. These charts provides altitude correction (∆H) for indicated airspeeds up to 220 knots below 10. These charts (figure 11-8. sheets 1 and 2). airspeed position error is automatically compensated for by the air datacomputer system (ADC).07 A. Configuration: Gear Down. and maneuvering configurations. . B. Sample Problem Sample Problem A. USE Enter the chart with the applicable gross weight and project vertically up to intersect the 0° bank angle. From this intersection. then horizontally left to read stall speed. project vertically up to the appropriate power setting curve. From this point. project horizontally right to the appropriate bank angle. Bank angle 45° E. Gross weight 35. approach. C. D. Flaps 30° A. project horizontally left to read the corresponding angle of attack for the specified flight condition/ configuration. Gross weight 35. B. Stall speed curve (MIL) C. Corresponding angle of attack 6. Stall speed 106 Kt.5° 11-6 . The data are based on catapult. From this intersection. Enter the applicable plot at the airspeed scale and project vertically up to intersect the appropriate aircraft gross weight curve. Stall speed 133 Kt. bank angle and power setting at maximum lift.000 Lb.Section XI Part 1 A1-F18AC-NFM-200 STALL SPEEDS CHART The Stall Speeds chart (figure 11-10) presents stall speeds for various combinations of gross weight.000 Lb. USE ANGLE OF ATTACK CONVERSION CHART This chart (figure 11-11) presents the corresponding angle of attack in degrees for various combinations of calibrated airspeed and gross weight. Calibrated airspeed 160 Kt. The data are based on stabilized 1 G level flight conditions with separate plots for 30° and 45° flap settings both with landing gear down. A1-F18AC-NFM-200 Figure 11-1. Sample Drag Computation Section XI Part 1 11-7 . 0 pylon: 6.2 CL: 10.5 CVER: 9.5 cruise 0 on wingtips: -4.366 1.5 dash.3 dash. 7.0.0 pylon: 5.0 LAU-115: 6.0 1 on wingtips: -2.2212 1. -8. P/N suffix 1019 or 1021 fuselage: 4. pilot option LD/HD 1. 15.-6.5 CVER: 9.0 LAU-117: 10.2132 1.0 . -3. TDD or ogive nose MAU-91 Retard 9954 9894 1.0 cruise 2 under wing on LAU-7 or LAU-127: 6.0 2 on wingtips: 0. M904 or blunt nose Mk 83 CFA.055 330-gal circular.1641 1.-4.0314 MAU-93 CFA.530 JP5 290 empty Mk 83 CFA.0 pylon: 7.0 each (Wingtip drag also applies to TACTS pods) fuselage: 4.5 CVER: 9.0 (C)VER: 6.5 wing: 14.043 1. Med. pilot option LD/HD BSU-33 CFA.1691 1.000-lb TP Bomb BLU-111A/B 500-lb TP Bomb CBU-78 TP Gator CBU-99 TP Rockeye II CBU-100 NTP Rockeye II Figure 11-2. Rng.-8: captive trainer CATM-9L/M-2.0 pylon: 10.0 pylon: 11. TDD or ogive nose CBU-78/B & CBU-78B/B: Mk 339 CBU-78A/B: FMU-140 CBU-99/B: Mk 339 CBU-99A/B: FMU-140 CBU-100/B: Mk 339 CBU-100A/B: FMU-140 5154 5094 5604 5604 5164 5104 491 494 506 509 490 493 315-gal elliptical. Air-to-Air Msl.2212 1.5 LAU-118: 9. -4.5 pylon: 11. -6.056 BSU-85 Retard.0 pylon: 7. -8: improved IRCCM AIM-9 NATM-9L/M-1: live trainer--smoke/flash Sidewinder NATM-9L/M-2: live trainer--telemetry CATM-9L/M-2.Section XI Part 1 A1-F18AC-NFM-200 SUMMARY OF STORE DRAG INDEX NUMBERS STORE VERSION INTERNAL CANNON M61 M61A1 (to BuNo 164724) Internal Cannon M61A2 light cannon (from BuNo 164725) MISSILES AIM-7M: monopulse seeker AIM-7M (H-build): improved GCS AIM-7 AIM-7P: improved low altitude capability Sparrow III ATM-7M: live trainer--telemetry ‘warhead’ ATM-7P: live trainer--telemetry ‘warhead’ CATM-7F-3: captive trainer AIM-9L-1: all-aspect AIM-9M-1.4 pylon: 8.5 BOMBS BLU-110A/B 1.360 800 800 800 800 1.0 CL: 10.1691 1. -6.0 (C)VER: 7.0 pylon: 7.360 1.151 1. Summary of Store Drag Index Numbers (Sheet 1 of 5) 11-8 Change 5 pylon: 5. without fins/wings AIM-120A.0 pylon: 3. Adv. TDD or ogive nose Mk 15 Mod 6A Snakeye. LAU-127: 5. M904 or blunt nose MAU-93 CFA. AIM-120 AIM-120B AMRAAM JAIM-120A or B Air Vehicle.448 JP5 308 empty 2.-4. LD/HD BSU-86 Retard. P/N suffix 1005 (For empty ferry on stations 2/8) 2. Inst’d (AAVI) AGM-65 Maverick AGM-84 Harpoon AGM-84E SLAM AGM-88 HARM AGM-154 JSOW FUEL TANKS FPU-6/A External Fuel Tank FPU-8/A External Fuel Tank AGM-65E: Laser Guided A/A37A-T9: TGM-65E: captive laser trainer AGM-65F: imaging infrared guided CATM-65F: captive IIR trainer AGM-84C-1: Block 1B AGM-84D-1: Block 1C ATM-84C-1: exercise--telemetry ‘warhead’ ATM-84D-1: exercise--telemetry ‘warhead’ ATM-84C-1A: exercise--inert warhead ATM-84D-1A: exercise--inert warhead ATM-84A-1C: inert captive trainer CATM-84D-1: inert captive trainer AGM-84E-1C Standoff Land Attack Missile ATM-84E-1C: exercise--telemetry ‘warhead’ CATM-84E-1C: captive trainers AGM-88A: Block I & II seekers AGM-88B: Block II & III seekers AGM-88C: Block IV seekers3 CATM-88A/B/C: captive trainers AGM-154A: 145 X BLU-97A/B CEM CATM-154A: Captive Flight Vehicle (CFV) WEIGHT PER STORE LB CARRIAGE/DRAG 530 475 0 509 510 509 509 509 510 196 196 200 196 195 163 347 347 330 642 642 669 669 1.0 (C)VER: 4.0 (C)VER: 6.151 1. M904 or blunt nose BSU-33 CFA.0 pylon: 3.0 (C)VER: 4. TP.0 506 509 490 5134 5074 5224 5164 5584 5674 5584 5674 5144 5084 5234 5174 9864 9804 1. TP. TP.1145 2. M904 or blunt nose MAU-93 CFA. NTP MAU-93 CFA. TDD or ogive nose Mk 15 Mod 6 Snakeye.1535 6105 6195 1.1125 1. NTP. LD/HD Inert Mk 82 BSU-86 Retard NTP. M904 or blunt nose Mk 83 Mk 83 CFA. HD only (Mod 4: NTP MAU-91 retard. NTP. TP.6 pylon: 3. NTP.0 5 fwd: 1. M904 or blunt nose MAU-93 CFA.6 fwd: 1.0 (C)VER: 7. pilot option LD/HD Mk 84 Mk 84 Mods 4/7.0 (C)VER: 4.0 (C)VER: 6.0 pylon: 5. TP TDD or ogive nose Mk 83 CFA. M904 or blunt nose BSU-33 CFA. TP. LD/HD Mk 82 Mk 15 Mod 6A Snakeye.0 pylon: 3.0 pylon: 5. CFA PRACTICE STORES BDU-33 BDU-33D/B: LD practice bomb Practice Bomb carried on (I) MERs MAU-93 CFA. NTP. LD/HD BDU-45/B Mk 15 Mod 6A Snakeye. TP. TP. Summary of Store Drag Index Numbers (Sheet 2) Change 2 11-9 .043 1.0 (C)VER: 6.0 fwd: 1.5 pylon: 9. NTP. TP. M904 or blunt nose BSU-33 CFA. M904 or blunt nose BSU-33 CFA. TP. TDD or ogive nose BSU-33 CFA. TP.1 aft: 0. NTP.396 pylon: 16. M904 or blunt nose MAU-93 CFA. pilot option LD/HD spotting charges BSU-33 CFA.0 pylon: 5. TP.3 aft: 0.062 1.3 aft: 0. NTP.0 pylon: 3.5 2. FIRE BOMBS Mk 77 Mod 4: 71 gal.Section XI Part 1 A1-F18AC-NFM-200 SUMMARY OF STORE DRAG INDEX NUMBERS (Continued) STORE VERSION NTP GBU-10D/B & E/B TP GBU-10D/B & E/B NTP GBU-12C/B & D/B TP GBU-12C/B & D/B NTP GBU-16A/B & B/B TP GBU-16A/B & B/B Low Level Laser Guided Bomb TP GBU-24B/B Mk 20 Mod 11: Mk 339 fuze TP Mk 20 Mk 20 Mod 9: FMU-140 fuze. NTP. TDD or ogive nose MAU-93 CFA. LD/HD 500-lb Bomb BSU-86 retard NTP. HD only Mod 5: TP) BSU-85 retard. TP Rockeye II Mk 20 Mod 12: Mk 339 fuze. pilot option LD/HD BSU-85 retard. TDD or ogive nose BDU-48 BDU-48/B: HD practice bomb carried Practice Bomb on (I)MERs Mk 76 Mk 76 Mod 5: LD practice bomb Practice Bomb carried on (I)MERs Mk 106 Mk 106 Mod 5: HD practice bomb Practice Bomb carried on (I)MERs Laser Guided Training Round LGTR Carried on bottom (I)MER stations. pilot option LD/HD w/side-mounted BSU-86 Retard.0224 1.9924 2.5 CVER: 10.0 pylon: 11.0 (C)VER: 4.7 fwd: 1. TDD or ogive nose BSU-33 CFA.0 (C)VER: 4.000-lb Bomb Mk 84 Mods 3/5/6.0 (C)VER: 4. TP. pilot option LD/HD (Mod 1: NTP BSU-86 retard. NTP.1315 CARRIAGE/DRAG pylon: 15.5 CVER: 9. M904 or blunt nose Mk 83 CFA.5 10 25 Figure 11-2.0 pylon: 6. of gelled AVGAS Fire Bomb Mod 5: 43 lb imbiber beads + 63 gal of jet fuel GBU-10 (Mk 84) LGB GBU-12 (Mk 82) LGB GBU-16 (Mk 83) LGB GBU-24 (BLU-109) LLLGB WEIGHT PER STORE LB 2. TP.0054 9994 1. NTP.0 pylon: 7. TP. TDD or ogive nose MAU-93 CFA.0 (C)VER: 6.7 89 (I)MER: 3 520 520 pylon: 8. TDD or ogive nose Mk 15 Mod 6 Snakeye. NTP. TP. NTP. pilot option LD/HD Mod 2: TP) BSU-33 CFA. CFA 2. TDD or ogive nose 1. M904 or blunt nose MAU-93 CFA. TP.0 pylon: 5. NTP. NTP. M904 or blunt nose BSU-33 CFA.0 25 5024 4964 5114 5054 5474 5564 5474 5564 5034 4974 5124 5064 pylon: 3. NTP.0414 1.1 aft: 0. TDD or ogive nose Mk 83 CFA.000-lb Bomb MAU-91 retard.0314 pylon: 7. NTP OA 03: Mk 15 Mod 6A Snakeye. with fairing MARINE LOCATION MARKER Marine Location Marker: carried on Mk 58 MLM bottom and outboard (I)MER stations FLARES/MARKERS (EXTERNAL CARRIAGE) LUU-2A/B 1.130 1076 1366 1607 787 5528 5618 5368 5458 5528 5618 1. with fairing TP Quickstrike Mine Mods 0/1. Phase II Haze Penetrator (without wings) ROCKET LAUNCHERS LAU-10 LAU-10C/A: NTP 4 x 5.446 pylon: 5.75-inch (nose fairing adds 5. NTP OA 09: BSU-86 retard.6 Mcp for 5 minutes.415 2.Section XI Part 1 A1-F18AC-NFM-200 SUMMARY OF STORE DRAG INDEX NUMBERS (Continued) STORE VERSION EO GUIDED WEAPONS AGM-62A Mk 21 ER/DL. OA 01/02.224 1. TP Destructor OA 51/51K: Mk 12 paratail. WEIGHT PER STORE LB CARRIAGE/DRAG 1.354 pylon: 36. Phase II EO-Guided Bomb Mk 34 ER/DL. CV ops OK.0228 pylon: 14.0 pylon: 8. NTP OA 48: Mk 15 Mod 6A.0038 1. Mk 66 motors only 19 x 2. Phase II 2.0 w/o fairing: 12.5 (C)VER: w/fairing: 3.0-inch Zuni LAU-10D/A: TP Rocket Pod Mk 71 Mod 0 or Mod 1 motors LAU-61 LAU-61C/A. Mod 0: with fairing NTP Bottom Mine Mk 56 OA 06/06K/10/12. OA 01/01K NTP Moored Mine (enCAPsulated Mk 46 TORpedo) OA 03/03K: Mk 15 Mod 6 Snakeye.75-inch (nose fairing adds 2. Mod 0: with fairing NTP Moored Mine Mk 60 CAPTOR Mods 0/1. No CV ops.0 5528 5618 5368 5458 5528 5618 1.0 Mcp for 4 minutes.0 pylon: 5.063 pylon: 16. TP Mk 65 Mod 0/1.0 (C)VER: 6. Phase II Haze Penetrator Walleye PGW Mk 27 captive DL.0568 1.0 aft: 1. LUU-2 Paraflare LUU-2B/B 2.000-lb Mk 29 ER/DL.0 13 fwd: 3.0 (C)VER: w/fairing: 8.0 pylon: 11. TP OA 48/48K: MAU-91 retard.224 2. Mk 66 motors only 7 x 2.0 aft: 1. TP Mk 52 OA 05K: Mod 0: with fairing NTP Bottom Mine Mk 55 OA 04K.0 pounds) Rocket Pod MINES OA 48/48K: Mk 15 Mod 6 Snakeye. Snakeye.7 pounds) Rocket Pod LAU-68 LAU-68D/A. TP OA 03/03K: MAU-91 retard.0758 1.0 2. TP (Mod 0) OA 09/09K: BSU-86 retard.5 pylon: 12.130 1.0 (C)VER: w/fairings: 7. Summary of Store Drag Index Numbers (Sheet 3) 11-10 Change 2 .0 pylon: 16. NTP (Mod 0) OA 06: Mk 12 paratail.0 pylon: 9.0 2. TP. NTP (Mods 7/15) OA 51: Mk 12 paratail.0758 1. TP Mk 36 OA 51: Mk 16 paratail.059 pylon: 25.0 w/o fairings: 25. Phase II Haze Penetrator Mk 23 ER/DL. Phase I (Practice Guided Mk 38 captive DL.0 CVER: 10.0568 1. TP (Mods 7/15) OA 54: BSU-86 retard.415 2. .0 w/o fairing: 31.415 1.000-lb EOGB Mk 37 ER/DL. NTP Quickstrike Mine OA 06: Mk 16 paratail. TP Mk 62 OA 06/06K: Mk 16 paratail. NTP Mk 40 OA 48: MAU-91 retard.0 2.0 (C)VER: 6. TP.5 Figure 11-2.5 1.0 CVER: 10.130 1. OA 01K. Phase I Haze Penetrator Weapon) Mk 39 captive DL. NTP Destructor OA 51: Mk 16 paratail.224 1. Phase I Walleye I 1. NTP OA 54: BSU-86 retard.5 30 30 fwd: 3.309 2.0 pylon: 9.210 pylon: 25. TP Quickstrike Mine OA 06/06K: Mk 12 paratail. NTP Mk 63 OA 03: MAU-91 retard.0228 2.0038 1.0 pylon: 11. Phase I Walleye II Mk 30 ER/DL. 0 65 65 0 135 pylon: 3.5 wingtip: * LAU-115: 2.0 76 76 175 200 240 124 90 90 (2 = 180) n/a n/a pylon: 9. Summary of Store Drag Index Numbers (Sheet 4) Change 3 11-10A .0 97 pylon: 4. RACKS.0) 52 pylon: 3.Section XI Part 1 A1-F18AC-NFM-200 SUMMARY OF STORE DRAG INDEX NUMBERS (Continued) STORE PODS AAR-50 Nav FLIR Pod AAS-38 Tgt FLIR Pod ADM-141 TALD ALQ-167 ECM Pod ASQ-173 LDT/Cam Pod ATARS Data Link Pod AWW-9B Data Link Pod AWW-13 Adv.0 (2 = 4.4 (2 = 4. or LAU-127s (w/AIM-9s/-120s) LAU-115C/A LAU-115A/A with jettison adapter for AIM-7 Launcher Adapter or two LAU-127s (W/AIM-9s/-120s) LAU-116 LAU-116/A for AIM-7 Sta 4/6 AIM Ejector LAU-116A/A for AIM-7 or AIM-120 LAU-117 LAU-117(V)-2/A wing pylon adapter for one AGM-65 Launcher AGM-65 Maverick LAU-118 LAU-118(V)-1/A wing pylon adapter for AGM-88 Launcher one AGM-88 HARM LAU-127A/A Pairs used with LAU-115 for AIM Launcher AIM-9.0 (each) (for wingtip.0 165 Station 6: 10. Walleye interface only Phase II AWW-13 for Walleyes & SLAM. see AIM-9) 277 tailhook: 200 200 pylon: 15.1 Phase II AWW-9B for Walleyes & SLAM.8) Figure 11-2.0 100 pylon: 3. ADM-141B: chaff dispensing ALQ-167(V)-10/14/15/21/25/50/52/71 ALQ-167(V)-11/20/70 (70 & 71 are TCPs) ALQ-167(V)-22 ALQ-167(V)-30/31/32/40 (30 is CV trainer) ALQ-167(V)-33 ALQ-167(V)-61 AN/ASQ-173 Laser Detector (formerly spot) Tracker/Strike Camera pod WEIGHT PER STORE LB CARRIAGE/DRAG 214 station 6: 9. bobtail (no fins) configuration only AN/ASQ T-16: Acft Inst Subsys. and MLMs BRU-32/A Non-ZRF SUU-62/63 ejector rack BRU-32A/A ZRF SUU-62/63 ejector rack BRU-33/A VER Non-ZRF Vertical Ejector Rack BRU-33A/A CVER ZRF Canted Vertical Ejector Rack BRU-41/A IMER ZRF Improved Multiple Ejector Rack BRU-42/A ITER ZRF Improved Triple Ejector Rack LAU-7 LAU-7/A through 163782 (Lot XI) Launch Rail for LAU-7B/A from 163985 (Lot XII) AIM-9 or TACTS Pod * See AIM-9 for more drag information LAU-115/A Wing pylon adapter for two LAU-7s Launcher Adapter (w/AIM-9s) LAU-115A/A Wing pylon adapter for two LAU-7s Launcher Adapter (w/AIM-9s).8 TOW BANNER TDU-32 TDU-32/B Tow Banner (w/ cable) PYLONS. or TACTS pod carriage LAU-115 and LAU-7 or LAU-127: 5.9 195 empty 545 full 32 122/18813 124/19013 123/18913 127/19313 127/19313 128/17814 31 wing: 12.9 707 pylon: 2. flares. 12 AN/ASQ T-31(V): AISI(K)10 645 pylon: 2.0 353 370 372 400 382 310/2799 322/2869 326 2389/274 272 306 station 4: 8.0 ATARS production centerline data link pod 552 8.0 pylon: 12. LAUNCHERS A/A37B-6E non-ZRF Multiple Ejector Rack MER-7 for practice bombs.0 ITER: 7. Data Link Pod CNU-188 Baggage Pod TACTS Pod (Tactical Aircrew Combat Training System) VERSION AN/AAR-50 Thermal Imaging Navigation Set (TINS) AN/AAS-38 FLIR AN/AAS-38A w/Lsr Tgt Desig/Rngfd (LTD/R) AN/AAS-38B w/Laser Spot Tracker (LST) ADM-141A. both Walleye and MIL-STD-1760 interfaces CNU-188/A: Converted AERO 1D fuel tank. AIM-120.0 pylon: 9. 11 AN/ASQ T-17: P4A11 AN/ASQ T-20: P4AX AN/ASQ T-25: P4AM12 AN/ASQ T-27: P4B12 AN/ASQ T-27(V)-1: P4BX12 AN/ASQ T-29: P4AW11. active/passive RF aug.0 95 (2 = 191) LAU-115: 2. Internal10.0 pylon: 12.0 59 pylon: 3.0 pylon: 15. fin. tail fuze. Includes weight of AS-4319 antenna. Boldface weight is for carrier qualified training and Tactical Contingency Pods (TCP) Mounted in gun bay (no drag).5 0 12 0 0 STORE VERSION SUU-62 Centerline pylon (w/BRU-32) SUU-63 Wing pylon (w/BRU-32) Empty Station Blank-Off Panel 1 2 3 4 5 6 7 8 9 10 11 12 13 14 Missiles fueled with JP10. 273 310 7. and 4-lb. Weights reflect Mk 80 series warheads. Carrier qualified. tail fuze. Summary of Store Drag Index Numbers (Sheet 5) 11-10B Change 2 . . warhead. Weights reflect Mk 80 series warheads including a MXU-735 nose plug and a 4-lb. Empty pods with tail fairings.Section XI Part 1 A1-F18AC-NFM-200 SUMMARY OF STORE DRAG INDEX NUMBERS (Continued) WEIGHT PER STORE LB CARRIAGE/DRAG SUU-62/A through 163782 (Lot XI) SUU-62/A from 163985 (Lot XII) 130 139 3.0 SUU-63/A F/A-18A/Bs SUU-63A/A F/A-18C/Ds to 163782 (Lot XI) SUU-63A/A from 163985 (Lot XII) No SUU-62 or -63 pylon mounted Used when no stores are carried on stations 4/6. F/A-18C/D Weights include nose plug (blunt unless specified). white missiles weigh 52 pounds less. USAF pods with MIL-STD-1760 data bus interface. Empty pods without fairings. Weights without and with three external ballast weights (weights required for wingtip carriage). Figure 11-2. those fueled with JP5 weigh 20 pounds less. Gray missiles. Weights without and with only fore and aft external ballast weights (weights required for wingtip carriage). 0 0.0 0.8 3.0 0.0 2.0 0.0 3.0 0.0 0.0 0.0 0.0 0.0 0.0 0.3 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 2.0 0.1 2.0 3.6 0.6 0.0 1.0 0.0 0.0 6.0 0.0 0.0 0.6 0.0 0.0 0.0 0.0 0.0 3.0 3.0 0.0 0.0 0.0 0.0 0.0 0.4 1.1 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.2 0.0 0.0 0.0 0.3 3.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.9 6.0 0.0 0.1 3.0 0.0 0.0 0.6 0.0 0.0 0.0 0.0 0.0 0.0 0.2 0.5 4.0 0.0 0.9 4.0 0.0 0.0 0.0 10.0 0.2 0.0 0.0 0.0 0.0 0.0 0.1 2.0 0.0 0.0 0.0 0.2 4. 330 gal fuel tank AIM-7 LAU-115C AIM-120 on LAU-115C & -127 AGM-65 Maverick on LAU-117 AGM-84D Harpoon AGM-84E SLAM ER AGM-88 HARM on LAU-118 AGM-154 JSOW AN/AWW-13 Data Link Pod CBU-78/-99/-100 & Mk-20 CBU CNU-188 Baggage Pod GBU-12 (Mk-82) LGB GBU-16 (Mk-83 LGB) GBU-31(v)2 (Mk-84 JDAM) GBU-31(v)4 (BLU-109 JDAM) Mk-77 Fire Bomb Mk-82.0 0.0 0.0 0.0 2.0 0.FPU-8.0 0.0 0.0 0.0 0.0 0.0 A1-F18AC-NFM-200 Change 7 Figure 11-3.0 0. BDU-45 or BLU-111 Mk-83 or BLU-110 Mk-84 PYLON PDU-5 BRU-33/A VER or BRU-33A/A CVER CBU-78/99/100 & Mk-20 on CVER Mk-77 Fire Bombs on CVER Mk-82.0 0.1 5.0 0.1 6.0 0.0 0.0 0.0 4.0 0.0 0.0 0.0 5.9 7.0 0.0 0.0 0.0 0.0 0.0 0.0 0.6 2.0 0.0 0.0 0.0 0.2 0.0 0.0 0.0 0.0 0.0 0.4 9.5 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.2 4.0 0.0 0.0 4.0 0.4 3.0 0.0 0.0 0.0 3.0 0.0 0.0 0.0 0.7 5.0 0.0 0.0 0.0 3.0 0.0 0.0 0.0 0.4 0.0 0.8 4.0 0.0 0.0 0.0 0.0 0.0 0.0 0.8 9.0 0.0 0.0 2. BDU-45 or BLU-111 on CVER OUTBOARD PYLONS AIM-7 LAU-115C/A AIM-9 on LAU-115C & -127 AIM-120 on LAU-115C & -127 AGM-65 Maverick on LAU-117 AGM-84D Harpoon AGM-84 SLAM AGM-84 SLAM ER AGM-88 HARM AGM-154 JSOW AN/ALQ-167 ECM POD AN/AWW-13 Data Link POD CBU-78/-99/-100 & Mk-20 CBU CNU-188 Baggage Pod FPU-8.0 0.1 3.0 2.0 0.0 0.0 0.5 0.0 0.1 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.4 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 2.0 3.0 0.0 0.0 0.0 0.0 0.1 0.0 0.0 0.0 0.0 0.6 1.0 0.0 8.0 4.0 0. BDU-45 or BLU-111 0.5 4.2 0.0 0.0 0.0 6.0 0.0 0.0 0.0 0.0 3.0 0.0 0.0 0.0 0.0 0.0 0.0 0.5 0.0 0.0 2.0 0.0 0.4 3.0 0.0 0.0 0.0 0.0 0.0 0.1 2.0 0.1 5.0 0.0 0.0 0.0 0.0 0.0 0.0 5.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.5 0.0 0.0 0.0 0.5 0.9 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.1 0.9 3.0 0.4 3.0 0.0 0.0 0.0 0.9 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.6 0.0 0.0 0.0 0.0 0.0 5.0 3.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.4 0.7 0.0 0.0 0.0 0.4 5. 330 gal fuel tank GBU-10 (Mk-84) LGB GBU-12 (Mk-82) LGB GBU-16 (Mk-83) LGB GBU-24 (BLU-109) LLLGB GBU-31(v)2 (Mk-84 JDAM) GBU-31(v)4 (BLU-109 JDAM) Mk-77 fire bomb Mk-82.0 2.0 0.0 0.0 0.2 4.0 0.0 0.0 0.0 4.0 0.0 0.0 0.8 0.0 0.0 0.0 0.0 0.1 0.0 0.0 0.0 4.0 0.0 0.0 0.0 0.0 0.0 0.0 0.9 4.7 1.0 0.0 0.0 0.0 0.0 0.5 0.0 0. Interference Code Numbers (Sheet 1 of 6) INBOARD PYLONS INTERFERENCE CODE NUMBERS Section XI Part 1 11-10C .0 0.0 0.0 0.5 8.0 0.0 9.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.4 3.0 0.8 9.0 0.0 0.0 3.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 3.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 2.0 0.6 0.5 0.0 0.0 0.0 0.7 4.2 0.0 0.0 0.6 10.0 0.0 0.1 6.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.1 0.0 0.0 2.0 0.0 0.0 0.0 0.5 0.0 0.0 0.0 0.0 1.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 2.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.1 0.0 0. 2 0.9 1.0 0.3 3.0 0.0 0.0 0.0 0.7 0.0 0.0 0.0 0.7 0.0 0.0 0.0 0.0 0.0 5.9 7.0 0.6 5.0 0.3 0.0 0.5 0.0 0.9 5.0 0. BDU-45 or BLU-111 on CVER Mk-83 or BLU-110 on CVER PDU-5 on CVER LAU-10 5″ pods on VER LAU-61 2.0 0.2 2.3 6.0 0.0 0.0 0.4 13.3 5.0 0.0 INBOARD PYLONS 0.0 0.4 0.0 0.0 0.7 4.0 0.8 3.0 0.0 0.3 3.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0. BDU-45 or BLU-111 Mk-83 or BLU-110 Mk-84 PYLON PDU-5 BRU-33/A VER or BRU-33A/A CVER CBU-78/99/100 & Mk-20 CVER Mk-77 Fire Bombs on CVER Mk-82.0 0.0 0.0 0.0 2.8 0.0 0.0 0.9 8.0 0.0 0.0 0.0 0.8 2.0 0.0 0.0 0.0 11.7 5.0 3.7 1.3 5.3 5.0 0.9 10.0 0.0 0.2 2.0 0.2 7.1 1.0 0.0 0.0 0.3 3.2 5.0 0.2 2.0 0.8 7.0 3.1 3.0 0.0 0.0 0.7 2.0 0.0 0.0 0.0 0.0 0.0 0.0 4.0 0.0 0.7 4.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.2 0.3 5.7 4.0 0.0 0.0 0.0 5.7 0.6 5.7 2.8 6.0 0.0 0.1 4.4 0.8 11.0 0.0 0.7 3.8 7.0 0.0 0.0 0.0 0.2 0.0 0.0 5.0 4.0 0.0 0.0 0.1 13.9 1.0 0. 330 gal fuel tank Change 7 OUTBOARD PYLONS Mk-83 or BLU-110 Mk-84 PDU-5 BRU-33/A VER or BRU-33A/A CVER CBU-78/99/100 & Mk-20 on CVER LAU-10 5″ pods on CVER LAU-61 2.0 0.0 0.0 0.0 A1-F18AC-NFM-200 Figure 11-3.0 0.5 11.0 0.0 0.0 0.0 0.2 2.0 4.0 0.0 0.0 5.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.2 5.6 4.6 6.0 0.0 0.6 3.3 7.2 0.1 12.0 0.2 2.0 0.4 12.0 0.0 0.7 5.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.1 5.0 0.0 0.0 5.0 0.0 0.2 0.0 0.0 0.8 5.4 1.0 0.0 0.0 0.7 2.0 0.0 0.1 6. BDU-45 or BLU-111 on CVER 0.0 0.0 0.6 5.0 0.0 0.4 6.0 0.0 0.0 0.0 0.0 0.0 0.2 3.8 1.0 0.0 0.0 0.0 0.0 0.0 0.0 0.4 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.6 4.0 0.2 2.0 0.0 0.75″ pods on CVER Mk-82.3 5.0 0.0 0.0 0.1 5.0 0.0 0.0 0.1 5.0 0.3 4.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 4.0 0.0 0.9 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.2 3.0 10.0 0.0 6.0 0.0 0.0 0.0 0.0 0.0 0.0 0.2 2.0 0.0 0.0 0.0 0.5 9.3 4.0 0.2 6.0 0.0 0.0 5.0 0.0 0.9 0.0 0.0 0.1 2.0 0.0 0.0 0.5 0.0 0.0 0.5 5.0 0.2 2.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 12.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.1 0.Section XI Part 1 11-10D INTERFERENCE CODE NUMBERS (Continued) AIM-7 LAU-115C AIM-120 on LAU-115C & -127 AGM-65 Maverick on LAU-117 AGM-84D Harpoon AGM-84E SLAM ER AGM-88 HARM on LAU-118 AGM-154 JSOW AN/AWW-13 Data Link Pod CBU-78/-99/-100 & Mk-20 CBU CNU-188 Baggage Pod GBU-12 (Mk-82) LGB GBU-16 (Mk-83 LGB) GBU-31(v)2 (Mk-84 JDAM) GBU-31(v)4 (BLU-109 JDAM) Mk-77 Fire Bomb Mk-82.0 0.0 3.0 0. Interference Code Numbers (Sheet 2) FPU-8.0 5.0 0.75″ pods on VER Mk-82.0 0.8 0.0 0.0 0.0 0.0 0.0 0.0 0.3 6.0 0.0 0.0 0.0 0.0 0.0 0.0 0.4 0.0 0.6 5.0 0.0 0.0 0.0 4.0 0.0 0.0 0.0 0.9 7.6 6.0 0.0 0.0 0.0 6.0 0.0 0.9 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.5 1.2 2.6 4.0 0.0 0.0 0.0 0.0 0.0 0.0 0.1 4.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.6 4. BDU-45 or BLU-111 on VER Mk-83 or BLU-110 on VER BRU-42 ITER ADM-141 TADL on ITER BRU-41 IMER BDU-33 or Mk-76 on IMER BDU-48 or Mk-106 IMER BDU-57.0 0.0 0.0 0.0 0.1 6.7 0.0 0.0 0.0 0.0 3.0 0.0 0.0 0.0 0.0 0.5 8.0 0.0 0.7 3.0 0.0 0.6 4.5 5.0 0.75″ pods on VER LAU-68 2.0 0.0 0.1 3.2 5.5 0.0 0.8 6.5 0.0 0.4 4.2 5.0 0.0 0.0 0.7 1.0 0. -59 & -60 LGTR on IMER .0 0.0 0.0 0.7 4.0 0.0 0.8 0.0 0.0 0.0 0.8 0.7 4.0 0.0 0.0 0.0 4.0 0.0 0.0 0.7 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 4.0 0.5 5.0 0.4 10.0 0.2 0.57″ pods on CVER LAU-68 2.7 0.9 0.7 1.0 0.0 0.6 6.0 0.0 0.0 7.0 0.0 0.0 0.0 0. 5 3.0 0.0 0.0 0.0 2.0 0.0 0.8 4.9 5.0 0.0 0.0 0.8 11.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.1 5.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 9.2 0.0 3.0 0.0 0.0 0.0 0.0 0.2 0.4 4.0 3.0 0.0 0. BDU-45 or BLU-111 on CVER OUTBOARD PYLONS LUU-2 on IMER Mk-58 Mk-52 1.0 0.0 0.0 0.0 0.0 3.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.000 lb bottom mine Mk-55 2.0 0.2 0.0 8.0 0.0 4.0 0.0 0.0 0.0 0.0 0.0 0.3 7.0 0.0 0.0 0.0 2.0 0.4 4.6 4.0 0. 330 gal fuel tank AIM-7 LAU-115C AIM-120 on LAU-115C & -127 AGM-65 Maverick on LAU-117 AGM-84D Harpoon AGM-84E SLAM ER AGM-88 HARM on LAU-118 AGM-154 JSOW AN/AWW-13 Data Link Pod CBU-78/-99/-100 & Mk-20 CBU CNU-188 Baggage Pod GBU-12 (Mk-82) LGB GBU-16 (Mk-83 LGB) GBU-31(v)2 (Mk-84 JDAM) GBU-31(v)4 (BLU-109 JDAM) Mk-77 Fire Bomb Mk-82.0 0.0 0.1 5. Interference Code Numbers (Sheet 3) INBOARD PYLONS INTERFERENCE CODE NUMBERS (Continued) FUSELAGE STATIONS AN/AAR-50 NAVFLIR (sta 6) AN/AAS-38 tgt FLIR (sta 4) AN/ASQ-173 LDT/Cam (sta 6) Section XI Part 1 11-10E .0 0.0 0.0 4.0 6.0 0.7 0.0 0.6 4.0 0.000 lb bottom mine Mk-62 QS Mk-15 or BSU-86 fin on CVER Mk-62 QS Mk-16 fin on CVER Mk-63 QS Mk-12 fin on CVER Mk-62 QS any fin on VER BDU-48 practice mine on IMER 0.0 0.0 4.0 0.0 0.9 0.0 0.4 4.4 0.0 0.0 0.3 0.0 0.0 0.0 0.2 7.0 0.0 0.0 0.0 0.0 0.3 6.0 0.2 0.0 0.0 0.6 3.0 0.0 0.0 0.0 0. BDU-45 or BLU-111 Mk-83 or BLU-110 Mk-84 PYLON PDU-5 BRU-33/A VER or BRU-33A/A CVER CBU-78/99/100 & Mk-20 CVER Mk-77 Fire Bombs on CVER Mk-82.0 0.0 5.1 5.5 5.0 0.8 0.5 0.0 0.0 3.0 0.0 0.4 0.0 0.0 0.0 0.0 0.7 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.1 0.0 0.0 0.0 0.2 6.0 0.0 0.0 0.0 0.5 0.0 0.2 0.0 0.5 0.000 lb moored mine Mk-62 QS Mk-15 or BSU-86 fin Mk-62 QS Mk-16 fin Mk-63 QS MAU-91 fin Mk-63 QS Mk-12 fin Mk-65 QS 2.0 0.0 0.0 0.7 7.7 0.1 5.0 0.0 3.0 0.0 0.0 0.0 3.0 0.8 3.0 0.0 0.0 0.2 11.5 3.0 0.4 8.0 0.0 0.0 0.0 0.0 0.9 5.0 0.3 A1-F18AC-NFM-200 Change 7 Figure 11-3.0 1.0 0.0 0.5 12.6 5.0 0.3 2.0 0.0 0.4 3.3 0.0 0.4 12.6 2.5 7.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.4 1.0 4.0 1.0 0.0 0.0 0.0 0.1 5.2 6.8 4.0 0.0 0.0 0.FPU-8.0 0.7 0.0 0.0 0.0 0.0 0.0 0.0 0.0 2.0 0.9 5.0 0.8 2.7 3.0 0.0 0.0 0.0 0.000 lb bottom mine Mk-55 2.0 0.0 0.5 11.0 0.0 0.0 0.0 0.0 0.8 2.0 0.0 0.0 0.1 9.7 4.0 0.0 0.0 0.0 0.0 0.0 0.5 6.0 0.0 0.0 0.3 1.0 0.0 0.2 6.2 5.0 0.0 0.2 0.0 0.6 11.1 3.2 2.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 5.0 0.0 0.9 3.0 0.0 1.0 0.0 0.3 5.0 0.0 0.0 0.0 0.3 2.0 0.0 2.2 0.0 0.0 0.0 0.0 0.0 0.0 6.0 0.0 0.0 0.0 0.0 0.0 0.2 5.0 0.0 0.0 2.5 3.0 0.0 0.0 0.0 4.0 0.0 0.0 0.0 0.0 0.8 0.0 0.1 5.0 0.0 0.3 5.0 0.0 0.0 0.0 0.0 0.0 0.8 0.3 0.0 0.0 5.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.9 3.0 0.0 0.1 3.1 0.0 0.0 0.8 0.0 0.0 7.0 5.0 0.2 0.0 0.8 2.0 1.0 4.0 0.0 0.0 0.4 11.0 0.0 0.0 0.0 0.0 0.0 0.4 4.0 0.0 0.0 0.0 0.0 0.8 4.0 0.0 0.0 0.0 0.2 0.0 0.0 0.0 0. 5 5.0 0.0 3.0 0.0 0.7 4.0 5.000lb bottom mine BRU-33/A VER or BRU-33A/A CVER Mk-62 QS Mk-15/BSU-86 fin on CVER Mk-62 QS Mk-16 fin on CVER Mk-62 QS any fin on VER BRU-41 IMER BDU-48 as practice mine on IMER 0.5 4. Interference Code Numbers (Sheet 4) INBOARD PYLONS Change 7 OUTBOARD PYLONS AIM-7 LAU-115C/A AIM-9 on LAU-115C & -127 AIM-120 on LAU-115C & -127 AGM-65 Maverick on LAU-117 AGM-84D Harpoon AGM-84 SLAM AGM-84 SLAM ER AGM-88 HARM AGM-154 JSOW AN/ALQ-167 ECM POD AN/AWW-13 Data Link POD CBU-78/-99/-100 & Mk-20 CBU CNU-188 Baggage Pod FPU-8.0 1.0 0.0 0.0 0.0 0.5 4.0 0.0 0.0 0.0 0.0 0.0 3.0 0.0 0.0 0.0 0.0 0.0 0.8 5.0 0.0 0.0 0.3 0.9 2.7 0.0 0.0 0. BDU-45 or BLU-111 Mk-83 or BLU-110 on CVER INTERFERENCE CODE NUMBERS (Continued) .0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.4 5.0 0.0 3.0 5.0 0.0 0.0 0.0 0.0 4.0 0.0 0.0 0.0 0.8 5.0 0.0 0.8 0.0 0.0 0.0 0.0 0.0 0.0 4.