PW127 Maintenance Manual chapter 72-00

PRATT & WHITNEY CANADAMAINTENANCE MANUAL MANUAL PART NO. 3045542 LIST OF EFFECTIVE PAGES CHAPTER SECTION PAGE LEP 1 2 3 4 5 6 7 8 DATE Jan Jan Jan Jan Jan Jan Jan Jan 24/2006 24/2006 24/2006 24/2006 24/2006 24/2006 24/2006 24/2006 Contents 1 2 3 4 5 6 7 8 9 10 11 12 blank Jan 24/2006 Jan 24/2006 Jan 24/2006 Jan 24/2006 Jan 24/2006 Jan 24/2006 Jan 24/2006 Jan 24/2006 Jan 24/2006 Jan 24/2006 Jan 24/2006 Jan 24/2006 72-00-00 Description and Operation 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 CHAPTER SECTION PAGE 20 21 22 23 24 25 26 27 28 29 30 31 32 33 34 35 36 37 38 39 40 41 42 43 44 45 46 47 48 49 50 51 52 53 54 55 56 57 58 59 60 72-00 LEP DATE Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Page 1 Jan 24/2006 PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3045542 LIST OF EFFECTIVE PAGES CHAPTER SECTION PAGE 61 62 63 64 65 66 67 68 69 70 71 72 73 74 75 76 77 78 79 80 81 82 83 84 DATE Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 72-00-00 Fault Isolation 101 102 blank Sep 03/99 Sep 03/99 72-00-00 Maintenance Practices 201 202 203 204 205 206 207 208 209 210 211 212 213 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 CHAPTER SECTION PAGE 214 215 216 217 218 219 220 221 222 223 224 225 226 227 228 229 230 231 232 233 234 235 236 237 238 239 240 241 242 243 244 245 246 247 248 249 250 250 A deleted 250 B deleted 251 252 72-00 LEP DATE Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Page 2 Jan 24/2006 PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3045542 LIST OF EFFECTIVE PAGES CHAPTER SECTION 72-00-00 Servicing PAGE DATE 253 254 255 256 blank Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 301 302 303 304 305 306 307 308 309 310 311 312 313 314 315 316 317 318 319 320 321 322 323 324 325 326 327 328 329 330 331 332 333 334 335 336 May 02/2003 May 02/2003 May 02/2003 May 02/2003 May 02/2003 May 02/2003 May 02/2003 May 02/2003 May 02/2003 May 02/2003 May 02/2003 May 02/2003 May 02/2003 May 02/2003 May 02/2003 May 02/2003 May 02/2003 May 02/2003 May 02/2003 May 02/2003 May 02/2003 May 02/2003 May 02/2003 Mar 11/2005 May 02/2003 May 02/2003 May 02/2003 May 02/2003 May 02/2003 May 02/2003 May 02/2003 May 02/2003 May 02/2003 May 02/2003 May 02/2003 May 02/2003 CHAPTER SECTION PAGE DATE 337 338 339 340 341 342 blank May 02/2003 May 02/2003 May 02/2003 May 02/2003 May 02/2003 May 02/2003 72-00-00 Removal/ Installation 401 402 403 404 405 406 407 408 409 410 blank Mar 11/2005 Mar 11/2005 Mar 11/2005 Mar 11/2005 Mar 11/2005 Mar 11/2005 Mar 11/2005 Mar 11/2005 Mar 11/2005 Mar 11/2005 72-00-00 Adjustment/ Test 501 502 503 504 505 506 507 508 509 510 511 512 512 A 512 B blank 513 514 515 516 blank 517 518 blank 519 520 blank 521 Mar 09/2001 Mar 01/2002 Jul 13/2001 Mar 09/2001 Jul 13/2001 Jul 13/2001 Mar 01/2002 Mar 01/2002 Mar 01/2002 Jul 13/2001 Mar 01/2002 Mar 01/2002 Jul 13/2001 Jul 13/2001 Mar 01/2002 Jan 16/2004 Mar 09/2001 Mar 09/2001 Mar 09/2001 Mar 09/2001 Mar 09/2001 Mar 09/2001 Mar 09/2001 72-00 LEP Page 3 Jan 24/2006 PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3045542 LIST OF EFFECTIVE PAGES CHAPTER SECTION 72-00-00 Inspection Check PAGE DATE 522 blank 523 524 blank 525 526 Mar 09/2001 Mar 09/2001 Mar 09/2001 Jan 16/2004 Mar 09/2001 601 602 603 604 605 606 607 608 609 610 611 612 613 614 615 616 617 618 619 620 621 622 623 624 625 626 627 628 629 630 631 632 632 A 632 B 632 C Jan 24/2006 Jan 24/2006 Jan 24/2006 Jan 24/2006 Jan 24/2006 Jan 24/2006 Jan 24/2006 Jan 24/2006 Jan 24/2006 Jan 24/2006 Jan 24/2006 Jan 24/2006 Jan 24/2006 Jan 24/2006 Jan 24/2006 Jan 24/2006 Jan 24/2006 Jan 24/2006 Jan 24/2006 Jan 24/2006 Jan 24/2006 Jan 24/2006 Jan 24/2006 Jan 24/2006 Jan 24/2006 Jan 24/2006 Jan 24/2006 Jan 24/2006 Jan 24/2006 Jan 24/2006 Jan 24/2006 Jan 24/2006 Jan 24/2006 Jan 24/2006 Jan 24/2006 CHAPTER SECTION PAGE 632 D 632 E 632 F 632 G 632 H 632 I 632 J 632 K 632 L 632 M 632 N 632 O 632 P 632 Q 632 R 633 634 635 636 637 638 639 640 640 A deleted 640 B deleted 640 C deleted 640 D deleted 640 E deleted 640 F deleted 640 G deleted 640 H deleted 640 I deleted 640 J deleted 641 642 643 644 645 646 647 648 72-00 LEP DATE Jan 24/2006 Jan 24/2006 Jan 24/2006 Jan 24/2006 Jan 24/2006 Jan 24/2006 Jan 24/2006 Jan 24/2006 Jan 24/2006 Jan 24/2006 Jan 24/2006 Jan 24/2006 Jan 24/2006 Jan 24/2006 Jan 24/2006 Jan 24/2006 Jan 24/2006 Jan 24/2006 Jan 24/2006 Jan 24/2006 Jan 24/2006 Jan 24/2006 Jan 24/2006 Jan 24/2006 Jan 24/2006 Jan 24/2006 Jan 24/2006 Jan 24/2006 Jan 24/2006 Jan 24/2006 Jan 24/2006 Page 4 Jan 24/2006 PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3045542 LIST OF EFFECTIVE PAGES CHAPTER SECTION PAGE 648 A deleted 648 B deleted 648 C deleted 648 D deleted 648 E deleted 648 F deleted 648 G deleted 648 H deleted 648 I deleted 648 J deleted 648 K deleted 648 L deleted 648 M deleted 648 N deleted 648 O deleted 648 P deleted 648 Q deleted 648 R deleted 648 S deleted 648 T deleted 649 650 651 652 653 654 655 656 657 658 659 660 661 662 663 664 665 666 667 668 669 DATE Jan 24/2006 Jan 24/2006 Jan 24/2006 Jan 24/2006 Jan 24/2006 Jan 24/2006 Jan 24/2006 Jan 24/2006 Jan 24/2006 Jan 24/2006 Jan 24/2006 Jan 24/2006 Jan 24/2006 Jan 24/2006 Jan 24/2006 Jan 24/2006 Jan 24/2006 Jan 24/2006 Jan 24/2006 Jan 24/2006 Jan 24/2006 CHAPTER SECTION 72-00-00 Cleaning/ Painting PAGE DATE 670 671 672 673 674 675 676 677 678 679 680 681 682 683 684 685 686 687 688 689 690 691 692 Jan 24/2006 Jan 24/2006 Jan 24/2006 Jan 24/2006 Jan 24/2006 Jan 24/2006 Jan 24/2006 Jan 24/2006 Jan 24/2006 Jan 24/2006 Jan 24/2006 Jan 24/2006 Jan 24/2006 Jan 24/2006 Jan 24/2006 Jan 24/2006 Jan 24/2006 Jan 24/2006 Jan 24/2006 Jan 24/2006 Jan 24/2006 Jan 24/2006 Jan 24/2006 701 702 703 704 705 706 707 708 709 710 711 712 713 714 715 716 717 Jan 24/2006 Jan 24/2006 Jan 24/2006 Jan 24/2006 Jan 24/2006 Jan 24/2006 Jan 24/2006 Jan 24/2006 Jan 24/2006 Jan 24/2006 Jan 24/2006 Jan 24/2006 Jan 24/2006 Jan 24/2006 Jan 24/2006 Jan 24/2006 Jan 24/2006 72-00 LEP Page 5 Jan 24/2006 PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3045542 LIST OF EFFECTIVE PAGES CHAPTER SECTION PAGE DATE 718 719 720 721 722 723 724 725 726 Jan 24/2006 Jan 24/2006 Jan 24/2006 Jan 24/2006 Jan 24/2006 Jan 24/2006 Jan 24/2006 Jan 24/2006 Jan 24/2006 72-00-00 Approved Repairs 801 802 803 804 805 806 807 808 809 810 811 812 blank Mar 01/2002 Mar 01/2002 Mar 01/2002 Mar 01/2002 Mar 01/2002 Mar 01/2002 Mar 01/2002 Mar 01/2002 Mar 01/2002 Jan 16/2004 Jan 16/2004 Mar 01/2002 72-00-01 Fault Isolation 101 102 103 104 105 106 107 108 109 110 111 112 113 114 115 116 117 118 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 CHAPTER SECTION PAGE 119 120 121 122 123 124 125 126 127 128 129 130 131 132 133 134 135 136 137 138 139 140 141 142 143 144 145 146 147 148 149 150 151 152 153 154 155 156 157 158 159 72-00 LEP DATE Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Page 6 Jan 24/2006 PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3045542 LIST OF EFFECTIVE PAGES CHAPTER SECTION 72-00-02 Fault Isolation PAGE DATE 160 161 162 163 164 165 166 167 168 169 170 171 172 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 Nov 04/2005 101 102 103 104 105 106 107 108 blank 109 110 blank 111 112 113 114 115 116 117 118 119 120 121 122 123 124 125 126 127 Oct 20/2000 Sep 03/99 Oct 20/2000 Oct 20/2000 Sep 03/99 Sep 03/99 Sep 03/99 Sep 03/99 Sep 03/99 Sep 03/99 Sep 03/99 Sep 03/99 Sep 03/99 Sep 03/99 Sep 03/99 Sep 03/99 Sep 03/99 Sep 03/99 Sep 03/99 Sep 03/99 Sep 03/99 Sep 03/99 Sep 03/99 Sep 03/99 Sep 03/99 Sep 03/99 Sep 03/99 CHAPTER SECTION PAGE DATE 128 129 130 131 132 133 134 135 136 137 138 139 140 141 142 143 144 145 146 147 148 149 150 151 152 153 154 155 156 157 158 159 160 161 162 163 164 165 166 167 168 Sep 03/99 Sep 03/99 Sep 03/99 Sep 03/99 Sep 03/99 Sep 03/99 Sep 03/99 Sep 03/99 Sep 03/99 Sep 03/99 Sep 03/99 Sep 03/99 Sep 03/99 Sep 03/99 Sep 03/99 Sep 03/99 Sep 03/99 Sep 03/99 Sep 03/99 Sep 03/99 Sep 03/99 Sep 03/99 Sep 03/99 Sep 03/99 Sep 03/99 Sep 03/99 Sep 03/99 Sep 03/99 Sep 03/99 Sep 03/99 Sep 03/99 Sep 03/99 Sep 03/99 Sep 03/99 Sep 03/99 Sep 03/99 Sep 03/99 Sep 03/99 Sep 03/99 Sep 03/99 Sep 03/99 72-00 LEP Page 7 Jan 24/2006 PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3045542 LIST OF EFFECTIVE PAGES CHAPTER SECTION PAGE DATE 169 170 171 172 173 174 175 176 177 178 179 180 181 182 183 184 185 186 187 188 189 190 Sep 03/99 Sep 03/99 Sep 03/99 Sep 03/99 Sep 03/99 Sep 03/99 Sep 03/99 Sep 03/99 Sep 03/99 Sep 03/99 Sep 03/99 Sep 03/99 Sep 03/99 Sep 03/99 Sep 03/99 Sep 03/99 Sep 03/99 Sep 03/99 Sep 03/99 Sep 03/99 Sep 03/99 Sep 03/99 72-00 LEP Page 8 Jan 24/2006 PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3045542 TABLE OF CONTENTS SUBJECT PAGE ENGINE - DESCRIPTION AND OPERATION 72-00-00 1. General 1 2. Description 1 A. Reduction Gearbox 1 B. Turbomachinery 9 C. Accessory Drives 11 D. Identification of Engine Bearings, Flanges and Stations 13 E. Oil System 19 F. Fuel and Control System 26 G. Propeller Control System 46 H. Inlet Temperature and Torque Sensing Systems 48 I. Ignition System 48 J. Performance Indicating System 51 K. Air System 53 3. Operation (A summary of the functions previously described) 64 4. Engine - Approved Fuels 64 A. Use of Approved Fuels 64 B. High Temperature Stability 71 C. Quality 71 D. Additives 71 E. Acceptable Fuels (Unrestricted Use) 75 F. Acceptable Fuels (Restricted Use) 77 5. G. Alternate/Emergency Fuels 78 Engine - Approved Lubricating Oils 78 A. General 78 B. Approved Oils 79 72-00 CONTENTS Page 1 Jan 24/2006 PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3045542 TABLE OF CONTENTS SUBJECT PAGE ENGINE - DESCRIPTION AND OPERATION (Cont’d) 72-00-00 C. Dupont Oil Blue Dye (PWC05-026) 80 D. Oil Drain Period 80 E. Oil Analysis 83 ENGINE - FAULT ISOLATION 72-00-00 1. General 101 2. Consumable Materials 101 3. Special Tools 101 4. Fixtures, Equipment and Supplier Tools 101 5. Fault Isolation Chart Locations 101 ENGINE - MAINTENANCE PRACTICES 72-00-00 1. General 201 2. Consumable Materials 201 3. Special Tools 202 4. Fixtures, Equipment and Supplier Tools 202 5. Standard Torques 202 6. Torque Wrenches 203 A. General 203 B. Standard Torque Wrenches and Extensions 203 C. Power Torque Wrenches 205 7. General Torque Recommendations 206 A. Oil Lubricated Parts 206 B. Self-locking Nuts and Helical Coil Inserts 206 C. Castellated Nuts 207 D. Standard and Stepped Studs 207 E. Tube Nuts 207 72-00 CONTENTS Page 2 Jan 24/2006 PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3045542 TABLE OF CONTENTS SUBJECT PAGE ENGINE - MAINTENANCE PRACTICES (Cont’d) 8. 9. 10. 11. 12. 13. 14. 72-00-00 Locking 207 A. General 207 B. Keywashers 207 C. Lockwire 210 D. Retaining Rings 212 Marking of Parts 212 A. General 212 B. Permanent Marking 217 C. Temporary Marking 217 Lubrication 219 A. 219 General Tube-to-Boss Elbows, Elbow Adapters, Elbow Assemblies, Tees and Tee Assemblies 219 A. Removal 219 B. Installation 219 Straight Nipples or Adapters, Bulkhead Couplings and Tube Connector Nipples 221 A. 221 Installation Wiring Harness Connectors 221 A. General 221 B. Installation Procedure 221 Inspection 225 A. General 225 B. Inspection Procedures 225 C. Inspection Terms 226 D. Inspection Gages 226 72-00 CONTENTS Page 3 Jan 24/2006 Fixtures.SERVICING 72-00-00 1. Equipment and Supplier Tools 302 5. Bearings 233 17. Precautions 232 16. Installation of Reduction Gearbox in Shipping Container 313 F.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. Magnetic Particle Inspection 231 F. Oil and Air Filters 232 Cleaning 232 A. Debris Analysis and Material Specifications 233 A. Preparation of Shipping Container for Service or Storage 302 B. Filter Patch Check Debris Inspection/Analysis 233 C. Fluorescent Penetrant Inspection 231 G. Consumable Materials 301 3. Removal of Turbomachinery from Shipping Container 314 72-00 CONTENTS Page 4 Jan 24/2006 . General 301 2. 3045542 TABLE OF CONTENTS SUBJECT PAGE ENGINE . General 233 B. Installation of Engine in Shipping Container 303 D. Removal of Engine from Shipping Container 302 C. Material Specifications 235 E. Removal of Reduction Gearbox from Shipping Container 308 E. Chip and Flake Analysis 234 D.MAINTENANCE PRACTICES (Cont’d) 15. General 232 B. Inspection of Fuel. Removal/Installation 302 A. Laboratories 250 ENGINE . 72-00-00 E. Special Tools 301 4. General Engine Storage/Preservation Procedure 320 B. Oil System Preservation 323 C. 11. Depreservation (Accessories) 329 Shipping 329 A. 8. 7. Accessories 325 E. 72-00-00 G. 333 Procedure Oil System Flushing and Filling 335 A. Fuel System 324 D. General 329 B. Oil Filling Procedure 337 B. 12. Installation of Turbomachinery in Shipping Container 319 Preservation/Depreservation 320 A. 335 Procedure Oil System Filling 337 A. Replenishing Empty Oil System 338 Oil Level Check and Top-up 339 A. 10. Top-up 339 72-00 CONTENTS Page 5 Jan 24/2006 . 9. Desiccant and Humidity Indicator Reactivation 326 F. 3045542 TABLE OF CONTENTS SUBJECT PAGE ENGINE . General Oil Level Check 339 B. Shipping Method 331 Oil Draining 332 A.Replacement 333 A.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. Depreservation (Engine) 326 G. 332 Main Oil Tank and/or RGB Chip Collector .SERVICING (Cont’d) 6. General 401 2. Procedure 340 ENGINE . Engine from Stand (PWC34200) 402 6. Engine in Airframe 403 B. Engine Ground Running Operating Limits 501 6. Consumable Materials 501 3. Equipment and Supplier Tools 501 5. Installation 403 A.REMOVAL/INSTALLATION 72-00-00 1. Fixtures. Consumable Materials 401 3. Engine/Component Replacement Test Requirements 501 7. Starting 503 A. Special Tools 501 4. Prestart 503 B. Wet Motoring 503 72-00 CONTENTS Page 6 Jan 24/2006 . Overtorque and Overtemperature Limits 502 8. Engine from Airframe 402 B. 3045542 TABLE OF CONTENTS SUBJECT PAGE ENGINE . General 501 2. Special Tools 401 4.ADJUSTMENT/TEST 72-00-00 1. Removal 402 A. 72-00-00 Oil Consumption Trend Monitoring 340 A.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. Engine in Stand (PWC34200) 409 ENGINE . Fixtures.SERVICING (Cont’d) 13. Equipment and Supplier Tools 402 5. General 340 B. D.O. Flight IDLE/MIN NP GOVERNING 508 F. and MAX NP Governing 508 G. Power Assurance Check 512 K. Autofeather and Uptrim (both engines running) 509 J. Equipment and Supplier Tools 601 5. Consumable Materials 601 3. Special Tools 601 4. 10. Leak Check 508 C.ADJUSTMENT/TEST (Cont’d) C. General 601 2.INSPECTION/CHECK 72-00-00 1. 3045542 TABLE OF CONTENTS SUBJECT PAGE ENGINE . 9. Periodic Inspection 602 6. REVERSE/MIN.Service Life 602 7.NH GOVERNING 508 D. Flight IDLE . Oil Pressure 507 B. Ground IDLE . Engines with Defects Outside Specified Limits 602 72-00 CONTENTS Page 7 Jan 24/2006 .PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 72-00-00 Dry Motoring (to purge engine of fuel after wet motoring run or in the event of fire occurring in the engine after starting or permit a compressor wash to be carried out. EEC Manual Reversion 509 I. 507 Procedure Checks 507 A.) 504 Start 504 Shutdown 507 A.P or ITT/T6 Limit) 509 H.NH GOVERNING 508 E. Fixtures. Rotor Components . Acceleration Check 514 ENGINE . Maximum Forward Governing (T. Intercompressor Case Air Plenum 627 M. Low Pressure Impeller 620 H. Light Source 617 D. High Pressure Impeller 623 I.INSPECTION/CHECK (Cont’d) 8. Starter-generator Drive Gear 625 L. LP Impeller 603 B. Troubleshooting 619 G. Second-stage Power Turbine Blades and Vane Ring 632H S. LP Turbine Blades and Stator Assembly 632C P. RGB Second-stage Gears (Bull Gear and Layshaft Pinions) 632M 72-00 CONTENTS Page 8 Jan 24/2006 .Foreign Object Damage 603 A. 632H R. Guide Tubes 619 F. Side-viewing Adapter 616 C. 5 Bearing Cavity N. 9. 629 Combustion Chamber Liner Assembly. Fuel Pump and Oil Pump Drive Bevel Gears 623 J. General 616 B.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. HP Turbine Vane Ring Segments and HP Turbine Blades 631 O. Camera 617 E. 632E Power Turbine Stator Assembly and First-stage Blades Q. 3045542 TABLE OF CONTENTS SUBJECT PAGE ENGINE . HP Impeller 609 Borescope Inspection 616 A. No. Accessory Drive Bevel Gears (Towershaft) 625 K. RGB First-stage Helical and Input Shaft Gears 632I T. 6 and 7 Bearing Vent Transfer Tube. No. 72-00-00 Low Pressure and High Pressure Impellers . General 701 2.and Second-stage Power Turbine Vanes 681 I. Combustion Chamber (Small Exit Duct. Consumable Materials 701 3. LP Turbine Stator . External Wash 702 B. Acceptable Conditions 685 B.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. Engine Cleaning 702 A. Compressor Wash 702 72-00 CONTENTS Page 9 Jan 24/2006 . General 632R B. First.CLEANING/PAINTING 72-00-00 1. High Pressure (HP) Turbine Vane Segments 643 D. Non-acceptable Conditions 688 12. HP Turbine Blades 646 E. Fixtures.INSPECTION/CHECK (Cont’d) 10. 3045542 TABLE OF CONTENTS SUBJECT PAGE ENGINE . Inner and Outer Liner Assemblies) 632R C. Equipment and Supplier Tools 701 5. Special Tools 701 4. Cracks in Gas Generator Case Firewall Support Ring 689 A. 72-00-00 Hot Section Component Borescope Inspection Criteria 632R A. LP Turbine Blades 678 H. Cracks in Turbine Support Case Inner Wall 688 13. First. 678 G.and Second-stage Power Turbine (PT) Blades 685 Gear Teeth Inspection 685 A. HP Turbine Shroud Segment 654 F. 689 Visual Inspection ENGINE . 11. Equipment and Supplier Tools 801 5. Procedure 803 Stud Replacement 806 A. Special Tools 801 4. 7.CLEANING/PAINTING (Cont’d) C. 811 Procedure ENGINE . Procedure (oversize insert replacement) 802 6. General 802 B. Consumable Materials 801 3. Procedure (same size insert replacement) 802 C. 3045542 TABLE OF CONTENTS SUBJECT PAGE ENGINE . Procedure 810 Jacking Insert Replacement 811 A. General 809 B. 72-00-01 General 101 72-00 CONTENTS Page 10 Jan 24/2006 . Helical Coil Insert Replacement 802 A. 808 Procedure Chromate Surface Repair of Magnesium 809 A.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 806 Procedure Stud Hole Repair 808 A.FAULT ISOLATION 1. General 801 2.APPROVED REPAIRS 72-00-00 1. 10. 9. 8. Turbine Wash 72-00-00 719 ENGINE . ’Keensert’ Insert Replacement 803 A. 808 Procedure Anodic Film Repair of Aluminum 808 A. 11. Fixtures. PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO.FAULT ISOLATION 72-00-02 1. Fault Isolation Steps 106 72-00 CONTENTS Page 11/12 Jan 24/2006 . Consumable Materials 101 3. 3045542 TABLE OF CONTENTS SUBJECT PAGE ENGINE . Equipment and Supplier Tools 101 5. Special Tools 101 4. Consumable Materials 101 3. Electronic Fuel Control System 101 A. Fault Isolation Fault Index 101 ENGINE .FAULT ISOLATION (Cont’d) 72-00-01 2. Fixtures. Equipment and Supplier Tools 101 5. Special Tools 101 4. 103 Procedure 7. Fixtures. General 101 2. Fault Isolation Fault Index 104 8. 101 6. Procedures Servicing Connectors with Aircraft Electrical Power On 103 A. . A mounting pad is provided on the right side of the front housing to accommodate an electric feathering pump. A propeller brake is fitted to the left pad. At the one and eleven o’clock positions on the front housing flange are two lifting brackets. Reduction Gearbox (Ref. The engine has two modules: a reduction gearbox module and a turbomachinery module. 1 and 2) The PW127H turboprop engine has two centrifugal impellers driven by independent axial turbines. Figs. 3045542 ENGINE . General (Ref. Reduction is accomplished by a two-stage geartrain. front roller bearing of the input shaft and the front roller bearings of both first-stage helical gears. Description A. (1) Front Housing The front housing holds the front roller bearings for the two second-stage gearshafts and the propeller shaft. The data plate of the reduction gearbox module is attached to the left side of the front housing. Push buttons on each solenoid valve allow manual operation of the brake release system during maintenance or when an electrical failure has occurred. Figs. In front of each gearshaft are mounting pads. 72-00-00 Page 1 ENGINE . 3. These pads are provided with seal drains blanked off with flight closures. Provision is made for the installation of airframe equipment on the engines. The modules are joined to form a rigid unit. The propeller brake (Ref. Fig.DESCRIPTION AND OPERATION 1.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 4 and 5) The reduction gearbox has an accessory drive cover and three housings: the front housing. The propeller shaft seal is under a cover on the front housing. the rear housing and the input housing (which together make up the housing set). (2) Rear Housing The rear housing carries the second-stage reduction gear and drive pinions. 2. and the ball thrust bearing for the propeller shaft. 5) is a hydromechanical type actuated by solenoid valves which are energized by an airframe-mounted control unit which controls the braking and unbraking sequences.DESCRIPTION AND OPERATION Nov 04/2005 . second-stage reduction gear rear roller bearings. The brake is used to immobilize the propeller when the engine is running and providing electricity and compressor air for off-engine use. a reverse flow annular combustor and a two-stage power turbine which provides the drive for the reduction gearbox. propeller shaft rear roller bearing. The pad has oil ports that are connected to an internal oil tank which is part of the rear housing. DESCRIPTION AND OPERATION Nov 04/2005 . 3045542 NP PULSE PICK−UP PROBE ENGINE FRONT MOUNTING PAD TORQUE MOUNTING PAD AMBIENT PRESSURE TRANSDUCER TOTAL INLET PRESSURE TRANSDUCER OIL INLET (FROM REMOTE OIL COOLER) MAIN OIL PRESSURE OIL PRESSURE REGULATING VALVE LOW OIL PRESSURE SENSOR SWITCH FUEL PUMP OUTLET FILTER T6 BUS−BARS MECHANICAL FUEL CONTROL UNIT MOUNTING PAD FUEL INLET OIL PRESSURE FILTER IMPENDING BYPASS INDICATOR OIL PRESSURE FILTER CHIP DETECTOR GEARBOX DATA PLATE OIL LEVEL INDICATOR ENGINE ELECTRONIC CONTROL TORQUE SENSOR C61309B Typical Engine Figure 1 (Sheet 1 of 2) 72-00-00 Page 2 ENGINE .PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 6 & 7 BEARING OIL PUMP OIL COOLER) SCAVENGE PIPE PACK PRESSURIZING AIR SUPPLY PIPE FUEL PUMP INLET FILTER GEARBOX OIL PRESSURE PIPE IGNITER PLUG ENGINE FRONT MOUNTING PAD HIGH PRESSURE ROTOR (NH) PULSE PICK−UP PROBE STARTER MOUNTING PAD TOTAL INLET TEMPERATURE SENSOR OIL SCAVENGE FILTER IMPENDING BYPASS INDICATOR OIL TO FUEL HEATER ENGINE DATA PLATE T6 TRIM RESISTOR ELECTRIC FEATHERING PUMP MOUNTING PAD C61311A Typical Engine Figure 1 (Sheet 2) 72-00-00 Page 3 ENGINE .PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3045542 REAR ENGINE MOUNTING PAD ENGINE FRONT MOUNTING PAD TORQUE MOUNTING PAD ACCESSORY GEARBOX BREATHER TUBE TORQUE SENSOR IGNITION EXCITER AIR INLET IGNITION HARNESS REDUCTION GEARBOX SCAVENGE OIL FILTER OIL OUTLET (TO REMOTE NO.DESCRIPTION AND OPERATION Nov 04/2005 . 5/T1.8 P1. Flanges and Stations Figure 2 (Sheet 1 of 2) 72-00-00 Page 4 ENGINE .5 BEARINGS FLANGES A B P2/T2 1 C 2 D C11121D_1 Bearings. 3045542 PRESSURE/TEMPERATURE STATIONS P0/T0 P1/T1 P1.DESCRIPTION AND OPERATION Nov 04/2005 .8/T1.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. DESCRIPTION AND OPERATION Nov 04/2005 . 3045542 P4/T4 P2. Flanges and Stations Figure 2 (Sheet 2) 72-00-00 Page 5 ENGINE .PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO.5 E 6 5 4 F P8/T8 P5/T5 P3/T3 3 P7/T7 P6/T6 7 K C11121D_2 Bearings.5/T2. DESCRIPTION AND OPERATION Nov 04/2005 . 3045542 TOP MOUNTING PAD ACCESSORY DRIVE COVER REAR HOUSING LIFTING BRACKETS INPUT DRIVE HOUSING FRONT HOUSING PROPELLER SHAFT PROPELLER SHAFT FLANGE ENGINE MOUNTING PAD ENGINE MOUNTING PAD TORQUE MOUNT FEATHERING PUMP MOUNT PAD DATA PLATE PROPELLER SHAFT SEAL DRAIN GEARSHAFT COVERS TORQUE MOUNT CHIP DETECTOR AND STRAINER C38713 Reduction Gearbox .PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO.3⁄4 View Figure 3 72-00-00 Page 6 ENGINE . PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3045542 PROPELLER MOUNTING FLANGE REDUCTION GEARBOX FRONT HOUSING REDUCTION GEARBOX REAR HOUSING OVERSPEED GOVERNOR DRIVE GEARSHAFT 135 TOOTH SECOND STAGE SPUR GEAR PROPELLER SHAFT SEAL PROPELLER SHAFT 38 TOOTH SECOND STAGE SPUR GEAR PROPELLER SHAFT FRONT ROLLER BEARING IDLER DRIVE SPUR GEARSHAFT INTERGRATED DRIVE GENERATOR GEARSHAFT PROPELLER BRAKE COUPLING 38 TOOTH SECOND STAGE SPUR GEAR FIRST STAGE HELICAL GEAR HELICAL INPUT GEARSHAFT FIRST STAGE HELICAL GEAR C69157 Reduction Geartrain Figure 4 72-00-00 Page 7 ENGINE .DESCRIPTION AND OPERATION Nov 04/2005 . 3/4 View Figure 5 72-00-00 Page 8 ENGINE .PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO.DESCRIPTION AND OPERATION Nov 04/2005 . 3045542 MANUAL CONTROL SOLENOID VALVES PROPELLER BRAKE C38712 Propeller Brake and Propeller Brake Control . contained in six casings (Ref. which is also driven by the 135-tooth second-stage gear.DESCRIPTION AND OPERATION Nov 04/2005 . 2). 72-00-00 Page 9 ENGINE . The casings are bolted together at flanges (Ref. The propeller (NP) pulse pickup probe is installed in a mounting pad at the 11 o’clock position. On the bottom right side is a pad for the chip detector and oil strainer. The engine oil tank forms part of the casing. Fig. the propeller shaft. The case contains two bearings (No. and the fuel-cooled oil cooler. and driven by. Fig. The propeller valve module is mounted on a pad behind. The rear inlet case joins the front case to the low pressure (LP) diffuser case at flange D. Turbomachinery The turbomachinery consists of four sections. 3045542 The front engine three main mounting pads are located as follows: two on either side of the housing.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. The front inlet case has the engine electronic control (EEC) and autofeather unit (AFU) mounted on the left side. 6). (4) Accessory Drives The overspeed governor/pump assembly is mounted on the right pad and driven by the 135-tooth second-stage gear. Torque mounts are located at the 5 and 7 o’clock positions on the housing. An access plate is on its top surface. 1 and 2) and seals for the power turbine shaft. (1) Air Inlet Section The air inlet section consists of the front inlet case and the rear inlet case bolted together at flange C. The forward flange of the front inlet case has two integral lifting brackets and is connected to the RGB at flange B. and the third at the top center. Another chip detector and strainer are installed on the upper left side. (3) Input Drive Housing The input drive housing carries the rear roller bearings of the input driveshaft and both layshafts. Two torque sensors are mounted on pads located opposite one another on the horizontal centerline of the input drive housing. B. An oil cooled integrated drive generator (IDG) is mounted on the left pad and is driven by the idler gear. ignition exciters and turbomachinery data plate on the right side. Mounting pads are provided for accessories. The accessory drive cover is mounted on the top rear face. 3045542 OIL TANK TURBINE SECTION INTERCOMPRESSOR CASE COMPRESSOR SECTION GAS GENERATOR CASE INLET SECTION COMBUSTION SECTION TURBINE SUPPORT FUEL MANIFOLD CASE & NOZZLES DIFFUSER EXIT DUCTS REAR INLET CASE FRONT INLET CASE L. DIFFUSER CASE C69158A Turbomachinery Figure 6 72-00-00 ENGINE .DESCRIPTION AND OPERATION Page 10 Nov 04/2005 .P.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. which contains the LP impeller. The central PT shaft is supported by the No. Provision is made for hand cranking the HP rotor using a socket wrench extension tool in the end of the starter-generator driveshaft. No. 3045542 (2) Compressor Section The compressor section comprises the low pressure (LP) and high pressure (HP) independent centrifugal impellers. 5 (roller) bearings. 3 and 4) are housed in the intercompressor case. 6 (roller) bearings. 4 bearing. Accessory Drives (Ref. Access is gained after removal of a cover opposite the starter-generator. 7) An inclined bevel gearshaft (5) transmits drive from a gear (4). 7 (roller) bearings. The fuel manifold is mounted around the exterior of the gas generator case. to the intercompressor case. The gas generator case incorporates an air bleed pad through which P3 air is supplied for off-engine use at low power and during starting. Two igniter plug bosses are provided on the gas generator case. A lifting bracket is located at the twelve o’clock position on flange K of the gas generator case. A spur gear (14) drives the fuel pump driveshaft (6) through gear (11). Two ball bearings (No. and another spur gear (7) meshes with gear (10) on the starter-generator driveshaft (9). A Y-adapter and non-return valve are located at the 12 o’clock position on the intercompressor case to supply low pressure air for use in the environment control system of the aircraft. C. secured to the impeller (3) forward of No. Concentric shafts connect the two-stage power turbine to the gearbox and the single-stage LP and HP turbines to the impellers.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. and the power turbines (PT) in the turbine support case. to the bevel gear (2) of the accessory drive coupling gearshaft (1). (3) Combustion Section The annular reverse-flow combustion chamber is contained in the gas generator case. Fig. The No. The centrifugal breather impeller (8) is mounted on the gearshaft (1). with spray nozzles which protrude into the combustion chamber liner. 72-00-00 ENGINE . The HP turbine shaft (integral with impeller) is supported by the No. 1 (ball). (4) Turbine Section The LP and HP turbines are housed in the rear of the gas generator case. with corresponding bosses in the liner. 4 (ball) and No. These are contained within the LP diffuser case (flange D to E) and the intercompressor case (flange E to F) and the front of the gas generator case (flange F to K). 3 (ball) and No. Diffuser pipes connect the diffuser case. 5 roller bearing is contained in the gas generator case. 2 (roller) and No. The intermediate LP turbine shaft is supported by the No. The oil pumps are driven by driveshaft (13) through bevel gears (12) and (15).DESCRIPTION AND OPERATION Page 11 Nov 04/2005 . DESCRIPTION AND OPERATION Page 12 Nov 04/2005 .PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3045542 2 1 10 7 14 16 9 11 6 12 8 5 13 15 3 4 C11186C Turbomachinery Accessory Drive Geartrain Figure 7 72-00-00 ENGINE . TABLE 1. 8) All the bearings used in the engine have position numbers from 1 thru 30 as per steps (2). Main Bearing Identification BEARING NO. Engine Main Bearings The main bearings in the turbomachinery have numbers per Table 1. Accessory Drive Coupling Gearshaft Bevel Gear HP Impeller Bevel Gear Gearshaft Fuel Pump Driveshaft Spur Gear Centrifugal Breather Impeller Starter-generator Driveshaft Spur Gear Spur Gear Bevel Gear Oil Pump Driveshaft Spur Gear Bevel Gear Bevel Gear (Ref. 6. 12. 3. (3) and (4). 4.DESCRIPTION AND OPERATION Page 13 Nov 04/2005 . NOTE: (2) The term ‘‘Not Used’’ is given to bearing numbers which are not. Flanges and Stations (1) Engine Bearing Identification (Ref. 5. POSITION TYPE 1 Power Turbine Shaft Ball 2 Power Turbine Shaft Roller 3 Low-pressure Impeller Ball 4 High-pressure Impeller Ball 5 High-pressure Impeller Roller 6 Low-pressure Turbine Roller 7 Power Turbine Shaft Roller 72-00-00 ENGINE . 3045542 Key to Figure 7 1. 8. Fig. 14. D.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 10. 15. 16. 11. 7. applicable to the engine model specified in this manual.) Identification of Engine Bearings. 9. 13. at this time. 2. 19 BEARING A No. 8 BEARING C32417C_1 Bearing Identification Figure 8 (Sheet 1 of 4) 72-00-00 ENGINE .DESCRIPTION AND OPERATION Page 14 Nov 04/2005 . 18 BEARING No.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 15 BEARING B B A No. 3045542 No. 9 BEARING No. 2 BEARING No.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO.DESCRIPTION AND OPERATION Page 15 Nov 04/2005 . 4 BEARING No. 7 BEARING No. 5 BEARING No. 3045542 No. 25 BEARING (REAR) No. 28 BEARING (REAR) No. 1 BEARING No. 3 BEARING No. 28 BEARING (FRONT) No. 30 BEARING No. 25 BEARING (FRONT) No. 27 BEARING No. 6 BEARING C32417C_2 Bearing Identification Figure 8 (Sheet 2) 72-00-00 ENGINE . 29 BEARING (LOWER) No. 14 BEARING NO.12 BEARING NO.22 BEARING (FRONT) NO.DESCRIPTION AND OPERATION Page 16 Nov 04/2005 .23 BEARING (REAR) B−B C33359 Bearing Identification Figure 8 (Sheet 3) 72-00-00 ENGINE .13 BEARING NO.9 BEARING NO.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO.23 BEARING (FRONT) NO.22 BEARING (REAR) SECTION NO.12 BEARING NO.20 BEARING (REAR) NO.11 BEARING NO.20 BEARING (FRONT) NO.13 BEARING NO.8 BEARING SECTION A−A FWD NO.14 BEARING NO. 3045542 FWD NO.11 BEARING NO. 24 BEARING (REAR) NO. 26 BEARING (REAR) NO. 26 BEARING (FRONT) NO.DESCRIPTION AND OPERATION Page 17 Nov 04/2005 . 3045542 F W D NO. 25 BEARING (FRONT) NO.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 24 BEARING (FRONT) NO. 25 BEARING (REAR) SECTION C−C C32419 Bearing Identification Figure 8 (Sheet 4) 72-00-00 ENGINE . 3045542 (3) Reduction Gearbox Bearings The RGB bearings have numbers per Table 2. POSITION TYPE 8 Input Drive Shaft Roller 9 Input Drive Shaft Roller 10 NOT USED NOT USED 11 First-stage Helical Gear Roller 12 First-stage Helical Gear Roller 13 Second-stage Spur Gearshaft (Pinion Gear) Roller 14 Second-stage Spur Gearshaft (Pinion Gear) Roller 15 Propeller Shaft Roller 16 NOT USED NOT USED 17 NOT USED NOT USED 18 Propeller Shaft Ball 19 Propeller Shaft Roller 20 (Front and Rear) Overspeed-governor Drive Gearshaft Roller 21 NOT USED NOT USED 22 (Front and Rear) Idler Drive Gearshaft Roller 23 (Front and Rear) Integrated Drive Generator Gearshaft Roller (4) Accessory Gearbox Bearings The accessory gearbox bearings. Accessory-gearbox Bearing Identification BEARING NO. in the upper section of the rear inlet case. Reduction-gearbox Bearing Identification BEARING NO. POSITION TYPE 24 (Front and Rear) Starter-generator drive Gearshaft Roller 25 (Front) Main-accessory-drive Gearshaft Roller 25 (Rear) Main-accessory-drive Gearshaft Ball 26 (Front) Fuel-pump Drive Shaft Roller 26 (Rear) Fuel-pump Drive Shaft Ball 27 Oil-pump Drive Shaft Ball 28 (Front) Accessory-drive Horizontal Gearshaft Roller 72-00-00 ENGINE . have numbers per Table 3.DESCRIPTION AND OPERATION Page 18 Nov 04/2005 . and in the angle drive gearbox which is on the intercompressor case. TABLE 2.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. TABLE 3. PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. Fig. contents gage and scavenge chip detector. The tank has a filler neck and cap. taken from a tapping downstream of the check valve. the valve opens a port. on the right side of the rear inlet case. Oil is bled from the main pressure line by the port and returned to the inlet side of the pump. Oil System (Ref. If oil output pressure. The oil is stored in a tank that is integral with the rear inlet case. in a pack with the scavenge pump. Figs. From the filter the oil flows in two directions: to the oil pressure check valve housing and to the fuel heater (then. An integral cast passage connects the oil tank to the inlet side of the pump. The pressure regulating valve (Ref. which supplies oil to the reduction gearbox and turbomachinery. in turn. via a restrictor to an oil pressure transducer and to the low oil pressure switch. From the cooler the oil flows via a heat exchanger (airframe component) to the pressure regulating valve and the pressure filter. It maintains a constant oil pressure above and in relation to the air pressure in the No. The pressure filter has a bypass valve to ensure adequate flow if the filter is blocked. 9 through 13) The oil system is a wet sump system. the scavenge system. overcomes the air pressure plus spring pressure. reducing output pressure. closing the bleed port at the desired pump output pressure. The check valve output pressure is also connected. Airframe-supplied tubes connect the outlet to the airframe air cooled oil cooler. Air pressure plus spring pressure overcomes the reduced oil pressure. A pressure relief valve returns oil to the tank to prevent a pressure surge during cold starting.DESCRIPTION AND OPERATION Page 19 Nov 04/2005 . to the fuel-cooled oil cooler). 3045542 TABLE 3. Accessory-gearbox Bearing Identification (Cont’d) BEARING NO. Figs. an indicator warns of impending blockage. cooled by an aircraft mounted air-cooled oil cooler and an integral fuel-cooled oil cooler. 72-00-00 ENGINE . The system is composed of three subsystems: the pressure system. which returns the used oil to the tank and the vent and breather system which vents the bearing cavities and removes oil from the vented air (Ref. 9 and 10). (1) Pressure System (a) Turbomachinery A spur gear type pressure pump is mounted. 11) consists of a piston valve and spring in a ported sleeve. 3 and 4 bearing cavity. POSITION TYPE 28 (Rear) Accessory-drive Horizontal Gearshaft Ball 29 (Upper) NOT USED NOT USED 29 (Lower) Accessory Drive Housing Roller 30 Accessory-drive Lower Bevel Gearshaft Ball E. Schematic Figure 9 (Sheet 1 of 2) 72-00-00 ENGINE .DESCRIPTION AND OPERATION Page 20 Nov 04/2005 .PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3045542 TO REDUCTION GEARBOX OIL COOLER OIL TO FUEL HEATER OIL PRESSURE TRANSDUCER AIR FROM NO.3 & 4 BEARING CAVITY LOW OIL PRESSURE SWITCH PRESSURE REGULATING VALVE RESTRICTOR MAIN OIL PRESSURE FILTER IMPENDING BYPASS INDICATOR PRESSURE REIEF VALVE FROM OIL COOLER VIA IDG HEAT EXCHANGER TO OIL COOLER OIL PUMP (PRESSURE) C69190_1A Turbomachinery Oil System . S AFT FRO ICING STRAINER STRAINER STRAINER VENT ANTI− GRAVITY DRAIN INLET STRUT DRIVESH VENT HAFT ACCESSORY GEARBOX NO. 3045542 CHECK VALVE BLEED LINE RESTRICTOR OIL TEMP.3 & 4 BEARING CAVITY NO.DESCRIPTION AND OPERATION Page 21 Nov 04/2005 .PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO.5 BEARING CAVITY JET PUMP BLOWDOWN GRAVITY DRAIN OIL TANK STRAINER SCREEN CHIP DETECTOR SCAVENGE FROM REDUCTION GEARBOX NO.6 & 7 CAVITY SCAVENGE PUMP PRESSURE OIL SCAVENGE OIL VENT AIR DRAIN AND UNPRESSURIZED OIL C69190_2A Turbomachinery Oil System .1 & 2 BEARING CAVITY NO. BULB STRAINER M H.Schematic Figure 9 (Sheet 2) 72-00-00 ENGINE .6 & 7 BEARING CAVITY NO.P. DESCRIPTION AND OPERATION Page 22 Nov 04/2005 . 3045542 ELECTRIC FEATHERING PUMP PROPELLER VALVE MODULE PUMP RESTRICTOR MAIN OIL PRESSURE FROM TURBOMACHINERY OVERSPEED GOVERNOR OVERSPEED MODE R.B.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO.G. AUXILLARY OIL TANK (PRESSURIZED) GOVERNING MODE DRAIN PRESSURE OIL DISTRIBUTION BY INTERNAL GALLERIES PROPELLER VALVE MODULE PROPELLER ACTUATOR DRAIN CHIP DETECTOR SIGNAL PRESSURE OIL ENGINE OIL (PRESSURE) PROPELLER VALVE MODULE OIL (BOOSTED) SCREEN SCAVENGE OIL REDUCTION GEARBOX REDUCTION GEARBOX SCAVENGE PUMP TURBOMACHINERY REDUCTION GEARBOX SCAVENGE FILTER MAIN OIL TANK IMPENDING BYPASS INDICATOR BYPASS C38658 Reduction Gearbox Oil System .Schematic Figure 10 72-00-00 ENGINE . 4 BEARING CAVITY C31422 Oil Pressure Regulating Valve . 3045542 OIL IN OIL OUT PORT NOT USED BEARING OIL PRESSURE SENSING AIR PRESSURE SENSING FROM NO.DESCRIPTION AND OPERATION Page 23 Nov 04/2005 .3⁄4 Cutaway Figure 11 72-00-00 ENGINE .PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO.3 & NO. This ensures that sufficient pressurized air is available at the bearings to enable the seals and blowdown scavenge system to function correctly and prevent oil flooding. Fig. to the electric feathering pump and the propeller valve module (PVM) pump.DESCRIPTION AND OPERATION Page 24 Nov 04/2005 . 6 and 7 bearing cavity. Fig. Pressure oil is also used to actuate a jet pump which scavenges No. In the overspeed mode. 4. The other part goes through the check valve after 25% NH has been exceeded. 2 bearing area. 6 and 7 bearing cavities when pump outlet pressure is below a minimum value. allowing oil to bypass when the pressure differential across the valve exceeds 40 psig (276 kPa). allowing oil to bypass the core until the temperature reaches 60 to 71°C (140-160°F). One part goes through an internal passage in the housing wall. The auxiliary tank is pressurized when the engine is running. The PVM receives pressure oil from the electric feathering pump and the PVM pump and signal pressure oil from the overspeed governor (when in the governing mode). the valve opens. Within this temperature range bypass flow is cut off and routed through the internal path. From the connection on the rear inlet case. past the temperature bulb and externally to a connection on the rear inlet case. signal pressure oil is drained through the overspeed governor. 1 and 2 bearing cavity passes through a strainer. 5. oil flows through strainers to lubricate the bearings and associated components in the bearing cavities. The oil circuit has two flow paths (bypass and internal) and a valve that controls flow between the paths. Oil from the auxiliary tank is distributed through internal galleries to the reduction and accessory geartrains and bearings. then to the reduction gearbox and oil-cooled AC generator. Oil flows through a restrictor before reaching the strainer in the line to the No. The fuel-cooled oil cooler (Ref. 10) the oil flows into an auxiliary oil tank (which is part of the casting). Pressure oil from the PVM actuates the pitch control mechanism in the propeller.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. oil flows by internal passages to the accessory gearbox through the inlet struts (for de-icing) to the No. 3. 3045542 Oil goes through internal passages to the check valve housing. To ensure the cooler is not over pressurized. the valve stops oil going to the No. Some of the accessory gearbox oil flows via a strainer to lubricate the drive gears and associated components. Oil flowing to the No. and is always full of oil (even when the engine is not running). Oil from the tank flows. by internal passages and tubes. During starting and shutdown. 72-00-00 ENGINE . The valve remains in the open position. After entering the housing. 1 and 2 bearing cavity. (b) Reduction Gearbox Inside the gearbox (Ref. the oil flows in two directions. 12) is a heat exchanger with two flow circuits: engine lubricating oil and fuel. Oil flows through tubes to the oil-to-fuel heater and fuel-cooled oil cooler. The check valve consists of a piston valve and spring in a ported sleeve. From the check valve. DESCRIPTION AND OPERATION Page 25 Nov 04/2005 .Schematic Figure 12 72-00-00 ENGINE . 3045542 OIL OUT OIL IN A FUEL IN FUEL OUT OIL IN OIL OUT DETAIL A OIL OUT TEMPERATURE CONTROL VALVE FUEL OUT FUEL IN OIL IN C63098 Fuel-cooled Oil Cooler .PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 1 bearing cavity is scavenged by gravity. Fig. a fuel pump and a mechanical fuel control unit (MFCU). 3. 2 bearing cavity oil is scavenged through a venturi by gravity aided by pressure oil. The cavity has a chip detector. Fig. which is part of the pump pack on the right side of the rear inlet case. gears and bearings drains into a cavity in the bottom of the reduction gearbox rear housing. From the inlet case. From the scavenge filter. (3) Vent and Breather System The oil tank and No. The No. The tube connects to an internal oilway (which provides anti-icing of the intake) in the front inlet case. The tube is looped upward to prevent gearbox oil from flooding the oil tank when the engine is not running. The No. to the accessory gearbox. F. It also comprises a flow divider and dump valve and fuel nozzle manifold mounted on the gas generator case. 1 and 2 bearing cavity are vented internally. Figs. Oil from the No. draws the oil through an external tube on the left side of the front inlet case.DESCRIPTION AND OPERATION Page 26 Nov 04/2005 . the oil flows to the tank. 6 and 7 bearing cavity oil is scavenged through an external tube connected to the scavenge pump.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. and the No. 4 and 5 bearing cavities is scavenged by gravity and assisted by air (blow-down) from the bearing labyrinth seals. 3045542 (2) Scavenge System (a) Reduction Gearbox Scavenge oil from the gearbox accessories. 14) is made up of a fuel heater. 13) fitted to the pressure and scavenge filters sense pressure filter differential. A scavenge pump. The fuel flow is controlled by the power lever and fuel shut off (condition) lever through two integrated systems: the mechanical fuel system and the electronic fuel system. An indicator warns of impending blockage. which induces a jet-pump action. The impending bypass indicators (Ref. 6 and 7 bearing cavity externally. Fuel and Control System (Ref. the oil flows through a tube to the scavenge pump. which are mounted on the accessory drive casing. then through the scavenge filter. When activated. 72-00-00 ENGINE . a signal gives advance warning of a filter blockage. (1) Engine Fuel System The engine mechanical fuel system (Ref. (b) Turbomachinery Oil from the accessory casing and the No. which is equipped with a valve to bypass the filter in the event of blockage. 14 through 21) The engine fuel and control system governs the power produced by the engine by controlling the fuel flow. A centrifugal oil separator (breather impeller) installed in the accessory gearbox removes oil before vented air is carried by an external tube and discharged into the exhaust. DESCRIPTION AND OPERATION Page 27 Nov 04/2005 .Location Figure 13 72-00-00 ENGINE .PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3045542 LEFT SIDE − MAIN PRESSURE OIL FILTER RIGHT SIDE − SCAVENGE OIL FILTER C30204A Oil System Impending Bypass Indicators . (c) The mechanical fuel control unit (MFCU) (Ref. which move a cam lever when the power lever is advanced. inside 72-00-00 ENGINE . 17 and 18). As the driveshaft speed increases. The MFCU consists of the following components: 1 Power Lever and Cam Assembly: The power lever shaft incorporates two speed set cams. A ball bearing on the governor lever contacts the top of the flyweight bearing assembly. and one end operates against an airflow restrictor to form the governor orifice (Ag). Px is used to pressurize the chamber containing the acceleration bellows. Fuel from the MFCU bypass outlet passes through the jet pump. (b) The fuel pump (Ref. an outlet filter and a bypass valve. A thermal sensor in the fuel circuit operates a valve to regulate the oil flow in order to maintain the required fuel temperature. centrifugal force causes the weights to pivot about their mounting points and contact the bottom face of the bearing assembly. 15) consists of a filter and fin-type heater in two integral housings. The heater housing is divided into two circuits. A spring connects the cam lever to the governor lever and exerts a force on the governor lever as a function of PLA. controls the engine fuel flow and thus the power output. When the power lever is advanced. and as the driveshaft revolves. Fig. Two spur gears pump fuel through the outlet filter.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 16) is a positive displacement spur gear assembly consisting of a fuel ejector (jet pump). This causes the bearing assembly to move upward on the driveshaft and apply pressure to the ball bearing on the governor lever arm. The governor orifice Ag opens whenever the driveshaft speed increases enough to overcome the force applied by the governor lever spring. which flows through the other circuit. mounted on the fuel pump. a self-relieving inlet screen. to maintain a constant inlet pressure.DESCRIPTION AND OPERATION Page 28 Nov 04/2005 . 2 Flyweight Assembly: The flyweights are mounted on a platform on the driveshaft. Figs. 3 Orifices (Fixed and Variable): High pressure compressor discharge pressure (P3) is supplied to the MFCU and metered through a fixed orifice to produce Px pressure. The self-relieving inlet screen. A bypass valve diverts fuel to the outlet port in the event of filter blockage: the differential pressure switch signals the impending blockage and activates a warning. two spur gears. The governor lever is pivoted. increased centrifugal force causes the weights to apply an increasing force against the bearing assembly. the cam applies tension to the spring. when blocked. The fuel pressure differential switch located in the fuel filter housing outlet port activates a warning indicator. lifts from its seat and allows fuel to enter the pump housing. The filter housing contains a bypass valve to ensure an adequate fuel flow in the event of blockage and an indicator to warn of impending blockage. positioned ahead of the main inlet. which applies a force on the governor lever to close Ag. Turbomachinery lubricating oil flows through one circuit to transfer heat to the fuel. Fig. 3045542 (a) The fuel heater (Ref. which parallels Ag. 3045542 the deceleration bellows and the governing bellows. In addition. In EEC mode. opening flapper valve Ag which bleeds and reduces Py pressure around the deceleration bellows (Px pressure in the bellows is not affected). reducing fuel flow until the deceleration stop is contacted. the manual cam holds valve Ap in the closed position and selects a low mechanical governor speed schedule which allows valve Ag to be controlled by the power lever angle (PLA). 5 Mode Cam Select Mechanism: The mode select mechanism is used to transfer control between the EEC and the MFCU. Pressure differential between inside (Px) and outside (Py) pressures causes the deceleration bellows to expand and reduce fuel flow. Py pressurizes the chamber containing the deceleration and governing bellows and is tapped off (then vented to atmosphere) via the governor (Ag) and stepper motor (Ap) flapper valve orifices. by the stepper motor. The bellows expand. As Px increases. An increase in Px pressure acting on the evacuated acceleration bellows increases fuel flow. when the EEC is not operating. In manual mode. This moves the bellows away from the stop into the governing range to control fuel flow at the selected power level. a Py tapping is connected to the overspeed governor. flapper valves Ag and Ap are closed. this equalizes and increases Px and Py air pressures. the valve closes and Py pressure increases. the acceleration bellows contract. and is metered through a fixed orifice to produce Py pressure. Movement of either flapper valve changes Py with respect to Px and repositions the bellows assembly. When governing. a high mechanical governor speed schedule is selected by the EEC cam to close valve Ag and allow the EEC to control parallel valve Ap through the stepper motor. The system is activated automatically by the EEC when a system fault occurs and also by cockpit command. Py is reduced slightly below Px air pressure to give the fuel flow required to run at the selected power. A solenoid operated pneumatic servo mechanism is used to select the appropriate cam which transfers control between the EEC and MFCU. 4 Flapper Valves (Ag and Ap): Ag is controlled by the mechanical speed governor and Ap. spring force on the governor flyweights is reduced. As governor speed reaches the desired lower setting. opening the metering valve and increasing fuel flow. spring force overcomes flyweight force.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. During acceleration. During deceleration. 6 Bellows Assembly: Consists of deceleration. 72-00-00 ENGINE . governor and acceleration bellows connected by a shaft linked to the fuel metering valve.DESCRIPTION AND OPERATION Page 29 Nov 04/2005 . DESCRIPTION AND OPERATION Page 30 Nov 04/2005 . 3045542 HEATED OIL INLET OUTLET FUEL FILTER AIRFRAME / ENGINE FUEL CONNECTION FUEL HEATER BYPASS IMPENDING BYPASS SWITCH FUEL FILTER / HEATER UNIT FUEL PRESSURE SENSING PORT C17520_1A Fuel System .Schematic Figure 14 (Sheet 1 of 2) 72-00-00 ENGINE .PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3045542 AIRFRAME EJECTOR PUMP MECHANICAL FUEL CONTROL UNIT MOTIVE FLOW VALVE OUTLET FILTER MOTIVE FLOW PUMP SELF RELIEVING SCREEN PUMP BYPASS FLOW METER (OPTIONAL) BYPASS FLOW OIL FUEL PUMP UNIT OUTLET INLET OIL COOLER FUEL TEMP PORT VENT AIRCRAFT DRAIN TANK FLOW DIVIDER WASTE FUEL EJECTOR TANK DUMP VALVE PRIMARY & SECONDARY FUEL NOZZLES AIRFRAME / ENGINE CONNECTION C17520_2A Fuel System .Schematic Figure 14 (Sheet 2) 72-00-00 ENGINE .PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO.DESCRIPTION AND OPERATION Page 31 Nov 04/2005 . DESCRIPTION AND OPERATION Page 32 Nov 04/2005 .PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3045542 HEAT EXCHANGER AND VALVE BODY FUEL IN OIL OUT FUEL OUT PRESSURE DIFFERENTIAL SWITCH OIL IN FUEL FILTER THERMAL ELEMENT VALVE COMPRESSION SPRING FUEL OUT VALVE SLEEVE FUEL IN OIL OUT OIL IN FUEL FILTER C15046B Fuel Heater .3⁄4 View and Schematic Figure 15 72-00-00 ENGINE . 3045542 OUTLET FILTER IMPENDING BYPASS SWITCH FUEL IN FUEL OUT OUTLET FILTER BYPASS VALVE BYPASS FUEL RETURN SELF RELIEVING INLET SCREEN OUTLET FILTER BYPASS VALVE IMPENDING BYPASS SWITCH OUTLET PORT OUTLET FILTER BYPASS RETURN PORT GEAR PUMP FUEL EJECTOR SELF RELIEVING INLET SCREEN INLET PORT C15047B Fuel Pump .3⁄4 View and Schematic Figure 16 72-00-00 ENGINE .DESCRIPTION AND OPERATION Page 33 Nov 04/2005 .PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3⁄4 View Figure 17 72-00-00 ENGINE .PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO.DESCRIPTION AND OPERATION Page 34 Nov 04/2005 . 3045542 FUEL CONTROL RIGGING HOLE FUEL MOTIVE FLOW OUTLET POWER LEVER PyAIR OUTLET FUEL SHUTOFF RIGGING HOLE P3AIR INLET FUEL OUTLET FUEL SHUTOFF LEVER C30201 Mechanical Fuel Control Unit (MFCU) . REVERSE MAX. 3045542 METERED FUEL OUT PRESSURIZING VALVE CONDITION / FUEL SHUTOFF LEVER METERING VALVE OFF REGULATOR BYPASS VALVE ON MANIFOLD−PRESS.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. REGULATOR P3 P0 FUEL DRAIN BELLOWS ASSY. POWER LEVER DEC.Schematic Figure 18 72-00-00 ENGINE . FORWARD GOV. INPUT ACC. BELLOWS PLA.BELLOWS RVDT EEC MODE CAM & FOLLOWER LEVER MANUAL MODE CAM & FOLLOWER LEVER NH DRIVE INPUT BLEED Px ORIFICE Py ORIFICE NH GOVERNOR FLYWEIGHTS GOVERNOR LEVER P3 TORQUE TUBE FUEL INLET BYPASS RETURN TO PUMP PRESSURE RELIEF VALVE MOTIVE FLOW VALVE MOTIVE FLOW P3 AIR INLET DRAIN Py TO PROPELLER OVERSPEED GOVERNOR MODE CAM SELECT SOLENOID GOVERNOR ORIFICE (Ag) STEPPER MOTOR ORIFICE (Ap) PRESSURE RELIEF VALVE STEPPER MOTOR & GEARHEAD SERVO VALVE ELECTRICAL CONNECTOR DRAIN LEGEND DIFFERENTIAL PRESSURE P3 COMPRESSOR DISCHARGE PRESSURE NH HIGH PRESSURE ROTOR SPEED Px ENRICHMENT PRESSURE Py GOVERNING PRESSURE RVDT ROTARY VARIABLE DIFFERENTIAL TRANSFORMER P0 AMBIENT PRESSURE C15041A Mechanical Fuel Control Unit (MFCU) . BELLOWS IDLE MAX.DESCRIPTION AND OPERATION Page 35 Nov 04/2005 . a ported sleeve and a valve spring. reducing fuel flow until the deceleration stop is contacted. 12 Shutoff Valve: An input shaft driven by the condition/fuel shutoff lever operates a valve that passes metered flow to the bypass port. Positioning of the needle valve is controlled by the bellows assembly in the pneumatic section through a torque tube that acts as a fuel/air seal. The valve is normally open.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. the stepper motor opens flapper valve Ap. consequently closing the pressurizing valve and shutting down the engine.DESCRIPTION AND OPERATION Page 36 Nov 04/2005 . the valve closes. Bimetallic disks under the spring compensate for variations in specific gravity due to fuel temperature change. bleeding and reducing Py pressure around the deceleration bellows. When the desired power level is reached. 7 Motive Flow Valve: The valve is spring loaded. 3045542 During deceleration. increasing Py pressure to move the bellows away from the stop into the governing range. the valve closes. 16 Mode Select Solenoid: Energized when selecting EEC mode. 14 Stepper Motor: Alters the position of the valve (Ap) which bleeds Py pressure to change metered fuel flow to the engine. which regulates the flow of fuel to the engine. and as P3 increases. The motor is controlled by the EEC. Actuation of the valve changes the orifice area. 11 Pressurizing Valve: Maintains a minimum fuel pressure in the MFCU during low flow conditions when starting. 8 High Pressure Relief Valve: Consists of a relief valve. 72-00-00 ENGINE . 15 Rotary Variable Differential Transformer: Fitted to the power lever shaft and signals power lever angle to the EEC. closes and opens when the pressure of unmetered fuel overcomes the spring force. 9 Differential Pressure Regulator (Pd Regulator): Maintains a constant pressure drop across the metering valve by bypassing excess fuel flow to the fuel pump ejector pump. The bellows expand. The valve provides fuel to operate a jet pump located in aircraft fuel tank. An external adjustment screw on the regulator cover is used to adjust for maximum Pd. The relief valve operates in parallel with the differential pressure regulator to prevent excessive buildup of fuel pressure in the main fuel control body. when the EEC is operating. 13 Manifold Pressure Regulator: Regulates starting fuel flow as a function of compressor discharge pressure (P3). 10 Metering Valve: Composed of a needle valve operating in a sleeve. an elbow and tube is fitted to the exhaust duct and connects to the main fuel drain valve. thereby facilitating the identification of MFCUs which cannot meet the fuel flow requirements of PW127H engines. to cool the nozzle and atomize the fuel. The code for the fault is stored in the EEC memory. The front valve has an adapter installed with a tube connected to the adapter to drain the fuel to the main fuel drain valve. The manifold consists of sheathed nozzle adapter assemblies (Ref. Some nozzles have a fine center hole for primary fuel flow and an annular orifice for secondary flow. The tank contains non-return valves. The valves open when the pressure inside the case falls to near ambient pressure. It comprises primary and secondary spool valves in a housing equipped with inlet and dump ports. When the fuel inlet pressure ceases. secondary fuel to the fuel nozzle adapters. 20). when the inlet fuel pressure overcomes the valve spring. a fault is generated which prevents the MFCU from going into EEC mode. a strainer. comprises a tank with inlet and outlet connections and a vent. (d) The flow divider and dump valve (Ref. 19) is connected to the fuel manifold at the bottom of the gas generator case (flange F to K). Fig.DESCRIPTION AND OPERATION Page 37 Nov 04/2005 . the valves close the inlet and open the dump ports. 1 The fuel waste ejector (Ref. the dump valve is connected to a waste fuel ejector. Fig. from the compressor. giving access to the primary manifold. (g) To eliminate atmospheric pollution and fuel wastage. The secondary valve opens when the primary manifold pressure overcomes the secondary valve spring. The sheath which surrounds the nozzle conveys air. a motive flow ejector pump. In addition. and a float-operated drain valve. One tube supplies primary fuel and the other two (which are connected). located in the airframe. connected to three flexible tubes. If an MFCU having a lower fuel flow but not the identification circuit is installed on a PW127H engine. Fig. 21). spring-loaded valves are installed at the front and rear of the underside of the gas generator case. (e) The fuel manifold delivers fuel to the combustion chamber. Nozzle adapter assemblies are produced by Delavan. which protrude into the combustion chamber. others have no center hole and are equipped for secondary flow only. 3045542 17 The MFCU has an identification circuit in the wiring which is read by the EEC. 72-00-00 ENGINE .PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. (f) To ensure adequate drainage of fuel after shutdown. The primary valve opens. allowing residual fuel to drain from the manifold through the flow divider to the dump port. PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. DUMP PORT CLOSED C38659 Flow Divider and Dump Valve .DESCRIPTION AND OPERATION Page 38 Nov 04/2005 . SECONDARY AND DUMP PORTS OPEN INLET PORT DUMP PORT PRIMARY MANIFOLD PORT SECONDARY MANIFOLD PORT FUEL MANIFOLD ADAPTOR MATING FACE INLET AND PRIMARY PORTS OPEN SECONDARY AND DUMP PORTS CLOSED INLET. PRIMARY AND SECONDARY PORTS OPEN. 3045542 SECONDARY MANIFOLD PORT INLET PORT PRIMARY MANIFOLD PORT SPRING HOUSING BODY ASSEMBLY DUMP PORT VALVE SPRINGS TRANSFER VALVE INLET PORT CLOSED PRIMARY.Schematic Figure 19 72-00-00 ENGINE . PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO.DESCRIPTION AND OPERATION Page 39 Nov 04/2005 . 