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 5.0 0.0 0.0 0.0 0.0 0.0 0.6 0.8 0.000 lb bottom mine Mk-56 2.0 5.1 0.0 0.0 0.0 0.0 0.0 0.2 5.0 0.0 5.4 0.0 3.0 0.0 1.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 3.0 0.0 0.0 0.0 0.0 0.1 0.8 0.3 2.0 0.0 2.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.4 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 4.7 0.0 0.0 0.0 3.0 0.0 0.0 0.0 0.0 1.0 0.0 0.7 2.0 0.0 0.0 0.0 0.0 0.0 0.0 3.9 0.0 0.8 4.0 0.0 0.0 0.0 0.0 0.0 0.8 0.0 0.6 5.0 0.0 0.0 0.2 0.0 0.0 0.8 4.0 0.0 0.0 0.1 0.0 0.2 0.0 0.0 0.3 0.0 0.0 0.6 6.0 0.0 0.0 0.0 2.0 3.4 0.0 0.0 0.0 0.0 0.0 0.0 0.6 0.0 0.0 0.0 0.0 0.7 2.0 0.0 0.8 0.2 0.5 0.0 0.0 0.7 2.0 0.0 0.0 0.0 5.3 0.0 0.0 0.0 0.0 0.0 0.5 0.9 6.0 0.0 0.0 0.0 3.0 3.5 4.2 0.0 0.0 0.0 0.0 0.0 2.0 0.0 0.0 0.0 5.0 0.0 0.0 0.0 3.0 3.3 2.0 2.9 0.0 0.0 4.0 0.0 0.0 0.0 4.0 0.0 0.0 0.0 0.7 4.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.2 0.0 0.0 0.0 0.1 0.0 0.0 0.0 0.0 0.0 4.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.5 3.0 0.0 0.0 0.0 0.0 0.0 6.2 0.0 0.0 3.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 5.4 2.0 0.1 5.0 0.0 0.0 0.0 0.0 0.0 0.5 4.0 0.0 0.8 4.0 0.9 0.6 0.3 5.0 0.0 0.0 0.0 0.0 1.0 0.0 0.0 0.0 0.2 0.0 0.0 4.0 0.0 0.0 5.0 0.0 0.0 0.0 0.0 4.0 0.2 3.3 4.0 0.0 0.0 0.0 0.0 0.Section XI Part 1 11-10F LAU-10 5″ pods on VER Mk-82. -59 & -60 LGTR on IMER Mk-52 1.6 0.0 4.0 0.8 0.0 0.8 0.7 0.0 0.0 0.0 0.5 0.2 0.0 0.0 0.0 0.0 0.4 0.2 3.9 0.0 0.0 0.0 0.0 0.0 0.0 0.0 1.0 0.1 4.0 0.0 0.0 0.0 0.0 0.4 0.0 0.0 0.0 0.4 4.0 0.0 0.0 3.8 4.0 3.0 0.0 0.7 2.0 0.8 0.4 0.0 0.9 6.0 0.0 0.0 3.0 0.0 0.0 0.0 0.0 0.0 0.0 0.6 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 3.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.4 2.0 0.0 0.1 5.0 0.0 0.0 0.0 0.2 0.0 0.0 0.0 0.2 3.0 0.0 1.0 0.0 0.0 0.0 0.0 0.0 3.0 0.0 0.0 5.0 0.4 4.1 2.0 0.0 0.6 5.0 0.9 0.0 0.0 0.0 0.0 0.0 0.5 3.0 0.0 0.0 0.0 0.0 1.0 0. BDU-45 or BLU-111 on VER Mk-83 or BLU-110 on VER BRU-42 ITER ADM-141 TADL on ITER BRU-41 IMER BDU-33 or Mk-76 on IMER BDU-46 or Mk-106 on IMER BDU-57.0 0.0 0.0 0.0 0.0 0.7 4. 330 gal fuel tank GBU-10 (Mk-84) LGB GBU-12 (Mk-82) LGB GBU-16 (Mk-83) LGB GBU-24 (BLU-109) LLLGB GBU-31(v)2 (Mk-84 JDAM) GBU-31(v)4 (BLU-109 JDAM) Mk-77 fire bomb Mk-82.0 0.0 0.0 0.0 0.0 A1-F18AC-NFM-200 Figure 11-3.0 0.0 0.000 lb moored mine Mk-62 QS Mk-15 or BSU-86 fins Mk-62 QS Mk-16 fin Mk-63 QS MAU-91 fin Mk-63 QS Mk-12 fin Mk-65 QS 2.0 0.0 0.0 0.2 0.7 4.0 0.0 1.0 0.1 5.0 0.0 0.0 0.000 lb bottom mine Mk-55 2.0 0.1 5.0 0.0 0.0 0. 0 4.0 0.5 5.0 0.0 0.3 1.5 2.0 0.0 0.0 0.0 0.0 0.000 lb moored mine Mk-62 QS Mk-15 or BSU-86 fins Mk-62 QS Mk-16 fin Mk-63 QS MAU-91 fin Mk-63 QS Mk-12 fin Mk-65 QS 2.0 0.0 0.0 0.0 0.8 5.0 0.1 5.5 7.4 1.0 0.0 3.0 0.0 0.0 0.6 0.2 7.0 0.0 0.0 0.0 0.3 5.0 0.0 0.0 0.4 0.6 5.0 0.0 0.0 2.4 0.0 0.0 0.0 0.0 0.5 5.0 0.7 0.0 5.0 0.3 5.0 0.0 5.9 7.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.7 6.0 0.1 5.2 7.0 0.0 0.0 2.0 5.0 0.0 0.0 0.5 8.6 3.0 0.0 0.2 3.5 0.2 4.0 0.0 0.6 4.0 0.0 0.0 0.0 0.0 0.0 0.7 3.000 lb bottom mine Mk-55 2.0 5.0 0.0 0.0 0.0 0.0 0.5 4.0 0.0 0.0 0.5 0.6 0.2 4.0 0.1 0.0 0.0 5.6 0.0 0.0 0.0 0.0 0.0 0.9 5.0 0.0 0.0 0.0 5.0 0.4 4.0 0.0 0.0 0.9 5.75″ pods on CVER Mk-82.0 0. BDU-45 or BLU-111 on VER Mk-83 or BLU-110 on VER BRU-42 ITER ADM-141 TADL on ITER BRU-41 IMER BDU-33 or Mk-76 on IMER BDU-46 or Mk-106 on IMER BDU-57.0 0.0 0.0 0.0 0.3 4.5 3.5 0.6 0.0 0.0 0.2 3.0 0.0 0.0 0.0 0.0 0.0 0.0 0.6 0.0 0.0 0.0 0.57″ pods on CVER LAU-68 2.0 0.000 lb bottom mine BRU-33/A VER or BRU-33A/A CVER Mk-62 QS Mk-15/BSU-86 fin on CVER Mk-62 QS Mk-16 fin on CVER Mk-62 QS any fin on VER BRU-41 IMER BDU-48 as practice mine on IMER 0.0 0.0 0.0 0.0 0.6 7.0 0.8 5.7 4.0 0.0 0.3 5.0 0.6 6.0 0.0 0.0 0.1 7.0 0.0 0.0 0.0 0.9 0.0 0.0 0.8 0.0 0.0 5.0 0. Interference Code Numbers (Sheet 5) Change 7 OUTBOARD PYLONS Mk-83 or BLU-110 on CVER INTERFERENCE CODE NUMBERS (Continued) .0 0.0 0.0 0.8 5.8 0.0 0.9 6.0 0.0 3.0 0.0 0.0 0.0 0.0 0.0 0.0 0. BDU-45 or BLU-111 on VER Mk-83 or BLU-110 on VER BRU-42 ITER ADM-141 TADL on ITER BRU-41 IMER BDU-33 or Mk-76 on IMER BDU-48 or Mk-106 IMER BDU-57.0 0.0 0.5 0.2 5.9 6.0 7.7 5.0 0.0 0.6 3.9 5.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 2.9 0.0 0.2 2.0 0.0 0.0 0.0 0.0 0.0 0.2 0.0 4.9 5.0 0.0 0.0 2.0 5.0 0.0 0.0 0.0 0.0 0.0 0.0 0.2 4.0 0.4 1.0 0.0 0.2 2.75″ pods on VER Mk-82.0 0.3 5.0 0.7 4.0 0.0 0.0 0.2 5.3 5.0 0.0 0.9 3.4 1.0 0.0 0.0 0.0 2.0 0.9 5.7 5.0 0.0 0.0 0.6 5.LAU-10 5″ pods on VER Mk-82.2 2.8 0.2 2.0 0.0 0.4 3.0 0.0 6.0 4.8 5.0 0.0 0.7 5.0 0.0 4.6 4.0 0.0 5.0 0.0 0.0 0.3 5.0 0.0 0.1 0.0 0.0 0.0 0.6 4.4 1.0 0.0 0.0 0.0 0.0 0.0 0.0 5.0 0.0 5.9 5.0 6.9 6.6 6.0 0.0 0.0 5.0 5.7 3.0 0.0 0.0 0.0 0.0 0.0 0.2 3.0 0.0 0.0 0.5 2.0 0.75″ pods on VER LAU-68 2.0 0.0 0.0 0.0 0.0 0.0 0.0 0.5 6.3 4.0 0.0 0.0 0.5 8.0 0.0 0.0 0.0 0.0 0.5 2.1 3.0 0.5 5.0 0.0 0.7 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.9 5.0 0.0 0.0 0.0 0.0 0.6 6.0 0.0 0.2 2.4 6.0 0.0 0.0 0.2 3. -59 & -60 LGTR on IMER Mk-52 1.0 0.0 0.0 0.0 0.0 5.0 0.0 0.0 0.0 0.0 Section XI Part 1 Mk-83 or BLU-110 Mk-84 PDU-5 BRU-33/A VER or BRU-33A/A CVER CBU-78/99/100 & Mk-20 on CVER LAU-10 5″ pods on CVER LAU-61 2.1 3.0 0.2 3.000 lb bottom mine Mk-56 2.0 0.3 4.0 0.2 9.0 0.0 0.3 1.0 3.0 0.0 0.3 5.0 0.0 0.0 7. -59 & -60 LGTR on IMER A1-F18AC-NFM-200 11-10G/(11-10H blank) Figure 11-3.0 0.0 0.5 4.4 4.0 0.0 5.6 0.0 0.0 0.0 0.6 6.0 0.0 0.0 0.8 0.0 0.9 3.0 0.0 0.0 0.0 0.2 4.0 0.0 0.0 0.7 4.7 4.0 0.5 7.0 0.0 0.0 0.0 0.0 0.3 0.0 0.0 0.0 3.0 0.0 0.0 0.0 5.0 0.0 0.8 3.0 0.0 0.0 4.5 5.0 INBOARD PYLONS 0.0 0.0 0.0 3.0 2.0 0.0 0.0 0.6 4.0 0.0 0.0 0.0 0.2 2.0 0.0 0.0 0.0 0.0 0.0 0.1 5.1 5.0 0.8 4.6 5.0 0.0 0.9 3.0 0.3 4.0 0. BDU-45 or BLU-111 on CVER Mk-83 or BLU-110 on CVER PDU-5 on CVER LAU-10 5″ pods on VER LAU-61 2.0 0.7 3.0 0.0 0.0 0.7 3.2 9.0 0.0 0.0 0.0 0.0 0.0 0.0 0.5 5.0 0.0 0.5 5.0 0.0 5.0 5.0 0.9 4.9 0.0 0.0 0.0 3.0 0.9 6.0 0.0 0.0 0.0 0.0 0.0 0.0 0.8 6.4 5.0 0.0 0.5 0.0 0.4 0.0 0.0 0.4 3.0 0. . 0 0.0 0.9 0.0 1.7 0.0 0.8 0.0 0.7 0.7 2.0 4.0 0.0 A1-F18AC-NFM-200 Figure 11-3.0 4.0 0.0 0.0 0.0 0.0 0.9 6.1 5.0 0.0 0.0 0.0 0.0 0.0 3.0 2.0 0.0 0.0 0.9 0.0 0.0 0.9 5.0 0.0 0.000 lb bottom mine Mk-62 QS Mk-15 or BSU-86 fin on CVER Mk-62 QS Mk-16 fin on CVER Mk-63 QS Mk-12 fin on CVER Mk-62 QS any fin on VER BDU-48 practice mine on IMER 0.0 0.3 4.2 4.0 0.6 5.0 0.0 0.2 0.0 0.0 5.0 0.0 0.3 2.0 0.0 0.0 1.0 0.0 0.7 0.7 3.3 5.5 0.0 0.0 7.5 7.9 0.0 0.0 0.0 0.0 0.000 lb moored mine Mk-62 QS Mk-15 or BSU-86 fins Mk-62 QS Mk-16 fin Mk-63 QS MAU-91 fin Mk-63 QS Mk-12 fin Mk-65 QS 2.0 0.0 0.0 0.0 0.0 0.0 4.0 0.0 0.5 4.0 0.4 5.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.1 4.0 0.0 2.3 4.0 0.0 0.0 0.1 5.0 0.0 0.0 0.5 5.7 1.0 0.1 3.0 0.0 3.0 0.0 0.2 0.0 0.1 5.0 0.0 0.0 0.000 lb bottom mine Mk-55 2.0 0.0 0.0 0.0 0.0 0.1 5.5 4.0 0.5 0.0 0.0 0.0 0.4 4.8 4.0 0.5 5.0 0.0 4.3 7.0 0.1 6.0 1.0 0.0 4.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.9 7.0 0.0 0.0 0.0 0.0 0.0 0.0 0.000 lb bottom mine Mk-55 2.5 2.7 2.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.7 3.4 3.0 0.1 7.5 1.5 6.0 0.0 0.0 0.0 0.5 0.9 0.0 0.0 0.0 1.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.2 0.000 lb moored mine Mk-62 QS Mk-15 or BSU-86 fin Mk-62 QS Mk-16 fin Mk-63 QS MAU-91 fin Mk-63 QS Mk-12 fin Mk-65 QS 2.0 0.8 4.3 5.0 0.0 0.0 0.0 0.6 4.6 5.0 0.0 0.0 8.4 5.0 0.3 4.0 0.0 0.0 2.0 0.7 3.5 6.7 4.0 0.8 6.0 0.0 0.0 0.0 0.0 0.0 0.0 0.5 2.1 5.1 3.0 0.0 0.9 4.0 0.0 0.0 0.000 lb bottom mine BRU-33/A VER or BRU-33A/A CVER Mk-62 QS Mk-15/BSU-86 fin on CVER Mk-62 QS Mk-16 fin on CVER Mk-62 QS any fin on VER BRU-41 IMER BDU-48 as practice mine on IMER Change 7 Mk-83 or BLU-110 on CVER OUTBOARD PYLONS LUU-2 on IMER Mk-58 on IMER Mk-52 1.1 0.0 0.0 0.9 5.0 0.0 1.000 lb bottom mine Mk-56 2.0 0.0 0.0 0.0 0.0 3.7 5.4 0.0 0.0 0.0 0.2 6.5 5.0 0.6 2.0 0.1 4.8 0.0 0.0 0.0 0.0 0. BDU-45 or BLU-111 on VER Mk-83 or BLU-110 on VER BRU-42 ITER ADM-141 TADL on ITER BRU-41 IMER BDU-33 or Mk-76 on IMER BDU-46 or Mk-106 on IMER BDU-57.0 0.0 0.0 0.0 0.0 0.2 4.0 0.2 4.3 2.0 1.0 0.2 4.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 3.0 0.0 0.9 0.0 0.0 0.9 0.0 0.0 0.0 0.0 0.1 0.0 0.8 3.0 0.1 0.0 0.0 0.1 0.0 0.0 0.0 0.0 0.0 0.0 0.2 7.0 0.8 3.0 0.0 0.0 0.5 6.0 0.0 0.0 0.0 0.0 0.0 0.0 0.0 1.5 0.0 0.0 0.0 0.0 0.0 0.0 0.2 0.3 2.0 0.0 0.0 0.0 0.0 0.5 2.0 0.9 2.0 0.0 0.0 0.0 0.0 0.6 0.0 0.0 0.0 0.0 4.7 3.9 6.0 0.0 0.0 0. -59 & -60 LGTR on IMER Mk-52 1.8 5.9 5.0 5.5 5.0 0.0 0.LAU-10 5″ pods on VER Mk-82.4 0.000 lb bottom mine Mk-55 2.5 6.0 0.5 6.2 4.0 6.0 0.0 0.8 3.0 1.0 0.1 0.5 0.9 4.8 0.0 4.9 5.0 0.0 0.0 0. Interference Code Numbers (Sheet 6) INBOARD PYLONS INTERFERENCE CODE NUMBERS (Continued) FUSELAGE STATIONS AN/AAR-50 NAVFLIR (sta 6) AN/AAS-38 tgt FLIR (sta 4) AN/ASQ-173 LDT/Cam (sta 6) Section XI Part 1 11-11 .0 0.4 4.0 0.0 0.0 0.0 1.0 0.0 0.0 4.0 0.5 7.0 0.0 2.0 0.0 0.0 0.0 0.0 5.0 0.0 0.0 0.0 0.0 0.0 0.9 5.9 0.0 0.9 1.5 6.0 4.0 0.0 0.0 0.0 0.0 0.0 0.0 0.4 4.8 6.9 0.0 0.0 4.5 0.0 0.0 0.0 0.0 0.2 6.3 2.0 0.0 2.0 0.0 0.0 0.0 0.0 3.0 4.8 6.5 0. Section XI Part 1 A1-F18AC-NFM-200 Figure 11-4. . Interference Code Number To Interference Drag Index Number Conversion 11-12 . 000 13.2462 0.9827 0.455 -44.338 19.8909 0.5881 3.718 -16.471 26.000 9.9250 0.3345 0.249 -65.05840 0.924 1.8671 0.3028 1.9175 0.8359 0.511 -38.1387 0.905 23.1764 0.604 9.297 8.492 -40.1936 0.000 46.000 50.4173 0.500 -56.9606 3.000 1.8320 0.097 5.6968 1.812 -6.07792 0.000 28.000 27.286 -40.0368 1.037 30.000 56.000 31.018 1.29 17.08972 0.1845 0.2138 0.8671 0.000 62.9896 0.568 -32.852 -44.000 37.8962 0.3700 1.816 -69.500 -56.0454 1.1681 0.03 18.9470 0.9024 0. Standard Atmosphere Table 11-13 .000 48.8671 0.4198 3.041 6.222 2.0000 0.000 13.473 -42.8903 2.6360 0.5 FT/SECE661.5420 0.0773 1.1662 2.4428 2.500 -56.6645 1.08150 0.700 -69.4223 0.82 26.075 5.3848 2.397 6.1197 0.700 -69.6292 0.8671 0.7964 1.693 2.09444 0.681 -20.770 3.3881 0.8671 0.700 -69.10 10.9213 0.488 8.000 10.000 4.22 15.1040 0.500 -56.700 -69.0645 2.000 33.2403 1.500 -56.9428 0.4325 0.3552 0.000 -1.5892 0.1318 0.151 3.500 -56.11 11.5 KNOTS AIR TEMPERATURE DEG F DEG C 0.9507 0.63 10.1145 0.58 16.000 36.9677 2.500 SPEED OF SOUND a/a0 1.7148 0.8671 0.1091 0.662 -22.500 -56.09 22.154 -33.117 -58.000 64.057 7.2970 0.700 -69.2038 0.683 -62.113 1.700 -69.500 -56.382 -69.8671 0.2606 1.000 29.500 -56.0326 3.500 -56.700 -69.000 19.2189 2.000 22.1819 3.8671 0.000 43.889 -19.593 3.700 -69.9434 0.9644 0.8714 0.8671 0.735 41.5511 0.09877 0.076475 LB/SQ FTE0.08551 0.7860 0.6614 0.8793 0.436 -46.3876 0.074 5.624 -26.2710 0.1322 0.278 5.985 -51.132 -0.000 45.9287 0.79 19.3386 3.4678 1.0034 1.8671 0.9298 0.3107 0.1637 1.000 58.000 63.9209 1.111 2.4046 0.9855 1.2815 1.9138 0.8671 0.9721 0.1758 0.4025 0.1597 0.3741 0.5630 2.8671 0.39 20.587 -30.9966 0.1141 0.756 -12.793 -8.500 -56.0000 0.1522 0.700 -69.5150 0.86 27.3099 0.8671 0.538 5.700 -69.9714 0.419 -47.07767 0.1455 0.191 -8.6090 0.000 40.06429 0.0938 1.4791 0.09414 0.8671 0.774 -10.7546 2.700 -69.000 20.8671 0.4642 0.000 41.500 -56.09909 0.9686 0.000 65.8671 0.030 4.500 -56.8014 0.019 11.8948 0.09001 0.8671 0.87 16.5480 1.500 -56.000 47.625 -5.000 0 1.9100 0.2011 1.0155 2.8671 0.831 -4.500 -56.551 -55.92 28.022 -26.75 13.355 4.500 -56.000 60.5699 0.2353 0.5875 0.118 2.000 34.1256 0.3250 0.4912 LB/SQ IN.8671 0.3935 1.700 -69.2583 0.5206 1.000 24.2728 2.700 -69.811 5.000 32.9324 0.000 51.4481 0.700 -69.094 3.794 4.9397 0.2837 0.665 PRESSURE RATIO p/p0Eδ 1.9862 0.000 54.849 -2.05566 Figure 11-5.382 7.07078 0.Section XI Part 1 A1-F18AC-NFM-200 STANDARD ATMOSPHERE STANDARD SEA LEVEL AIR: TE59°F (15°C) PE 29.323 -56.000 53.038 9.1279 1.15 31.3605 0.000 18.8671 0.6754 66.6052 1.0000 0.8315 1.700 18.2586 0.000 35.0611 1.772 16.3281 2.000 52.700 -69.8106 0.07426 0.603 34.000 55.700 -69.323 -15.732 LB/SQ FTE0.500 -56.8637 0.569 4.2470 1.57 14.000 39.8871 0.1383 0.6892 2.58 19.0299 1. HG E 70.000 23.379 -52.7291 1.965 2.000 55.757 -12.588 -30.8671 0.22 21.567 2.1676 0.1087 0.18 12.2709 0. 1 IN.700 -69.699 -18.398 -50.500 -56.000 49.1851 0.956 3.885 8.5022 2.2346 0.8675 0.737 -14.500 -56.826 2.0000 1.921 IN.6500 0.000 15.1201 0.456 -23.3473 0.2593 3.000 42.4807 0.700 -69.302 44.500 -56.9579 0.530 -36.000 14.0068 1.1456 1.500 -56.9151 0.962 16.82 25.08176 0.361 -54.000 17.000 6.342 -56.0298 1.2205 1.169 37.9931 0.700 -69.132 62.2844 0.8881 0.434 51.6932 0.9543 0.566 59.8671 0.06746 0.9711 0.7385 0.868 48.8753 1.1527 0.90 23.700 -69.7620 0.981 15.643 -24.3398 0.1942 0.2236 0.98 23.331 2.8671 0.605 -28.8986 0.720 -37.1451 0.4406 0.7716 0.417 -48.1260 0.1036 0.206 12.02 29.08578 0.508 1.737 7.941 -1.700 -69.3246 1.000 61.5328 0.1148 2.106 7.9062 0.6113 0.000 26.700 -69.5029 3.000 21.700 -69.264 3.700 -69.725 9.4424 1.9614 0.6349 1.549 -34.446 2.94 14.7623 1.8617 0.7428 0.1602 0.000 38.2131 0.8671 0.8754 0.4593 0.5643 0.000 57.000 8.0148 1.60 11.8671 0.34 13.747 1.000 44.2031 0.700 -69.0745 1.500 -56.4176 1.500 -56.000 11.000 3.000 59.9650 0.500 -56.833 1.500 -56.0023769 SLUGS/CU FT.000 16.700 -69.8671 0.7156 0.2467 0.0598 1.000 12.5762 1.500 -56.000 7.3711 0.5203 0.700 -69.4938 1.8671 IN HG 32.6713 0.500 -56.9756 0.1107 1.1822 1.425 3. a0 E1116.3220 0.712 6.8216 2.500 -56.17 9. HG ALTITUDE FEET DENSITY RATIO ρ/ρ0E0— -2.64 12.84 24.8671 0.4994 0.000 5.06127 0.000 30.2981 0.8671 0.2243 0.1063 3.9792 0.000 2.700 -69.07403 WE0.8832 0.6254 2.4976 0.6877 0.000 25.9361 0. .Section XI Part 1 A1-F18AC-NFM-200 Figure 11-6. Temperature Conversion 11-14 . A1-F18AC-NFM-200 Section XI Part 1 Figure 11-7. Airspeed Conversion .Low Mach (Sheet 1 of 2) 11-15 . .Section XI Part 1 A1-F18AC-NFM-200 Figure 11-7.High Mach (Sheet 2 of 2) 11-16 . Airspeed Conversion . Indicated Airspeed (Sheet 1 of 2) 11-17 . Airspeed Position Error Correction .A1-F18AC-NFM-200 Section XI Part 1 Figure 11-8. Airspeed Position Error Correction .Section XI Part 1 A1-F18AC-NFM-200 Figure 11-8. .Mach Number (Sheet 2 of 2) 11-18 . Indicated Airspeed (Sheet 1 of 2) 11-19 . Altimeter Position Error Correction .A1-F18AC-NFM-200 Section XI Part 1 Figure 11-9. Section XI Part 1 A1-F18AC-NFM-200 Figure 11-9.Mach Number (Sheet 2 of 2) 11-20 . . Altimeter Position Error Correction . F404-GE-400 11-21 . Stall Speeds .A1-F18AC-NFM-200 Section XI Part 1 Figure 11-10. Angle of Attack Conversion 11-22 .Section XI Part 1 A1-F18AC-NFM-200 Figure 11-11. . ..... 0..... Density ratio must be determined before the takeoff data charts can be utilized.. Headwind component 33 Kt............ For headwind component add onehalf the gust velocity (incremental wind factor) to the steady state velocity... descend vertically to read the crosswind component........g....... reported wind 050/30 G40..... Density Ratio . e.. Takeoff Ground Roll Correction for CG ............. From this point.......... Intersect: Crosswind windspeed arc 40 Kt Headwind windspeed arc 35 Kt........ From the intersection of bearing and effective headwind speed........ reported wind 050/30 G40.... runway heading 030...... e. From this point.......... Sample Problem A..Section XI Part 2 A1-F18AC-NFM-200 PART 2 .. Move along the relative bearing to intercept the crosswind effective wind speed arc. Crosswind component 14 Kt......... For crosswind component add the full value of any reported gust velocity (incremental wind factor) to the steady state velocity.. Relative bearing 20° B...93 Change 6 11-23 ........ Reduce the reported wind direction to a relative bearing by determining the wind direction and runway heading.. D. Minimum Go Speed .. C...TAKEOFF F404-GE-400 TABLE OF CONTENTS Charts Wind Components............. Sample Problem Reported wind 050/30 G40............. A... Pressure altitude C....g. USE Determine the effective wind velocity..... project horizontally to the left to read headwind component. Temperature B.. Density ratio 60°F 2........... project horizontally to the left scale to read density ratio..........000 Ft... DENSITY RATIO CHART This chart (figure 11-13) provides a means of obtaining a single factor (density ratio) that may be used to represent a combination of temperature and pressure altitude. effective wind is 050/35.. Maximum Abort Speed ....... It is not to be used as a ground controllability chart. 11-28 11-29 11-30 11-32 11-34 11-36 WIND COMPONENTS CHART This chart (figure 11-12) is used primarily for breaking a forecast wind down into crosswind and headwind components for takeoff computations......... effective wind is 050/40.... Enter the chart with the relative bearing..... USE Enter the chart with existing temperature and project vertically to intersect the applicable pressure altitude curve..... Takeoff Distance. gross weight. If this projected line does not intersect the computed takeoff gross weight curve.700 Lb. From this point project horizontally to read the maximum gross weight. Maximum Gross Weight 60° F (15. the takeoff should be aborted. If an engine is lost above the maximum abort speed but below the minimum go speed or at a condition where insufficient rate of climb capability exists. If the takeoff weight is higher than this value and gross weight cannot be safely reduced. and project horizontally to the available runway length grid line. Separate plots are provided for maximum and military thrust conditions. Parallel the nearest guideline up or down to intersect the baseline. USE To determine the maximum gross weight for 100 fpm single engine rate of climb. The minimum go speed for a maximum thrust takeoff will be less than that for a military thrust takeoff due to the greater acceleration with maximum thrust up to and including the 3-second decision time. NOTE This problem assumes maximum thrust on operating engine within 5 seconds after engine failure. If the gross weight curve lies to the right of the projected line. From this point descend vertically to intersect the applicable takeoff gross weight curve. 11-24 . enter the applicable chart with the field temperature and project vertically up to the field altitude. a singleengine takeoff cannot be made under the combined conditions. and the runway length remaining. then there will be no corresponding minimum go speed.Section XI Part 2 A1-F18AC-NFM-200 MINIMUM GO SPEED CHARTS These charts (figures 11-14 and 11-15) provide the means of determining the minimum speed at which the aircraft can experience an engine failure and still take off under existing conditions of temperature. . In the case of a military thrust takeoff.6 °C) 8000 Ft 43. enter the applicable plot with the prevailing density ratio. Altitude C. the pilot can neither abort nor take off safely on the runway length remaining without considering such factors as reducing gross weight or engaging the overrun end arrestment cable. then horizontally to read minimum go speed. Sample Problem A. Temperature B. USE To determine minimum go speed. pressure altitude. The data is based on an engine failure occurring at the minimum go speed and allows for a 3-second decision period with one engine operating at its initial thrust setting. an additional 2-second period is allowed for advancing the operating engine throttle to maximum thrust. 000 Lb. Sample Problem Maximum Thrust Takeoff. 150 KCAS MAXIMUM ABORT SPEED CHARTS These charts (figures 11-16 and 11-17) provide a means of determining the maximum speed at which an abort may be started and the aircraft stopped within the remaining runway length. A. Separate charts are provided for maximum and military thrust and various takeoff gross weights on both dry and wet runways.000 Ft. From this point.90 8.90 8. project vertically down to the applicable gross weight curve for either dry or wet runway conditions.000 Ft. Parallel guideline to baseline D. Sample Problem Maximum Thrust Takeoff A. 45. Gross weight D. 120 KCAS 105 KCAS 11-25 . Minimum go speed 0. Dry Runway E. The data are based on a 3-second reaction time after engine failure followed by a 2-second transition time to reach idle thrust and full braking (brake limits applied). Density ratio B. Maximum abort speed Wet Runway 0. Takeoff gross weight E. 50. Maximum abort speed. Available runway length C. Density ratio B. Available runway length C.000 Lb.A1-F18AC-NFM-200 Section XI Part 2 USE Enter the chart with the prevailing density ratio and project horizontally right to intersect the available runway length curve. then horizontally left to read maximum abort speed. Use figures 11-20 and 11-21 to adjust for other CG locations. G. Separate charts are provided for maximum and military thrust. Minimum Density Ratio 0. These takeoff speeds and distances reflect a CG location of 22% MAC. project vertically down to read no wind ground run distance. Parallel the appropriate wind guideline (headwind or tailwind) to intersect the takeoff wind velocity. A table has been provided on each chart to show nosewheel liftoff speed with the corresponding aircraft takeoff speed for various gross weight and CG combinations. Nosewheel liftoff speed for a 163 KIAS CG of 22% MAC (from table) K.200 Ft.000 Ft. Ground run (wind corrected) 4.300 Ft. project horizontally to the left to read the minimum allowable density ratio for takeoff at this weight/CG combination. to a height of 50 feet J. Gross weight 48. wind adjusted ground run and the total distance to climb to a height of 50 feet.83 (Applicable density ratio > Minimum density ratio) D. continue down to the reflector line and project horizontally to the left scale.90 E. H.Section XI Part 2 A1-F18AC-NFM-200 TAKEOFF DISTANCE CHARTS These charts (figures 11-18 and 11-19) are used to determine the no wind ground run distance. CG 20% MAC C.000 Lb. No wind ground run distance 4. Effective headwind 10 Kt. Sample Problem Maximum Thrust Takeoff A. Total distance required to climb 5. . From this intersection. F. From this intersection. I. Takeoff speed (from table) 173 KIAS 11-26 Change 1 . Enter the chart with the applicable density ratio and project horizontally to the right to intersect the appropriate takeoff gross weight curve. B. Gross weight 48. USE Enter the density ratio plot with the gross weight and project vertically up to intersect the appropriate CG curve.000 Lb. To find the total distance required to climb to a height of 50 feet. Applicable Density ratio 0. From this point project vertically down to read ground run adjusted for wind effects. then project vertically down.000 Lb.000 Ft.300 Ft. To determine wind effect on ground run and total distance to height of 50 feet.Maximum Thrust . Parallel acceleration guideline F.20% MAC A. Normal CG takeoff speed 173 KIAS D. From this intersection. Gross weight 48. From this intersection. Read nosewheel liftoff speed at 20% MAC 170 KIAS (From Takeoff Distance . project horizontally left to ground run corrected for CG. To determine speed at a given distance on the takeoff run. enter the chart at the ground run distance and project horizontally to the reference acceleration curve. Normal CG 22% MAC C. The charts can also be used to obtain any distance and speed relationship during the takeoff ground run. B.Nosewheel Liftoff/Takeoff Speeds) Change 1 11-27 . (from Takeoff Distance chart) E. Ground run corrected for CG 5. Takeoff CG 20% MAC G. Sample Problem Maximum Thrust Takeoff CG . Intersection of new acceleration curve I. 20% MAC takeoff speed 183 KIAS H. The nosewheel liftoff speed can be determined in the takeoff distance chart by interpolation in the speed table using gross weight and CG. then vertically down to intersect the new acceleration curve. parallel the nearest acceleration guideline. Normal no wind ground run 4. Then project vertically up to the corresponding speed. Given distance on ground run 2. The vertical projection passes through the actual CG takeoff speed. J. USE Enter the chart with the applicable takeoff gross weight and project horizontally right to intersect the normal CG curve. Return to the gross weight-normal CG intersection and project further right to the actual takeoff CG curve. K. Reenter the chart with the normal no wind ground run (from Takeoff Distance chart) and project horizontally right to intersect the vertical projection from the normal CG curve.000 Ft. Corresponding ground run 130 KIAS speed L. The vertical projection passes through the normal CG takeoff speed.Section XI Part 2 A1-F18AC-NFM-200 TAKEOFF GROUND ROLL CORRECTION FOR CG CHARTS These charts (figures 11-20 and 11-21) are used primarily to determine takeoff distances resulting from adverse conditions of gross weight and CG. reenter appropriate takeoff distance chart with corrected ground roll. Section XI Part 2 A1-F18AC-NFM-200 Figure 11-12. . Wind Components 11-28 . Density Ratio 11-29 .A1-F18AC-NFM-200 Section XI Part 2 Figure 11-13. .Section XI Part 2 A1-F18AC-NFM-200 Figure 11-14. Minimum Go Speed .F404-GE-400 11-30 .Maximum Thrust . Military Thrust .A1-F18AC-NFM-200 Section XI Part 2 Figure 11-15.F404-GE-400 11-31 . Minimum Go Speed . F404-GE-400 11-32 . Maximum Abort Speed .Maximum Thrust . .Section XI Part 2 A1-F18AC-NFM-200 Figure 11-16. Military Thrust .A1-F18AC-NFM-200 Section XI Part 2 Figure 11-17.F404-GE-400 11-33 . Maximum Abort Speed . Takeoff Distance .Section XI Part 2 A1-F18AC-NFM-200 Figure 11-18.Maximum Thrust .F404-GE-400 11-34 Change 1 . . Takeoff Distance .F404-GE-400 Change 1 11-35 .Military Thrust .Section XI Part 2 A1-F18AC-NFM-200 Figure 11-19. . Takeoff Ground Roll Correction for CG .Maximum Thrust .Section XI Part 2 A1-F18AC-NFM-200 Figure 11-20.F404-GE-400 11-36 Change 1 . F404-GE-400 Change 1 11-37 .Section XI Part 2 A1-F18AC-NFM-200 Figure 11-21.Military Thrust . Takeoff Ground Roll Correction for CG . ...... time and distance data from brake release to 350 KIAS or climb speed.. and distance required to climb from sea level to selected altitude at climb speed schedule....... fuel............ Also provided are data for peak rate of climb (figure 11-27) and instantaneous rate of climb (figure 11-28) for two-engine operation at military thrust........................... and separate charts for time.. Climb charts are also included to present the maximum thrust climb performance for two-engine operation.............................. Peak Rate of Climb-Military Thrust................. USE CLIMB SPEED SCHEDULE ..From the appropriate drag index column determine the optimum climb speed (calibrated airspeed to constant Mach number) for the selected climb altitude...... Adjustment to SEROC for Retracting Landing Gear ..... Distance ............. COMBAT CEILING AND SERVICE CEILING Enter the chart with the initial climb gross weight and project vertically up to the appropriate drag index curve....Section XI Part 3 A1-F18AC-NFM-200 PART 3 .... Military Thrust Climb One Engine Operating ............. The data include peak rate of climb Mach number........... and distance required to climb from sea level to selected altitude at peak rate of climb. Single Engine Rate of Climb .................... Supersonic Maximum Thrust Climb ........................ MAXIMUM THRUST CLIMB Maximum thrust climb charts for two-engine operation (figure 11-29) are provided for various drag indexes and gross weights............................................ 11-44A 11-45 11-51 11-52 11-53 11-54 11-58 11-59 11-64 11-65 11-71 11-75 11-84C TAKEOFF ALLOWANCES CHART The takeoff allowances and acceleration to climb speed chart (figure 11-22) presents fuel usage during start.................... combat ceiling.... ...... Climb .............. These charts are used to obtain climb data after takeoff to selected altitude in a gear-up and flaps-up configuration.. This chart is used to determine fuel..350 KCAS Time ..CLIMB F404-GE-400 MILITARY THRUST CLIMB TABLE OF CONTENTS CHARTS Takeoff Allowances and Acceleration to Climb Speed ................ The data includes climb speed schedule... Instantaneous Rate of Climb Military Thrust .... Peak Rate of Climb-Maximum Thrust ...... taxi.... Also included are data for instantaneous rate of climb (figure 11-30). combat ceiling and service ceiling.................................. Project horizontally left to find the service ceiling and the combat ceiling for initial climb gross weight...................... Fuel.......... 11-38 Change 4 Military thrust climb charts (figure 11-23 for twoengine operation and figure 11-31 for single engine operation) are provided for various drag indexes and gross weights........ Instantaneous Rate of Climb Maximum Thrust . Military Thrust Climb ......................... and separate charts for time............. fuel.. CLIMB PERFORMANCE CHARTS Climb charts present the military thrust climb performance for two-engine and single engine operation............ optimum cruise altitude....... The preclimb fuel requirements should be noted if the takeoff acceleration phase is to be considered in the climb planning............... then horizontally left to the temperature baseline and parallel the appropriate temperature deviation guideline to the correct temperature deviation........... engine runup. 11-39 .Presentations of these charts are identical: therefore.A1-F18AC-NFM-200 Optimum Cruise Altitude (figure 11-23. Drag Index C. From this point project horizontally left to the temperature baseline and parallel the appropriate temperature deviation guideline to the correct temperature deviation. 100 -10°C 41. FUEL. Sample Problem Combat Ceiling and Service Ceiling (figure 11-23. Enter the appropriate chart with the initial gross weight and project horizontally right to intersect the desired altitude then vertically down to the appropriate drag index curve. Service ceiling E. fuel.500 Ft. they are used in the same manner.450 Ft. Initial gross weight B. 100 -10°C 36. Project horizontally left to find the optimum cruise altitude for initial climb gross weight. Optimum cruise altitude Section XI Part 3 44. Initial gross weight B. then horizontally left to the temperature baseline and parallel the appropriate temperature deviation guideline to the correct temperature deviation. Temperature deviation from standard day D.000 Ft. 39.000 Lb. project horizontally left to find time. Drag Index C.Enter the chart with the initial gross weight and project vertically up to the appropriate drag index curve. OPTIMUM CRUISE ALTITUDE . sheet 3) A. Temperature deviation from standard day D. TIME. or distance required.000 Lb. AND DISTANCE . sheet 2) A. Combat ceiling 44. Temperature baseline E. 4. Parallel the applicable guideline (hotter or colder) to intersect a vertical grid line corresponding to the degree of deviation between forecast flight temperature and standard day temperature. fuel. Drag index D. then maintaining constant Mach to cruise altitude. From this point continue horizontally to the left to read the planning data (fuel.350 KCAS These charts (figure 11-24 thru figure 11-26) show time. Temperature deviation from standard day E.000 Ft. Drag Index D.Section XI Part 3 A1-F18AC-NFM-200 Time. 5. time. 30. 60NM Sample Problem A. Distance 44. Fuel. sheets 4. and distance for a simplified military thrust climb. Project vertically downward to intersect the applicable drag index line.000 Ft.000 Lb. Time to climb F. Temperature deviation F. 100 +10°C 7. & 6) A. or the optimum cruise altitude for the computed drag index. Fuel required G. Fuel required Time to Climb Distance nautical miles 35. Cruise Altitude C. Selected altitude C. 150 +5°C 1000 Lb.000 Lb. .4 Min.8 Min. Project horizontally to the right and intersect the assigned cruise altitude. or distance). Gross Weight B. USE Enter the charts with the initial climb gross weight. These data charts are based on climbing at 350 knots until interception of the constant Mach portion of the military thrust climb speed schedule. 35. Initial gross weight B. Standard day (°C)). 1480 Lb.S. and Distance to Climb (figure 11-23. then project horizontally to the left to the temperature deviation baseline (corresponds to a U. 33 NM CLIMB CHARTS . 11-40 . Selected altitude C. gross weights.000 Ft. 30. INSTANTANEOUS RATE OF CLIMB CHARTS These charts are based on two-engine operation at military thrust (figure 11-28) or maximum thrust (figure 11-30) and provides instantaneous rate of climb for any given altitude gross weight combination with various drag indexes. and drag indexes. fuel. then horizontally left to read the instantaneous rate of climb in feet per minute. Drag index D. 100 4. The charts include a climb schedule (Mach number) and the normal time. then vertically down to find the Mach number for peak rate of climb. A combat ceiling chart is included for maximum thrust.100 FPM 11-41 .Enter the chart at the selected pressure altitude and project horizontally right to the appropriate drag index curve. Gross weight B. The data are based on either military thrust (figure 11-27) or maximum thrust (figure 11-29) at selected altitudes.Section XI Part 3 A1-F18AC-NFM-200 PEAK RATE OF CLIMB CHARTS These charts provide peak rate of climb data for two-engine operation. From this point. project vertically down to the computed drag index curve. Sample Problem Instantaneous Rate of Climb (figure 11-28) A. and distance required charts which are used in an identical manner as the military thrust climb charts based on the climb speed schedule. USE Enter the chart with the appropriate gross weight and project horizontally right to the selected altitude curve. Instantaneous rate of climb 40. USE MACH NUMBER .000 Lb. Total fuel required to accelerate and climb (J+R) 1. Climb Mach number F.1 0.4 Min. subtract the distance.7 Min. Time at end of climb 3. and time required to accelerate. fuel used (gross weight change). P. 1. since acceleration to supersonic Mach numbers at this altitude provides for the optimum performance capability. From these values.6 Min. Distance required for acceleration (G-D) 6. proceed parallel along the guidelines to the desired altitude. Distance required for climb (N-G) 29. . fuel. fuel and time are desired. and time corresponding to the initial Mach number to determine the distance. acceleration at 35.500 Lb.0 Min. Gross weight at end of acceleration 41. I. From the climb Mach number gross weight intersection (start of climb). Time at end of acceleration 11-42 42. Project both vertically downward and horizontally to the left from this point to read gross weight and distance traveled. Time corresponding to initial Mach number D. J. T.500 Lb. If total distance.Section XI Part 3 A1-F18AC-NFM-200 SUPERSONIC MAXIMUM THRUST CLIMB CHARTS These charts (figure 11-32. also note the time. Time required for acceleration (F-C) 0.0 NM R. and time for this starting point. Enter the chart with the gross weight and proceed vertically to the initial Mach number and note the corresponding distance and time. gross weight. Fuel required for climb (H-O) 1. add the climb and acceleration values together.000 Lb. USE G. Gross weight at end of climb 40.1 NM U.1 NM L.000 Ft.000 feet to the supersonic combat ceiling. Distance at end of acceleration 13. Distance at end of climb 42. Total time required to accelerate and climb (I+P) 3. Subtract from this data the corresponding values at the start of climb to obtain the distance traveled.000 Lb. Sample Problem Configuration: (2)AIM-9 +(2)AIM-7 A. Total distance required to accelerate and climb (K+Q) 35.0 NM O. Initial gross weight B. If supersonic climb is contemplated. and distance required to accelerate from the subsonic to the supersonic climb Mach number at 35. Obtain the distance. Distance corresponding to initial Mach number E. The time to distance/altitude relationship is superimposed on the plot. with guidelines provided to show the weight reduction as the climb progresses.000 feet. N. .3 Min. Distance traveled in the climb is plotted against gross weight. Q. Level flight acceleration data are provided which includes time. M. sheets 1 thru 4) are plotted for supersonic maximum thrust climb from 35. K. Fuel required for acceleration (A-H) 500 Lb. and the time required to complete the climb. weight.7 Min.0 NM H. Altitude at end of climb 46.9 NM 1.000 feet followed by the climb is recommended. 6.500 Lb.24 1. Initial Mach number C. Proceed parallel to the guidelines to the desired supersonic climb Mach number (end of acceleration). S. Time required for climb (M-F) 2. the weight change (fuel used). Sample Problem FE + 330 Gallon Centerline Tank. For air temperatures between the values listed at the top of each chart. and airspeed. Voperational endspeed 59°F 166 knot (from operational endspeed table at top of chart) C. Stores retained SEROC 1. From this intersection. sheet 3) A. Stores retained 1g trim AOA 9. Launch weight 40.Section XI Part 3 A1-F18AC-NFM-200 SINGLE ENGINE RATE OF CLIMB LAUNCH/TAKEOFF CONFIGURATION CHARTS These charts (figure 11-33. Stores jettisoned SEROC 2. (2)AIM-9 + (2)AIM-7 + 330 Gallon Centerline Fuel Tank.730 fpm Change 4 11-43 . Single engine rate of climb is presented as a function of temperature. Maximum thrust launch power seting (figure 11-33. gear down) configurations with both maximum afterburner and military rated thrust on the operating engine.000 lb F.3° G. Charts are provided for six different external store loadings. Stores jett 1g trim AOA 7. angle of attack. USE Enter the chart representing the applicable air temperature at the desired airspeed and project vertically upward until intersecting the appropriate gross weight curve.2° H.000 lb E. The single engine rate of climb achievable with external stores jettisoned is also provided on each chart.820 fpm I. Stores jettisoned weight 36. sheets 1 thru 12) provide the single engine rate of climb capability in the catapult launch and field takeoff (half flaps. Dual engine operational launch endspeeds are provided for reference on each of the charts. read the angle of attack required to maintain 1 g. Vsingle engine endspeed 161 knot (assume 5 knot reduction in endspeed due to single engine thrust loss) D. linear interpolation between the two applicable charts must be used. unaccelerated flight at this condition and then project horizontally left to obtain the corresponding single engine rate of climb. gross weight. Temperature B. Sample Problem A Gear down SEROC B. gear down) configurations with maximum afterburner thrust on the operating engine.340 fpm . sheets 1 through 12. From this intersection. project horizontally left to obtain the corresponding gear up single engine rate of climb. 1g trim AOA C. USE Enter the chart with the gear down single engine rate of climb established using figure 11-33 and project vertically upward to the appropriate angle of attack.2° 3. Gear up single engine rate of climb is presented as a function of gear down single engine rate of climb and the angle of attack required to maintain 1g. Gear up SEROC 11-44 Change 4 2. unaccelerated flight as determined from figure 11-33.730 fpm 7.Section XI Part 3 A1-F18AC-NFM-200 ADJUSTMENT TO SEROC FOR RETRACTING LANDING GEAR CHART This chart (figure 11-33A) provides the effect of raising the landing gear on single engine rate of climb capability in the catapult launch and field takeoff (half flaps. 30 SEC AT MIL E 66 LB /ENG MIL TAKEOFF MIL ACCEL TO 350 KNOTS MIL TAKEOFF MIL ACCEL TO MIL CLIMB SPEED MAX TAKEOFF MIL ACCEL TO MIL CLIMB SPEED MAX TAKEOFF MAX ACCEL TO MAX CLIMB SPEED DI E0 TO 75 TOGWE 38.0 Figure 11.7 1.4 1. BRAKE RELEASE TO CLIMB SPEED (NOMINAL VALUES) TIME (MIN) FUEL (LB) DIST (NM) 1.5 440 4.000 LB.3 670 4.Section XI Part 3 A1-F18AC-NFM-200 TAKEOFF ALLOWANCES AND ACCELERATION TO CLIMB SPEED F404-GE-400 AIRCRAFT CONFIGURATION VARIOUS DRAG INDEXES REMARKS ENGINE(S): (2) F404-GE-400 U.6 1. STANDARD DAY.3 400 5.F404-GE-400.1 1120 4.000 LB.2 540 5.8 850 3.5 DI > 75 TOGWE 50.1 1. Takeoff Allowances and Acceleration to Climb Speed . TIME (MIN) FUEL (LB) DIST (NM) 0.8 LB/GAL START E 10 LB /ENG TAXI AT IDLE E 14 LB /MIN /ENG ENGINE RUNUP. 1962 DATE: 15 JULY 1986 DATA BASIS: ESTIMATED (BASED ON FLIGHT TEST) FUEL GRADE: JP-5 FUEL DENSITY: 6.S.4 0.9 260 2. Change 4 11-44A/(11-44B blank) .22.5 1.4 410 4. . 78 500 .50 285 .74 425 .84 317 .75 280 .83 308 .69 35 272 .74 243 .83 360 .85 356 .85 321 .62 280 .46 285 .63 20 398 .85 287 .83 360 .51 320 .81 272 . AND IS BASED ON START.66 285 .47 15 305 .81 308 . Figure 11-23.83 276 .Section XI Part 3 A1-F18AC-NFM-200 CLIMB SPEED SCHEDULE F404-GE-400 MILITARY THRUST AIRCRAFT CONFIGURATION VARIOUS DRAG INDEXES ALL GROSS WEIGHTS REMARKS ENGINE(S): (2) F404-GE-400 U.70 360 .80 320 .80 425 .73 320 .80 285 .83 425 .81 276 .74 216 .84 253 .65 340 .42 270 .72 260 .78 229 .68 285 .76 222 .57 25 305 . 515 .51 280 .83 342 .83 426 .41 260 .85 432 .84 284 .83 276 .S.56 280 .85 256 . Military Thrust Climb .51 270 .55 285 .77 340 .81 246 .67 320 .81 340 .47 285 .43 280 .56 285 .L.80 AIRCRAFT DRAG INDEX PRESSURE ALTITUDE 1000FT 175 200 225 250 275 300 KCAS MACH KCAS MACH KCAS MACH KCAS MACH KCAS MACH KCAS MACH S.54 340 .73 285 .8 LB/GAL AIRCRAFT DRAG INDEX PRESSURE ALTITUDE 1000FT 0 25 50 75 100 125 150 KCAS MACH KCAS MACH KCAS MACH KCAS MACH KCAS MACH KCAS MACH KCAS MACH S.78 257 .84 500 .69 25 361 .76 250 . STANDARD DAY.81 242 .65 260 .85 394 .76 30 325 .56 320 .79 236 . 20 MINUTES AT IDLE.59 340 .46 270 .43 10 305 .80 40 259 .80 240 . 1962 DATE: 16 JULY 1986 DATA BASIS: ESTIMATED (BASED ON FLIGHT TEST) FUEL GRADE: JP-5 FUEL DENSITY: 6.83 490 .58 15 438 .84 352 .62 285 .68 280 .72 NOTE FUEL ALLOWANCE FOR TAKEOFF AND ACCELERATION TO CLIMB SPEED IS 1200 POUNDS.47 280 .52 20 305 .59 260 .55 270 .80 35 291 .74 270 .84 391 . 30 SECONDS RUNUP AT MIL.64 360 .71 340 .72 40 242 .83 317 .51 285 . 305 .80 269 .75 285 .61 270 .43 285 .76 360 .85 472 .76 490 .81 304 .L.84 466 .67 270 .54 260 .84 426 .49 260 .F404-GE-400 (Sheet 1 of 6) 11-45 .83 246 .39 5 305 .61 320 .60 285 .45 260 .48 5 515 . AND A MIL POWER TAKEOFF.83 352 .83 391 .63 30 304 .53 10 478 .79 265 .83 246 . Section XI Part 3 A1-F18AC-NFM-200 Figure 11-23. . Military Thrust Climb .F404-GE-400 (Sheet 2 of 6) 11-46 . Military Thrust Climb .F404-GE-400 (Sheet 3 of 6) 11-47 .A1-F18AC-NFM-200 Section XI Part 3 Figure 11-23. Military Thrust Climb .Section XI Part 3 A1-F18AC-NFM-200 Figure 11-23. .F404-GE-400 (Sheet 4 of 6) 11-48 . F404-GE-400 (Sheet 5 of 6) 11-49 .A1-F18AC-NFM-200 Section XI Part 3 Figure 11-23. Military Thrust Climb . Military Thrust Climb . .Section XI Part 3 A1-F18AC-NFM-200 Figure 11-23.F404-GE-400 (Sheet 6 of 6) 11-50 . 350 KCAS .Military Thrust . Time to Climb .F404-GE-400 11-51 .A1-F18AC-NFM-200 Section XI Part 3 Figure 11-24. F404-GE-400 11-52 .350 KCAS . . Fuel to Climb .Section XI Part 3 A1-F18AC-NFM-200 Figure 11-25.Military Thrust . F404-GE-400 11-53 .350 KCAS .Military Thrust . Distance To Climb .A1-F18AC-NFM-200 Section XI Part 3 Figure 11-26. .Section XI Part 3 A1-F18AC-NFM-200 Figure 11-27.Military Thrust . Peak Rate of Climb .F404-GE-400 (Sheet 1 of 4) 11-54 . F404-GE-400 (Sheet 2 of 4) 11-55 . Peak Rate of Climb .A1-F18AC-NFM-200 Section XI Part 3 Figure 11-27.Military Thrust . . Peak Rate of Climb .F404-GE-400 (Sheet 3 of 4) 11-56 .Section XI Part 3 A1-F18AC-NFM-200 Figure 11-27.Military Thrust . A1-F18AC-NFM-200 Section XI Part 3 Figure 11-27. Peak Rate of Climb - Military Thrust - F404-GE-400 (Sheet 4 of 4) 11-57 Section XI Part 3 A1-F18AC-NFM-200 Figure 11-28. Instantaneous Rate of Climb - Military Thrust - F404-GE-400 11-58 . A1-F18AC-NFM-200 Section XI Part 3 Figure 11-29. Peak Rate of Climb - Maximum Thrust - F404-GE-400 (Sheet 1 of 5) 11-59 Section XI Part 3 A1-F18AC-NFM-200 Figure 11-29. Peak Rate of Climb - Maximum Thrust - F404-GE-400 (Sheet 2 of 5) 11-60 . A1-F18AC-NFM-200 Section XI Part 3 Figure 11-29. Peak Rate of Climb - Maximum Thrust - F404-GE-400 (Sheet 3 of 5) 11-61 Section XI Part 3 A1-F18AC-NFM-200 Figure 11-29. Peak Rate of Climb - Maximum Thrust - F404-GE-400 (Sheet 4 of 5) 11-62 . Peak Rate of Climb .F404-GE-400 (Sheet 5 of 5) 11-63 .A1-F18AC-NFM-200 Section XI Part 3 Figure 11-29.Maximum Thrust . Instantaneous Rate of Climb .F404-GE-400 11-64 .Maximum Thrust .Section XI Part 3 A1-F18AC-NFM-200 Figure 11-30. . 1962 INOPERATIVE ENGINE WINDMILLING DATE: 15 JULY 1986 DATA BASIS: ESTIMATED (BASED ON FLIGHT TEST) FUEL GRADE: JP-5 FUEL DENSITY: 6. AND IS BASED ON START.70 NOTE FUEL ALLOWANCE FOR TAKEOFF AND ACCELERATION TO CLIMB SPEED IS 1200 POUNDS.8 LB/GAL AIRCRAFT DRAG INDEX PRESSURE ALTITUDE 1000FT 0 25 50 & ABOVE KCAS MACH KCAS MACH KCAS MACH S.45 265 265 .L.58 .F404-GE-400 (Sheet 1 of 6) 11-65 .70 .67 35 40 235 208 .42 .60 . Figure 11-31. 5 275 275 .70 .38 . Military Thrust Climb . STANDARD DAY.44 250 250 .50 .70 265 265 265 265 263 .55 . 20 MINUTES AT IDLE.S.41 10 15 20 25 30 275 275 275 275 263 .48 .45 .One Engine Operating .70 235 208 .60 . AND A MIL POWER TAKEOFF. 30 SECONDS RUNUP AT MIL.Section XI Part 3 A1-F18AC-NFM-200 CLIMB SPEED SCHEDULE F404-GE-400 ONE ENGINE OPERATING MILITARY THRUST AIRCRAFT CONFIGURATION VARIOUS DRAG INDEXES ALL GROSS WEIGHTS REMARKS ENGINE(S): (2) F404-GE-400 U.54 .70 235 208 .40 .64 .50 .66 .53 .70 250 250 250 250 250 .70 . .Section XI Part 3 A1-F18AC-NFM-200 Figure 11-31.F404-GE-400 (Sheet 2 of 6) 11-66 . Military Thrust Climb .One Engine Operating . F404-GE-400 (Sheet 3 of 6) 11-67 .One Engine Operating .A1-F18AC-NFM-200 Section XI Part 3 Figure 11-31. Military Thrust Climb . F404-GE-400 (Sheet 4 of 6) 11-68 . .Section XI Part 3 A1-F18AC-NFM-200 Figure 11-31. Military Thrust Climb .One Engine Operating . F404-GE-400 (Sheet 5 of 6) 11-69 .A1-F18AC-NFM-200 Section XI Part 3 Figure 11-31.One Engine Operating . Military Thrust Climb . F404-GE-400 (Sheet 6 of 6) 11-70 .Section XI Part 3 A1-F18AC-NFM-200 Figure 11-31.One Engine Operating . . Military Thrust Climb . A1-F18AC-NFM-200 Section XI Part 3 Figure 11-32.F404-GE-400 (Sheet 1 of 4) 11-71 . Supersonic Maximum Thrust Climb . .Section XI Part 3 A1-F18AC-NFM-200 Figure 11-32. Supersonic Maximum Thrust Climb .F404-GE-400 (Sheet 2 of 4) 11-72 . A1-F18AC-NFM-200 Section XI Part 3 Figure 11-32. Supersonic Maximum Thrust Climb .F404-GE-400 (Sheet 3 of 4) 11-73 . Section XI Part 3 A1-F18AC-NFM-200 Figure 11-32. .F404-GE-400 (Sheet 4 of 4) 11-74 . Supersonic Maximum Thrust Climb . Single Engine Rate of Climb .F404-GE-400 (Sheet 1 of 12) Change 4 11-75 .Section XI Part 3 A1-F18AC-NFM-200 Figure 11-33. F404-GE-400 (Sheet 2 of 12) 11-76 Change 4 . Single Engine Rate of Climb .Section XI Part 3 A1-F18AC-NFM-200 Figure 11-33. Section XI Part 3 A1-F18AC-NFM-200 Figure 11-33.F404-GE-400 (Sheet 3 of 12) Change 4 11-77 . Single Engine Rate of Climb . Section XI Part 3 A1-F18AC-NFM-200 Figure 11-33. Single Engine Rate of Climb .F404-GE-400 (Sheet 4 of 12) 11-78 Change 4 . Single Engine Rate of Climb .Section XI Part 3 A1-F18AC-NFM-200 Figure 11-33.F404-GE-400 (Sheet 5 of 12) Change 4 11-79 . Single Engine Rate of Climb .Section XI Part 3 A1-F18AC-NFM-200 Figure 11-33.F404-GE-400 (Sheet 6 of 12) 11-80 Change 4 . F404-GE-400 (Sheet 7 of 12) Change 4 11-81 . Single Engine Rate of Climb .Section XI Part 3 A1-F18AC-NFM-200 Figure 11-33. Single Engine Rate of Climb .F404-GE-400 (Sheet 8 of 12) 11-82 Change 4 .Section XI Part 3 A1-F18AC-NFM-200 Figure 11-33. Section XI Part 3 A1-F18AC-NFM-200 Figure 11-33.F404-GE-400 (Sheet 9 of 12) Change 4 11-83 . Single Engine Rate of Climb . F404-GE-400 (Sheet 10 of 12) 11-84 Change 4 . Single Engine Rate of Climb .Section XI Part 3 A1-F18AC-NFM-200 Figure 11-33. Single Engine Rate of Climb .Section XI Part 3 A1-F18AC-NFM-200 Figure 11-33.F404-GE-400 (Sheet 11 of 12) Change 4 11-84A . Section XI Part 3 A1-F18AC-NFM-200 Figure 11-33. Single Engine Rate of Climb .F404-GE-400 (Sheet 12 of 12) 11-84B Change 4 . Adjustment to SEROC for Retracting Landing Gear .F404-GE-400 Change 4 11-84C/(11-84D blank) .Section XI Part 3 A1-F18AC-NFM-200 Figure 11-33A. . .. Combat Fuel Flow ............ Combat Specific Range. Drag index C...... To read optimum cruise altitude.. Specific Range One Engine Operating ... The charts depict cruise altitude. Change 1 11-85 ... 50 0...................RANGE F404-GE-400 TABLE OF CONTENTS CHARTS Optimum Cruise ................ project horizontally left from the intersection of the drag index curve to the temperature baseline and parallel the appropriate temperature deviation guideline to the correct temperature deviation......... reflect horizontally left and read Mach number and specific range in nautical miles per pound.................700 Ft........... 11-91 11-93 11-94 11-160 11-200 11-204 11-208 11-210 11-210A 11-211 11-221 OPTIMUM CRUISE CHARTS These charts (figures 11-34 and 11-35) present cruise data for two-engine and single engine operation.................................... Bingo ..... Sample Problem One Engine Operating (figure 11-35) A..............000 Lb.......................... specific range (nautical miles per pound of fuel (NMPP))...... and cruise Mach number for various gross weights and drag indexes...... Optimum cruise altitude 40...... Constant Altitude/Long Range Cruise ...... Specific range E.............. Mach number D.....Section XI Part 4 A1-F18AC-NFM-200 PART 4 ................ Optimum Cruise One Engine Operating ............................. Temperature deviation from standard day F..64 0.......079 NMPP +10°C 20.. USE Enter the chart with the applicable gross weight and project vertically up to intersect the appropriate drag index curves... From the intersection of these drag index curves........ Bingo One Engine Operating .................. Rangewind Correction............... Gross weight B............. Headwind Effects on Bingo Fuel .................................. Specific Range.... Project horizontally to read optimum cruise altitude. Mach number (cruise AOA) B. 35. Drag index (total) C.900 PPH 0. 10.000. Standard Day VMAX O.000 pounds in 4. total fuel flow and specific range for optimum cruise can be obtained by entering the chart on the optimum cruise line at the appropriate drag index and projecting vertically down and horizontally left to read Mach number and specific range respectively. and 45. Mach number (optimum cruise) J. Repeat this process to obtain like data for desired Mach number at dash AOA. multiply the maximum Mach number obtained by the VMAX factor corresponding to the desired temperature deviation. 25. Mach number (dash AOA) F. Specific range H. Mach number. Specific range K. From this point read total fuel flow. Specific range E.42.Section XI Part 4 A1-F18AC-NFM-200 SPECIFIC RANGE CHARTS These charts (figures 11-36 thru 11-141) present planning data for constant altitude cruise with various drag indexes at altitudes of sea level. Total fuel flow I. USE Enter the appropriate chart for desired cruise altitude and gross weight with the desired Mach number for cruise AOA and project vertically up to the computed drag index.000.862 0.000. 