3045542 SECONDARY COOLING AIR PRIMARY SWIRL VANE C38663 Fuel Manifold Adapter and Nozzle .Cross-section Figure 20 72-00-00 ENGINE . the intercompressor bleed valve remains controlled by the EEC and engine acceleration is usually faster than in EEC mode . preventing fuel from the mechanical fuel control from entering the tank from the orifice. The value of the power required is stored internally in the EEC and is also an output to the aircraft cockpit instrumentation where it is displayed as an equivalent torque value. raising a lever and unseating a valve covering an orifice. The ejector tank is vented to an airframe tank. the majority of the control functions are taken over by the Mechanical Fuel Control Unit (MFCU). As the fuel level rises. Engine Control System (a) Electronic Engine Control The electronic engine control (EEC) (Ref. the float moves upwards. In manual (degraded EEC) mode. fuel flow is controlled by the MFCU only. In this mode. starting). Above 30% NH. The non-return valve then closes.g. Figs. fuel drains from the dump valve and is collected in the ejector tank. which also collects fuel and oil from various drains on the engine. the EEC determines the power required. Fuel is then drawn from the tank through the orifice.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. combined with the pressure drop on the bottom. Fuel pressure acting on top of the orifice. to be conveyed by a tube to the inlet side of the fuel pump. The EEC. The EEC also controls minimum power turbine speed (NPT). the MFCU controls high pressure rotor speed based on power lever angle. In manual mode.g. as follows: 72-00-00 ENGINE . operating on 28 VDC. corrects and changes fuel flow through various inputs. Fuel from the hydromechanical fuel control flowing through a venturi causes a pressure drop below the orifice. 3045542 2 (2) During engine operation. Rating Selector Switch (RSS). The EEC operates in conjunction with the mechanical fuel control unit (MFCU) and the autofeather unit (AFU) to provide control of engine power. 22 and 23) is located on the left side of the front inlet case. The control system then adjusts fuel flow to obtain the power required and ensure it does not fluctuate. In addition. both airframe and engine. In EEC mode. Below 30% NH (e.DESCRIPTION AND OPERATION Page 40 Nov 04/2005 . acceleration and deceleration. Monitoring and adjustment of the torque (power) produced is the responsibility of the person running the engine. opens a non-return valve located on the bottom of the orifice. When the tank fuel level drops. From these inputs. HP compressor rotor speed (NH) until just above flight idle. ambient conditions and aircraft requirements (e. bleed demand). the EEC controls the intercompressor bleed valve (IBV) which ensures surge free transient operation. the EEC maintains closed loop control as described above. the float moves down and the orifice is covered by the valve. the EEC has inputs from the Power Lever Angle (PLA). 3045542 VENT WASTE FUEL INLET WASTE FUEL EJECTOR TANK MOTIVE FLOW INLET FUEL OUTLET C11865 Waste Fuel Ejector .3⁄4 View Figure 21 72-00-00 ENGINE .DESCRIPTION AND OPERATION Page 41 Nov 04/2005 .PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. DESCRIPTION AND OPERATION Page 42 Nov 04/2005 .3⁄4 View and Schematic Figure 22 72-00-00 ENGINE . 3045542 C38697 Electronic Engine Control .PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 8 AUTO FAIL LAMP TORQUE 2 ENGINE CONTROL SYSTEM FAULT INDICATOR UART / ARINC MAINTENANCE DIAGNOSTICS ELECTRONIC ENGINE CONTROL (EEC) PAMB DISCRETES CONDITION FUEL SHUT OFF LEVER DISCRETES TO & FROM OPPOSITE ENGINE EEC BLEED TORQUEMOTOR STEPPER MOTOR Wf PLA MECHANICAL FUEL CONTROL UNIT (MFCU) NH P3 FUEL FLOW NH PVM PLA FUEL PUMP LOW PRESSURE FUEL IN CLA PLA RVDT POWER LEVER MOTIVE FLOW BYPASS FLOW RVDT ROTARY VARIABLE DIFFERENTIAL TRANSFORMER PVM PROPELLER VALVE MODULE CLA CONDITION LEVER ANGLE PLA POWER LEVER ANGLE WF FUEL FLOW PAMB AMBIENT PRESSURE P1.Schematic Figure 23 72-00-00 ENGINE .DESCRIPTION AND OPERATION Page 43 Nov 04/2005 . 3045542 AIRFRAME AUTOFEATHER RELAY AUTOFEATHER UNIT (AFU) ENGINE TORQUE 1 LOW TORQUE LAMP AUTOFEATHER ARMED LAMP ARINC 429 INPUT FROM ADC NH1 NH2 ACTUAL TORQUE TORQUE BUG COCKPIT DISPLAYS ARINC 429 OUTPUT 28 VDC T1.8 TOTAL INLET PRESSURE T1.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO.8 TOTAL INLET TEMPERATURE NH HIGH PRESSURE ROTOR SPEED P3 INTERSTAGE AIR PRESSURE C63872 Engine Control and Electrical System . 2 EEC rating selector. Maintenance activated switch controls display of EEC fault codes. 5 Engine trim switch. Adjusts the measured power lever angle to eliminate power lever stagger due to system tolerances. This signal comes from either the condition lever angle switch. Sends uptrim signal when commanded by opposite engine autofeather control unit (AFU). Manual switch: This switch selects manual (MFCU) control of the engine. 3045542 (b) Airframe Inputs 1 Mode selector. 7 Propeller brake signal. MCT (maximum continuous). 4 Uptrim relay. CLB (maximum climb) and CRZ (maximum cruise). Indicates bleed air extraction level and lowers thermal power limit of engine. 3 Propeller feathered signal (feather discrete). The engine sensors are used only when a fault occurs in the air data input to the EEC.DESCRIPTION AND OPERATION Page 44 Nov 04/2005 . Not used. Electrical signals from the computer transmit outside air temperature (OAT).i.e. 6 LRU fault select. manual feather switch or autofeather relay to cancel propeller ‘‘underspeed fuel governing’’ whenever the propeller is feathered. 10 Air data computer.. These signals are normally used instead of those from engine sensors to compute and transmit a signal to the torque gage which positions the bug to control engine fuel flow. Selects NH limited APU mode operation. 72-00-00 ENGINE . 9 Bleed signal (2 Discrete Inputs).PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. altitude pressure (PALT) and indicated airspeed (IAS). ATO (alternate take off). 8 Ground test switch. Selects the required bug power rating . 5 Torque and power turbine rotor speed (NPT). 2 coil and a fault is recorded in the EEC memory.8) Pneumatic signal to a transducer installed in the EEC. ensuring power changes during the reversion are minimized. 2 A reference bug on the torque indicator. Electrical signal from a sensor installed in the rear inlet case.DESCRIPTION AND OPERATION Page 45 Nov 04/2005 . Electrical signals from a torque sensor installed in the reduction gearbox input housing. Pneumatic signal to a transducer installed in the EEC. The torque signal is modified by a characterization plug to compensate for torque shaft variations due to tolerances. 3 The torque indicator to show the actual torque produced by the engine.e.8). then stepper motor is frozen (fail fixed). 3 Total inlet temperature (T1. The power lever may be adjusted to bring engine torque into line with rated torque. The position of the bug shows the actual rated engine torque for the current operating conditions. 2 Total inlet pressure (P1. holding fuel flow and power stable under steady state conditions until reversion to manual occurs. NOTE: After a major EEC or EEC input failure. (d) EEC output The airframe and engine inputs are processed by logic in the EEC and compared with reference data stored in the units memory. 1 coil deviates beyond set limits. at low power). The sensor has two coils. Electrical signals from pulse pick-up probes installed in the accessory gearbox. the EEC uses the signal from No. Commands are then generated and transmitted to: 1 The MFCU stepper motor to adjust fuel flow. This is used to generate an airspeed signal used by the control logic. If the signal from No.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. Reversion to manual is automatic when PLA is below 65 degrees (i. 3045542 (c) Engine Inputs 1 Ambient pressure (PAMB). 72-00-00 ENGINE . 4 High pressure turbine rotor speed (NH). (3) Autofeather Unit The autofeather unit (AFU) (Ref. The propeller control system consists of the electronic propeller control (EPC). The plug contains links which are set up during the calibration of the torque shaft and testing of the engine. In that event the EEC of the twin engine increases power (uptrim) to compensate for the failed engine. depending on the type of failure. PLA and PAMB input. Fig. 7 There is a degraded mode which occurs automatically after a major EEC or EEC input failure. The valve is closed when the MFCU is in manual mode. The following two modes are used to generate the commands transmitted to the intercompressor bleed valve: a Electronic mode: normal control depending on NH. 3045542 4 The intercompressor bleed valve which is opened to bleed LP compressor air and prevent surge. step (d) 7): Control depends on NH input. Should an engine fail. The case has four mounting pads and two electrical connectors. 72-00-00 ENGINE . 5 A cockpit warning light (auto fail lamp) when a failed fixed condition occurs. b Degraded mode (Ref. The AFU operates on 28 VDC and receives signals from the AFU of the second (twin) engine. stalls and reduce noise at low power and during rapid power lever movement. Propeller Control System In addition to the components of the fuel control. the propeller overspeed governor and the hydraulic pump described below. (1) The EPC is mounted on the airframe (Ref. The unit comprises two circuit boards contained in a metal case. the engine power output is governed by the propeller overspeed governor. Existing commands may continue to be generated by the EEC. 24) is mounted on the left side of the front inlet case (flange B to C) adjacent to the EEC. The MFCU stepper motor is frozen (fail fixed) holding fuel flow steady or the units reverts to manual control where the fuel flow is controlled by the power lever angle (PLA). propeller valve module (PVM). A torque shaft characterization plug is installed on the connectors located at the top of the AFU. 6 The EEC degraded lamp located on the maintenance panel when a fault occurs in the EEC.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. its AFU will initiate the engine’s autofeather system and signal the EEC and AFU of the twin engine. They bring the torque signals to a nominal value and compensate for any differences due to material inconsistency and machining tolerances of the torque shaft. (e) Most control system faults are recorded in the EEC memory and identified by a two-digit code which can be shown on a maintenance panel or ARINC 429 receiver. The twin AFU disables its autofeather system to ensure both engines are not feathered at the same time. AMM).DESCRIPTION AND OPERATION Page 46 Nov 04/2005 . G. 3045542 TORQUE SHAFT CHARACTERIZATION PLUG RECEPTACLE VIBRATION ISOLATED MOUNTING PAD ELECTRICAL CONNECTOR ENGINE ELECTRONIC CONTROL OF SECOND ENGINE 28 VOLTS TORQUE AUTOFEATHER UNIT OF SECOND ENGINE AUTOFEATHER ENABLE AUTOFEATHER UNIT AUTOFEATHER UNIT OF SECOND ENGINE EEC LOCAL AUTOFEATHER ENGINE OUT AUTOFEATHER TEST C14834A Autofeather Unit .3⁄4 View and Schematic Figure 24 72-00-00 ENGINE .DESCRIPTION AND OPERATION Page 47 Nov 04/2005 .PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. These resistance variations are transmitted to the EEC. (a) The exciter is a sealed unit containing electronic circuitry encased in epoxy resin. propeller speed. A switch is linked to the PVM condition lever to restrict the use of reverse pitch. A power lever on the PVM controls reverse pitch and beta scheduling. (1) The total inlet temperature (T1. respectively. 26) have identical tubular housings with a magnet and coil at the inner (tip) end. but can function on 9 to 30 volts. mounted in the rear inlet case (flange C to D). the temperature of the torque shaft varies the resistance of the platinum at the tip of the No. Fig. A six-pin electrical connector and mount flange are at the outer end. generating a pulse. Current is supplied through the engine electrical harness. The resistance of the sensor changes with temperature. (1) The ignition exciters are flexibly mounted on the right side of the front inlet case.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. Fig. 25 and Fig. where it is converted into engine torque indications. Fig. two individual high tension cables and two spark igniters. therefore. 1 and 2 sensors is transmitted to the AFU and the EEC. Tooth separation time sensed by the No. It transforms the DC input into a pulsed high voltage output. where they are converted into temperature readings. The oil pressure is transmitted to the propeller pitch change system by a transfer tube that runs through the propeller shaft. consists of a resistor in a sleeve fitted with a threaded connector. The PVM is mounted behind the propeller shaft on the rear face of the reduction gearbox. 27) The ignition system provides a quick light-up capability over a wide temperature range. It requires a nominal 28 volts DC to operate. 26) The inlet temperature and torque sensing systems consist of a total inlet temperature (T1. Torque changes cause rotational displacement of the outer tube with respect to the inner shaft. 2 sensor. Additionally. Fig. Ignition System (Ref. A condition lever governs the propeller pitch range and. It receives a fixed low current input from the EEC. 25).8) sensor and the engine torque sensor. Temperature affects the shaft’s twist rate (torque) and must therefore be compensated for. causing the distance between the teeth to lengthen/shorten. 72-00-00 ENGINE . The engine torque shaft assemblies consist of an outer reduction gearbox torque shaft and an inner torque shaft metering tube. Inlet Temperature and Torque Sensing Systems (Ref. (2) The torque sensors (Ref.DESCRIPTION AND OPERATION Page 48 Nov 04/2005 . 3045542 (2) H. These units provide signals which are passed to the engine control system by the engine electrical harness. I.8) sensor (Ref. Teeth on the inner shaft and on the outer tube pass the sensor inner tip. The system comprises two ignition exciters. The PVM receives oil from a pump mounted on the reduction gearbox. varying the current returned to the EEC in proportion. Location and Schematic Figure 25 72-00-00 ENGINE .PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3045542 C14760 Temperature Sensor (T1.DESCRIPTION AND OPERATION Page 49 Nov 04/2005 .8) . DESCRIPTION AND OPERATION Page 50 Nov 04/2005 .PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3045542 C14758A Torque Sensors .Location and Details Figure 26 72-00-00 ENGINE . 28 through 30) Engine performance is monitored by various sensors. This is situated immediately above the oil tank on the left side of the rear inlet case. These electromagnetic sensors protrude into the engine at various locations. high energy discharges across the gap.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. Their signals are received by the instrumentation. Electromagnetic pulses are generated when associated gears or toothed wheels pass through the magnetic field created at the tips of the sensors. a capacitor on the high voltage side of the output transformer is progressively charged. 28) are located on the right side of the rear inlet case. (3) The speeds of the major rotating assemblies are monitored by pulse pickup probes. Fig. or if the input voltage is switched off. Fig. (a) Two identical sensors referred to as NH1 and NH2 (Ref. J. It senses low pressure rotor speed (NL) from the No. 3045542 (b) When the unit is energized. (b) One sensor is located below the engine mounting pad on the right side of the intercompressor case. Fig. The electrical potential developed by the ignition exciter is applied across the gap between the central electrode and the shell (ground). The unit will continue functioning if one of the igniters is open or shorted. transmitters and thermocouples mounted on the engine. 3 bearing-retaining nut lugs (Ref. Each igniter has a central electrode enclosed in semi-conducting material. As the potential increases. 29). High pressure rotor speed (NH). If both igniters fail. Performance Indicating System (Ref. (2) Provision is made for an oil pressure transmitter tapping in the pressure regulating valve housing. low pressure rotor speed (NL) and propeller speed (NP) are sensed by these probes. to operate the remaining igniter. 72-00-00 ENGINE . (d) The two air-cooled spark igniters are located at the 5 and 7 o’clock positions on the gas generator case (flange F to K) adjacent to the fuel manifold. (c) The two ignition cable assemblies carry the output from the ignition exciters to the spark igniters. The spark always occurs between the electrode and the shell. At this point. Each assembly consists of an insulated electrical lead inside a flexible metal braiding and is connected to the exciter and plug by coupling nuts. a small current passes across the semi-conducting material until the air between the electrode and the shell ionizes. These sensors pick up high pressure rotor speed signals from the starter motor gearshaft teeth. When sufficient energy to ionize a spark gap in the unit is accumulated. (1) Provision is made for the fitting of an oil temperature sensor in the oil pressure check valve housing. The pulse frequencies are transmitted directly to cockpit instrumentation or indirectly through the fuel control system by the electrical harness. either directly through the wiring harness or indirectly through the EEC and AFU. the capacitor automatically discharges. probes.DESCRIPTION AND OPERATION Page 51 Nov 04/2005 . The housing is located behind the pressure oil filter on the left side of the rear inlet case (flange C to D). the capacitor discharges through a dividing and step-up transformer network across the two spark igniters. 3045542 GAS GENERATOR CASE FRONT INLET CASE IGNITION EXCITER IGNITER IGNITER CABLES SEMI CONDUCTOR INCONEL 600 COOLING AIR GLASS SEAL IGNITION CABLE CONNECTOR INPUT IGNITION CROSS SECTION C30203A Ignition System Figure 27 72-00-00 ENGINE .PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO.DESCRIPTION AND OPERATION Page 52 Nov 04/2005 . Air System (Ref. 3045542 (c) Another sensor is located on the left side of the reduction gearbox rear housing.DESCRIPTION AND OPERATION Page 53 Nov 04/2005 . one lug-mounted T6 thermocouple trim resistor and the airframe wiring harness and gage. the thermocouples are connected in parallel. A thermocouple. Fig. one positive and one negative bus-bar. 72-00-00 ENGINE .5) and high pressure (P3) compressor stages is utilized for sealing bearing cavities.8) sensor are also part of performance indicating (Ref. It senses propeller speed (NP) from the teeth on the accessory-drive idler gearshaft (Ref. respectively. of an appropriate class and easily removed/installed. 1 and 2 bearings. (b) The T6 thermocouple trim electrical cable is installed on the right side of the engine. 32) Air from the low pressure (P2.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. Fig. (a) Each thermocouple has two single-core conductors of different material (alumel and chromel) that are joined at one end (the bimetal junction) and covered by a protective sheath. Fig. The oil. At the other end of the conductor is a terminal lug. The actual temperature is calculated at engine test and compared with that obtained by the thermocouples. 30). (4) The torque monitor sensors and the inlet temperature (T1. ensures constant resistance. one T6 thermocouple trim branched electrical cable. (5) The turbine interstage temperature (T6) indicating system (Ref. To obtain an average reading. P3 air is also used in the fuel control system and the propeller overspeed governor. Subpara. (c) Gas temperature generates a voltage in each thermocouple. 31) monitors gas path temperature. 7). A bimetallic junction (chromel and alumel) surrounded by a metal sheath terminates the cable. A cable fitted with a fixed resistor is connected in parallel with the thermocouples to bias the average reading. It consists of nine immersion thermocouples. A terminal block. A classified bias resistor and external leads to cockpit instrumentation are installed on the terminal block located on flange K. of an almost unvarying temperature. Another resistor. one terminal block. which bolts to flange C. to assist oil scavenging and for internal engine cooling and for off-engine use. Because of the limited sampling by the thermocouples. the reading is not an accurate indication of gas path temperature. and for off-engine services. The thermocouples are installed in bosses in the turbine support case (flange K). integral with the terminal block is installed in a passage through which oil flows to the No. The branched cable consists of a positive (chromel) lead and a negative (alumel) lead that connect to a terminal block which is connected to the positive and negative bus-bars. and a bias resistor are at the other end. K. is fitted on the terminal block to provide further required T6 temperature correction. at one end. PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO.DESCRIPTION AND OPERATION Page 54 Nov 04/2005 .Location Figure 28 72-00-00 ENGINE . 3045542 REAR INLET CASE NH2 PULSE PICKUP PROBE ELECTRICAL WIRING HARNESS PLUG P5 ELECTRICAL WIRING HARNESS PLUG P14 NH1 PULSE PICKUP PROBE C63112 NH Speed Sensor Probes . DESCRIPTION AND OPERATION Page 55 Nov 04/2005 .Location and Details Figure 29 72-00-00 ENGINE . 3045542 1 ENGINE RH SIDE 3 2 PROBE CIRCUIT DIAGRAM NL PULSE PICKUP PROBE AIR GAP INTERCOMPRESSOR CASE NL PULSE PICKUP PROBE C30205 NL Speed Sensor Probe .PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO.DESCRIPTION AND OPERATION Page 56 Nov 04/2005 . 3045542 C14754 NP Speed Sensor Probe .Location and Details Figure 30 72-00-00 ENGINE . 3045542 IMMERSION THERMOCOUPLE POSITIVE BUS BAR NEGATIVE BUS BAR T6 THERMOCOUPLE TRIM BRANCHED ELECTRICAL CABLE PROBE BUS BAR SUPPORT BRACKET TERMINAL BLOCK LUG MOUNTED T6 THERMOCOUPLE TRIM RESISTOR TERMINAL HOUSING C63109A T6 Monitoring System .Location and Details Figure 31 72-00-00 ENGINE .PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO.DESCRIPTION AND OPERATION Page 57 Nov 04/2005 . 5 overcomes the spring and pushes the valve and piston up to block P3 air. and is vented via an external tube into the exhaust. it prevents lubricating oil from entering the power turbine shaft. 2 bearing and also helps to scavenge oil from the No. This air passes through holes in the shaft to seal the No. which is higher than oil cavity pressure.5 or P3) or pressure in the area to be sealed. (d) Air from the switching valve is delivered through external and internal transfer tubes to the inside of the power turbine shaft. A labyrinth seal is a circumferentially multi-grooved ring in a close-fitting plain ring. The valve assembly comprises inner and outer housings. 3 and 4 bearing seals are pressurized by air from the switching valve through internal passages. provides adequate air supply during starting by directing P3 air to areas normally pressurized by P2. 4 bearing seals also receive air from the No.5. Air pressure (P2.DESCRIPTION AND OPERATION Page 58 Nov 04/2005 . (e) The No. adjusting washers and a thrust washer retained by a cover. P3 is the only sufficiently pressurized air available). a piston. 3 bearing cavity through the space between the HP and LP shafts. P3 pressure increases at a faster rate than P2. through the turbine support case.5 (during initial start-up. The valve spring holds the valve against the seat. As the air leaks across the turbine shaft carbon air seals. (f) The No.5 air enters the intercompressor case and also replaces P3 air in the power turbine shaft seal housing situated in the rear inlet case. 3045542 (1) Air for Cooling and Sealing (Ref. and an external adapter with a tube that connects to the rear inlet case. 33). P2. P2.5 air. Fig. 32) (a) Labyrinth seals are used throughout the turbomachinery to prevent seepage between air and oil passages. The No. located in the intercompressor case. blocking P2. then through an external pipe into the accessory gearbox and out through the centrifugal breather and engine exhaust. The air is vented by an internal transfer tube. The air is also used to scavenge the bearing cavity. 72-00-00 ENGINE . undergoes a gradual pressure drop as it travels in and out of the grooves across the seal. (c) When the engine is started.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. either one or both may rotate. (b) A switching valve (Ref. The air from these cavities assists in oil scavenging (blow-down) and vents through the centrifugal breather in the accessory drives section.5 increases with increasing NH. 6 and 7 bearings and cavity comes from the holes in the power turbine shaft and stubshaft. P3 air enters the intercompressor case through slots in the valve housing and exits through the adapter to the rear inlet case. Fig. valve and springs. (g) Air for sealing and pressurizing the No. 5 bearing cavity and seals receive air from the switching valve chamber through an internal passage and from a vent at the rear of the HP impeller. 1 and 2 bearing areas. and at 40% to 45% NH. P2. flow in either direction is stopped. When sealing pressure is equal to the opposing pressure. and exits into the gas path downstream of the power turbine stator. 35) consists of a housing. Fig 34) Compressor air is vented to prevent surge and stalls. the airframe shut-off valve (Ref. The inner and outer platforms are also cooled. The P2.5 check and intercompressor bleed valves are mounted on two branches of a Y-shaped adapter installed on the intercompressor case. cools the bolts. After passing through the blades. Fig. When P3 air pressure is below approximately 41 psia.5 air. The inner and outer platforms are also cooled. 2 The LP Turbine Stator Air enters each stator vane through a slot in the top and exits through slots in the trailing edge. This air is also used in the air conditioning system of the aircraft and for de-icing. 3045542 (h) P3 air taken from around the combustion chamber liner cools: 1 The HP Turbine Vane Ring Air enters each vane or stator through a slot in the top and exits through holes in the airfoil leading edge and slots in the trailing edge. 3 The HP and LP Turbine Disks: Air supplied by internal nozzles cools the front and rear faces.5) The P2. 5 (i) (2) The turbine interstage case/power turbine stator bolts: air passes through holes in the turbine support case. It also seals the bearing cavity. along the LP turbine seal housing. along the bottom of the disk fir-trees into slots in the blade roots. As P3 air pressure increases 72-00-00 ENGINE . Compressor Air (Ref.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. The air is vented through an outlet at the bottom of the oil tank. the air exits through slots in the trailing edge and at the tip. seat. 34) is open and the check valve piston is held in the closed position by spring and P3 air pressure. spring. (b) LP Compressor Air (P2.DESCRIPTION AND OPERATION Page 59 Nov 04/2005 . (a) LP Compressor Shroud Bleed Air (P2) Slots at the forward edge of the LP impeller housing allow P2 air to enter the adjacent cavity to prevent surge and improve performance. piston and a sleeve secured in the housing by a retaining ring. 6 and 7 bearing housing. Fig. and to reduce noise at low power and during rapid power lever movement. Air from the end of the power turbine shaft cools the front and rear faces of the first and second-stage power turbine disks and the No. the common base supplies P2. 4 The HP Turbine Blades: Air passes through holes in the HP turbine disk front cover.5 check valve (Ref. P.DESCRIPTION AND OPERATION Page 60 Nov 04/2005 .5 / P3 AIR (FROM SWITCHING VALVE) RGB INPUT HOUSING TO REDUCTION GEARBOX GAS PATH L. IMPELLER COOLING AND SEALING AIR FLOW (CRUISE CONDITION) C17577 Gas Path/Cooling and Sealing Air Figure 32 (Sheet 1 of 2) 72-00-00 ENGINE . 3045542 CENTRIFUGAL BREATHER IMPELLER FLANGE E P2.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. NO. 6 BRG. 7 BRG L. 5 BEARING INTERNAL VENT OUTLET NOZZLE H. VENT P3 P2. NO. 3045542 AIR SWITCHING VALVE NO.P.5 FWD NO.P.DESCRIPTION AND OPERATION Page 61 Nov 04/2005 . 5 BRG NO. 6 & 7 BRG. 3 BRG. 4 BRG.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. IMPELLER NO. H. NO. TURBINE TURBINE POWER TURBINE C20250C Gas Path/Cooling and Sealing Air Figure 32 (Sheet 2) 72-00-00 ENGINE .P. DESCRIPTION AND OPERATION Page 62 Nov 04/2005 .5 VALVE PISTON RING (AT INITIAL START−UP) P3 P2.Location and 3⁄4 Cutaway Figure 33 72-00-00 ENGINE .5 P2.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO.5 P2.5 (AT 40 − 45% NH) C15050A Air Switching Valve . 3045542 SPRING INTERCOMPRESSOR ADAPTER CASE TO REAR INLET CASE GUIDE PIN P3 COVER WASHER P3 THRUST WASHER BOLT INNER HOUSING RETAINING RING SLEEVE SEAT P2.5 P3 PISTON TO REAR INLET CASE P2. 5) SHUT−OFF VALVE LP BLEED P2.DESCRIPTION AND OPERATION Page 63 Nov 04/2005 .Schematic Figure 34 72-00-00 ENGINE . 3045542 AIR CONDITIONING CONTROL VALVE TO AIR CONDITIONING PACK P2.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO.5 CHECK VALVE INTERCOMPRESSOR BLEED VALVE (P2.5 HP BLEED P3 DE−ICING AIR AND ACOC EJECTOR C66913 Compressor Bleed Air Interconnecting Airflow . (c) HP Compressor Air (P3) The P3 bleed air venturi adapter is installed on the gas generator case left side. The piston moves to the open position and P2. when viewed from the rear. Check valve spring pressure is overcome by the increased P2. P2. servo valve and pressure sensing line. the shut-off valve closes. 72-00-00 ENGINE .5 pressure to seat the check valve piston and stop the flow of P2.4 air is such that the force tending to close the piston is greater than the force tending to open it. cutting off the supply of P3 air.5 air. When P3 air pressure falls below approximately 41 psig. Airworthiness authorities normally require operators to follow these recommendations unless alternative fuels have been agreed between the operator and P&WC and approved by the operator’s airworthiness authority. duct. 36) consists of a housing. As the pressure of P2.4 air in the chamber above the piston. allowing P2. spring and P3 pressure overcomes P2.5 air is supplied to the environmental control system. Operation (Ref. 3. 37) (A summary of the functions previously described) The engine is started by the starter-generator rotating (cranking) the HP impeller and turbine. The flow of gas through the engine also drives the power turbine. respectively. The resultant rearward flow of expanding gas drives the HP and LP turbines. and the starter-generator functions as a generator. It vents P3 air. The intercompressor bleed valve (Ref. The area of the piston exposed to P2. Fuel is sprayed into the combustion chamber. the shut-off valve opens. The duct air back pressure modulates the bleed and improves valve functioning. Use of Approved Fuels (1) The fuels specified in Tables 13 and 14 are recommended by P&WC. restrictor.5 air. This causes higher expansion and increases the speed of the turbines and impellers until the engine has achieved self-sustaining speed with continuous combustion. the piston moves up. 4. The igniter plugs are switched on. transfer tube.DESCRIPTION AND OPERATION Page 64 Nov 04/2005 .Approved Fuels A. Fig. resulting in an increase in turbine and impeller speed.5 air pressure which is proportional to P3 pressure. and the air and fuel mixture is ignited. Fig. and the LP rotor rotates counterclockwise. the manifold and the transfer tube into the bleed valve chamber above the piston. The rotating turbines turning the impellers draw in more air to mix and burn with the fuel. The igniters may then be switched off. Further increase in fuel flow to the combustion chamber will increase gas expansion.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3045542 above approximately 41 psig.5 air to vent. The HP and power turbine rotors rotate clockwise.4 air obtained from a diffuser exit duct tapping passes through the restrictor. cover.4 air falls below that of P2. The drive is taken through the accessory gearbox and down the associated driveshaft to rotate the bevel gear splined to the HP impeller. which are connected to the HP and LP impellers. which is ducted through an airframe shut-off valve controlling its flow to supply air conditioning system demand. Engine . where it is mixed with the incoming air from the impeller. A signal from the EEC opens the servo valve to bleed into the duct via an internal line which reduces the pressure of P2. piston. which turns the propeller through the gearbox. Details Figure 35 72-00-00 ENGINE .DESCRIPTION AND OPERATION Page 65 Nov 04/2005 . 3045542 C63889 P2.5 Check Valve .PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 5 TUBE DUCT SERVO VALVE P 2.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO.4 BLEED COVER TO EEC ELECTRICAL HARNESS CONNECTOR P 2.4 PISTON P2.5 C38664 Intercompressor Air Bleed Valve Figure 36 72-00-00 ENGINE .4 MANIFOLD RESTRICTOR P2. 3045542 SERVO CONTROLLED P2.DESCRIPTION AND OPERATION Page 66 Nov 04/2005 . PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. Technical requirement tests shall be performed. 72-00-00 ENGINE . As these properties only meet minimum engine requirements. it is intended to allow operators to include minimum approved fuel requirements for PW100 engines in conjunction with other functional requirements when formulating their own procurement specification or judging the acceptability of fuels manufactured to other national specifications that exist throughout the world. in accordance with the latest issue of the listed American Society for Testing and Materials (ASTM) test methods. NOTE: (3) The fuel properties specified in Table 4 are the minimum requirements for fuel used in PW100 engines.DESCRIPTION AND OPERATION Page 67 Nov 04/2005 . the list is not intended or suitable for use as a purchase specification for procurement of fuel for PW100 engines. Rather. 3045542 (2) The fuels recommended have been substantiated by P&WC and are Transport Canada approved. IMPELLER C14840_1 Engine Operation Figure 37 (Sheet 1 of 2) 72-00-00 ENGINE .S.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3045542 DRIVE SHAFT TO REDUCTION GEARBOX MAX OIL 1 ADD LITRES OR U.P. QUARTS 2 3 MIN GAS PATH L.DESCRIPTION AND OPERATION Page 68 Nov 04/2005 . IMPELLER H.DESCRIPTION AND OPERATION Page 69 Nov 04/2005 . TURBINE L.P. TURBINE C14840_2 Engine Operation Figure 37 (Sheet 2) 72-00-00 ENGINE .P.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO.P. 3045542 COMBUSTION CHAMBER FUEL MANIFOLD ADAPTER FUEL NOZZLE POWER TURBINE COAXIAL SHAFTS H. 5 ASTM D445 Water Reaction. 72-00-00 ENGINE .0 per cent by volume of naphthalene as determined in accordance with ASTM D1840. lb ASTM D130 Viscosity. BTU/lb 18300 Min. % Max. 25 ASTM D1319 Burning Quality Luminometer Number (See NOTE 2) Min. ml Max.5 Sulfur. 3045542 TABLE 4. Fuel Properties Properties Gravity.84 kg per 1) 57 (0. % Max. 1-b ASTM D1094 NOTE: 1.005 ASTM D1323 Net Heat of Combustion. Test Method ASTM D287 or D1298 ASTM D86 10% Evaporated Max.4°C (-30°F) Max. as necessary. cs at -34.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. % by Weight Max. 16. K/kg 42.8°F). 205°C (401°F) 50% Evaporated Max.DESCRIPTION AND OPERATION Page 70 Nov 04/2005 . Volume Change. 0. ASTM D2382 Freezing Point. 232°C (450°F) End Point Max.6x10 Min. 0. ASTM D240 or 6 Net Heat of Combustion. a waiver is in current effect which authorizes the relaxation. (c) Due to occasional difficulties in meeting the requirements of step (b) above. -45°C (-49°F) ASTM D2386 Reid Vapour Pressure. in the value of minimum smoke point down to 18 mm. deg API at 15°C (59°F) Limits Limits 37 (0. 1. % by Weight (See NOTE 1) Max. 3 psi (21 kPa) ASTM D323 Aromatic Content. % by volume Max. Mercaptan sulfur determination may be omitted provided Doctor test in accordance with ASTM D484 is conducted and results are negative.5 Residue.75 kg per 1) Distillation Temperature. 2 hrs.40 ASTM D1266 or ASTM D2622 or ASTM D4294 Mercaptan Sulfur. 300°C (572°F) Loss. No. Fuels will be acceptable provided they meet one of the following alternative requirements or combination of requirements: (a) Smoke point of not less than 25 mm when determined in accordance with ASTM method D1322. NOTE: 2. 45 ASTM D1740 Copper Strip Corrosion 100° ± 1°C (212° ± 1. 1. Max. Interface rating Max. (b) Smoke point of not less than 20 mm when determined in accordance with ASTM method D1322 provided fuel does not contain more than 3. Max. °F (°C) Max. 1 ASTM D1094 Water Reaction. It shall be clear and free from water. and pre-heater deposit shall be less than Code 3 in accordance with ASTM D1660. 6-Ditertiary Butyl Phenol v 75% 2. NOTE: C. tested as in preceding step (1). Mixed Tertiary Butyl Phenol. No substances of known dangerous toxicity under usual conditions of handling and use shall be used. Quality (1) Fuel shall consist solely of hydrocarbon components except as otherwise specified herein. 72-00-00 ENGINE . may be used as an alternate test method to ASTM D1660.DESCRIPTION AND OPERATION Page 71 Nov 04/2005 .PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO.): test time 150 minutes. 6-Ditertiary-Butyl Phenol. 10-15% 2.4 mm) Hg and pre-heater deposit shall be less than Code 3 in accordance with ASTM D1660.0 inch (25. (2) The Jet Fuel Thermal Oxidation Tester (JFTOT) ASTM D3241. 2. Maximum pressure change shall be 3 inches (76. 4. v 72% Min. 6-Tritertiary Butyl Phenol.CRC fuel coker after 5 hours of operation at 149°C (300°F) pre-heater temperature. fuel flow rate: 2. Monomethyl and Dimethyl Tertiary Butyl Phenol.025 g/1) to prevent formation of gum. 4-Ditertiary Butyl Phenol. Additives (1) One or a combination of the following oxidation inhibitors may be added to the basic fuel in total concentration not greater than 25 milligrams per liter (0. and six (6) pounds (2. D. and shall be suitable for use in aircraft turbine engines. and suspended matter. (2) The odor of the fuel shall not be nauseating or irritating. maximum heater tube temperature fuel system pressure: 500 psig (3447. 40% Max. (a) Testing shall be conducted at 260°C (500°F). v 2. Maximum pressure change shall be 1. 2. 4-Dimethyl-6 Tertiary Butyl Phenol v 2. 28% Max.72 kg) per hour fuel flow rate.2 mm) Hg. The results from both the 260°C (500°F) and 245°C (473°F) Control-temperature tests must be reported by the refiner on all fuel analysis reports. High Temperature Stability (1) The high temperature stability property shall be measured in an ASTM . v 60% Min. 4-Dimethyl-6 Tertiary Butyl Phenol. 3045542 B. sediment. 6-Ditertiary-Butyl-4 Methyl Phenol v 2.85 US gal/hr (3 ml/Min. 10-15% Orthotertiary Butyl Phenol. (b) If JFTOT test at control temperature of 260°C (500°F) should fail to meet specification requirements of preceding sub-step (a). 205°C (400°F) filter temperature. then test shall be conducted at a temperature of 245°C (473°F) (See following Note) or.4 kPa). per 1000 Barrels Grams per 10000 Liters Dupont AFA-1 16 456 Lubrizol 451 20 570 Nalco 5400-A 8 228 Nalco 5403 8 228 20 570 Petrolite TOLAD 245 2 Anti-corrosion and Fuel Lubricity Improver Additives (Ref.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. (a) Anti-corrosion and lubricity additives in the following tables of this sub-section are described as being primary corrosion inhibitors and secondarily as lubricity improvers to meet a U. NOTE: Extensive operation on low lubricity fuel can result in accelerated engine fuel pump wear. Until a generally accepted method of measuring and defining fuel lubricity is available. 1 Anti-corrosion Additives used to inhibit corrosion are listed in Table 5 and are approved for the concentrations listed. Table 6). Anti-corrosion Additives Maximum Concentration Allowed Additive (Trade Name) lb. TABLE 5.S. it is necessary to adjust concentration of such additives to obtain necessary lubricity improvement. TABLE 6. Anti-corrosion and Fuel Lubricity Improver Additives Additive (Trade Name) Maximum Concentration Allowed lb. at the concentration specified. NOTE: These fuel additives were approved on the basis of information received from manufacturers or suppliers of the additives. per 1000 Barrels Grams per 10000 Liters Apollo PRI-19 4 114 Cooper Hiltec E-580 8 228 Dupont DCI-4A 8 228 72-00-00 ENGINE . Analysis of this information and results of tests on product samples have indicated no significant adverse effect on engine materials provided the concentration does not exceed the recommended maximum. by P&WC as both corrosion inhibitors and lubricity improvers. in addition to the oxidation inhibitors listed in step (1) above. 3045542 (2) The additives in Tables 5 thru 10. Military Specification. are acceptable for use in engine fuel subject to the limitations stated. rapid fuel pump wear should be considered an indication of low lubricity fuel and dictates a change in the fuel or addition of a lubricity improver. Only products listed in Table 6 have been tested and approved.DESCRIPTION AND OPERATION Page 72 Nov 04/2005 . The following corrosion inhibitor and fuel lubricity improver additives are approved for the concentrations listed. In certain cases. Thermal Stability Additive Maximum Concentration Allowed Additive (Trade Name) lb.Disalicylidene .1. Any anti-icing additive which is directly equivalent to any of those listed in Table 9 is approved. THESE PRODUCTS MUST BE HANDLED WITH EXTREME CARE. ANY CLOTHING ACCIDENTALLY CONTAMINATED BY SPLASHING SHOULD BE PROMPTLY REMOVED AND THE SKIN WASHED WITH SOAP AND WATER. Anti-corrosion and Fuel Lubricity Improver Additives (Cont’d) Maximum Concentration Allowed Additive (Trade Name) lb.15 0. TABLE 7. CONSULT WITH A PHYSICIAN AS RAPIDLY AS POSSIBLE AFTER ALL CONTACT CASES.15 0. per 1000 Barrels Grams per 10000 Liters 1 57 N. N1 .Diamine WARNING: 5 THESE FUEL SYSTEM ANTI-ICING ADDITIVES CONTAIN ETHYLENE OR DIETHYLENE GLYCOL MONOMETHYL ETHER WHICH IS HIGHLY TOXIC. TABLE 8. IF CONTACT IS MADE WITH EYES. per 1000 Barrels Grams per 10000 Liters 30 855 Dupont JFA-5 4 The metal deactivator in Table 8 is approved.DESCRIPTION AND OPERATION Page 73 Nov 04/2005 . PREVENT CONTACT WITH EYES AND AVOID INHALATION OF VAPORS. TABLE 9.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 2 Propane . Metal Deactivator Additive Maximum Concentration Allowed Additive (Trade Name) lb. at the option of refiner. 3045542 TABLE 6.15 72-00-00 ENGINE . Anti-icing additives Additive (Trade Name) Phillips PFA 55MB MIL-I-27686D Ethylene Glycol Monomethyl Ether as defined in MIL-I-27686E Maximum Concentration Allowed Percentage by Volume 0. AVOID ALL DIRECT CONTACT WITH SKIN OR CLOTHING. per 1000 Barrels Grams per 10000 Liters 8 228 Mobilad F-800 3 The thermal stability additive in Table 7 is approved for use in engine fuel. to ensure adequate high temperature stability at time of use. THEY SHOULD BE FLUSHED WITH WATER FOR 15 MINUTES. 3 0. where the need for biocide use is indicated (blocked LP filters). P&WC recommends.3 The anti-static additives in Table 10 are approved. TABLE 10.3 0. either greater or lesser. 3045542 TABLE 9. Liquid ‘‘I’’) as defined in GOST 8313 Mix 50% Liquid ‘‘I’’ 50% methyl alcohol (Liquid I-M) as defined in TU 6-10-1458 Tetrahydrofurfuryl alcohol (TGF) as defined in GOST 17477 Mix 50% TGF 50% methyl alcohol (Liquid TGF-M) as defined in TU 6-10-1457 6 Maximum Concentration Allowed Percentage by Volume 0. Anti-icing additives (Cont’d) Additive (Trade Name) Diethylene glycol monomethyl ether as defined in MIL-I-85470A Ethylene Glycol Monomethyl Ether (Ethylcellosolve. as the operator’s own experience dictates.0 Anti-microbial Organisms Additive (Ref. b Executive Aircraft Operation The additive may be used continuously in executive aircraft where utilization is less than 1200 hours per year. Limited basis is defined as intermittent or non-continuous use in a single application to sterilize aircraft systems suspected or found to be contaminated by microbial organisms.0 3.DESCRIPTION AND OPERATION Page 74 Nov 04/2005 . For those operators. such as fungi.15 0. a dosage interval of once a month.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. as a guide. a Airline Operation The following biocide additive may be used on a limited basis. This interval can then be adjusted. Table 11). Anti-static Additives Additive (Trade Name) Shell ASA3 Dupont Stadis 450 7 Maximum Concentration Allowed Parts per Million by Weight 1.3 0. bacteria and yeasts. 72-00-00 ENGINE . the latest issue of fuel specifications applies. TABLE 12. a Leak Check Additive (Ref. SF6) E. TABLE 13. Leak Check Additive Additive (Trade Name) Tracer A (Sulfur Hexafluoride. An acceptable fuel or any mixture of acceptable fuels may be used.DESCRIPTION AND OPERATION -46 (-51) - Page 75 Nov 04/2005 . 3045542 TABLE 11. Anti-microbial Organisms Additives Additive (Trade Name) Biobor JF 8 Maximum Concentration Allowed Parts per Million by Weight 270 Other Additives. Approved Fuels ISSUING AUTHORITY BODY KEROSENE TYPE FREEZE POINT WIDE CUT °C (°F) TYPE FREEZE HIGH FLASH POINT KEROSENE °C (°F) TYPE FREEZE POINT °C (°F) Jet A -40 (-40) Jet B -50 (-58) - - Jet A-1 -47 (-53) - - - - Jet A-2 (See Note 1) (See Note 2) - - - Kerosene Type Fuel -47 (-53) Wide Cut Type Fuel -50 (-58) - - US MIL-DTL-5624 - - US MIL-DTL-83133 JP-8 (See Note 3) -47 (-53) - ASSOCIATIONS ASTM (D1655) IATA - MILITARY JP-4 -58 (-72) JP-5 (See Note 3) (See Note 3) - - 72-00-00 ENGINE . NOTE: 1. NOTE: 2.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. Unless otherwise specified. Maximum Concentration Allowed Parts per Million 1 Acceptable Fuels (Unrestricted Use) (1) Fuels listed in Table 13 comply with P&WC specifications and are approved for unrestricted use in PW100 engines. Table 12) This additive is used by local airport authorities to detect leaks in airport fuel distribution systems. DESCRIPTION AND OPERATION Page 76 Nov 04/2005 .S.S. Standards Board 3. -47 (-53) CAN/ General 3. 3-GP-24c -46 (-51) Defense Standard 91-87 (NATO Code F34) -47 (-53) Defense -58 (-72) Defense Standard Standard 91-86 91-88 (NATO (NATO Code Code F40) F44) -46 (-51) Defense Standard 91-91 (See Note 3) (NATO Code F35) -47 (-53) -46 (-51) AIR 3405 -50 (-58) AIR 3407 -58 (-72) AIR 3404 -46 (-51) RT -60 (-76) - - - - CSN 65619 PL5 (See Note 5) -50 (-58) - - - - CSN 6520 RT (See Note -55 (-67) 5) - - - French/ Ministry of the Armed Forces Defense Standard 91-86 (See Note 3) Governments CIS GOST 10227 Czechoslovakia 72-00-00 ENGINE .B. Approved Fuels (Cont’d) ISSUING AUTHORITY BODY KEROSENE TYPE FREEZE POINT WIDE CUT °C (°F) TYPE FREEZE HIGH FLASH POINT KEROSENE °C (°F) TYPE FREEZE POINT °C (°F) US MIL-DTL-83133 JP-8 +100 (See Note 6) -47 (-53) - - - - British Joint Services AVTUR (See Note 4) NA AVTAG NA (See Note 4) AVCAT (See Note 4) NA Designation AVTUR/FSII (See Note 3) NA AVTAG/FSII NA (See Note 3) AVCAT/FSII (See Note 3) NA NATO Code F34 (See NA Note 3 and 4) F40 (See Note 3 and 4) NA F43 NA F35 (See Note 4) - - F44 (See Note 3 NA and 4) - Governments Canadian/ CAN/C.22-97 British/ Ministry of Defence -51 (-60) CAN/C.23-97 C.G.G.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3045542 TABLE 13.G.B.B.S. Fuel Jet A-2 conforming to CAN/C. the results of the inspection must be acceptable to P&WC. therefore there are no freeze point definitions. Acceptable Fuels Subject to Restricted Use ISSUING AUTHORITY BODY KEROSENE TYPE FREEZE POINT WIDE CUT °C (°F) TYPE FREEZE HIGH FLASH POINT KEROSENE °C (°F) TYPE FREEZE POINT °C (°F) TS-1 -60(-76) -60(-76) - CIS GOST 10227 T-2 (See Note) - 72-00-00 ENGINE .H2. NOTE: 6. F. If these fuels are used in an engine for more than 1000 hours (intermittently or continuously). To enable continuous use of these fuels in excess of 1000 hours.23-M86 is acceptable for use providing the restrictions covering flash and freezing points are strictly observed. NOTE: 3.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. NOTE: 2. NOTE: 4. a fuel nozzle inspection must be carried out when 1000 hours running has accumulated. TABLE 14. 3045542 TABLE 13. NOTE: Unless otherwise specified. Use of fuel lubricity improver strongly recommended.DESCRIPTION AND OPERATION Page 77 Nov 04/2005 .B. the latest issue of fuel specifications applies.S. Contains thermal stability improver additive.G. NOTE: 5.331 GM-1 -55 (-67) - - - - China RP-3 -47 (-53) - - - - KEROSENE TYPE PND-25-005-76 Poland BN-70/0533-71 Romania STAS 5639/88 Yugoslavia NOTE: 1. This fuel has both summer and winter freeze points of -40°C (-40°F) and -47°C (-53°F) respectively. These designations are not specifications. Approved Fuels (Cont’d) ISSUING AUTHORITY BODY FREEZE POINT WIDE CUT °C (°F) TYPE FREEZE HIGH FLASH POINT KEROSENE °C (°F) TYPE FREEZE POINT °C (°F) PL6 (See Note 5) -55 (-67) - - - - ATK -50 (-58) - - - - TH -53 (-63) - - - - JUS. Acceptable Fuels (Restricted Use) (1) The fuels listed in Table 14 are considered by P&WC to be satisfactory for occasional use only. Contains fuel system icing inhibitor (FSII).B. 3. PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3045542 TABLE 14, Acceptable Fuels Subject to Restricted Use (Cont’d) ISSUING AUTHORITY BODY KEROSENE TYPE FREEZE POINT WIDE CUT °C (°F) TYPE FREEZE HIGH FLASH POINT KEROSENE °C (°F) TYPE FREEZE POINT °C (°F) GOST 10227 T-1 -60(-76) - - - - BDS 5075-71 TS-1 -60(-76) T-2 (See Note) -60(-76) - - BDS 5075-71 T-1 -60(-76) - - - - PL-3 -60(-76) - - - - PN-72/C-96026 P-2 -60(-76) - - - - PN-72/C-96026 PSM-2 -60(-76) - - - - Bulgaria Czechoslovakia CSN 65619 Poland NOTE: Use of fuel lubricity improver strongly recommended. G. Alternate/Emergency Fuels CAUTION: ADDITIVES SUCH AS TETRA-ETHYL LEAD AND PHOSPHORUS COMPOUNDS, COMMON TO GASOLINE FUELS ARE HARMFUL TO HOT SECTION PARTS FROM A CORROSION, SULPHIDATION AND METALLURGICAL STANDPOINT. (1) The use of aviation gasoline (Avgas) is restricted and must be used only during an emergency. Avgas must not be used for more than 150 hours between engine overhauls. CAUTION: ALTHOUGH DIESEL AND HEATING FUELS ARE CHEMICALLY SIMILAR TO JET FUELS, THEIR COLD FLOW, VISCOSITY AND FREEZING POINT CHARACTERISTICS ARE SPECIFICALLY CONTROLLED DURING REFINING TO LEVELS NOT SUITABLE FOR USE IN AIRCRAFT. (2) 5. The operation of PW100 engines on fuels other than the approved jet fuels is not recommended. Specifically excluded as possible alternate or emergency fuels are such products as automotive gasoline, diesel fuel, heating fuel or any combination of these products with the approved fuels. Engine - Approved Lubricating Oils A. General (1) Major factors affecting oil deterioration over time are engine mechanical condition, climatic, atmospheric and environmental conditions, dust and sand ingestion during take-off/landing modes and engine utilization. (2) When switching between approved oil brands, the following should be adhered to: 72-00-00 ENGINE - DESCRIPTION AND OPERATION Page 78 Nov 04/2005 PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3045542 (a) If switching from a Type II, 5 Centistoke oil, listed in Table 16 (not third generation), to another oil brand also listed in Table 16 then: Switch to new oil brand by adding new oil as required (topping off). NOTE: Original oil does not need to be drained and engine does not need to be flushed. (b) If switching to an oil brand not listed in Table 16, the engine oil must be drained and the engine flushed (Ref. Servicing). (3) If oil of different brands or viscosities become inadvertently combined, the following applies: (a) If the oils which are combined are Type II, 5 Centistoke oils listed in Table 16, (not third generation), no further action is required. (b) Any combining of all other oils: drain and flush complete oil system and; fill with an approved oil (Ref. Servicing and Tables 16, 17 and 18). (4) B. Operators wishing to monitor oil quality are recommended to establish a program in collaboration with their oil supplier/manufacturer. Approved Oils (1) 5 Centistoke Oils The oils listed in Table 16 comply with specification PWA 521, Type II oil Ts3. These oils are fully approved for use in PW100 engines. (2) 4 Centistoke Oils The oils listed in Table 17 have undergone extensive engine and laboratory qualification testing prior to being approved for use in PW100 engines. (3) Third Generation Oils The term ’Third Generation’ is one that oil companies use to describe turbine oils which they claim have superior thermal and oxidative stability when compared to typical Type II, 5 centistoke oils. To ensure that there is no confusion regarding the term ’Third Generation’, P&WC consider as ’Third Generation’ lubricants, only those listed in Table 18. (4) Other Oils No other oils are approved for use in the PW127H engines. Should the use of an oil not listed be desired, the intended user should contact Pratt & Whitney Canada, Product Support Department, for consultation. 72-00-00 ENGINE - DESCRIPTION AND OPERATION Page 79 Nov 04/2005 PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3045542 C. Dupont Oil Blue Dye (PWC05-026) (1) This dye (PWC05-026) may be added to any P&WC approved lubricating oil on a one time basis when filling the system. The dye improves sight glass visibility and aids in the detection of oil leaks. (2) Use 0.5499 - 0.7699 milliliters per liter or 0.0703 - 0.0985 ounces per US gallon of oil. The maximum concentration must not exceed 0.7699 milliliters per liter or 0.0985 ounces per US gallon. (3) The dye is blue in color, however when mixed with some oils which are yellow in color, the result may be green colored oil. TABLE 15, Approved Dye BRAND Dupont Oil Blue D. SUPPLIER Pylam Products Company Inc. 2175 East Cedar Street Tempe, Arizona USA 85281-7431 TEL: 1-800-645-6096 TEL: (480) 929-0070 FAX: (480) 929-0078 URL: http://pylamdyes.com Oil Drain Period CAUTION: WHEN CHANGING FROM AN EXISTING LUBRICANT FORMULATION TO A ‘‘THIRD GENERATION’’ LUBRICANT FORMULATION (SEE TABLE 18), P&WC STRONGLY RECOMMENDS THAT SUCH A CHANGE SHOULD ONLY BE MADE WHEN AN ENGINE IS NEW OR IMMEDIATELY AFTER OVERHAUL. (1) Engines in airline operation flying a minimum of 1200 hours annually where conditions are not known to be detrimental to engine oil: (a) The oil does not have to be drained between engine restoration/overhaul thresholds provided that the integrity of the oil system has been maintained, i.e. no engine maintenance has been carried out where there was a risk of introducing foreign matter into the oil system. (2) Engines operated in aircraft with an annual utilization of less than 1200 hours: (a) The oil drain period may be either: 1 At fixed intervals (Ref. 05-20-00, SCHEDULED INSPECTION/MAINTENANCE INTERVALS); or 2 When oil quality is outside limits (Ref. Para. E.). 72-00-00 ENGINE - DESCRIPTION AND OPERATION Page 80 Nov 04/2005 PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3045542 TABLE 16, Approved Lubricating Oils - PWA 521, Type II (5-Centistoke) BRAND Aero Shell Turbine Oil 500 Royco Turbine Oil 500 Mobil Jet Oil II Castrol 5000 SUPPLIER Shell Canada Ltd. 400-4th Avenue S.W. Calgary, Alberta Canada T2P 0J4 TEL: 1-800-661-1600 Shell International Petroleum Co. Shell Center London, SE1 7NA England TEL: 44 (0) 20 7934 1234 FAX: 44 (0) 20 7934 8060 URL: http://www.shell.com Royal Lubricants Inc. P.O. Box 518 East Hanover, NJ 07936 USA TEL: 1-800-989-7692 FAX: (973) 887-6930 URL: http://www.royallube.com Exxon Mobil Corp. 3225 Gallows Road Fairfax, VA 22037 USA TEL: 1-800-662-4525 FAX: (203) 846-3355 URL: http://www.exxonmobil.com Castrol Industrial North America Inc. 1001 West 31st Street Downers Groove, IL 60515 USA TEL: 1-800-462-6835 TEL: (630) 241-4000 FAX: (630) 241-1957 URL: http://www.castrolindustrial.com Castrol Canada Inc. 3620 Lakeshore Blvd. West Toronto, Ontario Canada M8W 1P2 TEL: (416) 252-5511 FAX: (416) 252-7315 72-00-00 ENGINE - DESCRIPTION AND OPERATION Page 81 Nov 04/2005 PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3045542 TABLE 16, Approved Lubricating Oils - PWA 521, Type II (5-Centistoke) (Cont’d) BRAND BP Turbo Oil 2380/ Exxon Turbo Oil 2380 SUPPLIER Castrol Specialised Industrial (U.K.) Wakefield House Pipers Way Swindon, Wilts SN3 1RE England TEL: 44 (0) 1793 512712 TEL: 44 (0) 1793 511521 FAX: 44 (0) 1793 453218 Air BP BP Exploration & OIl Inc. Maple Plaza ll - 1N 6 Campus Drive Parsippany, NJ 07054 USA TEL: 973-401-4350 FAX: (973) 401-4355 URL: http://www.airbp.com TABLE 17, Approved Lubricating Oils - 4-Centistoke BRAND Castrol 4000 SUPPLIER Castrol Industrial North America Inc. 1001 West 31st Street Downers Groove, Il 60515 USA TEL: 1-800-462-6835 TEL: (630) 241-4000 FAX: (630) 241-1957 URL: http://www.castrolindustrial.com Castrol Canada Inc. 3620 Lakeshore Blvd. West Toronto, Ontario Canada M8W 1P2 TEL: (416) 252-5511 FAX: (416) 252-7315 Castrol Specialised Industrial (U.K.) Wakefield House Pipers Way Swindon, Wilts SN3 1RE England TEL: 44 (0) 1793 512712 TEL: 44 (0) 1793 511521 FAX: 44 (0) 1793 453218 72-00-00 ENGINE - DESCRIPTION AND OPERATION Page 82 Nov 04/2005 PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3045542 TABLE 18, Approved Lubricating Oils - PWA 521, Type II (5-Centistoke) ‘‘THIRD GENERATION’’ BRAND Aero Shell Turbine Oil 560 DELETED DELETED E. SUPPLIER Shell Canada Ltd. 400-4th Avenue S.W. Calgary, Alberta Canada T2P 0J4 TEL: 1-800-661-1600 Shell International Petroleum Co. Shell Center London, SE1 7NA England TEL: 44 (0) 20 7934 1234 FAX: 44 (0) 20 7934 8060 URL: http://www.shell.com DELETED DELETED Oil Analysis (1) Before obtaining an oil sample to analyze, start engine and run until oil temperature is 70° (158°F) minimum. Shutdown engine (Ref. Adjustment/Test). (2) If in the absense of a maximum TAN number from an oil brand specification and the TAN is above 1.0, or water content is more than 800 parts per million, either by weight or volume, proceed as follows: (a) Drain and discard oil from main oil tank and reduction gearbox (Ref. Engine/Servicing). (b) Refill engine with fresh oil. (Ref. Engine/Servicing). (c) Run engine (Ref. Adjustment/Test). (d) Drain and discard oil from main oil tank and reduction gearbox (Ref. Engine/Servicing). (e) Refill engine with fresh oil. (Ref. Engine/Servicing). NOTE: 1. The value of TAN in unused oil conforming to specification varies depending on brand and manufacturer. NOTE: 2. As oil deteriorates, the color becomes black and a strong harsh odor is given off. Although this in itself is not a reason to change the oil, it would be an indication that the oil should be analyzed. NOTE: 3. Use a Titra-Lube TAN Test Kit (P/N TI-TAN) to analyze the oil. The kit can be obtained from the following address or contact a local distributor for availability of the kit: 72-00-00 ENGINE - DESCRIPTION AND OPERATION Page 83 Nov 04/2005 PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3045542 Dexsil Chemical Corp. 1 Hamden Park Drive Hamden, CT 06517 USA TEL: 1-800-4-DEXSIL 203-288-3509 FAX: 203-248-6523 72-00-00 ENGINE - DESCRIPTION AND OPERATION Page 84 Nov 04/2005 PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3045542 ENGINE - FAULT ISOLATION 1. 2. General A. This section provides a series of checks to enable problems occurring in the operation of the engine to be isolated and rectified. B. Reference should be made to the flight log and engine log for any entry relating to the current problem. Consumable Materials Not Applicable 3. Special Tools Not Applicable 4. Fixtures, Equipment and Supplier Tools Not Applicable 5. Fault Isolation Chart Locations For PW127H engines, refer to Chapter 72-00-01 for a series of charts having checks to enable problems that occur in the operation of the engine to be isolated and rectified. For PW127H engines, refer to Chapter 72-00-02 for a series of charts having checks to enable problems that occur in the electronic control system to be isolated and rectified. 