40.300 PPH +20°C 0. Total fuel flow L. .5 0. Total fuel flow D.0515 NMPP 6. VMAX Factor N. Total fuel flow for any combination of Mach number and drag index can be obtained by interpolating between the total fuel flow lines provided on the charts.000 feet and gross weights of 26.0362 NMPP 14.000. The charts depict specific range (nautical miles per pound of fuel (NMPP)) and total fuel flow in pounds per hour for various Mach numbers at cruise AOA (greater than approximately 2.300 PPH 0.000. Maximum endurance data is obtained in an identical manner entering the chart on the line labeled maximum endurance.000. Maximum Mach number at a particular drag index and military power setting can be obtained by reading the VMAX curve at that drag index. 20.827 .8 152. 11-86 Sample Problem Chart: 5. 15.6 138. Correct VMAX 0.000. 30.000 Feet .5° or lower). then project horizontally left to read specific range in nautical miles per pound of fuel. Also depicted on the charts are lines for optimum cruise and maximum endurance. To correct for nonstandard day conditions.000 pound increments.5°) and dash AOA (approximately 2.5 0.5 7.000 Pounds (figure 11-47) Problem based on loading in figure 11-1.96 0.0495 NMPP 0.000 thru 50. Temperature deviation from standard day M. Drag index (total) G. 5.000. A. and then project horizontally to the left to read specific fuel flow. Note the general thrust setting required. Proceed vertically upward to the selected flight altitude. sheets 1 thru 4) present the specific range and the general thrust settings required to maintain a constant Mach number for a U. Thrust setting required Mod.S. These charts (figure 11-143. Specific fuel flow 630 Lb/Min.4 B. The fuel flow values are based on a stabilized level flight condition and do not represent the fuel flow required to accelerate to a given Mach number.000 feet.S. USE USE Enter the chart corresponding to the aircraft configuration with the desired Mach number for stabilized level flight. Desired Mach number 1. standard day and standard day +10°C at all altitudes between sea level and 50. Enter the chart corresponding to the aircraft configuration with the desired Mach number for stabilized level flight. Afterburners D. and then project horizontally left to obtain the specific range.000 feet. Sample Problem Sample Problem Configuration: (2)AIM-9 +(2)AIM-7 A. Each chart is plotted for a specific configuration. standard day and standard day +10°C at all altitudes from sea level to 50. C.023 NMPP Configuration: (2) AIM-9 + (2)AIM-7 A. 11-87 . Specific range 0. Desired Mach number 1. The specific range values are based on a stabilized level flight condition and do not represent the fuel flow required to accelerate to a given Mach number. Altitude (Standard Day) 25. Note the general thrust setting required. Afterburners D. Proceed vertically upward to the selected flight altitude. Altitude (Standard Day) 30.000 Ft.A1-F18AC-NFM-200 Section XI Part 4 COMBAT SPECIFIC RANGE CHARTS COMBAT FUEL FLOW CHARTS These charts (figure 11-142. Thrust setting required Mod.000 Ft. sheets 1 thru 4) present the specific fuel flow and general thrust setting to maintain a constant Mach number for a U.2 B. C. Cruise Mach B. Intersect OAT D. From this point. sheet 1) is used to determine the airspeed. Fuel flow K. 4. then vertically down to read fuel required. then horizontally left to read time required. The chart may be used for single engine or two-engine operation. True airspeed F. . Selected distance I. Headwind G. outside air temperature (OAT). wind component at altitude. Sample Problem A.65 20 °F 0 410 Kt. USE Enter the chart with the desired cruise Mach number and parallel the guidelines to intersect a vertical line projected up from the outside air temperature scale. Time required J. Continue to project horizontally left to the appropriate fuel flow line. 50 Kt. trace back to the zero wind line and project horizontally to the appropriate headwind or tailwind line.000 PPH 6. . OAT C. If winds are expected at the cruise altitude. project horizontally to the zero wind component line. Wind component E. and fuel flow are known. 600 NM 100 Min. continue to project vertically up to the selected distance curve. From this point. then vertically down to read true airspeed. Fuel required 0.667 Lb.Section XI Part 4 A1-F18AC-NFM-200 CONSTANT ALTITUDE/LONG RANGE CRUISE (SPEED-TIME-FUEL) CHART This chart (figure 11-144. 11-88 then vertically up to read groundspeed. 360 Kt. and fuel required to travel a given distance when the cruise Mach number. time. Groundspeed H. altitude and drag index of interest. 0. The chart may be used for single engine or two-engine operation. Sample Problem A. Specific Range E. outside air temperature (OAT). Cruise Mach B.52 -20°C 320 Kt. 8. From the intersection of the nautical miles per pound curve project horizontally left to read total fuel flow. Project horizontally down to read true airspeed and continue projection down to the specific range (nautical miles per pound) curve as determined from the specific range charts at the gross weight. sheet 2) is used to determine the true airspeed and total fuel flow when the cruise Mach number.0400 NM/Lb.A1-F18AC-NFM-200 Section XI Part 4 CONSTANT ALTITUDE/LONG RANGE CRUISE (TRUE AIRSPEED AND FUEL FLOW) CHART This chart (figure 11-144. USE Enter the chart with the desired cruise Mach number and project horizontally right to the outside air temperature curve. True Airspeed D.100 PPH 11-89 . OAT C. Total Fuel Flow 0. and specific range are known at a particular cruise condition. Enter the chart with relative wind direction and proceed vertically to the interpolated wind speed. add 360° to the wind direction and then perform the subtraction. If the aircraft heading is greater than forecast wind direction. USE Determine the relative wind direction by subtracting the aircraft heading from the forecast wind direction. From this point. Range . Relative wind direction B. The presented range factors consider wind speeds up to 150 knots from any relative wind direction for aircraft speeds of 200 to 1. project horizontally to intersect the aircraft true airspeed and reflect to the lower scale to read the range factor. Aircraft speed D. Multiply computed range by this range factor to find range as affected by wind. Wind speed C. .25 .factor 11-90 Change 1 150° 125 Kt.Section XI Part 4 A1-F18AC-NFM-200 RANGEWIND CORRECTION CHART This chart (figure 11-145) provides a means of correcting computed range (specific or total) for existing wind effects. Sample Problem A.300 KTAS. 400 KTAS 1. Charts are provided for Bingo cruise at best altitude and cruise at sea level. Adjusted fuel required 4. aircraft landing gear. fuel. B. Zero wind fuel required 3. USE Enter the appropriate chart with the zero wind fuel required and project horizontally to the headwind speed. Fuel required values include a 1. From this point. and flap setting.500 pound reserve. and airspeed required to travel a given distance using a combination of climb. weight and gear up and gear down configurations. and normal descent. BINGO CHARTS These charts (figures 11-146 thru 11-154) show time. Gear Up .A1-F18AC-NFM-200 Section XI Part 4 HEADWIND EFFECTS ON BINGO FUEL These charts (figure 11-145a and 11-145b) show the adjusted fuel required to perform the Bingo mission profiles as a function of headwind. Sample Problem Cruise at Sea Level. Charts are provided for twoengine and single engine operation at various combinations of drag index.460 Lb. C. maximum range cruise. Data are provided for both cruise at optimum cruise altitude and at sea level.200 Lb. Change 1 11-90A/(11-90B blank) .Flaps Half A. Headwind speed 75 Kts. project vertically down to read the adjusted fuel required. . A1-F18AC-NFM-200 Section XI Part 4 Figure 11-34. Optimum Cruise .F404-GE-400 (Sheet 1 of 2) 11-91 . F404-GE-400 (Sheet 2 of 2) 11-92 . Optimum Cruise . .Section XI Part 4 A1-F18AC-NFM-200 Figure 11-34. One Engine Operating . Optimum Cruise .A1-F18AC-NFM-200 Section XI Part 4 Figure 11-35.F404-GE-400 11-93 . 26.Sea Level . Specific Range .000 Pounds .F404-GE-400 11-94 . .Section XI Part 4 A1-F18AC-NFM-200 Figure 11-36. 000 Pounds . Specific Range .Sea Level .F404-GE-400 11-95 .30.A1-F18AC-NFM-200 Section XI Part 4 Figure 11-37. 34. .Sea Level .000 Pounds .Section XI Part 4 A1-F18AC-NFM-200 Figure 11-38. Specific Range .F404-GE-400 11-96 . Sea Level .F404-GE-400 11-97 .38. Specific Range .000 Pounds .A1-F18AC-NFM-200 Section XI Part 4 Figure 11-39. Section XI Part 4 A1-F18AC-NFM-200 Figure 11-40.Sea Level .000 Pounds .42. .F404-GE-400 11-98 . Specific Range . A1-F18AC-NFM-200 Section XI Part 4 Figure 11-41. Specific Range .000 Pounds .46.Sea Level .F404-GE-400 11-99 . Sea Level . Specific Range .50.000 Pounds . .F404-GE-400 11-100 .Section XI Part 4 A1-F18AC-NFM-200 Figure 11-42. 26.F404-GE-400 11-101 .5.000 Pounds . Specific Range .A1-F18AC-NFM-200 Section XI Part 4 Figure 11-43.000 Feet . .5.30.000 Pounds .Section XI Part 4 A1-F18AC-NFM-200 Figure 11-44. Specific Range .F404-GE-400 11-102 .000 Feet . 5.34.A1-F18AC-NFM-200 Section XI Part 4 Figure 11-45.000 Feet .000 Pounds .F404-GE-400 11-103 . Specific Range . 000 Feet .38. .000 Pounds . Specific Range .Section XI Part 4 A1-F18AC-NFM-200 Figure 11-46.5.F404-GE-400 11-104 . Specific Range .F404-GE-400 11-105 .5.A1-F18AC-NFM-200 Section XI Part 4 Figure 11-47.000 Feet .42.000 Pounds . 000 Feet .46. . Specific Range .5.F404-GE-400 11-106 .000 Pounds .Section XI Part 4 A1-F18AC-NFM-200 Figure 11-48. F404-GE-400 11-107 . Specific Range .000 Pounds .50.5.000 Feet .A1-F18AC-NFM-200 Section XI Part 4 Figure 11-49. Section XI Part 4 A1-F18AC-NFM-200 Figure 11-50.26. .10. Specific Range .000 Pounds .F404-GE-400 11-108 .000 Feet . A1-F18AC-NFM-200 Section XI Part 4 Figure 11-51. Specific Range - 10,000 Feet - 30,000 Pounds - F404-GE-400 11-109 Section XI Part 4 A1-F18AC-NFM-200 Figure 11-52. Specific Range - 10,000 Feet - 34,000 Pounds - F404-GE-400 11-110 . A1-F18AC-NFM-200 Section XI Part 4 Figure 11-53. Specific Range - 10,000 Feet - 38,000 Pounds - F404-GE-400 11-111 Section XI Part 4 A1-F18AC-NFM-200 Figure 11-54. Specific Range - 10,000 Feet - 42,000 Pounds - F404-GE-400 11-112 . A1-F18AC-NFM-200 Section XI Part 4 Figure 11-55. Specific Range - 10,000 Feet - 46,000 Pounds - F404-GE-400 11-113 Section XI Part 4 A1-F18AC-NFM-200 Figure 11-56. Specific Range - 10,000 Feet - 50,000 Pounds - F404-GE-400 11-114 . A1-F18AC-NFM-200 Section XI Part 4 Figure 11-57. Specific Range .15.F404-GE-400 11-115 .000 Pounds .26.000 Feet . 000 Feet .Section XI Part 4 A1-F18AC-NFM-200 Figure 11-58.30.15.F404-GE-400 11-116 . Specific Range .000 Pounds . . 000 Pounds .A1-F18AC-NFM-200 Section XI Part 4 Figure 11-59.F404-GE-400 11-117 .000 Feet .34. Specific Range .15. Specific Range .F404-GE-400 11-118 .Section XI Part 4 A1-F18AC-NFM-200 Figure 11-60.38.000 Feet .15.000 Pounds . . 000 Pounds .A1-F18AC-NFM-200 Section XI Part 4 Figure 11-61.15.F404-GE-400 11-119 .000 Feet .42. Specific Range . 000 Pounds .46.Section XI Part 4 A1-F18AC-NFM-200 Figure 11-62. Specific Range . .F404-GE-400 11-120 .000 Feet .15. 50.F404-GE-400 11-121 .000 Pounds .000 Feet .A1-F18AC-NFM-200 Section XI Part 4 Figure 11-63.15. Specific Range . F404-GE-400 11-122 .000 Feet .Section XI Part 4 A1-F18AC-NFM-200 Figure 11-64.26.000 Pounds . .20. Specific Range . 000 Feet . Specific Range .20.A1-F18AC-NFM-200 Section XI Part 4 Figure 11-65.F404-GE-400 11-123 .000 Pounds .30. 000 Feet .000 Pounds .F404-GE-400 11-124 . Specific Range .Section XI Part 4 A1-F18AC-NFM-200 Figure 11-66. .20.34. 000 Pounds .A1-F18AC-NFM-200 Section XI Part 4 Figure 11-67.000 Feet . Specific Range .F404-GE-400 11-125 .20.38. 42.20.F404-GE-400 11-126 . .Section XI Part 4 A1-F18AC-NFM-200 Figure 11-68. Specific Range .000 Pounds .000 Feet . 46.000 Pounds .20.000 Feet .A1-F18AC-NFM-200 Section XI Part 4 Figure 11-69.F404-GE-400 11-127 . Specific Range . 50.000 Feet . . Specific Range .F404-GE-400 11-128 .20.Section XI Part 4 A1-F18AC-NFM-200 Figure 11-70.000 Pounds . 000 Pounds .A1-F18AC-NFM-200 Section XI Part 4 Figure 11-71.25.000 Feet .F404-GE-400 11-129 .26. Specific Range . 000 Feet .Section XI Part 4 A1-F18AC-NFM-200 Figure 11-72. Specific Range .25.F404-GE-400 11-130 .000 Pounds .30. . F404-GE-400 11-131 .000 Feet .A1-F18AC-NFM-200 Section XI Part 4 Figure 11-73.25.34.000 Pounds . Specific Range . 25.000 Feet . .38. Specific Range .Section XI Part 4 A1-F18AC-NFM-200 Figure 11-74.000 Pounds .F404-GE-400 11-132 . 000 Pounds .42.000 Feet .A1-F18AC-NFM-200 Section XI Part 4 Figure 11-75.25. Specific Range .F404-GE-400 11-133 . 25. . Specific Range .000 Feet .F404-GE-400 11-134 .000 Pounds .46.Section XI Part 4 A1-F18AC-NFM-200 Figure 11-76. Specific Range .25.F404-GE-400 11-135 .000 Feet .000 Pounds .A1-F18AC-NFM-200 Section XI Part 4 Figure 11-77.50. F404-GE-400 11-136 .Section XI Part 4 A1-F18AC-NFM-200 Figure 11-78. Specific Range .30.000 Feet .000 Pounds .26. . A1-F18AC-NFM-200 Section XI Part 4 Figure 11-79. Specific Range .000 Feet .F404-GE-400 11-137 .30.30.000 Pounds . 000 Pounds . .30.000 Feet .Section XI Part 4 A1-F18AC-NFM-200 Figure 11-80. Specific Range .F404-GE-400 11-138 .34. 38.000 Pounds .A1-F18AC-NFM-200 Section XI Part 4 Figure 11-81.F404-GE-400 11-139 .000 Feet .30. Specific Range . Section XI Part 4 A1-F18AC-NFM-200 Figure 11-82. . Specific Range .F404-GE-400 11-140 .000 Feet .30.000 Pounds .42. A1-F18AC-NFM-200 Section XI Part 4 Figure 11-83. Specific Range - 30,000 Feet - 46,000 Pounds - F404-GE-400 11-141 Section XI Part 4 A1-F18AC-NFM-200 Figure 11-84. Specific Range - 30,000 Feet - 50,000 Pounds - F404-GE-400 11-142 . A1-F18AC-NFM-200 Section XI Part 4 Figure 11-85. Specific Range - 35,000 Feet - 26,000 Pounds - F404-GE-400 11-143 Section XI Part 4 A1-F18AC-NFM-200 Figure 11-86. Specific Range - 35,000 Feet - 30,000 Pounds - F404-GE-400 11-144 . A1-F18AC-NFM-200 Section XI Part 4 Figure 11-87. Specific Range - 35,000 Feet - 34,000 Pounds - F404-GE-400 11-145 Section XI Part 4 A1-F18AC-NFM-200 Figure 11-88. Specific Range - 35,000 Feet - 38,000 Pounds - F404-GE-400 11-146 . 35.42.A1-F18AC-NFM-200 Section XI Part 4 Figure 11-89. Specific Range .000 Pounds .F404-GE-400 11-147 .000 Feet . 000 Feet .35.46.Section XI Part 4 A1-F18AC-NFM-200 Figure 11-90.F404-GE-400 11-148 . Specific Range . .000 Pounds . F404-GE-400 11-149 . Specific Range .35.000 Pounds .50.000 Feet .A1-F18AC-NFM-200 Section XI Part 4 Figure 11-91. .F404-GE-400 11-150 .26. Specific Range .40.Section XI Part 4 A1-F18AC-NFM-200 Figure 11-92.000 Feet .000 Pounds . A1-F18AC-NFM-200 Section XI Part 4 Figure 11-93.40.F404-GE-400 11-151 .30.000 Pounds . Specific Range .000 Feet . .34.F404-GE-400 11-152 .Section XI Part 4 A1-F18AC-NFM-200 Figure 11-94.40.000 Pounds . Specific Range .000 Feet . A1-F18AC-NFM-200 Section XI Part 4 Figure 11-95.38. Specific Range .40.F404-GE-400 11-153 .000 Feet .000 Pounds . .F404-GE-400 11-154 .000 Pounds .000 Feet .Section XI Part 4 A1-F18AC-NFM-200 Figure 11-96.40. Specific Range .42. 46.F404-GE-400 11-155 . Specific Range .A1-F18AC-NFM-200 Section XI Part 4 Figure 11-97.000 Pounds .40.000 Feet . 45. Specific Range .000 Feet .F404-GE-400 11-156 .000 Pounds .Section XI Part 4 A1-F18AC-NFM-200 Figure 11-98. .26. 000 Pounds .45.A1-F18AC-NFM-200 Section XI Part 4 Figure 11-99.30. Specific Range .F404-GE-400 11-157 .000 Feet . Section XI Part 4 A1-F18AC-NFM-200 Figure 11-100.000 Feet .34. . Specific Range .F404-GE-400 11-158 .000 Pounds .45. Specific Range .F404-GE-400 11-159 .A1-F18AC-NFM-200 Section XI Part 4 Figure 11-101.45.38.000 Feet .000 Pounds . .F404-GE-400 11-160 .26.One Engine Operating . Specific Range .000 Pounds .Sea Level .Section XI Part 4 A1-F18AC-NFM-200 Figure 11-102. 000 Pounds . Specific Range .F404-GE-400 11-161 .A1-F18AC-NFM-200 Section XI Part 4 Figure 11-103.One Engine Operating .30.Sea Level . Sea Level .One Engine Operating . Specific Range .34.Section XI Part 4 A1-F18AC-NFM-200 Figure 11-104. .F404-GE-400 11-162 .000 Pounds . Sea Level .38. Specific Range .A1-F18AC-NFM-200 Section XI Part 4 Figure 11-105.One Engine Operating .F404-GE-400 11-163 .000 Pounds . Sea Level . Specific Range .One Engine Operating . .42.F404-GE-400 11-164 .Section XI Part 4 A1-F18AC-NFM-200 Figure 11-106.000 Pounds . F404-GE-400 11-165 .One Engine Operating .46.A1-F18AC-NFM-200 Section XI Part 4 Figure 11-107.Sea Level .000 Pounds . Specific Range . Sea Level .000 Pounds . Specific Range .Section XI Part 4 A1-F18AC-NFM-200 Figure 11-108.One Engine Operating .F404-GE-400 11-166 .50. . One Engine Operating .000 Feet .000 Pounds .5. Specific Range .A1-F18AC-NFM-200 Section XI Part 4 Figure 11-109.F404-GE-400 11-167 .26. F404-GE-400 11-168 .000 Pounds .Section XI Part 4 A1-F18AC-NFM-200 Figure 11-110. .000 Feet .5.30.One Engine Operating . Specific Range . A1-F18AC-NFM-200 Section XI Part 4 Figure 11-111. Specific Range .000 Pounds .One Engine Operating .000 Feet .F404-GE-400 11-169 .5.34. Section XI Part 4 A1-F18AC-NFM-200 Figure 11-112.000 Feet . Specific Range .38.One Engine Operating .5.F404-GE-400 11-170 . .000 Pounds . 5.F404-GE-400 11-171 .42.A1-F18AC-NFM-200 Section XI Part 4 Figure 11-113.000 Feet . Specific Range .000 Pounds .One Engine Operating . One Engine Operating .000 Feet .000 Pounds .46.F404-GE-400 11-172 . Specific Range .Section XI Part 4 A1-F18AC-NFM-200 Figure 11-114. .5. 000 Feet .50.One Engine Operating .5.F404-GE-400 11-173 .000 Pounds .A1-F18AC-NFM-200 Section XI Part 4 Figure 11-115. Specific Range . 26.One Engine Operating .Section XI Part 4 A1-F18AC-NFM-200 Figure 11-116.10. Specific Range .000 Feet .F404-GE-400 11-174 .000 Pounds . . Specific Range .30.A1-F18AC-NFM-200 Section XI Part 4 Figure 11-117.000 Feet .F404-GE-400 11-175 .One Engine Operating .000 Pounds .10. .Section XI Part 4 A1-F18AC-NFM-200 Figure 11-118.One Engine Operating .000 Pounds .F404-GE-400 11-176 .34.10.000 Feet . Specific Range . F404-GE-400 11-177 .10.38.One Engine Operating . Specific Range .A1-F18AC-NFM-200 Section XI Part 4 Figure 11-119.000 Feet .000 Pounds . 000 Feet .000 Pounds .10.One Engine Operating .42. . Specific Range .F404-GE-400 11-178 .Section XI Part 4 A1-F18AC-NFM-200 Figure 11-120. 10.A1-F18AC-NFM-200 Section XI Part 4 Figure 11-121.000 Pounds .One Engine Operating . Specific Range .46.F404-GE-400 11-179 .000 Feet . 10.50.000 Feet . Specific Range .Section XI Part 4 A1-F18AC-NFM-200 Figure 11-122.One Engine Operating .F404-GE-400 11-180 . .000 Pounds . 000 Pounds .One Engine Operating .F404-GE-400 11-181 .26. Specific Range .000 Feet .15.A1-F18AC-NFM-200 Section XI Part 4 Figure 11-123. Specific Range .One Engine Operating .30.15.Section XI Part 4 A1-F18AC-NFM-200 Figure 11-124.000 Feet . .000 Pounds .F404-GE-400 11-182 . A1-F18AC-NFM-200 Section XI Part 4 Figure 11-125.F404-GE-400 11-183 . Specific Range .000 Pounds .One Engine Operating .15.000 Feet .34. 000 Pounds .Section XI Part 4 A1-F18AC-NFM-200 Figure 11-126.15.F404-GE-400 11-184 .One Engine Operating .000 Feet .38. . Specific Range . 000 Feet .A1-F18AC-NFM-200 Section XI Part 4 Figure 11-127.F404-GE-400 11-185 .15.One Engine Operating .42. Specific Range .000 Pounds . 46.000 Pounds . .000 Feet .One Engine Operating .Section XI Part 4 A1-F18AC-NFM-200 Figure 11-128.15.F404-GE-400 11-186 . Specific Range . 15.F404-GE-400 11-187 . Specific Range .One Engine Operating .50.000 Pounds .000 Feet .A1-F18AC-NFM-200 Section XI Part 4 Figure 11-129. 20.F404-GE-400 11-188 .26.000 Feet . .One Engine Operating . Specific Range .000 Pounds .Section XI Part 4 A1-F18AC-NFM-200 Figure 11-130. 20.F404-GE-400 11-189 .30.One Engine Operating .000 Feet .000 Pounds .A1-F18AC-NFM-200 Section XI Part 4 Figure 11-131. Specific Range . 000 Feet .20.000 Pounds . .Section XI Part 4 A1-F18AC-NFM-200 Figure 11-132.One Engine Operating .34.F404-GE-400 11-190 . Specific Range . F404-GE-400 11-191 .One Engine Operating .000 Pounds . Specific Range .000 Feet .38.20.A1-F18AC-NFM-200 Section XI Part 4 Figure 11-133. 42. .One Engine Operating .F404-GE-400 11-192 .000 Pounds .Section XI Part 4 A1-F18AC-NFM-200 Figure 11-134.20.000 Feet . Specific Range . F404-GE-400 11-193 .A1-F18AC-NFM-200 Section XI Part 4 Figure 11-135.20.46.000 Feet .One Engine Operating .000 Pounds . Specific Range . F404-GE-400 11-194 .000 Feet . .One Engine Operating .Section XI Part 4 A1-F18AC-NFM-200 Figure 11-136. Specific Range .000 Pounds .25.26. 000 Feet .One Engine Operating .30. Specific Range .A1-F18AC-NFM-200 Section XI Part 4 Figure 11-137.000 Pounds .F404-GE-400 11-195 .25. Section XI Part 4 A1-F18AC-NFM-200 Figure 11-138.34.One Engine Operating .000 Pounds .F404-GE-400 11-196 . Specific Range .000 Feet .25. . One Engine Operating .A1-F18AC-NFM-200 Section XI Part 4 Figure 11-139.38. Specific Range .25.000 Feet .000 Pounds .F404-GE-400 11-197 . Section XI Part 4 A1-F18AC-NFM-200 Figure 11-140.One Engine Operating .000 Feet .30.000 Pounds . Specific Range .26.F404-GE-400 11-198 . . 30.30.A1-F18AC-NFM-200 Section XI Part 4 Figure 11-141.F404-GE-400 11-199 .000 Pounds .000 Feet . Specific Range .One Engine Operating . .F404-GE-400 (Sheet 1 of 4) 11-200 .Section XI Part 4 A1-F18AC-NFM-200 Figure 11-142.34.000 Pounds .Stabilized Level Flight . Combat Specific Range . F404-GE-400 (Sheet 2 of 4) 11-201 . Combat Specific Range .Stabilized Level Flight .000 Pounds .A1-F18AC-NFM-200 Section XI Part 4 Figure 11-142.34. Combat Specific Range .000 Pounds .Section XI Part 4 A1-F18AC-NFM-200 Figure 11-142.F404-GE-400 (Sheet 3 of 4) 11-202 .34. .Stabilized Level Flight . 000 Pounds .A1-F18AC-NFM-200 Section XI Part 4 Figure 11-142.F404-GE-400 (Sheet 4 of 4) 11-203 .Stabilized Level Flight . Combat Specific Range .34. 34.000 Pounds .Stabilized Level Flight .F404-GE-400 (Sheet 1 of 4) 11-204 . . Combat Fuel Flow .Section XI Part 4 A1-F18AC-NFM-200 Figure 11-143. 34.Stabilized Level Flight .000 Pounds .A1-F18AC-NFM-200 Section XI Part 4 Figure 11-143.F404-GE-400 (Sheet 2 of 4) 11-205 . Combat Fuel Flow . F404-GE-400 (Sheet 3 of 4) 11-206 .34. Combat Fuel Flow .Section XI Part 4 A1-F18AC-NFM-200 Figure 11-143.000 Pounds . .Stabilized Level Flight . F404-GE-400 (Sheet 4 of 4) 11-207 .Stabilized Level Flight .34.000 Pounds .A1-F18AC-NFM-200 Section XI Part 4 Figure 11-143. Combat Fuel Flow . . Constant Altitude/Long Range Cruise (Sheet 1 of 2) 11-208 .Section XI Part 4 A1-F18AC-NFM-200 Figure 11-144. A1-F18AC-NFM-200 Section XI Part 4 Figure 11-144. Constant Altitude/Long Range Cruise (Sheet 2 of 2) 11-209 . .Section XI Part 4 A1-F18AC-NFM-200 Figure 11-145. Rangewind Correction 11-210 . F404-GE-400 Change 1 11-210A . Headwind Effects on Bingo Fuel .Section XI Part 4 A1-F18AC-NFM-200 Figure 11-145a.Cruise at Best Altitude . Headwind Effects on Bingo Fuel .F404-GE-400 11-210B Change 1 .Section XI Part 4 A1-F18AC-NFM-200 Figure 11-145b. .Cruise at Sea Level . MILITARY THRUST CLIMB TO INDICATED ALTITUDE.120 1.660 3.000 33.S.000 40.940 4.130 2.150 1.000 40.000 258 258 258 258 263 272 280 278 277 278 254 254 253 253 253 258 268 268 269 270 259 259 259 259 258 256 259 260 262 262 243 243 243 242 242 245 248 252 256 254 FUEL GRADE: JP-5 FUEL DENSITY: 6.830 5.760 4.390 2.510 2. 2. 3.570 2.160 3.610 3.000 7.200 1.270 3.980 2.040 4.880 279 279 279 278 278 278 277 277 277 276 275 275 274 274 274 273 273 272 272 272 271 270 270 269 269 268 268 267 267 266 266 265 265 264 264 263 263 262 262 261 43 39 34 30 26 22 17 13 9 4 44 39 35 31 26 22 18 13 9 4 44 40 36 31 27 22 18 13 9 5 45 41 36 32 27 23 18 14 9 5 DATA BASED ON: 1.550 4.26.Section XI Part 4 A1-F18AC-NFM-200 BINGO F404-GE-400 GEAR UP .680 4.330 3.470 2. 5.000 40.020 2.910 2.000 3.000 39.470 3.010 1.400 3.000 18.000 35.580 3.070 1.260 1.8 LB/GAL DESCEND NM FUEL REQD LB TIME REQD MIN 73 73 73 73 71 66 58 44 30 12 65 65 65 65 65 62 51 42 27 5 57 57 57 57 57 56 48 38 25 4 52 52 52 52 52 50 44 35 20 8 3. SEE HEADWIND EFFECTS CHART.860 29 26 24 21 19 16 14 11 8 4 29 26 24 21 19 16 13 11 7 4 28 26 23 21 18 16 13 10 7 4 29 27 24 21 19 16 14 11 8 4 DIST SEA LEVEL CRUISE FUEL SPEED TIME REQD CAS REQD LB KNOTS MIN 4.120 2.000 40.780 3.000 26.090 1.170 3.150 2.990 2.970 2.410 2.280 2.330 2.190 2.670 2.000 Pounds F404-GE-400 (Sheet 1 of 2) Change 2 11-211 .600 2.000 29. 250 KCAS IDLE THRUST DESCENT TO SEA LEVEL (SPEEDBRAKE RETRACTED).000 40.850 5.000 40.710 2.000 17.000 35.000 39. 4.Gear Up .160 1.450 3.000 40.340 2.000 19.000 28.880 3.470 2.820 3.830 2.480 4.850 3.790 3.310 3.000 39.000 39.76 DRAG INDEX 150 COUNTS DRAG INDEX 100 COUNTS DRAG INDEX 50 COUNTS DRAG INDEX 0 COUNTS INBD DIST NM CRUISE SPEED ALT CAS FEET KNOTS 40.330 4. 1962 DATE: 16 NOVEMBER 1989 DATA BASIS: ESTIMATED (BASED ON FLIGHT TEST) 505 KCAS to M E 0.100 3.140 2.000 40. Figure 11-146.000 40.26.86 475 KCAS to M E 0.770 3. FIGURE 11-145.000 40.550 2.000 28.000 37.260 2.850 2.000 40.000 18. FUEL REQUIRED INCLUDES 1500 POUNDS RESERVE FUEL.78 200 180 160 140 120 100 80 60 40 20 200 180 160 140 120 100 80 60 40 20 200 180 160 140 120 100 80 60 40 20 200 180 160 140 120 100 80 60 40 20 CLIMB MACH OR KCAS 330 KCAS to M E 0.000 40.000 40.82 450 KCAS to M E 0.000 40.610 2. Bingo .490 3.310 3. INITIAL ALTITUDE IS SEA LEVEL.090 2. NO WIND.000 40.000 3.800 2.790 2.000 33.960 2.000 40.680 2.000 40.640 2.FLAPS AUTO WEIGHT .970 3.430 2.Flaps Auto .000 POUNDS (WEIGHT E ZERO FUEL WEIGHT) REMARKS ENGINE(S): (2)F404-GE-400 U.260 2.000 7.000 40.720 2.800 4.840 2.430 4. STANDARD DAY.990 2. 070 2.260 3.000 40.000 7.030 3.360 3.000 39.810 3.690 2.000 40.000 7. FIGURE 11-145.75 300 KCAS to M E 0. Bingo .26.000 28.000 38.450 5.420 1.540 3.000 38.720 2.780 4.000 40. INITIAL ALTITUDE IS SEA LEVEL.620 5.000 40.Section XI Part 4 A1-F18AC-NFM-200 BINGO F404-GE-400 GEAR UP . .26.120 3.000 39.910 5.560 4.000 238 238 238 237 237 237 240 246 250 250 232 232 232 231 231 229 236 240 244 245 226 226 226 225 225 225 230 235 238 241 FUEL GRADE: JP-5 FUEL DENSITY: 6.S.390 3.910 4.970 2.370 1.950 3.190 5.880 2.000 POUNDS (WEIGHT E ZERO FUEL WEIGHT) REMARKS ENGINE(S): (2)F404-GE-400 U.72 200 180 160 140 120 100 80 60 40 20 200 180 160 140 120 100 80 60 40 20 200 180 160 140 120 100 80 60 40 20 CLIMB MACH OR KCAS 280 KCAS to M E 0.180 2.000 39. 250 KCAS IDLE THRUST DESCENT TO SEA LEVEL (SPEEDBRAKE RETRACTED).820 3.000 40.520 3.220 3.880 2.750 3.000 34.840 3. 4. 1962 DATE: 16 NOVEMBER 1989 DATA BASIS: ESTIMATED (BASED ON FLIGHT TEST) 320 KCAS to M E 0.230 4. MILITARY THRUST CLIMB TO INDICATED ALTITUDE.Gear Up .910 5.FLAPS AUTO WEIGHT .000 40. SEE HEADWIND EFFECTS CHART.830 2.000 Pounds F404-GE-400 (Sheet 2 of 2) 11-212 Change 2 .8 LB/GAL DESCEND NM FUEL REQD LB TIME REQD MIN 47 47 47 47 47 47 40 31 19 8 43 43 43 43 43 40 35 29 17 7 39 39 39 39 39 37 33 26 16 6 3.200 4. STANDARD DAY.460 3.800 2.000 17.650 3.760 2. 3.070 2.710 5.130 2.000 40.000 34.350 2.000 7.250 1.890 4.940 29 27 24 21 19 16 13 11 8 4 30 27 25 22 19 16 14 11 8 4 31 28 25 23 20 17 14 11 8 5 DIST SEA LEVEL CRUISE FUEL SPEED TIME REQD CAS REQD LB KNOTS MIN 5.000 39.470 2.000 40.000 17.240 2. Figure 11-146.010 4.680 3.530 2.000 35.000 39. FUEL REQUIRED INCLUDES 1500 POUNDS RESERVE FUEL.600 3.300 3. 2.750 4.210 1.000 40.590 2.000 28.310 1.290 1.990 3.68 DRAG INDEX 300 COUNTS DRAG INDEX 250 COUNTS DRAG INDEX 200 COUNTS INBD DIST NM CRUISE SPEED ALT CAS FEET KNOTS 40. NO WIND.280 3.000 40.940 6. 5.000 17.960 262 261 260 260 259 258 258 257 256 256 258 257 256 256 255 254 253 253 252 251 254 253 252 252 251 250 249 248 247 246 46 41 37 32 28 23 19 14 9 5 47 42 37 33 28 24 19 14 10 5 47 43 38 33 29 24 19 15 10 5 DATA BASED ON: 1.000 28.Flaps Auto . 690 2.880 29 26 24 21 19 16 14 11 8 4 29 26 24 21 19 16 13 11 7 4 29 26 24 21 19 16 13 10 7 4 29 26 24 21 19 16 14 11 8 4 DIST SEA LEVEL CRUISE FUEL SPEED TIME REQD CAS REQD LB KNOTS MIN 4.490 3.000 18.870 5.86 475 KCAS to M E 0.760 2.000 40.230 3.000 27.460 3.000 17.000 40.200 2.340 2. Figure 11-147.000 38.470 2. 4.000 14.000 262 262 266 266 271 286 295 297 294 296 256 256 256 261 286 278 288 287 285 285 253 253 253 254 254 269 273 277 278 278 259 259 259 259 258 259 265 267 274 273 FUEL GRADE: JP-5 FUEL DENSITY: 6. SEE HEADWIND EFFECTS CHART.600 2.Gear Up .460 4.820 2.220 4. FIGURE 11-145.400 2.000 18.650 2.920 4.000 3. 1962 DATE: 16 NOVEMBER 1989 DATA BASIS: ESTIMATED (BASED ON FLIGHT TEST) 505 KCAS to M E 0.800 3.960 2.000 40.490 2.000 39. 3.30. STANDARD DAY.970 2.680 2.290 3.76 DRAG INDEX 150 COUNTS DRAG INDEX 100 COUNTS DRAG INDEX 50 COUNTS DRAG INDEX 0 COUNTS INBD DIST NM CRUISE SPEED ALT CAS FEET KNOTS 40.180 1.700 4.120 2.120 1.630 3.310 2.000 40.940 2.000 40.000 36.520 5.610 4.000 40.000 40.860 3. 250 KCAS IDLE THRUST DESCENT TO SEA LEVEL (SPEEDBRAKE RETRACTED).000 24.000 38. MILITARY THRUST CLIMB TO INDICATED ALTITUDE.810 4.150 1.000 37.980 3.000 POUNDS (WEIGHT E ZERO FUEL WEIGHT) REMARKS ENGINE(S): (2)F404-GE-400 U.000 3.050 2.200 1.570 4.78 200 180 160 140 120 100 80 60 40 20 200 180 160 140 120 100 80 60 40 20 200 180 160 140 120 100 80 60 40 20 200 180 160 140 120 100 80 60 40 20 CLIMB MACH OR KCAS 330 KCAS to M E 0.Flaps Auto .S. NO WIND.100 1.000 28.280 3.000 32. 2.000 33.870 3.000 40.000 33.000 32.000 36.970 2.430 2.Section XI Part 4 A1-F18AC-NFM-200 BINGO F404-GE-400 GEAR UP .580 2.280 3.82 450 KCAS to M E 0.900 302 302 301 301 300 299 299 298 297 297 293 292 291 290 289 289 288 287 286 285 282 281 280 280 279 279 279 278 278 277 277 277 276 276 275 275 274 273 273 272 40 36 32 28 24 20 16 12 8 4 41 37 33 29 25 21 17 13 8 4 43 38 34 30 26 22 17 13 9 4 43 39 35 30 26 22 18 13 9 4 DATA BASED ON: 1.480 3.830 3.840 5.430 3.520 2.080 3.110 2.040 1.880 3.000 26.540 3.090 2.30.000 7.230 2.380 2.810 2.540 2. Bingo .710 3.830 4.000 39.230 3. INITIAL ALTITUDE IS SEA LEVEL.000 40.000 3.280 3.230 1. FUEL REQUIRED INCLUDES 1500 POUNDS RESERVE FUEL.000 Pounds F404-GE-400 (Sheet 1 of 2) Change 2 11-213 .000 39.890 2.000 38.670 3.290 1.740 2.000 35.110 4.890 3.000 40.860 2. 5.360 3.000 40.100 2.290 3.000 40.670 3.000 40.690 2.090 2.FLAPS AUTO WEIGHT .8 LB/GAL DESCEND NM FUEL REQD LB TIME REQD MIN 74 74 72 72 69 62 56 42 29 5 66 66 66 64 62 58 50 40 28 5 60 60 60 60 60 52 47 38 25 4 54 54 54 54 51 49 43 36 18 9 3. 68 DRAG INDEX 300 COUNTS DRAG INDEX 250 COUNTS DRAG INDEX 200 COUNTS INBD DIST NM CRUISE SPEED ALT CAS FEET KNOTS 40.000 40.940 2. 5.350 1.640 3.930 4.460 3. 250 KCAS IDLE THRUST DESCENT TO SEA LEVEL (SPEEDBRAKE RETRACTED).120 5.000 2. MILITARY THRUST CLIMB TO INDICATED ALTITUDE.000 38.000 Pounds F404-GE-400 (Sheet 2 of 2) 11-214 Change 2 .470 1.FLAPS AUTO WEIGHT .100 2.300 1.820 5.430 3.180 4.000 39.350 1.000 37.860 2.780 3.960 6. SEE HEADWIND EFFECTS CHART. FIGURE 11-145.950 2. Bingo .000 39.210 3.000 36.440 2.000 POUNDS (WEIGHT E ZERO FUEL WEIGHT) REMARKS ENGINE(S): (2)F404-GE-400 U.000 33.910 4.710 4.930 6.30.000 40.000 36.72 200 180 160 140 120 100 80 60 40 20 200 180 160 140 120 100 80 60 40 20 200 180 160 140 120 100 80 60 40 20 CLIMB MACH OR KCAS 280 KCAS to M E 0.910 4. 2.410 1.000 37.770 2.S. Figure 11-147.000 27. 1962 DATE: 16 NOVEMBER 1989 DATA BASIS: ESTIMATED (BASED ON FLIGHT TEST) 320 KCAS to M E 0.000 39.000 15.000 243 243 243 247 250 253 256 259 266 267 242 242 242 245 245 248 248 254 261 261 240 240 240 240 241 241 243 249 255 255 FUEL GRADE: JP-5 FUEL DENSITY: 6.000 27.860 2. FUEL REQUIRED INCLUDES 1500 POUNDS RESERVE FUEL.000 37.000 14.410 4.050 3.280 4. 3.240 3.000 37.720 3.960 29 27 24 22 19 16 14 11 8 4 30 27 25 22 19 17 14 11 8 4 31 28 25 23 20 17 14 11 8 4 DIST SEA LEVEL CRUISE FUEL SPEED TIME REQD CAS REQD LB KNOTS MIN 5.Section XI Part 4 A1-F18AC-NFM-200 BINGO F404-GE-400 GEAR UP .340 3.000 33.250 1.000 37.780 2.000 36.000 7. STANDARD DAY.070 3.570 3.910 5.8 LB/GAL DESCEND NM FUEL REQD LB TIME REQD MIN 50 50 50 48 47 45 40 32 16 8 45 45 45 43 43 40 37 31 15 7 39 39 39 39 37 37 34 27 15 7 4.210 2.000 7. .000 7.410 5.070 3.640 3.000 14.240 3.Flaps Auto .420 3.000 39.930 3. INITIAL ALTITUDE IS SEA LEVEL.Gear Up .650 5.600 2.75 300 KCAS to M E 0.500 4.980 274 273 272 272 271 270 270 269 269 268 270 269 268 268 267 266 266 265 265 264 266 265 265 264 263 262 262 261 260 260 44 40 35 31 27 22 18 13 9 4 45 40 36 31 27 23 18 14 9 5 45 41 36 32 27 23 18 14 9 5 DATA BASED ON: 1.980 3.320 2.810 3.30.210 2.000 38. NO WIND.000 33.000 28.000 38.510 4.860 3.670 2. 4.540 2.380 4.940 4. 46 220 KCAS to M E 0.580 5.770 5. 1962 DATE: 16 NOVEMBER 1989 DATA BASIS: ESTIMATED (BASED ON FLIGHT TEST) 225 KCAS to M E 0.440 2.230 5.000 28.830 2.000 33.740 3.070 2.360 7.600 2.910 7.960 2.100 3.000 19.010 2.140 8.000 32.000 30.750 4.930 6.000 4.000 18.000 34.HALF FLAPS WEIGHT .540 4.700 2.130 6.000 27.240 6.640 4.000 33.640 6.000 33.850 3. STANDARD DAY.000 32.790 2.020 4.940 3.570 5.000 7.350 3. NO WIND.000 5.100 7.000 33.460 4.310 2.000 30.000 18.200 4.390 5. SEE HEADWIND EFFECTS CHART.440 6.120 8.370 2.280 4.110 5.680 7.000 27.400 5.000 32.920 3.26.000 33.310 2.130 2. MILITARY THRUST CLIMB TO INDICATED ALTITUDE 3.000 30. Bingo .690 2.540 3.380 3.000 32.140 7. 250 KCAS IDLE THRUST DESCENT TO SEA LEVEL (SPEEDBRAKE RETRACTED) 4.000 27.170 3.000 198 198 198 198 198 198 198 197 197 200 192 193 194 194 195 195 196 195 194 197 187 187 187 187 187 187 191 190 192 194 196 194 192 190 189 187 186 186 190 191 FUEL GRADE: JP-5 FUEL DENSITY: 6.010 3.47 225 KCAS to M E 0.460 3.580 5.750 6.650 2.850 4.000 30.000 18.000 32.000 7.000 30.360 5.000 7.000 Pounds F404-GE-400 (Sheet 1 of 2) Change 2 11-215 .500 2.090 5.080 5.570 2.26.000 32.780 5.410 4.660 3.670 4.000 7.Section XI Part 4 A1-F18AC-NFM-200 BINGO F404-GE-400 GEAR UP .000 30.160 38 34 31 27 24 20 16 13 9 5 39 35 32 28 24 20 17 13 9 5 40 37 33 29 25 21 17 13 9 5 40 37 33 29 25 21 18 13 10 6 DIST SEA LEVEL CRUISE FUEL SPEED TIME REQD CAS REQD LB KNOTS MIN 7.330 3.000 30.S.170 4.530 3.000 29.43 DRAG INDEX 150 COUNTS DRAG INDEX 100 COUNTS DRAG INDEX 50 COUNTS DRAG INDEX 0 COUNTS INBD DIST NM CRUISE SPEED ALT CAS FEET KNOTS 34.000 30.000 34.000 32.000 30.8 LB/GAL DESCEND NM FUEL REQD LB TIME REQD MIN 22 22 22 22 22 20 19 17 11 4 20 20 20 20 20 20 18 16 11 4 18 18 18 18 18 18 17 15 10 4 16 16 16 16 16 16 15 14 9 4 5.090 3.150 4. Figure 11-148.46 200 180 160 140 120 100 80 60 40 20 200 180 160 140 120 100 80 60 40 20 200 180 160 140 120 100 80 60 40 20 200 180 160 140 120 100 80 60 40 20 CLIMB MACH OR KCAS 210 KCAS to M E 0.000 34.990 3.830 4.170 207 207 206 206 205 205 204 204 203 203 206 205 204 204 203 203 202 202 201 201 204 203 202 202 201 201 200 200 199 199 202 201 200 200 199 199 198 198 197 197 58 52 47 41 35 29 24 18 12 6 58 53 47 41 35 30 24 18 12 6 59 53 47 42 36 30 24 18 12 6 60 54 48 42 36 30 24 18 12 6 DATA BASED ON: 1.Gear Up .230 3. INITIAL ALTITUDE IS SEA LEVEL 2.Half Flaps .000 POUNDS (WEIGHT E ZERO FUEL WEIGHT) REMARKS ENGINE(S): (2)F404-GE-400 U.000 33.610 4. FIGURE 11-145. FUEL REQUIRED INCLUDES 1500 POUNDS RESERVE FUEL 5.920 5.750 2.000 34.040 6.760 4. 260 3.520 5. FIGURE 11-145.560 2.300 4.000 3.160 4.880 4.240 2. Bingo .26.000 30.S.000 30.340 3.440 6.290 2.560 4.210 3.Section XI Part 4 A1-F18AC-NFM-200 BINGO F404-GE-400 GEAR UP .190 8.000 30.000 30.Gear Up . STANDARD DAY.000 30.000 27.000 30.770 2.450 5. INITIAL ALTITUDE IS SEA LEVEL 2.26.800 2.180 2.000 30.720 2.000 7.000 POUNDS (WEIGHT E ZERO FUEL WEIGHT) REMARKS ENGINE(S): (2)F404-GE-400 U. FUEL REQUIRED INCLUDES 1500 POUNDS RESERVE FUEL 5.000 194 192 189 187 184 182 181 181 187 189 175 173 173 174 174 174 175 176 184 188 172 171 171 171 171 171 172 173 180 185 FUEL GRADE: JP-5 FUEL DENSITY: 6.680 2.030 3.120 4.HALF FLAPS WEIGHT .Half Flaps .910 5.810 8.230 199 199 198 198 197 197 196 195 195 194 197 197 196 196 195 194 194 193 192 192 195 194 194 194 193 192 192 191 190 190 60 54 48 43 37 31 25 18 12 6 61 55 49 43 37 31 25 19 12 6 62 56 49 43 37 31 25 19 13 6 DATA BASED ON: 1.610 3. Figure 11-148.180 6.030 7.370 5.450 4.210 9.000 30.000 26.790 5.000 18.000 18.870 2.690 3.000 30.050 5.730 5.270 6.43 200 180 160 140 120 100 80 60 40 20 200 180 160 140 120 100 80 60 40 20 200 180 160 140 120 100 80 60 40 20 CLIMB MACH OR KCAS 200 KCAS to ME0.530 7.660 4.000 29.840 7.220 41 37 33 30 26 22 18 14 10 6 44 40 36 31 27 22 18 14 10 6 45 40 36 32 27 23 19 14 10 6 DIST SEA LEVEL CRUISE FUEL SPEED TIME REQD CAS REQD LB KNOTS MIN 8.230 7.42 DRAG INDEX 300 COUNTS DRAG INDEX 250 COUNTS DRAG INDEX 200 COUNTS INBD DIST NM CRUISE SPEED ALT CAS FEET KNOTS 30.120 3.580 5.000 30.020 8.360 5.420 3.000 29.000 26.000 4.960 4.950 2. MILITARY THRUST CLIMB TO INDICATED ALTITUDE 3.520 6.000 30.000 Pounds F404-GE-400 (Sheet 2 of 2) 11-216 Change 2 .750 3.060 4.910 2. NO WIND.000 30. 1962 DATE: 16 NOVEMBER 1989 DATA BASIS: ESTIMATED (BASED ON FLIGHT TEST) 210 KCAS to ME0.000 18.000 30.000 3.670 5.000 30. .900 5.000 30.200 6.000 29. 250 KCAS IDLE THRUST DESCENT TO SEA LEVEL (SPEEDBRAKE RETRACTED) 4.620 2.000 30.660 4.43 200 KCAS to ME0.8 LB/GAL DESCEND NM FUEL REQD LB TIME REQD MIN 15 15 15 15 15 15 15 14 9 3 15 15 15 15 15 15 14 13 9 1 14 14 14 14 14 14 13 12 8 1 6.170 5.000 30. SEE HEADWIND EFFECTS CHART.100 6. 000 24.000 29.000 29.030 5.30.000 30.Gear Up .250 3.000 30.060 3.000 4.090 4.040 4.810 5.550 3.000 28.860 3.830 8.46 200 180 160 140 120 100 80 60 40 20 200 180 160 140 120 100 80 60 40 20 200 180 160 140 120 100 80 60 40 20 200 180 160 140 120 100 80 60 40 20 CLIMB MACH OR KCAS 210 KCAS to ME0.390 4.670 4.000 18.000 Pounds F404-GE-400 (Sheet 1 of 2) Change 2 11-217 .860 2.000 29.000 30.8 LB/GAL DESCEND NM FUEL REQD LB TIME REQD MIN 21 21 21 21 21 21 19 18 11 3 20 20 20 20 20 19 18 17 12 3 18 18 18 18 18 18 17 15 10 2 17 17 17 17 17 17 15 13 10 2 5.620 5.000 28. NO WIND.080 3.070 2.000 17.30.000 30.960 3.920 6.770 2.330 7.640 2.000 4.000 30.840 7. FIGURE 11-145.130 2.580 7.680 2.200 226 225 224 222 220 219 217 215 213 212 224 222 221 219 217 215 213 212 210 209 221 219 217 216 214 212 211 209 208 207 217 215 213 212 210 208 207 206 205 204 53 48 43 38 33 27 22 17 11 6 54 49 44 38 33 28 23 17 11 6 54 49 44 39 34 28 23 17 12 6 55 50 45 40 34 29 23 17 12 6 DATA BASED ON: 1. STANDARD DAY.Section XI Part 4 A1-F18AC-NFM-200 BINGO F404-GE-400 GEAR UP .000 30.060 5.Half Flaps . MILITARY THRUST CLIMB TO INDICATED ALTITUDE 3.000 28.S.780 4.250 2.470 3.000 28.000 22.47 225 KCAS to ME0.000 29.260 5.840 5.000 28.720 3.930 4.730 4.160 3.000 POUNDS (WEIGHT E ZERO FUEL WEIGHT) REMARKS ENGINE(S): (2)F404-GE-400 U.820 2.000 29.000 29.490 2.770 2.000 30.000 211 210 209 208 207 206 207 207 206 213 208 207 206 206 205 205 206 206 205 211 207 206 205 205 204 203 204 204 202 208 202 201 201 201 201 201 202 202 201 206 FUEL GRADE: JP-5 FUEL DENSITY: 6.000 4. 250 KCAS IDLE THRUST DESCENT TO SEA LEVEL (SPEEDBRAKE RETRACTED) 4.640 4. 1962 DATE: 16 NOVEMBER 1989 DATA BASIS: ESTIMATED (BASED ON FLIGHT TEST) 225 KCAS to ME0.630 3.000 28.810 5.000 17.000 27.080 7. Bingo . Figure 11-149.000 28.46 220 KCAS to ME0.180 8. SEE HEADWIND EFFECTS CHART.140 6.000 26.180 3.620 6.HALF FLAPS WEIGHT .220 5.530 4.560 5.190 38 35 31 27 24 20 16 13 9 5 39 35 31 28 24 20 17 13 9 5 39 36 32 28 24 21 17 13 9 5 41 37 33 29 25 21 17 13 9 5 DIST SEA LEVEL CRUISE FUEL SPEED TIME REQD CAS REQD LB KNOTS MIN 8.000 4.510 6. FUEL REQUIRED INCLUDES 1500 POUNDS RESERVE FUEL 5.000 29.960 4.390 5.070 4.440 5.43 DRAG INDEX 150 COUNTS DRAG INDEX 100 COUNTS DRAG INDEX 50 COUNTS DRAG INDEX 0 COUNTS INBD DIST NM CRUISE SPEED ALT CAS FEET KNOTS 30.000 26.000 18.550 2.000 30.070 7.000 26.840 4.310 6.370 3.000 30.160 8.630 4.190 2.000 27.140 8.720 2. INITIAL ALTITUDE IS SEA LEVEL 2.730 6.370 4.250 3.340 3.420 2.040 5.000 30.400 6.170 6.910 2.560 5.120 6.120 6.490 4.200 4.620 2. 690 2.000 26.400 4.170 6.490 3.000 28.000 26.330 8.42 DRAG INDEX 300 COUNTS DRAG INDEX 250 COUNTS DRAG INDEX 200 COUNTS INBD DIST NM CRUISE SPEED ALT CAS FEET KNOTS 28.000 3.390 3.000 198 199 199 199 198 198 200 201 198 203 192 193 194 195 195 196 198 199 196 201 189 190 191 191 191 192 192 196 194 198 FUEL GRADE: JP-5 FUEL DENSITY: 6.950 2.000 17.450 2.880 6.740 4. SEE HEADWIND EFFECTS CHART.000 23.220 9.Half Flaps .750 2.510 7.900 3.000 26.430 5.870 7.690 6.710 5.720 7.310 2.710 6.000 27.000 26.Gear Up .040 6.540 5.30.950 6.860 2.520 3.810 3.190 4. Bingo .800 2.000 26. NO WIND.620 6.390 2.000 26.220 5.080 8.500 6.000 27.000 POUNDS (WEIGHT E ZERO FUEL WEIGHT) REMARKS ENGINE(S): (2)F404-GE-400 U.080 5.30.030 2.410 4.890 4.900 2. .300 4.43 200 KCAS to ME0.000 27.000 22. INITIAL ALTITUDE IS SEA LEVEL 2.260 41 37 33 29 25 21 17 13 10 6 43 39 34 30 26 22 18 14 10 6 44 40 35 31 27 22 18 14 10 6 DIST SEA LEVEL CRUISE FUEL SPEED TIME REQD CAS REQD LB KNOTS MIN 9.000 26.990 2.000 Pounds F404-GE-400 (Sheet 2 of 2) 11-218 Change 2 .000 27.260 213 211 210 208 206 205 204 203 202 201 209 207 206 204 203 202 201 200 199 198 206 204 202 201 200 199 198 197 197 196 56 51 46 40 35 29 24 18 12 6 57 52 47 41 35 30 24 18 12 6 58 53 47 42 36 30 24 18 12 6 DATA BASED ON: 1.8 LB/GAL DESCEND NM FUEL REQD LB TIME REQD MIN 16 16 16 16 16 16 15 13 9 2 15 15 15 15 15 15 14 12 9 2 13 13 13 13 13 13 13 11 9 2 6. Figure 11-149.000 27. MILITARY THRUST CLIMB TO INDICATED ALTITUDE 3.570 8.S. FIGURE 11-145.000 28.000 26.240 7. STANDARD DAY.000 26.240 9.010 4.000 28.000 27.000 3.910 5. 1962 DATE: 16 NOVEMBER 1989 DATA BASIS: ESTIMATED (BASED ON FLIGHT TEST) 210 KCAS to ME0.610 3.210 6.790 3.43 200 180 160 140 120 100 80 60 40 20 200 180 160 140 120 100 80 60 40 20 200 180 160 140 120 100 80 60 40 20 CLIMB MACH OR KCAS 200 KCAS to ME0.080 5.270 3.720 5.220 4.000 4.000 17.000 22.970 3. 250 KCAS IDLE THRUST DESCENT TO SEA LEVEL (SPEEDBRAKE RETRACTED) 4.290 7.430 3. FUEL REQUIRED INCLUDES 1500 POUNDS RESERVE FUEL 5.950 5.210 5.000 28.Section XI Part 4 A1-F18AC-NFM-200 BINGO F404-GE-400 GEAR UP .HALF FLAPS WEIGHT .000 28.000 17. 490 4.420 4.000 33.110 5.26.450 2.000 28.320 2.510 6.52 220 KCAS to ME0.780 4.000 201 200 199 198 197 198 199 201 201 207 198 198 197 196 195 195 195 197 197 203 194 194 193 193 192 193 192 194 194 200 186 186 187 187 188 188 190 191 191 197 FUEL GRADE: JP-5 FUEL DENSITY: 6.630 2.090 6.000 7.300 2.000 32. 1962 DATE: 16 NOVEMBER 1989 DATA BASIS: ESTIMATED (BASED ON FLIGHT TEST) 220 KCAS to ME0.310 4. SEE HEADWIND EFFECTS CHART.000 27.890 6.630 3.600 2.000 32.950 2.130 8.430 5.970 3.FLAPS AUTO WEIGHT .000 30.080 7.960 5.000 27.000 18.26.Section XI Part 4 A1-F18AC-NFM-200 BINGO F404-GE-400 GEAR DOWN .070 5.100 7.000 32.040 4.360 3.070 3.000 33.660 4.840 3.440 4.810 3.050 2.8 LB/GAL DESCEND NM FUEL REQD LB TIME REQD MIN 24 24 24 24 24 23 22 19 12 4 21 21 21 21 21 21 20 18 11 4 20 20 20 20 20 19 19 16 10 4 18 18 18 18 18 18 17 15 10 4 5.450 3.230 2. 250 KCAS IDLE THRUST DESCENT TO SEA LEVEL (SPEEDBRAKE RETRACTED) 4.760 7. FIGURE 11-145.550 3.130 37 33 30 27 23 20 16 12 9 5 38 34 31 27 23 20 16 13 9 5 39 35 31 27 24 20 16 13 9 5 40 36 32 29 25 21 17 13 9 5 DIST SEA LEVEL CRUISE FUEL SPEED TIME REQD CAS REQD LB KNOTS MIN 7.860 3.Flaps Auto .810 4.000 32.000 34.000 18.110 3.000 35.020 3.000 33.930 3.770 4.140 4.380 2.000 32.120 5. STANDARD DAY.47 DRAG INDEX 150 COUNTS DRAG INDEX 100 COUNTS DRAG INDEX 50 COUNTS DRAG INDEX 0 COUNTS INBD DIST NM CRUISE SPEED ALT CAS FEET KNOTS 35.000 32.000 POUNDS (WEIGHT E ZERO FUEL WEIGHT) REMARKS ENGINE(S): (2)F404-GE-400 U.800 5.310 3.090 5.000 2.180 3.000 32.330 4.140 4.940 7. INITIAL ALTITUDE IS SEA LEVEL 2.650 4.000 33.000 18.720 3.000 33. Bingo .800 6.000 7.000 35.900 2.670 2.000 33.720 5.000 33.170 4.000 32.990 4. Figure 11-150.000 28.S.560 4.000 35. MILITARY THRUST CLIMB TO INDICATED ALTITUDE 3.000 35.000 33.560 2.000 32.250 2.440 3.650 5.520 2. FUEL REQUIRED INCLUDES 1500 POUNDS RESERVE FUEL 5.150 218 217 216 215 214 213 212 211 210 209 204 209 213 212 211 210 210 209 208 207 212 211 211 210 209 208 207 206 205 204 210 209 209 208 207 206 205 204 203 202 55 50 45 39 34 28 23 17 11 6 59 52 45 40 34 29 23 17 12 6 57 51 46 40 34 29 23 17 12 6 57 52 46 40 35 29 23 18 12 6 DATA BASED ON: 1.940 4. NO WIND.280 6.180 3.710 2.170 7.000 33.000 Pounds F404-GE-400 (Sheet 1 of 2) Change 2 11-219 .50 200 180 160 140 120 100 80 60 40 20 200 180 160 140 120 100 80 60 40 20 200 180 160 140 120 100 80 60 40 20 200 180 160 140 120 100 80 60 40 20 CLIMB MACH OR KCAS 220 KCAS to ME0.000 7.000 33.620 5.000 7.000 18.790 2.000 32.340 4.000 33.510 5.270 5.480 6.Gear Down .51 220 KCAS to ME0.750 2.430 3. 970 6.950 4.620 7.170 6.000 POUNDS (WEIGHT E ZERO FUEL WEIGHT) REMARKS ENGINE(S): (2)F404-GE-400 U. SEE HEADWIND EFFECTS CHART.150 6.880 4.880 7. STANDARD DAY.S.290 3.880 2.670 5.000 30.26.000 30.580 5.990 3.680 6.390 4. MILITARY THRUST CLIMB TO INDICATED ALTITUDE 3.840 5.400 7.000 189 189 188 188 188 187 188 188 189 194 187 187 187 186 186 185 186 186 188 192 186 185 185 184 184 183 184 184 186 190 FUEL GRADE: JP-5 FUEL DENSITY: 6.000 6.840 2.FLAPS AUTO WEIGHT .240 4.570 4.700 4.510 2.000 30.220 2.510 4.570 2.Section XI Part 4 A1-F18AC-NFM-200 BINGO F404-GE-400 GEAR DOWN .000 30.750 2. INITIAL ALTITUDE IS SEA LEVEL 2.170 8.900 3.000 30.Gear Down .710 2.510 5.210 208 207 206 206 205 204 203 201 200 199 205 205 204 203 202 201 200 199 198 196 203 202 201 201 199 198 197 196 195 194 58 52 47 41 35 29 24 18 12 6 58 53 47 41 36 30 24 18 12 6 59 53 48 42 36 30 24 18 12 6 DATA BASED ON: 1.500 3.000 30.000 19. 1962 DATE: 16 NOVEMBER 1989 DATA BASIS: ESTIMATED (BASED ON FLIGHT TEST) 220 KCAS to ME0.990 4.000 29.45 220 KCAS to ME0.160 2.Flaps Auto . Bingo .670 2.000 30.190 3.000 30.000 30. 250 KCAS IDLE THRUST DESCENT TO SEA LEVEL (SPEEDBRAKE RETRACTED) 4.080 3.44 DRAG INDEX 300 COUNTS DRAG INDEX 250 COUNTS DRAG INDEX 200 COUNTS INBD DIST NM CRUISE SPEED ALT CAS FEET KNOTS 30.000 30.270 5.400 3.000 18.000 Pounds F404-GE-400 (Sheet 2 of 2) 11-220 Change 2 . FUEL REQUIRED INCLUDES 1500 POUNDS RESERVE FUEL 5.000 30.100 5.920 5.280 5.650 3. .000 30.830 5.000 30. FIGURE 11-145.330 6.000 6.090 4.100 4.820 4.000 19.640 2.920 2.000 26.000 30.280 3.100 2.150 6.26.190 8.000 30.580 3.080 7.000 29.45 200 180 160 140 120 100 80 60 40 20 200 180 160 140 120 100 80 60 40 20 200 180 160 140 120 100 80 60 40 20 CLIMB MACH OR KCAS 220 KCAS to ME0.000 30.000 27.850 8. NO WIND. Figure 11-150.000 29.000 30.360 3.190 41 37 33 29 25 21 17 13 9 6 41 37 33 29 25 21 17 13 10 6 42 38 34 30 26 22 18 13 10 6 DIST SEA LEVEL CRUISE FUEL SPEED TIME REQD CAS REQD LB KNOTS MIN 8.8 LB/GAL DESCEND NM FUEL REQD LB TIME REQD MIN 16 16 16 16 16 16 16 14 10 3 15 15 15 15 15 15 15 14 9 3 15 15 15 15 15 15 14 13 9 3 5.000 27.700 4.000 6.420 5. 570 2.000 19.470 4. 250 KCAS IDLE THRUST DESCENT TO SEA LEVEL (SPEEDBRAKE RETRACTED).050 1.740 4.300 2.000 20.160 1.800 4.000 17.630 2. Bingo .930 2.870 2.940 3.000 Pounds F404-GE-400 (Sheet 1 of 2) Change 2 11-221 .730 2.70 200 180 160 140 120 100 80 60 40 20 200 180 160 140 120 100 80 60 40 20 200 180 160 140 120 100 80 60 40 20 200 180 160 140 120 100 80 60 40 20 CLIMB MACH OR KCAS 290 KCAS to M E 0.040 1.Flaps Auto .130 3.200 3. 3.090 1.000 8.000 9.000 23.150 1.040 3.680 3.000 20.520 3.000 30.780 3.790 4.000 21.000 14.730 2.490 3.000 30.Section XI Part 4 A1-F18AC-NFM-200 BINGO F404-GE-400 ONE ENGINE OPERATING GEAR UP .26.770 2.280 2.000 3.310 3.000 28.000 18.800 4.330 3.560 3.8 LB/GAL DESCEND NM FUEL REQD LB TIME REQD MIN 52 52 52 48 43 33 27 21 13 6 41 41 41 37 31 30 23 17 12 4 28 28 28 27 26 22 21 16 10 4 22 22 22 22 21 19 18 14 9 3 3.770 4.100 2.000 20.000 30.000 22.000 13.210 3. 5.210 1.370 4.75 310 KCAS to M E 0.70 DRAG INDEX 150 COUNTS DRAG INDEX 100 COUNTS DRAG INDEX 50 COUNTS DRAG INDEX 0 COUNTS INBD DIST NM ENGINE(S): (2)F404-GE-400 U.S.000 9.Gear Up .000 13. STANDARD DAY.000 23.560 2.590 3.FLAPS AUTO WEIGHT . 2.000 23.000 33.460 3.820 5.000 1.000 275 275 274 273 272 268 266 264 264 264 263 263 262 262 261 260 258 258 257 257 254 254 253 253 253 253 252 252 251 252 248 248 247 247 247 247 246 246 245 247 FUEL GRADE: JP-5 FUEL DENSITY: 6.000 3.000 17.120 2.000 31.780 3.110 1. INITIAL ALTITUDE IS SEA LEVEL. SEE HEADWIND EFFECTS CHART.70 300 KCAS to M E 0.300 4.260 3.850 271 271 270 270 269 269 269 268 268 267 266 265 265 264 264 263 263 262 262 261 260 260 259 258 258 257 257 256 256 255 255 255 254 253 252 251 250 250 249 248 44 40 36 31 27 22 18 13 9 4 45 41 36 32 27 23 18 14 9 5 46 42 37 33 28 23 19 14 9 5 47 42 38 33 29 24 19 14 10 5 DATA BASED ON: 1. MILITARY THRUST CLIMB TO INDICATED ALTITUDE.210 2.410 2.930 2. 4.000 33.450 2.000 27.990 2. FIGURE 11-145.890 3.000 8.000 13.One Engine Operating .380 3.230 3.480 2.000 22.000 17. FUEL REQUIRED INCLUDES 1500 POUNDS RESERVE FUEL.26.110 4.000 3. Figure 11-151. NO WIND.500 4.640 3.000 3.800 3.520 2.920 2.600 2.370 2.290 2.800 2.840 31 28 25 23 20 18 15 12 8 4 32 29 26 23 21 18 15 12 8 4 34 31 27 24 21 18 15 12 8 4 36 33 29 25 22 19 15 12 9 5 DIST SEA LEVEL CRUISE FUEL SPEED TIME REQD CAS REQD LB KNOTS MIN 4.000 POUNDS (WEIGHT E ZERO FUEL WEIGHT) REMARKS DATE: 16 NOVEMBER 1989 DATA BASIS: ESTIMATED (BASED ON FLIGHT TEST) 315 KCAS to M E 0.840 2.130 2.000 2.000 20.390 2.000 4.130 2. 1962 INOPERATIVE ENGINE WINDMILLING CRUISE SPEED ALT CAS FEET KNOTS 33.690 2.660 3.000 16.820 4.290 2.000 18.000 3.760 3.080 2.000 22.000 23.390 3. 830 4.260 1.100 4.180 3.730 2.000 18.26.000 4. 250 KCAS IDLE THRUST DESCENT TO SEA LEVEL (SPEEDBRAKE RETRACTED).400 3.000 17. 3.120 2.700 3.000 POUNDS (WEIGHT E ZERO FUEL WEIGHT) REMARKS DATE: 16 NOVEMBER 1989 DATA BASIS: ESTIMATED (BASED ON FLIGHT TEST) 275 KCAS to M E 0.250 2.000 18.500 4.70 200 180 160 140 120 100 80 60 40 20 200 180 160 140 120 100 80 60 40 20 200 180 160 140 120 100 80 60 40 20 CLIMB MACH OR KCAS 240 KCAS to M E 0.830 2.410 5.000 17. INITIAL ALTITUDE IS SEA LEVEL.000 17.420 3. 2.390 4.000 13.S. FUEL REQUIRED INCLUDES 1500 POUNDS RESERVE FUEL.150 3.740 4.320 1.000 18.000 9.600 2.810 3.030 2.210 1.Flaps Auto .680 2.860 3.000 17.000 18.240 2. MILITARY THRUST CLIMB TO INDICATED ALTITUDE. 4.400 3.600 4.000 3.Section XI Part 4 A1-F18AC-NFM-200 BINGO F404-GE-400 ONE ENGINE OPERATING GEAR UP . .000 16.870 4. NO WIND.70 DRAG INDEX 300 COUNTS DRAG INDEX 250 COUNTS DRAG INDEX 200 COUNTS INBD DIST NM ENGINE(S): (2)F404-GE-400 U.8 LB/GAL DESCEND NM FUEL REQD LB TIME REQD MIN 19 19 19 19 18 17 16 13 8 3 17 17 17 17 17 17 16 12 8 3 15 15 15 15 15 15 15 12 8 3 4. FIGURE 11-145.000 Pounds F404-GE-400 (Sheet 2 of 2) 11-222 Change 2 .000 19.050 3.140 2.550 4.900 5.000 17.000 17.020 2.530 2.000 3. STANDARD DAY.600 4.000 13.000 9.060 4.320 1.000 19.Gear Up .970 3.000 18.910 5.690 3.000 14.880 5.360 3.560 3.930 250 250 249 248 247 246 245 245 244 243 246 245 244 244 243 242 241 240 239 238 241 240 240 239 238 237 236 235 234 233 48 43 39 34 29 24 20 15 10 5 49 44 39 35 30 25 20 15 10 5 50 45 40 35 30 25 20 15 10 5 DATA BASED ON: 1.550 3.26. 1962 INOPERATIVE ENGINE WINDMILLING CRUISE SPEED ALT CAS FEET KNOTS 19.000 19.FLAPS AUTO WEIGHT .810 2.000 8.210 3.000 18.260 3.One Engine Operating .000 17.930 38 34 30 26 23 19 16 12 9 5 39 35 32 28 24 20 16 13 9 5 41 37 33 29 25 21 17 13 9 5 DIST SEA LEVEL CRUISE FUEL SPEED TIME REQD CAS REQD LB KNOTS MIN 5.980 3.260 4.690 5.980 5.700 3. SEE HEADWIND EFFECTS CHART.70 260 KCAS to M E 0.000 17.820 4. Bingo . Figure 11-151.260 1.000 242 241 241 240 240 240 239 239 240 242 236 236 235 234 234 233 233 234 235 237 232 231 231 230 229 229 228 228 230 232 FUEL GRADE: JP-5 FUEL DENSITY: 6.920 2.000 3.000 18.000 17.370 1. 5.510 5.650 2. 000 28. 2.380 4.680 3.970 2.000 17.960 3.Flaps Auto .000 30.050 2.000 19.000 22.250 1.700 4.000 8.840 4.090 1.940 4.000 POUNDS (WEIGHT E ZERO FUEL WEIGHT) REMARKS DATE: 16 NOVEMBER 1989 DATA BASIS: ESTIMATED (BASED ON FLIGHT TEST) 315 KCAS to M E 0.000 8.660 4.040 3.000 19. 