72-00-00 ENGINE - FAULT ISOLATION Page 101/102 Sep 03/99 PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3045542 ENGINE - MAINTENANCE PRACTICES 1. General A. During removal of engine components, such as tubes, look for indications of scoring, burning or other undesirable conditions. To facilitate reinstallation, observe the location of each component during removal. Tag unserviceable components for investigation and possible repair. B. Suitable plugs, caps, and other coverings shall be used to protect all openings as they are exposed. NOTE: Dust caps used to protect open lines against contamination shall always be installed over and not inside the tube ends. Flow through the lines may be blocked off if lines are inadvertently installed with dust caps inside the tube ends. C. If items are dropped into the engine, the dropped articles must be retrieved immediately. D. Before assembling or installing any part, be sure it is thoroughly clean. E. Lockwire, keywashers and cotterpins must not be reused. F. Use new gaskets, backup rings and packings at assembly. Make sure new non-metallic parts (i.e., carbon seal) show no sign of deterioration due to length of time in storage. G. When installing engine parts requiring the use of a hammer to facilitate assembly or installation, use only a plastic or rawhide hammer. H. When used, masking tape must be removed and parts cleaned with petroleum solvent (PWC11-027) or cleaner (PWC11-031) before assembly into the engine. Tape residue can cause corrosion at engine running temperatures. NOTE: 2. Tergit (PWC11-031) is recommended to be used as an alternative to petroleum solvent when the use of this product is restricted by local environmental and/or health legislation. I. Ensure that antiseize compounds are applied in a thin, even coat. Excess compound must be completely removed to avoid contamination of adjacent parts, passages or surfaces. J. All external joint faces must be sealed with compound (PWC09-003) after installation or test. Protect all external bolts and studs with a film of silicone compound. Do not apply silicone compound to any threads of bolts used to retain accessories. These threads are to be coated with engine oil (PWC03-001) as required by normal torquing procedures. K. Parts coated with corrosion-preventive compound must have all traces of the compound removed before assembly. Consumable Materials The consumable materials listed below are referred to in this section. For more data, refer to the CONSUMABLE MATERIALS section at the beginning of this manual. 72-00-00 ENGINE - MAINTENANCE PRACTICES Page 201 Nov 04/2005 PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3045542 WARNING: 3. READ THE MATERIAL SAFETY DATA SHEETS BEFORE YOU USE THESE MATERIALS. SOME MATERIALS CAN BE DANGEROUS. Item No. Name PWC03-001 PWC05-002 PWC05-018 PWC05-018A PWC05-046 PWC05-061 PWC05-103 PWC05-256 PWC09-003 PWC11-014 PWC11-027 PWC11-031 Oil, Engine Dye, Layout Marker, Pen and Pencil Marker, Ink Cloth, Abrasive, Coated, Crocus Marker, Pencil Enhancer, Contact, Electrical Compound, Sealing Alcohol, Isopropyl Petroleum Solvent Cleaner, Engine Parts Special Tools Special tools are identified in procedural text by part number in parentheses. 4. Tool No. Name PWC58104 Wrench Fixtures, Equipment and Supplier Tools The fixtures, equipment and supplier tools listed below are referred to in procedural text. Name Glass container Pliers, Soft-jaw - Glenair (TG69) Wrench, Mini-strap - Glenair (TG70) 5. Standard Torques A. B. Torque limits are to be interpreted as follows: (1) Torque values are at room temperature. (2) Angles of turn are in degrees. (3) All torques specified in this manual are the effective torques which must be applied to the part. They do not take into consideration any adapter or extension used when applying the torque. Thread lubricant is engine oil (PWC03-001), unless otherwise specified. NOTE: C. Silver-plated bolts do not require lubrication prior to assembly. Flange bolts must be torqued in a diametrically opposed sequence. 72-00-00 ENGINE - MAINTENANCE PRACTICES Page 202 Nov 04/2005 in.in.60 Nm When using an extension or adapter which does not change the effective length of a standard torque wrench (Ref. Therefore. 201. 3045542 6. the manufacturer’s instructions must always be followed. Detail A). (76.in.72 Nm) Adapter or extension length = 3 in. D.00 mm) Then: R (lb. Checking one torque wrench against another does not give accurate results.20 + 381.72 76.) = a bT +b = 15 x 1440 3 + 15 = 1200 lb. General Check and calibrate torque wrenches before use. Standard Torque Wrenches and Extensions When using an extension or adapter with standard torque wrenches (Ref. Fig. a correction of the indicated torque reading is required and the following formula must be used: a b c R T R= Effective length of extension or adapter Effective length of torque wrench Distance through which force is applied to part Reading on scale or dial of torque wrench Desired torque on the part bT c = bT a+b Formula to be used Example: Desired torque (T) = 1440 lb.20 mm) Torque wrench length = 15 in. (162. 72-00-00 ENGINE . Detail B). E.00 = 135. (381. Some wrenches are sensitive to the method of support used during the torquing procedure.00 x 162. OR R (Nm) = 381. Torque Wrenches A. Parts heated or cooled before assembly must be at room temperature when the final torque is applied.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. B. Torque should be applied slowly and evenly for consistency and accuracy.MAINTENANCE PRACTICES Page 203 Nov 04/2005 . a correction of the indicated torque reading is not required. 3045542 a b c DETAIL A b c DETAIL B C12854A Torque Wrench and Extension Figure 201 72-00-00 ENGINE .PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO.MAINTENANCE PRACTICES Page 204 Nov 04/2005 . 05 mm) square drive bar (supplied with the wrench) transmits the output torque of the geartrain.70 mm) diameter pins on the wrench adapter transmit counteracting loads. as follows: (a) Install socket on nut.MAINTENANCE PRACTICES Page 205 Nov 04/2005 . except for rotational direction of ratchet and input shaft. (19. The input drive rotation is opposite to that required when turning the nut. allowing it to be withdrawn from the adapter. A 3⁄4 in. (e) Turn ratchet (located on front face of power wrench). (b) Install appropriate countertorque adapter on part being assembled.. (g) Continue rotating until torque indicator reaches required reading on scale. the appropriate conversion must be made when torquing to values specified in lb. adapter and socket. 72-00-00 ENGINE . 3045542 C. drive bar. repeat step (4).PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. (f) Insert input driveshaft (handle or power operated) in input shaft.in. (2) When tightening a nut. when loosening. (c) Install power torque wrench on adapter and engage both pins. (4) Nuts are tightened. which must be reversed. Two 1⁄2 in. the input drive must be turned counterclockwise. (19. NOTE: Follow instructions marked on adapter showing direction of rotation required when torquing and untorquing. (d) Insert 3⁄4 in. Power Torque Wrenches (1) Power torque wrenches employ a high ratio geartrain operated by a handcrank (supplied with the wrench) or a pneumatic ratchet drive tool. (h) Remove the power wrench as follows: (i) (5) 1 Alter the position of the ratchet. Remove power wrench. To untorque. the reverse rotation applies. (12.05 mm) output drive bar into wrench output shaft and turn until bar engages socket. (3) A countertorque adapter is installed on the nut when torque is applied to turn the part and not the nut. NOTE: Since the torque indicator is calibrated in lb. 2 Reverse direction of rotation of the input drive until the indicator returns to zero (green band). Wrench input and output shafts rotate in the same direction. using the power torque wrench and appropriate countertorque adapter.ft. Rotate driveshaft in same direction as that required for output shaft. This removes the holding pressure on the wrench. MAINTENANCE PRACTICES Page 206 Nov 04/2005 .27) 0.52) 0.4375-14 16.5 (1.2500-12 143.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO.36) 0.0 (4.78) 0.27) 0.0 (0.050 (1.050 (1.06) 0.070 (1.91) 0.0 (16. The locking torque must.78) 1.39) 0.16) NOTE: Protrusion dimension includes chamfer.5 (0.040 (1.0 (15.61) 0.1250-8 137.0000-14 92.050 (1.060 (1.0 (13.1250-12 117.0 (10.5 (0.090 (2.11) 0.3125-24 6.IN.070 (1.71) 0.02) 0.71) 0.06) 0. 72-00-00 ENGINE .5625-18 24.52) 1.5 (0.5 (0.0 (9.52) 1.0 (7.0 (2. (mm) 0. Table 201).0 (12.0 (5. (Nm) MINIMUM PROTRUSION IN.0 (3.27) 0.0 (0.060 (1.8750-9 82.3750-16 12.5 (0. care must be taken to ensure the fastener is not seated. (3) To ensure the locking feature in the self-locking nut engages the fully formed external thread on the mating part. This ensures that only the torque necessary to overcome the friction holding the thread is measured.52) 0.8750-14 70.78) 0.52) 0.11) 0.78) 0.IN.2500-28 3.3125-18 7. not be less than the values shown in Table 201. (Nm) 0.070 (1.0 (2.040 (1.070 (1.5000-20 18.050 (1. TABLE 201.1120-40 MINIMUM PROTRUSION IN. unless otherwise specified.1900-32 2.0 (1.78) 1.1640-36 1.48) 0.0 (1.060 (1.52) 0.3750-24 9.11) 0.29) 0.5625-12 30.85) 0.03) 1.1380-40 1.5 (0. (2) When checking self-locking torque.1120-48 0.5 (0.22) 0.5000-14 24.23) 0.65) 0.23) 0.03) 0.02) 0.0000-8 110.1640-32 1.1250-40 1.43) 0.0 (2.6250-11 40.5 (1.1900-24 2.0 (0. Oil Lubricated Parts Torque limits.40) 0.060 (1.73) 0.07) 0.86) 0.0 (0.0 (3.52) 0.4375-20 14.060 (1.51) 0.17) 0.0 (6.080 (2. (mm) THREAD SIZE TORQUE LB.27) 0. B.080 (2. detailed in the assembly instructions for oil lubricated parts.060 (1. a minimum thread protrusion is required (Ref. General Torque Recommendations A.17) 0.2500-20 4. Self-locking Nuts and Helical Coil Inserts (1) The locking torque for self-locking nuts and helical coil inserts must be checked at assembly.40) 0.0 (0. 3045542 7. apply only if engine oil (PWC03-001) is used on the parts.7500-10 60.080 (2.27) 0.1380-32 1.03) 0. Minimum Locking Torque for Self-locking Nuts and Helical Coil Inserts and Minimum Thread Protrusion for Self-locking Nuts THREAD SIZE TORQUE LB.7500-16 50.03) 0.5 (0.6250-18 32.58) 0. B. Tube Nuts If leakage occurs at a tube nut. all unbent keys must be bent. If maximum torque is exceeded. burrs and/or foreign matter. keywashers and cotterpins must not be reused. (c) At least one key must be bent sufficiently to meet gap requirement. Fig. If necessary. (d) Fuel nozzle keywasher keys must not be bent using impact-type tools. (c) Replace nut if locking slot cannot be aligned within the recommended torque limits. Fig. causing damage. do not use sharp-pointed tools. on becoming detached. use new parts. 3045542 C. do not attempt to correct by overtorquing. can pass through the engine. D. General Lockwasher. Standard and Stepped Studs When the torque required to drive a stud to the correct projection length is not within the minimum and maximum limits. Use of this type of tool can lead to failure of keys. Disassemble fitting and check for nicks. E. a new stud must be used. (b) If locking slot is not aligned with the associated lockwire or cotterpin hole. (2) Key-type (Ref. back off nut 1/2 turn and repeat procedure. 204) 72-00-00 ENGINE . 8. Other keys may be bent in any convenient way. which. Various examples of these locking washers are shown in Figure 202. (b) Pre-bent keys must be positioned against side of locking hole to prevent movement of bolt being locked.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 203) (a) To prevent reuse.MAINTENANCE PRACTICES Page 207 Nov 04/2005 . (3) Cup-type (Ref. Castellated Nuts (1) Install castellated nuts as follows: (a) Tighten nut to the minimum recommended torque. Keywashers (1) General (a) When bending keys. A minimum of 75% of its width as measured at base of key must engage flat on bolt being locked. increase torque until alignment is obtained. Locking A. 3045542 CUP WASHER KEY WASHER KEY WASHER CUP WASHER CUP LOCKING WASHER KEY WASHER KEY WASHER KEY WASHER KEY WASHER TAB WASHER TAB WASHER C3036 Typical Locking Washers Figure 202 72-00-00 ENGINE .MAINTENANCE PRACTICES Page 208 Nov 04/2005 .PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 50mm) MAXIMUM GAP FOR FASTENERS WITH THREAD SIZES GREATER THAN 0. 3045542 DIRECTION TO LOOSEN NUT A 75% OR MORE OF KEY WIDTH FOR AT LEAST ONE KEY DETAIL A 0.010 INCH (0.Installation Figure 203 72-00-00 ENGINE .3125 INCH (7.93mm) 0.MAINTENANCE PRACTICES Page 209 Nov 04/2005 .020 INCH (0.25mm) MAXIMUM GAP FOR FASTENERS WITH THREAD SIZES EQUAL TO OR LESS THAN 0.3125 INCH (7.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO.93mm) C30219 Keywashers (Typical) . 3 Punch: Impact forms indentations in cupwasher OD. (1. (c) Crimping should be carried out using one of the tools listed below: 1 Drift-type tool: This tool consists of a ring with prongs on the ID. This involves marking cupwasher and an adjacent surface. 2 Squeeze-action tool: This tool forms indentations by pressing cupwasher OD into nut slots. if any.12 mm). (2) Alignment (a) Check components before securing with lockwire to make sure that they have been correctly torqued. NOTE: Use of a punch should be avoided where possible and drift or squeeze-type tools used where practical. (b) Never overtorque or loosen components to obtain correct hole alignment. This enables any rotation of cupwasher.27 mm).PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. This avoids sharp or projecting ends. when tightening nut. C. The spherical radius must not be less than 0. This counteracts the natural tendency of part to loosen. (d) The portion of the tool that forms indentations must be spherically shaped. (c) Lockwire must never be overstressed. after installation. Also. Lockwire must be pulled tight when being twisted and have minimum tension. when installed. (0. which could present a safety hazard. 3045542 (a) The OD of cup-type keywashers must be deformed (crimped) into at least two of the slots in the associated nut.005 in. (b) The gap between nut OD and cupwasher ID must not exceed 0. Lockwire (1) General (a) Lockwire must be tight. The radius must not be larger than is required to fully form the indentation into the associated slot.MAINTENANCE PRACTICES Page 210 Nov 04/2005 . ensure the lockwire holes are correctly positioned in relation to one another. (d) Lockwire ends must be bent towards the engine or part. to prevent failure due to rubbing or vibration. It will break under vibration if twisted too tightly. the position of cupwasher must not change during assembly. the tool forms indentations on cupwasher OD. (e) To prevent shearing of internal keys. When placed over cupwasher and moved in an axial direction. Replace component if necessary. (b) Lockwire must be installed in a manner that tends to tighten and keep a part locked in place. to be detected.050 in. 72-00-00 ENGINE . Installation Figure 204 72-00-00 ENGINE . 3045542 A DIAPHRAGM 0D B B EXTERNAL CUP WASHER A SECTION A−A SECTION C−C C SECTION B−B C INTERNAL CUP WASHER C12856 Cup-type Keywashers .MAINTENANCE PRACTICES Page 211 Nov 04/2005 .PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. must be 0. (2) Internal-type rings must not be compressed beyond the point where ends of the ring meet.52-4. 9. Taking care. Marking of Parts A. that of original marking. (3) All marking characters. unless otherwise specified. (2) Except where otherwise specified. (4) After installation. characters not less than 0. cut near component locking hole. In special cases. Although there are numerous applications for lockwire installation.060 to 0.016 inch (0. (5) Procedure (a) Figure 205 illustrates typical procedure and Figure 206 illustrates basic examples. (c) When cutting off ends. or in a location similar to.06 mm) high. (4) Removal (a) Do not twist lockwire off with pliers. reidentification of parts must be accomplished adjacent to. General (1) Marking of engine parts.250 inch (6. which could cause damage to associated component. when marking area is governed by size or configuration of part. without permanent distortion occurring. ensure each retaining ring is completely seated in its groove. Retaining Rings (1) Retaining rings must be installed using approved retaining ring pliers.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. assemblies. D.35 mm) in height are permitted.41 mm) nor more than 0. kinked or mutilated.160 inch (1. Only applicable Pratt & Whitney Canada marking methods must be used. 3045542 (3) Installation (a) Secure lockwire at the ends or at a point that will not be twisted. or weldments shall be applied so as to ensure maximum legibility and durability of mark but in a manner that will not affect function or serviceability of part. Ensure ends do not fall into the engine. without looseness or distortion. 72-00-00 ENGINE .MAINTENANCE PRACTICES Page 212 Nov 04/2005 . (3) External-type rings must be expanded only enough to allow installation. This ensures the twisted section is not damaged. practically all are derived from the basic examples shown. leave at least three complete turns after the loop securing the component. (b) Lockwire must not be nicked. CUT OFF EXCESS WIRE WITH DIAGONAL CUTTERS. GRASP THE WIRE BEYOND THE TWISTED PORTION AND TWIST THE WIRE ENDS COUNTER− CLOCKWISE UNTIL TIGHT. DURING THE FINAL TWISTING MOTION OF THE PLIERS. BEND THE WIRE DOWN AND UNDER THE HEAD OF THE BOLT. BRING THE FREE END OF THE WIRE AROUND THE BOLT HEAD IN A COUNTERCLOCKWISE DIRECTION AND UNDER THE END PROTRUDING FROM THE BOLT HOLE. BE SURE WIRE IS TIGHT AROUND HEAD. INSERT PROPER GAGE WIRE.MAINTENANCE PRACTICES Page 213 Nov 04/2005 . THEN UNDER THE OTHER END OF THE WIRE. TWIST WIRE UNTIL WIRE IS JUST SHORT OF HOLE IN THE SECOND BOLT. C194C Lockwire Installation Procedure Figure 205 72-00-00 ENGINE . GRASP UPPER END OF THE WIRE AND BEND IT AROUND THE HEAD OF THE BOLT. INSERT THE UPPERMOST WIRE. TWIST THE WIRE IN A COUNTERCLOCKWISE DIRECTION. TWIST IN A CLOCKWISE DIRECTION UNTIL THE WIRE IS TIGHT. 3045542 10:30 O’CLOCK 4:30 O’CLOCK POSITION THE HOLES.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. THROUGH THE HOLE WHICH LIES BETWEEN THE NINE AND TWELVE O’CLOCK POSITIONS. WHICH POINTS TOWARDS THE SECOND BOLT. KEEPING WIRE UNDER TENSION. WHEN TIGHTENED THE WIRE SHALL HAVE APPROXI− MATELY 7 TO 10 TWISTS PER INCH. GRASP THE END OF THE WIRE WITH A PAIR OF PLIERS AND PULL THE WIRE TIGHT. EXAMPLE 10 EXAMPLE 10 SHOWS HOLLOW HEAD PLUGS WIRED WITH THE TAB BENT INSIDE THE HOLE TO AVOID SNAGS AND POSSIBLE INJURY TO PERSONNEL WORKING ON THE ENGINE. SQUARE HEAD PLUGS. AND OTHER SIMILAR PARTS WHICH ARE WIRED SO THAT THE LOOSENING TENDENCY OF EITHER PART IS COUNTERACTED BY TIGHTENING OF THE OTHER PART.7 AND 8 SHOW METHODS FOR WIRING VARIOUS STANDARD ITEMS. C195_1 Examples of Lockwire Installation Figure 206 (Sheet 1 of 3) 72-00-00 ENGINE . EXAMPLE 5 EXAMPLE 6 EXAMPLE 7 EXAMPLE 8 EXAMPLES 5.MAINTENANCE PRACTICES Page 214 Nov 04/2005 . NOTE THAT WIRE SHOULD ALWAYS BE APPLIED SO THAT TENSION IS IN THE TIGHTENING DIRECTION. EXAMPLE 9 EXAMPLE 9 SHOWS THE METHOD FOR WIRING BOLTS IN DIFFERENT PLANES. FILLISTER HEAD SCREWS. THE LOOP WILL BE SECURED IN PLACE AROUND THE HEAD OF THAT BOLT. 3045542 EXAMPLE 1 EXAMPLE 2 EXAMPLE 3 EXAMPLE 4 EXAMPLES 1.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. WIRE MAY BE WRAPPED OVER THE UNIT RATHER THAN AROUND IT WHEN WIRING CASTELLATED NUTS OR ON OTHER ITEMS WHEN THERE IS A CLEARANCE PROBLEM. IS COUNTER−CLOCKWISE TO KEEP THE LOOP IN POSITION AGAINST THE HEAD OF THE BOLT. THE WIRE ENTERING THE HOLE IN THE THIRD UNIT WILL BE THE LOWER WIRE AND BY MAKING A COUNTER−CLOCKWISE TWIST AFTER IT LEAVES THE HOLE.6.2. FROM THE SECOND TO THE THIRD UNIT. THE DIRECTION OF TWIST. EXAMPLE 11 EXAMPLE 11 SHOWS CORRECT APPLICATION OF SINGLE WIRE TO CLOSELY SPACED MULTIPLE GROUP.3 AND 4 APPLY TO ALL TYPES OF BOLTS. WIRE SHOULD BE APPLIED AS SHOWN IN EXAMPLES 19 AND 20 WITH CAUTION BEING EXERTED TO ENSURE THAT WIRE IS WRAPPED TIGHTLY AROUND THE FITTING. EXAMPLE 14 EXAMPLE 15 EXAMPLE 14 SHOWS BOLT WIRED TO A RIGHT ANGLE BRACKET WITH THE WIRE WRAPPED AROUND THE BRACKET.MAINTENANCE PRACTICES Page 215 Nov 04/2005 . WHERE NO LOCKWIRE LUG IS PROVIDED. EXAMPLE 21 SMALL SIZE COUPLING NUTS SHALL BE WIRED BY WRAPPING THE WIRE AROUND THE NUT AND INSERTING IT THROUGH THE HOLES AS SHOWN. EXAMPLE 17 EXAMPLE 18 EXAMPLE 19 EXAMPLE 16 EXAMPLE 16 SHOWS CORRECT METHOD FOR WIRING THE COUPLING NUT ON FLEXIBLE LINE TO THE STRAIGHT CONNECTOR BRAZED ON RIGID TUBE. EXAMPLE 20 FITTINGS INCORPORATING WIRE LUGS SHALL BE WIRED AS SHOWN IN EXAMPLES 17 AND 18. EXAMPLE 15 SHOWS CORRECT METHOD FOR WIRING ADJUSTABLE CONNECTING ROD. C195_2 Examples of Lockwire Installation Figure 206 (Sheet 2) 72-00-00 ENGINE . 3045542 EXAMPLE 12 EXAMPLE 13 EXAMPLES 12 AND 13 SHOW METHODS FOR ATTACHING LEAD SEAL TO PROTECT CRITICAL ADJUSTMENTS.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 27 AND 28 SHOW THE VARIOUS STANDARD FITTINGS WITH CHECK NUT WIRED SO THAT IT NEED NOT BE DISTURBED WHEN REMOVING THE COUPLING NUT. 3045542 EXAMPLE 22 EXAMPLE 23 COUPLING NUTS ATTACHED TO STRAIGHT CONNECTORS SHALL BE WIRED AS SHOWN WHEN HEX IS AN INTEGRAL PART OF THE CONNECTOR.MAINTENANCE PRACTICES Page 216 Nov 04/2005 . C195_3 Examples of Lockwire Installation Figure 206 (Sheet 3) 72-00-00 ENGINE .PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. EXAMPLE 25 STRAIGHT CONNECTOR (BULKHEAD TYPE) EXAMPLE 26 EXAMPLE 27 EXAMPLE 28 EXAMPLES 26. EXAMPLE 24 COUPLING NUTS ON A TEE SHALL BE WIRED AS SHOWN ABOVE SO THAT TENSION IS ALWAYS IN THE TIGHTENING DIRECTION. sharp edge. 2 Manual: Tool is hand-guided and has a single tip. whereby characters are formed by action of an acid on surface of part. (b) Permanent markings must not extend on to any radius. particularly hand arc scribing. Permanent Marking (1) General (a) Permanent methods of marking are those in which marking is legible throughout entire service life of part. (6) Do not use soapstone to mark engine parts. 3 Mechanical: Tool is mechanically guided and has a single tip or multiple tips. The vibration peening method can be used to mark parts originally marked by diamond drag or roll marking. (4) Electric arc scribing. or fillet adjoining designated marking surface. radius-tipped. 3045542 B. conical tool.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 72-00-00 ENGINE . Temporary Marking (1) General (a) Temporary methods of marking are those in which the marking will ensure identification or facilitate handling. (2) Marking Methods (a) Electrolytic Etch CAUTION: DO NOT ELECTROLYTICALLY ETCH ANODIZED SURFACES. is not recommended because of its possible corrosive effects. NOTE: C.MAINTENANCE PRACTICES Page 217 Nov 04/2005 . whereby characters are produced by action of an electric arc between surface and an electrode (scriber). has been found unsuitable for jet engine parts and must not be used. (b) Vibration Peening 1 Characters are produced by a vibrating. storage and final assembly. 1 Characters are produced by electrolysis confined to area of characters by a stencil. chamfer. (5) Acid etching. MAINTENANCE PRACTICES Page 218 Nov 04/2005 . use ink types as follows: 400-1 (black) 400-2 (red) 400-7 (purple) (d) Micro Supreme No. does not move relative to a contacting surface. LEAD OR SIMILAR RESIDUE. NOTE: (3) Ink stamping and electrolytic etching may be applied to any surface that. 71 (red pencil) (PWC05-103) may be used on parts that are not directly exposed to the gas path. 3045542 CAUTION: LEAD OR METALLIC PENCILS. providing no surface damage occurs. This type of marking is easily removed and is therefore less durable. an ink that does not damage the surface. 72-00-00 ENGINE . Characters are produced by electrolysis confined to an area by a stencil. 142 (purple dye) (PWC05-002). (b) Ink Marking 1 Characters are produced by applying. after assembly. (f) Design Spectracolor Silver 1428 (Silver Pencil) (PWC05-018) or Verithin 753 (Silver Pencil) (PWC05-018A).PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. (2) Marking Methods (a) Electrolytic Etch CAUTION: DO NOT ELECTROLYTICALLY ETCH ANODIZED SURFACES. COPPER. (b) Marks-a-Lot Marker (PWC05-018). Hot and Cold Section Engine Parts (a) Felt Wick Pen and Speedy Dry Ink (PWC05-018). (c) Brushpen No. Marking Materials. OR ANY MARKING METHOD LEAVING A DEPOSIT OF CARBON. ZINC. Heavy deposits of marking material could adversely affect clearances and run-out. (e) Phano No. by any method. 1 This method is sometimes used as temporary marking. 57 (PWC05-018) and Tex-Rite Instant Dry Ink (PWC05-046). (b) A marking pencil must not be used to apply marks to the mating surfaces of finished machined parts. MAY CAUSE A REDUCTION IN FATIGUE STRENGTH DUE TO CARBURIZATION OR INTERGRANULAR ATTACK WHEN THE PART IS HEATED. 2 Inks used in marking may have a light etching action. backup ring (3) and packing (4) on tee/elbow fitting (1). This point will be recognized by an increase in torque. 11. and the excess completely removed. mark. using marker (PWC05-018). new preformed packings must be coated with a thin film of engine oil unless otherwise stated. This includes turbine blades and disks. the angular location of the tee/elbow on the engine or unit. (2) Antiseize and anti-galling compounds must be applied in a thin. Installation (Ref. This avoids contamination of adjacent parts. WHICH COULD CAUSE ENGINE MALFUNCTION. Fig. 451 (black). even coat. packing retainer (backup ring) and thread of tee/elbow with a light film of oil (PWC03-001). (2) Install nut (2). 207) (1) Lubricate preformed packing. General CAUTION: LUBRICATION PLUS PROPER ASSEMBLY WILL PREVENT DAMAGE TO PACKINGS. turbine vanes and the combustion chamber liner. (d) Carters Ink No. (3) Turn nut until backup ring is seated in non-threaded annulus of tee/elbow and packing is against first thread. Tees and Tee Assemblies A. passages and/or surfaces. Lubrication A. Before removal. allowing nut to turn with tee/elbow until packing contacts boss mating face. Elbow Assemblies. pressing backup ring into counterbore of nut. (1) Prior to installation. (c) Dykem Ink KXX122 (white). (5) Marking Materials. (b) Dykem Ink KX425 (black). Cold Section Engine Parts Only (PWC05-046) (a) Volgers Opaque Ink (black). 10. 72-00-00 ENGINE . Tube-to-Boss Elbows. (4) Install tee/elbow into boss (5) on unit.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. Removal (1) B. Elbow Adapters. 3045542 (4) Marking Materials. Hot Section Engine Parts Only (a) Use layout dye (PWC05-002) (lightly applied) to mark parts that are directly exposed to the engine gas path.MAINTENANCE PRACTICES Page 219 Nov 04/2005 . MAINTENANCE PRACTICES Page 220 Nov 04/2005 . 3045542 1 1 2 2 3 3 4 4 STEP 1 STEP 2 1 1 2 2 3 3 4 4 5 5 STEP 3 STEP 4 C8818 Installation of Typical Elbow/Tee Fitting Figure 207 72-00-00 ENGINE .PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. (3) 13. There are three basic styles. Bulkhead Couplings and Tube Connector Nipples A. With elbow fitting in correct aligned position. Should the tee/elbow tighten in the nut before completion of initial 1-1⁄2 turns or during final alignment. Fig. they must be correctly and fully coupled to ensure maximum sealing. CAUTION: OVERTORQUING WILL DAMAGE THREADS OF MATING PARTS. and there must be no extrusion of preformed packing or packing retainer. (2) Install preformed packing on fitting and screw fitting into boss. Installation Procedure (1) Style 1 (Ref. 3045542 Key to Figure 207 1. the tee/elbow may be turned inward to a maximum of one turn to facilitate alignment. NOTE: (6) From this position. OR ACCESSORY. When connecting harness connectors to their respective receptacles. Installation CAUTION: INSTALL FITTINGS (MS9193 AND SIMILAR) WITH STRAIGHT-THREADED END FITTING UNIT. General (1) B. Wiring Harness Connectors A. 208) 72-00-00 ENGINE . 5. unless otherwise stated in specific installation instructions. the nut may be allowed to turn with the tee/elbow for the remainder of the distance.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. (5) Hold nut stationary and turn tee/elbow into boss a further 1-1⁄2 turns. tighten nut and torque to value detailed in relevant installation instruction. Tighten fitting and torque to value detailed in relevant installation instruction. Straight Nipples or Adapters. Fitting Nut Backup Ring Packing Boss Metal-to-metal contact between nut and boss must be obtained without exceeding recommended torque.MAINTENANCE PRACTICES Page 221 Nov 04/2005 . 3. AND 37-DEGREE CONE SEAT END INTO MATING TUBE ASSEMBLY. 2. (1) Lubricate preformed packing with a light film of engine oil (PWC03-001). 4. NOTE: 12. NOTE: Let the liquid flow downward on each pin. using one of the following methods: 72-00-00 ENGINE . NOTE: 2 Method 2. apply reasonable force to ensure connector coupling nut is firmly tightened and metal-to-metal bottoming of connector is achieved. apply reasonable force to ensure connector coupling nut is firmly tightened and metal-to-metal bottoming of connector is achieved. NOTE: Let the liquid flow downward on each pin. (b) Use 1 ml of alcohol (PWC11-014) with 15 ml of electrical contact enhancer (PWC05-256) and mix thoroughly. (11. 1 Method 1. NOTE: (2) Mini-strap wrench has a design slip torque of 100 lb. (c) Put a drop of the diluted electrical contact enhancer (PWC05-256) on each connector and receptacle pin. It is recommended to further torque connector coupling nuts. Soft-jawed pliers have a design slip torque of 100 lb.in.MAINTENANCE PRACTICES Page 222 Nov 04/2005 .in. (c) Put a drop of the diluted electrical contact enhancer (PWC05-256) on each connector and receptacle pin. 3045542 (a) The connector has a blue color band and two short orange markings or a full orange color band on each side of a slot.3 Nm). It is recommended to further torque connector coupling nuts. (11. Soft-jawed Pliers (Glenair TG69) a Using soft-jawed pliers (Glenair TG69). (d) Instructions: Tighten each connector nut by hand until witness band(s) on mating receptacle is/are covered. using one of the following methods: CAUTION: DO NOT USE STEEL-JAWED PLIERS TO TIGHTEN CONNECTORS.3 Nm). Mini-strap Wrench (PWC58104) or (Glenair TG70) a Using mini-strap wrench (PWC58104) or (Glenair TG70). 208) (a) The connector has a blue color band and its associated receptacle has a red and a blue color band. (d) Instructions: Torque by hand until lock indicator (visible in the slot) is aligned with the orange markings or band.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. (b) Use 1 ml of alcohol (PWC11-014) with 15 ml of electrical contact enhancer (PWC05-256) and mix thoroughly. Fig. Style 2 (Ref. Installation Figure 208 72-00-00 ENGINE .MAINTENANCE PRACTICES Page 223 Nov 04/2005 . 3045542 STYLE 1 SLOT LOCK INDICATOR ORANGE BLUE STYLE 2 STYLE 3 BLUE BLUE COLORED RED C30216A Electrical Wiring Harness Connectors .PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. NOTE: Let the liquid flow downward on each pin. (11. using one of the following methods: CAUTION: DO NOT USE STEEL-JAWED PLIERS TO TIGHTEN CONNECTORS. Soft-jawed Pliers (Glenair TG69) 72-00-00 ENGINE . Fig.3 Nm). Method 2. NOTE: 2 Method 2. Soft-jawed pliers have a design slip torque of 100 lb.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. (d) Instructions: Tighten each connector nut by hand until witness band(s) on mating receptacle is/are covered. (11. apply reasonable force to ensure connector coupling nut is firmly tightened and metal-to-metal bottoming of connector is achieved. Soft-jawed Pliers (Glenair TG69) a Using soft-jawed pliers (Glenair TG69).in. (c) Put a drop of the diluted electrical contact enhancer (PWC05-256) on each connector and receptacle pin. NOTE: 2 Mini-strap wrench has a design slip torque of 100 lb. 208) (a) The receptacle has a blue or black color band. NOTE: (3) Mini-strap wrench has a design slip torque of 100 lb. apply reasonable force to ensure connector coupling nut is firmly tightened and metal-to-metal bottoming of connector is achieved. It is recommended to further torque connector coupling nuts.3 Nm). apply reasonable force to ensure connector coupling nut is firmly tightened and metal-to-metal bottoming of connector is achieved.in.in. 3045542 CAUTION: DO NOT USE STEEL-JAWED PLIERS TO TIGHTEN CONNECTORS. Style 3 (Ref. 1 Method 1. 1 Method 1. Mini-strap Wrench (PWC58104) or (Glenair TG70) a Using mini-strap wrench (PWC58104) or (Glenair TG70). (b) Use 1 ml of alcohol (PWC11-014) with 15 ml of electrical contact enhancer (PWC05-256) and mix thoroughly. Mini-strap Wrench (PWC58104) or (Glenair TG70) a Using mini-strap wrench (PWC58104) or (Glenair TG70). (11.3 Nm).MAINTENANCE PRACTICES Page 224 Nov 04/2005 . dowels and similar protruding parts for alignment and projection length. lack of lubrication. Inspection Procedures (1) All inspection procedures must be carried out in a lighted. clean and dust-free area. moisture. grinding. NOTE: 14. check the following: (a) Holes in cases. (f) Studs. Soft-jawed pliers have a design slip torque of 100 lb. shock or extension of minor damage such as scratches. nicks. Check for loose or missing parts and inspect any engine part or component that has been worn or damaged. All parts must be suitably tagged to indicate necessary repair or replacement. In addition. looseness. tool marks. A close and complete inspection is important to prolong engine life and give maximum performance. chemicals.. or from incorrect techniques during removal or installation. chips. cracks. parting and seating surfaces for smoothness and flatness. overloading. sharp edges. 3045542 a Using soft-jawed pliers (Glenair TG69). taper and wear. a certain number require use of gages and other measuring equipment. uneven load distribution.3 Nm). heat. Inspection A.in. (11. distortion. foreign matter. (d) Mounting pads. Although most parts require only a visual inspection. Some damage may be detected only by magnetic particle or fluorescent penetrant inspection methods.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 72-00-00 ENGINE . (g) Protective surface coatings for completeness. (b) Gear teeth and splines for contact patterns. (2) Inspect parts for alignment. apply reasonable force to ensure connector coupling nut is firmly tightened and metal-to-metal bottoming of connector is achieved. Damage to engine parts may also result from presence of foreign matter such as grit. Damage to engine parts may result from improper clearance.MAINTENANCE PRACTICES Page 225 Nov 04/2005 . (c) Magnesium parts for corrosion. scratches. (e) Plugs for tightness. (h) Condition of threads. Methods of inspection for specific parts and components are detailed in relevant sections of this manual. undesired movement of parts that are bolted or pressed together. Benches must be clean to keep previously cleaned parts free from dirt and dust. etc. NOTE: Use pencil carbon paper whenever a smear-type indication of surface smoothness is required. etc. manifolds. General (1) B. pipes and tubes for obstructions. minor isolated pitting is acceptable provided pitting is not greater than 0.08 mm) deep.00 in.remove rust and stains by lightly polishing with crocus cloth (PWC05-061) and engine oil (PWC03-001).13 mm).8 mm) length of tube are acceptable. (d) Pitting . Usual cause is presence of fine unwanted material between moving surfaces. (3) If a dial indicator is used.003 in. (0. (25. 3045542 (3) Inspect all external tubing. (c) Dents . vernier caliper or dial indicator must be used. When using depth gages.250 in. depending upon extent of reconditioning required to restore surface.Individual nicks should not be more than 0. (2) If a micrometer or vernier is used. Surfaces must be clean and free from dirt and burrs. Inspection Gages (1) When an inspection procedure requires a very accurate measurement. (0. a micrometer.57 mm) long. Inspection Terms For a definition of the inspection terms used throughout the manual.13 mm) should be blended out.010 in. 0.25 mm) wide and 0. (6. (0. (1. (0. 72-00-00 ENGINE .005 in. (4) When taking measurements with feeler gages. (e) Corrosion .005 in.08 mm) deep. except where special instructions apply.Well-rounded dents are acceptable provided depth does not exceed 10% of tube outside diameter and length and width are at least three times the depth. such dents must be separated by at least 0. Varying degrees of abrasion can be described as light or heavy. Clusters of pitting should be blended out to a maximum depth of 0. (0. TABLE 202.MAINTENANCE PRACTICES Page 226 Nov 04/2005 . refer to Table 202.4 mm) of ferrule scarf-welds or bonds. No more than three dents per 12 in. (0. for the following: (a) Scratches . (304. ensure that indicator base is anchored firmly and that any swivel connections are tightened securely.062 in. C. (b) Nicks .35 mm).13 mm) should be blended out to remove sharp edges. D. Scratches to a depth of 0.003 in.minor scratches having no appreciable depth are acceptable. Dents are unacceptable within 1. ensure anvil is held tight and square against part to be measured. Inspection Terms and Definitions TERM Abrasion DEFINITION A roughened area. Nicks to a maximum depth of 0. check gage for accuracy before taking measurement.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO.005 in. ensure final size of feeler is a reasonably snug fit. or any combination of these.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. by application of force on the free race. 72-00-00 ENGINE . Buckling Large scale deformation from original shape of a part. constant rotation and are subject to sudden loading. Inspection Terms and Definitions (Cont’d) TERM Blending DEFINITION An operation which removes an irregularity from a surface and results in a shallow. Burnishing Mechanical smoothing of a metal surface by rubbing. Brinelling Indentations sometimes found on the surface of ball or roller bearing parts. excessive localized heating. 3045542 TABLE 202. have brinelling tendencies. usually caused by pressure or impact of a foreign object.MAINTENANCE PRACTICES Page 227 Nov 04/2005 . Associated with flaking or peeling. by a loss or flow of material. Burning Damage to parts by excessive heat. Usual causes are excessive heat due to lack of lubrication. Bearings which do not have full. Evidenced by characteristic discoloration or in severe cases. or abnormal flame pattern. smooth depression. Blister Raised portion of surface caused by separation of surface from base. improper clearance. Usual cause is imperfect bond aggravated by presence of moisture. Usual causes are improper assembly or disassembly technique. Usually found on plated or painted surfaces. and if there is no evidence of pile-up or burning. not accompanied by removal of material but sometimes by discoloration around outer edges of area. heat or pressure. Operational burnishing is not detrimental if it covers approximately the area carrying the load. such as roller or ball bearings. unusual structural stresses. gas. Usual cause is normal operation of parts. Cracks A partial fracture. inclusions. Erosion Carrying away of material by flow of hot gases. Flaking Loose particles of metal on a surface or evidence of removal of surface covering. peening. or overheating. or chemicals. grit. scratches. Usual cause is impact of an unwanted object. extension of a nick or scratch. Usual cause is excessive stress due to sudden overloading. hot gases. Usual cause is a concentration of stress due to nicks. Inspection Terms and Definitions (Cont’d) TERM Burr DEFINITION A sharp projection or rough edge. Frosting An initial stage of scoring caused by irregularities or high points of metal welding together. or careless handling of parts. 72-00-00 ENGINE . or machining operation. or the striking of a part. Usual causes are concentrated overloading resulting from peening. Distortion Extensive deformation of the original contour of a part. Usual cause is presence of corrosion agents. 3045542 TABLE 202.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO.MAINTENANCE PRACTICES Page 228 Nov 04/2005 . or excessive localized heating. Do not confuse with flaking. or presence of chips between loaded surfaces. giving a frosted appearance. Usual causes are excessive wear. Dent Small. peening. Usual causes are flow of corroding liquids. Chipping Breaking out of small pieces of metal which have been removed mechanically. Minute particles of metal transfer to the mating surface. smoothly rounded hollow in the surface. structural stresses. Corrosion Breakdown of surface by chemical action. (Refer to Dent and Peening). or dirt-laden oil. Usual causes are carelessness in handling of parts or tools before or during assembly.MAINTENANCE PRACTICES Page 229 Nov 04/2005 . Both surface inclusions and those near the surface may be detected during magnetic inspection by grouping of magnetic particles. Gouging Displacement of material from a surface by a cutting or tearing action. 3045542 TABLE 202. whose sharp edges have been polished off. Inclusion Unwanted material in metal. 72-00-00 ENGINE . gouging or scuffing. tear marks). Metallization Coating by molten metal particles sprayed through the engine. Usual cause is presence of a comparatively large foreign unwanted body between moving parts. Heat Discoloration Staining. Inspection Terms and Definitions (Cont’d) TERM DEFINITION Galling A transfer of metal from one surface to the other of closely fitted surfaces causing damage to both surfaces. ranging from straw color (low temperature effects) to purple (high temperature effects). Examination of a fatigue fracture may reveal an inclusions at the focal point. Usual cause is a discontinuity in the material. or sand or fine unwanted particles in the engine during operation. Nick A small sharp indentation caused by striking part against another metal object. Usual cause is severe chafing or fretting action caused during engine operation by a slight relative movement of two surfaces under high contact pressure. or parts out of alignment. Surface inclusions are indicated by dark spots or lines.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. rounded furrows (such as. Do not confuse with scoring. abnormal relative motion of parts. Grooving Smooth. Usual causes are concentrated wear. or by electrolytic action. Usual cause is impact of a foreign object such as occurs in repeated blows of a hammer on part. shallow marks with a sharp bottom caused by movement of a sharp object or particles across a surface. Scuffing A dull or moderate wear of a surface resulting from a slight amount of rubbing.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. Peening Deformation of surface. 72-00-00 ENGINE . Scoring Multiple deep scratches made during engine operation by sharp edges or unwanted particles. irregularly shaped cavities (usually dark bottomed) in a surface from which material has been removed by corrosion or chipping. 3045542 TABLE 202. or sand or fine unwanted particles in the engine during operation. Usual causes are carelessness in handling of parts or tools before or during assembly. elongated gouges. Usual cause is presence of chips between loaded surfaces that have relative motion. Pitting Small. Usual causes of corrosive pitting are breakdown of surface by oxidation or some other chemical. or presence of unwanted particles. Scratches Narrow. Inspection Terms and Definitions (Cont’d) TERM DEFINITION Oxidation The chemical reaction of oxygen with metal producing discoloration of metal surfaces.MAINTENANCE PRACTICES Page 230 Nov 04/2005 . Rub A condition of fretting or chafing. Usual cause of mechanical pitting is chipping of loaded surfaces because of overloading or improper clearance. which may result in material removal. Corrosion pitting is usually accompanied by a deposit formed by a corrosive agent on base material. caused by moving along a surface with pressure and friction from another surface. subsurface holes and other imperfections. Magnetic Particle Inspection (1) F. With subsurface inclusions. subsurface inclusions. usually in the form of irregular.MAINTENANCE PRACTICES Page 231 Nov 04/2005 . Fluorescent Penetrant Inspection (1) Fluorescent penetrant inspection is a nondestructive means of inspecting nonferrous or nonmagnetic materials for cracks. Frequently not visible to the unaided eye. Do not confuse with flaking. torsion or shock. porosity and other defects having surface openings. or any similar surface damage that causes a progressive breaking away of surface under load. Usual causes are fatigue. Spalling Sharply roughened area. shear. voids. Stress-failure Metal failure due to compression forces. sharp-edged pits with edge conditions that indicate progressive chipping or peeling of surface material. Inspection Terms and Definitions (Cont’d) TERM Seizure DEFINITION A welding or binding of two adjacent surfaces. tension. preventing further movement.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. pits. This method is applicable to magnetic steel and cannot be used on other materials. This method may also be used on ferromagnetic parts of complex structure that could give false indications when checked by the magnetic particle inspection method. Usually results in vibration. Skidding To slide without rotating. The magnetic particle inspection is a nondestructive test procedure that detects cracks. 3045542 TABLE 202. 72-00-00 ENGINE . the bottom of the pit may be dark. surface cracks. E. Tear Removal of metal by tensile stresses imposed by a dull tool or too heavy a cut. Unbalance A condition created in a rotating body by an unequal distribution of weight about its axis. Wear A condition resulting from a relatively slow removal of parent material. could eventually lead to failure of a component or part. refer to the detailed procedure. (3) Perform all cleaning operations in a well-ventilated work area.2 m) of cleaning area. oil lubrication and pneumatic systems. USE AND CONTROL MEASURES. EXPLOSION. (1) Wear rubber gloves.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. CAUTION: TAKE PARTICULAR CARE IN SELECTING CLEANING METHOD TO ENSURE THAT ANODIZING AND OTHER PROTECTIVE COATINGS ARE NOT REMOVED FROM PARENT METAL. Oil and Air Filters (1) When determining the condition of engine fuel. NOTE: 15. PRECAUTIONS FOR SAFE HANDLING. which. (5) Do not smoke or expose a flame within 50 feet (15. apron or coveralls. removed filters must be inspected for condition. (2) Use the least toxic of available cleaning materials that will satisfactorily accomplish the work. HEALTH HAZARD DATA. and face shield or goggles when working with or near solvents. REACTIVITY.MAINTENANCE PRACTICES Page 232 Nov 04/2005 . Inspection of Fuel. MAGNESIUM AND ALUMINIZED AND PAINTED PARTS. if not detected. Avoid overcleaning. Other engine components are normally cleaned prior to carrying out inspection procedure. 3045542 G. General (1) B. contamination and other defects before the application of any allowable cleaning procedures. Precautions WARNING: REFER TO THE MANUFACTURER’S MATERIAL SAFETY DATA SHEETS FOR CONSUMABLE MATERIAL’S INFORMATION SUCH AS: HAZARDOUS INGREDIENTS. DO NOT USE ALKALIS ON ALUMINUM. 72-00-00 ENGINE . Cleaning A. Use recommended cleaning agents listed in CONSUMABLE MATERIALS. PHYSICAL/CHEMICAL CHARACTERISTICS. (4) Ensure that adequate and usable fire fighting and safety equipment is conveniently located and available to all personnel. The cleaning methods given in the following text are adequate for all maintenance levels. The primary purpose of cleaning is to remove contaminants that may conceal minor cracks and other defects. For compressor washing. Engine components or parts should be cleaned only as necessary to perform required inspection and repair. (6) Ensure all degreasing agents are removed after cleaning. FIRE. NOTE: Toxicity depends on the type of contamination that the cleaning agent contacts when it is applied. Debris Analysis and Material Specifications A.g. Bearings Bearings to be stored should be coated with a light film of lubricating oil. Filter Patch Check Debris Inspection/Analysis (1) The analysis should be carried out by any approved laboratory (Ref. dimensions.) produce debris. This procedure improves aircraft serviceability and dispatch reliability and reduces engine repair costs. appearance. (3) Analysis (form. quantity and material) of the debris captured by the filters and chip detectors is necessary to provide the information needed to facilitate locating the source of the debris and determining any preventive maintenance action required. 3045542 (7) 16. Para . etc. Record location of bearings removed during disassembly to ensure that serviceable bearings are installed in the original location. This is achieved by identifying potential engine problems at the earliest possible stage. A stiff bristle fiber brush is adequate for most cleaning operations. B. During disassembly. Keep inner and outer races as matched sets (i.) or interference between rotating and fixed components (e. SR. (2) The operator must provide to the laboratory the following information with the filter or debris: 72-00-00 ENGINE .). away-from-base engine changes and secondary damage. These bearings are to be maintained as assemblies as identified by the mating numbers.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO.MAINTENANCE PRACTICES Page 233 Nov 04/2005 . wrapped in clean plastic bags and placed in individual closed containers. housing bearing bores. General (1) Debris analysis monitors wear of oil-wetted engine parts. (2) Rapid wear or surface fatigue (e. oil pump pinions. 17. Operators may send the contaminated filter or the debris to the laboratory for the filter patch check and/or analysis to be carried out. Demountable and semi-demountable bearings are further identified by the same mating number on the inner and outer race and the cage. SERIAL NUMBER. etc. do not use steel brushes for cleaning operations. Magnetic debris over 100 microns in diameter are usually captured by the chip detectors. Except where specified. rolling elements. bearing raceways. mating number of races must be the same). Magnetic and non-magnetic debris over 10 microns in diameter are usually captured by the oil system filters (main and RGB scavenge oil filters). bearing inner and outer races will sometimes be removed at different stages. bearings assemblies are identified by serial number distinguished from the part number by prefix e.e.g. In addition to part numbers. on gear teeth contact surfaces. E. thus minimizing the possibility of in-flight shutdowns.g. associated housings and labyrinth seals. S/N. Chip and Flake Analysis (1) The analysis should be carried out by an approved laboratory (Ref.when the weight of the constituent is less than 50% of the total debris weight. (4) C.). (e) Reason for filter removal.when the weight of the constituent is more than 50% of the total debris weight. (2) The operator must provide to the laboratory the following information with the chips and/or flakes: (a) Engine model and serial number.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. inspection and debris analysis. 72-00-00 ENGINE . (b) Engine time since new (TSN) or time since overhaul or refurbishment (TSO or TSR). (d) Filter type (main or scavenge). appearance. (b) Engine time since new (TSN) or time since overhaul or refurbishment (TSO or TSR). (b) Total weight of debris. (c) Material and amount of non-magnetic debris when classified as major (Ref. v Traces . (c) Time since last filter inspection. appearance. Para . the operator must be advised as soon as possible by telephone and provided with a detailed written report. shape and amount of non-magnetic metallic debris.when the weight of the constituent is less than 5% of the total debris weight. (d) Material. Note). NOTE: The amount of individual constituents in the debris should be classified as: v Major . If bearing material (Ref. Table 203) is found. (3) The laboratory must issue an inspection report to the operator which includes: (a) Information provided by the operator with the filter or debris. v Minor . E.MAINTENANCE PRACTICES Page 234 Nov 04/2005 . 3045542 (a) Engine model and serial number. shape and amount of metallic debris. (d) Reason for chip detector inspection (scheduled or unscheduled). (c) Chip detector position (Reduction Gearbox or Turbomachinery). (e) Material. Scavenge Pump. 2 and No. Regulating Valve Oil System AMS4439 Magnesium (ZE41A) Housing. Shaft Coupling AGB AMS4173 Aluminum (6061) Stop. Rear Housing Propeller. Centrifugal Breather. RGB Scavenge Pump Pump Pack AMS4260 Aluminum Housing. the material specifications are listed in Table 203. Scavenge Pump Pump Pack AMS4261 Aluminum Impeller. Propeller. Material Specifications (1) To facilitate the identification of components which are the source of debris found in the oil system. Flanged RGB Scavenge Pump AMS4434 Magnesium Cover. Centrifugal Breather. the operator must be advised as soon as possible by telephone and provided with a detailed written report. (c) Shape and appearance of the material. (b) Type(s) of material found. D. Material Specification (Engine Components) SPECIFICATION GENERIC NAME PART NOMENCLATURE ENGINE LOCATION AMS4116 Aluminum (6061) Stop. Rear AGB AMS4275 Aluminum (850) Bearing.MAINTENANCE PRACTICES Page 235 Nov 04/2005 .PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. Pressure Pump Pump Pack Housing. RGB. Main Pressure Pump Pump Pack Housing. Cover. 7 Bearing Pump Pack Plate. Input Drive RGB Housing RIC Cover AGB Housing. Front AGB Impeller. Sleeve. No. Table 203) is found. TABLE 203. 3045542 (3) Reports supplied by the laboratory to the operator containing the results of the analysis must include: (a) Information provided by the operator when submitting the material for analysis. Front 72-00-00 ENGINE . The common contaminants found in the oil system are listed in Tables 204 and 205. Shaft Coupling AGB AMS4212 Aluminum (355) Cover. RGB. (d) If bearing material (Ref. 2 and No. Air. Bearing. Oil Transfer 72-00-00 ENGINE . Roller Hydraulic Pump Drive Overspeed Drive Accessory Drive Startergenerator Drive Accessory Drive Bevel Gearshaft Towershaft AMS4975 T1 Alloy HP Impeller and Shaft AMS4991 T1 Alloy Angle Drive Housing AMS5000 Steel (SAE 1000 series) Spacers SST No. 3045542 TABLE 203. No.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. Inspection.MAINTENANCE PRACTICES Page 236 Nov 04/2005 . 5 Bearing Housing Stator Nozzle. Oil. No. Fuel Drain. 3 Bearing Housing RIC AMS5350 or AMS5355 AMS5362 Steel (30347) Elbow. Turbine Support Boss. No. Material Specification (Engine Components) (Cont’d) GENERIC NAME SPECIFICATION PART NOMENCLATURE Housing. Tube-to-boss Elbow. Adapter. Transfer Tube Adapter. 6 and 7 Bearing Housing ITD No. Regulating Valve AMS4616 Copper Cage. Turbine Support Housing. RGB Scavenge Pump ENGINE LOCATION Pump Pack Housing. 5 Bearing Boss. 5 Bearing Housing Cover Seal. Fuel Manifold Flange. No. Pressure Setting HMU Flange. Air. 6 Bearing Rotor 72-00-00 ENGINE . Pressure Oil Check Valve Carrier.MAINTENANCE PRACTICES Page 237 Nov 04/2005 . Air/Oil. Compressor Wash Flange. Accessory Gearbox Breather AMS5383 Ni Alloy No. No. No. Turbine Interstage AMS5610 Steel (51416/10) Gas Generator Steel (51410) Seal. HP Turbine AMS5510 AMS5512 or AMS5646 AMS5540 Gas Generator Case Reduction Gearbox Gas Generator Case Seal. 3 Bearing Seal. Air. Abradable. No. Outlet Nozzle. Air. 3 Bearing Housing. 9 Bearing Keywashers Steel (30321) Keywashers SST No. 4 Bearing Seal. Multiple Jet Housing. No. No. Seal Nozzle. 5 Bearing Seal. Stator LP Diffuser Case Seal.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 5 Bearing Front Seal Abradable Steel (Inconel 600) Seal. 5 Bearing Housing AMS5504 Steel Keywashers Steel No. Material Specification (Engine Components) (Cont’d) GENERIC NAME SPECIFICATION PART NOMENCLATURE ENGINE LOCATION Valve. Abradable. Oil. 5 Bearing AMS5611 AMS5612 AMS5504 or AMS5613 or AMS5663 Seal. Diffuser Exit Duct. 3045542 TABLE 203. Air. RGB Scavenge Pump Pump Pack Shaft. RGB Scavenge Pump Drive Pump Pack Coupling. Bearing Hydraulic Pump Drive AMS5665 or AMS5666 AMS5689 AMS6250 or AMS6260 Overspeed Governor Drive Accessory Drive AMS6265 Steel (9310) Ring. Pressure Pump Pump Pack Shaft. HP Turbine Ni Alloy No.MAINTENANCE PRACTICES Page 238 Nov 04/2005 . Abradable Steel (30321) Bearing. Ball Towershaft Steel Ring. Main Pressure Pump Drive Pump Pack Shaft. PT Rotor Seal. Intershaft Rotor HP Impeller Seal. Labyrinth. 7 Bearing Seal. Stub. Outer. Air. Outer Bearing Startergenerator Drive Gear. Spur. AGB Drive HP Shaft 72-00-00 ENGINE .PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. No. Oil Pump Pump Pack Shaft. HP Turbine AMS5704 Ni Alloy (Waspalloy) (Post-SB21683) Shaft. 2 Bearing Gas Generator Case AMS5662 Ni Alloy (Inconel 718) (Pre-SB21683) Shaft. Labyrinth No. Drive. Idler. Stub. 3045542 TABLE 203. Bevel. Accessory Drive AGB Gear. RGB Input Shaft RGB Gear. Idler. 5 Bearing Rear Seal. Bevel. Material Specification (Engine Components) (Cont’d) GENERIC NAME SPECIFICATION PART NOMENCLATURE ENGINE LOCATION Seal. AGB AGB Shaft. Second-stage Reduction (RH) RGB Gearshaft. Bevel. Second-stage Reduction (LH) RGB Shaft. Accessory Drive AGB Gearshaft.MAINTENANCE PRACTICES Page 239 Nov 04/2005 . First-stage Reduction RGB Gear. Spur. AGB Drive (18 teeth) AGB Gearshaft. Spur. Spur. 3045542 TABLE 203. Drive. Spur. Starter-generator Drive AGB Gearshaft. Spur. Spur. Oil Pump Drive AGB Gear. Spur. Helical. Coupling. Spur. Spur. Overspeed Governor Drive RGB Gearshaft. Material Specification (Engine Components) (Cont’d) GENERIC NAME SPECIFICATION PART NOMENCLATURE ENGINE LOCATION Gear. Pulse Pick-up LP Shaft 72-00-00 ENGINE . Accessory Drive AGB Gearshaft. Idler Drive RGB Gearshaft.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. RGB RGB Gearshaft. Oil Pump Drive Pump Pack AMS6304 Steel LP Shaft LP Shaft AMS6322 Steel (8740) Runner. Accessory Drive AGB Gearshaft. Bevel. Bevel. AGB Drive (43 teeth) AGB Gearshaft. AGB Drive (46 teeth) AGB Gearshaft. Alternator Drive RGB Gearshaft. Input. Second-stage Reduction (LH) RGB Gearshaft. Hydraulic Pump Drive RGB Gearshaft. Bevel. Helical. Spur. 6) Low Pressure Turbine Cage. Pulse Pick-up LP Shaft AMS6414 Steel (4340) Coupling. Bearing. 18) Propeller Shaft (RGB) Cage.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. Roller (No. Bearing. 3) Low Pressure Impeller Cage. Roller (No. Bearing. Roller (No. 14) Second-stage Spur Gearshaft (RGB) Cage. Ball (No. Bearing. 12) First-stage Helical Gear (RGB) Cage. 2) Power Turbine Shaft Cage. Bearing. Roller (No.8) Input Drive Shaft (RGB) Cage. Ball (No. Layshaft RGB (Secondstage Reduction) Cage. 11) First-stage Helical Gear (RGB) Cage. Bearing. Bearing. 9) Input Drive Shaft (RGB) Cage. Roller (No. 3045542 TABLE 203. 19) Propeller Shaft (RGB) 72-00-00 ENGINE . Roller (No. Bearing.MAINTENANCE PRACTICES Page 240 Nov 04/2005 . Bearing. Roller (No. Ball (No. 5) High Pressure Impeller Cage. Roller (No. Bearing. Roller (No. Roller (No. Bearing. 1) Power Turbine Shaft Cage. 15) Propeller Shaft (RGB) Cage. Roller (No. Material Specification (Engine Components) (Cont’d) SPECIFICATION GENERIC NAME PART NOMENCLATURE ENGINE LOCATION AMS6323 Steel (8740) Runner. Bearing. 13) Second-stage Spur Gearshaft (RGB) Cage. Vernier. Bearing. Bearing. Bearing. Roller (No. Bearing. Bearing. Roller (No. Bearing. 24) Accessory Drive Spur Gearshaft (AGB) Cage. Ball (No.Front) Accessory Drive Spur Gearshaft (AGB) Cage. 25 Rear) Accessory Drive Spur Gearshaft (AGB) Cage. 25 . Roller (No.Front) Accessory Drive Spur Gearshaft (AGB) Cage. 22) Idler Drive Spur Gearshaft (RGB) Cage. Roller (No. Roller (No. Bearing. Bearing. Material Specification (Engine Components) (Cont’d) SPECIFICATION GENERIC NAME PART NOMENCLATURE ENGINE LOCATION Cage. Bearing. Bearing. 26 . Bearing. 21) Hydraulic Pump Drive Shaft (RGB) Cage. Bearing. Ball (No.Front) Accessory Drive Spur Gearshaft (AGB) Cage. Bearing.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3045542 TABLE 203. 28 .MAINTENANCE PRACTICES Page 241 Nov 04/2005 . Roller (No. Ball (No. 20) Overspeed Governor Drive Gearshaft (RGB) Cage. 23) Alternator Drive Spur Gearshaft (RGB) Cage. Roller (No. Roller (No. 26 Rear) Accessory Drive Spur Gearshaft (AGB) Cage. 28 Rear) Accessory Drive Spur Gearshaft (AGB) 72-00-00 ENGINE . Rear) Accessory Drive Spur Gearshaft (AGB) Bearing. Stub. 25 . Material Specification (Engine Components) (Cont’d) SPECIFICATION GENERIC NAME PART NOMENCLATURE ENGINE LOCATION Cage. 20) Overspeed governor Drive Gearshaft (RGB) Bearing. Abradable ICC Shaft.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. Bearing. 3045542 TABLE 203. Bearing. Roller (No. Roller (No. 29) Towershaft Cage. 24) Accessory Drive Spur Gearshaft (AGB) Bearing. 23) Alternator Drive Gearshaft (RGB) Bearing. Roller (No. Roller (No. Roller (No. 4 Bearing Seal. Ball (No. PT AMS6444 Steel (52100) Bearing . 25 Front) Accessory Drive Spur Gearshaft (AGB) Bearing. Ball (No. 22) Idler Drive Gearshaft (RGB) Bearing. Bearing.MAINTENANCE PRACTICES Page 242 Nov 04/2005 . Ball (No. Roller (No. 30) Towershaft Oil Pump Driveshaft AMS6415 Steel (4340) Cage. PT No. 7) Power Turbine Shaft No. Roller (No. 26 Front) Accessory Drive Spur Gearshaft (AGB) 72-00-00 ENGINE . 18 and 19 Bearing Sleeve RGB Shaft. Ball (No. 29) Towershaft Overspeed Governor Drive Accessory Drive (AGB) Startergenerator Drive Accessory Drive Bevel Gearshaft Towershaft Oil Pump Driveshaft AMS6491 M50 Bearing. Roller (No. 28 Front) Accessory Drive Spur Gearshaft (AGB) Bearing. 2) Power Turbine Shaft Bearing.Rear) Accessory Drive Spur Gearshaft (AGB) Bearing. 7) Power Turbine Shaft Bearing. 4) HP Impeller Bearing. Roller (No. Roller (No. Roller (No. Ball (No.