1962 INOPERATIVE ENGINE WINDMILLING CRUISE SPEED ALT CAS FEET KNOTS 30.680 3.870 2.220 2.250 3.000 19.Gear Up .220 2.150 1.350 2.000 21.560 3.070 1.780 4.090 3.030 1.870 31 28 26 23 20 17 14 11 8 4 32 29 26 23 20 18 15 11 8 4 34 31 27 24 21 18 15 12 8 4 35 32 29 25 22 18 15 12 8 4 DIST SEA LEVEL CRUISE FUEL SPEED TIME REQD CAS REQD LB KNOTS MIN 4.000 3.71 300 KCAS to M E 0.000 12.780 3.010 2.880 287 286 285 285 284 283 283 282 282 281 278 278 277 277 276 276 275 275 274 274 274 273 273 272 271 271 270 270 269 269 270 269 268 268 267 266 266 265 264 264 42 38 34 30 25 21 17 13 9 4 43 39 35 30 26 22 17 13 9 4 44 40 35 31 27 22 18 13 9 4 45 40 36 31 27 23 18 14 9 5 DATA BASED ON: 1.700 2.000 24.390 3.000 18.640 2. MILITARY THRUST CLIMB TO INDICATED ALTITUDE.000 9. 5.430 2.000 13.080 2.000 19.780 3.S.800 3.630 2.440 2.890 3.30.000 21.590 2.550 4.720 3.000 26.000 13.680 2.000 29.70 200 180 160 140 120 100 80 60 40 20 200 180 160 140 120 100 80 60 40 20 200 180 160 140 120 100 80 60 40 20 200 180 160 140 120 100 80 60 40 20 CLIMB MACH OR KCAS 290 KCAS to M E 0.520 2.000 21.300 3.000 18. FUEL REQUIRED INCLUDES 1500 POUNDS RESERVE FUEL.000 19.810 4.170 3.470 3.940 3.8 LB/GAL DESCEND NM FUEL REQD LB TIME REQD MIN 48 48 46 44 36 33 28 20 12 5 37 37 37 34 31 27 24 18 13 4 27 27 27 27 24 23 20 17 10 4 22 22 22 22 21 20 19 14 9 3 3. Figure 11-152.FLAPS AUTO WEIGHT .000 16.840 5.200 1.220 3. 250 KCAS IDLE THRUST DESCENT TO SEA LEVEL (SPEEDBRAKE RETRACTED).810 5. 3. NO WIND.540 2.000 19.000 23. STANDARD DAY.970 3.190 1.890 2.720 3.000 3.30.000 13.260 3.000 8.000 21. INITIAL ALTITUDE IS SEA LEVEL.000 26.220 3.70 DRAG INDEX 150 COUNTS DRAG INDEX 100 COUNTS DRAG INDEX 50 COUNTS DRAG INDEX 0 COUNTS INBD DIST NM ENGINE(S): (2)F404-GE-400 U.040 2.One Engine Operating .130 1.590 3.000 295 294 293 293 288 285 284 283 282 281 278 277 277 279 278 277 277 277 276 275 272 271 271 271 270 270 270 270 270 269 264 264 263 263 263 262 262 263 264 263 FUEL GRADE: JP-5 FUEL DENSITY: 6.400 3.75 310 KCAS to M E 0.340 4.020 4.000 21.000 26. SEE HEADWIND EFFECTS CHART. Bingo .000 3.820 2.110 2. 4. FIGURE 11-145.400 3.510 3.000 Pounds F404-GE-400 (Sheet 1 of 2) Change 2 11-223 .390 3.480 2.760 2.260 2.000 18.240 2.370 4.000 16.820 2.000 17.350 2.Section XI Part 4 A1-F18AC-NFM-200 BINGO F404-GE-400 ONE ENGINE OPERATING GEAR UP .930 2.530 4.000 3.470 3. 790 5. STANDARD DAY.000 8.260 1.800 4.000 14.210 3.000 15.500 5. 2.690 2.860 4.Section XI Part 4 A1-F18AC-NFM-200 BINGO F404-GE-400 ONE ENGINE OPERATING GEAR UP .000 Pounds F404-GE-400 (Sheet 2 of 2) 11-224 Change 2 .000 14.130 2.930 6.120 4. INITIAL ALTITUDE IS SEA LEVEL.700 3.960 5.000 259 259 258 258 257 257 257 258 257 256 253 253 252 252 251 250 250 250 250 251 248 247 246 246 245 245 244 244 244 246 FUEL GRADE: JP-5 FUEL DENSITY: 6.930 2.590 4. FIGURE 11-145.530 4.550 3.920 5.190 4.110 3. .600 2.000 17.000 14.830 4.000 12.310 1. 5.000 15.890 5.900 5. SEE HEADWIND EFFECTS CHART.000 17.940 3. Figure 11-152.250 2. Bingo .S.570 3.050 4.550 3.000 8.000 14.960 37 34 30 26 23 19 16 12 8 4 39 35 32 28 24 20 16 13 9 5 41 37 33 29 25 21 17 13 9 5 DIST SEA LEVEL CRUISE FUEL SPEED TIME REQD CAS REQD LB KNOTS MIN 5. 3.810 2.890 3.000 14.230 4.30. . MILITARY THRUST CLIMB TO INDICATED ALTITUDE.960 265 264 263 262 262 261 260 260 259 258 259 259 258 257 257 256 255 254 254 253 254 253 252 251 250 250 250 248 247 247 45 41 37 32 28 23 18 14 9 5 46 42 37 33 28 23 19 14 9 5 47 43 38 33 29 24 19 15 10 5 DATA BASED ON: 1.000 8.380 1.650 5. FUEL REQUIRED INCLUDES 1500 POUNDS RESERVE FUEL.8 LB/GAL DESCEND NM FUEL REQD LB TIME REQD MIN 18 18 18 18 18 18 18 13 9 3 15 15 15 15 15 15 14 12 8 3 13 13 13 13 13 13 13 11 7 3 4.70 200 180 160 140 120 100 80 60 40 20 200 180 160 140 120 100 80 60 40 20 200 180 160 140 120 100 80 60 40 20 CLIMB MACH OR KCAS 240 KCAS to M E 0.140 3.000 14.000 12.250 2. 1962 INOPERATIVE ENGINE WINDMILLING CRUISE SPEED ALT CAS FEET KNOTS 17.170 2.000 14.000 17.70 DRAG INDEX 300 COUNTS DRAG INDEX 250 COUNTS DRAG INDEX 200 COUNTS INBD DIST NM ENGINE(S): (2)F404-GE-400 U. 4.320 1.000 15. 250 KCAS IDLE THRUST DESCENT TO SEA LEVEL (SPEEDBRAKE RETRACTED).400 3.520 5.750 3.370 2.730 4.000 17.Gear Up .850 3.FLAPS AUTO WEIGHT .000 15.000 3.040 2.70 260 KCAS to M E 0.810 4.900 2.000 15. NO WIND.780 2.720 2.370 1.Flaps Auto .470 4.280 5.000 POUNDS (WEIGHT E ZERO FUEL WEIGHT) REMARKS DATE: 16 NOVEMBER 1989 DATA BASIS: ESTIMATED (BASED ON FLIGHT TEST) 275 KCAS to M E 0.330 3.960 3.000 14.330 3.430 1.000 17.000 14.000 12.380 3.30.One Engine Operating .000 3.000 3.000 15.300 4. 000 10.120 7.000 7.680 2.800 3.930 7. INITIAL ALTITUDE IS SEA LEVEL.690 2.630 3.HALF FLAPS WEIGHT .290 2.000 13.33 DRAG INDEX 150 COUNTS DRAG INDEX 100 COUNTS DRAG INDEX 50 COUNTS DRAG INDEX 0 COUNTS INBD DIST NM ENGINE(S): (2)F404-GE-400 U. 2.930 6.000 11.000 13.860 6. SEE HEADWIND EFFECTS CHART.490 3.650 6.250 3.000 12.910 3.Section XI Part 4 A1-F18AC-NFM-200 BINGO F404-GE-400 ONE ENGINE OPERATING GEAR UP .080 3.070 7.840 5.000 10.130 4.080 5.090 7.Gear Up .000 10.000 13.570 5.000 11. 5.S.120 8. 3.140 2.640 3.8 LB/GAL DESCEND NM FUEL REQD LB TIME REQD MIN 7 7 7 7 7 7 7 6 4 1 7 7 7 7 7 7 6 5 4 1 6 6 6 6 6 6 5 5 4 1 5 5 5 5 5 5 5 4 3 0 6.660 5.790 6.340 2.760 6.090 7.32 175 KCAS to ME0. FIGURE 11-145.380 5.550 6.470 6.780 4.900 3.270 4.Half Flaps .070 5.140 4.000 13.270 6.630 2.180 7.000 1.260 5.000 13.380 3.930 4.780 2.One Engine Operating .000 13.580 4.410 4.180 5.000 7.730 3.640 4.380 5.000 11.000 11.000 1.830 3.360 2.640 2.26.000 11.000 10.070 6.140 198 198 197 197 196 196 195 195 194 194 196 195 195 194 194 193 193 192 192 191 193 193 193 192 191 191 190 190 189 188 191 191 190 190 189 188 187 187 186 185 61 55 49 43 37 31 25 18 12 6 61 55 49 43 37 31 25 19 13 6 62 56 50 44 38 31 25 19 13 6 63 57 50 44 38 32 26 19 13 6 DATA BASED ON: 1. STANDARD DAY.210 2.310 4.430 6.140 3.280 2. MILITARY THRUST CLIMB TO INDICATED ALTITUDE. 250 KCAS IDLE THRUST DESCENT TO SEA LEVEL (SPEEDBRAKE RETRACTED).000 7.000 1.760 2.32 175 KCAS to ME0.160 5. Figure 11-153.490 4.740 2.920 5.32 175 KCAS to ME0.220 2.000 10. 4.000 13.000 1.140 52 47 42 37 32 27 22 17 12 6 54 48 43 38 32 27 22 17 12 6 57 51 45 39 34 28 23 18 12 6 58 52 46 40 35 29 23 18 12 6 DIST SEA LEVEL CRUISE FUEL SPEED TIME REQD CAS REQD LB KNOTS MIN 7.980 4.000 7.000 13.000 10.000 11. 1962 INOPERATIVE ENGINE WINDMILLING CRUISE SPEED ALT CAS FEET KNOTS 13.250 6.680 7.000 10.640 5.720 2.990 3.26.680 6.070 4.000 Pounds F404-GE-400 (Sheet 1 of 2) Change 2 11-225 .000 13.740 4.430 2.000 10. NO WIND.000 13.000 10.000 POUNDS (WEIGHT E ZERO FUEL WEIGHT) REMARKS DATE: 16 NOVEMBER 1989 DATA BASIS: ESTIMATED (BASED ON FLIGHT TEST) 200 180 160 140 120 100 80 60 40 20 200 180 160 140 120 100 80 60 40 20 200 180 160 140 120 100 80 60 40 20 200 180 160 140 120 100 80 60 40 20 CLIMB MACH OR KCAS 175 KCAS to ME0.000 10.000 13.390 3.000 9.000 11.750 5.020 6.000 9. FUEL REQUIRED INCLUDES 1500 POUNDS RESERVE FUEL.510 3.000 197 197 197 197 197 197 195 190 189 193 192 193 194 194 195 195 191 188 186 190 186 186 186 186 186 186 186 185 184 187 184 183 183 183 183 183 183 182 181 184 FUEL GRADE: JP-5 FUEL DENSITY: 6. Bingo . Figure 11-153.190 8.000 Pounds F404-GE-400 (Sheet 2 of 2) 11-226 Change 2 . .000 6.000 1.860 4.640 2.110 3.550 4.000 8.S. 2. FUEL REQUIRED INCLUDES 1500 POUNDS RESERVE FUEL.000 9.120 4.640 6. INITIAL ALTITUDE IS SEA LEVEL.510 5.000 9.690 6.380 3.26.410 5.Half Flaps .000 189 189 191 190 190 190 190 187 180 188 188 190 190 190 190 190 190 186 177 167 175 168 166 166 168 171 174 175 172 168 FUEL GRADE: JP-5 FUEL DENSITY: 6.000 6.26.000 9. 3.020 3.490 2.140 7.750 4.250 5. 5.870 5.000 9.120 7.000 9.500 7.510 2.000 1.31 160 KCAS to ME0.000 9.200 57 52 45 40 34 29 23 18 12 6 59 52 46 41 35 29 24 18 13 7 64 58 51 45 38 32 25 19 13 7 DIST SEA LEVEL CRUISE FUEL SPEED TIME REQD CAS REQD LB KNOTS MIN 8.32 DRAG INDEX 300 COUNTS DRAG INDEX 250 COUNTS DRAG INDEX 200 COUNTS INBD DIST NM ENGINE(S): (2)F404-GE-400 U.270 3.200 5.000 9.000 9.000 9. .31 175 KCAS to ME0.000 9.190 8.520 4. MILITARY THRUST CLIMB TO INDICATED ALTITUDE. 250 KCAS IDLE THRUST DESCENT TO SEA LEVEL (SPEEDBRAKE RETRACTED).540 2.890 6.000 8.880 2. STANDARD DAY.610 5.810 2.890 8.210 6.240 4.860 5. Bingo .970 4.900 7.000 9.000 6.960 6.000 9.390 4. 1962 INOPERATIVE ENGINE WINDMILLING CRUISE SPEED ALT CAS FEET KNOTS 9.570 2.860 2.000 1.200 189 189 188 188 187 187 188 192 193 193 187 186 186 186 185 184 181 175 169 165 184 187 192 198 188 176 165 165 165 167 64 57 51 45 39 33 26 19 13 6 64 58 52 45 39 33 27 21 14 7 65 58 50 42 38 34 29 22 15 7 DATA BASED ON: 1.690 4.000 9. NO WIND.670 7.380 6.HALF FLAPS WEIGHT .Section XI Part 4 A1-F18AC-NFM-200 BINGO F404-GE-400 ONE ENGINE OPERATING GEAR UP .000 9.000 POUNDS (WEIGHT E ZERO FUEL WEIGHT) REMARKS DATE: 16 NOVEMBER 1989 DATA BASIS: ESTIMATED (BASED ON FLIGHT TEST) 200 180 160 140 120 100 80 60 40 20 200 180 160 140 120 100 80 60 40 20 200 180 160 140 120 100 80 60 40 20 CLIMB MACH OR KCAS 160 KCAS to ME0.170 8.190 3.150 6.160 8.040 5.000 9.840 2.850 4.000 9.360 6.Gear Up . 4.000 9.920 2.One Engine Operating .630 4.890 2.410 2.000 9.180 3. FIGURE 11-145.710 6.000 8.430 7.000 9.880 7.000 9.8 LB/GAL DESCEND NM FUEL REQD LB TIME REQD MIN 4 4 4 4 4 4 4 4 3 0 4 4 4 4 4 4 4 4 3 0 4 4 4 4 4 4 4 3 3 0 7. SEE HEADWIND EFFECTS CHART. 000 197 195 195 194 194 193 193 194 191 193 195 194 194 195 196 197 198 195 193 195 194 194 195 193 192 190 189 189 190 192 193 190 189 188 188 187 186 185 188 189 FUEL GRADE: JP-5 FUEL DENSITY: 6.460 5.000 2.000 14.Section XI Part 4 A1-F18AC-NFM-200 BINGO F404-GE-400 ONE ENGINE OPERATING GEAR DOWN .500 6.000 12.260 6.800 3.000 12.310 2.550 3. 5.230 3.590 4.320 4.980 5.180 4. SEE HEADWIND EFFECTS CHART.000 11.020 3. NO WIND.650 2.000 7.050 6.000 12.440 3.760 7.050 7.060 5.390 4.640 6.050 5.000 Pounds F404-GE-400 (Sheet 1 of 2) Change 2 11-227 .000 11. FUEL REQUIRED INCLUDES 1500 POUNDS RESERVE FUEL.Gear Down .000 11.000 13.FLAPS AUTO WEIGHT .970 3.330 6.400 5.000 11.000 12.960 6.000 13.140 5.920 3.31 200 KCAS to ME0.850 5.000 8.360 3.040 2. 3. STANDARD DAY.000 12.000 12.030 4.000 7. Figure 11-154.250 6.880 4.730 3. 4.670 6.600 5.Flaps Auto . 1962 INOPERATIVE ENGINE WINDMILLING CRUISE SPEED ALT CAS FEET KNOTS 14.000 2.380 2.700 2.120 206 205 204 204 203 202 201 200 200 199 204 203 202 201 200 199 198 198 197 196 202 201 200 199 198 197 196 195 194 193 200 199 197 196 195 194 193 192 191 190 58 53 47 41 36 30 24 18 12 6 59 53 48 42 36 30 24 18 12 6 60 54 48 42 36 31 25 18 12 6 60 54 49 43 37 31 25 19 13 6 DATA BASED ON: 1.070 6.640 5.000 14.650 5.000 11. FIGURE 11-145.610 2.300 3.170 2.610 3.650 5.300 4.000 14.000 12.070 7.880 6. Bingo .090 7.110 6.710 3.810 5.480 4.26.090 4.190 2.8 LB/GAL DESCEND NM FUEL REQD LB TIME REQD MIN 8 8 8 8 8 8 8 7 5 1 7 7 7 7 7 7 7 7 4 1 7 7 7 7 7 7 7 6 4 1 6 6 6 6 6 6 6 6 4 1 6.110 51 46 41 36 31 26 21 16 11 6 52 47 42 36 31 26 21 16 11 6 53 48 43 38 33 27 22 17 11 6 55 50 44 39 33 28 23 17 12 6 DIST SEA LEVEL CRUISE FUEL SPEED TIME REQD CAS REQD LB KNOTS MIN 7.000 13.250 5.670 4.700 2.610 2.400 5.000 11.760 4.650 2.000 11.000 14.000 14.910 4.26.S.110 2. 250 KCAS IDLE THRUST DESCENT TO SEA LEVEL (SPEEDBRAKE RETRACTED).35 DRAG INDEX 150 COUNTS DRAG INDEX 100 COUNTS DRAG INDEX 50 COUNTS DRAG INDEX 0 COUNTS INBD DIST NM ENGINE(S): (2)F404-GE-400 U.100 3.510 3.34 200 KCAS to ME0.000 2.740 2.000 7.000 13.000 12.260 2.000 2.920 4.570 2. INITIAL ALTITUDE IS SEA LEVEL.100 8.240 2.000 11.000 POUNDS (WEIGHT E ZERO FUEL WEIGHT) REMARKS DATE: 16 NOVEMBER 1989 DATA BASIS: ESTIMATED (BASED ON FLIGHT TEST) 200 180 160 140 120 100 80 60 40 20 200 180 160 140 120 100 80 60 40 20 200 180 160 140 120 100 80 60 40 20 200 180 160 140 120 100 80 60 40 20 CLIMB MACH OR KCAS 195 KCAS to ME0.000 12.830 3. MILITARY THRUST CLIMB TO INDICATED ALTITUDE.000 13.000 14.000 13.870 5.000 13.31 200 KCAS to ME0.430 3.One Engine Operating .460 4. 2.010 7.000 11. .050 6.450 2. INITIAL ALTITUDE IS SEA LEVEL.000 8. 3.000 7.870 6. Bingo .640 5. 1962 INOPERATIVE ENGINE WINDMILLING CRUISE SPEED ALT CAS FEET KNOTS 11.320 5.000 9.440 4.160 8.Flaps Auto .470 3.200 3.000 9.000 8.780 4.850 6.770 6.510 2.8 LB/GAL DESCEND NM FUEL REQD LB TIME REQD MIN 5 5 5 5 5 5 5 4 3 1 4 4 4 4 4 4 4 4 3 1 4 4 4 4 4 4 4 3 2 0 7.490 5.560 6.000 8.290 7.490 5. 4. 250 KCAS IDLE THRUST DESCENT TO SEA LEVEL (SPEEDBRAKE RETRACTED).220 6.000 11.790 2. FIGURE 11-145.230 4.000 7. MILITARY THRUST CLIMB TO INDICATED ALTITUDE.750 5.780 4.000 6.000 9. 2.850 2.900 4.610 4.470 4.740 2.880 7.Section XI Part 4 A1-F18AC-NFM-200 BINGO F404-GE-400 ONE ENGINE OPERATING GEAR DOWN .000 2.000 9.000 4.000 9.100 5.590 2.160 8.000 Pounds F404-GE-400 (Sheet 2 of 2) 11-228 Change 2 .050 4.140 8. 5.000 11.31 INBD DIST NM ENGINE(S): (2)F404-GE-400 U.000 9.520 7.240 6.000 9.000 2.000 189 187 187 184 183 182 182 184 185 186 188 186 185 184 184 183 182 183 184 181 188 189 191 191 189 184 179 178 180 169 FUEL GRADE: JP-5 FUEL DENSITY: 6. NO WIND.Gear Down .000 8.850 5.26.760 8.31 180 KCAS to ME0.000 9.790 2.000 11.000 8.890 2.000 8. STANDARD DAY.000 11.130 3.110 3.830 2. SEE HEADWIND EFFECTS CHART.000 7.31 195 KCAS to ME0.000 8.490 2.000 1.610 4.S.One Engine Operating .000 11.26.190 56 51 45 40 34 28 23 17 12 6 58 53 46 41 35 29 24 18 12 6 60 53 46 41 35 30 25 19 13 7 DIST SEA LEVEL CRUISE FUEL SPEED TIME REQD CAS REQD LB KNOTS MIN 8.020 4.190 198 197 195 194 192 191 190 188 187 186 196 195 193 192 190 188 187 185 184 180 194 193 191 190 188 186 183 176 169 165 61 55 49 43 37 31 25 19 13 6 61 56 50 44 38 32 26 19 13 7 62 56 50 44 38 32 26 20 14 7 DATA BASED ON: 1. FUEL REQUIRED INCLUDES 1500 POUNDS RESERVE FUEL.530 6.000 POUNDS (WEIGHT E ZERO FUEL WEIGHT) REMARKS DATE: 16 NOVEMBER 1989 DATA BASIS: ESTIMATED (BASED ON FLIGHT TEST) DRAG INDEX 300 COUNTS DRAG INDEX 250 COUNTS DRAG INDEX 200 COUNTS 200 180 160 140 120 100 80 60 40 20 200 180 160 140 120 100 80 60 40 20 200 180 160 140 120 100 80 60 40 20 CLIMB MACH OR KCAS 165 KCAS to ME0. Figure 11-154.270 7.530 6.000 11.160 5.FLAPS AUTO WEIGHT .890 3.780 7.260 5.000 3.000 8.300 3.140 7.400 2.330 2. ........... Sample Problem A..... Drag index C. 11-232 Maximum Endurance One Engine Operating ..... USE MAXIMUM ENDURANCE ALTITUDE ..A1-F18AC-NFM-200 Section XI Part 5 PART 5 . 50 +10°C 30..... 11-229 ... Effective gross weight B..... Mach number and airspeed. 11-235 MAXIMUM ENDURANCE CHARTS Maximum endurance charts (figures 11-155 and 11-156) are provided for both two-engine and single engine operation.. Project horizontally left to read maximum endurance altitude.ENDURANCE F404-GE-400 TABLE OF CONTENTS CHARTS Maximum Endurance ..000 feet.Enter the chart with the effective gross weight and project up to the appropriate drag index curve...... and fuel required for various drag indexes at all gross weights and altitudes from sea level to 40.....800 Ft................ Included are separate charts for maximum endurance altitude..... Temperature deviation from standard day D.. Maximum endurance altitude 38.. then horizontally left to the temperature baseline and parallel the appropriate temperature deviation guideline to the correct temperature deviation.000 Lb. fuel flow.. 000 Ft. 20° 32. .Enter the chart with the average gross weight and follow the nearest guideline down to the desired bank angle. From this point.663 35. Endurance altitude I. Mach number H.000 Lb. then horizontally right to the appropriate drag index curve. Endurance altitude F. 11-230 Sample Problem A. then horizontally left to find the maximum corresponding endurance calibrated airspeed. Drag index E. Effective gross weight D. Average gross weight B. To find calibrated airspeed. Drag Index G. From the point. 50 35. 50 0.000 Ft.000 Lb. project vertically down to determine effective gross weight. project vertically up from the Mach number to the endurance altitude. project vertically (up or down) to intersect the optimum endurance at the appropriate drag index line or desired altitude. .Section XI Part 5 A1-F18AC-NFM-200 MACH NUMBER AND AIRSPEED . With the effective gross weight. Bank angle C. Calibrated airspeed 30. project vertically up to read maximum endurance Mach number. 220 Kt. From this point. Effective gross weight B. From this point. Section XI Part 5 Sample Problem A.A1-F18AC-NFM-200 FUEL FLOW AND FUEL REQUIRED . Endurance altitude E. Fuel required 32.Enter the chart with the effective gross weight and project vertically up to intersect the desired altitude for endurance. then horizontally right to the appropriate drag index curve. Temperature deviation from standard day F.550 PPH 100 Min 5. then vertically down to read fuel required.000 Lb. continue to project horizontally left to intersect the desired endurance time. project vertically down to the appropriate altitude. Fuel flow G. To find fuel required. then horizontally left to the temperature baseline and parallel the appropriate temperature deviation guideline to the correct temperature deviation. 11-231 . 100 35.000 Ft.920 Lb. project horizontally left to read fuel flow in pounds per hour. Drag index D. Endurance altitude C. -10°C 3. Endurance time H.000 Ft. 35. F404-GE-400 (Sheet 1 of 3) 11-232 .Section XI Part 5 A1-F18AC-NFM-200 Figure 11-155. Maximum Endurance . . Maximum Endurance .F404-GE-400 (Sheet 2 of 3) 11-233 .A1-F18AC-NFM-200 Section XI Part 5 Figure 11-155. Maximum Endurance . .Section XI Part 5 A1-F18AC-NFM-200 Figure 11-155.F404-GE-400 (Sheet 3 of 3) 11-234 . F404-GE-400 (Sheet 1 of 3) 11-235 .One Engine Operating . Maximum Endurance .A1-F18AC-NFM-200 Section XI Part 5 Figure 11-156. One Engine Operating .F404-GE-400 (Sheet 2 of 3) 11-236 . Maximum Endurance . .Section XI Part 5 A1-F18AC-NFM-200 Figure 11-156. F404-GE-400 (Sheet 3 of 3) 11-237 .A1-F18AC-NFM-200 Section XI Part 5 Figure 11-156. Maximum Endurance .One Engine Operating . Section XI Part 6 A1-F18AC-NFM-200 PART 6 . .INFLIGHT REFUELING F404-GE-400 To be supplied. 11-238 . Sample Problem A...... Included are separate charts for two-engine and single engine operation at various drag indexes.. then vertically down to read the corresponding descent Mach number. Maximum Range Descent .........000 Ft.. Optimum cruise altitudes are also depicted on the time... USE DESCENT SPEED ...... Maximum Range Descent One Engine Operating ......DESCENT F404-GE-400 TABLE OF CONTENTS Charts Normal Descent .... Descent Mach number 35. and distance data for a normal descent with speed brake retracted... and distance charts...... A descent speed of 250 KCAS is used.A1-F18AC-NFM-200 Section XI Part 7 PART 7 . If the cruise speed before descent is below 250 KCAS......Enter the chart with the pressure altitude at start of descent and project horizontally right to the 250 KCAS curve....... Normal descent speed C..................... maintain and descend at the cruise Mach number until 250 KCAS is reached................ time. 11-242 11-246 11-250 11-254 NORMAL DESCENT CHARTS These charts (figures 11-157 and 11-158) provide speed.......... 250 KCAS 0... fuel required.. Pressure altitude B.. descend at the cruise Mach until 250 KCAS is reached........ fuel... When cruise speed is below 250 KCAS... Normal Descent One Engine Operating ........74 11-239 ............ then horizontally left to the temperature baseline and follow the appropriate temperature deviation guideline to the appropriate temperature deviation. fuel.Presentation of these charts are identical. From this point. Sample Problem A. Distance 11-240 34. Temperature deviation from standard day E.Section XI Part 7 A1-F18AC-NFM-200 TIME. Enter the appropriate chart with the initial gross weight at start of descent and project horizontally right to intersect the pressure altitude at the start of descent. AND DISTANCE REQUIRED . From this point project horizontally left to read time. therefore.000 Lb. 50 +10°C 11.000 Ft. 61 NM . Time F. 35. they are used in the same manner. project vertically down to the appropriate drag index curve. Drag index D. Initial gross weight B. and distance required during descent. Fuel required G. . 292 Lb. Pressure altitude C. FUEL.1 Min. 285 Lb. If the cruise airspeed before descent is below the descent airspeed. Enter the appropriate chart with the initial gross weight at start of descent and project horizontally right to intersect the pressure altitude at the start of descent. 200 210 KCAS 11-241 . and distance required during descent. 48 NM Enter the chart with the initial descent gross weight and project horizontally right to the appropriate drag index curve and then vertically down to read the corresponding descent calibrated airspeed.000 Lb. Optimum cruise altitudes are also depicted on the time. Distance 35. 30. descend at the cruise Mach until the maximum range descent airspeed is reached. 100 10. Initial Descent Gross Weight B. fuel. FUEL. From this point. Maximum Range Descent Calibrated Airspeed 35. USE DESCENT SPEED TIME. Fuel required F. then horizontally left to read time. therefore. Initial Gross Weight B.Section XI Part 7 A1-F18AC-NFM-200 MAXIMUM RANGE DESCENT CHARTS These charts (figures 11-159 thru 11-160) provide speed. fuel required. Included are separate charts for two-engine and single engine operation at various drag indexes. and distance charts. project vertically down to the appropriate drag index curve. Sample Problem A. fuel. Drag Index C. Sample Problem A. Time E. and distance data for a maximum range descent at idle thrust with speedbrake retracted. maintain and descend at the cruise Mach number until the descent airspeed is reached. Pressure Altitude C.000 Ft. they are used in the same manner. Drag Index D. AND DISTANCE REQUIRED Presentation of these charts are identical.000 Lb. When cruise airspeed is below maximum descent airspeed.5 Min. time. F404-GE-400 (Sheet 1 of 4) 11-242 . . Normal Descent .Section XI Part 7 A1-F18AC-NFM-200 Figure 11-157. F404-GE-400 (Sheet 2 of 4) 11-243 . Normal Descent .A1-F18AC-NFM-200 Section XI Part 7 Figure 11-157. Section XI Part 7 A1-F18AC-NFM-200 Figure 11-157. .F404-GE-400 (Sheet 3 of 4) 11-244 . Normal Descent . F404-GE-400 (Sheet 4 of 4) 11-245 .A1-F18AC-NFM-200 Section XI Part 7 Figure 11-157. Normal Descent . Section XI Part 7 A1-F18AC-NFM-200 Figure 11-158.F404-GE-400 (Sheet 1 of 4) 11-246 .One Engine Operating . Normal Descent . . Normal Descent .F404-GE-400 (Sheet 2 of 4) 11-247 .A1-F18AC-NFM-200 Section XI Part 7 Figure 11-158.One Engine Operating . F404-GE-400 (Sheet 3 of 4) 11-248 .One Engine Operating . .Section XI Part 7 A1-F18AC-NFM-200 Figure 11-158. Normal Descent . One Engine Operating .F404-GE-400 (Sheet 4 of 4) 11-249 .A1-F18AC-NFM-200 Section XI Part 7 Figure 11-158. Normal Descent . . Maximum Range Descent .F404-GE-400 (Sheet 1 of 4) 11-250 .Section XI Part 7 A1-F18AC-NFM-200 Figure 11-159. A1-F18AC-NFM-200 Section XI Part 7 Figure 11-159. Maximum Range Descent - F404-GE-400 (Sheet 2 of 4) 11-251 Section XI Part 7 A1-F18AC-NFM-200 Figure 11-159. Maximum Range Descent - F404-GE-400 (Sheet 3 of 4) 11-252 . A1-F18AC-NFM-200 Section XI Part 7 Figure 11-159. Maximum Range Descent - F404-GE-400 (Sheet 4 of 4) 11-253 Section XI Part 7 A1-F18AC-NFM-200 Figure 11-160. Maximum Range Descent - One Engine Operating - F404-GE-400 (Sheet 1 of 4) 11-254 . A1-F18AC-NFM-200 Section XI Part 7 Figure 11-160. Maximum Range Descent - One Engine Operating - F404-GE-400 (Sheet 2 of 4) 11-255 Section XI Part 7 A1-F18AC-NFM-200 Figure 11-160. Maximum Range Descent - One Engine Operating - F404-GE-400 (Sheet 3 of 4) 11-256 . One Engine Operating . Maximum Range Descent .A1-F18AC-NFM-200 Section XI Part 7 Figure 11-160.F404-GE-400 (Sheet 4 of 4) 11-257 . .LANDING F404-GE-400 TABLE OF CONTENTS Charts Landing Approach Speed ..... From this point...1° AOA A. USE Enter the chart at the estimated landing gross weight and project vertically up to the appropriate flap deflection curve.. Recommended approach speed 32.. 11-258 Sample Problem Configuration: Full flaps...............1° AOA).. 8..Section XI Part 8 A1-F18AC-NFM-200 PART 8 .. AOA curve C............ in addition to three curves for landing configurations with various flight control failures..000 Lb... ..... ... 11-260 Landing Distance.... project horizontally left to read recommended approach speed....... The chart contains two curves for normal landing configurations (full and half flaps at 8.1° 135 Kt. Estimated landing gross weight B.. 11-261 LANDING APPROACH SPEED CHART The landing approach speed chart (figure 11-161) provides recommended approach speeds for various gross weights and landing configurations... Full flaps...... 8...... project vertically down to the wind baseline. Gross weight 32. −4° glide slope) (G + 720) 11-259 .420 3. gross weight and effective wind are taken into consideration. pressure altitude.000 Lb. Sample Problem A. Effective headwind 10 Kt.700 2. Variables of temperature. no stores) on the landing approach speed chart. Parallel the nearest guideline down to the effective headwind or tailwind.400 G. Increase landing ground rolls by 1. Then project horizontally to read the landing ground roll for dry or wet runway.700 4. Total Distance to clear 50 Ft.98 B. From this point. Wind baseline D. Runway condition Dry Wet Dry Wet G.A1-F18AC-NFM-200 Section XI Part 8 LANDING DISTANCE CHART This chart (figure 11-162) provides landing roll distance information for a dry hard runway and for various gross weights on a wet runway.100 6. add 720 feet for a −4° glide slope with no flare. Landing distance (Ft.120 (no flare. Obstacle 4. The data are for a normal landing using full anti-skid braking. or add 1200 feet with flare. Density ratio 0. To determine total distance required from a height of 50 feet. USE Enter the chart with the prevailing density ratio and project horizontally right to intersect the appropriate gross weight curve.) 