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. Ball (No. Ball (No.Rear) Accessory Drive Spur Gearshaft (AGB) Bearing.MAINTENANCE PRACTICES Page 243 Nov 04/2005 . 8) Input Drive Shaft (RGB) 72-00-00 ENGINE . 5) HP Impeller Bearing. 1) Power Turbine Shaft Bearing. Material Specification (Engine Components) (Cont’d) GENERIC NAME SPECIFICATION PART NOMENCLATURE ENGINE LOCATION Bearing. Roller (No. 3) LP Impeller Bearing. 6) LP Impeller Bearing. 28 . Roller (No. 3045542 TABLE 203. Roller (No. 26 . Ball (No. 12) First Stage Helical Gear (RGB) Bearing. Bearing. 9) Input Drive Shaft (RGB) Bearing. Material Specification (Engine Components) (Cont’d) GENERIC NAME SPECIFICATION PART NOMENCLATURE ENGINE LOCATION Bearing. Cage Accessory Drive Spur Gearshaft (AGB) Rivet. Ball (No. Roller (No.MAINTENANCE PRACTICES Page 244 Nov 04/2005 .5 Overspeed Governor Drive 72-00-00 ENGINE . 14) Second Stage Spur Gearshaft (RGB) Bearing. 15) Propeller Shaft (RGB) Bearing. 13) Second Stage Spur Gearshaft (RGB) Bearing. Roller (No. 3045542 TABLE 203. Roller (No. 22) Idler Drive Spur Gearshaft (RGB) Bearing. Roller (No.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 11) First Stage Helical Gear (RGB) Bearing. Cage AGB Driveshaft Oil Pump Drive Shaft Cage. 19) Propeller Shaft (RGB) Cage. Roller. Roller (No. Ball (No. 30) Towershaft AMS6512 Steel Layshaft Coupling Shaft RGB AMS7225 Steel Rivet. Flanged Hydraulic Pump Drive Si 0. Roller (No. Roller (No. Roller (No. Bearing. 18) Propeller Shaft (RGB) Bearing. Pump Base Overspeed Governor Pump Gear Casting. Upper Overspeed Governor Body. 3045542 TABLE 203. Overspeed. Pump Body Overspeed Governor Pump Gear Bushing.Element AMS4117 (6061-T6 AL) AMS4119E AMS4215 (C-355-T6 AL) Aluminum Aluminum B-10 High-leaded Tin Bronze AMS4215 Aluminum Plunger. Governor. Lower Overspeed Governor Casting.Case Motor Driven Pump AMS3662A PTFE . Reset Overspeed Governor Inlet Tube Aeroproducts Outlet Tube Motor Driven Pump Base.Gasket (Teflon) . Material Specification (Engine Components) (Cont’d) GENERIC NAME SPECIFICATION PART NOMENCLATURE ENGINE LOCATION Accessory Drive (AGB) Startergenerator Drive Nickel Plating Repair Silver Plating Chromium Plating Repair Cadmium Plating A1S1C1005 Steel Lip Seal Aeroproducts AMS3249 EPDM . Governor.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO.MAINTENANCE PRACTICES Page 245 Nov 04/2005 . Pump Overspeed Governor Pump Gear Housing Cover Aeroproducts Motor Driven Pump 72-00-00 ENGINE . Governor Overspeed Governor Body. Ballhead Overspeed Governor Plug. 3045542 TABLE 203. Retaining Overspeed Governor AMS5610 (416 SST) SST Pin. Speeder Spring Overspeed Governor Sleeve. Material Specification (Engine Components) (Cont’d) GENERIC NAME SPECIFICATION AMS4260 (356-T6 AL) AMS4610 AMS4842A PART NOMENCLATURE ENGINE LOCATION Aluminum Cover. Straight Overspeed Governor AMS5610 (416 SST) or AMS5613 (410 SST) SST Pin. Valve Oil Cooler Leaded Bronze Bearing Aeroproducts Motor Driven Pump AMS5343 Stainless Steel (17-4PH) Governor Drive Gear Propeller Control Unit AMS5516 Steel Shims Aeroproducts Motor Driven Pump AMS5520 Steel Retainer Aeroproducts Motor Driven Pump AMS5528 (17-7) Steel Ring. Piston Guide Overspeed Governor Seat.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. Governor Overspeed Governor Brass Guide. Pilot Valve Overspeed Governor Steel Governor Gear Propeller Control Unit AMS5618 or AMS5880 (440C SST) Steel or SST Bearing Overspeed Governor AMS5630 (440C SST) SST Main Poppett Overspeed Governor Pump Gear AMS5616 72-00-00 ENGINE .MAINTENANCE PRACTICES Page 246 Nov 04/2005 . MAINTENANCE PRACTICES Page 247 Nov 04/2005 . Material Specification (Engine Components) (Cont’d) GENERIC NAME SPECIFICATION AMS5630D Steel PART NOMENCLATURE ENGINE LOCATION Plunger. Speed Reset Overspeed Governor Spring. Valve Oil Cooler Sleeve. 3045542 TABLE 203. Sliding.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. Check Valve Overspeed Governor Pump Gear AMS5688F Steel Inlet Screen Aeroproducts Motor Driven Pump AMS6272 (8617) or AMS6274 (8620) Steel Shaft. Check Valve Overspeed Governor Pump Gear Pilot Poppet Overspeed Governor Pump Gear Poppet Aeroproducts Retainer Motor Driven Pump Seat AMS5639D Steel Sleeve Aeroproducts Motor Driven Pump AMS5640 Steel (303) AMS5643 (17-4) AMS5673 Steel Sleeve. Governor Drive Overspeed Governor Gear Aeroproducts AMS6274 (8620) Steel 72-00-00 ENGINE . O. Check Valve Overspeed Governor Pump Gear Spring Aeroproducts Motor Driven Pump AMS5678 (17-7) Steel Spring. Drive Overspeed Governor Pump Gear Ballhead. Airbleed Overspeed Governor Spring.S. Preformed Aeroproducts Motor Driven Pump Seat.C93200 (660 Bronze) Plate. Pump Pressure Overspeed Governor Pump Gear MIL-S-22141 (8620) Seat. Pump Drive Overspeed Governor Pump Gear Bearing. Speeder Overspeed Governor AMS6440 (AISI 52100) or Steel Steel AMS6442 (AISI 50100) AMS7270 Buna ASTM A108 (1117) TABLE 204. Speeder Spring Overspeed Governor Spring Wire Alloy 4920 Spring.MAINTENANCE PRACTICES Page 248 Nov 04/2005 . Ball Overspeed Governor Pin Overspeed Governor Packing. 3045542 TABLE 203. Pilot Valve Overspeed Governor Gear. Air Bleed Overspeed Governor CDA NO.Non-organic Material Contaminant Detected Alumina Main Elements Al203 Cause of Contaminants Manufacturing 72-00-00 ENGINE . Material Specification (Engine Components) (Cont’d) GENERIC NAME SPECIFICATION PART NOMENCLATURE ENGINE LOCATION Motor Driven Pump AMS6290 (4615) or AMS6272 (8617) or AMS6274 (8620) Gear. Idler Overspeed Governor Pump Gear Plunger. Bearing Overspeed Governor CA-6NM (ASTM A296) Lever. Common Contaminants .PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. Common Contaminants . Shiny. Seal Gaskets Chloroprene Nitrile Rubber Gaskets Carbon Decomposed Oil.Non-organic Material (Cont’d) Contaminant Detected Main Elements Cause of Contaminants Black Magnetic Fe304 Anaerobic decomposition of shaft material. Red Silicon Rubber. Common Contaminants . can look like carbon is a corrosive product. Non-magnetic Fe2O3 Rust Sand SiO2 Manufacturing/ Environment Silicon Carbide (Black.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3045542 TABLE 204. Usually found in new or overhauled engines.MAINTENANCE PRACTICES Page 249 Nov 04/2005 . Blue Fluorosilicon Rubber Preformed Packings. Carbon Seals 72-00-00 ENGINE . Calcium Chloride (Salt) CaCl2 Environment Sodium Chloride (Salt) NaCl Environment Calcium Sulphate (Salt) CaSO4 Environment TABLE 205. Calcium Oxide CaO Environment Rust. Angular) SiC Manufacturing/ Blasting ZrSiO4 Manufacturing Zirconia Mo52 Common as a trace. could combine with Fe (Iron) to indicate bearing alloy.Organic Material Contaminant Detected Source Black Fluorocarbon Rubber. GA 30091 USA TEL: 1-800-241-6315 (770) 448-5235 FAX: (770) 448-5918 Website: http://www.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO.MAINTENANCE PRACTICES Page 250 Nov 04/2005 . Common Contaminants . Japan TEL: 81-3-3747-9660 FAX: 81-3-3747-9648 Analysts Inc.com 72-00-00 ENGINE . 3045542 TABLE 205.Organic Material (Cont’d) Contaminant Detected Source Fibers Plastics Paint Flakes E. Air Canada Jazz (M50. Skywatch Aircraft Oil Analysis 3075 Corners North Court.W. Some of which are listed below. LTD Power Plant Maintenance Center Production Engineering & Control 1-8-2 Haneda Airport Ota-ku.analystsinc. N. Tokyo 144-0041. Norcross.. Laboratories (1) Chip and flake analysis should be carried out by a qualified laboratory. bearing alloy ONLY) ‘‘DELETED’’ Alfa Romeo Avio Laboratory 80038 Pomigliano D’Arco Napoli Italy TEL: 39-81-8430493 FAX: 39-81-8846522 ALL NIPPON AIRWAYS CO. 3045542 Areco Canada Inc.castc.cn/lab E-mail: [email protected] & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO.arecolabs. 86-10-64473548 Website: http://www. Ontario K2G 5X8 Canada TEL: 1-800-895-0510 (North America Only) (613) 228-1145 FAX: (613) 228-1148 Website: http://www. Building 24 Jia.avlab.castc. Beijing 100028 P.com Aviation Laboratories Inc.org. (Center of Aviation Safety Technology.castc. General Civil Aviation Administration of China). New Orleans International Airport 910 Maria Street Kenner. 40 Camelot Drive Napean. China TEL: 86-10-64473571.com Aviation Laboratories Inc.cn xieml@mail. 86-10-64473559 FAX: 86-10-64473569.R. LA 70062 USA TEL: (504) 469-6751 FAX: (504) 469-6886 Aviation Safety Institute Technology Lab. Coporate Headquarters 5401 Mitchelldale #B6 Houston. Xibahe Beili. Chaoyang District. TX 77092 USA TEL: 1-800-256-6876 (713) 864-6677 FAX: (713) 864-6990 Website: http://www.org.MAINTENANCE PRACTICES Page 251 Nov 04/2005 .org.cn Deutsche Lufthansa AG POSTFACH 300 22313 Hamburg 63 Germany TEL: (49) 0 4050 702233 72-00-00 ENGINE . 3045542 Jet-Care International Inc.com Martel Laboratories JDS Inc. 250 Meadowfern Drive Suite 102 Houston.O.MAINTENANCE PRACTICES Page 252 Nov 04/2005 . Taiwan TEL: (886) 3-591-8231 FAX: (886) 3-591-0073 Website: http://www.mrl.jet-care. IL 62702 USA TEL: (217) 522-0009 FAX: (217) 522-2119 Website: http://www. Chutung.com Martel Laboratories JDS Inc.C.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 195-5 Chung Hsing Road Section 4. MD 21286 USA TEL: (410) 825-7790 FAX: (410) 821-1054 Website: http://www.tw 72-00-00 ENGINE . Petroleum Laboratory Services 1025 Cromwell Bridge Road Baltimore.matelabs. Petroleum Laboratory Services 1438 E Samgamon Ave Springfield. TX 77067 USA TEL: (281) 872-9100 FAX: (281) 872-7916 Materials Research Laboratories Industrial Technology Research Institute Building 77. New Jersey 07927-902 USA TEL: (973) 292-9597 FAX: (973) 292-3030 Website: http://www. Hsinchu 310 R.com Martel Laboratories JDS Inc. 3 Saddle Road Cedar Knolls.org.matelabs.itri. pcaschem.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. Calgary. Quebec H3L 1Z8 Canada TEL: (514) 383-6330 FAX: (514) 383-5631 Website: http://www. Alberta T2E 6Z7 Canada TEL: (403) 295-8803 FAX: (403) 295-3848 PCAS (Produits Chimiques Auxiliaires et Syntheses) Zone Industrielle de la Vigne aux Loups 23 Rue Bosselet 91-161 LongJumeau France FAX: (1) 64-482319 Website: http://www. Alberta T1Y 5R8 Canada TEL: (403) 250-8378 FAX: (403) 286-8287 Qantas NDT Section Qantas Maintenance Base Melbourne Airport Base Victoria Australia TEL: (61) 3-92807265 FAX: (61) 3-92807393 72-00-00 ENGINE . Suite 101 Montreal.E. 2723-37 Avenue NE Calgary.com or Predictive Maintenance Corporation 206. 3045542 Metro Tech Systems Ltd.com Predictive Maintenance Corporation 400 Sauve Street West.MAINTENANCE PRACTICES Page 253 Nov 04/2005 .pmaint. Bay 112 5621-11th Street N. MAINTENANCE PRACTICES Page 254 Nov 04/2005 .sabena.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO.com E-mail: gpmccullough@qinetiq. 1930 Zaventem Belgium TEL: (32) 2 723 4958 FAX: (32) 2 723 5995 Website: http://www.qinetiq.com SN Brussels Airlines (formally Sabena Airlines) Building 12-012 International Airport Brussels. Hampshire RG29 1NP United Kingdom TEL: 44-0-1256 704000 FAX: 44-0-1256 704006 Website: http://www.com The University of Dublin Trinity Collage Department of Biochemistry Chemical Analyst Laboratory Dublin 2 Ireland TEL: (353) 1 608 1608 FAX: (353) 1 677 2400 Website: http://www.com Spectro Oil Analysis Company Ltd.ie/Biochemistry 72-00-00 ENGINE .tcd. 3045542 QinetiQ (formally DERA) Fuel and Lubricants Cody Technology Park Building 442 Pyestock Farnborough.specto-oil. Palace Gate High Street Odiham. Hampshire GU14 0LX England TEL: (44) 1252 374775/4776 (44) 7771 808541 (Off-hour) FAX: (44) 1252 374795 Website: http://www. wearcheck.com Xi’an Aero Engine Corp.MAINTENANCE PRACTICES Page 255/256 Nov 04/2005 .O. Box 13-88.com Wear Check Canada Inc.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO.vernolab. Ontario L5L 5R3 Canada TEL: (905) 569-8600 FAX: (905) 569-8605 Website: http://www. Physic and Chemical Testing Centre Xujiawan Beijiao P. Xi’an 710021 China TEL: 86-29-6613888-53144 FAX: 86-29-6614035 72-00-00 ENGINE . 3045542 Vernolab Zone Les Cents Sillone 27-138 Verneuil sur Avre Cedex France TEL: (33) 0 2 32 60 65 FAX: (33) 0 2 32 60 1646 Website: http://www. 4161 Sladeview Crescent Unit 11 Mississauga. . Use engine oil (PWC03-001) for general lubrication. WEAR GOGGLES WHEN REMOVING LOCKWIRE. Name PWC03-001 PWC05-026 PWC05-051 PWC05-053 PWC05-063 PWC05-069 PWC05-070 PWC05-077 PWC05-089 PWC05-107 PWC05-295 PWC15-011 Oil.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. WARNING: NOTE: 2. Reduction Gearbox (use with PWC34300) Drain Fitting Adapter Adapter Sling (Engine/Turbomachinery) 72-00-00 ENGINE . refer to the CONSUMABLE MATERIALS section at the beginning of this manual. Item No. Plastic. Moisture-Proof Strapping. Flat Steel Strapping Sheet. Engine Dye. installation/removal of the turbomachinery/reduction gearbox/engine in shipping container. For more data. Preservative Lockwire Polyurethane (Foam-in-place) Lockwire (may be used instead of PWC05-089) Inhibitor Special Tools Special tools are identified in procedural text by part number in parentheses. shipping instructions for accessories. 3045542 ENGINE . Filament-reinforced (Pressure-sensitive Adhesive) Oil. Tool No.SERVICING Page 301 May 02/2003 . WARNING: 3. Name PWC34300 PWC37825 PWC38001 PWC38147 PWC38212 PWC38307 PWC54002 Stand Adapter Adapter. SOME MATERIALS CAN BE DANGEROUS. Blue Seal. Steel Tape.SERVICING 1. These instructions provide information necessary for preservation or depreservation of the engine in storage. General A. READ THE MATERIAL SAFETY DATA SHEETS BEFORE YOU USE THESE MATERIALS. Pressure Sensitive Adhesive Tape. Consumable Materials The consumable materials listed below are referred to in this section. unless stated otherwise. oil draining and oil system flushing. (2) Position container under hoist (2000 lb. Removal/Installation A.250-28 thread) Heat Gun Hoist. (3) The container is intended for domestic shipping or for overseas shipping by air and must not be used for shipping by sea. Front Rod. Name PWC54212 PWC54213 PWC54214 PWC56515 Adapter. The interior walls and top are made of plywood.SERVICING Page 302 May 02/2003 . 3045542 4.134 m) (not including distance from hoist hook to container top) to enable engine to be lifted clear of container mounts. 1000 lb. but a properly sealed container may be stored in a relatively dry indoor shelter for periods of up to six months. NOTE: (3) Overhead clearance must be at least seven feet (2. B. (2) Post-SB21678: The shipping container comprises a plywood skid base to which a metal cradle is secured. (19. (907 kg) SWL). (454 kg) SWL Hoist. Name Bolts. 72-00-00 ENGINE . The interior top sheet is made of plywood with the exterior sleeve and cover are both made of fiberboard. Fig. check engine for corrosion). Front Adapter.1 mm) Vacuum Cleaner 5. The container must not be stored outdoors. 301) (1) Check condition of humidity indicator (1) (if pink. Removal of Engine from Shipping Container (Ref. equipment and supplier tools listed below are referred to in procedural text. Flapper Valve Fixtures. Slave (0. (907 kg) SWL Oven Strapping Tool 3/4 in. Preparation of Shipping Container for Service or Storage (1) Pre-SB21678: The shipping container comprises a wooden skid base to which a metal cradle is secured. 2000 lb. Equipment and Supplier Tools The fixtures. The humidity indicator must be monitored every 15 days.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. The exterior sleeve and cover are made of fiberboard. Rear Adapter. Remove steel strapping (PWC05-063) (2). Tool No. Exposure to adverse climatic conditions for more than seven days is prohibited. front adapter (15) and rear adapter (16) and retain in shipping container base (17). (17) Verify engine with engine documents. (16) Remove engine documents from base. (7) Post-SB21678: Remove sleeve (5). interstage seal. (1) Prepare engine for storage (Ref. (14) Remove and reactivate desiccant bags (10). attach sling (PWC54002) (8) to engine. (10) Remove quick-release pins (9) and lift engine clear of container. CAUTION: DO NOT ATTEMPT TO LIFT AN ENGINE STILL ATTACHED TO THE CONTAINER. AMM). (5) Remove plywood cover (4). HP turbine disk front and rear cover plates. C. washers (13. using front adapter (PWC54214 (21)) and rear adapter (PWC54213 (22)). (15) Remove bolts (11. 72-00-00 ENGINE . (3) Remove the fuel waste ejector tank from the airframe (Ref. (9) Attach hoist to sling and take weight of engine. EXTENSIVE DAMAGE HAS BEEN CAUSED TO COMPONENTS DUE TO ENGINES HAVING BEEN SHIPPED WITHOUT NO. (6) Pre-SB21678: Remove sleeve (5) and plywood sides (6). (11) Remove the fuel waste ejector tank box (23) from the container. ENSURE INTERNAL COMPONENTS ARE INSTALLED. (18) Check engine for defects and damage. 3045542 (4) Remove and discard cover (3). LP turbine disk and power turbine disk history records.SERVICING Page 303 May 02/2003 . 12). 6 AND 7 BEARING HOUSING. Preservation/Depreservation. Fig. 301) CAUTION: BEFORE SHIPPING ENGINES.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. AMM). v Life limited parts log sheet. Installation of Engine in Shipping Container (Ref. 14). (13) Install the fuel waste ejector tank (Ref. (2) Ensure following engine documents are complete: v HP turbine disk. (8) Cut envelope (7) and. Oil Draining and IPC). v Log book. (12) Remove the fuel waste ejector tank from the box. PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3045542 C11588A Shipping Container .Engine Removal/Installation Figure 301 (Sheet 1 of 2) 72-00-00 ENGINE .SERVICING Page 304 May 02/2003 . Humidity Indicator Strapping Cover Plywood Cover Sleeve Plywood Side (Pre-SB21678) Envelope Sling Pin Desiccant Bags (not illustrated) Bolt Bolt Washer Washer Adapter Adapter Base Support Support Corner Box.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 10. 20. 2. 5. 14. 8. 13. 17. 18. Ejector 72-00-00 ENGINE . 7. 6. 12. 9. 4. 3. 3045542 Key to Figure 301 1. 23. 16. 19. 15. 11.SERVICING Page 305 May 02/2003 . PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO.Engine Removal/Installation Figure 301 (Sheet 2) 72-00-00 ENGINE .SERVICING Page 306 May 02/2003 . 3045542 8 21 22 16 9 11 1 13 9 7 15 14 12 23 18 19 17 C11247D Shipping Container . (23) Store container under cover. USE OF UNAPPROVED COMPONENTS COULD CAUSE SERIOUS ENGINE DAMAGE DURING SHIPMENT AND HANDLING. Secure with tape (PWC05-069). 72-00-00 ENGINE . adapters (PWC38307) (15) and (PWC38212) (16). (13) Attach reactivated desiccant bags (10) to engine. (17) Fold down edges of sleeve and secure with tape (PWC05-070). (31. washers (13. (79. Secure with strapping seals (PWC05-051). (20) Install steel strapping (PWC05-063) (2) with strapping tool. Do not expose to climatic conditions for more than seven days. (10) Lower engine onto container base and align adapter with supports (18. 3045542 (4) Place the fuel waste ejector tank in the box (23). build specification (BSxxx).PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. (907 kg) SWL). (6) Install documents in envelopes and install envelopes in box glued to base (17) with pressure-sensitive tape (PWC05-070).08 Nm). (19) Install cover (3) and tape corners (20) in position.in. pierced side in line with humidity indicator. (14) Evacuate envelope using vacuum cleaner and heat-seal envelope using heat gun.in. (21) Seal edges of container with tape (PWC05-070). (8) Install envelope.10 Nm) and rear bolts 275 lb. 19). (12) Remove sling (PWC54002) (8). (16) Orientate transparent panel in sleeve (5) to humidity indicator and install sleeve. (18) Install plywood cover (4) and tape (PWC05-070) to sleeve. (5) Install the box on the base of the container. Do not dispatch container by sea. IPC) MUST BE USED TO SECURE MOUNTING ADAPTERS TO THE ENGINE AND CONTAINER. (9) Install ejector box (23) in base (17).SERVICING Page 307 May 02/2003 . (15) Pre-SB21678: Install plywood sides (6). CAUTION: APPROVED COMPONENTS (REF. (11) Install quick-release pins (9). (7) Install reactivated humidity indicator (1) in envelope (7). Torque front bolts 700 lb. 14) and bolts (11. serial number and preservation date on both ends of container. (22) Stencil engine model. 12). rear adapters (PWC54213 (22)) and front adapter (PWC54214 (21)) and hoist (2000 lb. 524 m) (not including distance from hoist hook to container top) to enable gearbox to be lifted clear of container mounts. NOTE: Overhead clearance must be at least five feet (1. check gearbox for corrosion). Store components in container base. Remove and reactivate desiccant (9). Fig. CAUTION: DO NOT USE THE CRADLE ADAPTER EYEBOLT TO RAISE OR ROTATE THE GEARBOX. bolts (23) and coupling cover (24). (14) Rotate gearbox 90 degrees.in. (13) Install bolts (18) and nuts (19). (8) Attach adapter (PWC37825) (10) to propeller shaft. Attach hoist (1000 lb.SERVICING Page 308 May 02/2003 . (16) Remove nuts (21).10 Nm).in. Torque bolts 700 lb. washers (12) and bolts (13) attaching cradle adapter (14) to container mounting bars and raise gearbox clear of container. 3045542 D. Removal of Reduction Gearbox from Shipping Container (Ref. 72-00-00 ENGINE . (11) Install adapter (PWC38001) (15) and bolts (16) on gearbox. (454 kg) SWL). (79. (10) Remove nuts (11). Torque nuts 700 lb. (4) Remove cover (4).10 Nm). (9) Attach hoist (1000 lb. washers (22). (17) Remove lifting adapter (10). (2) Position container under hoist (1000 lb. 302) (1) Check condition of humidity indicator (1) (if pink.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. CAUTION: USE EXTREME CARE WHEN REMOVING CRADLE ADAPTER. (12) Install gearbox in stand (PWC34300) (17) . (3) Remove steel strapping (2) and corners (3). cradle adapter (14). (15) Remove bolts (20) securing gearbox drive coupling to cradle adapter. (18) Remove gearbox documentation from box on plywood side. (454 kg) SWL) to cradle adapter (14) eyebolt and take up slack. (454 kg) SWL) to adapter and take weight of gearbox. (5) Remove plywood cover (5). (6) Remove sleeve (6) and plywood sides (7) (Pre-SB21678). (7) Cut envelope (8). (79. CAUTION: DO NOT ATTEMPT TO LIFT A REDUCTION GEARBOX WHOSE CRADLE ADAPTER IS ATTACHED TO THE CONTAINER MOUNTING BARS. PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO.SERVICING Page 309 May 02/2003 .Reduction Gearbox Removal/Installation Figure 302 (Sheet 1 of 3) 72-00-00 ENGINE . 3045542 4 5 2 3 6 7 8 1 C12626 Shipping Container . 3. 15. 8. 20. 25. 29. 17. 22. 7. 9. 23. 14. 5. 26. 31. 13.SERVICING Page 310 May 02/2003 . 24. 6. 3045542 Key to Figure 302 1.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 11. 2. 4. 10. 18. 16. 19. 12. 30. 32. Humidity Indicator Steel Strapping Corners Cover Plywood Cover Sleeve Plywood Side (Pre-SB21678) Envelope Desiccant (not illustrated) Adapter Nuts Washers Bolts Cradle Adapter Adapter Bolts Stand Bolts Nuts Bolts Nuts Washers Bolts Cover Overspeed Governor/PVM Oil Pump Envelope Cover Nuts Bolts Cushioning (not illustrated) Cover Nuts 72-00-00 ENGINE . 27. 28. 21. PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO.SERVICING Page 311 May 02/2003 . 3045542 10 11 12 16 15 14 13 29 27 25 28 26 C12627 Shipping Container .Reduction Gearbox Removal/Installation Figure 302 (Sheet 2) 72-00-00 ENGINE . PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO.SERVICING Page 312 May 02/2003 . 3045542 31 18 32 21 19 22 14 24 20 23 17 C12628 Shipping Container .Reduction Gearbox Removal/Installation Figure 302 (Sheet 3) 72-00-00 ENGINE . install cradle adapter (14). (454 kg) SWL) and aligning dowel holes.48-9. Torque bolts 75 to 85 lb. (21) Remove cover (31) and nuts (32) and install overspeed governor/PVM oil pump on reduction gearbox (Ref. 302) (1) Prepare gearbox for storage (Ref. (6) Install overspeed governor/PVM oil pump in envelope (26). washers (22) and nuts (21). bolts (29) and nuts (28) on PVM oil pump flange. CAUTION: DO NOT USE CRADLE ADAPTER EYEBOLT TO RAISE OR ROTATE THE GEARBOX. Install envelopes in box glued to plywood side.in. bolts (29) and cover (27) from overspeed governor/PVM oil pump. (19) Remove overspeed governor/PVM oil pump (25) and envelope (26) from box on container base. Secure box with tape (PWC05-070). (7) Install drive coupling protective cover (24). install bolts (20). AMM). 72-01-50). (3) Install documents in envelopes.61 Nm). (8. (12) Attach lifting adapter (PWC37825) (10) to propeller shaft. USE OF UNAPPROVED BOLTS COULD CAUSE SERIOUS DAMAGE DURING SHIPMENT AND HANDLING.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. Torque nuts 75 to 85 lb. 3045542 E. (11) Rotate gearbox 90 degrees. Install cover (31) and nuts (32). (23) Check gearbox for defects and damage.48-9. (22) Verify gearbox with documentation. Remove hoist.61 Nm). Oil Draining and IPC). (8) Using hoist (1000 lb. Preservation/Depreservation. Fig. (9) Install bolts (23). (10) Aligning holes in drive coupling and cradle adapter. CAUTION: APPROVED BOLTS (IPC) MUST BE USED TO SECURE CRADLE ADAPTER TO GEARBOX AND CONTAINER MOUNTING BAR.SERVICING Page 313 May 02/2003 . 72-00-00 ENGINE . (4) Remove overspeed governor/PVM oil pump (25) from gearbox (Ref. (5) Install cover (27). (8. (20) Remove nuts (28). Installation of Reduction Gearbox in Shipping Container (Ref. Secure box with tape (PWC05-070). Evacuate envelope using vacuum cleaner and heat-seal using heat gun.in. (2) Ensure log book and gearbox documentation are complete. Wrap with cushioning (30) and install in box located in container base. ensuring the envelope is not damaged.52 mm) (not including distance from hoist hook to top of lifting adapter).in. washers (12) and nuts (11). NOTE: F. (26) Install cover (4) and secure corners (3) in position with tape (PWC05-070). pierced side aligned with humidity indicator. (21) Install reactivated humidity indicator (1) in envelope (8). build specification (BSxxx). Fig. (20) Attach reactivated desiccant bags (9) evenly over gearbox. (14) Remove nuts (19) and bolts (18). 303) (1) Check condition of humidity indicator (1) (if pink. Raise gearbox clear of stand (17).PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. gearbox serial number and preservation date on both ends of container.95 Nm). securing folded-down edges with tape (PWC05-070). (454 kg) SWL) to adapter and take weight of gearbox. (25) Install plywood cover (5) and secure to sleeve with tape (PWC05-070). Secure with strapping seals (PWC05-051). (18) Install bolts (13). (28) Seal edges of container with tape (PWC05-070). (30) Store container under cover.26-16. (24) Align transparent panel with humidity indicator and install sleeve (6). (15. (15) Remove bolts (16) and adapter (15). check turbomachinery for corrosion). 3045542 (13) Attach hoist (1000 lb. Torque nuts 135 to 150 lb. Overhead clearance must be at least five feet (1.SERVICING Page 314 May 02/2003 . Removal of Turbomachinery from Shipping Container (Ref. 72-00-00 ENGINE . (16) Install envelope (8) with the opening at the top and the gaskets on the container mounting bar pins. (27) Install steel strapping (PWC05-063) (2) using strapping tool. (17) Align holes in cradle adapter (14) with pins on mounting bar and lower gearbox carefully into container. (23) Install plywood sides (7) (Pre-SB21678). (19) Remove lifting adapter. Do not expose to climatic conditions for more than seven days. (29) Stencil engine model. Do not dispatch container by sea. (22) Evacuate envelope using vacuum cleaner and heat-seal using heat gun. 3045542 C12649 Shipping Container .Turbomachinery Removal/Installation Figure 303 (Sheet 1 of 2) 72-00-00 ENGINE .PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO.SERVICING Page 315 May 02/2003 . 25. 31. 7. 23. 26. 9.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 32. 6. 19. 8. 29. Rear Adapter. 10. Front Sling Ball Lockpins Bolts Washers Brackets Base Caps Nuts Nuts Washers Washers Bolts Plate Support Desiccant Bags (not illustrated) Bolts Cover Bolts Support Packing 72-00-00 ENGINE . 15. 4. 30. 3045542 Key to Figure 303 1. 27. 18. 20. 21. 24. 28. 22. 2. 17. 3. 12. 16. 11. 14. 5.SERVICING Page 316 May 02/2003 . 13. Humidity indicator Steel Strapping Corner Cover Plywood Cover Sleeve Plywood Sides (Pre-SB21678) Envelope NOT USED NOT USED Adapter. Turbomachinery Removal/Installation Figure 303 (Sheet 2) 72-00-00 ENGINE . 3045542 13 12 11 30 28 31 29 25 32 19 23 20 14 15 16 17 26 18 24 22 21 C12653A Shipping Container .SERVICING Page 317 May 02/2003 .PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. (14) Remove bolts (30). 23). (12) Remove protective caps (19).PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. (9) Attach sling to hoist and apply enough tension to sling to allow removal of ball lockpins (14). (17) Verify turbomachinery with documentation. Discard packing. front adapter (PWC54212) (12) and rear adapter (PWC54213) (11). Store components in shipping container base (18). washers (22. (7) Cut envelope (8). using slave bolts (0. (15) Remove shaft support (31) and packing (32). 21). (6) Remove sleeve (6) and plywood sides (7) (Pre-SB21678). (13) Remove bolts (28) and cover (29). 72-00-00 ENGINE . (3) Remove steel strapping (2) and corners (3). NOTE: Overhead clearance must be at least seven feet (2. (11) Remove bolts (15). (18) Check turbomachinery for defects or damage. Adjust eye on sling to ensure a level lift. bolts (24) and plate (25).134 m) (not including distance from hoist hook to container top) to enable turbomachinery to be lifted clear of container mounts. (8) Install sling (PWC54002) (13). (907 kg) SWL).250-28 thread). washers (16) and brackets (17). (10) Remove ball lockpins (14) and raise turbomachinery clear of container. Remove and reactivate desiccant bags (27).SERVICING Page 318 May 02/2003 . 3045542 (2) Position container under hoist (2000 lb. (4) Remove cover (4). (16) Remove documentation from base. CAUTION: DO NOT ATTEMPT TO LIFT THE TURBOMACHINERY IF THE CONTAINER BASE IS ATTACHED TO THE MOUNTING BRACKETS. nuts (20. (5) Remove plywood cover (5). Store components in shipping container base. washers (22) and nuts (21). (13) Install brackets (17).in. 12) and hoist. Install envelopes in box glued to base (18).48 Nm). (1) Prepare turbomachinery for storage (Ref. (12) Install bolts (24). Secure with tape (PWC05-070). (8. Torque bolts fingertight. Installation of Turbomachinery in Shipping Container (Ref. (2) Ensure following documents are complete: v HP turbine disk. HP turbine disk front and rear cover plates. Fig.48 Nm). (17) Attach reactivated desiccant bags (27) evenly over turbomachinery. 3045542 G. (31. (16) Remove sling (13). brackets and plate. (3) Install documents in envelopes. (10) Install protective caps (19).08 Nm). CAUTION: APPROVED COMPONENTS (IPC) MUST BE USED TO SECURE MOUNTING BRACKETS AND PLATE TO THE TURBOMACHINERY AND CONTAINER.SERVICING Page 319 May 02/2003 . (7) Install packing (32) on support (31). (4) Install reactivated humidity indicator (1) in envelope (8). 303) CAUTION: BEFORE SHIPPING ENGINES ENSURE INTERNAL COMPONENTS ARE INSTALLED. aligning supports (26). (11) Install plate (25). Torque nuts 75 lb. USE OF UNAPPROVED COMPONENTS COULD CAUSE SERIOUS DAMAGE DURING SHIPMENT AND HANDLING. washers (23) and nuts (20). (8) Install support and bolts (30). (8. (9) Install cover (29) and bolts (28). (15) Install ball lockpins (14). Torque bolts fingertight. Torque bolts 275 lb. adapters (11. washers (16) and bolts (15). Torque nuts 75 lb. (6) Remove bolts (28) and cover (29). 6 AND 7 BEARING HOUSING. (5) Install envelope. EXTENSIVE DAMAGE HAS BEEN CAUSED TO COMPONENTS DUE TO ENGINES BEING SHIPPED WITHOUT NO. Oil Draining and IPC). v Life limited parts log sheet. (14) Lower turbomachinery onto container base. LP turbine disk and PT disk history records.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO.in. 72-00-00 ENGINE . v Log book. Preservation/Depreservation.in. (22) Install plywood cover (5) and secure to sleeve with tape (PWC05-070). Preservation/Depreservation A. pierced side in line with humidity indicator. using heat gun. Engine stored off aircraft or in QEC a Seal off all engine openings (Ref. (23) Install cover (4) and secure corners (3) in position with tape (PWC05-070). serial number and preservation date on both ends of container.SERVICING Page 320 May 02/2003 . General Engine Storage/Preservation Procedure CAUTION: ENGINE(S) REMOVED FROM SERVICE AND NOT PRESERVED PER THE PUBLISHED PROCEDURES.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. (27) Store container under cover. AMM). Do not expose to climatic conditions for more than seven days. using vacuum cleaner. (21) Fold down edges of sleeve and secure with tape (PWC05-070). COULD POSSIBLY SUFFER CORROSION DAMAGE. (20) Align transparent panel with humidity indicator and install sleeve (6). The storage procedure is as follows: (a) 0 to 7 days 1 Engines stored on aircraft a 2 Seal off all openings to engine (Ref. THE ONLY METHOD TO DETERMINE IF SUCH DAMAGE HAS OCCURRED IS FOR THE ENGINE TO BE PARTIALLY DISASSEMBLED FOR VISUAL INSPECTION OF ALL COMPONENTS. (18) Evacuate envelope (8). AMM) and store engine in a sheltered location where the engine is subjected to minimum temperature changes and the lowest possible humidity to minimize on the condensation. (25) Seal edges of container with tape (PWC05-070). build specification (BSxxx). (19) Install plywood sides (7) (Pre-SB21678). (26) Stencil engine model. Secure with strapping seals (PWC05-051). and heat-seal. (b) 8 to 28 days 1 Engines installed on aircraft 72-00-00 ENGINE . (1) Engines stored on/off aircraft or in QEC for a pre-determined amount of time. (24) Install steel strapping (PWC05-063) (2) using strapping tool. 3045542 6. Do not dispatch container by sea. Subpara. Shut down engine (Ref.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. e Ensure window is provided in exhaust duct closure to facilitate observation of humidity indicator. (d) Over 90 days 1 Engine stored on/off aircraft or in QEC: a Wash engine externals.0. AMM). or water content is more than 800 parts per million. A log recording the results of the inspections must be attached to the engine. d Seal off all openings to engine (Ref. NOTE: During the period of storage. AMM).5 kg) of desiccant and humidity indicator (IPC) on wooden racks in engine exhaust duct. 11. Subpara. (c) 29 to 90 days 1 Engine stored on/off aircraft or in QEC: a Preserve fuel system (Ref.SERVICING Page 321 May 02/2003 . AMM) and store engine in a sheltered location where the engine is subjected to minimum temperature changes and the lowest possible humidity. 3045542 2 a Before storage. Para. c Run engine every seven days.5 kg) of desiccant on wooden racks in engine exhaust duct. Run engine (Ref. If color changes show the humidity is above 40%.). Refill with fresh oil (Ref.). 8. c Place 1 lb. AMM) b Seal off all openings to engine (Ref. Engine stored off aircraft or in QEC: a Place 1 lb. carry out an oil analysis to determine acidity (TAN) and water content. AMM). either by weight or volume. (0. If in the absence of a maximum TAN number from an oil brand specification and the TAN is above 1. drain and discard oil from main oil tank and reduction gearbox (Ref. Para. the humidity indicator and desiccant must be replaced or reprocessed to eliminate moisture. b Preserve oil system (Ref. b Seal off all openings to engine (Ref. C. AMM) and reseal all engine openings after every engine run (Ref. B.) before engine is removed from aircraft or stored on wing or in QEC. 72-00-00 ENGINE . the humidity indicator must be inspected at seven-day intervals. Start engine and run until oil temperature is 70°C (158°F) minimum.) before engine is removed from aircraft or stored on wing or in QEC. (0. repair per the maintenance manual recommendations. Subpara. Para.) before engine is removed from aircraft or stored on wing or in QEC. d Place 1 lb. IPC). Run engine (Ref. v Carry out a visual inspection of the engine externals.). carry out an oil analysis to determine acidity (TAN) and water content. AMM). c Preserve oil system (Ref. AMM). CAUTION: UNDER NO CIRCUMSTANCES SHOULD ENGINE OIL BE SPRAYED INTO AIR INLET OR EXHAUST OF ENGINE. A log recording the results of the inspections must be attached to the engine. The following may be used as an alternative to the preceding storage procedure: (a) Before storage.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. (0.). drain and discard oil from main oil tank and reduction gearbox (Ref. either by weight or volume. f Ensure window is provided in exhaust duct closure to facilitate observation of humidity indicator. 3045542 v Wash engine externals thoroughly with cleaner (Ref. Engine stored on aircraft for an undetermined amount of time. e Seal off all openings to engine (Ref. C. Subpara. DIRT PARTICLES DEPOSITED ON ROTOR AND STATOR COMPONENTS COVERED WITH OIL COULD ADHERE AND ALTER AIRFOIL SHAPES. If color changes show the humidity is above 40%. 8. the humidity indicator and desiccant must be replaced or reprocessed to eliminate moisture.5 kg) of desiccant (Ref. Refill with fresh oil (Ref. If in the absence of a maximum TAN number from an oil brand specification and the TAN is above 1. the humidity indicator must be inspected at seven-day intervals. If corrosion found. IPC) and humidity indicator on wooden racks in tail pipe. g (2) Spray exposed accessory drive pads with engine oil (PWC03-001) and protect with shipping covers (Ref. Cleaning/Painting). ADVERSELY AFFECTING ENGINE EFFICIENCY. NOTE: This fluid protects engine external surfaces by displacing water. 11. or water content is more than 800 parts per million. B.) before engine is removed from aircraft or stored on wing or in QEC. b Preserve fuel system (Ref. NOTE: During the period of storage.0. (b) Seal off all openings to engine (Ref. AMM). 72-00-00 ENGINE . v Apply anti-corrosion fluid inhibitor (PWC15-011) to engine external surfaces (including propeller shaft). Para.SERVICING Page 322 May 02/2003 . AMM). Check closely the reduction gearbox. carry out the following: B. The kit can be obtained from the following address or contact a local distributor for availability of the kit: Dexsil Chemical Corp.SERVICING Page 323 May 02/2003 .PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. Para. 72-00-00 ENGINE . The requirement to analyze the oil is not necessary. 11. or water content is more than 800 parts per million. or water content is more than 800 parts per million. NOTE: 2. Refill with fresh oil (Ref. Para. 2 A visual inspection of the engine externals. If in the absence of a maximum TAN number from an oil brand specification and the TAN is above 1. (2) Carry out an oil analysis to determine acidity (TAN) and water content. Start engine and run until oil temperature is 70°C (158°F) minimum. 1 An oil analysis to determine acidity (TAN) and water content.). The value of TAN in unused oil conforming to specification varies depending on brand and manufacturer. (d) Every 30 days. Shut down engine and reseal all engine openings(Ref.). Para. either by weight or volume. 1 Hamden Park Drive Hamden. 8.0. propeller shaft.). Run engine (Ref. Para. front and rear inlet cases. either by weight or volume. 2 Refill engine with fresh oil. AMM). If corrosion is found. 8.). (Ref. AMM). drain and discard oil from main oil tank and reduction gearbox (Ref. Use a Titra-Lube TAN Test Kit (P/N TI-TAN) to analyze the oil. CT 06517 USA TEL: 1-800-4-DEXSIL 203-288-3509 FAX: 203-248-6523 1 Drain and discard oil from main oil tank and reduction gearbox (Ref. Shut down engine(Ref. engine accessories and all attaching hardware. repair per the maintenance manual recommendations. (a) If in the absence of a maximum TAN number from an oil brand specification and the TAN is above 1. provided you carry out the following steps.0. 3045542 (c) Run engine every seven days. NOTE: 3. Oil System Preservation (1) Start engine and run until oil temperature is 70°C (158°F) minimum. proceed as follows: NOTE: 1. 11. MFCU. fuel pump. (6) Disconnect oil supply. (a) Engines stored in a QEC: 1 DELETED CAUTION: DO NOT USE PRESERVATIVE OIL ON THE PNEUMATIC SIDE OF THE COMPONENT. (5) With ignition OFF. motor engine and inject preservative oil until oil flows from line disconnected from flow divider. FCOC. (4) Connect supply of 5-micron-filtered preservative oil (PWC05-077) at 5 to 25 psig (34. Fuel System CAUTION: EXTREME CARE MUST BE TAKEN TO PREVENT FOREIGN MATERIAL FROM BEING DRAWN INTO FUEL SYSTEM. AMM). 72-00-00 ENGINE . Para. Drain and discard oil from main oil tank and reduction gearbox (Ref.SERVICING Page 324 Mar 11/2005 . 8. 3045542 3 Run engine (Ref. EQUIPMENT MUST INCORPORATE SUITABLE FILTERS NO COARSER THAN 5 MICRON RATING. Para. (3) Disconnect and displace fuel supply line from flow divider (Ref. proceed as follows: 1 C. AMM). 72-01-40). (b) If TAN is less than 1. Blank off line.474-172. Reinstall all components on the engine and reconnect lines previously disconnected. 8. (1) Close engine fuel supply valve (Ref. and the fuel condition lever in the ‘‘FUEL ON’’ position. step (1)).PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. (7) Connect lines previously disconnected (Ref. 72-01-40). Fill fuel side of components with preservative oil (PWC05-077) and drain off excess. 2 Remove the fuel heater. (8) Tag fuel line with date of preservation.).370 kpa) and 16°C (60°F) to oil-to-fuel heater inlet fitting. 4 Drain and discard oil from main oil tank and reduction gearbox (Ref.). (2) Disconnect fuel supply line at engine (Ref.0 above the limit given in the specification for the specific brand of oil or water content is less than 800 parts per million either by weight or volume. CAUTION: OBSERVE STARTER MOTOR OPERATING LIMITS. Electrical connections must be mated. c Cabin air supply pneumatic valve Component must be kept dry. REACTIVITY. If mating is not possible. approved shipping covers must be installed on connector(s) and associated wiring harness. Electrical connections must be mated. A shipping closure is also required to seal the PO connection on the EEC. (c) Install shipping closures and wrap assembly with plastic sheet (PWC05-053). or C. (d) Secure component in shipping container with foam-in-place polyurethane (PWC05-107). (b) Fill components to be shipped. with preservative oil (PWC05-077) and drain off excess. If mating is not possible. PRECAUTIONS FOR SAFE HANDLING. Install approved shipping cover to seal opening. WARNING: REFER TO THE MANUFACTURER’S MATERIAL SAFETY DATA SHEETS FOR CONSUMABLE MATERIALS INFORMATION SUCH AS: HAZARDOUS INGREDIENTS. B.. USE AND CONTROL MEASURES. as applicable. (2) Storage (a) Accessory storage life is unlimited. PHYSICAL/CHEMICAL CHARACTERISTICS. b Electrical components No preservation required. FIRE.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. providing the following procedures are carried out: 1 Accessories installed on a stored engine a Fluid handling components Preserve in accordance with Subpara. EXPLOSION. d Intercompressor bleed valve 72-00-00 ENGINE . except electrical. (e) Identify shipping container. No lubricating required. Accessories (1) General (a) Retain shipping parts of replacement components for use when returning defective components. 3045542 D.SERVICING Page 325 May 02/2003 . HEALTH HAZARD DATA. approved shipping covers must be installed on connector and associated wiring harness. Para. AMM). (4) If engine has not run for more than 90 days. E. Place in a moisture-proof bag and store in a dry location. Drain excess. Place in a moisture-proof bag with a desiccant pouch and store in a dry location. b Electrical components Install covers on all electrical connections. 2 Accessories stored off the engine a Fluid handling components Fill fuel system component with preservative oil (PWC05-077) and oil system component with engine oil (PWC03-001). (3) Place desiccant and indicator in evacuated heat-sealed polyethylene envelope until required for use. Install covers on all electrical connectors. No lubricating required. Fig. d Intercompressor bleed valve Component must be kept dry. (2) Connect fuel supply line to engine (Ref. Heat desiccant for two hours. AMM). F. Install cover on electrical connector. shipping covers. air and oil passages. (2) Allow oven to cool to room temperature. caps and plugs. No lubricating required. (3) Fill oil system to MAX. prime oil system as follows: (a) Disconnect oil line from oil cooler adapter (2. c Cabin air supply pneumatic valve Install approved shipping cover to seal opening. Place in a moisture-proof bag and store in a dry location. Install approved shipping covers to seal openings. 11. Install approved shipping cover to seal opening. mark (Ref. Depreservation (Engine) (1) Remove desiccant. 72-00-00 ENGINE . 3045542 Component must be kept dry.). 304) located adjacent to pressure oil filter (Ref.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO.SERVICING Page 326 May 02/2003 . Desiccant and Humidity Indicator Reactivation (1) Heat humidity indicator in oven at 121°C (250°F) until humidity indicator turns blue. DETERMINE AND RECTIFY CAUSE BEFORE REPEATING RUN. CAUTION: ABORT MOTORING IF AN OIL-PRESSURE INDICATION IS NOT OBTAINED WITHIN 15 SECONDS. (n) Remove air tube assembly (6) (Ref. Discard packing. (i) Install air tube assembly (6). Record quantity. CAUTION: COVER RESTRAINS SPRING. (c) Connect the oil line to oil cooler adapter (2). REMOVAL/INSTALLATION). Discard packings (Ref. SERVICING). SERVICING). (m) Remove fuel heater inlet filter cover and filter. (f) Remove bolts (1). spring (4) and washers (5). 72-01-30. packing (3). Do not remove packings. (j) Install fuel heater inlet filter cover and filter (Ref. cover (2) and packing (3). 72-01-30. Fig. (d) Remove fuel heater inlet filter cover and filter (Ref. (p) Lubricate new packing (3) with engine oil (PWC03-001) and install on cover (2). SERVICING). CAUTION: ENSURE AIR BLEED IS OFF. (o) Remove bolts (1). 72-01-30. REMOVAL/INSTALLATION). Torque the connector (Ref. (l) Carry out a dry motoring run (Ref. 72-00-00 ENGINE . 72-01-40. AMM) until an oil-pressure indication is shown on gage. (h) Install cover (2) and bolts (1).SERVICING Page 327 May 02/2003 . 3045542 (b) Raise connector (1) above level of engine oil inlet port and pour oil (PWC03-001) slowly into the connector until the pressure oil pump is filled and oil flows from connector (1). cover (2). Do not remove packing from cover.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 72-01-40.OFF CAUTION: STOP MOTORING AFTER OIL PRESSURE IS REGISTERED ON GAGE. REMOVAL/INSTALLATION). 305) from pressure oil check valve (Ref. (k) Air Bleed . AMM). 72-01-40. Torque bolts fingertight. Do not secure clamp assemblies (Ref. (e) Remove air tube assembly (6. (g) Put spring and washers into a plastic bag identified with engine serial number. PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3045542 OIL 1 2 C32217 Aircraft Oil Cooler and Pressure Pump .Priming Figure 304 72-00-00 ENGINE .SERVICING Page 328 May 02/2003 . They are by: (a) A P&WC Shipping container. General (1) There are two (2) approved methods to ship engines. 3045542 Key to Figure 304 1. NOTE: (r) The number of washers varies between one minimum and five maximum. (t) (5) Install fuel heater inlet filter and cover (Ref. or 72-00-00 ENGINE . Check that stream of fuel stops. (10) Reconnect fuel supply line to the flow divider and dump valve (Ref. AMM). Disconnect fuel supply line to flow divider and dump valve (Ref. (s) Lubricate new packing with engine oil (PWC03-001) and install on fuel heater inlet filter cover. Torque bolts 32 to 36 lb.5 AIR PLENUM WITHIN COMPRESSOR CASE.SERVICING Page 329 May 02/2003 . 72-01-40. Re-assemble using the same number of washers recorded in step (f). (3) Flush replacement assemblies with appropriate system fluid. (1) Remove and retain shipping parts of replacement assemblies for use when returning defective assemblies. spring (4).62-4. Shipping A. 72-01-30. Connector Adapter (q) Install washers (5). CAUTION: PROLONGED MOTORING (IN EXCESS OF 15 SECONDS) MAY RESULT IN LEAKAGE OF OIL INTO EXHAUST DUCT AND P2. 72-01-40.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. cover (2) and bolts (1). G. (2) Drain preserving fluids.07 Nm) and secure with lockwire (PWC05-089) or (PWC05-295). Depreservation (Accessories) 7. (9) Move condition lever to START position. REMOVAL/INSTALLATION). SERVICING). (3. Install air tube assembly (6) (Ref. 2. Check that fuel stream resumes. (7) Check that a solid stream of fuel comes out of fuel-supply line. as defined in the IPC.in. (8) Move condition lever to . (6) Carry out a wet motoring run (Ref. 72-01-40. REMOVAL/INSTALLATION). REMOVAL/INSTALLATION). 3045542 3 2 4 6 5 1 C21069 Oil Check Valve .SERVICING Page 330 May 02/2003 .Removal of Spring and Washers Figure 305 72-00-00 ENGINE .PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. Tables 301. (970 mm) 46 in. before the engine is installed. (1170 mm) 691 lb. 2. 4. Shipping Method CAUTION: WHEN AN ENGINE IS NOT SHIPPED IN A P&WC SUPPLIED SHIPPING CONTAINER. (809 kg) 72-00-00 ENGINE . 5. IT IS MANDATORY TO TRANSPORT THE ENGINE IN A TRUCK EQUIPPED WITH AN AIR SUSPENSION SYSTEM (i. of the container shock absorbers is recommended to ensure they are not permanently deformed or damaged. DESCRIPTION Approximate External Dimensions Length Width Height Weight Empty Full DATA 93. to ensure the shock absorbers are free from cracks and excessive travel. Bolts Cover Packing Spring Washer Tube Assembly (b) Transportation stand. 6. 302 and 303 provide details of the shipping containers. Refer to the appropriate IPC for shipping container parts.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO.e. 3045542 Key to Figure 305 1.7 in. B. Engine Shipping Container (For Reference Purposes Only) These are the characteristics of the P&WC engine shipping container. (2) Transportation Stand (a) Engines supplied with a QEC kit (Airframe supplied) must be shipped in a transportation stand (local manufacture) firmly secured to the truck bed. TABLE 301. (1) Shipping Container (Ref. (2380 mm) 38. Repeat the inspection after the engine is installed. IPC) (a) An inspection. 3. The pickup points of the stand must use the aircraft/engine shock absorber mounts. (b) When loaded on a truck. (314 kg) 1781 lb.SERVICING Page 331 May 02/2003 . AIR SPRINGS).1 in. the container must be firmly secured to the truck bed. SERVICING Page 332 May 02/2003 . 3045542 TABLE 302. (1753 mm) 40 in. Refer to the appropriate IPC for shipping container parts. DATA 69 in. (1016 mm) 46 in. Main Oil Tank and/or RGB NOTE: Engine oil draining is carried out from four drain outlets. DESCRIPTION Approximate External Dimensions Length Width Height Weight Empty Full DATA 38 in.) shows they are damaged. etc. (940 mm) TBA TBA TABLE 303. Refer to the appropriate IPC for shipping container parts. RGB chip detector and plug. (965 mm) 35 in. (2) Operate feathering pump through full feather/unfeather/feather cycle. (3) Remove chip collector plugs (1) and packings (2). DESCRIPTION Approximate External Dimensions Length Width Height Weight Empty Full 8. turbomachinery chip detector and oil tank plug. NOTE: Replacement of the chip collector plug packings (2) is only necessary if a visual inspection (nicks. (1) Disconnect electrical harness from chip detector plugs (1) (Ref.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. cuts. (1168 mm) TBA TBA Oil Draining (Ref. Turbomachinery Shipping Container (For Reference Purposes Only) These are the characteristics of the P&WC Turbomachinery Shipping container. 72-00-00 ENGINE . CAUTION: ENSURE AIRFRAME ELECTRICAL POWER IS OFF WHEN DISCONNECTING RECEPTACLES AND PLUGS. AMM). Fig. Reduction Gearbox Shipping Container (For Reference Purposes Only) These are the characteristics of the P&WC Reduction Gearbox Shipping container. 306) A. (889 mm) 37 in. 3045542 (4) Install drain fitting (4) (PWC38147) in chip collector valves. (6) Remove plug (8) and packing (9). CAUTION: AFTER INSTALLATION. Torque 65 to 75 lb. 307) A. Fig. Chip Collector . Procedure (1) Drain oil (Ref. (7) Allow oil to drain to slow drip. (b) Install plug.Replacement (Ref. 8.6-25. (15) 9. (9) Lubricate packings (2) with engine oil (PWC03-001) and install on chip detector plugs (1). SCALLOP ON CHIP DETECTOR PLUG IS IN LINE WITH FLAT ON CHIP DETECTOR VALVE HEXAGON. (13) Install plug. Refill with oil (Ref. Remove chip collector valve (3) and packing (4). (22. CAUTION: ENSURE AIRFRAME ELECTRICAL POWER IS OFF WHEN CONNECTING RECEPTACLES AND PLUGS. (10) Install chip collector plugs (1). Remove plug (6) and packing (7).in. NOTE: (5) Ensure packing (5) is in place. Rotate plugs 90 degrees clockwise to locked position. Para. (14) If removed. 10.48 Nm) and secure with lockwire (PWC05-089) or (PWC05-295). 72-00-00 ENGINE . Para. Discard packing.in. Discard packing.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. NOTE: Plug (6) is only removed when an AC generator failure is suspected and strainer secured by plug is inspected. NOTE: (2) Chip collector plug (1) and packings (2) are removed when oil is drained. (7.SERVICING Page 333 May 02/2003 . AMM). (8) Remove drain fitting and hose assembly (4). Torque plug 200 to 225 lb.4 Nm) and secure with lockwire (PWC05-089) or (PWC05-295). (11) Connect electrical harness (Ref.). Discard packing. install plug (6) as follows: (a) Lubricate packing (7) with engine oil (PWC03-001) and install on plug. (12) Lubricate packing (8) with engine oil (PWC03-001) and install on plug (9).35-8.). ENSURE VISUALLY OR BY FEEL. SERVICING Page 334 May 02/2003 . 3045542 4 5 1 2 REDUCTION GEARBOX 4 3 7 6 5 REDUCTION GEARBOX 1 TYPICAL LOCKED POSITION 2 TURBOMACHINERY 8 9 3 C39231 Oil Draining Figure 306 72-00-00 ENGINE .PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. VISUALLY OR BY FEEL. (5) Lubricate packings (2) with engine oil (PWC03-001) and install on chip collector plug (1).PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. ENSURE. (6) Install chip collector plug (1). 7. 2. AMM).). 5. (2) Remove filler cap. (7) 10. Para. 9.60 Nm) and secure with lockwire (PWC05-089) or (PWC05-295). Connect electrical harness (Ref. 3. (19. THAT SCALLOP ON CHIP COLLECTOR PLUG IS IN LINE WITH FLAT ON CHIP COLLECTOR VALVE HEXAGON. CAUTION: AFTER INSTALLATION. Procedure (1) Drain oil (Ref. Rotate plug 90 degrees clockwise to locked position.in. CAUTION: DO NOT USE ANY SHARP TOOLS OR OBJECTS TO OPEN THE FLAPPER VALVE.SERVICING Page 335 May 02/2003 . 4. 6. CAUTION: ENSURE ELECTRICAL POWER IS OFF WHEN CONNECTING RECEPTACLES AND PLUGS. (4) Install valve.78-22. CONTINUAL USE OF A SHARP OBJECT MAY DAMAGE THE VALVE AND NOT ALLOW THE VALVE TO SEAL CORRECTLY. 8. Torque 175 to 200 lb. Engine oil is to be flushed when contamination is evident or when a change in operating conditions or oil supply occurs. 8. Oil System Flushing and Filling NOTE: A. 72-00-00 ENGINE . 3045542 Key to Figure 306 1. Chip Collector Plug Packing Chip Collector Valve Drain Fitting Packing Plug Packing Plug Packing (3) Lubricate packing (4) with engine oil (PWC03-001) and install on chip collector valve (3). (3) Use rod (PWC56515) to open flapper valve and fill engine with fresh oil (PWC03-001) to MAX mark on sight gage. PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3045542 1 2 3 4 REDUCTION GEARBOX 1 2 3 4 TYPICAL LOCKED POSITION TURBOMACHINERY C38739 Chip Collector .Replacement Figure 307 72-00-00 ENGINE .SERVICING Page 336 May 02/2003 . REFER TO ENGINE . Chip Collector Plug Packing Chip Collector Valve Packing (4) Install filler cap.APPROVED LUBRICATING OILS. Add engine oil (PWC03-001) to the required level as determined by operator’s experience. AMM). 11. IF CHANGING OIL BRANDS. 72-01-50).SERVICING Page 337 May 02/2003 . 4. never exceeding MAX indication or letting level drop below MIN or ADD 3 marks. 3045542 Key to Figure 307 1. not exceeding MAX indication.). (6) Drain oil (Ref. AMM). (12) Check for oil leaks. CAUTION: DO NOT USE ANY SHARP TOOLS OR OBJECTS TO OPEN THE FLAPPER VALVE. CONTINUAL USE OF A SHARP OBJECT MAY DAMAGE THE VALVE AND NOT ALLOW THE VALVE TO SEAL CORRECTLY. (11) Carry out a five-minute run at ground idle (Ref. 72-01-50). (5) Carry out a five-minute engine run at ground idle to fill and flush oil lines (Ref. 8.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. (13) Allow 15 ± 5 minute period after shutdown to stabilize the engine. 72-01-50). Oil Filling Procedure (1) Gravity Fill (a) Remove filler cap. A. 2. (b) Use rod (PWC56515) to open flapper valve and fill with engine oil to required level as determined by operator’s experience. Oil System Filling CAUTION: TO AVOID THE POSSIBILITY OF INTERNAL ENGINE DAMAGE. (10) Fill with fresh oil (PWC03-001) to MAX mark on sight gage. (7) Remove pressure and scavenge oil filter covers (Ref. (c) Install filler cap. 3. (9) Install clean pressure and scavenge filter elements (Ref. nor allowing level to drop below MIN or ADD 3 marks. (8) Remove pressure and scavenge filter elements (Ref. Para. 72-00-00 ENGINE . Replenishing Empty Oil System NOTE: If the sight glass is dirty. CAUTION: OIL LEVEL ABOVE THE MAX MARK CAN NOT ALWAYS BE CLEARLY SEEN ON THE SIGHT GLASS. (10) Check for oil leaks. 72-00-00 ENGINE . (3) Add oil (PWC03-001) until level shown on sight glass is 3 quarts below MAX mark. Description and Operation. (2) Carry out a dry motoring run to prime oil pumps and lines (Ref. (1) Fill with engine oil (PWC03-001). Adjustment/Test). (6) Before shut down. Adjustment/Test). oil level inspection is not easy. (5) Run engine at ground idle and exercise the propeller a minimum of 3 times from feather to unfeather.SERVICING Page 338 May 02/2003 . OIL SMELL. SMOKE IN THE CABIN AND AN INTERNAL ENGINE FIRE. Refer to Chapter 72-01-50 for removal/cleaning/installation of the sight glass. (4) Start engine (Ref. run engine for a minimum of 20 seconds with propeller in feather position.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. (8) Check engine oil level within 30 minutes (15 ± 5 minutes is considered optimum) of engine shut down. 3045542 (2) Pressure fill (a) Connect pressure fill line to oil tank pressure fill valve. (7) Shut down engine (Ref. use blue dye (PWC05-026) (Ref. OIL ABOVE THE MAX MARK CAN POSSIBLY RESULT IN AN INTERNAL OIL LEAK. (9) Add engine oil (PWC03-001) to required level as determined by operator’s experience. never exceeding MAX indication nor letting level drop below MIN or ADD 3 marks. B. Adjustment/Test). Rectify if necessary. Bring level to MAX mark on sight gage. Engine Approved Lubricating Oils). 72-00-00. To improve visibility of the oil level during inspection. (b) Connect drain line to oil tank overfill valve. (1) Add engine oil (PWC03-001) as follows: (a) Oil level can be clearly seen through sight glass. 3045542 12. preceding.) to required level as determined by operator’s experience. refer to step (1)(a). oil level inspection is not easy. Description and Operation. as a minimum is not above 113°F (45°C). never exceeding MAX indication nor letting level drop below MIN or ADD 3 marks.SERVICING Page 339 May 02/2003 . General Oil Level Check (1) Engine oil levels must be checked within 30 minutes (15 ± 5 minutes is considered optimum) of engine shutdown. Oil Level Check and Top-up A. an engine run must be carried out per the step above.6 quarts of oil and check the oil level 1 If oil level can be clearly seen on the sight glass. During shutdown.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. If engine did not have level checked after last flight or the oil temperature. use blue dye (PWC05-026) (Ref. the engine must run for a minimum of 20 seconds with the propeller in feather. If this procedure is not followed. OIL ABOVE THE MAX MARK CAN POSSIBLY RESULT IN AN INTERNAL OIL LEAK. This ensures that the maximum amount of oil is returned from the PVM via the reduction gearbox to the oil tank. Engines left overnight may have misleading oil level indications. Para. 72-00-00 ENGINE . 2 If oil level still cannot be clearly seen on the sight glass: Drain oil (PWC03-001) (Ref. Engine Approved Lubricating Oils). Add 5. CAUTION: OIL LEVEL ABOVE THE MAX MARK CAN NOT ALWAYS BE CLEARLY SEEN ON THE SIGHT GLASS. (b) Oil level cannot be clearly seen through sight glass. To improve visibility of the oil level during inspection. NOTE: B. as a minimum above 113°F (45°C). with the oil temperature. the oil level sightglass indication may not be accurate. Drain (Ref.) or add oil (PWC03-001) to required level as determined by operator’s experience. Para. SMOKE IN THE CABIN AND AN INTERNAL ENGINE FIRE. Top-up NOTE: If the sight glass is dirty. 72-00-00. never exceeding MAX indication nor letting level drop below MIN or ADD 3 marks. Refer to Chapter 72-01-50 for removal/cleaning/installation of the sight glass. OIL SMELL. 8. 8. 308).PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. Step (1)) Flight hours (Ref. Step (2)) = oil/hour (4) Plot oil/hour value on a graph (Ref. Fault Isolation). 3045542 13.256 liter/hr). determine oil consumption rate: Oil consumption (Ref. Determine and rectify cause (Ref. (3) Oil level check and replenishing must be carried out at intervals recommended by MRB. measure and record amount of oil added to top up tank to MAX mark on sight glass. (3) Using following formula. The units may be lb/hr (kg/hr) or quart/hr (liter/hr). 72-00-00 ENGINE . Fig. Procedure (1) When carrying out oil system top-up. General (1) The amount of oil added to bring level on sight glass to MAX mark or normal operating level (Ref. (5) Oil consumption above maximum permissible or a sudden or gradual increase must be investigated. (2) Check number of flight hours from last top-up.) is recorded in graph form. B. 11.5 lb/hr (0. Oil Consumption Trend Monitoring A. (2) 0.227 kg/hr) is maximum oil consumption permissible which is equivalent to 0. Para.270 quart/hr (0.SERVICING Page 340 May 02/2003 . 181 0. 13 20 27 6 MAR.2 0.091 0.SERVICING Page 341/342 May 02/2003 . 13 20 27 3 10 17 24 APR.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO.4 0.3 0.5 0.045 0.227 0.1 6 FEB. 1 8 15 MAY NOTE: THIS GRAPH IS A SAMPLE ONLY OF TYPICAL NORMAL OIL CONSUMPTION.136 0. NOT TO BE USED AS A BASE LINE C18195 Oil Consumption Trend Monitoring . 3045542 KG / HR LB / HR 0.Sample Graph Figure 308 72-00-00 ENGINE . . MEDICAL TREATMENT IS REQUIRED AS SOON AS POSSIBLE IF THE ACID TOUCHES BARE SKIN. Front Sling. READ THE MATERIAL SAFETY DATA SHEETS BEFORE YOU USE THESE MATERIALS.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. General A. HYDROFLUORIC ACID IS PRODUCED WHEN THE MATERIAL DECOMPOSES. Name PWC03-001 PWC05-089 PWC05-295 Oil. B.REMOVAL/INSTALLATION Page 401 Mar 11/2005 .REMOVAL/INSTALLATION 1. 3045542 ENGINE . unless stated otherwise. NOTE: 2. WARNING: WEAR GOGGLES WHEN REMOVING LOCKWIRE. Engine Lockwire Lockwire (may be used instead of PWC05-089) Special Tools Special tools are identified in procedural text by part number in parentheses. For more data. Front 72-00-00 ENGINE . WARNING: 3. refer to the CONSUMABLE MATERIALS section at the beginning of this manual. Engine/Turbomachinery Adapter. Rear Adapter. These instructions provide the information necessary for the handling of the engine in and out of the airframe and engine stands and module separation. Name PWC34200 PWC34294 PWC37106 PWC37107 PWC37108 PWC37109 PWC38212 PWC38307 PWC54002 PWC54213 PWC54214 Stand Support Support Support Support Support Adapter. Rear Adapter. Use engine oil (PWC03-001). Consumable Materials The consumable materials listed below are referred to in this section. Item No. for general lubrication. WARNING: GLOVES MUST BE WORN TO PROTECT SKIN WHEN DECONTAMINATING AREAS CONTAINING GASKETS OR PACKINGS WHICH HAVE DECOMPOSED DUE TO HIGH TEMPERATURES. SOME MATERIALS CAN BE DANGEROUS. Tool No. Hot section component removal/installation is covered in 72-03-00 . (4) Remove bolts (9. rear adapter (PWC54213) (16) and front adapter (PWC54214) (15). (7) Attach sling to hoist and take weight of engine. respectively) (3. 6) and stand adapters (PWC38307. 401) (1) Drain oil if shipping intended (Ref. Servicing). Prepare engine for storage/shipping. Fig. (6) Lift engine clear of stand (2). 13) . system tubing. as necessary. (4) Disconnect and remove. (907 kg) safe working load (SWL) 5. PWC38212.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3045542 4. 10) and nuts (11). (5) Install shipping closures on disconnected tubes and engine adapters. (2) Depending on purpose of engine removal. electrical harness. (7) If fitted. 72-00-00 ENGINE . remove slave bolts (4. Removal A. Engine from Stand (PWC34200) (Ref. Name Hoist. 5) . (8) Release engine mounts and raise engine clear of airframe. rear adapter (PWC54213) and front adapter (PWC54214). Engine from Airframe (1) Remove power plant panels and drain oil (Ref. (3) Install shipping closures on apertures created by removal of accessories. Servicing). Fixtures. B. PWC37108.REMOVAL/INSTALLATION Page 402 Mar 11/2005 . (2) Install sling (PWC54002) (1). remove propeller and engine-mounted accessories. (6) Install sling (PWC54002). CAUTION: DO NOT ATTEMPT TO LIFT AN ENGINE THAT IS ATTACHED TO THE STAND. (3) Attach sling to hoist and take weight of engine. equipment and supplier tools listed below are referred to in procedural text. (5) Remove ball lockpins (14) and lower supports (PWC37106. control linkage and associated brackets and washers. Equipment and Supplier Tools The fixtures. 2000 lb. respectively) (12. (c) Raise connector (1) above level of engine oil inlet port. (5) Fill oil system to mark (Ref. (2) Install engine in airframe. (6) Advance condition lever to START position and push ignition button ON. AMM). Hand tighten loose connector and continue pouring until the oil lines and pressure pump are filled and oil flows from connector (1). Fig. 72-01-50. 403) from pressure oil check valve (Ref. electrical harness. NOTE: To facilitate oil system priming of engines which have not run for more than 90 days. (3) Remove sling and front and rear adapters. Install accessories and connect system tubing. (9) If the engine has not been run for more than 90 days.REMOVAL/INSTALLATION Page 403 Mar 11/2005 . (4) Remove shipping closures. AMM). connect engine mounts. Pour oil (PWC03-001) slowly into the connector until oil seeps from the loose connector adjacent to oil pump. (b) Remove air tube assembly (6.). Installation A. (b) Disconnect oil line from oil cooler adapter (2. Para. 3045542 6. SERVICING). Servicing). 72-01-30. control linkage and associated brackets and washers. 402) located adjacent to pressure oil filter (Ref. 72-10-00) Remove engine from stand (Ref. REMOVAL/INSTALLATION). prime oil system as follows: (a) Remove pressure oil filter and cover (Ref.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. AMM). Do not remove packings from cover and filter. electrical harnesses and control linkages (Ref. (8) Prime pressure oil pumps as follows: (a) Loosen oil line at oil cooler adapter located adjacent to oil pump (Ref. (7) Check that both igniters are audible. 72-00-00 ENGINE . Engine in Airframe NOTE: (1) Inspect propeller shaft inside diameter for visible crack before engine installation (Ref. B. 5. Fig. Steps (9) (a) to (g) inclusive). the pressure oil check valve spring and washers may be removed prior to engine installation (Ref. (d) Connect the oil line to the oil cooler adapter (2) and torque both oil line connectors (Ref. AMM). 3045542 1 16 15 10 11 6 5 9 13 4 8 12 7 3 14 2 14 17 C11867C Stand PWC34200 .Engine Removal/Installation Figure 401 72-00-00 ENGINE .PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO.REMOVAL/INSTALLATION Page 404 Mar 11/2005 . (e) Install cover (2) and bolts (1). REMOVAL/INSTALLATION). spring (4) and washers (5). CAUTION: ENSURE AIR BLEED IS OFF. (h) Air Bleed . 14. 72-00-00 ENGINE . 12. (d) Put spring and washers into a plastic bag identified with engine serial number. 9. CAUTION: STOP MOTORING AFTER OIL PRESSURE IS REGISTERED ON GAGE.REMOVAL/INSTALLATION Page 405 Mar 11/2005 . (i) Carry out a dry motoring run(AMM) until an oil pressure indication is shown on gage. (f) Install air tube assembly (6). 10. 8. (c) Remove bolts (1). (j) Remove pressure oil filter and cover. 72-01-50. Rear Bolt Support Support Bolt Bolt Nut Support Support Ball Lockpin Adapter. 72-01-50.OFF.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 16. Torque bolts fingertight. 13. Abort motoring if an oil pressure indication is not obtained within 15 seconds. Determine and rectify cause before repeating run. (g) Install pressure oil filter and cover (Ref. 3. 11. 2. Front Adapter. 5. Front Bolt Adapter. 3045542 Key to Figure 401 1. cover (2). SERVICING). Sling Stand Adapter. Do not remove packing from cover. 17. SERVICING). packing (3). Discard packings (Ref. Record quantity. 72-01-30. 4. Rear Support. Do not secure clamp assemblies (Ref. 7. Assy CAUTION: COVER RESTRAINS SPRING. 6. 15. 3045542 OIL 1 2 C32217 Aircraft Oil Cooler and Pressure Pump .PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO.REMOVAL/INSTALLATION Page 406 Mar 11/2005 .Priming Figure 402 72-00-00 ENGINE . (17) Switch on ignition and start engine (Ref. (16) Fill oil tank 2 quarts (1.5 AIR PLENUM WITHIN THE INTERCOMPRESSOR CASE. REMOVAL/INSTALLATION). Check that fuel stream resumes. (q) Install pressure oil filter and cover (Ref.07 Nm) and secure with lockwire (PWC05-089) or (PWC05-295). (15) Reconnect fuel supply line to flow divider and dump valve (Ref. 72-01-40. AMM).PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. (13) Move condition lever to SHUT position. NOTE: The number of washers varies between one minimum and five maximum.REMOVAL/INSTALLATION Page 407 Mar 11/2005 . 72-01-50. 2. (m) Lubricate new packing (3) with engine oil (PWC03-001) and install on cover (2). (18) Run engine at ground idle and exercise propeller a minimum of 3 times from feather to unfeather. 72-01-30. SERVICING). Check that stream of fuel stops. (14) Move condition lever to START position. Discard packing. REMOVAL/INSTALLATION). 72-01-40. using the same number of washers recorded in step (c). cover (2) and bolts (1). 403) (Ref. Connector Adapter (k) Remove air tube assembly (6.62-4. CAUTION: PROLONGED MOTORING (IN EXCESS OF 15 SECONDS) MAY RESULT IN LEAKAGE OF OIL INTO EXHAUST DUCT AND P2. spring (4). (p) Lubricate new packings with engine oil (PWC03-001) and install on pressure oil filter and filter cover. cover (2) and packing (3).892 liters) below maximum level.in. REMOVAL/INSTALLATION). (3. 72-00-00 ENGINE . (10) Disconnect fuel supply line to flow divider and dump valve (Ref. Fig. (12) Check that solid stream of fuel comes out of fuel supply line. (n) Install washers (5). Re-assemble. (11) Carry out a wet motoring run(AMM) . (l) Remove bolts (1). REMOVAL/ INSTALLATION). 3045542 Key to Figure 402 1. (o) Install air tube assembly (6) (Ref. Torque bolts 32 to 36 lb. 72-01-30. PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO.REMOVAL/INSTALLATION Page 408 Mar 11/2005 .Removal of Spring and Washers Figure 403 72-00-00 ENGINE . 3045542 3 2 4 6 5 1 C21069 Oil Check Valve . (7) Raise front support (PWC37106) (12) and rear support (PWC37108) (13) and align supports with adapters.in. 6. (5) Attach adapter (3) to front support with bolt (9). and attach support (13) to adapter with bolt (10) and nut (11). 16) and hoist. (2) Install rear adapters (if airframe/engine mounts removed) (PWC38212) (5) and bolts (6). (20) Shut down engine (Ref. (8) Attach support (12) to adapter with bolt (9). (81. (4) Lower engine onto stand and align front support (PWC37107) (7) and rear support (PWC37109) (8) with front and rear adapters on same side of engine. (6) Attach adapter (5) to rear support with bolt (10) and nut (11). Engine in Stand (PWC34200) (Ref. 3. NOTE: Reduction Gearbox and Turbomachinery modules are separated in 72-02-00. (22) Add engine oil to required level as determined by operator’s experience. AMM). (23) Check for fuel and oil leaks.40 Nm). torque bolts 720 to 800 lb. Fig. torque bolts 290 to 325 lb. (3) Position stand (2) under engine and apply stand brake. 72-00-00 ENGINE .in.77-36. 2. (9) Install ball lockpins (14) in supports. 5. 401) (1) Install front adapters (if airframe/engine mounts removed) (PWC38307) (3) and bolts (4).REMOVAL/INSTALLATION Page 409/410 Mar 11/2005 .73 Nm). with propeller in feather position. 3045542 Key to Figure 403 1. (10) Remove sling (1). (32.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. Bolt Cover Packing Spring Washer Tube Assembly (19) Before shutdown. (21) Check engine oil level within 30 minutes (15 ± 5 minutes is considered optimum) of engine shutdown.36-90. B. 4. Rectify if necessary. run engine for a minimum of 20 seconds. never exceeding MAX indication or letting level drop below MIN or ADD 3 marks. adapters (15. . Tool No. These instructions provide information necessary for adjusting and testing the engine after replacement of reduction gearbox. 6. the test required to functionally check the engine or component is listed in Table 501. engine or accessories. refer to the CONSUMABLE MATERIALS section at the beginning of this manual. Name PWC37651 Puller Fixtures. 3045542 ENGINE . Equipment and Supplier Tools Not Applicable 5. are shown in Chapter 05-10-00. unless otherwise stated. READ THE MATERIAL SAFETY DATA SHEETS BEFORE YOU USE THESE MATERIALS. B.ADJUSTMENT/TEST Page 501 Mar 09/2001 . turbomachinery. WARNING: WEAR GOGGLES WHEN REMOVING LOCKWIRE. Engine/Component Replacement Test Requirements In the event of an engine or component replacement. General A. For more data. Lubricate packings with engine oil (PWC03-001). Carry out instructions to operate engine in conjunction with instructions in airframe maintenance manual. NOTE: 2. Engine Lockwire Lockwire (may be used instead of PWC05-089) Special Tools Special tools are identified in procedural text by part number in parentheses. Item No.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO.ADJUSTMENT/TEST 1. SOME MATERIALS CAN BE DANGEROUS. 72-00-00 ENGINE . WARNING: 3. when installed in the aircraft. Name PWC03-001 PWC05-089 PWC05-295 Oil. Engine Ground Running Operating Limits The parameters which the engines should meet on ground test. Consumable Materials The consumable materials listed below are referred to in this section. CAUTION: INTERCHANGEABILITY REQUIREMENTS MUST BE REVIEWED WHEN REPLACING PARTS TO ENSURE COMPATIBILITY WITH EXISTING SERVICEABLE COMPONENTS. 4. Subpara. Overtorque and Overtemperature Limits Refer to Chapter 05-10-00 for overtorque limits and overtemperature limits. 10. K. Engine/Component Replacement Test Requirement Test Required (See NOTE 1) TMM / FUEL O/S GOV ENGINE/ PUMP / O/S HYDRAULIC RGB PROP EEC MFCU PCU AFU GOV.) X Propeller Purging X X Leak Check (See NOTE 2) X X Ground Idle X X Flight Idle/Maximum RPM X Minimum RPM (Min. J. Para.. Adjustment/Test) X NOTE: 1. Subpara. NOTE: 2..) X Propeller Overspeed Protection System Test X EEC Fail Fixed Mode and MFC Manual Mode Test X Acceleration Check (Ref. 10. Para. Refer to Aircraft Maintenance Manual unless otherwise stipulated. 7. PUMP IBV Oil Pressure (Ref. A leak check is necessary when fuel 72-01-40 or oil 72-01-50 system components have been replaced.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3045542 TABLE 501..) X X X X X X X X X X X X IBV Test (Ref.ADJUSTMENT/TEST Page 502 Mar 01/2002 . 72-00-00 ENGINE . 72-01-30. Para. Subpara. Governing NP) X X X X X X X X X X X X X X X X X X X X Maximum Power/ Maximum RPM X X X X X X X Reverse Maximum Governing X X X X X X X Propeller Overspeed X X X X X LO PITCH Test X X X X Engine Trimming (EEC) X Power Assurance (Ref. A. 10. ON. (11) Starter control switch . Servicing) . No. (10) Retard condition lever .ON. B. (4) Fuel boost pump .OFF. 3045542 8. CAUTION: PROLONGED MOTORING MAY RESULT IN LEAKAGE OF OIL INTO EXHAUST DUCT AND P2.ADJUSTMENT/TEST Page 503 Jul 13/2001 . NOTE: Discontinue engine motoring if positive oil pressure is indicated.OFF. (6) Condition lever . Check green light extinguishes.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. No. (5) Accessory loads .GRD IDLE.OPEN. 72-00-00 ENGINE .OFF. (4) Check engine controls for function and freedom of movement. 1 or Eng. Wet Motoring (1) Electrical power supply .OFF. (3) Fuel supply valve . (12) Check for unusual noises during rundown. (2) Check for security of engine and components. (9) When NH passes through 10%. advance appropriate condition lever to FEATHER (fuel on) for 15 seconds maximum. fill one quart below MAX (Ref. (2) Ignition .Press to OFF position. (5) Power lever . (8) Check NH starts to increase.5 PLENUM. CAUTION: OBSERVE STARTER MOTOR OPERATING LIMITS. (6) Bleed air .OFF. Starting A. 2 as appropriate and check green START light illuminates. Prestart CAUTION: GROUND RUNNING MUST ALWAYS BE CARRIED OUT WITH THE AIRCRAFT FACING INTO WIND. (7) Press START button for Eng. (1) Check oil level. (3) Check for fuel and oil leaks. Press to OFF position. CAUTION: OBSERVE STARTER MOTOR OPERATING LIMITS. (5) Fuel boost pump switch .OFF. (8) Engine start control switch .ADJUSTMENT/TEST Page 504 Mar 09/2001 . (1) Electrical power supply . Check NH starts to increase. (4) Fuel supply valve . NOTE: D. (11) Electrical power supply to engine .5 PLENUM. (7) Motor engine for 15 seconds. Dry Motoring (to purge engine of fuel after wet motoring run or in the event of fire occurring in the engine after starting or permit a compressor wash to be carried out.ON. Discontinue engine motoring if positive oil pressure is indicated.OFF.CLOSED. the engine is recommended to be run for at least 3 minutes before engine Air Bleed is selected ON.ON. (1) Condition lever . (2) Ignition . NOTE: A dry motoring run is not required if the wet motoring run was carried out to depreserve the fuel system. CAUTION: OIL AT TEMPERATURES BELOW -40°C (-40°F) MUST BE PREHEATED PRIOR TO STARTING ENGINE. NOTE: A ground power unit (GPU) is recommended to be used to reduce maximum ITT/T6 during engine start.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO.OPEN. 72-00-00 ENGINE . Start NOTE: After motoring cycle(s) or aborted start(s).ON. (6) Press START button for Eng. (9) Fuel boost switch . 2 as appropriate and check green START light illuminates.OFF. Check green light extinguishes.FUEL OFF. CAUTION: PROLONGED MOTORING MAY RESULT IN LEAKAGE OF OIL INTO EXHAUST DUCT AND P2. (10) Fuel supply valve . (3) Electrical power supply to engine . 3045542 C.OFF.) CAUTION: CARRY OUT DRY MOTORING RUN BEFORE STARTING ENGINE. (14) Check engine for oil or fuel leaks. (13) Electrical power supply . 1 and Eng. v INTERTURBINE TEMPERATURE (ITT/T6) EXCEEDS STARTING LIMITS (REF. (3) Ignition . 1 or Eng.FLT IDLE. CAUTION: IF ANY OF THE FOLLOWING OCCURS.ON. No.select ATO.Press to ON position. SWITCH IGNITION OFF.OPEN. 3045542 (2) Electronic engine control (EEC) . (b) NL starts to increase.‘‘1’’. (a) NH starts to increase. (4) Fuel valve . 2 as appropriate and check green START light illuminates.ADJUSTMENT/TEST Page 505 Jul 13/2001 . ALLOW ENGINE TO DRAIN FOR 30 SECONDS: v ENGINE FAILS TO LIGHT UP WITHIN 10 SECONDS AFTER ADVANCING CONDITION LEVER TO FEATHER. RETARD CONDITION LEVER TO ‘‘OFF’’. (5) Fuel boost pump . (10) Press START button for Eng. (6) Air bleed . SWITCH IGNITION OFF AND INVESTIGATE (REF. v NH EXCEEDS 78%. No. CAUTION: OBSERVE STARTER MOTOR OPERATING LIMITS. (8) Power lever .FUEL OFF. FAULT ISOLATION). PRESS START BUTTON TO OFF POSITION. v ENGINE LIGHTS UP BUT FAILS TO ACCELERATE TO 66% ± 2% NH WITHIN 50 SECONDS IN EEC MODE (30 SECONDS IN MANUAL MODE). 05-10-00).PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. (9) Power rating switch . 72-00-00 ENGINE .Closed. MOVE START CONTROL SWITCH TO OFF POSITION. (7) Condition lever . ‘‘2’’ or both as required. (11) Check: CAUTION: IF NH FAILS TO INCREASE AFTER PRESSING START BUTTON. (17) Start green light goes off at between 55 to 65% NH. A. or (b) If ITT/T6 is greater than or equal to 200°C (392°F) 1 Advance condition lever to FEATHER between 10 and 19% NH. FOLLOWED BY A 15 SECOND DRY MOTORING RUN. At first engine run after installation.positive reading must occur at or before 40% NH. BEFORE ATTEMPTING START. Refer to Engine Overhaul Manual. 05-10-00). CARRY OUT DRY MOTORING OF ENGINE. Shut engine down. Start engine. NOTE: 3. 72-00-00 ENGINE . oil pressure-positive reading must occur between 25-40% NH. 3045542 v NO POSITIVE OIL PRESSURE ABOVE 40% NH. CAUTION: SHUT DOWN ENGINE (REF. NOTE: 1. check for correct assembly of PRV. CAUTION: IF ITT/T6 MAINTAINS 950°C (1742°F) FOR MORE THAN 5 SECONDS OR CONTINUOUS FLAME ISSUE FROM EXHAUST. Start engine to warm up oil to between 50 to 115°C (122-239°F). ITT/T6 must not exceed limits (Ref. (15) Oil pressure 40 psi min. OBSERVING STARTER MOTOR OPERATING LIMITS. PARA. or maintenance to pressure regulating valve or oil check valve. a check should be made to verify correct operation. ALLOW ENGINE TO STOP ROTATING BEFORE REPEATING THE COMPLETE START PROCEDURE. NOTE: 2. (16) ENG FUEL PRESS caution light goes out at approximately 40% NH. (13) Check ITT/T6 starts to increase within ten seconds after selecting condition lever to START.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. (12) Either: (a) If ITT/T6 is less than 200°C (392°F) 1 Advance condition lever to FEATHER on passing 10% NH. ALLOW A 30 SECOND FUEL DRAIN PERIOD. If reading is not within limits. The pressure oil check valve must be calibrated on a test bench. remove and recalibrate pressure oil check valve. (14) Engine oil pressure .ADJUSTMENT/TEST Page 506 Jul 13/2001 .) IF OIL PRESSURE IS LESS THAN 40 PSI. CAUTION: AFTER AN ABORTED START. Ensure that oil pressure is observed during this run. CAUTION: IF FOR ANY REASON THE START IS ABORTED BEFORE FUEL ON. 501) 72-00-00 ENGINE . During rundown.OFF. Oil Pressure (1) Run engine at 80% NH and.(Ref. Procedure (1) Retard power lever to GRD IDLE.OFF. Check NH approximately 75% and NP 70. (20) After engine stabilizes at IDLE for 3 minutes. (18) Ensure engine accelerates normally to 66 ± 2% NH.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. IF FIRE PERSISTS. (6) Fuel boost pump .ADJUSTMENT/TEST Page 507 Mar 01/2002 . Servicing).8 ± 8% (850 ± 10 rpm). Fig. SWITCH IGNITION OFF AND DRY MOTOR ENGINE FOR 15 SECONDS. (21) Operate engine at ground idle until the oil temperature exceeds 0°C (32°F). (8) Electrical power supply . (3) Select Air Bleed . CAUTION: IF EVIDENCE OF FIRE EXISTS AFTER SHUTDOWN. 10. (2) Oil Pressure Adjustment (Ref.CLOSED. (7) Fuel supply valve .NH 66 ± 2%. 3045542 9. (2) Retard condition lever to FEATHER . This allows even dissipation of heat from turbine area and return of scavenge oil to the tank. INDICATED BY SUSTAINED INTERTURBINE TEMPERATURE (ITT/T6).OFF. check oil pressure is 55 to 65 psid. (4) Run engine for a minimum 30 seconds (following operation in forward mode) or 1 minute (following operation in reverse mode). (19) Ensure ENG OIL PRESS caution goes out. (9) Check oil level. (5) Retard condition lever to OFF. Check that propeller goes into feather. check compressors decelerate freely with no unusual noise and oil pressure decreases suddenly between 25% and 35% NH. when oil temperature reaches 70 to 90°C (160-194°F). select Air Bleed ON if required. Checks A. CONTINUE MOTORING ENGINE. Shutdown A. FI.FLT IDLE. (2) Check NH .in. NOTE: Number of spacers can vary between one minimum and six maximum. and MAX NP Governing (1) PLA .8 % (850 ± 10) rpm and NH is approximately 74%.66 ± 2%. E. ADJUSTMENT/TEST.FEATHER. ADJUSTMENT/TEST). (d) Install cover.in. bracket (2). (3. CLA . Ground IDLE . (3) Advance CLA .OFF. Leak Check (1) C. packing (4). F.FLT IDLE. 72-01-40. (a) Remove bolts (1). CLA .ATO. B. Discard packing. Torque bolts 32 to 36 lb. REVERSE/MIN.ADJUSTMENT/TEST Page 508 Mar 01/2002 .62-4. Air Bleed . Carry out leak check (Ref.NH GOVERNING (1) PLA .GI.OFF. (e) Run engine at 80% NH and. (b) Add spacer(s) (5) to increase or remove spacer(s) (5) to decrease oil pressure.74 ± 2%. CLA . (c) Lubricate packing (4) and install on cover (3).TO or FLIGHT. 72-00-00 ENGINE .PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO.8 ± . 72-01-50.OFF. and washer (6) using puller (PWC37651). when oil temperature reaches 70 to 90°C (160-194°F). Flight IDLE . (2) Engine rating selector . (4) Check propeller unfeathers.FEATHER.NH GOVERNING (1) PLA . Flight IDLE/MIN NP GOVERNING (1) Engine air-bleed OFF and PLA . NP increases to 70. D.UNFEATHER. cover (3).07 Nm) and secure with lockwire (PWC05-089) or (PWC05-295). (2) Check NH . (2) Engine rating selector . washer (6) and bolts (1).UNFEATHER position and Air Bleed . bracket (2). 3045542 WARNING: COVER RESTRAINS SPRING. check oil pressure is 55 to 65 lb. Air Bleed . ON.7 ± 0. (3) Change EEC MODE to MANUAL MODE.REVERSE. (6) Release No.O. CLA .UNFEATHER.8% (1100 ± 10 rpm). 2 AUTOFEATHER TEST switches on TEST. Check NH stabilizes at 77. (3) Check: MAX GOV at 1200 ± 10 NP. 72-00-00 ENGINE .5 ± 2%. 1 and No.OFF and EEC MODE .9 ± 2%. (4) Hold No.UNFEATHER and engine Air Bleed .ON. G. Autofeather and Uptrim (both engines running) (1) PLA . (4) Check: EEC reverts to MANUAL and NH stabilizes at 77.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. EEC Manual Reversion (1) PLA . I. Minimum NH 66%. (2) Record torque.FEATHER . select EEC MODE . (6) Advance PLA to FLT IDLE.P or ITT/T6 Limit) (1) PLA . Check NH stabilizes at 75. (8) Check: EEC changes to ON and NH returns to 74 ± 2%. CLA . H.ON.FLT IDLE. engine Air Bleed . (b) NH varies as propeller blade angles change due to BETA schedule.ADJUSTMENT/TEST Page 509 Mar 01/2002 . 3045542 (3) Retard PLA . Maximum Forward Governing (T. (2) Advance PLA until NP stabilizes (NP governing).9 ± 2%. (7) When conditions in step (6) are satisfied. CHAPTER 05-10-00). NH and propeller speed (both engines).OFF. (2) Check NH . (5) Check Autofeather ready message is displayed and both torque indicators show 55% minimum. CAUTION: DO NOT EXCEED TORQUE AND ITT/T6 LIMITS (REF. 2 TEST switch to TEST.FLT IDLE and CLA .FLT IDLE. (4) Check: (a) NP stabilizes at 91. (5) Retard PLA to GD IDLE.74 ± 2%. 1 AUTOFEATHER TEST switch while keeping No. (3) Select AUTOFEATHER . Adjustment Figure 501 72-00-00 ENGINE . 3045542 3 2 4 5 1 6 C12163A Oil Pressure .PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO.ADJUSTMENT/TEST Page 510 Jul 13/2001 . 2 AUTOFEATHER TEST switches on TEST. (11) Check Autofeather ready message comes on and both torque indicators show 55% minimum. No. 2 auxiliary feathering pump operation message is displayed. Autofeather ready message goes out and No. 3045542 Key to Figure 501 1. 4. torque and propeller speed return to the values recorded in step (2)). 2 ENGINE UPTRIMS . 1 engine UPTRIMS . (8) Release No. 2 AUTOFEATHER TEST switch. 3. (c) After approximately 2 seconds. 1 auxiliary feathering pump operation message is displayed. 2 AUTOFEATHER TEST switch while keeping No. (c) After approximately 2 seconds. 2 engine NH and torque return to the values recorded in step (2). 1 propeller unfeathers. 6.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. (b) No. 2. Autofeather ready message goes out and No. 1 propeller feathers and propeller speed decreases. (10) Hold No. (7) Bolt Bracket Cover Packing Spacer Washer Check: (a) No. 1 torque returns to value recorded in step (2).Record NH which should be the same or show a slight increase from value recorded in step (2). 1 TEST switch to TEST. 1 and No. (12) Release No. (d) No. (c) No.ADJUSTMENT/TEST Page 511 Mar 01/2002 . 2 torque returns to value recorded in step (2). 5. (b) PWR UPTRIM message comes on and on No. (13) Check: (a) No. 1 engine stabilizes at FLT IDLE (NH.record NH which should be the same or show a slight increase from value recorded in step (2). (b) PWR UPTRIM message comes on. (9) Check: (a) UPTRIM message goes out and No. 72-00-00 ENGINE . 506) values. (17) Check Autofeather ready message comes on. 502). v Do not use corrected barometric pressure as supplied by the tower. (18) Retard PLAs . Fig.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. (20) Select AUTO-FEATHER . 1 engine NH and torque return to the values recorded in step (2).FLT IDLE. NOTE: 2. (19) Check Autofeather ready message goes off. J. (4) Start engine (Ref. NL (Ref. (15) Check: (a) UPTRIM message goes off and No.ADJUSTMENT/TEST Page 512 Mar 01/2002 . torque and propeller speed return to the values recorded in step (2). AMM).OFF. (3) Determine and record maximum NH (Ref. 505) and WF (Ref. (2) Determine and record target torque (Ref. 503). Fig. ITT/T6 (Ref. 504). 2 propeller feathers and propeller speed decreases. but only about their overall performance. at any atmospheric condition in the operating envelope. v Altimeter reading is the actual Pressure Altitude around aircraft. 2 propeller unfeathers. Fig. All power assurance charts include an allowance for installation losses. (b) No.92 Hg) or (1013 Mbars). 3045542 (d) No. is to provide assurance that the engine will deliver power specified by the manufacturer. (14) Release No. (16) Advance PLA (both engines) until 70% torque is obtained. (c) No. Power Assurance Check NOTE: 1. (1) Record outside air temperature (OAT) and pressure altitude. Fig. 72-00-00 ENGINE . 2 engine stabilizes at FLT IDLE (NH. Fig. NOTE: The correct pressure altitude may be obtained as follows: v Set altimeter calibration window to standard barometric pressure (29. The main objective of the Power Assurance Check. The Power Assurance Test will not provide information about the condition of engine components. 1 AUTOFEATHER Test Switch. 72-00-00 ENGINE .PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO.ADJUSTMENT/TEST Page 512A/512B Jul 13/2001 . 3045542 (5) Move condition lever to MAX RPM position and check NP is 100%. . 2%/ −0. (7) Record NH. IF TARGET POWER CAN NOT BE ACHIEVED WITHIN MAXIMUM RATED TORQUE BECAUSE NP IS TOO LOW. 05-10-00). NL (± 0. Recommended Minimum Relative Margins at Power Assurance following an HSI NH NL ITT/T6 3. 72-00-00 ENGINE .3%) and ITT/T6 (± 8°C). perform another power assurance check within one (1) week. NL and ITT/T6 margins enable hot sections to complete an average life for an operator’s fleet. it is normal that the engine parameters (NH. AMM). NL. revise target torque. ITT/T6) may differ from the numbers derived from the test cell performance test sheet. ITT/T6 and WF. depending on operating conditions (environment and type of operation). FIND AND RECTIFY THE CAUSE OF LOW NP. (8) Shut down engine (Ref. step (2)). When performing a Power Assurance Check after installation.ADJUSTMENT/TEST Page 513 Mar 01/2002 .5%). (b) Power assurance check after hot section inspection (HSI) NOTE: 1 Adequate NH. the recommended minimum NH. (6) Move power lever until target torque is reached (Ref. (9) Check OAT and pressure altitude is same as that recorded in step (1). Ensure air bleed is closed.0% 30°C NOTE: When an engine is installed in an airframe after a shop visit. 2 If NH is within 0. using the corrected target torque. NL and ITT/T6 margins relative to the applicable chart is as indicated in Table 502: TABLE 502. (10) Check engine parameters as follows: (a) Normal power assurance check 1 If ITT/T6 is within 5°C of the limit. the following parameter changes relative to test cell parameters are typical: (NH (+ 0. NOTE: If NP is not 100%. If a Post-HSI power assurance has been carried out. NL. on the lower side perform another power assurance check within one (1) week.25% of the limit. on the lower side. 3045542 CAUTION: DO NOT EXCEED MAXIMUM RATED TORQUE (REF.2% 3. using the following formula: Corrected target torque = target torque x 100% NP Actual NP Repeat step (6). This life will differ from operator to operator. Stabilize for three minutes.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. (b) NL (%) (Ref. fuel flow serves as an indicator. NL. However. ITT) should be investigated. 72-00-00 ENGINE . (2) Determine and record target torque (Ref. Performance Deterioration (ECTM or High ITT (T6)). (8) Move power lever slowly until torque value equivalent to 95% of target torque is obtained (Ref. NOTE: K.ADJUSTMENT/TEST Page 514 Jan 16/2004 .PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. and the accuracy of the readings for other parameters (NH. step (3)). check instrumentation for each engine parameter (Ref.Approved Repair). AMM) and. (6) Move power lever until Flight Idle speed is obtained. AMM). or If within power assurance limits. rpm position. (9) Record NH and PLA position. 502). The engine is still serviceable if fuel flow (Wf) is over the limit and all other parameters are within limits. ITT/T6 and Wf recorded at step (7) are above maximum values recorded at step (3) or the margins are less then the minimum shown in step (10) (b) 1. Excessive Fuel Consumption). 72-03-00 . operate the engine and accept the reduced hot section life. (10) Move power lever to Flight Idle. Fig. (4) Start engine (Ref. 3045542 2 If the NH. (11) If NH. High Temperature). (3) Determine and record torque value equivalent to 95% of target torque recorded in step (2). NL and ITT/T6 margins recommended after HSI are not met. Operators can either: Remove and rematch the engine (Ref. (7) Select manual mode. (5) Move condition lever to MAX. (c) ITT (°C) (Ref. NL. refer to Fault Isolation: (a) NH (Ref. Acceleration Check (1) Record outside air temperature (OAT) and pressure altitude. hot section life will be affected. Performance Deterioration (ECTM or High ITT (T6)). if required. (d) Wf (Ref. −50. 50. 7000.ADJUSTMENT/TEST Page 515/516 Mar 09/2001 40. 70. TORQUE (%) 100. 9000. 5000. 3000. MAINTENANCE MANUAL MANUAL PART NO. 80.PRATT & WHITNEY CANADA 11000. −40. −20. 60. C66998 Power Assurance Check . 20. −30.Torque Figure 502 72-00-00 ENGINE . 10. 40. OAT ( o C) 0. 3045542 . 1000 −1000 ALT (FT) 50. 90. −10. 30. . −50. 30. 10. 11000. OAT ( o C) 0. 100.ADJUSTMENT/TEST Page 517/518 Mar 09/2001 −1000 94. 7000. −20. 1000 3000. −30. 104. ALT (FT) −40. 3045542 .NH (%) Figure 503 72-00-00 ENGINE . 50. 9000. 20.PRATT & WHITNEY CANADA C67000 Power Assurance Check . NH (%) 106. 102. 40. 96. MAINTENANCE MANUAL MANUAL PART NO. 98. 5000. −10. . PRATT & WHITNEY CANADA Power Assurance Check . C67001 ENGINE . 40. 20. −10. 5000 7000 9000 102. 104. 94. OAT ( o C) 0.ADJUSTMENT/TEST 1000 3000 98. MAINTENANCE MANUAL MANUAL PART NO. 30.NL (%) Figure 504 72-00-00 Page 519/520 Mar 09/2001 −1000 −40. 50. 96. 10. 100. −50. 3045542 . −20. 11000 NL (%) 106. ALT (FT) −30. . 40. 740.ADJUSTMENT/TEST Page 521/522 Mar 09/2001 600. 20. 1000 3000.ITT/T6 (°C) Figure 505 72-00-00 ENGINE . −10. 660. 11000. 9000. 5000. 720. −30.PRATT & WHITNEY CANADA C67002 Power Assurance Check . 3045542 . 9000. 50. 780. 700. INTERTURBINE TEMPERATURE (ITT/T6)( o C) ALT (FT) −40. −50. OAT ( o C) 0. 10. −1000 620. 30. 640. 760. 7000. 680. MAINTENANCE MANUAL MANUAL PART NO. 800. −20. 11000. . 1250.ADJUSTMENT/TEST Page 523/524 Mar 09/2001 750. 1350. OAT ( o C) 0.Fuel Flow (Wf) Figure 506 72-00-00 ENGINE . 30. 3045542 . MAINTENANCE MANUAL MANUAL PART NO. 20. −20. 40. 10. 1150. −30.PRATT & WHITNEY CANADA C67003 Power Assurance Check . 11000 9000 7000 5000 3000 1000 −1000 ALT (FT) 50. 950. −40. 850. −50. −10. 1050. FUEL FLOW (WF)(PPH) 1450. . ADJUSTMENT/TEST Page 525 Jan 16/2004 . (12) Record time taken by the engine to accelerate from Flight Idle to the NH speed recorded in Step (9). 3045542 (11) Perform a slam acceleration by moving power lever within one second from Flight Idle to PLA position recorded in step (9). switch on EEC and shutdown engine (Ref. 72-00-00 ENGINE . the MFC is serviceable. replace the MFC. (16) If acceleration time is above the limit shown in Figure 507.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. (13) Retard power lever to Flight Idle. and all other troubleshooting procedures do not cure the problem. (15) If engine acceleration time is below that shown in Figure 507. AMM). (14) Compare engine acceleration time recorded in step (12) to that shown in Figure 507 for an equivalent temperature. 0 8 SECOND LIMIT 8.0 3. 3045542 10.0 6.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO.0 1.0 4.ADJUSTMENT/TEST Page 526 Mar 09/2001 .0 7.0 9.0 −30 −20 −10 0 10 TEMPERATURE ( o C) 20 30 40 C31805A Acceleration .0 TIME (SEC’S) 5.Time Limits Figure 507 72-00-00 ENGINE .0 2. equipment and supplier tools listed below are referred to in procedural text. NOTE: 2. Abrasive. WARNING: READ THE MATERIAL SAFETY DATA SHEETS BEFORE YOU USE THESE MATERIALS. Consumable Materials The consumable materials listed below are referred to in this section. Abrasive.8 lens and a 1-9 focusing screen) Puller PWC37651 4. Crocus) Stone. refer to the CONSUMABLE MATERIALS section at the beginning of this manual. General A. Name PWC30128-15 PWC34910-101 PWC34910-800 PWC34910-802 PWC34910-804 PWC34913 PWC34939 PWC34960-201 Puller Borescope Assembly Guide Tube Guide Tube Guide Tube Holding Fixture Pusher Camera (optional) (Consists of an Olympus OM-2 Camera incorporating a 50 mm f:1. Flexible Cloth. unless stated otherwise. Use engine oil (PWC03-001) for general lubrication. Engine Lens Cleaner Lens Tissue Cloth.INSPECTION/CHECK 1. Name Fiberscope FBA 4-90T 72-00-00 ENGINE . unscheduled and borescope inspections. hot section component. Fixtures. 3045542 ENGINE .INSPECTION/CHECK Page 601 Jan 24/2006 . For more data. The instructions in this section outline details necessary to perform routine. (Coated. SOME MATERIALS CAN BE DANGEROUS. Equipment and Supplier Tools The fixtures. Abrasive (320 grit) PWC05-100 PWC05-101 3. Tool No. Name PWC03-001 PWC05-042 PWC05-043 PWC05-061 Oil. Special Tools Special tools are identified in procedural text by part number in parentheses.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. Item No. ) The local airworthiness authority must be informed of the P&WC recommendation. damaged impellers) may be returned to service providing the prior approval and substantiation data is obtained from the P&WC Design Approval Appointee (DAA). Longueuil. 6. Rotor Components . 1000 Marie Victorin Blvd.5 mm) Swiss File 5. Engines with Defects Outside Specified Limits Engines with defects outside specified limits (e. 7. The number of cycles at which the affected components must be replaced is specified in AIRWORTHINESS LIMITATIONS.Service Life Certain rotating components are subject to low cycle fatigue due to cyclic operation of the engine. SCHEDULED INSPECTION/MAINTENANCE INTERVALS). Operators must supply all relevant details of the defect to: Pratt & Whitney Canada Corp. (Copies of the substantiation documentation will be supplied to Transport Canada. 3045542 Name Magnet Square-drive Socket Extension.INSPECTION/CHECK Page 602 Jan 24/2006 . 3/8 in.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. Periodic Inspection Refer to (Chapter 05-20-00.g. (9. Quebec Canada J4G 1A1 Attention: Customer Support Customer Help Desk (24-hour service) US and Canada: 1-800-268-8000 International: (IAC)-8000-268-8000 Other: 1-450-647-8000 Fax: 1-450-647-2888 72-00-00 ENGINE . 76 mm) minimum (Ref. Low Pressure and High Pressure Impellers .Foreign Object Damage A. View D). to determine the source of damage and whether the intake bypass system has been operated correctly. Inspection of the LP impeller may be carried out by a qualified technician using a suitable light source and viewing the impeller through the air intake duct. 72-00-00 ENGINE . providing the blends conform with the following requirements: 1 When the distance between the blended area and vane tip is less than 2 times depth. Precautions must be taken to ensure further damage does not occur. 4 Radius at the edges of a blend must be 0.) is optional. Detail F).INSPECTION/CHECK Page 603 Jan 24/2006 . when damaged impellers are found.81 mm). blend up to tip (Ref. An investigation must be carried out. 3 In Area Cc. NOTE: 1. Use of a borescope (Ref. LP Impeller (1) Visually inspect impeller for dents and nicks (Ref.cut triangularly (Ref. 601 and Table 601). (2) Tools and Materials Required v Swiss file v Abrasive cloth (PWC05-101) v Crocus cloth (PWC05-061) v Abrasive stone (PWC05-100) (3) Blending Procedure CAUTION: INSPECT HP IMPELLER BEFORE REWORKING DAMAGED LP IMPELLER TO DETERMINE IF ENGINE REPLACEMENT IS REQUIRED. 9. NOTE: 2. 2 Leading edge tip damage . Para. If any FOD has caused the engine to become prone to engine surges or causes unusual compressor whining. Fig.15 in. CAUTION: DO NOT USE POWER TOOLS.03 in. (3. NOTE: 3. View E). (0. 3045542 8. except in Area Cc where only one blend is allowed.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. (a) The length and number of blends per vane are not restricted. NOTE: 4. the engine must be removed immediately. P&WC recommends inspection of the HP impeller when a damaged LP impeller is found. the minimum blend radius is 0. the minimum blend Length G must be at least 2 times Depth H. The recommended length is 3 times Depth H (Ref. 72-00-00 ENGINE . Detail F).INSPECTION/CHECK Page 604 Jan 24/2006 . 3045542 5 In Areas Ca and Cb.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. MAX (6.76 mm.35 mm) D Cb 1 IN.4 mm) 0.030 IN.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO.030 IN.35 mm) VIEW D A E 0.Inspection (Full and Splitter Vanes) Figure 601 (Sheet 1 of 3) 72-00-00 ENGINE . MIN (0. (3. (3. .) . MIN (0.125 IN.030 IN. MIN (0.) Cb 0.17 mm) 0.) C−C VIEW E C30221B LP Impeller .INSPECTION/CHECK Page 605 Jan 24/2006 .76 mm.76 mm. MAX (6.150 IN.) (ONLY) 0.81 mm) MINIMUM RADIUS ACCEPTABLE NOT ACCEPTABLE AREA Cc & H − BLEND LIMITS A C 0.76 mm.250 IN. MIN (0.250 IN. 3045542 C E A 0. (25.030 IN. AS REQUIRED (AREA Cb ONLY) E Ca Cc SECTION H 0. 76 mm) G H1 K H H2 0.76 mm) ACCEPTABLE DISTANCE BETWEEN ADJACENT BLENDS BLEND SHAPE DETAIL K F DETAIL J H1 H2 MERGED BLENDS ACCEPTABLE DISTANCE BETWEEN ADJACENT BLENDS NOT ACCEPTABLE DETAIL J AREA Ca & Cb − BLEND LIMITS C33529 LP Impeller .INSPECTION/CHECK Page 606 Jan 24/2006 .030 IN (MIN) (0.Inspection (Full and Splitter Vanes) Figure 601 (Sheet 2) 72-00-00 ENGINE . 3045542 0.030 IN (MIN) (0.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. Bent Damage (Typical) C100507 LP Impeller .INSPECTION/CHECK Page 607 Jan 24/2006 . 3045542 Airfoil Tip .PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO.Inspection (Full and Splitter Vanes) Figure 601 (Sheet 3) 72-00-00 ENGINE . 52 mm) long. (3. are serviceable. Notes 2 and 3). Blend repair nicks or dents more than 0. (0. (Ref.76 mm) deep Max.05 mm) deep.52 mm) long Max. are serviceable. (6.060 in. (0.125 in.60 mm) deep and 0. Notes 2 and 3). (0.040 in. 72-00-00 ENGINE .52 mm) long Max. (0.063 in. and 0. (25. Notes 2 and 3). (0. to a maximum depth of 0.35 mm).52 mm) long.76 mm) deep and 0.76 mm) deep Max.063 in. (5.250 in.030 in.15 mm) and 0. (0.060 in.125 in. (0.003 in.002 in. Blend repair nicks or dents more than 0. (0.030 in.10 mm) deep. (0.025 in.200 in.10 mm).030 in.060 in.. to a maximum depth 0.17 mm) long Max.10 mm) deep Max. (1. are serviceable. (0. (1.52 mm) long. H Root radius (away from leading edge) Nicks or dents 0.63 mm) long. and 0.25 mm) long.52 mm) long Max. (3.INSPECTION/CHECK Page 608 Jan 24/2006 .004 in. and 0. (Ref.060 in.60 mm) deep Max. and 0.76 mm) deep Max. are serviceable.17 mm).76 mm) deep and 0. (1.010 in.4 mm) from root radius) Nicks or dents 0. 3045542 TABLE 601.060 in.060 in.030 in.76 mm) deep and 0. Replace the impeller if nicks or dents are more than 0. (1. (Ref. (0.0 in. Nicks or dents 0. to a maximum depth 0. (0. E Vane sides (suction/pressure) Nicks or dents 0. (0. Cb Outer leading edge and blade tip (extends from Ca to vane tip) Cc Leading edge root radius (at leading edge) A Vane tip Nicks or dents 0. Blend repair nicks or dents 0.004 in. Notes 2 and 3).006 in. Notes 2 and 3). to a maximum depth 0. Blend repair nicks or dents more than 0.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. (1. (0. (Ref.002 in. (1. are serviceable.07 mm) and 0. to a maximum depth 0.030 in. Blend repair nicks or dents more than 0. (1. (Ref.05 mm) deep Max. (1.030 in. Replace the impeller if nicks or dents are more than 0. LP Impeller Inspection (Full and Splitter Vanes) Area Area Name Inspection Limits Ca Inner Leading Edge (extends 1. INSPECTION/CHECK Page 609 Jan 24/2006 . 6 When the distance between the deepest points in two adjacent blended areas is less than 3 times depth (H2) of the deepest blend. Nicks or dents must be blended if raised material or tears are present.070-0. Para.) to do a visual inspection of the impeller for dents. HP Impeller (1) Use a borescope (Ref. A dent is surface damage without sharp edges. (2) With the borescope findings. every routine periodic inspection for the presence of or beginning of a crack. 602). NOTE: 3. length x depth / 2). 9 No tool marks or grooves are permitted after rework. the opposite vane must be reworked to incorporate blended area(s) having similar shape(s) and position(s). Cracks are not acceptable. The periodic inspection interval must not exceed 1250 hours. NOTE: 2. 7 Rework along and parallel to leading edge.045 sq. when finish blending. tears and/or cracks (Ref.032 sq. use Table 602 to identify the necessary actions based on the type and location of damage 72-00-00 ENGINE . 3045542 NOTE: 1. NOTE: For triangular cuts.015 in. by visual inspection or by using a borescope. (29. 8 Break sharp edges 0.380 mm) after rework. Fig. A nick is surface damage with sharp edges. 10 Round bottom of blend. (0. after rework. mm). 9. Detail J). Note). multiply depth of the blended area(s) with the length(s) (Ref. nicks.e. If the result is more than 0.003 to 0.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. (i. Serviceable and blend repaired nicks or dents must be monitored. in. multiply length by depth and divide by 2. 11 To ensure the amount of rotor unbalance is minimized. the blends should be merged (Ref. B. 900 in. (66. 1.Inspection (Full and Splitter Vanes) Figure 602 72-00-00 ENGINE . 0.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO.125 in. (40. 0. (22. 2.05 mm) SPLITTER BLADES 0.86 mm) Ref.INSPECTION/CHECK Page 610 Jan 24/2006 . (3.17 mm) Ref.86 mm) Ref. (3.17 mm) Ref. 3045542 A A C Cc AREA Cc C A FULL BLADES 0.125 in.600 in.900 in.600 in.64 mm) C12555B HP Impeller . (22. 03 mm) in size.040 to 0.7 mm) in length. (0. A tear between 0. A dent less than 0.05-7.02 mm) in size.020 in. No action required. No action required.080 in. (3. refer to Category 1.120 in. (12.020 to 0.300 in. A nick more than 0.500 in. (12.INSPECTION/CHECK Page 611 Jan 24/2006 . refer to Category 1.05 mm) in size. (1. (7. refer to Category 1. 603) Nick (Ref.05-7. HP Impeller Inspection (Full and Splitter Vanes) (Ref.51-3.51-1. at leading edge) A dent less than 0. A dent more than 0. 604) (Ref. Fig. A tear between 0.51 mm) in size is serviceable. 602) TYPE OF DAMAGE Dent (Ref.51 mm) in size is serviceable. (0.62 mm) in size.03 mm) in size.300 in.300 in. A tear between 0. refer to Category 3.080 in. Fig. 3045542 TABLE 602. (2.51 mm) in size is serviceable.020 in.7 mm) in length that extends into Area Cc. A dent more than 0.62 mm) in size. (0.02-2.51-3. (3. (0. A nick less than 0. refer to Category 1. 72-00-00 ENGINE .020 to 0.51-1. No action required.020 to 0. 605) (Ref.020 in. (12. refer to Category 2. extends from root radius) AREA Cc (Root radius. refer to Category 3. A tear more than 0. Fig. (1. No action required. refer to Category 1.040 to 0. A nick more than 0.080 in. (0. A tear less than 0.03 mm) in size.7 mm) in length that is mostly included or partially extends into Area Cc is serviceable. (0. A tear between 0. refer to Category 2.02-2.7 mm) in length is serviceable. (0.62 mm) in size.51 mm) in size is serviceable.05 mm) in size.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO.500 in.02 mm) in size. A nick between 0. refer to Category 3. (7.120 to 0.080 in.62 mm) in size. (12.500 in.120 in. A nick less than 0. A tear less than 0. A nick between 0. Fig. NOTE 1) Tear (Ref. A nick between 0. (2.500 in.040 in.020 to 0.03 mm) in size.020 in. refer to Category 2. refer to Category 3. refer to Category 1. (0.120 to 0. A nick between 0. No action required.300 in. No action required.040 in. NOTE 1) AREA A (Vane tip) or Area C (Leading edge. refer to Category 2 A tear more than 0. either length or depth. the engine must be scheduled for removal in less than 10 hours. Do a subsequent borescope inspection after 100 hours. up to a maximum of 1000 cycles. refer to Category 3. 72-00-00 ENGINE . Do a subsequent borescope inspection at intervals not to exceed 200 hours.120 in.62 mm) in size. refer to Category 3.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. Category 2: Record the size and type of damage found. (0. the engine must be removed immediately. or if material is missing since the last inspection.05 mm) in size. characterizing the damage. NOTE: 2. Category 3: The engine must be scheduled for removal in less than 10 hours. (0. NOTE: 1.020 to 0. refer to Category 1. A crack between 0. no more action is required. If any crack is seen to grow in size or propagate from the damaged area. (3. at leading edge) Any crack in this Area. tear or crack and is defined as the greater dimension. HP Impeller Inspection (Full and Splitter Vanes) (Ref.120 to 0. extends from root radius) TYPE OF DAMAGE Crack (Ref. The term ‘‘Size’’. No action required. is used for a nick. If any crack is seen to grow in size or propagate from the damaged area. Fig. A crack more than 0. NOTE 1) A crack less than 0.INSPECTION/CHECK Page 612 Jan 24/2006 . refer to Category 2.62 mm) in size. after which the engine must be removed. the engine must be scheduled for removal in less than 10 hours.51 mm) in size is serviceable.300 in.300 in. but not later then 200 hours.05-7. A crack between 0. or if material is missing since the last inspection. Category 1: Record the size and type of damage found.020 in.51-3. If the subsequent inspection reveals no change in the condition of the damage from the initial inspection. 3045542 TABLE 602. (7. AREA Cc (Root radius. 602) (Cont’d) AREA A (Vane tip) or Area C (Leading edge. If any FOD has caused the engine to become prone to engine surges or causes unusual compressor whining. INSPECTION/CHECK Page 613 Jan 24/2006 .Example of a Dent Figure 603 72-00-00 ENGINE .PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3045542 DENT LENGTH C76645 HP Impeller . PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO.Example of a Nick Figure 604 72-00-00 ENGINE . 3045542 C76646 HP Impeller .INSPECTION/CHECK Page 614 Jan 24/2006 . INSPECTION/CHECK Page 615 Jan 24/2006 .Example of a Tear Figure 605 72-00-00 ENGINE . 3045542 C76647 HP Impeller .PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. Borescope Inspection A. Side-viewing Adapter (Ref.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 72-00-00 ENGINE . (2) Installation (a) Hold the fiberscope as closely as possible to the distal end and remove the protective ring. SHOCK. 3045542 9. a camera (PWC34960-201) may be used to photograph the engine areas being inspected. 606) (1) The side-viewing adapter is used to inspect components located at a nominal 90-degree angle to the fiberscope distal tip. THE NORMAL COOLING PERIOD IS 40 MINUTES AFTER ENGINE SHUTDOWN.INSPECTION/CHECK Page 616 Jan 24/2006 . THE ADAPTER COULD FALL INTO THE ENGINE. DO NOT ROTATE FIBERSCOPE TIP BY TURNING THE EYEPIECE ONLY. If required. (3) Removal (a) Hold the fiberscope as close as possible to the distal end and remove the side-viewing adapter. ASSIST ROTATING MOTION OF EYEPIECE WITH ONE IN SAME DIRECTION AT PART OF FIBERSCOPE CLOSEST TO ENTRY INTO ENGINE. EXTREME CARE IS REQUIRED DURING HANDLING TO ENSURE DAMAGE AND SERVICEABILITY PROBLEMS ARE AVOIDED. (b) Hold the fiberscope as close as possible to the distal end. ENGINE TEMPERATURE MUST BE LESS THAN 66°C (150°F) BEFORE AN INSPECTION CAN BE CARRIED OUT. NOTE: B. CARRY OUT DRY MOTORING RUNS TO ACCELERATE COOLING (Ref. CAUTION: DO NOT SUBMERGE IN LIQUID. (1) The borescope is used to inspect the inside of the engine. OVERTIGHTENING THE ADAPTER COULD DAMAGE THE DISTAL END. CAUTION: INSTALL THE SIDE-VIEWING ADAPTER CAREFULLY. AMM). Access is through ports or openings created by the removal of components. IF NOT INSTALLED AND TIGHTENED CORRECTLY. CAUTION: EXCESSIVE TWISTING OF FIBERSCOPE CAN SEVER OPTIC FIBERS. A ring is installed to protect the distal end when the side-viewing adapter is not fitted. Install the adapter. CAUTION: HEAT CAN DAMAGE THE BORESCOPE. TWISTING AND PINCHING. General CAUTION: THE BORESCOPE IS FRAGILE AND VULNERABLE TO RADIATION. IF REQUIRED. ensuring the indexing slot and lug are aligned. Torque the adapter fingertight. Fig. 50-cycle power supply. OVERTIGHTENING THE RING COULD DAMAGE THE DISTAL END. (1) A halogen lamp is used to provide lighting from either a 110V. (b) Install the focusing screen in the camera. 60-cycle or a 220V. (3) Set intensity knob at maximum for best results. focusing screen and 50 mm lens with lens cleaning tissue (PWC05-043) and lens cleaner (PWC05-042). BORESCOPE OR ASSOCIATED EQUIPMENT. (h) Align the bayonet slots of the adapter and install the camera on the borescope eyepiece pins.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. (c) Install the 50 mm lens. Torque the ring fingertight. camera handbook).8 lens. THE RING COULD FALL INTO THE ENGINE. (f) Set the camera film speed to suit the film and the exposure compensation to -2 (Ref. Light Source NOTE: D. (i) Turn the outer ring of the adapter to lock the camera on the borescope. Camera (1) General (a) The camera (PWC34960-201) is used with the borescope to photograph internal engine components. C. (a) Clean the camera viewfinder. Specify power requirements when purchasing borescope. 3045542 CAUTION: INSTALL THE PROTECTIVE RING CAREFULLY. 72-00-00 ENGINE . (g) Release the knurled screw on the outer ring of the camera adapter and align the bayonet slots with those on the inner ring. (b) Hold the fiberscope as close as possible to the distal end and install the protective ring. (4) Before installing light source. (e) Load the camera with film (Ref.INSPECTION/CHECK Page 617 Jan 24/2006 . (2) Installation CAUTION: DO NOT USE COMPRESSED AIR TO CLEAN THE CAMERA. (d) Install the camera adapter on the lens. (2) Remove the top cover from the light source to replace the lamp. camera handbook). IF NOT INSTALLED AND TIGHTENED CORRECTLY. refer to manufacturer’s instructions. It must be equipped with a 50 mm f: 1. 3045542 BORESCOPE DISTAL END PROTECTIVE RING DIRECTION OF ROTATION FOR RING REMOVAL RING REMOVAL PRISM BODY INDEXING LUG INDEXING SLOT BORESCOPE DISTAL END SIDE VIEWING ADAPTER THREADED RING DIRECTION OF ROTATION FOR RING REMOVAL ADAPTER INSTALLATION C12191 Side-viewing Adapter .INSPECTION/CHECK Page 618 Jan 24/2006 .Removal/Installation Figure 606 72-00-00 ENGINE .PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. NOTE: (3) Make sure the distal end is not moved when taking photographs. hold the eyepiece and turn the camera. v Date and area or component photographed. (b) Turn the outer ring of the camera adapter to align the bayonet slots and remove the camera from the eyepiece. Guide Tubes (1) General (a) Guide tubes are used to guide the fiberscope distal end to an intended location inside the engine. F. using a label.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. Removal (a) Release the knurled knob on the camera adapter. problems encountered when using the borescope are shown in Table 603. 72-00-00 ENGINE . and remedies for. etc. (k) To obtain alignment.INSPECTION/CHECK Page 619 Jan 24/2006 .). (2) Guide tube types (a) There are two guide tubes: v Flexible guide tube installed in the T6 thermocouple port. v Rigid guide tube installed in the fuel manifold adapter port. add the following data: v Engine serial number. (3) Installation and removal (a) Installation and removal are covered in the appropriate paragraphs. v Engine operating time or cycles since last overhaul. 3045542 (j) Torque the knurled screw on the adapter fingertight. Camera Handbook) and remove the film from the camera and. v Reason for borescope inspection (suspected foreign object damage. Troubleshooting (1) The possible sources of. (d) Rewind film (Ref. E. (c) Remove the camera adapter from the lens. low power. Light source intensity switch set at low Set switch at high. Damaged fibers in fiberscope (seen as black dots through viewer) Return to manufacturer for repair. Fig. (2) Inspection Through the Air Intake Duct (Ref. (c) Clamp the borescope eyepiece to the fixture and connect the light source. 3045542 TABLE 603. Diopter ring not adjusted correctly Adjust to suit eyes. AMM). G.INSPECTION/CHECK Page 620 Jan 24/2006 . Low Pressure Impeller (1) General (a) Borescope inspection of the low pressure impeller can be carried out using three different access routes and without the use of a guide tube. Defective lamp in light source Replace lamp. (b) Clamp the holding fixture (PWC34913) to a convenient surface. Defective transformer Return to manufacturer for repair. Borescope Troubleshooting PROBLEM Poor illumination Poor definition Flexible guide tube (PWC34910-802) or fiberscope distal end does not move when control knobs are turned POSSIBLE SOURCE REMEDY Oil or dirt on distal tip or side-viewing adapter prism Clean using lens cleaner (PWC05-042) and lens tissue (PWC05-043). 607) (a) Remove the air intake duct (Ref. Damaged control wires in guide tube or fiberscope Return to manufacturer for repair. Damaged borescope light tube Return to manufacturer for repair. Poor illumination See previous problem.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. NOTE: Repairs should be carried out only by the manufacturer. 72-00-00 ENGINE . PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO.INSPECTION/CHECK Page 621 Jan 24/2006 . 3045542 DIFFUSER EXIT DUCT PORT FIBERSCOPE REAR INLET CASE FRONT INLET CASE DISTAL−END PORT IN THE REAR INLET CASE LP IMPELLER DISTAL−END FIBERSCOPE DIFFUSER EXIT DUCT FLANGE D C32399 LP Impeller .Borescope Inspection Figure 607 72-00-00 ENGINE . cover (3) using puller (PWC37651). 607) 72-00-00 ENGINE . Fig. 607) (a) Remove nut (7. Discard packing. CAUTION: EXTREME CARE MUST BE TAKEN TO ENSURE FOREIGN OBJECTS DO NOT FALL INTO THE OPEN PORTS. 608) and bolt (8).in. Torque bolts 32 to 36 lb.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 8. 72-30-00. (e) Secure the borescope eyepiece to the fixture. Fig.52 Nm). inspect for damage (Ref. or wash nozzle (4) using puller (PWC30128-15) and packing (5). bracket (6) and bolts (1).07 Nm). (4) Inspection Through the Diffuser Exit Duct Port (Ref. (h) Lubricate packing (5) with engine oil (PWC03-001) and install on cover (3) or wash nozzle (4). (f) Inspect the impeller for damage (Ref. (d) Using the fiberscope and rotating the impeller manually. connect the light source and insert the fiberscope into the inspection port. (g) Remove the fiberscope and holding fixture.in. Torque nut 36 to 40 lb. washer (2). (d) Clamp the holding fixture (PWC34913) to a convenient surface. (e) Remove borescope and holding fixture. 72-30-00).62-4. Fig. Inspection Through the Rear Inlet Case Port (Ref. (i) Install cover or wash nozzle. bracket (6). (j) Install bolt (8) and nut (7) to secure clamp holding oil tube to bracket. (b) Remove bolts (1). (4.07-4. NOTE: Rotate the impeller using pusher (PWC34939) through the exit duct port. 3045542 CAUTION: WITHDRAW THE FIBERSCOPE FROM THE VICINITY OF THE IMPELLER BEFORE THE LATTER IS ROTATED. Para. washer (2). 8. (k) Install the diffuser exit duct (Ref. (c) Remove the most accessible diffuser exit duct (Ref. (3. AMM). Para.).INSPECTION/CHECK Page 622 Jan 24/2006 . (f) (3) Install air intake duct (Ref.). CAUTION: WITHDRAW THE FIBERSCOPE FROM THE VICINITY OF THE IMPELLER BEFORE THE LATTER IS ROTATED. Install the diffuser exit duct (Ref. CAUTION: WITHDRAW THE FIBERSCOPE FROM THE VICINITY OF THE IMPELLER BEFORE THE LATTER IS ROTATED. 8.). (c) Secure the borescope eyepiece to the fixture. 72-30-00). 72-30-00). Fuel Pump and Oil Pump Drive Bevel Gears (1) Remove oil pump drive cover (Ref. High Pressure Impeller (1) Remove the starter-generator drive cover (Ref. 72-20-00)) and install a square-drive socket extension. Para. Rotate the impeller using a socket extension installed in the startergenerator driveshaft. remove fiberscope and rotate impeller using pusher (PWC34939). (b) Clamp the holding fixture (PWC34913) to a convenient surface. NOTE: When necessary. (5) Inspect the impeller for damage (Ref.INSPECTION/CHECK Page 623 Jan 24/2006 . (7) Install the diffuser exit duct (Ref. Para. (2) Remove the most accessible diffuser exit duct (Ref. connect the light source and insert the fiberscope into the exit duct port (Ref. 609). NOTE: I. 72-30-00).PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. CAUTION: EXTREME CARE MUST BE TAKEN TO ENSURE FOREIGN OBJECTS DO NOT FALL INTO THE OPEN PORTS. (3) Clamp the holding fixture (PWC34913) to a convenient surface. 72-20-00). (6) Remove the fiberscope and holding fixture. (a) Remove the most accessible diffuser exit duct (Ref. (8) Remove the socket extension and install the starter-generator drive cover (Ref. 72-00-00 ENGINE . (f) H. Fig. connect the light source and insert the fiberscope into the exit duct port. 3045542 CAUTION: EXTREME CARE MUST BE TAKEN TO ENSURE FOREIGN OBJECTS DO NOT FALL INTO THE OPEN PORTS. 72-20-00)). (d) Inspect the impeller for damage (Ref. (4) Secure the borescope eyepiece to the fixture. 8.). 