4.5° glide slope with no flare.420 5.2% for each knot that the approach speed exceeds that shown (25% CG. E. add 820 feet for a −3. Flaps Half Full F. C. From this point project vertically down to read flap setting (half or full).820 7. . Landing Approach Speed .Section XI Part 8 A1-F18AC-NFM-200 Figure 11-161.F404-GE-400 11-260 . Landing Distance .A1-F18AC-NFM-200 Section XI Part 8 Figure 11-162.F404-GE-400 11-261 . .... Load factor is also included for each bank angle........ Bank angle C. constant speed turn....... Load factor D..... 60° 2. Rate of turn 11-262 420 Kt............................. Turn data is available for various speeds and bank angles...................... 11-265 11-266 11-274 11-275 11-285 11-290 11-297 TURN CAPABILITIES CHART This chart (figure 11-163) presents the radius of turn and the rate of turn for a constant altitude....... note the load factor and then proceed vertically downward to read the rate of turn...... Rate of Turn A................ Medium Altitude .0 G 4............ Bank angle C.. 60° 2................... Radius of Turn 420 Kt..... USE Enter the radius of turn plot with the true airspeed.......MISSION PLANNING F404-GE-400 TABLE OF CONTENTS Charts Turn Capabilities. Proceed horizontally to the right to the bank angle..Section XI Part 9 A1-F18AC-NFM-200 PART 9 ....... Low Altitude Acceleration........ Level Flight Envelope..... True airspeed B..5°/sec .. Maximum Thrust Acceleration Low Altitude . Enter the rate of turn plot with the true airspeed.. ...................... Proceed horizontally to the right to the desired bank angle........ Load factor D........... Note the load factor..0 G 9000 Ft................. High Altitude ............ Dive Recovery ....................... Sample Problem Radius of Turn A.... then proceed vertically downward and read the radius of turn.. True airspeed B.......... 0G per second.70 75° 2. Combat Altitude 36. whichever occurs first. with entry rates of 4. Altitude at start of pull-out 15. proceed vertically downward to read the maximum attainable Mach number in level flight. USE Enter the appropriate chart with the desired combat altitude.000 pounds and with the speedbrake retracted. LEVEL FLIGHT ENVELOPE CHART This chart (figure 11-165) presents the aircraft level flight speed envelope for various configurations at combat gross weights equal to 60% total fuel.000 Ft. The second set of charts show pull-ups limited by maximum lift or 7. B.5G per second A.0G and 3. A. Proceed horizontally to intersect the applicable configuration power curve.A1-F18AC-NFM-200 DIVE RECOVERY CHARTS Subsonic dive recovery charts (figure 11-164) for two-engine operation are provided for the fighter escort configuration ((2)AIM-9 + (2)AIM-7) at a gross weight of 36.0G and 2.000 Ft. 3.5G per second. Both maximum and military thrust flight envelopes are present.60 11-263 . with entry rate of 7.0G.0G. Data is included for both military power and idle power settings. B. Sample Problem Sample Problem Military Power. From this point project vertically down to intersect the dive angle at start of the pull-out then horizontally left to read altitude lost during pull-out. Dive angle at start of pull-out D. Mach number at start of pull-out C. Configuration Line: (2) AIM-9 + (2) AIM-7 C. Parameters of the envelopes extend from the lift limit to Vmax throughout the altitude range. From this point. USE Enter the chart with the altitude at the start of the pull-out and project horizontally right to intersect true Mach number or calibrated airspeed at the start of the pull-out. Altitude lost during pull-out Section XI Part 9 0.900 Ft. The first set of charts show pull-ups limited by maximum lift or 4. Maximum attainable Mach number 1. Two sets of dive recovery data are presented. whichever occurs first. Time corresponding to new Mach number H. distance and gross weight corresponding to the desired Mach number to determine the time. distance.95 1. Parallel guidelines F. Gross weight B. and fuel required for acceleration.000 feet. . and proceed upwards parallel to the vertical guide lines to the Mach number desired at the end of the acceleration. 6. D. maximum thrust accelerations. Proceed vertically upward to the initial Mach number. Desired Mach number G. Project from this point both horizontally to the left and note the time and distance. The Maximum Endurance Mach number (MAX END) for a given gross weight is provided across the bottom of the charts. Subtract the time.2 Min. 2.000. 0. however. Distance required for acceleration (H-D) L. The time and fuel values are calculated for U. 10. Distance E. Time required for acceleration (G-C) K.000 Lb.000. 34. This data is presented for various altitudes and configurations.750 Lb. A.7 0.000.S. and fuel required for level flight.3 NM 37. 0. and gross weight corresponding to the initial Mach number from the time. and vertically downwards and note gross weight. Distance corresponding to new Mach number I.4 Min.5 NM 250 Lb.000. USE Enter the applicable chart with the aircraft gross weight.8 NM 0.000 pounds.000 Feet. distance. correction factors are given for nonstandard temperatures. 9. 11-264 Sample Problem Configuration: (2)AIM-9 + (2)AIM-7. and 42. 4. distance. Time 38. Fuel required for acceleration (A-I) 2.8 Min. 38.000. and 6. 30.000. MAXIMUM THRUST ACCELERATION CHARTS These charts (figure 11-176 thru figure 11-180) show the relationship of time. Gross weight corresponding to new Mach number J. Separate charts are provided for both maximum and military thrust for gross weights of 26. Project from this point both horizontally to the left and note the time and distance. Initial Mach number C. Standard Day conditions.Section XI Part 9 A1-F18AC-NFM-200 LOW ALTITUDE ACCELERATION These charts (figure 11-166 thru 11-175) present time and fuel required to accelerate from 360 KIAS to desired KIAS up thru 550 KIAS at altitudes of Sea Level. . A1-F18AC-NFM-200 Section XI Part 9 Figure 11-163. Turn Capabilities 11-265 . Section XI Part 9 A1-F18AC-NFM-200 Figure 11-164. Dive Recovery .F404-GE-400 (Sheet 1 of 8) 11-266 . . A1-F18AC-NFM-200 Section XI Part 9 Figure 11-164. Dive Recovery .F404-GE-400 (Sheet 2 of 8) 11-267 . Dive Recovery .Section XI Part 9 A1-F18AC-NFM-200 Figure 11-164. .F404-GE-400 (Sheet 3 of 8) 11-268 . A1-F18AC-NFM-200 Section XI Part 9 Figure 11-164. Dive Recovery .F404-GE-400 (Sheet 4 of 8) 11-269 . Section XI Part 9 A1-F18AC-NFM-200 Figure 11-164. .F404-GE-400 (Sheet 5 of 8) 11-270 . Dive Recovery . A1-F18AC-NFM-200 Section XI Part 9 Figure 11-164. Dive Recovery .F404-GE-400 (Sheet 6 of 8) 11-271 . Dive Recovery . .Section XI Part 9 A1-F18AC-NFM-200 Figure 11-164.F404-GE-400 (Sheet 7 of 8) 11-272 . A1-F18AC-NFM-200 Section XI Part 9 Figure 11-164. Dive Recovery .F404-GE-400 (Sheet 8 of 8) 11-273 . .F404-GE-400 11-274 .Section XI Part 9 A1-F18AC-NFM-200 Figure 11-165. Level Flight Envelope . 18/1.S.85/.10 .92 10/212 11/220 11/228 12/236 12/246 13/268 14/295 16/332 19/387 1.91 — 1.92 480 6/128 7/131 7/135 7/138 7/142 8/150 8/159 9/169 9/181 1.22/1.19/1.88/.89/. 1962 DATE: 16 NOVEMBER 1989 DATA BASIS: ESTIMATED (BASED ON FLIGHT TEST) FUEL GRADE: JP-5 FUEL DENSITY: 6.89 550 12/220 12/230 13/241 13/253 14/268 16/308 20/388 1.15 .Section XI Part 9 A1-F18AC-NFM-200 LOW ALTITUDE ACCELERATION F404-GE-400 MAXIMUM THRUST GROSS WEIGHT E 26.18 .92 480 6/126 6/129 6/133 7/136 7/139 7/147 8/155 8/165 9/175 1.17/1.91/.14/1.11 . EFFECT FACTORS 11/215 11/224 12/233 12/243 13/254 14/281 16/319 19/379 360 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 420 4/65 4/66 4/68 4/69 4/71 4/74 4/78 5/82 5/87 1.89/.86/.15/1.17/1.13 .12 .26.84/.91 4000 FEET (7°C) 550 360 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 420 3/63 3/64 4/65 4/67 4/68 4/71 4/75 4/78 4/83 1.16/1.91 480 7/133 8/137 8/141 8/145 8/149 9/159 9/170 10/183 11/198 1.89/.92 520 9/175 9/180 9/185 10/191 10/198 11/211 11/228 12/247 13/271 1. Low Altitude Acceleration .Maximum Thrust .10 .91 480 7/130 7/134 7/137 7/141 8/145 8/154 9/164 9/175 10/189 1.16 .88/.89 550 6000 FEET (3°C) DRAG INDEX TEMP.21/1.87/.10 .13 .8 LB/GAL TIME TO ACCELERATE (SEC) / FUEL TO ACCELERATE (LBS) SEA LEVEL (15°C) SPEED (KIAS) 0 25 50 75 100 150 200 250 300 +10°C -10°C 360 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 420 3/61 3/62 3/64 3/65 3/66 3/69 4/72 4/75 4/79 1.14/1.14 .15/1.87/.92/.09 .23/1.89/.92 10/209 10/216 11/223 11/231 11/239 12/258 13/282 15/312 17/352 1.000 Pounds .89/.14 .17/1.16/1.000 POUNDS REMARKS ENGINE(S): (2)F404-GE-400 U.88/.18 .91 520 9/177 9/183 10/189 10/195 10/202 11/217 12/236 13/259 15/287 1.91 520 10/181 10/187 10/194 11/201 11/209 12/227 13/249 15/278 17/318 1.87 — — Figure 11-166.11 . STANDARD DAY.89/.19/1.11 .20/1.92 520 8/172 8/177 9/182 9/187 9/193 10/206 11/221 11/238 12/259 1.93 2000 FEET (11°C) 550 360 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 420 3/62 3/63 3/64 3/66 3/67 4/70 4/73 4/77 4/81 1.F404-GE-400 11-275 . Low Altitude Acceleration .17 .F404-GE-400 11-276 .87 21/110 26/134 34/179 520 20/104 21/111 23/120 25/132 28/146 36/193 — — — 1.85/.8 LB/GAL TIME TO ACCELERATE (SEC) / FUEL TO ACCELERATE (LBS) SEA LEVEL (15°C) SPEED (KIAS) 0 25 50 75 100 150 200 250 300 +10°C -10°C 360 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 420 6/32 6/33 6/35 7/36 7/38 8/41 8/45 9/51 11/57 1.26/1.79/.23/1. STANDARD DAY.25/1.89 480 14/74 15/78 16/82 17/88 18/94 — 1.88 550 23/126 25/137 28/152 31/171 36/199 — — — — 1.31/1.29/1.88 360 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 420 7/34 7/35 7/37 8/39 8/40 9/45 10/50 11/57 13/66 1.19 .17 .89 480 12/69 13/73 14/77 15/81 15/86 18/98 21/115 25/140 33/187 1.28/1.88 480 15/76 16/81 17/86 18/92 - 1.16 .87 550 27/137 30/156 36/188 — — — — 1.83/.16 .22 .17 .86/.82/.19 .27/1.27/1.20 .19/1.82 520 19/101 20/108 21/116 23/125 25/137 32/172 — — — 1.19 .16 .83/.20 .87 550 25/130 27/144 30/162 36/193 — — — — — 1.18 . 1962 DATE: 16 NOVEMBER 1989 DATA BASIS: ESTIMATED (BASED ON FLIGHT TEST) FUEL GRADE: JP-5 FUEL DENSITY: 6.84/.88 360 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 420 6/33 7/34 7/36 7/37 7/39 8/43 9/48 10/54 12/61 1.84/.Military Thrust .000 Pounds .83/.82/.16 .24/1.S.87 520 17/98 4000 FEET (7°C) 2000 FEET (11°C) 550 6000 FEET (3°C) DRAG INDEX TEMP.88 — — — — 1.000 POUNDS REMARKS ENGINE(S): (2)F404-GE-400 U.16 .25/1.84/.83/.23/1.25/1. EFFECT FACTORS 18/104 20/111 21/119 23/130 28/158 38/216 22/122 23/132 26/144 28/160 32/180 — — 1.86 — — Figure 11-167.84/.90 480 13/71 14/75 15/79 16/84 17/90 19/103 23/123 29/154 43/235 1.84/.83/.15 .26. .22/1.88 20/100 24/118 30/149 43/218 520 21/108 23/117 25/127 28/141 31/160 — — — — 1.23/1.28/1.84/.87 360 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 420 7/36 8/37 8/39 8/41 9/43 10/48 11/54 13/62 15/73 1.Section XI Part 9 A1-F18AC-NFM-200 LOW ALTITUDE ACCELERATION F404-GE-400 MILITARY THRUST GROSS WEIGHT E 26. 14/1.89 550 13/254 14/256 15/278 15/292 16/309 19/353 23/436 1.18 .09 .11 .14 .86/.F404-GE-400 11-277 .23/1.21/1.13 .92 480 7/148 8/152 8/155 8/159 8/164 9/173 9/183 10/195 11/209 1.87/.89/.87/.Maximum Thrust .84/.14/1.91/.13 .15/1.92 550 11/241 12/249 12/257 13/266 13/276 14/298 15/325 17/358 19/403 1.10 .88/.91 520 11/210 12/217 12/224 12/232 13/241 14/261 15/287 17/319 19/363 1.15/1. STANDARD DAY.Section XI Part 9 A1-F18AC-NFM-200 LOW ALTITUDE ACCELERATION F404-GE-400 MAXIMUM THRUST GROSS WEIGHT E 30.89/.16 .16/1.92/.89/.8 LB/GAL TIME TO ACCELERATE (SEC) / FUEL TO ACCELERATE (LBS) 6000 FEET (3°C) 4000 FEET (7°C) 2000 FEET (11°C) SEA LEVEL (15°C) SPEED (KIAS) DRAG INDEX TEMP. 1962 DATE: 16 NOVEMBER 1989 DATA BASIS: ESTIMATED (BASED ON FLIGHT TEST) FUEL GRADE: JP-5 FUEL DENSITY: 6.91 520 11/205 11/211 11/218 12/225 12/233 13/251 14/272 15/297 17/329 1.91 360 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 420 4/72 4/74 4/75 4/77 4/79 4/82 5/86 5/91 5/95 1.11 . Low Altitude Acceleration .30.11 .89/.89 360 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 420 4/75 4/76 4/78 5/80 5/82 5/86 5/90 5/95 6/100 1.18 .19/1.87 — — Figure 11-168.88/.000 POUNDS REMARKS ENGINE(S): (2)F404-GE-400 U.22/1.89/.17/1.92 520 10/199 10/204 10/210 10/216 11/223 11/238 12/254 13/274 14/298 1.88/.19/1.12 .91 480 8/154 9/158 9/162 9/167 9/172 10/183 11/196 12/210 12/227 1.000 Pounds .17/1.93 360 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 420 4/72 4/73 4/74 4/76 4/78 4/81 4/85 5/89 5/93 1.S.10 .92 520 10/202 10/208 11/214 11/221 11/228 12/244 13/262 14/285 15/312 1.20/1.92 480 7/146 7/150 7/153 8/157 8/161 8/169 9/179 9/190 10/202 1.18/1.89/.16/1.14 .91 480 8/151 8/154 8/159 9/163 9/167 9/177 10/189 11/202 11/217 1. EFFECT FACTORS 0 25 50 75 100 150 200 250 300 +10°C -10°C 360 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 420 4/71 4/72 4/73 4/75 4/76 4/80 4/83 4/87 5/91 1.17/1.91 550 13/249 13/258 14/269 15/280 15/293 16/324 18/366 22/431 — 1.85/.10 .92 550 12/245 12/254 13/263 13/273 14/283 15/308 17/340 19/381 21/442 1.15 . F404-GE-400 11-278 .88 360 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 420 8/39 8/41 8/43 9/45 9/47 10/52 11/58 13/66 15/76 1.19/1.000 Pounds .Section XI Part 9 A1-F18AC-NFM-200 LOW ALTITUDE ACCELERATION F404-GE-400 MILITARY THRUST GROSS WEIGHT E 30.000 POUNDS REMARKS ENGINE(S): (2)F404-GE-400 U.83/.16 .16 .16 .88 20/100 21/107 23/115 27/136 34/170 48/245 520 25/125 27/135 29/147 32/163 36/184 — — — — 1.15 .87 520 20/113 21/120 23/128 25/138 27/149 32/182 44/247 — — 1.25/1.26/1.82/.16 .84/.17 .86 — — Figure 11-169. .88 550 25/141 27/153 29/166 33/184 37/208 — — — — 1. Low Altitude Acceleration .22 .84/.28/1.20 .27/1.84/.83/.82/.88 550 27/146 29/159 32/175 36/197 42/229 — — — — 1.84/.8 LB/GAL TIME TO ACCELERATE (SEC) / FUEL TO ACCELERATE (LBS) 6000 FEET (3°C) 4000 FEET (7°C) 2000 FEET (11°C) SEA LEVEL (15°C) SPEED (KIAS) DRAG INDEX TEMP.82 19/103 22/119 26/141 33/179 520 21/117 23/124 25/134 27/145 29/158 36/198 — — — 1.90 480 15/83 16/87 17/92 18/97 — 1.19 .87 360 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 420 8/41 9/43 9/45 10/47 10/50 11/55 13/62 15/72 17/84 1.79/.84/.87 550 31/158 35/180 42/215 — — — — 1.20 .Military Thrust .16 . STANDARD DAY.17 .86/.83/.18 .29/1.88 480 18/88 19/94 — 1.24/1.28/1.25/1.87 550 28/151 31/166 35/187 41/222 — — — — — 1.89 480 14/80 15/84 16/89 17/94 18/99 20/113 24/132 29/161 38/213 1.83/.17 .84/.S.88 360 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 420 7/38 8/40 8/41 8/43 9/45 9/50 10/55 12/62 13/71 1.23/1. EFFECT FACTORS 0 25 50 75 100 150 200 250 300 +10°C -10°C 360 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 420 7/37 7/39 7/40 8/42 8/44 9/48 10/53 11/59 12/66 1.23/1.19 . 1962 DATE: 16 NOVEMBER 1989 DATA BASIS: ESTIMATED (BASED ON FLIGHT TEST) FUEL GRADE: JP-5 FUEL DENSITY: 6.89 480 16/85 17/90 18/95 — 1.30.25/1.83/.27/1.22/1.23/1.20 .87 20/102 21/109 24/127 29/154 39/204 520 23/120 24/129 26/139 29/152 32/168 42/221 — — — 1.85/.31/1. 09 .17/1.18 .91 360 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 420 4/82 5/84 5/86 5/88 5/89 5/94 5/98 6/103 6/108 1.F404-GE-400 11-279 .19/1.88/.89/.92 520 11/226 11/232 11/239 12/246 12/253 13/269 14/288 15/310 16/337 1.92 520 11/230 12/236 12/243 12/251 13/259 14/276 15/297 16/322 17/352 1.12 .89/.87/.15/1.91 480 9/171 9/175 9/180 10/185 10/190 11/201 11/214 12/229 13/246 1.18/1.88/.Section XI Part 9 A1-F18AC-NFM-200 LOW ALTITUDE ACCELERATION F404-GE-400 MAXIMUM THRUST GROSS WEIGHT E 34.14/1.18 .8 LB/GAL TIME TO ACCELERATE (SEC) / FUEL TO ACCELERATE (LBS) 6000 FEET (3°C) 4000 FEET (7°C) 2000 FEET (11°C) SEA LEVEL (15°C) SPEED (KIAS) DRAG INDEX TEMP.11 .16 .13 .10 .92 550 14/278 14/288 15/298 15/309 16/321 17/349 19/384 21/430 24/496 1.20/1.10 .11 .15/1.14/1.89/.19/1.14 .92 550 13/274 13/283 14/292 14/302 15/313 16/337 17/367 19/405 21/454 1.11 .17/1.91 550 14/283 15/293 16/305 16/317 17/332 19/366 21/412 24/482 — 1.16/1.89 550 15/289 16/301 17/315 17/331 18/349 21/397 25/483 1.23/1.15 .88/.87 — — Figure 11-170.93 360 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 420 4/81 4/83 4/85 4/86 5/88 5/92 5/96 5/101 5/106 1.85/.87/.17/1.92 480 8/166 8/170 8/174 9/178 9/183 9/192 10/203 10/215 11/229 1. 1962 DATE: 16 NOVEMBER 1989 DATA BASIS: ESTIMATED (BASED ON FLIGHT TEST) FUEL GRADE: JP-5 FUEL DENSITY: 6.S.89 360 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 420 5/85 5/87 5/89 5/91 5/93 5/97 6/102 6/108 6/114 1.91 520 12/233 12/240 13/247 13/256 14/264 15/284 13/250 17/336 19/371 1.91 480 10/175 10/179 10/184 10/190 11/195 11/208 12/222 13/238 14/257 1.84/.92 480 9/168 9/172 9/177 9/181 9/186 10/196 10/208 11/221 12/236 1.86/.91 520 13/238 13/246 14/254 14/263 15/273 16/296 17/324 19/359 22/407 1.14 .92/. STANDARD DAY.000 POUNDS REMARKS ENGINE(S): (2)F404-GE-400 U.000 Pounds .16/1.21/1.22/1. Low Altitude Acceleration . EFFECT FACTORS 0 25 50 75 100 150 200 250 300 +10°C -10°C 360 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 420 4/80 4/82 4/83 4/85 4/87 5/90 5/94 5/98 5/103 1.89/.10 .Maximum Thrust .89/.13 .89/.91/.34. 20 .84/.28/1.16 .88 550 30/166 33/180 36/199 41/223 47/258 — — — — 1.F404-GE-400 11-280 . EFFECT FACTORS 0 25 50 75 100 150 200 250 300 +10°C -10°C 360 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 420 8/43 8/44 8/46 9/48 9/50 10/54 11/60 12/67 14/75 1.S.25/1.83/.23/1.88 360 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 420 9/45 9/47 10/49 10/51 11/53 12/59 13/66 15/75 17/86 1.83/.87 20/102 21/109 22/115 24/123 28/144 34/175 44/230 520 26/137 28/146 30/158 33/172 36/190 47/249 — — — 1.90 480 18/94 18/99 — 1.16 . 1962 DATE: 16 NOVEMBER 1989 DATA BASIS: ESTIMATED (BASED ON FLIGHT TEST) FUEL GRADE: JP-5 FUEL DENSITY: 6.23/1.23/1.34.18 .86/.89 480 19/97 — 1.19 .84/.22 .31/1.20 .19 .88 360 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 420 8/44 9/45 9/47 9/49 10/51 11/57 12/63 13/70 15/81 1.87 520 23/128 24/136 26/146 28/157 30/170 37/206 49/277 — — 1.20 .22/1.Section XI Part 9 A1-F18AC-NFM-200 LOW ALTITUDE ACCELERATION F404-GE-400 MILITARY THRUST GROSS WEIGHT E 34.84/.27/1.15 .89 480 16/91 17/96 18/101 19/107 20/113 23/129 27/150 33/182 43/242 1.27/1.88 550 29/161 31/174 33/189 37/209 42/235 — — — — 1.8 LB/GAL TIME TO ACCELERATE (SEC) / FUEL TO ACCELERATE (LBS) 6000 FEET (3°C) 4000 FEET (7°C) 2000 FEET (11°C) SEA LEVEL (15°C) SPEED (KIAS) DRAG INDEX TEMP. STANDARD DAY.84/.16 .29/1.19/1.84/.82 19/104 21/111 22/118 25/135 30/160 37/202 520 24/133 26/141 28/152 30/164 33/179 41/224 — — — 1.88 520 28/142 30/153 33/167 36/185 41/208 — — — — 1.87 550 35/180 39/204 47/243 — — — — 1.79/.28/1.17 .16 .Miliatry Thrust .85/.25/1.86 — — Figure 11-171.84/.16 .82/.17 .82/.83/.000 Pounds .83/.24/1.17 . .83/.25/1.87 360 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 420 10/47 10/49 11/51 11/54 12/57 13/63 15/71 17/82 20/96 1.87 550 32/172 36/189 40/212 47/250 — — — — — 1.000 POUNDS REMARKS ENGINE(S): (2)F404-GE-400 U.26/1. Low Altitude Acceleration .88 480 20/101 21/107 23/114 24/121 26/131 31/155 38/193 54/273 — 1. F404-GE-400 11-281 .16/1. EFFECT FACTORS 0 25 50 75 100 150 200 250 300 +10°C -10°C 360 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 420 4/90 5/92 5/94 5/95 5/97 5/101 5/106 6/110 6/116 1.10 .89/.12 .15/1.89 550 17/323 18/337 19/352 19/369 21/389 23/441 28/529 1.38.000 Pounds .09 .17/1.16/1.89/.92/.87/.88/.92 550 15/307 15/317 15/327 16/338 17/350 18/377 19/410 21/451 24/505 1.92 480 9/186 9/190 9/195 10/199 10/204 10/215 11/227 12/241 12/256 1.11 .91/.000 POUNDS REMARKS ENGINE(S): (2)F404-GE-400 U.11 .91 550 16/317 17/328 17/341 18/355 19/371 21/408 23/458 27/531 — 1.Section XI Part 9 A1-F18AC-NFM-200 LOW ALTITUDE ACCELERATION F404-GE-400 MAXIMUM THRUST GROSS WEIGHT E 38. STANDARD DAY.14 .91 520 14/267 15/275 15/285 16/295 16/306 18/331 19/361 21/400 24/451 1.19/1.88/.85/. 1962 DATE: 16 NOVEMBER 1989 DATA BASIS: ESTIMATED (BASED ON FLIGHT TEST) FUEL GRADE: JP-5 FUEL DENSITY: 6.14/1.92 550 15/312 16/322 17/334 17/346 18/359 19/390 21/428 23/478 27/549 1.11 .19/1.89/.8 LB/GAL TIME TO ACCELERATE (SEC) / FUEL TO ACCELERATE (LBS) 6000 FEET (3°C) 4000 FEET (7°C) 2000 FEET (11°C) SEA LEVEL (15°C) SPEED (KIAS) DRAG INDEX TEMP.89/.16 .91 480 10/192 10/197 11/202 11/207 11/213 12/225 13/239 13/256 14/274 1.92 480 10/188 10/193 10/198 10/203 11/208 11/220 12/233 12/247 13/264 1.87 — — Figure 11-172.89 360 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 420 5/95 6/97 6/100 6/102 6/104 6/109 6/115 7/121 7/127 1.14/1.18 .10 .15/1.13 .91 360 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 420 5/92 5/94 5/96 5/98 5/100 6/105 6/110 6/115 7/122 1.18 .10 .93 360 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 420 5/91 5/93 5/95 5/97 5/99 5/103 6/108 6/113 6/119 1.91 480 11/196 11/201 11/207 12/213 12/219 13/232 14/248 15/266 16/287 1.20/1.86/.22/1.18/1.13 .91 520 13/261 14/269 14/277 15/286 15/296 16/317 18/343 19/374 21/413 1. Low Altitude Acceleration .92 520 13/257 13/264 14/272 14/280 14/289 15/309 16/332 18/360 19/393 1.17/1.89/.84/.92 520 12/253 12/260 13/267 13/275 14/283 14/301 15/322 17/347 18/376 1.89/.87/.Maximum Thrust .14 .88/.23/1.17/1.21/1.S.15 . 88 360 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 420 9/49 10/51 10/53 11/55 11/58 12/64 13/71 15/80 17/91 1.87 550 39/203 44/288 52/270 — — — — 1.S.16 .16 .88 480 23/113 24/120 25/128 27/136 29/147 35/173 43/216 60/301 — 1.000 POUNDS REMARKS ENGINE(S): (2)F404-GE-400 U.17 .84/.90 480 20/105 21/111 22/117 23/124 25/132 28/152 33/180 42/225 — 1.23/1.22 .87 550 36/193 40/212 45/237 52/278 — — — — — 1.84/.87 520 26/144 27/153 29/163 31/176 34/190 41/230 54/308 — — 1.26/1.16 .84/. 1962 DATE: 16 NOVEMBER 1989 DATA BASIS: ESTIMATED (BASED ON FLIGHT TEST) FUEL GRADE: JP-5 FUEL DENSITY: 6.25/1.18 .83/.87 360 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 420 11/53 11/55 12/58 12/61 13/64 15/71 16/80 19/92 22/109 1.Military Thrust .84/.28/1. EFFECT FACTORS 0 25 50 75 100 150 200 250 300 +10°C -10°C 360 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 420 9/48 9/50 9/52 10/54 10/56 11/61 12/67 14/75 16/85 1.82/.17 .19/1.23/1. .27/1.84/.83/88 520 31/159 34/172 37/188 41/207 46/233 — — — — 1.28/1.16 .89 480 18/103 19/108 20/113 22/120 23/127 26/144 30/168 37/204 48/270 1.84/.88 360 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 420 10/50 10/53 11/55 11/57 12/60 13/66 15/74 17/84 19/98 1.83/.20 .16 .15 .88 550 34/186 37/202 41/223 45/249 47/255 — — — — 1.8 LB/GAL TIME TO ACCELERATE (SEC) / FUEL TO ACCELERATE (LBS) 6000 FEET (3°C) 4000 FEET (7°C) 2000 FEET (11°C) SEA LEVEL (15°C) SPEED (KIAS) DRAG INDEX TEMP.F404-GE-400 11-282 .86/.79/.19 .19 .23/1.89 480 21/109 22/115 23/122 25/130 27/139 31/161 38/195 49/256 — 1.25/1.Section XI Part 9 A1-F18AC-NFM-200 LOW ALTITUDE ACCELERATION F404-GE-400 MILITARY THRUST GROSS WEIGHT E 38.87 520 29/153 31/164 34/177 37/193 40/213 52/277 — — — 1.31/1.88 550 32/180 34/195 37/212 41/234 46/263 — — — — 1.24/1.25/1.27/1.82/.83/.17 . STANDARD DAY.86 — — Figure 11-173.20 .82 520 27/149 29/159 31/170 34/184 37/201 46/250 — — — 1.29/1.20 . Low Altitude Acceleration .22/1.83/.38.000 Pounds .85/. 85/.16/1.92 480 10/206 10/211 10/216 11/221 11/227 12/238 12/252 13/267 14/284 1.15/1.18 .87 — — Figure 11-174.89 550 19/358 20/373 21/390 22/408 23/430 25/485 30/574 1. Low Altitude Acceleration .91 550 18/351 19/364 19/377 20/393 21/410 23/450 25/504 29/581 — 1.92 550 16/340 17/351 17/362 18/374 18/387 20/417 21/453 23/498 26/556 1.92 550 17/346 18/357 18/369 19/383 20/397 21/431 23/473 26/527 29/602 1.14/1.000 POUNDS REMARKS ENGINE(S): (2)F404-GE-400 U.8 LB/GAL TIME TO ACCELERATE (SEC) / FUEL TO ACCELERATE (LBS) 6000 FEET (3°C) 4000 FEET (7°C) 2000 FEET (11°C) SEA LEVEL (15°C) SPEED (KIAS) DRAG INDEX TEMP.16/1. 1962 DATE: 16 NOVEMBER 1989 DATA BASIS: ESTIMATED (BASED ON FLIGHT TEST) FUEL GRADE: JP-5 FUEL DENSITY: 6.Maximum Thrust .92 480 11/209 11/214 11/219 11/225 12/231 12/243 13/258 14/274 15/292 1.88/.93 360 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 420 5/101 5/103 5/105 6/107 6/110 6/114 6/120 7/125 7/132 1.86/.89/.21/1.10 .15/1.14/1.15 .12 .91 520 15/289 15/298 16/307 16/317 17/327 18/351 20/379 21/413 23/456 1.14 .23/1.000 Pounds .17/1.17/1.88/.16 .11 .91 480 12/217 12/223 13/229 13/236 13/242 14/257 15/275 16/294 17/318 1.10 .89/.87/.F404-GE-400 11-283 .91/.14 .11 .88/.20/1.92 520 14/285 15/293 15/302 15/311 16/320 17/342 18/367 20/397 21/434 1.89/.87/. STANDARD DAY.89/.91 480 11/213 11/218 12/224 12/230 12/236 13/250 14/265 15/283 16/304 1.19/1.92/. EFFECT FACTORS 0 25 50 75 100 150 200 250 300 +10°C -10°C 360 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 420 5/100 5/102 5/104 5/106 5/108 6/112 6/117 6/123 6/129 1.18 .42.84/.22/1.10 .92 520 13/280 14/288 14/296 15/304 15/313 16/333 17/357 18/384 20/416 1.89/.18/1.Section XI Part 9 A1-F18AC-NFM-200 LOW ALTITUDE ACCELERATION F404-GE-400 MAXIMUM THRUST GROSS WEIGHT E 42.11 .91 520 16/296 16/305 17/315 18/326 18/338 20/366 21/399 24/440 26/495 1.13 .19/1.89 360 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 420 6/106 6/108 6/111 6/113 7/116 7/121 7/127 8/134 8/142 1.17/1.13 .91 360 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 420 6/102 6/105 6/107 6/109 6/111 6/117 7/122 7/128 7/135 1.S.09 .89/. 