72-30-00). (2) Clamp holding fixture (PWC34913) to a convenient surface. (e) Remove the fiberscope and holding fixture. INSPECTION/CHECK Page 624 Jan 24/2006 .PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO.Removal/Installation Figure 608 72-00-00 ENGINE . 3045542 5 3 1 1 6 2 4 7 8 C12709A LP Impeller Borescope Inspection Port Cover/Nozzle . 8.). Para. 72-30-00).INSPECTION/CHECK Page 625 Jan 24/2006 . (5) Remove all borescope equipment and socket extension. (9. 72-01-60. (9. (5) Remove all borescope equipment and socket extension. (6) Reinstall accessory drive cover (Ref. 72-20-00 for removal of starter-generator drive cover). 6. 72-20-00 for removal of starter-generator drive cover) . Starter-generator Drive Gear (1) Remove NH sensor (Ref. 72-20-00). (3) Secure borescope eyepiece to fixture. 72-20-00). (2) Clamp holding fixture (PWC34913) to a convenient surface. retract fiberscope and rotate gears using a 3⁄8 in. 3. (4) Inspect gear teeth for damage (Ref. 11. Bolt Washer Cover Wash Nozzle Packing Bracket Nut Bolt For viewing and inspecting all teeth. 72-00-00 ENGINE . NOTE: J. connect light source and insert fiberscope into aperture. REMOVAL/INSTALLATION). 11. Para. (2) Clamp holding fixture (PWC34913) to a convenient surface. connect light source and insert fiberscope into aperture. (4) Inspect gear teeth for damage (Ref. 4. 5. 7.5 mm) square-drive socket extension installed on starter-generator driveshaft (Ref. 3045542 Key to Figure 608 1.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. Accessory Drive Bevel Gears (Towershaft) (1) Remove accessory drive cover (Ref. NOTE: K. 72-30-00) and starter-generator drive cover (Ref. For viewing and inspecting all teeth. retract fiberscope and rotate gears using a 3⁄8 in. (6) Reinstall oil pump drive cover and starter-generator drive cover (Ref.5 mm) square-drive socket extension installed on starter-generator driveshaft (Ref.). 2. (3) Secure borescope eyepiece to fixture. Borescope Inspection Figure 609 72-00-00 ENGINE . 3045542 DIFFUSER EXIT DUCT PORT FIBERSCOPE LP IMPELLER HP IMPELLER DISTAL END DIFFUSER EXIT DUCT C32400 HP Impeller .PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO.INSPECTION/CHECK Page 626 Jan 24/2006 . 11. NOTE: Pre-SB21486: If more convenient. use alternate port. MAINTENANCE PRACTICES). Para.5 mm) square-drive socket extension installed on starter-generator driveshaft (Ref. (c) Oil accumulation 72-00-00 ENGINE . and send to an approved laboratory to be analyzed (Ref. using a 3⁄8 in. connect light source and insert fiberscope into aperture. NOTE: L.INSPECTION/CHECK Page 627 Jan 24/2006 . if found. Fig. 72-01-60.). 72-20-00). retract fiberscope and rotate gears. c Repeat borescope inspection at next aircraft ‘‘A’’ check or 500 FH whichever comes first to monitor the remaining bolts. (4) Inspect the bottom of intercompressor case air plenum for oil accumulation and debris which. (4) Inspect gear teeth for damage (Ref. 72-00-00. (2) Clamp holding fixture (PWC34913) to a convenient surface. 72-20-00 for removal of starter-generator drive cover). Intercompressor Case Air Plenum (Ref. connect light source and secure eyepiece to holding fixture. (5) Remove all borescope equipment and socket extension. REMOVAL/INSTALLATION) and starter-generator cover (Ref. b A borescope inspection confirms the remaining bolts are not backing out and the missing bolts were not adjacent to one another.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. (3) Insert fiberscope into NL pickup probe port. (9. (b) Other Debris 1 Remove. For viewing and inspecting all teeth. 3045542 (3) Secure borescope eyepiece to fixture. 610) (1) Remove NL pulse pickup probe (Ref. 72-01-60). (6) Reinstall NH sensor (Ref. using a magnet. must be handled as follows: (a) HP Impeller Shroud Retaining Bolts 1 An engine may be returned to service with a maximum of three bolts missing provided: a The bolts and associated keywashers are removed from the engine and. PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO.Borescope Inspection Figure 610 72-00-00 ENGINE . 3045542 VIEW A (POST−SB21486) A NL SPEED PROBE PORT (PRE−SB21486) NL SPEED PROBE PORT C21110A Intercompressor Case Air Plenum .INSPECTION/CHECK Page 628 Jan 24/2006 . shown by enlarged corners and raised material adjacent to the roller side face. No. (2) Clamp holding fixture (PWC34913) to a convenient surface. 72-00-01. (1) Remove No.0 cm) into intercompressor case (ICC) No. 72-01-60). v Excessive wear and scratches on end face of any roller. (29. 611) NOTE: Due to casting differences. INSPECTION/CHECK) and fault isolation chart Oil on Flanges E and/or F (Ref.INSPECTION/CHECK Page 629 Jan 24/2006 .5 Cavity Inspection (Ref. (6) Install NL pulse pickup probe (Ref. (5. 72-00-00 ENGINE . 5 Bearing Cavity (Ref. access holes into No.0 in. Intercompressor Case P2. NOTE: Use of a side-viewing adapter to inspect the bearing cavity is not recommended due to the difficulties encountered locating the entrance hole to the bearing cavity.0 cm) into the scavenge passage through the hole in the housing (Ref. (4) Insert the borescope a further 2.4 in. 72-01-50). 3045542 1 Refer to the inspection procedure. (3) Carefully insert borescope 11. OIL SYSTEM. 72-01-50. M.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. This could require the use of a smaller borescope to enter the cavity. 5 bearing cavity may vary in size. View B) until one bearing roller can be clearly seen. 5 bearing oil scavenge passage in the direction opposite to the flight direction. Fig. (5) Inspect bearing for: v Fracture of the cage. 5 bearing scavenge oil tube assembly (Ref. v Excessive cage roller pocket wear. ENGINE FAULT ISOLATION). (5) Remove the fiberscope and holding fixture. ) (0. 5 Bearing Cavity . 3045542 A B CROWNS 0.100 IN. ROLLER (TYP.Borescope Inspection Figure 611 72-00-00 ENGINE . (6. DIA. 5 BEARING HOUSING RAISED MATERIAL THIN BRIGHT IS NORMAL LINE VIEW ON ARROW B C21111C No.54 mm) CORNER RADIUS DEFECTIVE ROLLER ENLARGED ROLLER POCKET CORNER CAGE WEAR AND SCRATCHES ON END FACES WEIGHT REDUCTION POCKETS (12) ROLLERS (12) RAISED MAT’L SHOWS UP HERE WHEN ROLLERS ARE UNSTABLE AND POCKETS WEAR 0.INSPECTION/CHECK Page 630 Jan 24/2006 .PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO.452 mm) TANG NORMAL ROLLER VIEW ON ARROW B WITH OUTER RACE REMOVED FOR CLARITY 0.275 IN.018 IN. (2.985 mm) END FACE WEAR ON CROWN SILVER BEARING CAGE GREY STEEL NO. (7) Install No. 72-01-40) or igniters (Ref. gold or oil stained color.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. install a 3⁄8 in. (2) Clamp the holding fixture (PWC34913) to a convenient surface. (6) Remove the borescope and holding fixture. 72-01-20). light gold. NOTE: 2. NOTE: 3. 5 bearing scavenge oil tube assembly (Ref. CAUTION: ENSURE ENGINE TEMPERATURE IS BELOW 60°C (140°F). (1. (4) Inspect the combustion chamber liner assembly for damage (Ref. and the crown has thin bright line(s) which may occasionally appear around the circumference of any number of rollers at random axial locations.) using different ports for complete coverage. (1) Remove the fuel manifold adapters (Ref. Para. 72-01-50). Also there may be raised material (silver plate) 0. N. 10.5 mm) square-drive extension and rotate the starter-generator driveshaft. Fig.127-0. To rotate the HP rotor to inspect the complete bearing. Under normal wear the end face has a thin 0. gold or oil stained and its end face may have been machined over one segment during balancing.INSPECTION/CHECK Page 631 Jan 24/2006 . connect the light source (RH-150A3) and secure the eyepiece to the holding fixture (Ref. 612). NOTE: The entire combustion chamber formed by the small exit duct and inner and outer liner assemblies can be inspected through three approximately equally spaced fuel nozzle ports. its color is either silver. 72-00-00 ENGINE . light gold.020 in. remove starter-generator drive cover. B.005 to 0.508 mm) high next to roller pocket tang. To compare.050 in. max (0. Normal cage appearance after engine running shows no fractures. tang is 0. NOTE: 1.025 in. (3) Insert the fiberscope into a fuel manifold adapter or igniter port. 3045542 v Excessive wear on the crown of any roller or thin bright lines at the same axial location on the crown of every roller. Normal roller appearance after engine running shows a light grey to dark grey. Rotate the rotor in the direction in which the rollers roll away from the tip of the borescope. (0.270 mm) high. Combustion Chamber Liner Assembly.635 mm) bright circumferential line at the edge. (9. HP Turbine Vane Ring Segments and HP Turbine Blades CAUTION: ENSURE FOREIGN OBJECTS DO NOT FALL INTO THE ENGINE. PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO.INSPECTION/CHECK Page 632 Jan 24/2006 . 3045542 FIBERSCOPE FUEL MANIFOLD ADAPTER BOSS COMBUSTION CHAMBER DISTAL−END HP IMPELLER HP TURBINE C70681 Combustion Chamber Liner Assembly .Borescope Inspection Figure 612 72-00-00 ENGINE . If significant defects are found. Record the location and extent of significant defects which require further inspections to determine the rate of deterioration and to ensure the inspection limits are not exceeded. (7) Remove the starter-generator drive cover (Ref. (6) Insert the fiberscope into the guide tube and inspect the HP turbine vane ring segments for damage (Ref. 72-20-00) and install a 3⁄8 in. Using a side-viewing adapter. All the segments can be inspected through three approximately equally spaced ports located at the 4. (a) Fuel manifold port 1 Insert guide tube (PWC34910-800) (Ref. Insert the tip of the fiberscope between the vane ring segments and inspect the HP turbine blades for damage. (b) Right (view from rear) igniter port 1 Insert guide tube (PWC34910-804) into port in an upward direction. Use different fuel manifold ports to obtain complete coverage. 8 and 12 o’clock positions. (9. If more than four consecutive vanes require inspection through one port. turning it counterclockwise until fully installed (at 270 degrees). (c) Left (view from rear) igniter port 1 Insert guide tube (PWC34910-804) into port in a downward direction. 72-00-00 ENGINE . 3045542 CAUTION: DO NOT USE FORCE WHEN INSERTING THE GUIDE TUBE. use the first port located next to the recommended location. turning it counterclockwise until fully installed. The first segment which can be inspected is located 120 degrees clockwise from the port. examine the leading edges and pressure sides of the four nearest vane segments. Insert the fiberscope into the guide tube and using the distal end.INSPECTION/CHECK Page 632A Jan 24/2006 . 613) into port. NOTE: (8) Borescope inspection of the HP turbine blades should be carried out using one fuel nozzle/igniter port and using the manual drive to rotate the HP rotor. If any of the ports are not accessible. 10. inspect the other vane segment leading edges. the pressure sides must also be inspected. turning it counterclockwise until fully installed.).5 mm) square-drive socket extension. a side-viewing adapter must be used. Para. (5) Remove fiberscope and insert guide tubes into fuel manifold or igniter ports as follows: NOTE: Carrying out a borescope inspection through one nozzle port using the distal end allows a detailed inspection of the leading edges and pressure sides of up to four consecutive segments located clockwise from the port.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. Fig. Borescope Inspection Figure 613 72-00-00 ENGINE .INSPECTION/CHECK Page 632B Jan 24/2006 . 3045542 COMBUSTION CHAMBER FIBERSCOPE GUIDE−TUBE SUPPORT FLANGE GUIDE−TUBE LP TURBINE HP IMPELLER GUIDE−TUBE OPEN TIP DISTAL−END HP TURBINE C70682 HP Turbine Vane Ring Segments and Blades .PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. Stop inserting fiberscope as soon as distal tip passes through guide tube. LP Turbine Blades and Stator Assembly (1) Remove the T6 thermocouples and adapters(Ref. (6) Slowly rotate guide tube control knob to point fiberscope towards LP turbine blades. (2) Install flexible guide tube (PWC34910-802) as follows (Ref. CAUTION: CARRY OUT LEAK CHECK (REF. (4) Secure borescope eyepiece to the holding fixture and connect the light source. NOTE: 2. 72-20-00). (c) Secure with knurled sleeve. rigid guide tube and holding fixture. 614): CAUTION: TO AVOID INTERNAL DAMAGE. (12) Remove socket extension and install the starter-generator drive cover (Ref. 3045542 CAUTION: WITHDRAW THE FIBERSCOPE TIP BEFORE ROTATING THE TURBINE ROTOR. O. 72-01-20). CAUTION: ENSURE ENGINE TEMPERATURE IS BELOW 66°C (150°F). screw fingertight (four turns minimum) and stop when arrows are parallel to engine axis. (3) Clamp the holding fixture (PWC34913) to a convenient surface. (5) Slowly insert fiberscope into guide tube while looking through eyepiece. (b) Insert guide tube through T6 thermocouple threaded port. 72-01-40) or igniters (Ref. (11) Install fuel manifold adapters (Ref. After reaching stop. pull control knob out to lock guide tube into position. 72-00-00 ENGINE . To orient the flexible tip toward the PT (first-stage) or LP stator and disk. 72-01-60). ADJUSTMENT/TEST) FOLLOWING REINSTALLATION OF FUEL MANIFOLD ADAPTERS. Pull hand knob to lock flexible tip in position. Remove fiberscope. 72-01-40. Fig. (a) Ensure guide tube flexible end is straight. Fiberscope may be inserted into flexible guide tube before or after installation of flexible guide tube. NOTE: 1.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. INSERT GUIDE TUBE SLOWLY AND WITHOUT FORCING. turn the hand knob clockwise or counterclockwise. (9) (10) Inspect the remaining HP turbine blades using the socket extension to rotate the turbine rotor.INSPECTION/CHECK Page 632C Jan 24/2006 . INSPECTION/CHECK Page 632D Jan 24/2006 . 3045542 ARROW POSITION ENGINE AXIS A FIBERSCOPE VIEW AT A GUIDE−TUBE CONTROL KNOB GUIDE−TUBE COMBUSTION CHAMBER KNURLED SLEEVE T6 IMMERSION THERMOCOUPLE BOSS HP IMPELLER DISTAL−END HP TURBINE LP TURBINE POWER TURBINES C70257 LP Turbine Blades and Stator Assembly .Borescope Inspection Figure 614 72-00-00 ENGINE .PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 72-01-60). CAUTION: ENSURE FLEXIBLE TIP IS UNLOCKED AND STRAIGHT BEFORE CARRYING OUT ANY REMOVAL STEPS. 72-00-00 ENGINE . (7) Rotate the LP turbine rotor using either of the following methods: (a) Remove most accessible diffuser exit duct (Ref. INSERT GUIDE TUBE SLOWLY AND WITHOUT FORCING. (8) Inspect LP turbine blades for damage (Ref. (12) Install the T6 thermocouples and adapters(Ref. 72-01-60). (2) Install flexible guide tube (PWC34910-802) as follows (Ref. AMM).INSPECTION/CHECK Page 632E Jan 24/2006 . Power Turbine Stator Assembly and First-stage Blades (1) Remove the T6 thermocouples and adapters (Ref. AMM) and rotate the LP impeller manually. (10) Push fiberscope slowly through guide tube until LP turbine stator vanes can be inspected for damage. 10. 10. (b) Remove the flexible guide tube. Retighten sleeve. CAUTION: ENSURE LP TURBINE ROTOR IS NOT TURNED WHEN LP TURBINE STATOR ASSEMBLY IS BEING INSPECTED. (a) Ensure guide tube flexible end is straight. 615): CAUTION: TO AVOID INTERNAL DAMAGE. P. (b) Insert guide tube through T6 thermocouple threaded port. The following must be carried out to inspect the complete LP stator assembly (Ref. CAUTION: ENSURE ENGINE TEMPERATURE IS BELOW 66°C (150°F). swivelling eyepiece to move the distal end of the fiberscope. 3045542 CAUTION: ENSURE FIBERSCOPE TIP IS NOT BETWEEN TURBINE BLADES WHEN THE LATTER ARE ROTATED. (c) Repeat the installation. Para. (11) Install the diffuser exit duct (Ref. 72-30-00) and rotate LP impeller. (b) Remove the air intake duct (Ref.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. inspection and removal procedures at the remaining T6 ports. Para. 72-30-00) or the air intake duct (Ref.): (a) Remove the fiberscope and holding fixture.). Fig. screw fingertight (four turns minimum) and stop when arrows are parallel to engine axis. using pusher (PWC34939). (9) Loosen guide tube knurled sleeve sufficiently to allow tube to move and facilitate insertion of fiberscope distal end between LP turbine blades. INSPECTION/CHECK Page 632F Jan 24/2006 .Borescope Inspection Figure 615 72-00-00 ENGINE . 3045542 ARROW POSITION ENGINE AXIS VIEW AT A A FIBERSCOPE GUIDE−TUBE GUIDE−TUBE CONTROL KNOB KNURLED SLEEVE COMBUSTION CHAMBER T6 IMMERSION THERMOCOUPLE BOSS POWER TURBINE STATOR POWER TURBINE VANE RING HP IMPELLER TURBINE EXHAUST DUCT LP TURBINE HP TURBINE DISTAL−END POWER TURBINES C70258 Power Turbine Stator Assembly and First-stage Blades .PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. PROPELLER SHAFT MUST BE ROTATED SLOWLY. 10.). (8) Loosen the guide tube knurled sleeve sufficiently to allow the tube to move and facilitate insertion of the fiberscope distal end between the stator vanes. CAUTION: ENSURE FLEXIBLE TIP IS UNLOCKED AND STRAIGHT BEFORE CARRYING OUT ANY REMOVAL STEPS.).INSPECTION/CHECK Page 632G Jan 24/2006 . Para. 3045542 (c) Secure with knurled sleeve. NOTE: 1. if accessible. (c) Remove the guide tube.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. Para.) as follows: (a) Remove the fiberscope and holding fixture. DUE TO GEAR RATIO. Look through eyepiece and stop inserting as soon as the distal tip passes through the guide tube. (7) Inspect the power turbine stator for damage (Ref. rotate the propeller shaft slowly or. (11) Inspect the complete power turbine stator for damage (Ref. (6) Slowly rotate the guide tube control knob to point the fiberscope towards the power turbine stator. pull the control knob out to lock the guide tube into position. To orient the flexible tip toward the PT (first-stage) or LP stator and disk. 10. Fiberscope may be inserted into flexible guide tube before or after installation of flexible guide tube. the second-stage power turbine. (4) Secure the borescope eyepiece to the holding fixture and connect the light source. turn the hand knob clockwise or counterclockwise. 72-00-00 ENGINE . CAUTION: TO AVOID DAMAGE TO DISTAL TIP. (9) Push the fiberscope slowly through the guide tube until the distal tip is adjacent to the first-stage power turbine blades. (3) Clamp the holding fixture (PWC34913) to a convenient surface. NOTE: Inspection of the complete power turbine stator should be carried out after the first-stage power turbine blades have been checked. Retighten the sleeve. (b) Push in and turn the guide tube control knob to straighten flexible tip. (5) Slowly insert the fiberscope into the guide tube. Para. ENSURE IT IS RETRACTED FROM TURBINE BLADES BEFORE ROTATING TURBINE. After reaching the stop. swivelling the eyepiece to move the distal tip of the fiberscope. (10) Inspect the first-stage power turbine blades for damage (Ref. NOTE: 2. 10. To alter blade position. Pull hand knob to lock flexible tip in position. 72-01-50. NOTE: A thin layer of soot is considered normal. If carbon deposit is less then 25%. REMOVAL/INSTALLATION). reinstall bearing vent tube (Ref. 6 and 7 Bearing Vent Transfer Tube. 6 and 7 bearing vent transfer tube. (a) Remove transfer tube (Ref. 617). (5) If carbon over maximum allowable is observed. (3) Examine transfer tube walls for carbon deposits which obstruct air flow. 72-01-60). 72-01-50. (b) Clean transfer tube (Ref. (c) Secure borescope eyepiece to fixture. proceed as follows: CAUTION: UNDER NO CIRCUMSTANCES MUST ANY ATTEMPT BE MADE TO REMOVE CARBON WITHOUT REMOVING TRANSFER TUBE. (12) Install the T6 thermocouples and adapters(Ref. 72-00-00 ENGINE . The vane ring should be inspected only through exhaust duct. REMOVAL/INSTALLATION) sufficiently to permit the fiberscope to be inserted into the inspection port. inspection and removal procedures at the remaining T6 ports. Fig. (6) Install transfer tube (Ref. (2) Slowly insert the fiberscope down into the No. REMOVAL/INSTALLATION). (7) Install vent tube (Ref. CAUTION: TAKE EXTREME CARE WHEN INSERTING BORESCOPE TO ENSURE CARBON DOES NOT FALL INTO THE NO. CLEANING/PAINTING). 3045542 (d) Repeat the installation. 5 bearing vent tube and intercompressor case drain tube (Ref. (4) A carbon deposit covering a maximum of approximately 25% of the tube cross section is acceptable. (1) Remove No. REMOVAL/INSTALLATION) . No. (b) Clamp holding fixture (PWC34913) to a convenient surface. REMOVAL/INSTALLATION). (2) Inspection Through Inspection Port (second-stage power turbine blades) (a) Remove security bolts and loosen No.INSPECTION/CHECK Page 632H Jan 24/2006 . 72-01-50. 6 AND 7 BEARING HOUSING. 6 and 7 bearing vent tube (Ref. 72-10-50. R. Q. connect light source and insert fiberscope into the inspection port (Ref. 72-01-50. 72-01-50. Second-stage Power Turbine Blades and Vane Ring (1) General (a) Borescope inspection of second-stage power turbine blades can be carried out using two different access routes and without use of a guide tube. REMOVAL/INSTALLATION). 72-01-50.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. connect the light source and. (b) Clamp the holding fixture (PWC34913) to a convenient surface. 618). (d) Inspect the second-stage power turbine blades for damage (Ref. NOTE: Although not as effective. (e) Remove the fiberscope and holding fixture. clean fiberscope. (b) Clamp holding fixture (PWC34913) to a convenient surface. AMM). OIL SYSTEM .REMOVAL/INSTALLATION). (d) If necessary. 72-01-50.). inspect the second-stage turbine blades for damage (Ref. Rotate the propeller shaft slowly to alter blade position. PROPELLER SHAFT MUST BE ROTATED SLOWLY. Fig. (c) Secure the borescope eyepiece to the fixture. washers (2) and cover (3) from left and right-hand side of gearbox. Para. 72-00-00 ENGINE . (c) Secure borescope eyepiece to holding fixture and connect light source. DUE TO GEAR RATIO. 10.INSPECTION/CHECK Page 632I Jan 24/2006 .). both helical and input gears can be inspected through one of the ports if access to one side of the engine is restricted. (f) S. 3045542 CAUTION: ENSURE DISTAL TIP OF FIBERSCOPE IS NOT BETWEEN POWER TURBINE BLADES WHEN LATTER ARE ROTATED.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. Para. 11. 10. using the fiberscope. CAUTION: DO NOT ROTATE POWER TURBINE WHEN INSPECTING VANE RING. (e) Remove the fiberscope and holding fixture..). (e) Slowly insert fiberscope into gearbox through LH (from front) inspection port. 5 bearing vent tube and intercompressor case drain tube (Ref. (d) Insert the distal tip of the fiberscope between the second-stage power turbine blades and inspect the power turbine vane ring for damage (Ref. H. Para.). (f) (3) Secure No. Discard packings (4). (f) Inspect teeth on gears for damage (Ref. Install the tailpipe (Ref. using a lint-free cloth. RGB First-stage Helical and Input Shaft Gears (1) Input Shaft Gear (a) Remove rear bolts (1. 10. AMM). Inspection Through the Exhaust Duct (second-stage power turbine blades and vane ring) (a) Remove the tailpipe (Ref. Para. 3045542 1 2 3 C12712 Borescope Inspection Port Cover .INSPECTION/CHECK Page 632J Jan 24/2006 .PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO.Removal/Installation Figure 616 72-00-00 ENGINE . NOTE: 2. 72-00-00 ENGINE . CAUTION: TO AVOID DAMAGE. Keeping a reduction gearbox in service while a removal is planned may substantially increase the cost of repair/refurbishment due to further gear and/or bearing damage. return reduction gearbox to an overhaul facility for repair. WITHDRAW FIBERSCOPE FROM GEARBOX BEFORE TURNING PROPELLER SHAFT. until RGB is refurbished.). 2. If acceptable spalling is evident (Ref. Keeping a reduction gearbox in service while a removal is planned may substantially increase the cost of repair/refurbishment due to further gear and/or bearing damage. for engines on an on-condition program.INSPECTION/CHECK Page 632K Jan 24/2006 . Repeat steps (i). NOTE: It may be necessary to use lens tissue (PWC05-043) and lens cleaner (PWC05-042) to remove oil film from distal tip lens. Bolt Cover Gasket CAUTION: TO AVOID DAMAGE. (k) Withdraw fiberscope from gearbox and turn propeller shaft 5 degrees CW. 11. Para. further borescope inspections must be carried out at intervals not to exceed 300 hours until the threshold inspection limit is exceeded or for engines on an on-condition program until RGB is refurbished. Para. NOTE: 2. 11. (j) Inspect teeth on gears for damage (Ref. (g) Withdraw fiberscope from gearbox and turn propeller shaft 5 degrees CW. (i) Slowly insert fiberscope through RH (from front) inspection port. further borescope inspection must be carried out at intervals not to exceed 300 hours until the threshold inspection limit is exceeded or. (j) and (k) until all teeth have been inspected. If unacceptable spalling is evident on one or more teeth. Para.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3. (f) and (g) until all teeth have been inspected. 11. NOTE: 1. If unacceptable spalling is evident on one or more teeth. NOTE: (l) It may be necessary to use lens tissue (PWC05-043) and lens cleaner (PWC05-043) to remove oil film from distal tip lens. (h) Repeat steps (e). NOTE: 1. If acceptable spalling is evident (Ref.). 3045542 Key to Figure 616 1.). return reduction gearbox to an overhaul facility for repair. WITHDRAW FIBERSCOPE FROM GEARBOX BEFORE TURNING PROPELLER SHAFT. INSPECTION/CHECK Page 632L Jan 24/2006 .PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3045542 TURBINE SUPPORT INSPECTION PORT HP TURBINE HP IMPELLER POWER TURBINES LP TURBINE FIBERSCOPE TURBINE EXHAUST DUCT DISTAL END COMBUSTION CHAMBER POWER TURBINE STATOR POWER TURBINE VANE RING C70277 Second-stage Power Turbine Blades .Borescope Inspection Figure 617 72-00-00 ENGINE . washers (6) and cover (7) from left and right-hand side of gearbox. (3. Para. (c) Secure borescope eyepiece to holding fixture and connect light source. 11. CAUTION: TO AVOID DAMAGE. RGB Second-stage Gears (Bull Gear and Layshaft Pinions) (1) Inspection with Front Borescope Inspection Covers Removed (a) Remove rear bolts (5. 3045542 (m) Remove fiberscope. NOTE: Although not as effective. (b) Clamp holding fixture (PWC34913) to a convenient surface. both helical and input gears can be inspected through one of the ports if access to one side of the engine is restricted. NOTE: It may be necessary to use lens tissue (PWC05-043) and lens cleaner (PWC05-042) to remove oil film from distal tip lens (h) Repeat steps (e). washers (2) and nuts (1). (f) Inspect teeth on both gears for damage (Ref. Fig. (e) Slowly insert fiberscope into gearbox through LH (from front) inspection port. WITHDRAW FIBERSCOPE FROM GEARBOX BEFORE TURNING PROPELLER SHAFT. (f) and (g) until all teeth on both gears have been inspected. (o) Install covers (3). clean fiberscope. CAUTION: TO AVOID DAMAGE. 618). Para.INSPECTION/CHECK Page 632M Jan 24/2006 .). (n) Lubricate packings (4) with engine oil (PWC03-001) and install on covers (3). (i) Slowly insert fiberscope through RH (from front) inspection port and inspect teeth visible on layshaft pinion for damage (Ref.07 Nm). Discard packings (8).). 11. light source and fixture. (d) If necessary.62-4. 72-00-00 ENGINE .in. WITHDRAW FIBERSCOPE FROM GEARBOX BEFORE TURNING PROPELLER SHAFT. (j) Withdraw fiberscope from gearbox and turn propeller shaft 5 degrees CW. (g) Withdraw fiberscope from gearbox and turn propeller shaft 5 degrees CW. Torque nuts 32 to 36 lb. T. using lint-free cloth.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO.Removal/Installation Figure 618 72-00-00 ENGINE .INSPECTION/CHECK Page 632N Jan 24/2006 . 3045542 4 3 2 8 1 7 6 5 LEFT HAND VIEW 4 8 3 2 2 1 5 6 7 RIGHT HAND VIEW C61606 RGB Borescope Inspection Covers . Nut Washer Cover Packing Nut Washer Cover Packing (k) Repeat steps (i) and (j) until all layshaft pinion teeth have been inspected. If unacceptable spalling is evident on one or more teeth. light source and fixture.INSPECTION/CHECK Page 632O Jan 24/2006 . 6. (m) Lubricate packings (8) with engine oil (PWC03-001) and install on covers (7). (d) Insert fiberscope into rear housing aperture where bull gear is visible. 3. 2.62-4. 8.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. (b) Clamp holding fixture (PWC34913) to a convenient surface. return reduction gearbox to an overhaul facility for repair. Keeping a reduction gearbox in service while a removal is planned may substantially increase the cost of repair/refurbishment due to further gear and/or bearing damage. Torque nuts 32 to 36 lb. Para. 5. washers (6) and nuts (5). Para. (l) Remove fiberscope.). (n) Install covers (7). further borescope inspections must be carried out at intervals not to exceed 300 hours until the threshold inspection limit is exceeded or for engines on an on-condition program until RGB is refurbished. 11. 72-00-00 ENGINE . NOTE: 1. following along bull gear teeth to one side until second-stage gear is reached. (2) Inspection with Accessory Gearbox Drive Cover Removed (a) Remove RGB accessory drive cover and gears (Ref.). (3. 4. 72-10-00). 7. (c) Secure borescope eyepiece to fixture and connect light source. 11. If acceptable spalling is evident (Ref.in. (e) Inspect gear teeth for damage (Ref. NOTE: 2. 3045542 Key to Figure 618 1.07 Nm). until RGB is refurbished. If acceptable spalling is evident (Ref. using a lint-free cloth. Discard packings (4). (c) Secure borescope eyepiece to holding fixture and connect light source.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. To view and inspect all teeth. Repeat as required to view and inspect all teeth. turn propeller shaft and reinsert fiberscope. clean fiberscope. further borescope inspection must be carried out at intervals not to exceed 300 hours until the threshold inspection limit is exceeded or.). following along bull gear to other side until second-stage gear is reached. 11. NOTE: 3.INSPECTION/CHECK Page 632P Jan 24/2006 . Fig. 11. NOTE: 3. 11. NOTE: 1. for engines on an on-condition program. Inspection with Layshaft Covers Removed (a) Remove nuts (1. NOTE: 2. Para.). for engines on an on-condition program. return reduction gearbox to an overhaul facility for repair. If acceptable spalling is evident (Ref. using puller (PWC37651). If unacceptable spalling is evident on one or more teeth. Para.). Keeping a reduction gearbox in service while a removal is planned may substantially increase the cost of repair/refurbishment due to further gear and/or bearing damage. Para. (g) To view other second-stage gear. (h) Inspect gear teeth for damage (Ref. washers (2) and covers (3). NOTE: 1. Keeping a reduction gearbox in service while a removal is planned may substantially increase the cost of repair/refurbishment due to further gear and/or bearing damage. until RGB is refurbished. repeat step (f). 72-00-00 ENGINE . (d) If necessary. 72-10-00). return reduction gearbox to an overhaul facility for repair. 618). Approximately a quarter turn of propeller shaft rotates second-stage gear 360 degrees. 3045542 (f) Retract fiberscope. insert fiberscope into other aperture where bull gear is visible. If unacceptable spalling is evident on one or more teeth. NOTE: 2. (i) (3) Remove all borescope equipment and reinstall gears and RGB accessory cover (Ref. (b) Clamp holding fixture (PWC34913) to a convenient surface. further borescope inspection must be carried out at intervals not to exceed 300 hours until the threshold inspection limit is exceeded or. light source and fixture. return reduction gearbox to an overhaul facility for repair. (i) Slowly insert fiberscope through RH (from front) No. Remove fiberscope. (m) Install layshaft covers (Ref.). 11. Para. further borescope inspection must be carried out at intervals not to exceed 300 hours until the threshold inspection limit is exceeded or. If acceptable spalling is evident (Ref. Para. 72-00-00 ENGINE . 11.). 14 bearing at 2 o’clock position and inspect teeth visible on layshaft pinion for damage (Ref.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO.). (f) Inspect teeth visible on both bullgear and LH second-stage pinion gear for damage (Ref. Keeping a reduction gearbox in service while a removal is planned may substantially increase the cost of repair/refurbishment due to further gear and/or bearing damage. Para. WHICH MUST BE CLEAN. (f) and (g) until all teeth on both gears have been inspected. 72-10-00). NOTE: It may be necessary to use lens tissue (PWC05-043) and lens cleaner (PWC05-042) to remove oil film from distal tip lens. 11.). NOTE: (l) If acceptable spalling is evident (Ref. Para. STEEL BRAIDED FIBERSCOPES MUST NOT BE USED. until RGB is refurbished. for engines on an on-condition program.INSPECTION/CHECK Page 632Q Jan 24/2006 . CAUTION: TO AVOID DAMAGE. NOTE: 2. 3045542 CAUTION: USE ONLY APPROVED FIBERSCOPE (MACHIDA 5 mm FBA 4-90T) TO INSPECT SECOND-STAGE REDUCTION SPUR GEAR TEETH. WITHDRAW FIBERSCOPE FROM GEARBOX BEFORE TURNING PROPELLER SHAFT. (g) Withdraw fiberscope from gearbox and turn propeller shaft 5 degrees CW. 11. (e) Slowly insert fiberscope into gearbox through LH (from front) No. CAUTION: TO AVOID DAMAGE. WITHDRAW FIBERSCOPE FROM GEARBOX BEFORE TURNING PROPELLER SHAFT. further borescope inspection must be carried out at intervals not to exceed 300 hours until the threshold inspection limit is exceeded. EXTREME CARE MUST BE TAKEN TO NOT DAMAGE OR SCRATCH BEARING RACE WHEN INSERTING FIBERSCOPE. (k) Repeat steps (i) and (j) until all layshaft pinion teeth have been inspected. If unacceptable spalling is evident on one or more teeth. NOTE: 1. 14 bearing at 10 and 11 o’clock positions. (j) Withdraw fiberscope from gearbox and turn propeller shaft 5 degrees CW. (h) Repeat steps (e). PAY SPECIAL ATTENTION TO ROTATING COMPONENTS. This will enable them to schedule an HSI for economic reasons before damage increases to the extent that components cannot be repaired and must be replaced. Adjustment/Test) is carried out to ensure engine performance is within acceptable limitations. Inner and Outer Liner Assemblies) (1) General (a) Combustion chamber components can be repaired (Ref. 72-03-00. components may remain in service until in-service limits are reached. If further extensions are required. 72-00-00 ENGINE .) must be carried out before the next flight.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. (3) Only. B. if damage is beyond repair limits. to determine the area to be borescoped. a borescope inspection of the affected area must be carried out within 50 flight hours. However. NOTE: B. Consult Fault Isolation (Performance Deterioration (ECTM shift) or High ITT (T6)). Extensions must not go beyond an individual operator’s approved inspection interval (TBO). Combustion Chamber (Small Exit Duct.e. INSPECTION/CHECK). Keeping an engine in service after components have deteriorated beyond suggested economical criteria may substantially increase the cost of subsequent repairs/refurbishments due to the possible effect on downstream components. A. Hot Section Component Borescope Inspection Criteria CAUTION: GAS PATH COMPONENTS DOWNSTREAM OF COMPONENTS HAVING MATERIAL MISSING MUST BE INSPECTED TO ENSURE SECONDARY DAMAGE HAS NOT OCCURRED. 3045542 10. blades) being outside the guidelines given in the following procedures (Ref. Para. provided a power assurance check (Ref. Also. through I. (2) A hot section inspection (HSI) recommended due to rotating components (i. an HSI/engine removal which is recommended due to deteriorating non-rotating engine components may be delayed. General (1) Borescope inspection is usually a troubleshooting procedure carried out to determine the reasons for performance deterioration. Borescope inspection of specific areas may also be required by the maintenance program.INSPECTION/CHECK Page 632R Jan 24/2006 . and operators are recommended to consider repair limits as well as in-service limits before deciding action to be taken after a borescope inspection. subsequent inspections and power assurance checks must be carried out at intervals depending on the rate of progression and level of deterioration seen. (b) Deterioration must be recorded to provide a baseline to enable rate of progression to be assessed at subsequent inspections. Table 1 or 2).200 sq. Exposure to these peaks contributes to premature hot section deterioration.2 sq.0 sq. the associated fuel nozzle must be inspected and replaced if not within specified limits.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO.mm) equivalent to one hole of 0.. steps (2) and (3) for additional HSI recommendations. Carbon accumulation is progressive and can affect all nozzles. NOTE: The 50 FH interval is subject to acceptable condition of the downstream hot section components. 72-00-00 ENGINE . P&WC recommends to remove the engine and carry out the incorporation of SB21598 Part B within the next 10 FH to avoid potential downstream damages. 620). 622). Therefore. 3045542 (c) When localized combustion chamber deterioration is observed. it is suggested. 621). until incorporation of SB21598.000 sq. 2 If there is evidence that the center cooling ring is detached. (2) Inspection Criteria (a) Combustion Chamber Outer Liner Center Cooling Ring (Item X) (Pre-SB21598.mm). A.250 in. (d) Refer to Para. 623) 1 The following holes are acceptable: a Area a: holes having a total surface area less than 0. that all nozzles be inspected to minimize the possibility of premature deterioration occurring at other locations. Fig. (b) Combustion chamber inner and outer liner assemblies (Ref. (129. P&WC recommends to carry out repeated borescope inspections at 50 FH intervals.500 in.35 mm) diameter.7 mm) diameter. (6.in. b Area b: holes having a total surface area less than 0. Carbon accumulation inside fuel nozzle passages is the principal cause of spray pattern degradation which results in non-uniform combustion and local high temperature peaks. 1 Inspect the center cooling ring for evidence of detachment from the back-up ring support (Ref. Fig. (1290. c Area c: holes having a total surface area less than 2. Fig. Part B (Ref. providing there are no cracks or holes in the associated bottom support. (12. (32. Fig.050 sq. 619) NOTE: Refer to SB21598 for the applicability (Ref.INSPECTION/CHECK Page 633 Jan 24/2006 . Part B) (Ref.in.in.mm) equivalent to one hole of 0. Fig. NOTE: 3 Detachment is when a section of the center cooling ring is cracked axially completely across the ring and is pulled away from the liner wall to the extent shown (Ref.0 sq. If there is a section of the center cooling ring missing. for economic reasons. Location of Figure 619 72-00-00 ENGINE . 3045542 q r r c x r r q q q C18576 Combustion Chamber Outer Liner Center Cooling Ring .INSPECTION/CHECK Page 634 Jan 24/2006 .PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. Example of Detachment Figure 620 72-00-00 ENGINE .PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3045542 CENTER−COOLING−RING CENTER−COOLING−RING DETACHED FROM SUPPORT TOP VIEW C67441 Center Cooling Ring .INSPECTION/CHECK Page 635 Jan 24/2006 . 3045542 CENTER−C00LING−RING CENTER−C00LING−RING C67229A Center Cooling Ring .PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO.Detachment of Figure 621 72-00-00 ENGINE .INSPECTION/CHECK Page 636 Jan 24/2006 . Example of Missing Section Figure 622 72-00-00 ENGINE .INSPECTION/CHECK Page 637 Jan 24/2006 .PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3045542 CENTER−C00LING−RING MISSING SECTION OF COOLING RING C67414 Center Cooling Ring . If no further deterioration is observed. an HSI is recommended to be carried out within 100 flight hours. providing the total surface area between the sides of the cracks does not exceed the area allowed for holes (Ref. Subsequent inspections must be carried out at intervals depending upon rate of progression and level of deterioration seen. Subsequent inspections must be carried out at intervals depending upon rate of progression and level of deterioration seen. A repeat inspection of the affected area must be carried out within 300 flight hours. If no further deterioration is observed. the engine may continue in service with subsequent inspections carried out as defined in the regular maintenance program. 3045542 d A repeat inspection of the affected area must be carried out within 300 flight hours. step 1) will be produced. 624) 72-00-00 ENGINE . The engine may continue in service with subsequent inspections carried out as defined in the regular maintenance program. 3 Converging cracks in walls of inner and outer liner assemblies similar to those shown in View D are acceptable. 6 Bulging with no abrupt change in curvature and/or hot spots is acceptable. 2 Non-converging cracks in the walls of the inner and outer liner assemblies are acceptable. The engine may continue in service with subsequent inspections carried out as defined in the regular maintenance program. Fig. an HSI is recommended to be carried out within 100 flight hours. If no further deterioration is observed. 5 Plasma top coating (ceramic) loss on inner and outer liner assemblies is acceptable. The engine may continue in service with subsequent inspections carried out as defined in the regular maintenance program. If deterioration exceeds the above limits or the bottom support is cracked or has holes. NOTE: Cooling rings having material missing may change air flow which could accelerate combustion chamber deterioration. step 1). (c) Small exit duct (Ref. If deterioration exceeds the limits specified in step 1. If converging cracks are anticipated to progress to an extent that a hole larger than those considered acceptable (Ref. providing a repeat borescope inspection of the affected area is carried out within 300 flight hours. the engine may continue in service with subsequent inspections carried out as defined in the regular maintenance program.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 4 Cooling rings eroded and/or cracked and/or having material missing due to metal break away are acceptable. an HSI is recommended to be carried out within 100 flight hours. Subsequent inspections must be carried out at intervals depending upon rate of progression and level of deterioration seen.INSPECTION/CHECK Page 638 Jan 24/2006 . the engine may continue in service with subsequent inspections carried out as defined in the regular maintenance program. 7 All other defects are acceptable. PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO.INSPECTION/CHECK Page 639 Jan 24/2006 . 3045542 BULGING E a F b D b BULGING c BOTTOM SUPPORT C22738 Combustion Chamber Inner and Outer Liner Assemblies .Typical In-service Defects Figure 623 (Sheet 1 of 4) 72-00-00 ENGINE . INSPECTION/CHECK Page 640 Jan 24/2006 .763 mm) 1.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. REF (8.290 in.345 in.766 mm) REF ACCEPTABLE HOLE VIEW D C22737A Combustion Chamber Inner and Outer Liner Assemblies .Typical In-service Defects Figure 623 (Sheet 2) 72-00-00 ENGINE . (32. 3045542 0. 680 in. (17.920 in.62 mm) REF 0.272 mm) REF C22736A Combustion Chamber Inner and Outer Liner Assemblies .PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. (23. 3045542 0.368 mm) REF ACCEPTABLE HOLE VIEW E 0.Typical In-service Defects Figure 623 (Sheet 3) 72-00-00 ENGINE .300 in.INSPECTION/CHECK Page 641 Jan 24/2006 . (7. 368 mm) REF 0.62 mm) REF ACCEPTABLE HOLE VIEW F C22735A Combustion Chamber Inner and Outer Liner Assemblies . 3045542 0.Typical In-service Defects Figure 623 (Sheet 4) 72-00-00 ENGINE . (23.920 in.300 in.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. (7.INSPECTION/CHECK Page 642 Jan 24/2006 . 72-00-00 ENGINE .0 sq.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. Continued service may also result in damage to the turbine support case (TSC) due to oxidation/erosion between HP shroud segments located in the hot gas streak path. MORE FREQUENT BORESCOPE INSPECTIONS MAY BE REQUIRED DUE TO THE REINSTALLATION OF DAMAGED VANE SEGMENTS. Distance Ref. Table 604). providing that holes or cracks in the inner flange support are within limits (Ref. a borescope inspection of the associated HP turbine vanes must be carried out. (REF. If deterioration exceeds the above limits or the inner flange support is cracked or has holes.000 sq. A repeat inspection of the affected area must be carried out within 300 flight hours. 2 Plasma top coating (ceramic) loss is acceptable.mm) in the heat shield are acceptable. 3045542 1 As structural integrity is not affected. A (IN) Approx. B (IN) -- 21629 0. ENGINE LOGBOOK AND 72-03-00. therefore segments cannot be completely inspected). decrease HP compressor speed (NH) and may result in higher interturbine temperature (ITT/T6).INSPECTION/CHECK Page 643 Jan 24/2006 .600 C. When damage is found. Repair to the TSC at the HP shroud segment support will significantly increase shop visit cost. However. Reference Dimensions (Ref. TABLE 604. erosion and/or holes having total surface area less than 2. If this occurs. the HP shroud segments must be inspected. Inner Flange Holes.100 0. Fig. 3 All other defects are acceptable. flight safety is not affected. cracks (including open radial cracks extending from inner to outer diameter). 624) Pre-SB Post-SB Hole Dia. When inspected through the borescope.050 0. Subsequent inspections must be carried out at intervals depending upon the rate of progression and level of deterioration seen. (1290. The engine may continue in service with subsequent inspections carried out as defined in the regular maintenance program. deteriorated HP vane segments may already be beyond repairable limits.in. High Pressure (HP) Turbine Vane Segments CAUTION: AFTER A SHOP VISIT. (b) The inspection criteria for HP vane segments is separated into two categories: 1 Criteria for installed vane segments which are visually inspected using a borescope (visual access is limited.300 21629 -- 0. INSPECTION/CHECK) (1) General (a) Hot gas streaks can result in burnt/eroded areas on the HP turbine vane ring segments which usually increase flow area. an HSI is recommended to be carried out within 100 flight hours. 3045542 A F A INNER FLANGE SUPPORT COATING MISSING HEAT SHIELD SECTION A−A INNER FLANGE SUPPORT B COOLING HOLES ON INNER FLANGE (DIA A REF.Typical In-service Defects Figure 624 72-00-00 ENGINE .PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO.) (REF.INSPECTION/CHECK Page 644 Jan 24/2006 .) HEAT SHIELD CRACK VIEW F C22701B Small Exit Duct . (e) The description and illustrations of various types of HP vane segment damage which follow. it is good maintenance practice to borescope the combustion chamber. 72-03-00.INSPECTION/CHECK Page 645 Jan 24/2006 . 3045542 2 Expanded criteria for vane segments which are removed from the engine during shop visits (Ref. Certain damage may be classified as allowable for continued service. 2 Category 2 Minor repairable damage (Ref. the fuel nozzle set associated with the damage will not be known if the condition of these components was not checked when doing fuel nozzle changes. Category 3 72-00-00 ENGINE . (c) For both categories. 1 Category 1 No visible deterioration. It should be noted that if HP vane segments are reinstalled at shop visit. The actual interval used is determined by reviewing the borescope inspection requirements of HP vane segment(s) and other hot end components. Subsequent borescope inspection interval: 1500 hours Max. (2) Inspection Criteria (a) The five categories listed below cover HP vane segment deterioration. These expanded limits can be used to reduce the work done during engine repair by allowing the vane segments to remain in service. subsequent on-wing intervals may be shorter due to the deterioration which continues when the engine is returned to service. Inspection/Check). (d) Regardless of the borescope interval recommended. then choosing the shortest interval. 625). give the criteria used when deciding if an HP vane segment should continue in service.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. If subsequent borescope inspections reveal hot section damage. Dents and/or impact damage are acceptable but may cause the segment to become unrepairable. the applicable borescope inspection intervals are listed for HP turbine vane segments which remain in service. safety and engine operation will not be affected. NOTE: 3 The repairability criteria and examples shown in this category are guidelines to be used only for maintenance planning purposes. HP vane segments and HP turbine blades during a fuel nozzle change. subsequent borescope inspections may show damage increasing to category 4 which may require more frequent inspections and/or engine removal. When damaged segments are returned to service after a shop visit. Subsequent borescope inspection interval: Refer to Chapter 05-20-00. but recommendations may be given not to reinstall the segment if the damage is found during a shop visit. although flight safety is not affected. however. Fig. This interval is determined by hardware condition which is divided into five categories. to borescope through the igniter ports instead of the fuel nozzle ports which involves disturbing the fuel system. Immediate removal is required if rotating components are not within borescope inspection limits and/or if power assurance check limits are not met. Engine removal is recommended within 50 hours for economic reasons. 628). Subsequent borescope inspection interval: 400 hours Max. HP turbine blades. it is recommended. (2) Inspection Criteria (a) Coating loss on the leading edge surface of the blade. An increase in turbine tip clearance can significantly increase the interturbine temperature (ITT/T6) and reduce Nh rotor speed. fuel nozzles are recommended to be changed as a precaution in order to minimize the possibility of further downstream damage occurring. Fig. Carry out a detailed borescope inspection of the combustion chamber. 626).PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. is acceptable. To keep an engine in service after components have deteriorated more than the recommended economical criteria can possibly increase the cost of subsequent repairs/refurbishment because of the effect on downstream components. HP turbine shrouds. 72-00-00 ENGINE . HP turbine blades. LP turbine vanes and LP turbine blades for evidence of widespread damage. For these more frequent borescope inspections. Fig. LP turbine vanes and LP turbine blades for evidence of widespread damage.350 inch in height or covering less than 40% of the leading edge surface. 5 Category 5 Unserviceable condition requiring scheduled engine removal (Ref. where possible. Subsequent borescope inspection interval: 1500 hours Max. that is less than 0. Re-evaluate segment(s) during subsequent inspections to see if the condition has degraded to category 5 damage. Damage of this type may be caused by deviating fuel nozzle flow or prolonged use of vane segments which are in an unrepairable condition. HP turbine shrouds. HP Turbine Blades (1) General (a) The condition of HP turbine blade airfoils and tips is critical to obtain rated power. NOTE: D. If continued service is planned. 3045542 Minor non-repairable damage (Ref. 627). 4 Category 4 Non-repairable damage requiring more frequent monitoring (Ref. Carry out a detailed borescope inspection of the combustion chamber.INSPECTION/CHECK Page 646 Jan 24/2006 . Fig. C69267 HP Turbine Vane Segment . CONTINUED SERVICE MAY CAUSE THE SEGMENT TO BE NON−REPAIRABLE AT NEXT SHOP VISIT.Minor Repairable Damage Figure 625 72-00-00 ENGINE . IF AN AREA BOUNDED BY CONVERGING CRACKS DOES NOT EXTEND INTO THIS SUPPORTING ZONE. THE SEGMENT IS RECOMMENDED TO BE REPLACED. 3045542 THESE EXAMPLES SHOW REPAIRABLE EROSION AND CRACKS THAT ARE ACCEPTABLE FOR CONTINUED SERVICE.500 CONVERGING AIRFOIL CRACKS ARE ALLOWABLE. ALLOWABLE NOT ALLOWABLE 0. AIRFOIL SURFACES ARE INTERNALLY SUPPORTED UP TO 0.INSPECTION/CHECK Page 647 Jan 24/2006 .7 MM) FROM THE TRAILING EDGE.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO.500 IN (12. VANE SEGMENTS WITH THIS TYPE OF DAMAGE ARE RECOMMENDED TO BE REPLACED AT SHOP VISIT.INSPECTION/CHECK Page 648 Jan 24/2006 .PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. C69269 HP Turbine Vane Segment . 3045542 CRACKS WHICH FORM A CIRCULAR PATTERN BETWEEN A GROUP OF ADJACENT LEADING EDGE COOLING HOLES ARE ACCEPTABLE.Minor Non-repairable Damage Figure 626 72-00-00 ENGINE . FUEL NOZZLES ARE RECOMMENDED TO BE REPLACED IF THIS CONDITION HAS NOT BEEN OBSERVED AT PREVIOUS INSPECTION. 3045542 OUTER PLATFORM TRAILING EDGE EROSION AIRFOIL SURFACE MISSING (BURNT) MATERIAL EXPOSING INSERT BURNT MATERIAL EXPOSING THE INSIDE OF THE VANE REQUIRES FREQUENT (i.e.Non-repairable Damage (Category 4) Figure 627 72-00-00 ENGINE .PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. C69270 HP Turbine Vane Segment . CATEGORY 4) MONITORING.INSPECTION/CHECK Page 649 Jan 24/2006 . ENGINE MUST BE REMOVED IMMEDIATELY.INSPECTION/CHECK Page 650 Jan 24/2006 . IF ROTATING COMPONENTS ARE NOT WITHIN BORESCOPE INSPECTION LIMITS OR POWER ASSURANCE CHECK INDICATES THE ENGINE IS NOT OPERATING WITHIN DEFINED LIMIT. VANE SEGMENTS WITH THE MAJORITY OF THE INTERNAL INSERT EXPOSED OR WITH ENTIRE AIRFOILS MISSING. C69272B HP Turbine Vane Segment . NOTE: TO KEEP AN ENGINE IN SERVICE AFTER COMPONENTS HAVE DETERIORIATED MORE THAN THE RECOMMENDED ECONOMICAL CRITERIA CAN POSSIBLY INCREASE THE COST OF SUBSEQUENT REPAIRS / REFURBISHMENT BECAUSE OF THE EFFECT ON DOWNSTREAM COMPONENTS.Non-repairable Damage Requiring Scheduled Engine Removal Figure 628 72-00-00 ENGINE .PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3045542 ENGINE REMOVAL IS RECOMMENDED WITHIN 50 HOURS FOR ECONOMIC REASONS IF. INSPECTION/CHECK Page 651 Jan 24/2006 . Additional borescope inspections must be carried out at intervals not to exceed 1500 flight hours. NOTE: If borescope limits are being used to determine the serviceability of the HP turbine blades during an engine repair and the erosion has reduced the wall thickness at the leading edge tip (Dim. may appear on a blade set or on individual blades. For scheduling purposes. depending upon the rate of progression and level of deterioration seen. A. To determine the appropriate maintenance action. refer to the action required for the highest level of corrosion stage present. providing engine performance is within limits. providing internal cooling air passages are not visible and engine performance is within limits. NOTE: (f) (3) Refer to Para. (e) Visible internal cooling air passages or trailing edge defects exceeding those shown on Figure 630 are not acceptable. For scheduling purposes. follow the borescope inspection intervals in step (c). for additional HSI recommendations. 72-00-00 ENGINE . depending upon the rate of progression and level of deterioration seen. for each of the blade corrosion conditions. (d) Leading edge/tip erosion and open cracks at blade tip exceeding those shown on Figure 630 are acceptable for further service. Table 605 provides a summary of the maintenance actions required. Corrosion that goes through the HP blade platform as shown on figure 630. A repeat borescope inspection and power assurance check must be carried out within 100 flight hours. Subsequent borescope inspections and power assurance checks must be carried out at intervals not to exceed 300 flight hours.020 in. the HSI can be delayed for a maximum of 100 flight hours. T) to less than 0. (c) Defects exceeding those shown on Figure 629 but not exceeding the acceptable defects shown on Figure 630 are acceptable for further service. Airfoil corrosion is described in the table that follows. 3045542 (b) Defects shown on Figure 629 are acceptable for further service. depending upon rate of progression and level of deterioration seen. Further increased erosion and blade tip oxidation will be indicated by an increase in ITT and a drop in Nh rotor speed when monitored using ECTM. (0. is not acceptable and an HSI is recommended to be carried out.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. providing engine performance is within limits. Refer to steps (3) (b) thru (e) for corrosion stage definition. NOTE: It is possible that multiple corrosion stages. and an HSI is recommended to be carried out. the HSI can be delayed for a maximum of 100 flight hours.50 mm). providing engine performance is within limits. providing engine performance is within limits. A repeat borescope inspection and power assurance check must be carried out within 300 flight hours. Subsequent borescope inspections and power assurance checks must be carried out at intervals not to exceed 600 flight hours. (2) FOR RECOMMENDED SERVICE ACTION.00mm) COATING LOSS HAIRLINE CRACK LEADING EDGE NOTES: 1. C18657H HP Turbine Blade . (8. THE ABOVE DEFECTS ARE ACCEPTABLE FOR FURTHER SERVICE. D.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 2. BLADE TIP (2.080 IN. HAIRLINE CRACKS WITH NO SIGNS OF EROSION OR CORROSION AND STARTING AT THE TIP OF THE BLADE ARE ACCEPTABLE.300 IN.Typical Damage (Blade Tip May Be Repairable By Grinding) Figure 629 72-00-00 ENGINE . REFER TO PARA.0 mm) OPEN CRACK T TRAILING EDGE 0. 10.INSPECTION/CHECK Page 652 Jan 24/2006 . 3045542 EROSION HEAVY RUBBING AND BURNT MATERIAL 0. ( 2) (d) FOR RECOMMENDED SERVICE ACTION.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. REFER TO PARA. C18658K HP Turbine Blade . THEREFORE THE EXTENT OF THE DAMAGE MAY BE ESTIMATED AS A PERCENTAGE OF AIRFOIL TRAILING EDGE HEIGHT AND TIP LENGTH. TRAILING EDGE EROSION.250 IN.Damage Limits Figure 630 72-00-00 ENGINE .INSPECTION/CHECK Page 653 Jan 24/2006 . COATING LOSS OR BURNT MATERIAL LEADING EDGE CORROSION THAT GOES THROUGH BLADE PLATFORM NOTES: 1. D. D.900 IN.35 mm) OR 24% 0. (2) (f) FOR RECOMMENDED SERVICE ACTION.250 IN. 10. 10. (22. THE DIMENSIONS CANNOT BE ACCURATELY MEASURED WHEN USING A BORESCOPE. CORROSION THAT GOES THROUGH THE BLADE PLATFORM IS NOT ACCEPTABLE. D. REFER TO PARA 10.86 mm) APPROX. TRAILING EDGE DEFECTS EXCEEDING THE ABOVE LIMITS ARE NOT ACCEPTABLE. (6. 3045542 BLADE TIP OPEN CRACK EROSION 0. (2) (c) FOR RECOMMENDED SERVICE ACTION. 2. REFER TO PARA. 3. (6.35 mm) OR 28% HEAVY RUBBING. THE ABOVE LEADING EDGE/TIP EROSION AND OPEN CRACKS AT BLADE TIP ARE ACCEPTABLE FOR FURTHER SERVICE. BURNT OR MISSING MATERIAL 0. since this is a manual operation. Fig. Effectiveness of turbine wash should be assessed via borescope inspection per Table 605. These dimples are superfluous material left from the casting process and are normally removed by hand. During borescope. sheet 3). Airfoil Corrosion / Maintenance Actions Blade Inspection Area (Ref. 72-00-00. sheet 4). Fig. 633 . 633 . Structural Integrity of base material affected (Ref.INSPECTION/CHECK Page 654 Jan 24/2006 .125 inch.125 x 0. (a) Manufacturing Dimples on blade: (Ref to Fig. E. Structural integrity of the base material may be affected if corrosion blister is located in Area A. 633 .125 x 0. Structural integrity of base material is not affected (Ref. 632) 1 2 3 4 Area ‘‘B’’ Upper 50% Borescope 1500 FH Intervals Borescope 500 FH Intervals Replace Blade Within 500 FH Replace Blade Within 10 FH Area ‘‘A’’ Lower 50% Borescope 1500 FH Intervals Replace Blade Within 50 FH Replace Blade Within 10 FH Replace Blade Within 10 FH Corrosion Stages NOTE: General Recommendation on Turbine Wash: When corrosion is observed on turbine airfoils. (c) Corrosion Stage 2: Oxidation of base material has started. it is an indicator that turbine wash procedures or wash frequency needs correction or adjustment. These dimples have no effect on blade structural integrity and blade performance. the surface profile may vary from one hand tool operator to the other. 633 . The dimples. Structural integrity of the base material may be affected (Ref. (d) Corrosion Stage 3: Oxidation of the base material has penetrated to a significant depth. Evidence of blistering caused by formation of corrosion products under the coating. 3045542 TABLE 605. Their presence is often highlighted by dirt / soot deposits that gather on the dimple. (Ref. inspectors must pay attention as to not confuse corrosion blisters with manufacturing dimples that may be present. Fig. sheet 2). Fig. (b) Corrosion Stage 1: Slight roughening of the surface caused by some growth and localized breakdown of the protection coating is evident. using tool PWC56502 as described in. Fig. on the whole fleet. are approximately 1/8 inch in diameter and are located at the mid-chord of the pressure side (concave) of the airfoil (about 1/8 inch above the platform). (e) Corrosion Stage 4: Deep penetration of corrosion going though the airfoil wall. Individual blisters do not exceed 0. P&WC recommends the implementation of turbine wash method 2.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. HP Turbine Shroud Segment (1) Borescope Inspection Intervals: 72-00-00 ENGINE . 631). In such a case. sheet 1). Engine Cleaning. Blister(s) size is greater than 0. However.125 inch. if present. C101553 HP Turbine Blade .PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO.INSPECTION/CHECK Page 655 Jan 24/2006 . 3045542 DIMPLE DIMPLE DIMPLE NOTE: NO MAINTENANCE ACTIONS REQUIRED.Manufacturing Dimples Figure 631 72-00-00 ENGINE . PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO.875 IN. 3045542 AREA B 0.INSPECTION/CHECK Page 656 Jan 24/2006 . (APPROX) AREA A C101557 HP Turbine Blade Inspection Area’s Figure 632 72-00-00 ENGINE . C101558 Stage 1 Airfoil Corrosion Samples Figure 633 (Sheet 1 of 4) 72-00-00 ENGINE .INSPECTION/CHECK Page 657 Jan 24/2006 .PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3045542 AREA A NOTE: BORESCOPE AT 1500 FH. C101559 Stage 2 Airfoil Corrosion Samples Figure 633 (Sheet 2) 72-00-00 ENGINE .PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3045542 0.125 IN. MAXIMUM AREA A NOTE: REPLACE BLADE WITHIN 50 FH.INSPECTION/CHECK Page 658 Jan 24/2006 . PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO.INSPECTION/CHECK Page 659 Jan 24/2006 . 3045542 AREA B AREA B REPLACE BLADE WITHIN 500 FH AREA B AREA A AREA A AND AREA B REPLACE BLADE WITHIN 10 FH PER WORSE CONDITION C101563 Stage 3 Airfoil Corrosion Samples Figure 633 (Sheet 3) 72-00-00 ENGINE . 3045542 REPLACE BLADE WITHIN 10 FH C101566 Stage 4 Airfoil Corrosion Samples Figure 633 (Sheet 4) 72-00-00 ENGINE .PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO.INSPECTION/CHECK Page 660 Jan 24/2006 . If major rubbing is present. every 200 FH maximum (Ref. A. may be seen located in the center and / or at the trailing edge area of the shroud segment. Slight changes to surface texture may be visible. 634) v Borescope inspection shows silver-grey heat discoloration. 3045542 (a) Initial borescope inspection to be made at 1500 hours or more of accumulated service. refer to Category 5. (2) HP Turbine Shroud Segment Borescope Inspection Criteria (Ref. NOTE: 2.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 636) 72-00-00 ENGINE . for additional HSI recommendations. Refer to Para. TABLE 606. Hairline axial crack(s) may appear in the thermal barrier coating. Fig. (b) Category 2: Subsequent borescope inspection interval. (a) Category 1: Subsequent borescope inspection interval.INSPECTION/CHECK Page 661 Jan 24/2006 . to Table 606) NOTE: The following Table provides a summary of the maintenance action required for each shroud segment deterioration category. it is necessary to inspect the entire shroud circumference to determine the worst condition. Fig. every 1000 FH maximum (Ref. with no axial cracks. Therefore. The presence of burnt HP vanes may help locate shrouds that are in a more advanced state of deterioration. (c) Category 3: Subsequent borescope inspection interval. The presence of hot streaks can result in wide variation of shroud deterioration on any one engine. NOTE: Witness marks from slight HPT blade tip rubbing are acceptable. Maintenance summary for HP Turbine Shroud Segment Categories Borescope Inspection Interval 1 Every 1000 FH Maximum 2 Every 500 FH Maximum 3 Every 200 FH Maximum Categories Replacement Required 4 Within 50 FH Maximum 5 Within 10 FH Maximum NOTE: 1. 635) v Borescope inspection shows minor oxidation characterized by silver-grey heat discoloration and/or initiation of dark gray spotting. every 500 FH maximum (Ref. Fig. T.P.P.P. BLADE BORESCOPE VIEW IN THE ENGINE C75121 HPT Shroud Segments .P. 3045542 LEADING EDGE TRAILING EDGE H.T.Category 1: Borescope Required within Next 1000 FH Maximum.INSPECTION/CHECK Page 662 Jan 24/2006 . BLADE H.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO.T.T. Figure 634 (Sheet 1 of 2) 72-00-00 ENGINE . SHROUD SEGMENT LEADING EDGE LEADING EDGE H. SHROUD SEGMENT ON BENCH TRAILING EDGE H. Category 1: Borescope Required within Next 1000 FH Maximum.P. SHROUD SEGMENT ON BENCH C88430A HPT Shroud Segments .PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3045542 LEADING EDGE LEADING EDGE TRAILING EDGE TRAILING EDGE LEADING EDGE LEADING EDGE TRAILING EDGE TRAILING EDGE H.T. Figure 634 (Sheet 2) 72-00-00 ENGINE .INSPECTION/CHECK Page 663 Jan 24/2006 . P. 3045542 TRAILING EDGE H. Figure 635 (Sheet 1 of 3) 72-00-00 ENGINE .P.T.T.Category 2: Borescope Required within Next 500 FH Maximum. BLADE H.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO.T. BLADE BORESCOPE VIEW IN THE ENGINE C75124 HPT Shroud Segments . SHROUD SEGMENT LEADING EDGE LEADING EDGE H.INSPECTION/CHECK Page 664 Jan 24/2006 .P. T. SHROUD SEGMENT ON BENCH C88431 HPT Shroud Segments . 3045542 CRACK LEADING EDGE MINOR OXIDATION TRAILING EDGE H.Category 2: Borescope Required within Next 500 FH Maximum.INSPECTION/CHECK Page 665 Jan 24/2006 .PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. Figure 635 (Sheet 2) 72-00-00 ENGINE .P. INSPECTION/CHECK Page 666 Jan 24/2006 . 3045542 LEADING EDGE TRAILING EDGE LEADING EDGE TRAILING EDGE LEADING EDGE TRAILING EDGE H.Category 2: Borescope Required within Next 500 FH Maximum. SHROUD SEGMENT ON BENCH C98171 HPT Shroud Segments .PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. Figure 635 (Sheet 3) 72-00-00 ENGINE .P.T. v Erosion / oxidation within the limits shown in figure 637 sheet 3. Eroded / oxidized shroud segments are normally located around bottom dead center (BDC). is acceptable.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. To keep an engine in service after components have deteriorated. in excess of the maximum allowable limits. 638) 72-00-00 ENGINE . ranging from silver-grey to dark-grey. If major rubbing is present. NOTE: 4. refer to Category 5. Fig. and/or darker and rougher surface texture across entire shroud length. more than the recommended economical criteria. If major rubbing is present. steps at adjacent shroud ends. Witness marks from slight HPT blade tip rubbing are acceptable. and causes the gap between two adjacent shroud segments to increase. NOTE: 2. more than the recommended economical criteria.INSPECTION/CHECK Page 667 Jan 24/2006 . The oxidation is characterized by heat discoloration. NOTE: 2. or completely missing thermal barrier coating. can possibly increase the cost of subsequent repairs / refurbishment because of the adverse effect on downstream components. NOTE: 3. can possibly increase the cost of subsequent repairs / refurbishment because of the adverse effect on downstream components. located at the center and / or trailing edge area of the shroud segment. will damage the turbine support case (cracking and burning of the HP shroud attachment rim). Completely missing thermal barrier coating may be difficult to see through borescope unless when compared to adjacent shrouds that are not missing coating. refer to Category 5. (e) Category 5: HP Turbine Shroud Segment replacement within next 10 FH maximum (Ref. Operating the engine with burnt areas on the shroud segments. NOTE: 5. Fig. 3045542 v Borescope inspection shows curling and / or oxidation. Visually check for increased tip clearances over individual shrouds. (d) Category 4: HP Turbine Shroud Segment replacement within next 50 FH maximum (Ref. Thermal barrier coating with partial coating delamination and / or multiple small or long axial cracks. Erosion / oxidation of the HP shroud front area results in the rim becoming thin (knife edge). 637) v Borescope inspection reveals curling and / or heavy oxidation with missing pieces of thermal barrier coating. NOTE: 1. To keep an engine in service after components have deteriorated. NOTE: 1. Borescope inspection is to be carried out prior returning to service. Immediate removal is required if the borescope inspection of downstream rotating components shows evidence of debris impact. an HSI is recommended for economic reasons. SHROUD SEGMENT ON BENCH C75128 HPT Shroud Segments .INSPECTION/CHECK Page 668 Jan 24/2006 . 3045542 LEADING EDGE HEAVY OXIDATION MATERIAL MISSING NUMEROUS CRACKS TRAILING EDGE H.T. Figure 636 (Sheet 1 of 5) 72-00-00 ENGINE .P.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO.Category 3: Borescope Required within Next 200 FH Maximum. Figure 636 (Sheet 2) 72-00-00 ENGINE .T.Category 3: Borescope Required within Next 200 FH Maximum. 3045542 LEADING EDGE CRACKS OXIDATION TRAILING EDGE H. SHROUD SEGMENT ON BENCH C88432 HPT Shroud Segments .P.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO.INSPECTION/CHECK Page 669 Jan 24/2006 . PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO.T. SHROUD SEGMENT ON BENCH C98188 HPT Shroud Segments .INSPECTION/CHECK Page 670 Jan 24/2006 . Figure 636 (Sheet 3) 72-00-00 ENGINE .Category 3: Borescope Required within Next 200 FH Maximum. 3045542 LEADING EDGE TRAILING EDGE LEADING EDGE TRAILING EDGE H.P. P.T.Category 3: Borescope Required within Next 200 FH Maximum. BLADE TIP PARTIAL THERMAL BARRIER COATING DELAMINATION C88425 HPT Shroud Segments . Figure 636 (Sheet 4) 72-00-00 ENGINE .PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO.INSPECTION/CHECK Page 671 Jan 24/2006 . 3045542 H. SHROUD H.P.T. Figure 636 (Sheet 5) 72-00-00 ENGINE . 3045542 CURLING / EROSION B TRAILING EDGE LEADING EDGE CURLING / EROSION VIEW B C88424 HPT Shroud Segments .INSPECTION/CHECK Page 672 Jan 24/2006 .Category 3: Borescope Required within Next 200 FH Maximum.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3045542 LEADING EDGE CRACK MISSING COATING TRAILING EDGE H.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. SHROUD SEGMENT ON THE BENCH C88433 HPT Shroud Segments .INSPECTION/CHECK Page 673 Jan 24/2006 .P.T.Category 4: Shroud Replacement Required Within Next 50 FH Maximum Figure 637 (Sheet 1 of 3) 72-00-00 ENGINE . P.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3045542 LEADING EDGE TRAILING EDGE LEADING EDGE TRAILING EDGE H.Category 4: Shroud Replacement Required Within Next 50 FH Maximum Figure 637 (Sheet 2) 72-00-00 ENGINE .INSPECTION/CHECK Page 674 Jan 24/2006 .T. SHROUD SEGMENT ON BENCH C98189 HPT Shroud Segments . Category 4: Shroud Replacement Required Within Next 50 FH Maximum Figure 637 (Sheet 3) 72-00-00 ENGINE . 0.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. (6.250 IN. ADJOINING SEGMENTS VIEW A A EROSION / OXIDATION C32405B HPT Shroud Segments . 3045542 EROSION / OXIDATION 0.INSPECTION/CHECK Page 675 Jan 24/2006 .250 IN.35 MM) MAX.35 MM) MAX. (6. Category 5: Shroud Replacement Required Within Next 10 FH Maximum Figure 638 (Sheet 1 of 2) 72-00-00 ENGINE . BLADE TIP CRACK H.P. 3045542 H.T. BLADE TIP RUBBING HEAVY OXIDATION BORESCOPE VIEW IN THE ENGINE C88435 HPT Shroud Segments . BLADE LEADING EDGE H.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO.P.T.P.INSPECTION/CHECK Page 676 Jan 24/2006 .T. 3045542 LEADING EDGE TRAILING EDGE H. SHROUD SEGMENT ON BENCH C98190 HPT Shroud Segments .Category 5: Shroud Replacement Required Within Next 10 FH Maximum Figure 638 (Sheet 2) 72-00-00 ENGINE .INSPECTION/CHECK Page 677 Jan 24/2006 .T.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO.P. NOTE: 4. Adjustment/Test) there is no need to carry out a hot section inspection regardless of the amount of damage. exposing the turbine support case attachment rim. G.350 mm) of material missing and wide open cracks are acceptable. for additional HSI recommendations. To keep an engine in service after components have deteriorated. (6. Trailing edges with up to 0. Visually check for increased tip clearances over individual shrouds. with missing pieces of thermal barrier coating. LP Turbine Stator (Ref. providing the structural integrity of the vanes is not affected. However.250 in. NOTE: Refer to Para. LP Turbine Blades (1) Inspection Criteria 72-00-00 ENGINE . Corrosion (shown as burn through to the core) are not acceptable and an HSI is recommended. as only cracks can be repaired.INSPECTION/CHECK Page 678 Jan 24/2006 . Providing the ITT/T6 is below the maximum acceptable limit (Ref. NOTE: 2. A. F.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 639 and 640). and/or darker and rougher surface texture across entire shroud length. more than the recommended economical criteria. Completely missing thermal barrier coating may be difficult to see through borescope unless when compared to adjacent shrouds that are not missing coating. can possibly increase the cost of subsequent repairs / refurbishment because of the adverse effect on downstream components. Fig. 3045542 v Borescope inspection reveals major rubbing with curling and / or heavy oxidation. steps at adjacent shroud ends. (1) Inspection Criteria (a) Burnt areas of the LP stator vanes produce an increase in flow area. NOTE: 1. or completely missing thermal barrier coating. Shroud segment trailing edge may also be completely missing. it must be understood that keeping the engine in service may increase HSI costs. Borescope inspection is to be carried out prior returning to service. NOTE: 3. Immediate removal is required if the borescope inspection of downstream rotating components shows evidence of debris contact. decrease LP compressor speed (NL) and increase ITT/T6. Operating the engine with the shroud segments in excess of the maximum allowable limits described above will damage the turbine support case (cracking and burning of the HP shroud attachment rim). INSPECTION/CHECK Page 679 Jan 24/2006 . C107964 LP Turbine Stator .Borescope Inspection Reference Points Figure 639 72-00-00 ENGINE . LEADING EDGE 1.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO.0 INCH APPROX.4 INCH APPROX. 3045542 TRAILING EDGE 1. DIM FOR BORESCOPE C107975 LP Turbine Vane . 3045542 BORE SCOP E 0.INSPECTION/CHECK Page 680 Jan 24/2006 .PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO.Borescope Inspection Reference Dimension Figure 640 72-00-00 ENGINE .375 IN REF. 54 mm) wide from the leading edge. Adjustment/Test).07 mm) deep maximum. dent or pit 0. This condition is unacceptable. dent or pit 0. seen using a borescope. (b) Airfoil core corrosion can be seen as blistering or erosion on the convex or concave side of the blade (usually near the tip at the leading edge).003 in. NOTE: Area c includes an area 0. The LP Turbine blades can continue in service. (b) area b (leading edge): a maximum of one nick. dent or pit 0. 3045542 (a) The condition of LP turbine blade airfoils and tips is critical to obtain rated power.54 mm) wide from the trailing edge.and Second-stage Power Turbine Vanes (1) Inspection Criteria 72-00-00 ENGINE . First.025 in. Subsequent inspections must be carried out at intervals which must not exceed 600 flight hours. (e) area e (leading edge tip): erosion up to a 0. Fig. defects shown in Figure 641 are acceptable. (0. for additional HSI recommendations. increase interturbine temperature (ITT/T6) toward the maximum acceptance limit (Ref. Even if ITT/T6 is below the maximum limit an HSI is recommended for economic reasons if defects are beyond the limits shown in Figure 641. providing they meet the following criteria (Ref.005 in. (0.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO.INSPECTION/CHECK Page 681 Jan 24/2006 .12 mm) deep maximum. Adjustment/Test). (2. A. (d) area d (root area): a maximum of one nick. If defects are in excess of those shown in Figure 642.100 in. NOTE: Area d includes an area 0. an HSI is recommended to be carried out.12 mm) deep maximum.12 mm) deep maximum.005 in. H.100 in. (2. Alternately. providing their condition is monitored by further borescope inspections and power assurance check (Ref.005 in.54 mm) wide from the platform surface. Most significant blade tip defects (rubs and oxidation). 643): (a) area a (airfoil): a maximum of three nicks. (0. (2. (0. NOTE: (2) Refer to Para.100 in. and the disk assembly must be replaced within 50 flight hours. (c) area c (trailing edge): a maximum of one nick.63 mm) tip radius. dents or pits 0. (0. NOTE: Area b includes an area 0. C32423A LP Turbine Blade .INSPECTION/CHECK Page 682 Jan 24/2006 . 3045542 HEAVY RUBBING AND BURNT MATERIAL ACCEPTABLE PROVIDING ENGINE PERFORMANCE IS WITHIN LIMITS TRAILING EDGE LEADING EDGE COATING LOSS NOTE: THE ABOVE DEFECTS ARE ACCEPTABLE FOR FURTHER SERVICE.Acceptable Damage May Be Repairable By Blade Tip Grinding Figure 641 72-00-00 ENGINE . THE EXTENT OF THE DEFECT(S) MUST BE RECORDED AND MONITORED BY ADDITIONAL BORESCOPE INSPECTIONS.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. (12.7 MM) OR 36% 0.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO.56 MM) APPROX EROSION. (6. (20.Non-repairable Damage Figure 642 72-00-00 ENGINE .(6) FOR RECOMMENDED SERVICE ACTION.32 MM) 0. (35. BURNT MATERIAL OR FOREIGN OBJECT DAMAGE (FOD) BLISTERING CAUSED BY CORROSION NOTE: INDIVIDUAL DEFECTS EXCEEDING THE ABOVE LIMITS ARE NOT ACCEPTABLE.800 IN.INSPECTION/CHECK Page 683 Jan 24/2006 .35 MM) OR 31% BURNT OR MISSING MATERIAL BLISTERING OR EROSION CAUSED BY CORE CORROSION 0. (6. THE DIMENSIONS CANNOT BE ACCURATELY MEASURED WHEN USING A BORESCOPE THERFORE THE EXTENT OF THE DAMAGE MAY BE ESTIMATED AS A PERCENTAGE OF AIRFOIL TIP LENGTH AND TRAILING EDGE HEIGHT.250 IN. SEE PARA.250 IN. 3045542 0.35 MM) OR 18% TRAILING EDGE LEADING EDGE 1.500 IN.400 IN. C32424B LP Turbine Blade . 54 mm) WIDE C C VIEW A C71325 LP Turbine Blade Visual Inspection Figure 643 72-00-00 ENGINE . 3045542 a TRAILING EDGE LEADING EDGE e c 0.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. WIDE (2.100 in.54 mm) A d b DETAIL 0. (2.100 in.INSPECTION/CHECK Page 684 Jan 24/2006 . and second-stage PT blades decreases LP compressor speed (NL). Fig 644). If condition worsens. 72-00-00 ENGINE .g. is found. increases HP compressor speed (NH) and interturbine temperature (ITT/T6). investigate associated oil nozzle. Fig 644). excessive foreign object damage (FOD) or blade distortion are unacceptable).g. First. there is no need to change the PT assembly irrespective of the amount of damage. I. NOTE: Presence of scoring usually indicates poor lubrication. (b) Light shallow scoring. (a) An engine may be returned to service after PT blade fracture(s) providing: 1 The inspection required to determine if vibration produced by PT blade fracture(s) was sufficient to cause secondary damage requiring return of the engine to an overhaul facility detailed in 72-03-00. If corrosion of the airfoil base material (seen as blistering). the disk assembly must be replaced within 50 flight hours. Gear Teeth Inspection A.INSPECTION/CHECK Page 685 Jan 24/2006 . Check gear regularly once scoring is evident. (c) Corrosion seen as pitting or coating loss is acceptable for continued services (Ref. (b) Increased tip clearance of the first. If these parameters stay within limits. excessive foreign object damage (FOD) and missing or burnt material are unacceptable). Refer to Figure 645 to determine acceptable accessory gearbox angle drive gear teeth spalling. missing material. there is no need to change the stator(s) irrespective of the amount of damage. providing the structural integrity of the components is not affected (e. Acceptable Conditions (a) Small clusters of spalling at one extremity of the tooth width or in a narrow band along the tooth on less than 1⁄2 tooth length. Providing NL stays within limits or the engine does not surge. 3045542 (a) Damaged areas on the first-stage and/or second-stage PT stator (vane) produce an increase in flow area which increases LP compressor speed (NL) and lowers interturbine temperature (ITT/T6). 1 11. INSPECTION/CHECK is carried out.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO.and Second-stage Power Turbine (PT) Blades (1) Inspection Criteria (Ref. wide open cracks. cracks. 2 The Power Turbine Rotating Balancing Assembly is replaced before the first engine run. unless the structural integrity of the vanes is affected (e. Inspection Criteria Figure 644 72-00-00 ENGINE . 3045542 CORROSION PITTING / COATING LOSS ACCEPTABLE CONDITION BLISTERING CONDITION / NOT ACCEPTABLE REPLACE BLADE WITHIN 50 FHR C106030 First and Second Stage Power Turbine Blades .PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO.INSPECTION/CHECK Page 686 Jan 24/2006 . PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3045542 A B DETAIL DETAIL B A C62117 Accessory Gearbox Angle Drive Gears .INSPECTION/CHECK Page 687 Jan 24/2006 .Unacceptable Teeth Spalling Figure 645 72-00-00 ENGINE . Fig. (a) Spalling in a narrow band along whole width of tooth root or dispersed throughout contact area.6 mm). Cracks in the turbine support case inner wall.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. (4) Cracks are recorded (Ref. (6) Subsequent inspections are done at intervals depending on the rate of increase and level of deterioration seen. Check gear regularly. Cracks in Turbine Support Case Inner Wall A. 646. (c) Rough tooth contact surface due to excessive wear. Any deviation is caused by incorrect tooth contact. (5) An additional inspection of the affected area is carried out at an interval not to exceed 300 flight hours. Turbine Support Case . Sheet 3). investigate associated oil nozzle. Table 607). 12. Check gear regularly. (2) Not more than 6 cracks are found. NOTE: Discoloration usually indicates poor lubricating and may lead to scoring. NOTE: 1. (3) There are no cracks on the same side of adjacent bosses (Ref. B. NOTE: 2. Ideal tooth contact is a centrally-located strip on face of tooth. then spalling. Fig.INSPECTION/CHECK Page 688 Jan 24/2006 . 3045542 (c) Discoloration. TABLE 607. (d) Incorrect tooth contact pattern. Non-acceptable Conditions NOTE: Replace affected module (RGB or Turbomachinery) if any non-acceptable condition is evident. Incorrect tooth contact pattern may lead to spalling because pressure surfaces between teeth are either concentrated on a smaller area along teeth width and/or off-center along depth. found when carrying out a borescope inspection of the LP turbine blades and first-stage power turbine stator (Ref. with raised material at tooth extremities. are acceptable providing: (1) Crack length does not exceed 4.Crack Record Boss Location Length/ Flight Hours Length/ Flight Hours Length/ Flight Hours Length/ Flight Hours Length/ Flight Hours Length/ Flight Hours Length/ Flight Hours 1 72-00-00 ENGINE . 646). If condition worsens. (b) Deep scoring (root/tip direction) across tooth contact surface. (101. but not later than 300 flight hours.0 in. 3045542 TABLE 607.Crack Record (Cont’d) Boss Location Length/ Flight Hours Length/ Flight Hours Length/ Flight Hours Length/ Flight Hours Length/ Flight Hours Length/ Flight Hours Length/ Flight Hours 2 3 4 5 6 7 8 9 10 11 12 NOTE: No. v The breaking away of small areas of the ring is acceptable or loose pieces of the ring can be cut away and discarded provided there is a minimum of 2. Turbine Support Case .PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. may propagate through the gas generator case wall. (b) Circumferential cracks adjacent to the weld are acceptable. The consequences of a crack through the gas generator case wall is that the case will be non-repairable at next overhaul or major refurbishment. Cracks in Gas Generator Case Firewall Support Ring NOTE: A. Cracks extending into the continuous seam of spot weld (original support ring) and cracks extending through the tack welds (repaired gas generator support ring).80 mm) of material on each side of any support brackets. 72-00-00 ENGINE .INSPECTION/CHECK Page 689 Jan 24/2006 . in the portion resting on the the gas generator case is acceptable.0 in. installed on the firewall support ring. (c) Axial cracks are acceptable provided that: 1 The breaking away of small areas of the ring. 13. Visual Inspection (1) Visually inspect firewall support ring for cracks as follows: (a) Cracks radiating outwards from bolt holes are acceptable. (50. 1 boss TDC and remaining bosses are numbered counterclockwise from rear of engine. The decision to remove the engine or continue in service should be based on Operator experience and economic considerations. Inspection Figure 646 (Sheet 1 of 3) 72-00-00 ENGINE .PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO.INSPECTION/CHECK Page 690 Jan 24/2006 . 3045542 A a THERMOCOUPLE BOSSES C32863 Turbine Support Case Inner Wall . INSPECTION/CHECK Page 691 Jan 24/2006 .PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO.6 mm) MAX (TYP) AREA a AREA a AREA a C32861 Turbine Support Case Inner Wall . (101. 3045542 3. (96.Inspection Figure 646 (Sheet 2) 72-00-00 ENGINE .52 mm) (TYP) 4 IN.8 IN. PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO.INSPECTION/CHECK Page 692 Jan 24/2006 .Inspection Figure 646 (Sheet 3) 72-00-00 ENGINE . 3045542 AREA a AREA a C32862 Turbine Support Case Inner Wall . Equipment and Supplier Tools The fixtures.2 off 72-00-00 ENGINE . (19 liters) capacity . refer to the CONSUMABLE MATERIALS section at the beginning of this manual. Engine Parts Detergent. equipment and supplier tools listed below are referred to in procedural text. Consumable Materials The consumable materials listed below are referred to in this section.1 off Containers. 5 gal.2 off Centrifugal pump. Name PWC30128-15 PWC32677-300 PWC37771 PWC56502 Puller Cart. The importance of cleaning the engine regularly cannot be overemphasized.CLEANING/PAINTING Page 701 Jan 24/2006 . B. Petroleum Cleaner. SOME MATERIALS CAN BE DANGEROUS. General A. Compressor/Fuel Nozzle Wash Nozzle Wash Nozzle Fixtures. 2. (37.85 liters) per minute minimum flow rate . Tool No. This helps in the early detection of leaks and exterior deterioration. WARNING: 3. 3045542 ENGINE . For more data.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. Water-based Alkaline Gel Special Tools Special tools are identified in procedural text by part number in parentheses. Item No. Instructions and information necessary for cleaning and painting the engine are provided in this section. Name Air supply valve . Name PWC03-001 PWC05-005 PWC05-050 PWC05-089 PWC05-295 PWC11-001 PWC11-010 PWC11-027 PWC11-031 PWC11-034 Engine Oil Emulsifier Nitrogen Lockwire Lockwire (may be used instead of PWC05-089) Cleaning Agents Methanol Solvent. 4. 10 gal.CLEANING/PAINTING 1. READ THE MATERIAL SAFETY DATA SHEETS BEFORE YOU USE THESE MATERIALS. PRECAUTIONS FOR SAFE HANDLING. WHEN USING COMPRESSED AIR FOR DRYING. low pressure. EXPLOSION. Wash nozzle (PWC37771) is recommended to be used to wash the turbine area. DO NOT ATTEMPT TO WASH AN ENGINE THAT IS STILL HOT OR RUNNING. PHYSICAL/CHEMICAL CHARACTERISTICS. HEALTH HAZARD DATA. External Wash WARNING: REFER TO THE MANUFACTURER’S MATERIAL SAFETY DATA SHEETS FOR CONSUMABLE MATERIALS INFORMATION SUCH AS: HAZARDOUS INGREDIENTS. Compressor Wash (1) General NOTE: A compressor wash can be carried out only on engines incorporating wash nozzle P/N 3121033-01. Tergit (PWC11-031) is recommended to be used as an alternative to petroleum solvent when the use of this product is restricted by local environmental and/or health legislation. FIRE. (1) Wash engine using water or petroleum solvent (PWC11-027). NOTE: (2) Thoroughly rinse with clean water if solvent gel or cleaner is used. 3045542 Name Fluid shutoff valve . Dry with clean. REGULATE PRESSURE TO 29 psig (200 kPa) OR LESS. 72-00-00 ENGINE .1 off Recirculation pump with relief valve . WEAR GOGGLES OR FACE SHIELD TO PROTECT EYES.CLEANING/PAINTING Page 702 Jan 24/2006 . CAUTION: DO NOT USE GASOLINE OR SIMILAR TOXIC SUBSTANCES FOR EXTERNAL ENGINE CLEANING. (a) Washing removes salt. Engine Cleaning A. compressed air.1 off Tubing 5.2 off Hose Pressure gage . WARNING: (3) B. or detergent gel (PWC11-034) water emulsion or cleaner (PWC11-031).PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. dirt and other baked-on deposits that accumulate in the gas path and cause engine performance deterioration. REACTIVITY. USE AND CONTROL MEASURES. (4. (f) Depending upon the operating environment. Table 701 or Fig. 72-00-00 ENGINE . cover (3) using puller (PWC37651). washer (2). Fig. Desalination/Rinse Solutions AMBIENT TEMPERATURE WATER % by Vol. (e) Install bolt (8) and nut (7) to secure clamp holding oil tube to bracket. bracket (6). (c) A rinse wash uses the same solution (according to temperature) as the desalination wash (Ref. (b) Remove bolts (1). (3. Torque nut 36 to 40 lb. TABLE 701. NOTE: Figure 701 introduces an alternate method to determine the methanol requirement when mixing a desalination/rinse solution for use at temperatures below 0°C (32°F).07-4. Discard packing. 702) and bolt (8). Torque bolts 32 to 36 lb. bracket (6) and bolts (1). (d) A performance recovery wash uses cleaning agents (Ref.62-4. (e) The formula of the P&WC developed performance recovery solution WCT is shown in Table 704. washer (2). Table 701) and is used after a performance recovery wash to clean the gas path.in. (c) Lubricate packing (5) with engine oil (PWC03-001) and install on cover (3) or wash nozzle (4).07 Nm). (d) Install cover or wash nozzle. NOTE: Performance recovery washing must be carried out only when necessary to ensure residue does not build up in engine components. +2°C up +36°F up 100 Nil -25 to +2°C -13 to +36°F 50 50 Below -25°C Below -13°F 40 60 (2) Inspection Port Cover/Wash Nozzle . 3045542 (b) A desalination wash uses water or water/methanol (PWC11-010) (Ref. METHANOL % by Vol. 701) to remove salt and light deposits. or wash nozzle (4) using puller (PWC30128-15) and packing (5).in. The addition of cleaning agents is not recommended.52 Nm). Tables 702. the nature and frequency of washing are recommended to be in accordance with Chapter 05-20-00.Removal/Installation (a) Remove nut (7. 704 and 705) in the wash solution to remove deposits that cannot be dissolved by a desalination wash. 703.CLEANING/PAINTING Page 703 Jan 24/2006 . (g) Wash solution quantity requirements are contained in Table 706.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. CLEANING/PAINTING Page 704 Jan 24/2006 .PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO.Determining Methanol Requirement at Temperatures Below 0°C (32°F) Figure 701 72-00-00 ENGINE . 3045542 70% 60% METHANOL VOLUME 50% 40% 30% 20% 10% 0% 0 −10 −20 −30 −40 −50 −60 OAT ( o C) C33859 Desalination/Rinse Solution . (c) The use of Witconate HC-59B or P10-59B emulsifying agent (PWC05-005) (150 ml in 5 liters) is highly recommended to prevent fuel separation. (5) Wash Schedule Recommendations (a) Refer to Chapter 05-20-00. (a) Appearance: free from visible impurities. PHYSICAL/CHEMICAL CHARACTERISTICS. HEALTH HAZARD DATA. step (7)). 3045542 (3) Preparation of Desalination/Rinse Solutions (a) The minimum standard for water is drinking quality (Ref.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. Where no specific recommendation is provided. (7) Drinking Water Quality Requirements NOTE: Since drinking water quality varies from place to place and from season to season.CLEANING/PAINTING Page 705 Jan 24/2006 .0 inclusive. (6) Wash Solution Quantity Requirements (a) Refer to Table 706. FIRE. (b) Biodegradable cleaning agents (Ref. PRECAUTIONS FOR SAFE HANDLING. (c) PH value: 6. 72-00-00 ENGINE . REACTIVITY. step (7)). WARNING: REFER TO MANUFACTURER’S MATERIAL SAFETY DATA SHEETS FOR CONSUMABLE MATERIALS INFORMATION SUCH AS: HAZARDOUS INGREDIENTS. the proportion of cleaning agent should be as shown in the applicable table. EXPLOSION. (4) Preparation of Performance Recovery Solutions (a) The minimum standard for water is drinking quality (Ref. (e) Sulfates: 10 ppm (mg/liter) maximum. Table 705) are recommended to be used.0 to 8. (d) Chlorides: 15 ppm (mg/liter) maximum. these requirements are provided as a guide only. (b) Total solids: 175 ppm (mg/liter) maximum. Solution strength must be as per manufacturer/supplier’s recommendation. USE AND CONTROL MEASURES. Removal/Installation Figure 702 72-00-00 ENGINE .PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO.CLEANING/PAINTING Page 706 Jan 24/2006 . 3045542 5 3 1 1 6 2 4 7 8 C12709A Inspection Port Cover/Wash Nozzle . PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3045542 Key to Figure 702 1. 2. 3. 4. 5. 6. 7. 8. Bolt Washer Cover Wash Nozzle Packing Bracket Nut Bolt TABLE 702, CLIX (PWC11-001), Almon AL-333 (PWC11-001A), Magnus 1214 (PWC11-001B), B & B 3100 (PWC11-001C), Turco 5884 (PWC11-001G) and WCT Performance Recovery Solutions AMBIENT TEMPERATURE CLEANING AGENT % by Vol. FUEL % by Vol. METHANOL % by Vol. WATER % by Vol. +2°C up +36°F up 25 Nil Nil 75 -25 to +2°C -13 to +36°F 25 15 20 40 Below -25°C Below -13°F 25 15 40 20 EXAMPLE: Typical mixture proportions using B & B 3100 at ambient temperature of -25 to + 2°C (-13 to +36°F). CAUTION: ADD 150 ml OF WITCONATE EMULSIFYING AGENT (PWC05-005) AND MIX SOLUTION THOROUGHLY BEFORE USE TO PREVENT FUEL SEPARATION. B & B 3100 25% by Vol = 1250 ml in 5 liters (1.33 US gal.) Fuel 15% by Vol = 750 ml Methanol 20% by Vol = 1000 ml Water 40% by Vol = 2000 ml Total 100% by Vol = 5000 ml or 5 liters (1.33 US gal.) 72-00-00 ENGINE - CLEANING/PAINTING Page 707 Jan 24/2006 PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3045542 TABLE 703, Turco 4217 (PWC11-001F) (concentrate) and Ardrox 624 (PWC11-001H) (concentrate) - Performance Recovery Solutions AMBIENT TEMPERATURE CLEANING AGENT Qty (ml) FUEL Qty (ml) METHANOL Qty (ml) WATER Qty (ml) CAUTION: ADD 150 ML OF WITCONATE EMULSIFYING AGENT (PWC05-005) AND MIX SOLUTION THOROUGHLY BEFORE USE TO PREVENT FUEL SEPARATION. +2°C up +36°F up 200 2000 Nil 2800 -25 to +2°C -13 to +36°F 200 2000 100 1800 Below -25°C Below -13°F 200 2000 1800 1000 TABLE 704, WCT Performance Recovery Wash Solution Developed by P&WC MATERIAL QUANTITY Witconate HC59B or P10-59B (PWC05-005) 2 parts Carbitol (PWC11-001) 4 parts Triethanolamine (PWC11-001) 1 part TABLE 705, Ardrox 6345 (PWC11-003), Ardrox 6367 (PWC11-003B) (previously identified as Turboclean 2), Ardrox 6368 (PWC11-003C) (previously identified as Turboclean 2 RTU), ZOK27 (PWC11-003D), and B & B TC100 (PWC11-003E) Biodegradable Performance Recovery Solutions AMBIENT TEMPERATURE CLEANING AGENT % by Vol. METHANOL % by Vol. WATER % by Vol. +2°C up +36°F up 20 NIL 80 -25 to +2°C -13 to +36°F 20 30 50 Below -25°C Below -13°F 20 40 40 NOTE: Ardrox 6368 (PWC11-003C) is used undiluted at temperatures above +2°C (36°F). This product must not be used below this temperature. 72-00-00 ENGINE - CLEANING/PAINTING Page 708 Jan 24/2006 PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3045542 TABLE 706, Wash Solution Quantity Requirements TYPE OF WASH LITERS US GALLONS Desalination 19 5 Rinse 19 5 Performance Recovery 10 2.66 (8) Demineralized Water Quality Requirements (a) Appearance: free of suspended solids. (b) Total solids: 10 ppm (mg/liter) maximum. (c) Specific conductance: 11 micro-ohms/cm maximum. (d) Silica content: 3 ppm (mg/liter) maximum. (e) PH value: 5.0 to 7.5 inclusive. (f) (9) Intake filter not coarser than 10 microns. Equipment Required (a) Compressor wash nozzle P/N 3121033-01. (b) Compressed air or nitrogen (PWC05-050) supply, regulated up to 50 psig (345 kPa). (c) Alternate Fluid Supply Systems 1 Compressor wash cart (PWC32677-300) a 2 This cart contains the components required to enable wash fluid to be supplied to the engine at the specified rate and pressure. Individual components (Ref. Fig. 703) a Two stainless steel containers, 5 US gallons (19 liters) capacity, each capable of withstanding up to 80 psi (550 kPa) working pressure. b A mechanical agitator, or recirculation pump with relief valve, for mixture agitation. c One pressure gage located in air delivery line. d Two air supply valves. e Two fluid shut-off valves. f Suitable tubing to interconnect components. Valve and tubing connections to be 0.3125 in. (8 mm) ID minimum. 72-00-00 ENGINE - CLEANING/PAINTING Page 709 Jan 24/2006 PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3045542 (10) g Wash nozzle connection having a 0.5625-18 UNJF thread. h Two flow control valves for use with recirculating pump. i If required, a centrifugal pump with flow rate of 10 gallons (37.85 liters) per minute minimum, for use when drinking water pressure is below 30 psig (207 kPa). Desalination Wash Procedure NOTE: A hand wash of the engine air intake gas path up to and including the flanged joint is recommended to be carried out prior to starting the desalination wash procedure. Use a sponge dipped in a mixture of drinking quality water and detergent gel (PWC11-034) or equivalent mild detergent. After the wash, rinse with clean water to remove the soap residue. (a) Engine Not Running 1 Depending upon the ambient temperature, fill the wash tank or cart (PWC32677-300) with the appropriate mixture (Ref. Table 701). Alternately, at temperatures above +2°C (+36°F), use a suitable hose connected to drinking water tap. 2 Disconnect line from flow divider and dump valve drain. Install a cap on flow divider dump valve. (Ref. AMM). 3 Disconnect the P3 air pressure sensing tube at the intercompressor case end. Put a plastic bag over the end of the tube. NOTE: Disconnection of the P3 air pressure sensing tube from the intercompressor case is optional and is at the discretion of the operator. Operators whose experience indicates MFC pneumatic side contamination may want to cap the P3 line to prevent contamination of the MFC. 4 Connect compressed air or nitrogen supply (PWC05-050), regulated to 30 to 50 psig (207-345 kPa) to wash tanks or cart. If drinking water is used, connect through a centrifugal pump if water pressure is below 30 psig (207 kPa). 5 Remove plug (1, Fig. 704) and packing (2). Discard packing. 6 Install nozzle connection (3). Torque connection 110 to 120 lb.in. (12.43-13.56 Nm). 7 Connect pressurized tank, wash cart or drinking water supply to nozzle connection. CAUTION: WATER USED TO ACCELERATE ENGINE COOLING MUST BE DEMINERALIZED. 8 Before washing, ensure engine temperature is below 65°C (150°F) by one of the following methods: 72-00-00 ENGINE - CLEANING/PAINTING Page 710 Jan 24/2006 PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3045542 MECHANICAL AGITATOR CLEANING SOLUTION/STEEL TANK 5 U.S. GALS (19 LITERS) CAPACITY WORKING PR. 345 KPa (50 P.S.I.G.) AIR SUPPLY VALVE SHUT OFF VALVE PRESSURE GAGE VALVE VALVE RELIEF VALVE TO WASH NOZZLE AIR / NITROGEN PRESSURE SOURCE REGULATED UP TO 345 KPa (50 P.S.I.G.) RECIRCULATION PUMP AIR SUPPLY VALVE RINSE SOLUTION TANK 19 LITERS (5 U.S. GALS) CAPACITY WORKING PR. 345 KPa (50 P.S.I.G.) SHUT OFF VALVE C12546A Wash Rig - Schematic Figure 703 72-00-00 ENGINE - CLEANING/PAINTING Page 711 Jan 24/2006 PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3045542 a Allowing engine time to cool. b Carrying out a dry motoring run and injecting demineralized water through the wash nozzle. NOTE: c An engine temperature below 65°C (150°F) ensures that inadvertent use of hard water does not result in precipitation of deposits. Forced air cooling: An air conditioning unit can be used to accelerate engine cooling temperature. 9 Ensure aircraft bleed air is OFF. CAUTION: DO NOT MOTOR FOR MORE THAN 30 SECONDS; OBSERVE STARTER COOLING PERIOD (REF. STARTER MANUFACTURER’S MANUAL). 10 Carry out a dry motoring run (Ref. AMM). 11 When NH reaches 5%, inject water or water/methanol as applicable, into engine. 12 Stop motoring run after 30 seconds (Ref. AMM). 13 Shut off water or water/methanol when NH reaches 5%. 14 Disconnect pressurized tank, cart or drinking water supply from nozzle connection. 15 Remove nozzle connection. 16 Lubricate packing (2) with engine oil (PWC03-001) and install on plug (1). 17 Install plug. Torque plug 110 to 120 lb.in. (12.43-13.56 Nm) and secure with lockwire (PWC05-089) or (PWC05-295). CAUTION: OBSERVE STARTER COOLING PERIOD (REF. STARTER MANUFACTURER’S MANUAL). 18 Carry out an additional 30-second dry motoring run (Ref. AMM) if water/methanol has been used. 19 Remove cap from dump valve and connect drain line to flow divider and dump valve (Ref. AMM). 20 Remove the plastic bag from the P3 air pressure sensing tube. Install the tube on the intercompressor case (Ref. 72-01-30, Removal/Installation). 72-00-00 ENGINE - CLEANING/PAINTING Page 712 Jan 24/2006 PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3045542 CAUTION: OBSERVE STARTER COOLING PERIOD (REF. STARTER MANUFACTURER’S MANUAL). 21 Switch ignition ON and start engine (Ref. AMM). Run at 80% NH for one minute or more to completely dry the engine. NOTE: 22 Engine ground run must be carried out as soon as possible to avoid corrosion problems. Shut down engine (Ref. AMM). (b) Engine Running NOTE: 1 2 Not recommended for operators whose experience indicate MFC pneumatic side contamination. Rig Calibration: one of the factors affecting the flow rate of the wash nozzle is the difference in height between the nozzle, when installed in the engine, and the wash rig. Therefore, the following procedure must be carried out to obtain the correct flow rate: a Remove plug (1, Fig. 705) and packing (2). Discard packing. b Remove bolts (3), washers (4), wash nozzle (5), using puller (PWC30128-15), and packing (6). Discard packing. c Install nozzle connection (7). Torque connection 110 to 120 lb.in. (12.43-13.56 Nm). d Using suitable hose, connect wash rig or cart to nozzle connection. e Adjust wash rig to obtain a flow rate of 4 to 5 liter/min (1.1-1.3 gal/min) with the wash nozzle at the same height as it was when installed in the engine. f Remove hose and nozzle connection. g Lubricate packing (6) with engine oil (PWC03-001) and install on wash nozzle (5). h Install wash nozzle (5), washers (4) and bolts (3). Torque bolts 36 to 40 lb.in. (4.07-4.52 Nm). i Lubricate packing (2) with engine oil (PWC03-001) and install on plug (1). j Install plug. Torque plug 110 to 120 lb.in. (12.42-13.56 Nm) and secure with lockwire (PWC05-089) or (PWC05-295). Wash Procedure 72-00-00 ENGINE - CLEANING/PAINTING Page 713 Jan 24/2006 PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3045542 2 1 3 C12547 Wash Nozzle Connection - Removal/Installation Figure 704 72-00-00 ENGINE - CLEANING/PAINTING Page 714 Jan 24/2006 PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3045542 Key to Figure 704 1. 2. 3. Plug Packing Connection CAUTION: DEMINERALIZED OR DISTILLED WATER MUST BE USED FOR WASHING WHEN ENGINE IS RUNNING. THE USE OF HARD WATER OR CLEANING AGENTS MAY RESULT IN THE PRECIPITATION OF DEPOSITS. a Fill wash tank or cart with demineralized or distilled water. NOTE: 20 to 25 liters (5.28-6.6 gal) of water are required per engine. b Open and secure left side engine cowl doors (Ref. AMM). c Remove plug (1, Fig. 704) and packing (2). Discard packing. d Install connection (3). Torque connection 110 to 120 lb.in. (12.42-13.56 Nm). WARNING: ENSURE HOSE IS ROUTED TO THE REAR AND DOWN TO AVOID INTERFERENCE WITH PROPELLER. CAUTION: ENSURE PART NO. OF NOZZLE USED FOR RIG CALIBRATION IS SAME AS THE NOZZLE TO BE USED FOR THIS WASH. e Using suitable hose, connect wash tank or cart to nozzle. f Start engine (Ref. AMM). g Ensure cabin air bleed is OFF. h Stabilize engine at disk with propeller feathered. CAUTION: FLOW RATES HIGHER THAN THOSE RECOMMENDED MAY FLOOD THE LUBRICATION SYSTEM WITH WATER. i Inject water at 4 to 5 liter/min (1.1-1.3 gal/min) for 5 minutes. NOTE: ITT indication may decrease during water injection. j After 5 minutes shut off water supply. k Allow engine to continue running for a further 2 minutes to purge drain lines and dry engine. NOTE: l Water may continue to flow from drains for approximately 20 to 30 seconds. Shut down engine (Ref. AMM). 72-00-00 ENGINE - CLEANING/PAINTING Page 715 Jan 24/2006 PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3045542 (11) m Disconnect hose from connection (3). n Remove connection (3). o Lubricate packing (2) using engine oil (PWC03-001) and install on plug (1). p Install plug. Torque plug 110 to 120 lb.in. (12.42-13.56 Nm) and secure with lockwire (PWC05-089) or (PWC05-295). q Close and secure cowl doors (Ref. AMM). Performance Recovery Wash Procedure NOTE: A hand wash of the engine air intake gas path up to and including the flanged joint is recommended to be carried out prior to starting the wash procedure. Use a sponge dipped in a mixture of drinking quality water and detergent gel (PWC11-034) or equivalent mild detergent. After the wash, rinse with clean water to remove the soap residue. (a) Depending upon ambient temperature, fill wash tank or wash cart (PWC32677-300) with 10 liters of cleaning solution (Ref. Tables 702, 703, 704 and 705) and fill rinse tank with 19 liters of solution (Ref. Table 701). (b) Disconnect the P3 air pressure sensing tube at the intercompressor case end. Put a plastic bag over the end of the tube. NOTE: DELETED (c) Connect compressed air or nitrogen (PWC05-050) supply, regulated to 30 to 50 psig (207-345 kPa) to wash tank or cart. (d) Remove plug (1, Fig. 704) and packing (2). Discard packing. (e) Install nozzle connection (3). Torque connection 110 to 120 lb.in. (12.43-13.56 Nm). (f) Connect pressurized tank or wash cart to nozzle connection. CAUTION: WATER USED TO ACCELERATE ENGINE COOLING MUST BE DEMINERALIZED. (g) Before washing, ensure engine temperature is below 65°C (150°F) by one of the following methods: 1 Allowing engine time to cool. 2 Carrying out a dry motoring run and injecting demineralized water through the wash nozzle. NOTE: An engine temperature below 65°C (150°F) ensures that inadvertent use of hard water does not result in precipitation of deposits. 72-00-00 ENGINE - CLEANING/PAINTING Page 716 Jan 24/2006 PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3045542 3 Forced air cooling: a An air conditioning unit can be used to accelerate engine cooling temperature. (h) Ensure aircraft bleed air is OFF. CAUTION: DO NOT MOTOR FOR MORE THAN 30 SECONDS; OBSERVE STARTER COOLING PERIOD (REF. STARTER MANUFACTURER’S MANUAL). WHEN USING WATER/METHANOL, CARRY OUT AN ADDITIONAL 30-SECOND DRY MOTORING RUN TO REMOVE VOLATILE FUMES BEFORE OPERATING ENGINE. (i) Carry out a dry motoring run (Ref. AMM). (j) When NH reaches 5%, inject cleaning solution into engine. (k) Stop motoring after 30 seconds. (l) Shut off cleaning solution when NH reaches 5%. (m) Allow cleaning solution to soak for 15 to 30 minutes. CAUTION: OBSERVE STARTER COOLING PERIOD (REF. STARTER MANUFACTURER’S MANUAL). (n) Carry out a dry motoring run (Ref. AMM). When NH reaches 5%, inject rinse solution (half the quantity) or drinking water from tap into engine. Stop motoring after 30 seconds. CAUTION: OBSERVE STARTER COOLING PERIOD (REF. STARTER MANUFACTURER’S MANUAL). (o) Carry out a dry motoring run. When NH reaches 5%, inject remaining rinse solution or drinking water into engine. Stop motoring after 30 seconds. (p) Shut off drinking water or rinse solution tank or wash cart when NH reaches 5%. (q) Disconnect pressurized tank, wash cart or drinking water supply from nozzle connection. (r) Remove nozzle connection. (s) Lubricate packing (2) with engine oil (PWC03-001) and install on plug (1). (t) Install plug. Torque plug 110 to 120 lb.in. (12.43-13.56 Nm) and secure with lockwire (PWC05-089) or (PWC05-295). CAUTION: OBSERVE STARTER COOLING PERIOD (REF. STARTER MANUFACTURER’S MANUAL). (u) Carry out an additional 30-second dry motoring run (Ref. AMM) if water/methanol has been used. 72-00-00 ENGINE - CLEANING/PAINTING Page 717 Jan 24/2006 PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO.Removal/Installation Figure 705 72-00-00 ENGINE . 3045542 6 5 4 3 1 7 2 C33441 Compressor Wash Nozzle .CLEANING/PAINTING Page 718 Jan 24/2006 . 3. AMM).CLEANING/PAINTING Page 719 Jan 24/2006 . Table 701) is used to wash turbines. 2. Install the tube to the intercompressor case (Ref.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 7. (c) Depending upon the operating environment. 72-01-30. (e) 1 Turbine wash can be performed using one of the two methods that follow. (d) Approximately 0. 6. Ref. 4. (b) Water or water/methanol (according to temperature.90 liters) will pass through the turbines during a 30-second motoring cycle. (x) Shut down engine (Ref. low pressure and power turbines. the nature and frequency of turbine washing is recommended to be in accordance with the Gas Path Wash recommended schedule per Chapter 05-20-00. AMM). CAUTION: OBSERVE STARTER COOLING PERIOD (REF. 3045542 Key to Figure 705 1. NOTE: Engine ground run must be carried out as soon as possible to avoid corrosion problems. Run at 80% NH for one minute or more to completely dry the engine. (w) Switch ignition ON and start engine (Ref. Turbine Wash (1) General (a) Turbine washing removes salt and sulphide deposits from the high pressure. a Method 1: 72-00-00 ENGINE . C. Plug Packing Bolt Washer Wash Nozzle Packing Connection (v) Remove the plastic bag from the P3 air pressure sensing tube. REMOVAL/ INSTALLATION).5 US gallons (1. 5. STARTER MANUFACTURER’S MANUAL). use a suitable hose connected to a drinking water tap. Chapter 05-20-00. (2) Turbine Wash Schedule Recommendations. . This nozzle is longer than PWC37771 and extends all the way to the HP turbine blade airfoil. WARNING: RESIDUAL VOLTAGE IN IGNITION EXCITER MAY BE DANGEROUSLY HIGH. 5 Install nozzle connection. b Method 2: This method includes wash nozzle PWC56502. connect through a centrifugal pump if water pressure is below 30 psig (207 kPa). at temperatures above +2°C (+36°F). regulated to 30 to 50 psig (207-345 kPa). Method 2 is recommended in areas where the HPT airfoil is exposed to harsh or marine environment. 3045542 This method includes wash nozzle PWC37771. (3) ensuring that RGB inscribed on tang is pointing towards the reduction gearbox. ALWAYS DISCONNECT COUPLING NUTS AT IGNITION EXCITER END FIRST. (b) Turbine Wash Procedure 1 Depending upon the ambient temperature. In addition. This nozzle goes through a short distance in the combustion chamber and gives a an effective washing of the HPT vanes and sufficient washing of the HPT blades.. REMOVAL/INSTALLATION). ALWAYS USE INSULATED TOOLS TO REMOVE COUPLING NUTS. (3) Method 1: (a) Equipment Required 1 A wash nozzle (PWC37771) installed in one of the igniter ports is used when washing turbines .CLEANING/PAINTING Page 720 Jan 24/2006 . Torque nozzle fingertight. B. DO NOT TOUCH OUTPUT CONNECTORS OR COUPLING NUTS WITH BARE HANDS.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. to wash tanks or cart. 2 Connect compressed air or nitrogen (PWC05-050) supply. fill the wash tank or cart with the appropriate mixture (Ref. the wash cart or containers and associated components listed in Subpara. 72-01-20. Fig. Discard gasket. 3 Remove the most accessible igniter (1. Alternately. step (9). If drinking water is used. It has been designed specially to give an effective washing of the HP turbine blade airfoil and downstream components. 72-00-00 ENGINE . are required if drinking quality water obtained directly from a tap at the correct pressure is not used. Table 701). refer to Gas Path Wash recommended schedule. 4 Install turbine wash nozzle. 706) and gasket (2) (Ref. ENSURE IGNITION IS SWITCHED OFF. b Carrying out a dry motoring run and injecting demineralized water through the wash nozzle. 72-00-00 ENGINE . wash cart or drinking water supply to nozzle connection. 7 Connect pressurized tank. into engine. wash cart or drinking water supply from nozzle connection. 8 Before washing. 9 Ensure aircraft bleed air is OFF. The delivery hose must be supported to avoid damage to the wash nozzle. CAUTION: OBSERVE STARTER COOLING PERIOD (REF.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. STARTER MANUFACTURER’S MANUAL). as applicable. 11 When NH reaches 5%. Forced air cooling: An air conditioning unit can be used to accelerate engine cooling temperature. 10 Carry out a dry motoring run (Ref. Adjustment/Test). 12 Stop motoring run after 30 seconds (Ref. CAUTION: WATER USED TO ACCELERATE ENGINE COOLING MUST BE DEMINERALIZED. OBSERVE STARTER COOLING PERIOD (REF. 3045542 6 Disconnect combustion chamber drain line to ecology tank and drain line from flow divider and dump valve drain. Install a cap on flow divider and dump valve drain (Ref. Adjustment/Test). NOTE: c An engine temperature below 65°C (150°F) ensures that the inadvertent use of hard water does not result in the precipitation of deposits. ensure engine temperature is below 65°C (150°F) by one of the following methods: a Allowing engine time to cool. 16 Remove nozzle connection and nozzle (3).CLEANING/PAINTING Page 721 Jan 24/2006 . STARTER MANUFACTURER’S MANUAL). 14 Repeat washing cycles as necessary to remove contaminants from turbines. CAUTION: DO NOT MOTOR FOR MORE THAN 30 SECONDS. inject water or water/methanol. AMM). 13 Shut off water or water/methanol when NH reaches 5%. 15 Disconnect pressurized tank. CLEANING/PAINTING Page 722 Jan 24/2006 . 3045542 D FW 2 1 3 PWC37771 3 PWC56502 C12552A Turbine Wash Nozzle Connection .PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO.Removal/Installation Figure 706 72-00-00 ENGINE . Adjustment/Test) if water/methanol has been used. Adjustment/Test). REMOVAL/ INSTALLATION). CAUTION: OBSERVE STARTER COOLING PERIOD (REF. STARTER MANUFACTURER’S MANUAL). 72-00-00 ENGINE . Shut down engine (Ref. (b) This procedure can be used on all engines but will be most effective on engines operated continuously in a marine or harsh environment. v No need to disconnect fuel drain lines at the flow divider. 1 Advantages: v Increased flow of water directly onto turbine blades. 19 Carry out an additional 30-second dry motoring run (Ref. 3045542 Key to Figure 706 1. v No need to disconnect the P3 line. v No need for post-wash engine drying runs because of very low residual wash water. AMM). Connect drain line to flow divider and dump valve (Ref. 2. CAUTION: OBSERVE STARTER COOLING PERIOD (REF. NOTE: 21 (4) Engine ground run must be carried out as soon as possible to avoid corrosion problems. Run at 80% NH for one minute or more to completely dry the engine. Igniter Gasket Turbine Wash Nozzle 17 Install gasket (2) and igniter (1) (Ref. STARTER MANUFACTURER’S MANUAL). v Negligible accumulation of water in the gas generator case.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3. Adjustment/Test). 18 Connect combustion chamber drain line to ecology tank.CLEANING/PAINTING Page 723 Jan 24/2006 . 20 Switch ignition ON and start engine (Ref. 72-01-20. Method 2: (a) This alternate turbine wash procedure provides increased water flow directly to the HP turbine blade area and reduce the time it takes to perform the turbine wash. v Eleminates riskof MFCU contamination. fill the wash tank or cart with the appropriate mixture (Ref. 3 Adjust supply pressure to get a flow of 7 to 9 liters over a 20 second period 4 Water accumulated in the bucket should measure between 7 and 9 liters 5 If this specified flow cannot be obtained. check if there is any restrictions in the wash rig and correct the problem. HIGH PRESSURE CAN CAUSE SERIOUS INJURIES. the nature and frequency of turbine washing is recommended to be in accordance with the Gas Path Wash recommended schedule per Chapter 05-20-00. 3 If tap water is used.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. drinking quality tap water. regulated to the pressure as determined in step (3). connect through a centrifugal pump to get a flow of 7 to 9 liters in 20 seconds. at temperatures above 2°C (36°F). Table 701). (d) Equipment Required 1 A wash nozzle (PWC56502) installed in the left igniter port is used when washing turbines. 2 Use a graduated measuring bucket and attach the wash nozzle to the wash rig and spray water into the bucket for 20 seconds at a pressure of 50 to 80 Psi. WARNING: (f) DO NOT EXCEED MAXIMUM RATED PRESSURE FOR WASH RIG. 3045542 (c) Depending upon the operating environment. water flows must be calibrated with the operator’s wash rig to ensure water flow is sufficient to adequately clean the turbines. (e) Flow Calibration of the Wash nozzle and the Wash Rig. 72-00-00 ENGINE .CLEANING/PAINTING Page 724 Jan 24/2006 . REFER TO MANUFACTURER SPECIFICATION. Turbine Wash Procedure 1 Depending upon the ambient temperature. 1 Prior to using the turbine wash nozzle. Alternately. 2 Connect compressed air or nitrogen (PWC05-050) supply. 3045542 WARNING: 4 RESIDUAL VOLTAGE IN IGNITION EXCITER MAY BE DANGEROUSLY HIGH. make sure the engine temperature is below 65°C (150°F) by one of the following methods: a Allowing engine time to cool at ambient temperature. MAKE SURE THE IGNITION IS SWITCHED OFF. The delivery hose must be supported to avoid damage to the wash tube. 7 Connect the wash rig hose to the fluid fittings on the wash nozzle using appropriate adapters. Apply a slight counter-clockwise rotation as the tube is inserted.CLEANING/PAINTING Page 725 Jan 24/2006 . Step 3). CAUTION: WATER USED TO ACCELERATE ENGINE COOLING MUST BE DEMINERALIZED. ALWAYS DISCONNECT COUPLING NUTS AT IGNITION EXCITER END FIRST. 5 If the tube gets stuck at any time during insertion. do not attempt to force it. 9 Before washing. c Use of portable air conditioning unit through exhaust duct or inlet passage. NOTE: d An engine temperature below 65°C (150°F) ensures that the accidental use of hard water does not result in the precipitation of deposits. Remove the left (port side) igniter and install the turbine wash nozzle by directing the tip upward after insertion through the igniter hole.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. It could cause damage to the combustor coating. ALWAYS USE INSULATED TOOLS TO REMOVE COUPLING NUTS. 8 Set the wash rig delivery pressure to what is required to deliver 7 to 9 liters of water over a 20 seconds period (Ref. carrefully thread the nozzle into the igniter port a few turns using only your hands for torque. This will cause wash water to be improperly dispersed through the turbines during the wash. b Use of demineralized water. NOTE: Using the right side (starboard) igniter port wil result in the nozzle being positioned at the bottom of the engine. Carefully. 72-00-00 ENGINE . pull back the tube slightly and reinsert using a light shaking motion to prevent jamming. Make sure the aircraft bleed air is OFF. 6 Once the wash nozzle is inserted. DO NOT TOUCH OUTPUT CONNECTORS OR COUPLING NUTS WITH BARE HANDS. j There is no need to perform a post-wash engine drying run when using this wash procedure if the engine is not exposed to temperature below 2° C and the engine is scheduled to be started within the next 12 hours. h Disconnect the wash rig and remove the wash nozzle.CLEANING/PAINTING Page 726 Jan 24/2006 . 72-01-50) and plug to drain intercompressor cavity (Ref. is necessary to ensure the residual water is carried out back of the engine.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. AMM). SB 21136 and Chap. The 10 seconds of motoring at the end of the cycle with no water applied. b Run at 80% NH for one minute or more to completely dry the engine. open the supply valve to apply wash water to the engine. STARTER MANUFACTURER’S MANUAL). c Shutdown engine (Ref. SB21053 and Chap. 72-10-50). remove the blanking cover to drain no. 72-01-20. 5 bearing vent passage (Ref. OBSERVE STARTER COOLING PERIOD (REF. k 10 If required. i Install gasket (2) and igniter (1) (Ref. 72-00-00 ENGINE . e Carry out a dry motoring run (to be timed for 30 seconds). f Within 3 seconds of the start of the motoring run. DRAIN NO. 3045542 CAUTION: DO NOT MOTOR FOR MORE THAN 30 SECONDS. a Switch ignition ON and start engine (Ref. g Shut off the supply water after 20 seconds and let the engine continue to motor until the 30 seconds motoring run is complete. 5 BEARING VENT PASSAGE AND INTERCOMPRESSOR CASE CAVITY IN ENGINES NOT INCORPORATING SB21053 AND SB21136 RESPECTIVELY IF OIL PRESSURE INDICATIONS WERE OBSERVED DURING TWO OR MORE OF THE MOTORING CYCLES CARRIED OUT WHEN WASHING THE COMPRESSORS AND/OR TURBINES. Engine Drying CAUTION: OBSERVE STARTER COOLING PERIOD (REF. CAUTION: PRIOR TO STARTING ENGINES. REMOVAL/ INSTALLATION). AMM). STARTER MANUFACTURER’S MANUAL). Distilled Chromel Pickle Solution Wetting Agent. Name Drill Driving tool ’Kee’ TD624L Heat Gun Helical coil insert extraction/installation tool Helical coil tang removal tool 72-00-00 ENGINE . Consumable Materials The consumable materials listed below are referred to in this section.APPROVED REPAIRS 1.APPROVED REPAIRS Page 801 Mar 01/2002 . Petroleum Cleaner. Locking Perchlorethylene Solution. Anodize Touch-up (Alodine) Water. Crocus) Solution.magnesium Compound. Abrasive (Coated. General A. equipment and supplier tools listed below are referred to in procedural text. SOME MATERIALS CAN BE DANGEROUS. For more data. Item No. Equipment and Supplier Tools The fixtures. 2. Chromic (Solution) Chromate Conversion Salts . Fixtures. Engine Parts Special Tools Not Applicable 4. WARNING: 3. Name PWC05-055 PWC05-057 PWC05-061 PWC05-064 PWC05-073 PWC05-161 PWC05-162 PWC05-195 PWC05-196 PWC05-197 PWC05-198 PWC09-002 PWC11-016 PWC11-019 PWC11-027 PWC11-031 Sodium Dichromate Sodium Hydroxide Cloth.