83/.28/1.83/.87 550 44/225 49/253 58/301 — — — — 1.17 .23/1.25/1.89 480 23/121 25/128 26/136 28/144 30/154 35/180 42/217 54/282 — 1.19 .F404-GE-400 11-284 .88 360 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 420 11/56 12/59 12/61 13/64 13/67 15/74 16/83 19/95 22/110 1.85/.18 .Section XI Part 9 A1-F18AC-NFM-200 LOW ALTITUDE ACCELERATION F404-GE-400 MILITARY THRUST GROSS WEIGHT E 42.86/.88 360 0/0 0/0 0/0 0/0 0/0 0/0 0/0 420 12/59 13/62 13/65 14/68 15/71 16/79 18/90 21/103 25/122 480 25/126 27/133 28/142 30/152 33/163 38/193 48/239 65/330 — 1.27/1.90 480 22/117 23/123 24/130 26/138 27/147 31/169 37/200 46/249 — 1.84/.16 .17 .31/1.82/. STANDARD DAY.82 520 30/165 32/176 35/189 38/204 41/223 51/277 — — — 1.20 .84/.87 520 29/160 30/170 32/182 35/195 37/211 45/255 60/339 — — 1.8 LB/GAL TIME TO ACCELERATE (SEC) / FUEL TO ACCELERATE (LBS) 6000 FEET (3°C) 4000 FEET (7°C) 2000 FEET (11°C) SEA LEVEL (15°C) SPEED (KIAS) DRAG INDEX TEMP.23/1.19 .17 .25/1.16 .84/.86 — — Figure 11-175.83/.S.000 Pounds .79/. Low Altitude Acceleration .22 .88 550 36/200 38/216 42/235 46/259 51/291 — — — — 1.20 .19/1.82/.28/1.42.27/1.89 480 21/114 22/120 23/126 24/133 25/141 29/160 34/187 41/226 53/298 1.000 POUNDS REMARKS ENGINE(S): (2)F404-GE-400 U.88 520 35/177 38/191 41/208 45/230 50/257 — — — — 1.16 .23/1.16 .15 .24/1.84/.88 360 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 420 10/55 11/57 11/59 12/62 12/65 14/71 15/79 17/89 19/102 1. 1962 DATE: 16 NOVEMBER 1989 DATA BASIS: ESTIMATED (BASED ON FLIGHT TEST) FUEL GRADE: JP-5 FUEL DENSITY: 6.83/.26/1. EFFECT FACTORS 0 25 50 75 100 150 200 250 300 +10°C -10°C 360 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 0/0 420 10/53 10/55 11/57 11/60 11/62 13/68 14/75 15/84 17/95 1.87 0/0 0/0 0/0 0/0 1.87 550 40/214 44/235 49/263 57/306 — — — — — 1.84/.88 550 38/207 41/225 45/247 50/276 58/320 — — — — 1.22/1.29/1.16 .25/1.87 520 32/170 35/183 37/197 41/214 45/236 58/305 — — — 1.20 . .Military Thrust .84/.83/. 10. Maximum Thrust Acceleration .000 Feet .F404-GE-400 11-285 .A1-F18AC-NFM-200 Section XI Part 9 Figure 11-176. .000 Feet .30.F404-GE-400 (Sheet 1 of 4) 11-286 . Maximum Thrust Acceleration .Section XI Part 9 A1-F18AC-NFM-200 Figure 11-177. A1-F18AC-NFM-200 Section XI Part 9 Figure 11-177.F404-GE-400 (Sheet 2 of 4) 11-287 .30.000 Feet . Maximum Thrust Acceleration . Maximum Thrust Acceleration .F404-GE-400 (Sheet 3 of 4) 11-288 .000 Feet .30.Section XI Part 9 A1-F18AC-NFM-200 Figure 11-177. . 000 Feet .A1-F18AC-NFM-200 Section XI Part 9 Figure 11-177. Maximum Thrust Acceleration .30.F404-GE-400 (Sheet 4 of 4) 11-289 . F404-GE-400 (Sheet 1 of 4) 11-290 . . Maximum Thrust Acceleration .000 Feet .Section XI Part 9 A1-F18AC-NFM-200 Figure 11-178.35. A1-F18AC-NFM-200 Section XI Part 9 Figure 11-178.F404-GE-400 (Sheet 2 of 4) 11-291 .000 Feet .35. Maximum Thrust Acceleration . Section XI Part 9 A1-F18AC-NFM-200 Figure 11-178. .35. Maximum Thrust Acceleration .000 Feet .F404-GE-400 (Sheet 3 of 4) 11-292 . Maximum Thrust Acceleration .A1-F18AC-NFM-200 Section XI Part 9 Figure 11-178.000 Feet .F404-GE-400 (Sheet 4 of 4) 11-293 .35. 000 Feet .F404-GE-400 (Sheet 1 of 3) 11-294 .Section XI Part 9 A1-F18AC-NFM-200 Figure 11-179. Maximum Thrust Acceleration . .40. Maximum Thrust Acceleration .000 Feet .A1-F18AC-NFM-200 Section XI Part 9 Figure 11-179.F404-GE-400 (Sheet 2 of 3) 11-295 .40. 40.F404-GE-400 (Sheet 3 of 3) 11-296 .Section XI Part 9 A1-F18AC-NFM-200 Figure 11-179. . Maximum Thrust Acceleration .000 Feet . 000 Feet .45.F404-GE-400 11-297 .A1-F18AC-NFM-200 Section XI Part 9 Figure 11-180. Maximum Thrust Acceleration . .EMERGENCY OPERATION F404-GE-400 To be supplied 11-298 .Section XI Part 10 A1-F18AC-NFM-200 PART 10 . . 11-38 Combat Fuel Flow . . . . . . . illustration page numbers are shown in parentheses. . . . . . . . . .Military Thrust . . . .(11-213) Bingo . . . ii B Bingo . . . . . . . . . . . . . . . . . . .A1-F18AC-NFM-200 ALPHABETICAL INDEX NOTE • All text & illustrations numbers in this alphabetical index refer to page numbers. . . 11-6 APPLICABLE PUBLICATIONS . . . . . . . . . . . . . . . . . . .000 Pounds -F404-GE-400 . . 11-89 D Density Ratio . . . . . . . . . . . . . . . . . . . . . . . .(11-221) Bingo . . . . . .One Engine Operating . . . . v Airspeed Conversion . . . . .Gear Down . . . . . . .000 Pounds F404-GE-400 . . . . .Flaps Auto . . .000 Pounds F404-GE-400 . . . . .000 Pounds . . . . . . . . .(11-53) Dive Recovery . . . . . . . . 11-263 DRAG INDEX SYSTEM . . .F404-GE-400 . . . . . . . . . . . . . .Flaps Auto . . . . . . . . .(11-227) Bingo . . . .One Engine Operating . . . . . . .26. . . . . . . . . . . . . . .(11-215) Bingo . . 11-87 Constant Altitude/Long Range Cruise . . . . . . . . . . . . . . . . . . . . . . .11-90A C I CHANGE RECOMMENDATIONS . . . ii Headwind Effects on Bingo Fuel Cruise at Best Altitude . . . . . . .(11-22) ANGLE OF ATTACK CONVERSION CHART . . . . . .Military Thrust F404-GE-400 . 11-2 H HOW TO GET COPIES .Military Thrust . . . .000 Pounds . . . . . . . .Gear Down . . . . . . . 11-40 CLIMB PERFORMANCE CHARTS. . . . . .30. . . . . . . . . . . . . . . 11-87 Combat Specific Range . . . . . . . . . . . . . . .F404-GE-400 .30. . . . . . . . . .Flaps Auto . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .000 Pounds -F404-GE-400 . . . . . . .(11-266) DIVE RECOVERY CHARTS . . . . . . . . . .000 Pounds . . . . . . . . . . . . . .(11-225) BINGO CHARTS . . . . . . . . . . . . . . . . . . . . . . .Gear Up . . . . . . . . . . . . . . . .26. . . . . . . .Gear Up . . . . . . . . . . . . .(11-200) COMBAT SPECIFIC RANGE CHARTS .Gear Up . . . . . . 11-41 Change 1 Index 1 . . . . . . . . . . . . . . . . . . . . . . .Stabilized Level Flight .(11-64) Instantaneous Rate of Climb .350 KCAS F404-GE-400 . . . . . . . . . . . . . .Half Flaps . . . . . .(11-52) G GLOSSARY OF TERMS .(11-217) Bingo . . . . . . . . . . . . A AIRSPEED. . . . ii Automatic Distribution (with updates) . . . . . . . . . . . . . . . . . . . 11-23 Distance To Climb . . . . . .(11-17) AIRSPEED POSITION ERROR CORRECTION CHARTS. . . . . . . .Gear Up . . . .(11-208) CONSTANT ALTITUDE/LONG RANGE CRUISE (SPEED-TIME-FUEL) CHART. . . . . .34. . . . . . . . . . . . .Stabilized Level Flight 34. . . . . . . . . . . . . . .26. . . . . . . . . . . . . . . . .(11-223) Bingo . . . 11-3 F Fuel to Climb . . . . . . .One Engine Operating . iii CHANGE SYMBOLS . . . . . . . .26. . . . . . . . . . . . . . . . . . . . . . .000 Pounds . . . . 11-4 Airspeed Position Error Correction . . . . . .F404-GE-400 . . . . . . . . . . . . .Flaps Auto . . .000 Pounds F404-GE-400 . . . . . . . . . . . . . . . . . . . . . .26. . . . v CLIMB CHARTS . . . . . . . . . . . . . .(11-19) ALTIMETER POSITION ERROR CORRECTION CHART . . . .One Engine Operating . .350 KCAS .26. . .Flaps Auto . . .350 KCAS F404-GE-400 . . . . . . . . . . . .Gear Up . . . . . . . . . . . . . . . . . . . . .(11-15) AIRSPEED CONVERSION CHARTS . . . . . . . .Flaps Auto . . . . . . . . . . . . . . . . . . . . . . . . . .(11-204) Instantaneous Rate of Climb . . . . . . 11-5 Altimeter Position Error Correction . 11-5 Angle of Attack Conversion .F404-GE-400 . . . . .Gear Up . . . . . . . . .Half Flaps . . .(11-219) Bingo . . . . . . . . (11-210A) Headwind Effects on Bingo Fuel Cruise at Sea Level . . . . . . . .Maximum Thrust F404-GE-400 . . . . . . . 11-90 COMBAT FUEL FLOW CHARTS . . . . . . . . .F404-GE-400 . . . . . . .(11-58) INSTANTANEOUS RATE OF CLIMB CHARTS. . . . . . . . . . . . . .000 Pounds . . . (11-210B) HEADWIND EFFECTS ON BINGO FUEL .30. . . . . . . . . .Gear Up . . . . 11-88 CONSTANT ALTITUDE/LONG RANGE CRUISE (TRUE AIRSPEED AND FUEL FLOW) CHART . . . . . . . . . . . . . .000 Pounds F404-GE-400 . .Half Flaps .(11-211) Bingo . . . . . . . . . .(11-29) DENSITY RATIO CHART . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .F404-GE-400. . . . . . . . . . .(11-284) LOW ALTITUDE ACCELERATION CHARTS. . . . . . . . . . . . . . . . . (11-65) (11-65) Minimum Go Speed . . . . . . . . . . . . . . ii Single Engine Rate of Climb . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .40. . . . . .000 Pounds . . . . . . . . .(11-275) Low Altitude Acceleration . . . . .F404-GE-400 . . . . . . . . . . . . . . . . . . .F404-GE-400 . . . . . . .000 Pounds . . .TAKEOFF CONFIGURATION CHARTS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .(11-7) SCOPE . 11-25 Maximum Endurance . . .26. . . .(11-75) SINGLE ENGINE RATE OF CLIMB . .F404-GE-400 . . . . . . .000 Feet F404-GE-400 . . . .(11-294) Maximum Thrust Acceleration .(11-254) MAXIMUM RANGE DESCENT CHARTS . . . . . .F404-GE-400 . . . . . .(11-242) Normal Descent . . . .(11-278) Low Altitude Acceleration . . . . . . . . . 11-85 M P MANUAL DEVELOPMENT . . . . . . . . . . .(11-286) Peak Rate of Climb . . . . . . .F404-GE-400 . . . . . .(11-31) MINIMUM GO SPEED CHARTS. .Maximum Thrust F404-GE-400 . .(11-232) Maximum Endurance . . . . . . . . . . . . . . . . .F404-GE-400 . . . . . . . .000 Pounds . . . . . . . . . . . . . . . . . . . . . . . . . . .F404-GE-400 . . . . . . . . . . . . .F404-GE-400 . . . . .(11-280) Low Altitude Acceleration .(11-45) Military Thrust Climb .000 Feet F404-GE-400 . . . . . . . . . . . .35. . .000 Feet . . . . 11-41 Index 2 Change 7 N NATOPS FLIGHT MANUAL INTERIM CHANGES .(11-276) Low Altitude Acceleration . . . . .Military Thrust F404-GE-400 . .(11-246) NORMAL DESCENT CHARTS. . . . . . . . 11-258 Landing Distance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .A1-F18AC-NFM-200 Interference Code Numbers . . . .One Engine Operating F404-GE-400 . . . . .(11-59) Peak Rate of Climb . . . . . . . . . . .Military Thrust 42. . . 11-259 Level Flight Envelope . . . .(11-12) INTRODUCTION .000 Pounds F404-GE-400 . . . . . . . . . . . .(11-260) LANDING APPROACH SPEED CHART . . . . . . .000 Feet F404-GE-400 . . . . . .(11-235) MAXIMUM ENDURANCE CHARTS . . .(11-93) OPTIMUM CRUISE CHARTS. . . .F404-GE-400 . . . .F404-GE-400 . .000 Pounds . . . . . . . . . . . . . . . . . . . . ii Optimum Cruise . . . . . . . . . . . . . . . .Military Thrust 30. . . .F404-GE-400 . . . . . . .(11-285) Maximum Thrust Acceleration . . . . . .30.F404-GE-400 . . . 11-263 Low Altitude Acceleration .(11-297) MAXIMUM THRUST ACCELERATION CHARTS.(11-283) Low Altitude Acceleration . . . . . . . . . . . . . . .000 Pounds . . . . . . .One Engine Operating F404-GE-400 . . . . . . . . . . . . . . (11-10C) Interference Code Number To Interference Drag Index Number Conversion . . . . 11-2 L Maximum Thrust Acceleration . . . . . .One Engine Operating F404-GE-400 . .(11-32) Maximum Abort Speed . 11-90 S Sample Drag Computation . . . v Maximum Abort Speed . . . . . .(11-290) Maximum Thrust Acceleration . . . . . . . . . . . . . . . . . . . . . . . .Maximum Thrust F404-GE-400 . . . . . . . . . . . . . v Normal Descent . . . . . . . . . . . . . . . . . . . . .Maximum Thrust 30. . . .Miliatry Thrust 34. . . . . . . .000 Pounds . . . . . . . . . . . .(11-210) RANGEWIND CORRECTION CHART . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .45. . . . . . . . . .000 Feet F404-GE-400 . . . . . 11-229 Maximum Range Descent F404-GE-400 . .Maximum Thrust 42. . . . . .000 Pounds . . . . . . . .F404-GE-400 . . . . .(11-281) Low Altitude Acceleration . . . . . . . . . . . .(11-108) . . . . . . . . . .(11-261) LANDING DISTANCE CHART . . . . . . . (11-277) (11-279) Low Altitude Acceleration . . . . . . .000 Feet F404-GE-400 . . .Maximum Thrust 26. . . .Military Thrust F404-GE-400 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .000 Pounds . . . . . . . . . . . . . . . . .One Engine Operating F404-GE-400 . . . . . . . . . 11-241 Maximum Thrust Acceleration . . . . . . .10. . . . 11-264 One Time Orders. . . . 11-43 Specific Range . 11-24 Landing Approach Speed . . .One Engine Operating F404-GE-400 . . .10. . . . . . . . . . . . . . . . . . . . . . . . . . . . . .F404-GE-400 . . . . .(11-274) LEVEL FLIGHT ENVELOPE CHART . . . . . . . . . . . . . . . . . .Military Thrust 38. . .Military Thrust F404-GE-400 . . . . . . . . . . . . . . . . . .(11-54) PEAK RATE OF CLIMB CHARTS . . . . .(11-282) Low Altitude Acceleration . . . . . . . . . .(11-33) MAXIMUM ABORT SPEED CHARTS. . .Maximum Thrust F404-GE-400 . . . .(11-30) Minimum Go Speed . .F404-GE-400. . . . . . . . . . . . .Military Thrust 26. . . . . . . . . . . . . . . . . . 11-264 11-264 Military Thrust Climb . . . . . . . .Takeoff Configuration . .(11-91) Optimum Cruise . .F404-GE-400 . . .F404-GE-400 . . . . . . . . . . . . . . . . . . . . . . .Maximum Thrust 38. .000 Pounds . . . . 11-239 O R Rangewind Correction .(11-250) Maximum Range Descent . . . . . . . . . . . . . . . . . . . . . .30. .(11-155) Specific Range .000 Pounds F404-GE-400 . . . . . . . .000 Feet . .000 Feet . .000 Pounds F404-GE-400 . . . . . . . . . . . . .45.(11-150) Specific Range .000 Feet .34. . . . . . . . .(11-128) Specific Range .000 Pounds F404-GE-400 . . . . .000 Feet . . . . . . . . .(11-139) Specific Range .000 Pounds F404-GE-400 . . . . . . . . . . . . .000 Pounds F404-GE-400 . . . . . .20. . . . . . . . . . .000 Feet . . . . . . . . . . . . .000 Feet . . . . . .30.35. . . . . . . . .(11-113) Specific Range . .000 Pounds F404-GE-400 . . .000 Pounds F404-GE-400 . . . . . .35. . . . . . . . . . .000 Pounds F404-GE-400 . . . . . . . . . . . . . . . . . . . .10. . . . . . . . . . . . . . . . . .50. . . .000 Pounds F404-GE-400 . . . . . .000 Pounds F404-GE-400 . . . . . . . . . . .000 Pounds F404-GE-400 .000 Feet . . . . . . . . . . . . .A1-F18AC-NFM-200 Specific Range . . .42. .34. .40. .40. .000 Feet . .40.000 Feet . . . .000 Pounds F404-GE-400 . . . . . . . . . . . . . . . . . .(11-102) Specific Range . . . . .46.000 Pounds F404-GE-400 . .000 Pounds F404-GE-400 . . . . .(11-115) Specific Range . .(11-117) Specific Range . . . . .30. . . . . . . . . . . . . . .10. . . . .46. . . . . .000 Feet . .5. . . . . . . .34. . . .30. . . . . . . . . . . . . . . . . . . . .40. . . .(11-111) Specific Range .(11-147) Specific Range . . . . . .(11-129) Specific Range . . . .34. .000 Feet .50. .000 Feet . . . .(11-157) Specific Range . . . . .000 Pounds F404-GE-400 . . .000 Feet . .20. . . .000 Feet . . . . . . . .46. . . . . .38. . . . . . .20. . .38. . . . . . . .(11-146) Specific Range . .(11-109) Specific Range . .000 Feet . . .000 Pounds F404-GE-400 . . . . . . . .15. . . . . . . . .38.000 Pounds F404-GE-400 .5. . . . . . .46. . . .000 Pounds F404-GE-400 . . . . . . . . .000 Feet .30. . . . .(11-156) Specific Range .000 Feet .000 Pounds F404-GE-400 .(11-124) Specific Range . . . . .46. . . . .000 Pounds F404-GE-400 . . . . . . . . . . . .000 Pounds F404-GE-400 . .26.000 Pounds F404-GE-400 . .000 Feet . . .000 Feet . . .000 Pounds F404-GE-400 . . .(11-118) Specific Range .(11-101) Specific Range . . . . . . . . . . . . . . . . . . . .000 Feet . . . . . . . . . .26. . . . . . . . . . .000 Pounds F404-GE-400 . . .000 Feet . . . . . . . . .35. .000 Feet . .(11-145) Specific Range . .30. . . . . . . . . . . . . . .20. . . . . . . . . . . .000 Pounds F404-GE-400 . . . . . . . .(11-133) Specific Range . .000 Feet . . . . . .000 Feet . .000 Pounds F404-GE-400 . . . . . . . .000 Feet . . . . . . . . .(11-154) Specific Range . . . . . . . . . .000 Feet . . . . . . . . . . . .000 Pounds F404-GE-400 . . .000 Pounds F404-GE-400 . . . . . . .25. . . .15. . . . . . .42. .5. . . . . . . . . . . . .(11-137) Specific Range . . . . . .000 Pounds F404-GE-400 . . .42. . . . . . . . .000 Feet . . . . . . . . .000 Pounds F404-GE-400 .000 Feet . . . . . . .50. . . . . .000 Feet . . . . .50. .(11-103) Index 3 . . . .(11-132) Specific Range . . . . .30. . . . . . .(11-134) Specific Range . . . . . . .000 Feet .34. . . . . . .(11-142) Specific Range . . . . . . . . .38. . . . . . . .15. . .26. .000 Pounds F404-GE-400 . . . . . . .(11-126) Specific Range . . . . . . .(11-110) Specific Range . . . .(11-158) Specific Range .000 Feet . .34. . .000 Feet .000 Pounds F404-GE-400 . . .(11-153) Specific Range . . . . . .(11-159) Specific Range . . . . . .000 Pounds F404-GE-400 . . . . . . . . . . . .30. .38. . . . . . . . . . . . . . . . . . . . . . . . . . . .45. .45. . . . . .20. . . . . .(11-131) Specific Range . . . . . . . .42.000 Pounds F404-GE-400 . .000 Pounds F404-GE-400 . . . . . . . .34. . . . .26. . . .000 Pounds F404-GE-400 . . . .000 Feet . . .000 Pounds F404-GE-400 . . .50. . .000 Pounds F404-GE-400 . . . .(11-144) Specific Range . . . . . . .(11-130) Specific Range . . .35. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .000 Feet . . . . . . . . . . . . . . .000 Pounds F404-GE-400 . . . . .(11-122) Specific Range .38. . . . . . . . .26. . . . .15.26. . .(11-123) Specific Range . . . . . . . . . . . .000 Pounds F404-GE-400 . . . . .42. . . . . . . . .30. . . . . . . . . . . . . .25. . . . . . . . . . . . . . . . . . .10.(11-140) Specific Range . . . . .15. . .38. .25. . .000 Feet .(11-148) Specific Range .(11-116) Specific Range . .000 Pounds F404-GE-400 . . . . . . . . . .25.15. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .000 Pounds F404-GE-400 . .46. . . . . . . . . . . .34.000 Pounds F404-GE-400 . . . . . . . . . . . .000 Pounds F404-GE-400 . .000 Feet . . . . . . . . . . . . . . . . . . . . . . .30. . . . . . . . . . .000 Feet . . .000 Feet . . . . . . . . .30. . .38. . .(11-149) Specific Range . . . . .000 Pounds F404-GE-400 .26. . . .000 Feet . . .30. . .10. . . .(11-112) Specific Range . . . . . .000 Feet .34. .35. . .40. .20. . . .25. . . . . . . . .000 Pounds F404-GE-400 .15. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .000 Feet . . . .000 Feet . . . .000 Feet . . . . . . . . . . .(11-119) Specific Range . . . . . . . .10. . . . . . . . . . . . . . . . . . . . . .35. . . . . . . . . . .20. .50. .(11-141) Specific Range . . . .42. . . . . . .46. . . .000 Pounds F404-GE-400 . . . .30. . . .000 Feet . . . . . . . . . . . . . . . . . . . . . .30. . . . .(11-138) Specific Range . . .000 Feet . .000 Feet . .000 Feet . . . . . . . . .(11-152) Specific Range . . . . . . .000 Feet . .000 Feet .000 Pounds F404-GE-400 .(11-127) Specific Range .000 Feet . . . . . . . . . .(11-120) Specific Range . . . . . . . .000 Pounds F404-GE-400 . . . . . . . .000 Pounds F404-GE-400 . . . . . . .000 Pounds F404-GE-400 . . . . .30. . . . .45. . . . . . . . .000 Pounds F404-GE-400 . . . . . . . . . . . . . . .35. . . . . . .(11-114) Specific Range .(11-143) Specific Range . . . . . .26. . . . . . . . . . . . . . . . . . . .000 Feet . . .30. . . . . . . . . . . . . . .40. . . . . . .000 Pounds F404-GE-400 .42.000 Feet . . . . . . . . . . . . .10.(11-136) Specific Range . . . .000 Feet . . . . .(11-151) Specific Range . . . . . .25. .000 Feet . . .000 Pounds F404-GE-400 . . .(11-125) Specific Range .(11-135) Specific Range . . .(11-121) Specific Range . .25. . . . . . . . . . . . . . . . . . . . . . . . .F404-GE-400 . . . . .(11-99) Specific Range .(11-188) Specific Range . . .000 Pounds . . . . . . . .(11-165) Specific Range . . . . . . .One Engine Operating .(11-104) Specific Range .Sea Level .(11-98) Specific Range . . . . .5.One Engine Operating .F404-GE-400 .(11-176) Specific Range . . . . . . .000 Pounds F404-GE-400 .(11-100) SPECIFIC RANGE CHARTS .One Engine Operating .000 Feet . . . . . . .000 Pounds . . .30. . . . . . .000 Pounds . . . . .38. .000 Pounds . . . . . . . . .(11-180) Specific Range .One Engine Operating . . .10.000 Pounds . . . . . . . . .000 Pounds . . . . . .F404-GE-400 . . .15. . . .000 Feet .26.000 Feet .(11-95) Specific Range . . .(11-195) Specific Range . . .(11-193) Specific Range .F404-GE-400 . . . . . .5.F404-GE-400 . .000 Pounds . . . . .000 Pounds .000 Pounds . .10.42. . . . . . . . . . .000 Feet .000 Pounds . . . .F404-GE-400 .One Engine Operating .(11-166) Specific Range . .(11-191) Specific Range . .000 Feet . .(11-167) Specific Range .F404-GE-400 .(11-164) Specific Range . .One Engine Operating . . . .30.5. . .(11-8) . . . . . .(11-173) Specific Range . .One Engine Operating .50. . .34.F404-GE-400 .10. . . .26. . . . .(11-179) Specific Range . . .000 Pounds . . .34.000 Feet .(11-186) Specific Range . . .42. . .One Engine Operating .(11-194) Specific Range . .000 Pounds . . .(11-177) Specific Range . . .46.One Engine Operating . . .000 Pounds .000 Feet .Sea Level .000 Pounds . . . . . . .(11-181) Specific Range .000 Pounds . . .000 Pounds F404-GE-400 .One Engine Operating .(11-199) Specific Range . .F404-GE-400 .10. . . .000 Pounds .One Engine Operating . . . .000 Feet .F404-GE-400 . .(11-196) Index 4 Specific Range .34. . . .000 Pounds . . .Sea Level .One Engine Operating .15. . . . .Sea Level .(11-171) Specific Range .F404-GE-400 . . . .15. . . .(11-168) Specific Range . .000 Feet .10. . .000 Pounds .000 Feet . .Sea Level .26.42.000 Feet .F404-GE-400 . .Sea Level .(11-107) Specific Range . . 11-6 Standard Atmosphere Table. . .One Engine Operating . . . . . .(11-96) Specific Range . .46. . .5. . . . . . .(11-13) Summary of Store Drag Index Numbers .F404-GE-400 . .42.(11-175) Specific Range . . .Sea Level . . .One Engine Operating .15. . . .26.One Engine Operating .Sea Level .One Engine Operating .26.000 Feet .(11-174) Specific Range . . .000 Feet .F404-GE-400 . .Sea Level . .000 Pounds . .26.20. . . . . .30.000 Feet . .F404-GE-400 .38. . . .000 Feet .38. .A1-F18AC-NFM-200 Specific Range . . .000 Pounds . . . . . .F404-GE-400 . . . .One Engine Operating . . . . .34. . . . .46. . .(11-192) Specific Range . . . . . . .30. . . . . . . .One Engine Operating . .000 Feet . .000 Pounds . .50. . . .000 Pounds .000 Pounds . . . . . . . . . . . . .5. . .5. . .000 Pounds F404-GE-400 . . .38. . .F404-GE-400 .000 Pounds .000 Pounds . . . . .F404-GE-400 . .000 Pounds . . . . .50. . .F404-GE-400 . . . .30. . . . .(11-183) Specific Range . . . . . .(11-184) Specific Range . . .000 Pounds . . .Sea Level . .000 Pounds .000 Feet . . . . . . .000 Feet . .000 Pounds . . .10.5. . .000 Pounds . . .25.000 Feet . . .(11-105) Specific Range . . .000 Pounds . .F404-GE-400 . . . .38. . . . . .5. .(11-161) Specific Range .000 Feet . . .F404-GE-400 .30.000 Feet .F404-GE-400 . . . . . . . .F404-GE-400 . . . . .(11-182) Specific Range . .000 Feet . .F404-GE-400 . . . . . . .F404-GE-400 .20. . . . .One Engine Operating . . .000 Pounds .000 Pounds . . . .30. .46. . . . .One Engine Operating .One Engine Operating . . . . .One Engine Operating .000 Feet . . . . .F404-GE-400 . . . . . .25.One Engine Operating . . .46.One Engine Operating . . .30. . . . . .42. .34.5. . .25.(11-97) Specific Range .000 Pounds F404-GE-400 . . .(11-172) Specific Range . .F404-GE-400 .000 Feet .38.000 Pounds F404-GE-400 .F404-GE-400 . . . . . . .One Engine Operating . .F404-GE-400 .F404-GE-400 . . . . .26. .One Engine Operating . . . . . . . . . . . . . . .(11-178) Specific Range . .20. .46. .000 Pounds .One Engine Operating .34.000 Pounds . .One Engine Operating . .Sea Level . .(11-187) Specific Range . .000 Pounds F404-GE-400 .000 Pounds F404-GE-400 .000 Feet . . .One Engine Operating . .(11-185) Specific Range . . . .46. .(11-94) Specific Range .38.(11-160) Specific Range . . . . . .One Engine Operating .Sea Level . . . .F404-GE-400 . .One Engine Operating .000 Feet . . .50. .F404-GE-400 . .000 Pounds F404-GE-400 .10. . . . . . . .000 Pounds . .000 Pounds . . . 11-86 Stall Speeds .50.(11-163) Specific Range . . . .One Engine Operating .000 Pounds F404-GE-400 . .F404-GE-400 . . . . . . . . . . .One Engine Operating .15. . . . . . . .F404-GE-400 . . .F404-GE-400 .Sea Level . . . .(11-190) Specific Range .30. . .000 Feet . .000 Pounds . . . . . .(11-198) Specific Range .(11-21) STALL SPEEDS CHART .25.000 Feet .000 Feet . . . . . .000 Pounds .000 Feet . . .000 Feet . . .One Engine Operating . .(11-170) Specific Range . . . .26. . . . . .15. . . .000 Feet .Sea Level .(11-169) Specific Range .34. . .(11-197) Specific Range . . .One Engine Operating . .20.000 Pounds F404-GE-400 . . . .50. .30. . . . . . .F404-GE-400 .F404-GE-400 . . . . .42. . .20. . .20. . . .000 Pounds F404-GE-400 . . .F404-GE-400 .One Engine Operating .(11-106) Specific Range .000 Feet .38. . .One Engine Operating . . . . . . . . . .One Engine Operating .000 Feet . . . .000 Feet .000 Feet . . . . . . .F404-GE-400 . .One Engine Operating .000 Feet . . . . . . .(11-162) Specific Range .000 Pounds . . . .One Engine Operating .(11-189) Specific Range .15. .42. .F404-GE-400 .5.F404-GE-400 .5. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .(11-37) TAKEOFF GROUND ROLL CORRECTION FOR CG CHARTS . . . . . . . . . . . . . . . . . . . . . . v Wind Components . . . . .Maximum Thrust F404-GE-400 . . . . . . . . . . 11-262 Turn Capabilities . . .(11-51) TURN CAPABILITIES CHART. ii W WARNING. . .(11-14) Time to Climb . . . . . . AND NOTES . . . . .(11-28) WIND COMPONENTS CHART . .F404-GE-400 . . . . . . . . . . . . . . 11-23 WORDING . . . . .(11-71) SUPERSONIC MAXIMUM THRUST CLIMB CHARTS. . . . . . . . . . 11-38 Takeoff Distance . . .(11-265) U UPDATING THE MANUAL . . .(11-34) Takeoff Distance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11-42 T Takeoff Allowances and Acceleration to Climb Speed . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . CAUTIONS. . . . . . . . . . . . . .Maximum Thrust . . .(11-36) Takeoff Ground Roll Correction for CG . . . . . . . . .Military Thrust . . .(11-44) TAKEOFF ALLOWANCES CHART . . . . . . . . . . . . .F404-GE-400 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .F404-GE-400. . . . . . . . . . . . . .Military Thrust . . . . . . . . .350 KCAS F404-GE-400 . . . . . . . .A1-F18AC-NFM-200 Supersonic Maximum Thrust Climb F404-GE-400 . . . . . . . . . . . . . . 11-26 Takeoff Ground Roll Correction for CG . . . . . . . 11-27 Temperature Conversion . . . . . . . . . . . . . . . . . . . . v Index 5/(Index 6 blank) . . . . . . . . . . . . . . . .Military Thrust F404-GE-400 . . . . . . . . . . . . . . . . . . . . . . . . . . v Y YOUR RESPONSIBILITY . . . . .(11-35) TAKEOFF DISTANCE CHARTS . . . . . . . . . . . . . . . .
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