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. These instructions provide information of a general nature applicable to the repair sections throughout this manual. refer to the CONSUMABLE MATERIALS section at the beginning of this manual. 3045542 ENGINE . READ THE MATERIAL SAFETY DATA SHEETS BEFORE YOU USE THESE MATERIALS. Chromate Nitric Acid Hydrochloric Acid Acid. Chromate Conversion Solvent. Procedure (same size insert replacement) (1) If part being repaired is made from magnesium.004 in. Para. 3045542 Name Helical coil thread plug gage and bottoming tap (standard thread size) Helical coil thread plug gage and bottoming tap (oversize thread size) Oven Stud drivers Thread plug gage Wire brush 5. (4) Inspect the replaced helical coil insert (Ref. (3) Clean out hole and ensure debris and other foreign matter are removed. install insert into threaded hole using insert installation tool. Install oversize replacement insert (Ref. (2) Remove unserviceable insert. B. Para. Insert outer thread must be between one and one and one-half threads below surface of hole or counterbore. C. MAINTENANCE PRACTICES). 10. Para. (4) Check threads using thread plug gage as follows: (a) Insert hole is standard size if thread plug gage (NO GO side) enters less then three turns.101 mm) oversize insert has been installed at each location.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. (3) Cut off driving tang at notch using tang removal tool. General (1) Check near hole for identification of oversize insert installation.). Install replacement insert of standard size (Ref.). (b) Insert hole is oversize if thread plug gage (NO GO side) enters more then three turns. Para. using extraction tool.). treat hole as specified in chromate surface repair (Ref.APPROVED REPAIRS Page 802 Mar 01/2002 . (2) Using new helical coil insert. (0. treat as per anodic film repair (Ref. 72-00-00. whichever applies. 72-00-00 ENGINE . Procedure (oversize insert replacement) (1) Tap hole with appropriate bottoming tap if oversize helical coil is required. REFER TO ILLUSTRATED PARTS CATALOG TO ENSURE CORRECT INSERT FOR THE PARTICULAR LOCATION IS USED. If part is made from aluminum. C. and remove tang from hole.). 9. Helical Coil Insert Replacement A. a marking of +4 indicates a 0. CAUTION: BEFORE INSTALLING HELICAL COIL INSERTS. For example. B. detail E).0150 mm) deep next to insert hole (Ref. (0. detail D). 6. 802) A. FILTER BYPASS & PRESSURE RELIEF VALVE OR RGB OIL FILTER & BYPASS VALVE) TO ENSURE CORRECT INSERT FOR PARTICULAR LOCATION IS USED. 10. treat hole as specified in chromate surface repair (Ref. bend keys inward and break them off (Ref. (3) Remove insert with an ’E-2’ type tool (Ref. (4) Identify oversize insert installation using the following example ‘‘+4’’ for a 0. (10. Procedure ⁄ 13 32 in.002 to 0. 0. (6) Screw in new insert. 72-00-00. CAUTION: DO NOT PUT THE MARKING ON A SEALING FACE OR AREA WHICH WOULD AFFECT FUNCTION OF PART. Fig. (7) Using a ’Kee’ driving tool (TD624L) and a hammer. REFER TO ILLUSTRATED PARTS CATALOG (REF. CAUTION: BEFORE INSTALLING KEENSERT INSERTS. detail A).76 mm) below surface of parent component (Ref.010 to 0. Fig. Para. Blend to remove raised material. drive down keys with several light taps (Ref.25-0. and remove tang from hole. detail C). (0. (4) Clean out hole and ensure swarf and other foreign matter is removed.006 in. by vibropeen method. (0.101 mm) oversize. install insert into threaded hole using insert installation tool. (5) If part being repaired is made from magnesium.). using fingers. 3045542 CAUTION: BEFORE INSTALLING HELICAL COIL INSERTS. to a depth of 0. REFER TO ILLUSTRATED PARTS CATALOG FOR OVERSIZE INSERT P/N TO ENSURE CORRECT INSERT FOR THE PARTICULAR LOCATION IS USED. Mark part. (2) Using new helical coil insert. (5) Inspect the replaced helical coil insert (Ref. MAINTENANCE PRACTICES).030 in.050-0.004 in.319 mm) (1) Drill out insert material between keys to depth shown using a diameter drill (Ref.APPROVED REPAIRS Page 803 Mar 01/2002 . Para. whichever applies.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO.). detail B). 9. (2) Using a small pin punch. 72-00-00 ENGINE . ’Keensert’ Insert Replacement (Ref. treat hole as specified in anodic film repair (Ref. (3) Cut off driving tang at notch using tang removal tool. 801). Insert outer thread must be between one and one and one-half threads below surface of hole or counterbore. If part is made from aluminum. PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO.APPROVED REPAIRS Page 804 Mar 01/2002 . 3045542 +4 A +4 TYPICAL AREA FOR OVERSIZE MARKING VIEW A C24386 Identification of Oversize Insert Installation Figure 801 72-00-00 ENGINE . (0.319 mm) LOCKING WIRES 0.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3045542 13 INCH DRILL 32 (10. (0.762−0.010 IN.200 IN.APPROVED REPAIRS Page 805 Mar 01/2002 .030−0.508 mm) KEENSERT DETAIL DETAIL B DETAIL C A 0.254 mm) KEE DRIVING TOOL DETAIL D DETAIL E C17622 Replacement of ’Keensert’ Inserts Figure 802 72-00-00 ENGINE . (4) Install stud to correct protrusion height using an approved stud driver.78) 300 (33.6250-18 525 (59.4375-20 175 (19.87) 180 (20. (Nm) Torque (Maximum) lb. NOTE: Stud holes with threads damaged beyond the dimensions suitable for maximum oversize stud installation may be repaired with helical coil inserts.38) 450 (50. 72-00-00 ENGINE .85) 0.1900-32 23 (2.in.70) Thread Size (Nut End) * When drive end is 0. (Nm) 0.90) 0. REFER TO ILLUSTRATED PARTS CATALOG TO ENSURE THE CORRECT STUD FOR THE PARTICULAR LOCATION IS USED.82) 240 (27.in.34) 0. Stud Replacement A.3125-24 105 (11.60) 45* (5. as applicable.5000-20 260 (29. TABLE 801. Standard and Stepped Studs Installed in Self-locking Helical Coil Inserts Torque (Minimum) lb. Ensure torque limits given in Tables 801. are not exceeded.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO.55) 640 (75. reduce this value to 40 (4. CAUTION: BEFORE INSTALLING NEW STUDS.32) 0.APPROVED REPAIRS Page 806 Mar 01/2002 . (2) Remove damaged stud.52). (3) Examine stud hole for condition. Procedure (1) Measure stud protrusion height (use adjacent stud in case of stretched or broken stud).88) 90 (10.3750-24 140 (15.17) 0.32) 900 (101.09) 0. specific instances should be referred to P&WC Customer Support Department (Ref.2500-28 52 (5. on worn stud holes use oversize studs. 802 or 803.5625-18 350 (39. 3045542 7. therefore.1900-24. Use of an insert reduces wall thickness and strength of surrounding metal.12) 0. INTRODUCTION) for approval. 73) 230 (25. (Nm) Torque (Maximum) lb. in.09) 0.09) 50 (5.00) 1400 (158.74) 105 (11.87) 0.95) 1300 (146.50) 0.1640-32 15 (1.35) 1050 (118.00) 450 (50.2500-28 50 (5.70) 30 (3.80) 1800 (203.00) 240 (27.00) 950 (107.6250-11 900 (100.5625-12 625 (70.99) 0.in.80) Thread Size (Drive End) 72-00-00 ENGINE .6250-18 900 (100. (Nm) Plain # 0. (Nm) Necked $ Torque (Maximum) lb.80) 45 (5.50) 95 (10.2500-20 50 (5. (Nm) Plain # 0.1640-36 15 (1.85) 500 (56.80) 40 (4.39) 0.1900-24 25 (2.13) 0.00) 700 (79.20) 1500 (169.5000-13 450 (50.40) 0.38) 425 (48.00) 3500 (395.38) 0. in. Stepped Interference Fit Studs Torque (Minimum) lb.00) 2400 (271.00) 210 (23.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO.7500-10 1550 (175. Standard Interference Fit Studs Torque (Minimum) lb.5000-20 450 (50.00) 1900 (214. 3045542 TABLE 802.5625-18 625 (70.39) 30 (3. in.50) 0.10) 800 (90. # These limits apply where the unthreaded diameter of the stud is equal to or greater than the minimum minor diameter of the coarse pitch thread (drive end).00) 600 (67. (Nm) Torque (Maximum) lb. (Nm) Necked $ Torque (Maximum) lb.52) 45 (5.in.3750-24 180 (20.30) 0.39) 0.APPROVED REPAIRS Page 807 Mar 01/2002 .00) 125 (14.50) 3800 (429.3125-18 100 (11.28) 0.1900-32 25 (2.00) 375 (42.50) 115 (13.3750-16 180 (20.4375-14 280 (32.65) 0. TABLE 803.40) Thread Size (Drive End) $ These limits apply where the unthreaded diameter of the stud is less than the minimum minor diameter of the coarse pitch thread (drive end).80) 675 (76.in.39) 30 (3.65) 0.70) 2100 (237.00) 1150 (129.12) 260 (29.3125-24 100 (11.4375-20 280 (32.03) 0.90) 0.20) 2600 (293.70) 30 (3.40) 0.00) 1600 (180. of existing hole. Clean surface to be repaired using a swab soaked in perchlorethylene (PWC11-016) and/or crocus cloth (PWC05-061). (8) If part being repaired is magnesium. 72-00-00 ENGINE . PHYSICAL/CHEMICAL CHARACTERISTICS. 9.60) 4600 (519. in. 10. (7) Clean out hole and ensure freedom from metal chippings and other foreign matter. (Nm) Plain # 1550 (175. # These limits apply where the unthreaded diameter of the stud is equal to or greater than the minimum minor diameter of the fine pitch thread (nut end). if any. counterbore hole to required angle and depth. Stepped Interference Fit Studs (Cont’d) Thread Size (Drive End) 0. Anodic Film Repair of Aluminum A. Procedure WARNING: (1) REFER TO THE MANUFACTURER’S MATERIAL SAFETY DATA SHEETS FOR CONSUMABLE MATERIALS INFORMATION SUCH AS: HAZARDOUS INGREDIENTS. treat as per anodic film repair (Ref. (4) Select relevant size drill and drill hole to core depth of existing hole.7500-20 Torque (Minimum) lb. 9.). Stud Hole Repair A. (9) Using appropriate size helical coil insert.80) $ These limits apply where the unthreaded diameter of the stud is less than the minimum minor diameter of the fine pitch thread (nut end). 8. Procedure (1) Ensure damaged hole is suitable for repair.APPROVED REPAIRS Page 808 Mar 01/2002 . (5) Tap hole one thread deeper than insert to be fitted. install insert into repaired stud hole. in. USE AND CONTROL MEASURES. HEALTH HAZARD DATA. in. (2) Measure core depth of existing hole. Para.00) 4200 (474. (Nm) Necked $ Torque (Maximum) lb. 3045542 TABLE 803. PRECAUTIONS FOR SAFE HANDLING. (6) Where applicable. (Nm) Torque (Maximum) lb.). EXPLOSION. (3) Determine angle and depth of counterbore. If part is aluminum.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. FIRE. treat tapped hole as specified in chromate surface repair (Ref. REACTIVITY. Para. 1 NOTE: To maintain (PWC05-162). remove with clean cloth and reclean (Ref. wt/gal 4. step (1)). add 0. General (1) The following procedures outline how to prepare the chromate solutions. (4) Examine coating and ensure repair surface is completely covered.APPROVED REPAIRS Page 809 Mar 01/2002 . as necessary. Reapply treatment as necessary. Chromate Surface Repair of Magnesium A.6 . (3) Allow surface to air dry or wipe off solution with cloth soaked in clean water. 72-00-00 ENGINE . 5 Fill container to operating level and stir to mix.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. (a) Prepare chromate conversion solution (PWC11-019) using Table 804 and the steps that follow: TABLE 804. pH = 0.5 ml for every 5 oz (PWC05-198) added.5 oz. 2 Slowly and cautiously add required amount of conversion salts (PWC05-198).5. Chromate Conversion Solution (PWC11-019) Material Operating Limits Make-up (PWC05-198) Chromate Conversion Salts . 1 Fill suitable container to 3/4 level with tap water.3 fl oz/gal (PWC05-162) Wetting agent 1 ml/gal Sodium Hydroxide. NOTE: 10. 4 Slowly and cautiously add required amount of wetting agent (PWC05-162) and stir to mix.5 . 3 Slowly and cautiously add required amount of hydrochloric acid (PWC05-196) and stir to mix. wt/gal (PWC05-196) Hydrochloric Acid 2 fl oz/gal 1 . If solution does not wet surface. Repeat application frequently to ensure surface is continually wet with solution during the treatment.1. consists of (PWC05-057) and water (PWC05-073) (16 oz) Add. 3045542 (2) Apply anodize touch-up solution (PWC05-064) for three to four minutes to prepared surface using a swab or brush. to raise pH to operating range.magnesium 5 oz. (b) Prepare chromel pickle solution (PWC05-161) using Table 805 and the steps that follow: TABLE 805. Procedure WARNING: (1) REFER TO THE MANUFACTURER’S MATERIAL SAFETY DATA SHEETS FOR CONSUMABLE MATERIALS INFORMATION SUCH AS: HAZARDOUS INGREDIENTS. Remove all debris.4 pints 1. Stir to dissolve.0 . REACTIVITY. Clean impeller. EXPLOSION.1. HEALTH HAZARD DATA. if the solution has been accidentally applied. NOTE: Use a suitable cover to protect area around the surface to be repaired to prevent contamination.5 lbs 1. as necessary. lightly remove all traces of corrosion (magnesium oxide). 3 Add slowly and cautiously the required amount of nitric acid (PWC05-195). PRECAUTIONS FOR SAFE HANDLING.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. (2) Clean the surface to be repaired with a swab soaked in isopropyl alcohol (PWC05-014) and a crocus cloth (PWC05-061).0 . With the use of a small steel brush. B. Chromel Pickle Solution (PWC05-161) Material Operating Limits Make-up (PWC05-055) Sodium Dichromate 1. PHYSICAL/CHEMICAL CHARACTERISTICS. 2 Add slowly and cautiously the required amount of sodium dichromate (PWC05-055). 4 Fill remainder of the container with tap water. (4) Wipe the affected area with a swab and clean water until successive swabs are no longer stained yellow. Stir to mix.APPROVED REPAIRS Page 810 Jan 16/2004 . 1 Fill container 1/2 full with tap water. 72-00-00 ENGINE .5 lbs (PWC05-195) Nitric Acid 1. FIRE. a crocus cloth (PWC05-061) or an abrasive cloth (PWC05-101). using a swab or brush. Stir to mix. Stir to mix.5 pints NOTE: Figures given are weights per gallon of solution.1. Repeat application frequently to make sure the surface is continually wet with solution during the treatment. USE AND CONTROL MEASURES. (3) Apply chromate solution (PWC11-019) or chromel pickle solution (PWC05-161) at a temperature of 13 to 29°C (55-85°F) for 30 to 45 seconds to prepared surface. 3045542 6 Add hydrochloric acid (PWC05-196) or a combination of sodium hydroxide (PWC05-057) and 16 oz of water (PWC05-073) to adjust pH. make sure the compressed air is free of oil vapors if continuing with step (6). (7) Let the air dry the primer for 8 hours before the application of enamel paint.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. using a drill. FIRE. NOTE: 11. You can use clean low pressure compressed air at 29 psig (200 kPa) to accelerate drying. 72-00-00 ENGINE . WARNING: (2) REFER TO THE MANUFACTURER’S MATERIAL SAFETY DATA SHEETS FOR CONSUMABLE MATERIALS INFORMATION SUCH AS: HAZARDOUS INGREDIENTS. using a heat gun for 10 to 15 minutes. NOTE: (6) Apply two coats of primer (PWC13-001) (primer can be diluted with 10% solvent). PHYSICAL/CHEMICAL CHARACTERISTICS. continue with steps (6) to (8). NOTE: Tergit (PWC11-031) is recommended to be used as an alternative to petroleum solvent when the use of this product is restricted by local environmental and/or health legislation. Drying times of primer and paint can be reduced by heating (use a heat gun at the low heat setting . Let surface of enamel to become tacky (approximately 15 minutes) between each coat. EXPLOSION. Let the final coat of enamel paint to dry for 24 hours before returning engine to service. (8) Apply three to four coats of enamel (PWC05-037) to primed surface. HEALTH HAZARD DATA. USE AND CONTROL MEASURES.APPROVED REPAIRS Page 811/812 Jan 16/2004 . Procedure (1) Remove jacking insert. locally heat insert to 100 ± 3°C (212 ± 5°F). (3) Coat insert with locking compound (PWC09-002) and install in flange.see manufacturers instructions). If the surface being repaired is not in contact with another part. Jacking Insert Replacement A. (4) To cure compound. 3045542 (5) Dry thoroughly with clean low pressure compressed air at 29 psig (200 kPa). Remove locking compound residue and clean insert seat and associated area. REACTIVITY. PRECAUTIONS FOR SAFE HANDLING. using a wire brush and solvent (PWC11-027) or cleaner (PWC11-031). . Fixtures. 3045542 ENGINE . C. Name Heat gun .FAULT ISOLATION Page 101 Nov 04/2005 .Thermofit minigun (with reflector) 5. provided the end result is the same or better. 2.Unable to Achieve Take-off Power Mismatched Power Setting Engine Fails to Start High Oil Consumption Smoke from Exhaust on Start-up or Shutdown/Engine Flooded with Oil/Oil Odor in Cockpit Low or Loss of Oil Pressure High Oil Pressure 101 102 103 104 105 106 107 108 109 72-00-01 ENGINE . This section provides a series of checks to enable problems occurring in the operation of the engine to be isolated and rectified. The recommended procedures in this section are intended to provide satisfactory results to common engine faults. Equipment and Supplier Tools The fixtures. Consumable Materials Not Applicable 3. experience and/or operating practices. General A. equipment and supplier tools listed below are referred to in procedural text. Fault Isolation Fault Index The actions required to locate and rectify problems with the engine are detailed in the following figures. FAULT FIGURE Unable to Select Manual Mode Incorrect MFCU Operation Reference Pressure Leak . Reference should be made to the flight log and engine log for any entry relating to the current problem. B. The steps can be changed by the Operator to make the troubleshooting procedures better and adapted to their own operation.FAULT ISOLATION 1. Special Tools Not Applicable 4. Substantiation is based on the Operator’s own reliability data.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. FAULT ISOLATION Page 102 Nov 04/2005 .Evaluation of Laboratory Report Oil Leak From Propeller Shaft Area Oil on Flange(s) E and/or F LP Fuel Filter Impending Bypass Indicator Activated Fuel Temperature Too High or Too Low Engine Overtorque 110 111 112 113 114 115 116 117 118 119 120 121 122 123 124 125 126 127 128 129 130 131 132 133 134 135 72-00-01 ENGINE . 3045542 FAULT FIGURE High Oil Temperature Incorrect Torque Readings Torque Fluctuations Excessive Fuel Consumption HP Fuel Filter Impending Bypass Indicator Activated Propeller Slow to Unfeather Performance Deterioration (ECTM Shift) or High ITT/T6 Hot Start Propeller Speed (NP) Fluctuations Slow Oil Pressure Buildup after 40% NH during Starting High ITT/T6 Temperature Engine Stall Unable to Rotate Propeller Manually after Engine Shutdown/Propeller does not rotate after Engine Start Chip Detector Circuit Completion Main Oil Filter Impending Bypass Indicator Activated RGB Scavenge Oil Filter Impending Bypass Indicator Activated Hung Start Debris in Oil System Debris in Oil System From the Tubomachinery Module Debris in Oil System from the Reduction Gearbox Module Oil Debris .PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. AMM) YES MANUAL LAMP GOES OUT? NO REPLACE MANUAL SWITCH (REF. 72−01−40) ENGINE WIRING HARNESS OK? REPLACE MFCU NO RECTIFY OR REPLACE (REF. NO PRESS MANUAL SWITCH. PRESS MANUAL SWITCH ON AND RELEASE. AMM) YES MANUAL OCCURS WHEN PULLING OUT MANUAL SOLENOID MFC BREAKER? YES NO SHUT DOWN ENGINE. FAULT LAMP. 1.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. DISCONNECT MFCU CONNECTOR. PRESS MANUAL SWITCH ON. 3. 3045542 SYMPTOMS SUSPECT LRU VERY HIGH FLIGHT IDLE OF 88% NH. MANUAL SWITCH MFCU ENGINE WIRING HARNESS AIRCRAFT WIRING AND RELAYS RUN ENGINE AT FLIGHT IDLE. CAN MFCU TRANSFER SOLENOID BE HEARD OPERATING ? YES NO PULL OUT EEC POWER CIRCUIT BREAKER. 72−01−10) YES AIRCRAFT WIRING NO AND RELAYS OK? RECTIFY OR REPLACE (REF. 4. AMM) C26208 Unable to Select Manual Mode Figure 101 72-00-01 ENGINE . IS VOLTAGE BETWEEN P8−N (RTN) AND P8−M (POSITIVE) EQUAL TO 0 VDC ? NO YES SYSTEM NORMAL REPLACE MFCU (REF. 2. GOES OUT ? REPLACE MANUAL SWITCH (REF. NO RESPONSE TO POWER LEVER MOVEMENT. AND/OR INABILITY TO ATTAIN TAKE−OFF POWER.FAULT ISOLATION Page 103 Nov 04/2005 . NH DROPS TO 75% ? NO STOP ENGINE. START ENGINE. PULL MFCU SOLENOID CIRCUIT BREAKER. DISCONNECT MFCU ELECTRICAL CONNECTION. 2. 3045542 SYMPTOMS SUSPECT LRU 1. 72−01−40) C38582 Incorrect MFCU Operation Figure 102 72-00-01 ENGINE . AMM) NO REPLACE MFCU (REF. NORMAL OPERATION IN MANUAL MODE. REPLACE MFCU (REF.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. MFCU SYMPTOM 1. 1. ENGINE ACCELERATES TO 75% ? YES CHECK AIRCRAFT WIRING OF MANUAL MODE SELECTOR SWITCH (REF. WITH ENGINE AT FLIGHT IDLE PLA. VERY HIGH FLIGHT IDLE OF ABOUT 88% NH IN MANUAL MODE. TAKE−OFF NOT ATTAINABLE AT LIMIT OF POWER LEVER TRAVEL IN EEC MODE.FAULT ISOLATION Page 104 Nov 04/2005 . 72−01−40) YES CHECK LINE 126 FOR SHORT CIRCUIT SYMPTOM 2. MFCU 2.Unable to Achieve Takeoff Power Figure 103 72-00-01 ENGINE .FAULT ISOLATION Page 105 Nov 04/2005 . OVERSHOOT ON TORQUE DURING POWER SETTING. 72−01−40) NO REPLACE PY TUBE (REF. IS TAKE−OFF NOW ATTAINABLE ? TIGHTEN FITTINGS ON P3 TUBE AT NO MFCU AND INTERCOMPRESSOR CASE. TIGHTEN FITTINGS ON PY TUBE AT NO MFCU AND OVERSPEED GOVERNOR. 72−01−30) YES CONNECT PY TUBE TO MFCU. DISCONNECT PY TUBE FROM OVERSPEED GOVERNOR AND BLANK OPEN END. IS TAKE−OFF NOW ATTAINABLE ? YES REPLACE OVERSPEED GOVERNOR (REF. IS TAKE−OFF NOW ATTAINABLE ? YES YES SYSTEM NORMAL SYSTEM NORMAL DISCONNECT PY TUBE FROM MFCU AND BLANK MFCU FITTING. OVERSPEED GOVERNOR 3. 72−01−50) C26210 Reference Pressure Leak . PY AIR TUBE UNABLE TO ACHIEVE TAKE−OFF POWER AT FULL POWER LEVER TRAVEL IN MANUAL OR EEC MODE. IS TAKE−OFF NOW ATTAINABLE ? NO REPLACE MFCU (REF. 3045542 SYMPTOMS SUSPECT LRU 1.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. AMM) NO REPAIR/REPLACE AIRCRAFT WIRING (REF. POWER EQUAL ? NO YES SYSTEM NORMAL TURN ON HP BLEEDS. AND BLEED SWITCH 2 TO BREAKER OK ? YES SYSTEM NORMAL C38583 Mismatched Power Setting Figure 104 72-00-01 ENGINE . INCREASE TO TAKE−OFF POWER. FAULT PERSISTS ? YES NO YES NO TURN ON LP BLEEDS. CHECK LINES 148 AND 149 CONTINUITY AND/OR INSULATION. POWER SETTING OK ? YES SYSTEM NORMAL NO SHUT DOWN ENGINES. ALL BLEEDS OFF. WIRING HARNESS 2. DOES POWER EQUALIZE ? ANY FDEP FAULT INDICATED ? YES RECTIFY. AIRCRAFT WIRING FOR SAME POWER LEVER AND RATING SELECTED. OK ? NO REPLACE WIRING HARNESS (REF. 3045542 SYMPTOMS SUSPECT LRU 1. 72−01−10) NO REPAIR/REPLACE AIRCRAFT WIRING (REF. AMM) YES P11−CC TO BLEED SWITCH 1.FAULT ISOLATION Page 106 Nov 04/2005 . ONE ENGINE MAY PRODUCE A DIFFERENT POWER. POWER EQUAL ? NO YES SYSTEM NORMAL CARRY OUT ENGINE TRIM ON BOTH ENGINES. TURN EEC POWER OFF.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. POWER ON ALL SYSTEMS. AND BLEED SWITCH 1 TO BREAKER OK ? YES P11−DD TO BLEED SWITCH 2. START ENGINES. ACCESSORY GEARBOX 2. LP AND HP FUEL FILTERS 7. BOOSTER PUMPS 5.FAULT ISOLATION Page 107 Nov 04/2005 . FLOW DIVIDER REFER TO SHEET 4 NO YES NH INCREASES UNUSUALLY FAST BORESCOPE AGB YES ANGLE DRIVE GEAR DAMAGE? NO NO REPLACE TURBOMACHINERY CONTACT P&WC FUEL FLOW LESS NO THAN 90pph WITH CLA AT FEATHER? OAT LESS YES THAN 5° C SWITCH ON YES IGNITERS FOR 30 SECONDS. ENGINE STARTS OK? NO SYSTEM NORMAL CONT’D ON SHEET 2 CONTACT P&WC SYSTEM NORMAL REPLACE FUEL YES NOZZLE SET ENGINE STARTS OK? NO CONTACT P&WC C26212B Engine Fails to Start Figure 105 (Sheet 1 of 4) 72-00-01 ENGINE . 3045542 SYSTOMS NO T6 INDICATION (LIGHT UP) WITHIN 10 SECONDS OF ADVANCING CONDITION LEVER TO START POSITION NH INDICATION YES LESS THAN 10% SUSPECT LRU 1. SYSTEM OK? REPLACE FLOW YES DIVIDER. AIRCRAFT LP FUEL VALVE 6. ENGINE STARTS? SYSTEM NORMAL NO YES NO REPLACE FLOW YES DIVIDER. IGNITION SYSTEM 3. FUEL SUPPLY 4.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. ENGINE STARTS OK? YES FUEL DRAINING FROM DUMP VALVE DURING START ATTEMPT NO NO FUEL DRAINING NO FROM FUEL MANIFOLD DRAIN? YES REPLACE FUEL NO NOZZLE PACKINGS ENGINE STARTS OK? YES IS FUEL DRAINING FROM NO GAS GENERATOR DURING START ATTEMPT? YES REFER TO SHEET 3 FOR IGNITION SYSTEM TROUBLESHOOTING. FUEL PUMP AND MFC 8. 3045542 COND’T FROM SHEET 1 AIRCRAFT FUEL TANKS NO CONTAIN FUEL? ADD FUEL YES BOOSTER PUMP OK? NO RECTIFY OR REPLACE (REF. CARRY OUT A WET MOTORING RUN. AMM) YES REFER TO TROUBLESHOOTING CHART "HP FUEL FILTER IMPENDING BYPASS INDICATOR ACTIVATED" HP FUEL FILTER YES BYPASS INDICATORS ACTIVATED? NO REPLACE FUEL FLOWMETER ENGINE STARTS OK? YES SYSTEM NORMAL NO DISCONNECT FUEL LINE FROM FLOW DIVIDER. 72−01−40) NO YES SYSTEM NORMAL C28474B Engine Fails to Start Figure 105 (Sheet 2) 72-00-01 ENGINE . CHECK FOR FUEL. OK ? REPLACE FUEL PUMP AND MFCU NO YES REPLACE FLOW DIVIDER (REF.FAULT ISOLATION Page 108 Nov 04/2005 .PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 72−01−40) ENGINE STARTS ? REPLACE FUEL NOZZLES (REF. AMM) YES NO AIRCRAFT LP VALVE OPEN (ON FIREWALL)? RECTIFY OR REPLACE (REF. 72−01−20) OK ? NO REPLACE IGNITERS (REF. IGNITER 4. (REF. 3045542 SUSPECT LRU SYMPTOMS 1. IGNITION EXCITER 3.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO.FAULT ISOLATION Page 109 Nov 04/2005 . 72−01−20) YES CHECK/REPLACE IGNITER LEADS (REF. 72−01−20) START OK ? YES SYSTEM NORMAL NO REMOVE AND VISUALLY CHECK IGNITERS FOR WEAR (REF. AMM) NO RECTIFY (REF. AIRCRAFT IGNITION SYSTEM 2. 72−01−20) C26213 Engine Fails to Start Figure 105 (Sheet 3) 72-00-01 ENGINE . AMM) YES REPLACE IGNITION EXCITER. IGNITER LEADS NO ITT/T6 INDICATION (LIGHT UP) WITHIN 10 SECONDS OF ADVANCING CONDITION LEVER TO START POSITION SNAPPING NOISE FROM IGNITERS ? NO PUSH CONTACT BREAKER IN AIRCRAFT IGNITION NO SYSTEM CONTACT BREAKER IS IN ? YES YES AIRCRAFT IGNITION SYSTEM OK ? (REF. 3045542 SYMPTOMS SUSPECT LRU 1.FAULT ISOLATION Page 110 Nov 04/2005 . FUEL PUMP 2. AMM) NO YES HP ROTOR ROTATES ? NO REMOVE FUEL PUMP (REF.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 72−02−00) NH INDICATOR OK ? (REF. AMM) HP ROTOR ROTATES ? YES REPLACE STARTER (REF. 72−01−40) YES NO REMOVE STARTER (REF. STARTER 3. AMM) YES REPLACE STARTER (REF. 72−01−40) HP ROTOR ROTATES ? YES REPLACE FUEL PUMP (REF. TURBOMACHINERY NO NH INDICATION STARTER CONTACT BREAKER IN ? NO RECTIFY YES ELECTRICAL POWER AT STARTER TERMINALS ? RECTIFY AIRCRAFT SYSTEM (REF. AMM) NO RECTIFY (REF. AMM) C26214 Engine Fails to Start Figure 105 (Sheet 4) 72-00-01 ENGINE . AMM) NO REPLACE TURBOMACHINERY (REF. AGB BREATHER COUPLING SHAFT STOP 11. 6 & 7 BEARING OIL SCAVENGE PUMP 13. OIL COOLER QUICK−RELEASE COUPLINGS 5. P2.5/P3 SWITCHING VALVE 12. NO. AGB CARBON SEAL 10. 3045542 SYMPTOMS HIGH OIL CONSUMPTION SUSPECT LRU 1. FIRST STAGE PT DAMAGE C62149 High Oil Consumption Figure 106 (Sheet 1 of 4) 72-00-01 ENGINE . OVER−SERVICING 4. EXTERNAL OIL LEAK 2. NL SENSOR AND SEALING TUBE PACKINGS 7. OIL COOLER 6.FAULT ISOLATION Page 111 Nov 04/2005 . PRESSURE REGULATING VALVE 3. 6 & 7 BEARING TRANSFER TUBES 9.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. NO. AGB BREATHER 8. NOTE 8 AND AMM). NOTE 1). OIL CONSUMPTION OK? ADJUST/REPLACE OIL PRESSURE YES REGULATING VALVE (REF. YES YES NO NO OIL PRESSURE TOO HIGH? (ABOVE 65 psid) RECTIFY. 72−01−50) OIL CONSUMPTION OK? NO DO AN OIL LEVEL CHECK.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. EXTERNAL OIL LEAK FOUND? CHECK OVERBOARD DRAINS (REF. 72−01−50) OIL PRESSURE OK? YES NO NO SYSTEM NORMAL REPAIR/REPLACE OIL PRESSURE YES REGULATING VALVE (REF. AFTER 20 SECS.FAULT ISOLATION Page 112 Nov 04/2005 . RUNNING IN FEATHER. 3045542 CHECK MAINTENANCE HISTORY FROM PRIOR TO THE FIRST REPORTS (REF. IS OIL LEVEL ABOVE "ADD 1" ? YES DRAIN OIL FROM TANK TO "ADD 1" OIL LEVEL (REF. SERVICING) OIL CONSUMPTION OK? YES NO CONT’D ON SHEET 3 C62148 High Oil Consumption Figure 106 (Sheet 2) 72-00-01 ENGINE . 6 & 7 BEARING TRANSFER TUBE LEAK (REF. NOTE 2) ? YES NO NO. AMM) OIL CONSUMPTION OK ? YES NO YES REPLACE PACKINGS (REF. 3045542 CONT’D FROM SHEET 2 A/C OIL COOLER QUICK YES RELEASE COUPLINGS LEAKING ? YES NO REMOVE AND INSPECT NL SENSOR & SEALING TUBE FOR SIGNS OF LEAKAGE (REF. PACKINGS DAMAGED ? YES NO NO A/C OIL COOLER LEAKING? RECTIFY (REF. 6 & 7 BEARING VENT TRANSFER TUBE INSIDE DIAMETER OBSTRUCTED BY COKED OIL ? RECTIFY OIL CONSUMPTION OK ? RECTIFY OIL CONSUMPTION OK ? YES NO YES CLEAN (REF. 72−01−60) OIL CONSUMPTION OK ? YES NO SYSTEM NORMAL NO OBSTRUCTION FOUND IN AGB BREATHER TUBE (REF. AMM) OIL CONSUMPTION OK ? RECTIFY OR REPLACE (REF. 72−01−50) ? YES NO YES NO NO. 72−01−50) NO CONT’D ON SHEET 4 C62126 High Oil Consumption Figure 106 (Sheet 3) 72-00-01 ENGINE .FAULT ISOLATION Page 113 Nov 04/2005 .PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 72−01−60). SCORING. NOTE 2: REMOVE AGB BREATHER PIPE AND VISUALLY INSPECT FOR BLOCKAGE. USE FLASHLIGHT TO ILLUMINATE CAVITY INSIDE THE SHAFT.FAULT ISOLATION Page 114 Nov 04/2005 . SUSPECT PLUNGER STUCK ON P2.B. INSP/CHECK) SEE NOTE 6 NOTE 1: LRU CHANGE MAY HAVE INTRODUCED AN EXTERNAL LEAK CONDITION. WHICH IS EQUIVALENT TO 0. C27410C High Oil Consumption Figure 106 (Sheet 4) 72-00-01 ENGINE .: SPRING PRESSURE SHOULD HOLD THE PLUNGER DOWN (P3 POSITION) UNTIL SUFFICIENT P2.227 kg/hr). REMOVE COVER AND VISUALLY CHECK THE PLUNGER FOR BEND. OK? (REF.5 IS AVAILABLE AFTER START.250 in. REMOVE ENGINE FOR INVESTIGATION. 72−30−00). CHECK SEAL MATING SURFACE ON SHAFT FOR DAMAGE. NOTE 7: MAXIMUM OIL CONSUMPTION PERMISSIBLE IS 0. IF MORE. IT SHOULD BE PROTRUDING BY LESS THAN 0. USE A 0.001 IN. ETC.250 LITERS/HOUR). COKING. NOTE 4: LOOK INSIDE CENTRIFUGAL BREATHER SHAFT TO CHECK THAT THE AGB BREATHER ADAPTER AIR WINDOWS ARE NOT OBSTRUCTED BY THE AGB STOP SHAFT PLUG (REF.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. BLADE SHIFT.270 QUART/HOUR (0.50 lbs/hr (0. OIL STAINS. NOTE 6: INABILITY TO IDENTIFY AND/OR RECTIFY HIGH OIL CONSUMPTION (ABOVE MAX LIMIT) AFTER CARRYING OUT THE LISTED CHECKS INDICATES INTERNAL ENGINE DAMAGE/OIL LEAKAGE. 3045542 CONT’D FROM SHEET 3 REMOVE ENGINE FOR INVESTIGATION BORESCOPE FIRST STAGE PT BLADES TO CHECK FOR IMPACT DAMAGE TO LEADING EDGES AND/OR TIPS. NOTE 3: ADAPTER ASSEMBLIES MUST BE CHECKED TO ENSURE THE ADJUSTING SPACER THICKNESS IS CORRECT AND THE SEAL IS SERVICEABLE. NOTE 5: VISUALLY CHECK THE AIR SWITCHING VALVE PLUNGER "IN SITU" PRIOR TO ENGINE START−UP. (0. REFER TO CHAPTER 72−20−00 FOR SPACER THICKNESS CALCULATION AND INSPECTION CRITERIA FOR CARBON SEAL AND MATING GEARSHAFT SEALING FACE. RUBS. N.025mm) FEELER GAGE TO ENSURE NO CLEARANCE EXISTS BETWEEN THE ADAPTER/SPACER/SEAL OVER 360 DEGREES.5 (REMOVE COVER AND INSPECT). FREEDOM OF MOVEMENT. NO. TOO HIGH ? YES NO NO SYSTEM NORMAL REPLACE OIL PRESSURE CHECK VALVE (REF. OIL PUMP PRESSURE RELIEF VALVE 5. FLOODED WITH OIL 2. NO. 3045542 SYMPTOMS SUSPECT LRU SMOKE FROM EXHAUST ON START−UP OR SHUTDOWN/ENGINE FLOODED WITH OIL/OIL ODOR IN COCKPIT LONG WET OR DRY OR REPETITIVE MOTORING RUNS CARRIED OUT ? 1.FAULT ISOLATION Page 115 Nov 04/2005 .5/P3 SWITCHING VALVE 6.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. ENGINE YES START ENGINE AND RUN AT GND IDLE FOR 5 MINUTES WITH AIR BLEED OFF. 6 & 7 BEARING TRANSFER TUBES 7. OIL PRESSURE REGULATING VALVE 4. 72−01−50). OK ? YES ADJUST/REPLACE OIL PRESSURE REGULATING VALVE YES (REF. 72−01−50). P2. OK ? YES SYSTEM NORMAL NO YES OIL PRESSURE TOO HIGH ? YES NO NO OIL PRESSURE INCREASES/DECREASES BETWEEN 25 AND 40% NH DURING START−UP OR SHUTDOWN ? DRAIN FROM OIL TANK TO MAX OIL LEVEL. 6 & 7 BEARING OIL SCAVENGE PUMP 8. OIL PRESSURE OK ? SYSTEM NORMAL NO CONT’D ON SHEET 2 CONT’D ON SHEET 2 C26217B Smoke from Exhaust on Startup or Shutdown/Engine Flooded With Oil/Oil Odor in Cockpit Figure 107 (Sheet 1 of 3) 72-00-01 ENGINE . OIL PRESSURE CHECK VALVE 3. OK ? YES SYSTEM NORMAL NO NO EXAMINE OIL LEVEL. VENT AND SCAVENGE TRANSFER TUBES OK ? NO CLEAN/REPLACE AS NECESSARY (REF.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. YES SYSTEM NORMAL NO NO ADD SPACERS (4 MAX) (REF. OK ? NO YES HAS THE P2.5/P3 SWITCHING VALVE.FAULT ISOLATION Page 116 Nov 04/2005 . 72−30−00). 72−30−00). 72−01−50). OK ? SYSTEM NORMAL NO EXAMINE P2. 72−01−50) YES CONT’D ON SHEET 3 C26218B Smoke from Exhaust on Startup or Shutdown/Engine Flooded With Oil/Oil Odor in Cockpit Figure 107 (Sheet 2) 72-00-01 ENGINE . 3045542 CONT’D FROM SHEET 1 CONT’D FROM SHEET 1 REPAIR/REPLACE OIL PUMP YES PRESSURE RELIEF VALVE (REF. 72−30−00). OK ? REPAIR/REPLACE AS NECESSARY (REF. YES NO. 6 & 7 BEARING.5/P3 SWITCHING VALVE FOUR (4) SPACERS? (REF. PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. INSPECTION /CHECK) NO SEE NOTE NOTE: INABILITY TO IDENTIFY AND/OR RECTIFY THE FAULT AFTER CARRYING OUT THE LISTED CHECKS INDICATES INTERNAL ENGINE DAMAGE/OIL LEAKAGE. REMOVAL/INSTALLATION) YES OIL FOUND IN INTERCOMPRESSOR CASE P2. 6 & 7 BEARING TRANSFER TUBES OR EXTERNAL PIPES OK ? NO BORESCOPE INSPECTION OF HP.5 PLENUM ? YES INVESTIGATE (REF. OIL STAINS/ COKING. REMOVE ENGINE FOR INVESTIGATION. BLADE SHIFT.FAULT ISOLATION Page 117 Nov 04/2005 . LP AND PT BLADES FOR STRUCTURAL INTEGRITY. YES BORESCOPE FIRST−STAGE PT BLADES TO CHECK FOR IMPACT DAMAGE TO LEADING NO EDGES AND/OR TIPS. GO TO: CHAPTER 05−50−00 UNSCHEDULED MAINTENANCE INSPECTION AT "ENGINE RELATED VIBRATION AND / OR CRACKED TUBE". RUBS. OK ? REMOVE ENGINE FOR INVESTIGATION (REF. C26219A Smoke from Exhaust on Startup or Shutdown/Engine Flooded With Oil/Oil Odor in Cockpit Figure 107 (Sheet 3) 72-00-01 ENGINE . 3045542 CONT’D FROM SHEET 2 NO. 72−01−50. AIRCRAFT MANUAL) YES NO REPLACE YES CABLES AND CONNECTIONS NO OK? (REF. AIRCRAFT MANUAL) RECTIFY OR REPLACE YES OIL PRESSURE TRANSDUCER (LOW OIL PRESSURE SWITCH) OK? (REF. AIRCRAFT MANUAL) NO REPLACE YES TURN PROPELLER. 5. AIRCRAFT MANUAL) GAGE OK? (REF.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 9. 4. ENGINE KEPT RUNNING LONGER THAN REQUIRED TO COMPLY WITH FLIGHT/MAINTENANCE MANUALS? YES OIL LEAKS OIL LEVEL FUEL COOLED OIL COOLER FUEL HEATER INDICATING SYSTEM PRESSURE RELIEF VALVE PRESSURE REGULATING VALVE PRESSURE OIL PUMP PRESSURE OIL CHECK VALVE REPLACE ENGINE NO OIL PRESSURE INDICATING SYSTEM NO OK? (REF. 3045542 SYMPTOMS SUSPECT LRU LOW OR LOSS OF OIL PRESSURE 1.FAULT ISOLATION Page 118 Nov 04/2005 . 3. 2. 8. LP AND HP ROTORS ANY UNUSUAL NOISE? YES PRESSURE REGULATING VALVE RESTRICTOR BLOCKED? (REF. 6. 7. 72−01−50) YES CLEAN OR REPLACE IS NOISE FROM AN ACCEPTABLE POWER TURBINE RUB? NO REPLACE ENGINE/ MODULE NO YES CONT’D ON SHEET 2 C25394 Low or Loss of Oil Pressure Figure 108 (Sheet 1 of 4) 72-00-01 ENGINE . 72−01−50) RECTIFY OR REPLACE YES PRESSURE OIL CHECK VALVE NO OK? (REF. FUEL HEATER 5. PRESSURE REGULATING VALVE 8. PRESSURE OIL PUMP 9. FUEL COOLED OIL COOLER 4.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. VISUALLY INSPECT CHIP DETECTORS (REF. 72−01−50) RECTIFY OR REPLACE YES CONT’D ON SHEET 3 C25395 Low or Loss of Oil Pressure Figure 108 (Sheet 2) 72-00-01 ENGINE . IS ENGINE SERVICEABLE? NO NO REPLACE ENGINE/ MODULE YES CHECK ENGINE FOR EXTERAL OIL LEAKS.FAULT ISOLATION Page 119 Nov 04/2005 . DEBRIS FOUND? CARRY OUT PROCEDURE FOR DEBRIS IN OIL SYSTEM (REF. 3045542 SUSPECT LRU 1. NOTE). 72−01−50) RECTIFY OR REPLACE YES PRESSURE OIL PUMP OK? NO (REF. PRESSURE RELIEF VALVE 7. OIL LEVEL 3. OK? RECTIFY (REF. INDICATING SYSTEM 6. 72−01−50) NO REPLACE (REF. SERVICING) NO OIL SMELLS OF FUEL? YES NO FUEL COOLED OIL NO COOLER OK? REPLACE (REF. 72−01−50) YES OIL TO FUEL HEATER OK? OIL PUMP PRESSURE RELIEF NO VALVE OK? (REF. 72−01−50) YES OIL LEVEL LOW? YES FILL TO CORRECT LEVEL (REF. OIL LEAKS 2. 72−01−50) RECTIFY OR REPLACE YES OIL PUMP PRESSURE REGULATING NO VALVE OK? (REF. 72−01−50). PRESSURE OIL CHECK VALVE SYMPTOMS LOW OR LOSS OF OIL PRESSURE CONT’D FROM SHEET 1 PATCH CHECK PRESSURE AND SCAVENGE YES OIL FILTERS. 2. 3045542 SYMPTOMS SUSPECT LRU LOW OR LOSS OF OIL PRESSURE 1. 5. NOTE) CHECK FILTERS VISUALLY AND CHIP DETECTORS FOR CIRCUIT COMPLETION (REF. 3. 6. 9. YES MONITOR ENGINE OIL CONSUMPTION FOR 65 FH CONT’D ON SHEET 4 C25396 Low or Loss of Oil Pressure Figure 108 (Sheet 3) 72-00-01 ENGINE .FAULT ISOLATION Page 120 Nov 04/2005 . OIL LEAKS OIL LEVEL FUEL COOLED OIL COOLER FUEL HEATER INDICATING SYSTEM PRESSURE RELIEF VALVE PRESSURE REGULATING VALVE PRESSURE OIL PUMP PRESSURE OIL CHECK VALVE CONT’D FROM SHEET 2 IF NOT RUN PREVIOUSLY. 7. 8. 72−01−50) DEBRIS FOUND? YES CARRY OUT PROCEDURE NO FOR DEBRIS IN OIL SYSTEM. 4. IS ENGINE SERVICEABLE? REPLACE ENGINE / MODULE YES NO NO WAS OIL LEVEL OK AFTER 10 MINUTE RUN AT 80% TORQUE? CARRY OUT PROCEDURE FOR HIGH OIL CONSUMPTION. RUN ENGINE AT 80% TORQUE FOR TEN MINUTES (REF.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 6. 7. 4. 8. IF DEBRIS FOUND CARRY OUT PROCEDURE FOR DEBRIS IN OIL SYSTEM (REF. 3.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 129). OIL LEAKS OIL LEVEL FUEL COOLED OIL COOLER FUEL HEATER INDICATING SYSTEM PRESSURE RELIEF VALVE PRESSURE REGULATING VALVE PRESSURE OIL PUMP PRESSURE OIL CHECK VALVE CONT’D FROM SHEET 3 CHECK TURBOMACHINERY AND RGB CHIP DETECTORS DAILY UNTIL 65 FH IS EXCEEDED. 72−01−50) AFTER 65 ± 5 FH. 5. 3045542 SYMPTOMS SUSPECT LRU LOW OR LOSS OF OIL PRESSURE 1. 2. CARRY OUT PATCH CHECK ON PRESSURE AND SCAVENGE OIL FILTERS (REF. FIG. NOTE: CAUSE OF LOW OR LOSS OF OIL PRESSURE MUST BE FOUND AND RECTIFIED BEFORE THE ENGINE IS RUN.FAULT ISOLATION Page 121 Nov 04/2005 . 9. C25397A Low or Loss of Oil Pressure Figure 108 (Sheet 4) 72-00-01 ENGINE . 4. 2. PRESSURE INDICATING SYSTEM OK? NO GAGE OK? NO OIL PRESSURE GAGE AIRFRAME WIRING HARNESS OIL PRESSURE TRANSDUCER OIL PRESSURE REGULATING VALVE OIL PRESSURE FILTER REPLACE (REF. AMM) YES YES NO CABLES AND CONNECTION OK? RECTIFY OR REPLACE (REF.FAULT ISOLATION Page 122 Nov 04/2005 . 72−01−50 YES SYSTEM NORMAL C25398 High Oil Pressure Figure 109 72-00-01 ENGINE . 3.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. AMM) YES OIL PRESSURE TRANSDUCER OK? SYSTEM NORMAL PRESSURE REGULATING VALVE OK? NO REPLACE (REF. ADJUSTMENT/TEST OR 72−01−50) NO YES SYSTEM NORMAL MAIN OIL PRESSURE FILTER OK? NO CLEAN OR REPLACE (REF. AMM) ADJUST OR REPLACE (REF. 3045542 SYMPTOMS SUSPECT LRU HIGH OIL PRESSURE 1. 5. AMM) REPLACE (REF. OIL SYSTEM OK? NO YES OIL TANK LEVEL OK? FUEL COOLED OIL COOLER OIL TEMPERATURE GAGE AIRFRAME WIRING HARNESS OIL TEMPERATURE TRANSMITTER NO FILL TO CORRECT LEVEL (REF.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 4. 72−01−50) YES SYSTEM NORMAL TEMPERATURE INDICATING SYSTEM OK? AIRFRAME AIR−COOLED NO OIL COOLER OK? GAGE OK? NO REPLACE AIR−COOLED OIL COOLER (REF.FAULT ISOLATION Page 123 Nov 04/2005 . 2. SERVICING) YES ENGINE FUEL−COOLED OIL COOLER BYPASS NO VALVE/INTERNAL PASSAGES OK? REPLACE FUEL−COOLED OIL COOLER (REF. AMM) NO REPLACE (REF. AMM) YES SYSTEM NORMAL OIL TEMPEATURE TRANSMITTER OK? C25399 High Oil Temperature Figure 110 72-00-01 ENGINE . AMM) YES YES CABLES AND CONNECTIONS OK? NO RECTIFY OR REPLACE (REF. 3045542 SYMPTOMS SUSPECT LRU HIGH OIL TEMPERATURE 1. 3. READING OK ? (REF. AFU 2. TORQUE SHAFT CHARACTERIZATION PLUG 5. 3045542 SUSPECT LRU SYMPTOMS INCORRECT TORQUE READING 1. TORQUE INDICATOR 4. 72−01−10) DO EEC FAULTS AS FOLLOWS: LRU FAULT CODES− 09/28/29/31/61 OR 74 YES SYSTEM NORMAL YES SYSTEM NORMAL RECTIFY NO NO CHARACTERIZATION PLUG TO CORRECT VALUE ? (SEE DATA PLATE) NO REPLACE AFU TRIM PLUG TO CORRECT VALUE (REF. (REF.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. DATA PLATE) YES REPLACE EEC (REF. REDUCTION GEARBOX TORQUE SHAFTS (a) DIGITAL (EEC) (b) ANALOG (AFU) CHANGE TORQUE INDICATOR. 72−01−10) READING OK ? NO YES NO REPLACE YES SYSTEM NORMAL INVESTIGATE REDUCTION GEARBOX TORQUE SHAFTS INVESTIGATE REDUCTION GEARBOX TORQUE SHAFTS C38584 Incorrect Torque Readings Figure 111 72-00-01 ENGINE .FAULT ISOLATION Page 124 Nov 04/2005 . EEC 3. AMM) READING OK ? YES NO (b) (a) REPLACE AFU. 3045542 SYMPTOMS SUSPECT LRU TORQUE FLUCTUATIONS 1.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 72−01−40) NO RECTIFY (REF. AMM) NO REPLACE (REF. PCU 3.FAULT ISOLATION Page 125 Nov 04/2005 . 72−01−10) YES YES PCU OK ? SYSTEM NORMAL FUEL SYSTEM OK ? YES SYSTEM NORMAL NO MFCU OK ? YES ELECTRONIC FUEL CONTROL SYSTEM OK ? C26221 Torque Fluctuations Figure 112 72-00-01 ENGINE . MFCU PROPELLER SYSTEM OK ? NO OVERSPEED GOVERNOR OK ? NO RESET OR REPLACE (REF. 72−01−50) NO REPLACE (REF. OVERSPEED GOVERNOR 2. AMM) YES FLOWMETER OK? SYSTEM NORMAL FUEL SYSTEM OK ? YES NO MFCU OK? REPLACE (REF. 72−01−40) C26222 Excessive Fuel Consumption Figure 113 (Sheet 1 of 2) 72-00-01 ENGINE . 72−01−40) NO RECTIFY OR REPLACE (REF. 3. 2. AMM) NO REPLACE (REF. 5.FAULT ISOLATION Page 126 Nov 04/2005 . 72−01−40) NO YES ELECTRONIC FUEL CONTROL SYSTEM OK ? NO RECTIFY (REF. AMM) YES YES CABLES AND CONNECTIONS OK ? NO RECTIFY OR REPLACE (REF. 6.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 72−01−40) YES SYSTEM NORMAL FLOW DIVIDER AND DUMP VALVE OK? YES FUEL MANIFOLD NO PACKINGS OK? REPLACE (REF. 3045542 SYMPTOMS SUSPECT LRU EXCESSIVE FUEL CONSUMPTION 1. 4. INDICATING SYSTEM OK ? NO GAGE OK? FUEL FLOWMETER GAGE AIRFRAME WIRING HARNESS FUEL FLOWMETER MFCU FLOW DIVIDER AND DUMP VALVE FUEL MANIFOLD PACKINGS NO REPLACE (REF. FAULT ISOLATION Page 127 Nov 04/2005 .PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 6. 5. 3045542 SUSPECT LRU SYMPTOMS EXCESSIVE FUEL CONSUMPTION HOT SECTION BORESCOPE INSPECTION (REF. NO FUEL FLOWMETER GAGE AIRFRAME WIRING HARNESS FUEL FLOWMETER MFC FLOW DIVIDER AND DUMP VALVE FUEL MANIFOLD PACKINGS CARRY OUT HSI (REF. INSPECTION/CHECK) OK? 1. 4. 3. 2. 72−03−00) YES COLD SECTION BORESCOPE INSPECTION OK? NO REPLACE ENGINE IF OUTSIDE LIMITS YES SYSTEM NORMAL C25414 Excessive Fuel Consumption Figure 113 (Sheet 2) 72-00-01 ENGINE . 72−01−40) NO IS HP FUEL FILTER CONTAMINATED ? (REF. AIRCRAFT SYSTEM 5. 3045542 SYMPTOMS SUSPECT LRU IMPENDING BYPASS INDICATOR ACTIVATED IS LP FUEL FILTER BYPASS INDICATOR ACTIVATED? YES IS FUEL IN AIRCRAFT FUEL TANKS CONTAMINATED? NO 1. AMM) CLEAN OR REPLACE ENGINE LP.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. AMM) FLUSH AIRCRAFT FUEL SYSTEM DOWNSTREAM OF DEFECT (REF. HP AND INLET FUEL FILTERS (REF. FLUSH & CLEAN AIRCRAFT FUEL TANKS FUEL SYSTEM & FILTERS FLUSH AIRCRAFT FUEL SYSTEM DOWNSTREAM OF DEFECT NO REPLACE FUEL PUMP AND FUEL HEATER REMOVE AND VISUALLY INSPECT LP. FUEL 2. FUEL PUMP NO 4. MFCU FIND & CORRECT SOURCE OF CONTAMINATION YES DRAIN. FLUSH AND CLEAN AIRCRAFT FUEL TANKS AND FUEL SYSTEM (REF.FAULT ISOLATION Page 128 Nov 04/2005 . FUEL HEATER 6. HP AND FUEL PUMP INLET FUEL FILTERS (REF. NOTE 2) NO REPAIR/REPLACE SWITCH (REF. NOTE 1) FILTER BYPASS NO SWITCH OK ? YES YES REPLACE FUEL PUMP (REF. 72−01−40) CONT’D ON SHEET 2 C26223A HP Fuel Filter Impending Bypass Indicator Activated Figure 114 (Sheet 1 of 2) 72-00-01 ENGINE . AMM) YES IS FUEL IN AIRCRAFT FUEL TAMKS CONTAMINATED? NO FIND AND CORRECT SOURCE OF CONTAMINATION YES DRAIN. 72−01−40) (REF. BYPASS SWITCH 3. 72−01−40) ARE LP AND INLET FUEL FILTERS CONTAMINATED ? NO AIRCRAFT SYSTEM OK ? REPAIR SYSTEM (REF. ACCELERATION.FAULT ISOLATION Page 129 Nov 04/2005 . THE EFFICIENCY OF THE CLEANING PROCEDURE DECREASES AND THE FILTER MAY HAVE TO BE REPLACED. OK ? REPLACE MFCU. F1. NO DECELERATION AND T.O. OK ? NO RETRIM EEC. PLA STAGGER OK? NO CHANGE MFCU (REF. POWER IN BOTH EEC AND MANUAL. CHECK G1. HOWEVER. C26224A HP Fuel Filter Impending Bypass Indicator Activated Figure 114 (Sheet 2) 72-00-01 ENGINE . 72−01−40) YES YES SYSTEM NORMAL NOTE 1: THE HP FUEL FILTER IS RECOMMENDED TO BE CLEANED PERIODICALLY. AFTER REPEATED CLEANING. FLOW DIVIDER AND FUEL PUMP (REF. 72−01−40) YES START BOTH ENGINES AND CHECK PLA STAGGER.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3045542 CONT’D FROM SHEET 1 CARRY OUT ENGINE GROUND RUN. NOTE 2: THE FUEL PUMP MUST BE CHANGED IF DEBRIS COLLECTED BY THE HP FUEL FILTER ARE GENERATED BY THE FUEL PUMP. 3045542 SYMPTOMS SUSPCT LRU PROPELLER SLOW TO UNFEATHER ENGINE CONTROL LINKAGE SYSTEM OK ? NO 1.FAULT ISOLATION Page 130 Nov 04/2005 .PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. AMM) NO REPLACE (REF. 72−01−50) YES SYSTEM NORMAL OIL SUPPLY OK ? YES SYSTEM NORMAL NO PCU OK ? YES PCU PUMP OK ? C26225 Propeller Slow to Unfeather Figure 115 72-00-01 ENGINE . AMM) NO REPLACE (REF. AMM) NO ADJUST (REF. PCU 2. PCU PUMP PCU TO MFCU CONTROL ROD ADJUSTMENT OK ? (REF. IS ECTM CARRIED OUT? AIRCRAFT AIR BLEED SYSTEM AIRCRAFT INDICATING SYSTEMS ECTM RECORDER AIR DATA COMPUTER ENGINE NO YES IS PARAMETER SHIFT CONSIDERED NORMAL FOR ENGINE RUNNING TIME (SEE NOTE 1)? CONT’D ON SHEET 3 YES CARRY OUT RECOMMENDED PREVENTATIVE MAINTENANCE (SEE NOTE 3) NO ANALYZE THE TYPE OF PARAMETER SHIFT SEEN ON ECTM PLOTS (SEE NOTE 2) ANALYZE ECTM PLOTS FOR BOTH ENGINES OF SAME AIRCRAFT. 3. AIR DATA COMPUTER AND WIRING OK? NO RECTIFY (REF. ARE PARAMETER SHIFTS SIMILAR (SEE NOTE 4)? YES NO AIRCRAFT OAT. 4. AMM) CONT’D ON SHEET 2 C25389 Performance Deterioration (ECTM shift) or High ITT (T6) Figure 116 (Sheet 1 of 6) 72-00-01 ENGINE . AMM) YES CARRY OUT POWER ASSURANCE CHECK OF AFFECTED ENGINE. ALTITUDE AND SPEED INDICATING SYSTEMS OK? NO RECTIFY (REF. COMPARE WITH POWER ASSURANCE CHECK CARRIED OUT AT ENGINE INSTALLATION.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3045542 SYMPTOMS SUSPECT LRU ECTM PARAMETER SHIFT ENGINE ITT/T6 TEMPERATURE LIMITED 1. RECORD DIFFERENCES (SHIFT) IN PARAMETERS. 5. 2.FAULT ISOLATION Page 131 Nov 04/2005 . AMM) YES ECTM RECORDER OK? NO RECTIFY (REF. 4. AMM) NO RECTIFY (REF. AIRCRAFT AIR BLEED SYSTEM AIRCRAFT INDICATING SYSTEMS ECTM RECORDER AIR DATA COMPUTER ENGINE CONT’D FROM SHEET 1 SIGNIFICANT DIFFERENCE BETWEEN ECTM AND POWER ASSURANCE PARAMETER SHIFTS RECORDED (SEE NOTE 5)? YES AIR BLEED SYSTEM NO PRESSURE REGULATING VALVE OK? RECTIFY (REF. 3. 72−03−00) NO CARRY OUT AN HSI (REF. AMM) YES AIR BLEED SYSTEM DUCTING OK? COMPONENT DETERIORATION LIMITS EXCEEDED? YES CARRY OUT AN HSI (REF. SHEETS 4 AND 5) NO RECTIFY (REF. 3045542 SYMPTOMS SUSPECT LRU ECTM PARAMETER SHIFT ENGINE ITT/T6 TEMPERATURE LIMITED 1. 5.FAULT ISOLATION Page 132 Nov 04/2005 .PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. POWER ASSURANCE CHECK OK? YES SYSTEM NORMAL C25390 Performance Deterioration (ECTM shift) or High ITT (T6) Figure 116 (Sheet 2) 72-00-01 ENGINE . 2. 72−03−00) NO CHECK T6 SYSTEM AND REPEAT POWER ASSURANCE CHECK (SEE NOTE 6). AMM) YES NO AIR BLEED SYSTEM SHUT−OFF VALVE OK? TROUBLESHOOT (REF. RECORD DIFFERENCES IN PARAMETERS (SEE NOTE 3) YES AIR BLEED SYSTEM PRESSURE REGULATING VALVE OK? NO RECTIFY (REF. 72−03−00) YES SYSTEM NORMAL C25391 Performance Deterioration (ECTM shift) or High ITT (T6) Figure 116 (Sheet 3) 72-00-01 ENGINE .FAULT ISOLATION Page 133 Nov 04/2005 . AMM) YES NO AIR BLEED SYSTEM SHUT−OFF VALVE OK? RECTIFY (REF. 72−00−00) CARRY OUT AN HSI (REF.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3045542 SYMPTOMS SUSPECT LRU ECTM PARAMETER SHIFT ENGINE ITT/T6 TEMPERATURE LIMITED 1. 3. 2. 72−03−00) NO CHECK T6 SYSTEM AND REPEAT NO POWER ASSURANCE CHECK (SEE NOTE 6). AMM) YES AIR BLEED SYSTEM DUCTING OK? NO RECTIFY (REF. AIRCRAFT AIR BLEED SYSTEM AIRCRAFT INDICATING SYSTEMS ECTM RECORDER AIR DATA COMPUTER ENGINE CONT’D FROM SHEET 1 POWER ASSURANCE CHECK OF YES AFFECTED ENGINE OK? (SEE NOTE 7) NO COMPARE POWER ASSURANCE CHECK WITH POWER ASSURANCE CHECK CARRIED OUT AT ENGINE INSTALLATION. 5. 4. AMM) TROUBLESHOOT (REF. SHEETS 4 AND 5) COMPONENT DETERIORATION YES LIMITS EXCEEDED? (REF. POWER ASSURANCE CHECK OK? CARRY OUT AN HSI (REF. INSPECT/REPAIR − AIRCRAFT/ENGINE WF INDICATING SYSTEM. − INTERCOMPRESSOR BLEED VALVE SEIZED IN OPEN POSITION. INSPECT/REPAIR LP IMPELLER FOD. INSPECT/REPAIR − CRACKED LP DIFFUSER EXIT DUCT.FAULT ISOLATION Page 134 Nov 04/2005 . INSPECT/REPAIR IF LIMITS EXCEEDED CARRY OUT AN HSI − IF LIMITS EXCEEDED CARRY OUT AN HSI − REPLACE ENGINE IF DEFECT CONFIRMED − HIGH OIL CONSUMPTION EVIDENT HEAVY BREATHING C20168B Performance Deterioration (ECTM shift) or High ITT (T6) Figure 116 (Sheet 4) 72-00-01 ENGINE . LEAKING GAS GENERATOR DRAIN VALVE. ENGINE AIR INLET OBSTRUCTED. INSPECT/REPAIR AIRCRAFT/ENGINE NL INDICATING SYSTEM. CARRY OUT AN HSI IF ITT/T6 LIMIT IS EXCEEDED CHECK STANDARD HOT SECTION DETERIORATION. BORESCOPE HP VANE SEGMENTS AND BLADES HP TURBINE BLADE TIP OXIDATION/RUB. LP IMPELLER CONTAMINATION. INSPECT/REPLACE P2. INSPECT/REPAIR AIRCRAFT/ENGINE TORQUE INDICATING SYSTEM INSPECT/REPAIR − ITT/T6 USUALLY DECREASES WHEN PROBES UNSERVICEABLE REMOVE ENGINE IF FOD EXCEED LIMITS − − − AIRCRAFT/ENGINE ITT/T6 INDICATING SYSTEM (SEE NOTE 8) INSPECT/REPAIR OR − OR − − AIRCRAFT/ENGINE NH INDICATING SYSTEM. RUB. 3045542 ENGINE PARAMETERS ITT/T6 NH NL WF ACTION REQUIRED PROBABLE DEFECT REMARKS AIRCRAFT/ENGINE TORQUE INDICATING SYSTEM.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. BORESCOPE INSPECT COMPRESSOR WASH PT BLADE RUB.5/P3 SWITCHING VALVE COMPLETELY OR PARTIALLY SEIZED IN P3 POSITION. CHECK VALVE HP TURBINE VANE SEGMENTS BURNED/FLOW AREA INCREASED. LP TURBINE BLADE TIP OXIDATION/RUB. LP TURBINE STATOR VANES BURNED/FLOW AREA INCREASED. − − BORESCOPE LP STATOR VANES & LP BLADES GAS GENERATOR CASE CRACKED AT FUEL NOZZLE OR P3 BLEED BOSS.5 AIR LEAKS FROM ENGINE/AIRFRAME SYSTEM. INSPECT/REPAIR − OR OR IF LIMITS EXCEEDED CARRY OUT AN HSI P2. 3045542 C35198 Performance Deterioration (ECTM shift) or High ITT (T6) Figure 116 (Sheet 5) 72-00-01 ENGINE .PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO.FAULT ISOLATION Page 135 Nov 04/2005 . THE TREND MONITORING PROGRAM IS THE MAIN TOOL FOR HEALTH MONITORING OF PW100 ENGINES. INSPECTION/CHECK). WF AND ITT/T6 MAY INDICATE THAT THE CONDITION OF THE INTERNAL ENGINE COMPONENTS HAVE DETERIORATED. WHEN AN ENGINE IS T6 LIMITED ON CLIMB OR CRUISE AND THE POWER ASSURANCE CHECK IS SATISFACTORY. BORESCOPE INSPECTION IS THEN RECOMMENDED IN ORDER TO DETERMINE WHETHER COMPONENT DETERIORATION EXCEEDS LIMITS (REF. 9. 7. 3045542 6. AN INCREASE IN ITT/T6 TEMPERATURE WITHOUT OTHER PARAMETER CHANGES MAY BE THE RESULT OF DEFECTIVE FUEL NOZZLES ALTERING COMBUSTION AND CHANGING THE T6 TEMPERATURE DISTRIBUTION. THE DEFECT IS WITHIN THE AIRCRAFT BLEED SYSTEM ASSOCIATED WITH THE AFFECTED ENGINE. NL.FAULT ISOLATION Page 136 Nov 04/2005 . C35199A Performance Deterioration (ECTM shift) or High ITT (T6) Figure 116 (Sheet 6) 72-00-01 ENGINE . CHANGES OF ENGINE PARAMETERS LIKE NH.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. TO REMOVE DOUBTS. 8. A T6 SYSTEM CHECK (INCLUDING AN INDIVIDUAL T6 THERMOCOUPLE CHECK) AND A POWER ASSURANCE CHECK WITH THE AIR BLEED PORTS BLANKED-OFF IS RECOMMENDED BEFORE ENGINE REMOVAL. CONDITION LEVER ADVANCED AT OR ABOVE 10% AND AIR BLEED OFF ? NO REPEAT START YES ARE FLOW DIVIDER DUMP LINE AND/OR GAS GENERATOR DRAIN LINES AND VALVES FREE FROM RESTRICTIONS ? (i. 72−01−10) C26226A Hot Start Figure 117 (Sheet 1 of 2) 72-00-01 ENGINE . POWER SUPPLY 4.e. STARTER 6. MFCU 7. COKING) NO RECTIFY YES CARRY OUT T6 SYSTEM CHECK (REF. EEC 2. ELECTRICAL CONNECTORS 5. REFER TO OVERTEMPERATURE CHART (REF. WIRING HARNESS 3. 72−01−60). FUEL PUMP 8. 05−10−00) TO ENSURE TEMPERATURE LIMITS HAVE NOT BEEN EXCEEDED. 3045542 SYMPTOMS SUSPECT LRU HOT START 1.FAULT ISOLATION Page 137 Nov 04/2005 . 72−01−10) START OK ? YES SYSTEM NORMAL NO WIRING HARNESS OK ? YES CHANGE MFCU (REF. SYSTEM OK? NO RECTIFY YES ENGINE INLET OBSTRUCTED ? YES REMOVE OBSTRUCTION NO ENGINE STARTS NORMALLY IN MANUAL ? NO CONT"D ON SHEET 2 YES REPLACE EEC (REF. TURBOMACHINERY NOTE: BEFORE STARTING ENGINE. 72−01−40) NO REPAIR/REPLACE (REF.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. AMM). 3045542 CONT’D FROM SHEET 1 STARTER POWER SUPPLY OK ? NO RECTIFY (REF. AMM) YES STARTER ELECTRICAL CONNECTORS OK ? YES HP ROTOR ROTATES FREELY ? YES NO CHANGE STARTER (REF. START OK ? YES SYSTEM NORMAL NO CHANGE MFCU (REF. 72−01−40). 72−01−40) REPLACE FUEL PUMP (REF. HP ROTOR ROTATES FREELY ? REPLACE TURBOMACHINERY (REF.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 72−02−00) NO YES SYSTEM NORMAL C26227A Hot Start Figure 117 (Sheet 2) 72-00-01 ENGINE .FAULT ISOLATION Page 138 Nov 04/2005 . AMM) NO RECTIFY (REF. OVERSPEED GOVERNOR INVESTIGATE NP INDICATING SYSTEM (REF.FAULT ISOLATION Page 139 Nov 04/2005 . AMM) NO RECTIFY OR REPLACE (REF.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. AMM) ALL OTHER ENGINE YES PARAMETERS STABLE ? NO PROPELLER SYSTEM OK ? YES SYSTEM NORMAL NO PCU OK ? NO RECTIFY OR REPLACE (REF. 3045542 SYMPTOMS SUSPECT LRU PROPELLER SPEED (NP) FLUCTUATIONS 1. 72−01−50) YES PROPELLER OVERSPEED GOVERNOR OK ? C26228 Propeller Speed (NP) Fluctuations Figure 118 72-00-01 ENGINE . NP PULSE PICKUP PROBE 2. PCU 3. AMM) YES REGULATING VALVE RESTRICTOR OK ? YES OIL PRESSURE CHECK VALVE OK ? YES SYSTEM NORMAL REGULATING VALVE OK ? OIL PRESSURE INDICATING SYSTEM OK ? NO GAGE OK ? YES YES CABLES AND CONNECTIONS OK ? SYSTEM NORMAL YES OIL PRESSURE TRANSDUCER OK ? C26229A Slow Oil Pressure Buildup after 40% NH During Starting Figure 119 72-00-01 ENGINE . AMM) NO RECTIFY OR REPLACE (REF. 3045542 SYMPTOMS SUSPECT LRU SLOW OIL PRESSURE BUILDUP AFTER 40% NH DURING STARTING OIL SYSTEM OK ? NO YES 1. OILPRESSURE CHECK VALVE 3. AIRFRAME WIRING HARNESS 6.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 72−01−50) NO RECTIFY OR REPLACE (REF. AMM) NO REPLACE (REF. OIL PRESSURE GAGE 5. OIL PRESSURE REGULATING VALVE 4.FAULT ISOLATION Page 140 Nov 04/2005 . OIL PRESSURE REGULATING VALVE RESTRICTOR 2. 72−01−50) NO RECTIFY OR REPLACE (REF. OIL PRESSURE TRANSDUCER OIL TEMPERATURE OK ? NO RECHECK AT HIGHER OIL TEMPERATURES NO RECTIFY OR REPLACE (REF. 72−01−50) NO RECTIFY OR REPLACE (REF. 5 CHECK VALVE 8. LP DIFFUSER DUCTS HIGH ITT/T6 TEMPERATURE TEST ENGINE AND INDICATING SYSTEM WITH TEST SET EET 4000 INDICATING SYSTEM OK ? NO GAGE OK ? NO REPLACE (REF. AMM) NO RECTIFY OR REPLACE (REF. 72−01−60) YES TRIM RESISTER OK ? NO REPLACE (REF. THERMOCOUPLES 5. AMM) YES YES CABLES AND CONNECTIONS OK ? YES NO T6 WIRING HARNESS OK ? RECTIFY OR REPLACE (REF. T6 WIRING HARNESS 4. P2. AIRFRAME WIRING HARNESS 3.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. ITT GAGE 2. 3045542 SYMPTOMS SUSPECT LRU 1. T6 TRIM RESISTOR 6. P3 BLEED VENTURI 9. 72−01−60) YES SYSTEM NORMAL THERMOCOUPLES OK ? C74845 High ITT/T6 Temperature Figure 120 (Sheet 1 of 2) 72-00-01 ENGINE .FAULT ISOLATION Page 141 Nov 04/2005 . 72−01−60) NO REPLACE (REF. INTERCOMPRESSOR BLEED VALVE & TORQUE MOTOR 7. 3045542 SYMPTOMS SUSPECT LRU HIGH ITT/T6 TEMPERATURE AIR BLEED SYSTEM OK ? NO 1. T6 WIRING HARNESS 4. ITT GAGE 2. 72−30−00) YES P3 BLEED AIR VENTURI ADAPTER OK ? CHECK THE FOLLOWING FOR EXTERNAL AIR LEAKS: SWITCHING VALVE HOUSING SEAT SWITCHING VALVE BOSS LP DIFFUSER DUCTS GAS GENERATOR DRAIN. P2.5 CHECK VALVE OK ? NO REPLACE (REF. 72−01−30) YES SYSTEM NORMAL P2. THERMOCOUPLES 5.FAULT ISOLATION Page 142 Nov 04/2005 . P3 AND FUEL NOZZLE BOSSES AND ADJACENT AREA NL PROBE PACKINGS SEAL TUBE (NL PROBE OPPOSITE POSITION) PACKINGS T6 THERMOCOUPLE LOOSE/MISSING P2. P3 BLEED VENTURI 9.5 CHECK VALVE 8. LP DIFFUSER DUCTS NO REPLACE (REF.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 72−01−30) REPLACE AS REQUIRED NO SYSTEM NORMAL C26232 High ITT/T6 Temperature Figure 120 (Sheet 2) 72-00-01 ENGINE .5 AIR−TO−REAR INLET CASE TUBE OK ? NO YES REPLACE (REF. INTERCOMPRESSOR BLEED VALVE AND TORQUE MOTOR INTERCOMPRESSOR BLEED VALVE AND SERVO VALVE OK ? YES 7. AIRFRAME WIRING HARNESS 3. T6 TRIM RESISTER 6. PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO.FAULT ISOLATION Page 143 Nov 04/2005 . AMM) NO RECTIFY OR REPLACE (REF. EEC 7. MFCU NO LP COMPRESSOR BLEED SHROUD OK? NO RECTIFY OR REPLACE (REF. 72−01−30) YES P2. AFU 8. 3045542 SYMPTOMS SUSPECT LRU ENGINE STALL AIR SYSTEM OK ? YES 1. INTERCOMPRESSOR BLEED VALVE 5. 72−01−30) NO RECTIFY OR REPLACE (REF. 72−30−00) NO RECTIFY OR REPLACE (REF. 72−01−30) OK ? C26233A Engine Stall Figure 121 (Sheet 1 of 2) 72-00-01 ENGINE .5 CHECK VALVE OK ? YES INTERCOMPRESSOR BLEED VALVE SERVO VALVE OK ? YES SYSTEM NORMAL TEST INTERCOMPRESSOR BLEED VALVE (REF.5 CHECK VALVE 3. P2. MFCU P3 AIR TUBE 6. INTERCOMPRESSOR BLEED VALVE TORQUE MOTOTR 4. LP COMPRESSOR BLEED SHROUD 2. AMM) YES YES BORESCOPE INSPECTION OF IMPELLERS.5 CHECK VALVE 3. 3045542 SYMPTOMS SUSPECT LRU ENGINE STALL ENGINE STEADY STATE PERFORMANCE NORMAL RELATIVE TO GROUND RUN CHECK CHARTS ? 1. MFCU NO INSTRUMENTATION OK ? NO RECTIFY (REF. INTERCOMPRESSOR BLEED VALVE TORQUE MOTOR 4. 72−01−30) NO RECTIFY OR REPLACE COMPONENTS YES ELECTRONIC FUEL CONTROL CONTROL SYSTEM OK ? LRU FAULT CODE: 85 C38585 Engine Stall Figure 121 (Sheet 2) 72-00-01 ENGINE .FAULT ISOLATION Page 144 Nov 04/2005 . LP COMPRESSOR BLEED SHROUD 2. EEC 7. MFCU P3 AIR TUBE 6.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. INSPECTION/CHECK) OK ? SYSTEM NORMAL FUEL SYSTEM OK ? YES SYSTEM NORMAL NO P3 LINE TO MFCU OK ? NO RECTIFY OR REPLACE DEFECTIVE COMPONENTS NO RECTIFY (REF. VANES AND BLADES (REF. INTERCOMPRESSOR BLEED VALVE 5. DIFFUSERS. TURBINES. P2. P. A BORESCOPE INSPECTION SHOULD BE CARRIED OUT THE FIRST TIME A PROPELLER DOES NOT ROTATE MANUALLY OR WHEN THE BEHAVIOR OF THE PROPELLER DURING START−UP/SHUTDOWN DEVIATES FROM ITS USUAL PATTERN. THIS IS NORMAL AND USUALLY DISAPPEARS DURING ENGINESTART. C25382B Unable to Rotate Propeller Manually after Engine Shutdown/Propeller Does Not Rotate after Engine Start Figure 122 72-00-01 ENGINE . SYSTEM NORMAL NO REMOVE/SEND ENGINE FOR INVESTIGATION (REF. PLATFORM RUBS OR EVIDENCE OF OIL STAINS (REF.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO.FAULT ISOLATION Page 145 Nov 04/2005 . YES PROPELLER SHAFT ROTATES FREELY WITH NO RUBBING NOISE? INSTALL A SERVICEABLE POWER TURBINE ASSEMBLY (REF. STATOR DISTORTION AND TIGHT TIP CLEARANCES CAN CAUSE BLADE RUBBING. IS RUB AUDIBLE? NO YES CAN POWER TURBINE ASSY. (REF. INSPECTION/CHECK). AMM). 3045542 SUSPECT LRU SYMPTOMS 1) UNABLE TO ROTATE PROPELLER MANUALLY ENGINE SEVERAL MINUTES AFTER ENGINE SHUTDOWN 2) PROPELLER DOES NOT ROTATE AFTER ENGINE START 3) LOUD RUBBING NOISE COMING FROM BACK END OF ENGINE WHEN PROPELLER IS ROTATED MANUALLY 4) OIL SMELL IN CABIN BLEEDS 5) VIBRATION DURING PROPELLER UNFEATHERING SEQUENCE BORESCOPE THE FIRST− STAGE PT BLADES TO CHECK FOR BLADE SHIFT.T. OK (REF. LEADING EDGE/TIP IMPACT DAMAGE. BE REMOVED WITHOUT REMOVAL OF ENGINE? NO REMOVE ENGINE (REF. NOTE)? YES PROPELLER ROTATES FREELY AT SUBSEQUENT ENGINE START − FREES UP AT GI? YES RUB PERSISTS 100 HOURS AFTER NEW/HSI/OVERHAUL NO YES NO IMMEDIATELY AFTER SHUTDOWN NO (WHEN ENGINE IS HOT) ROTATE PROPELLER. 72−03−00. NOTE: WHEN THE ENGINE HAS COOLED AND THE TEMPERATURE EQUALIZED. YES REMOVE POWER TURBINE ASSY. 72−03−00/TURBOMACHINERY REMOVAL). AMM). TURBOMACHINERY − INSTALLATION) AND RETURN ENGINE TO SERVICE. PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. MODULE MAGNETIC CHIPS FOUND NO ON CHIP DETECTOR? YES TROUBLESHOOT (REF.FAULT ISOLATION Page 146 Nov 04/2005 . 3045542 SYMPTOMS SUSPECT LRU ELECTRICAL CIRCUIT COMPLETED ON CHIP DETECTOR 1. INDICATING SYSTEM 3. DEBRIS IN OIL SYSTEM) CHIP DETECTOR CONTINUITY OK? REPLACE CHIP DETECTOR (REF. 72−01−50) NO YES INDICATING SYSTEM OK? NO RECTIFY YES SYSTEM NORMAL C25401 Chip Detector Circuit Completion Figure 123 72-00-01 ENGINE . CHIP DETECTOR 2. FAULT ISOLATION Page 147 Nov 04/2005 . CARBON CAN BE IDENTIFIED AS FINE BLACK SOOTY PARTICLES. NOTE 2: REVIEW/ADJUST OIL FILTER CLEANING OR REPLACEMENT INTERVAL BASED ON IMPENDING BYPASS EXPERIENCES. 72−01−50 DID PATCH CHECK REVEAL MATERIAL OTHER THAN FINE CARBON PARTICLES NOTE 1 NO CLEAN OR CHANGE OIL FILTER NOTE 2 RETURN ENGINE TO SERVICE YES REFER TO EMM 72−01−50 PAR. WHICH MAY NOT BE DISLODGED FROM FILTER ELEMENT DURING PATCH CHECK.H FOR MAINTENANCE RECOMMENDATION REFER TO FAULT ISOLATION CHART FIG.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. BYPASS INDICATOR 2. 3045542 SYMPTOMS SUSPECT LRU BYPASS INDICATOR ACTIVATED SCAVAENGE OIL FILTER BYPASS ACTIVATED? 1. C26235C Main Oil Filter Impending Bypass Indicator Activated Figure 124 (Sheet 1 of 2) 72-00-01 ENGINE . ENGINE REFER TO SCAVENGE OIL FILTER BYPASS INDICATOR ACTIVATION PROCEDURE YES NO REMOVE MAIN OIL FILTER CHIP DETECTOR & STRAINER IS MAIN OIL FILTER CONTAMINATED ? NO REPLACE BYPASS INDICATOR YES CARRY OUT PATCH CHECK REF. 128 OF DEBRIS IN OIL SYSTEM NOTE 1: THE MOST COMMON NON−METALLIC CONTAMINATION IS CARBON PARTICLES CAUSED BY THERMAL BREAKDOWN OF THE OIL DUE TO EXPOSURE TO HIGH TEMPERATURE. AIRCRAFT OIL COOLER. FLUSH AIRCRAFT OIL SYSTEM NO RETURN TO STANDARD BYPASS INDICATOR. ASSOCIATED HOUSING AND CHIP DETECTOR STRAINER. AN ASSESSMENT OF AMOUNT OF CONTAMINATION CAN INDICATE WHETHER A BYPASS HAS ACTUALLY OCCURRED.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3045542 Cont’ d from Sheet 1 IS BYPASS INDICATOR ACTIVATED ? YES REPLACE ENGINE.FAULT ISOLATION Page 148 Nov 04/2005 . IF DEBRIS IS DEPOSITED ON MOST OF SURFACE OF FILTER ELEMENT. PCU & REQUIRED PROPELLER COMPONENTS. IT CAN BE CONSIDERED THAT A BYPASS HAS OCCURRED. C35215A Main Oil Filter Impending Bypass Indicator Activated Figure 124 (Sheet 2) 72-00-01 ENGINE . CHECK INTERVAL. NOTE: AN IMPENDING BYPASS INDICATION DOES NOT NECESSARILY MEAN THAT OIL FILTER WAS BYPASSED. CARBON CAN BE IDENTIFIED AS FINE BLACK SOOTY PARTICLES. WHICH MAY NOT BE DISLODGED FROM FILTER ELEMENT DURING PATCH CHECK. CHIP DETECTOR AND STRAINERS IS RGB SCAVENGE FILTER CONTAMINATED WITH LOOSE DEBRIS ? NO REPLACE RGB SCAVENGE FILTER BYPASS INDICATOR YES DID PATCH CHECK REVEAL MATERIAL OTHER THAN FINE CARBON PARTICLES NOTE 1 NO CLEAN OR CHANGE OIL FILTER NOTE 2 RETURN ENGINE TO SERVICE YES REFER TO EMM 72−01−50 PAR.FAULT ISOLATION Page 149 Nov 04/2005 . C26236C RGB Scavenge Oil Filter Impending Bypass Indicator Activated Figure 125 (Sheet 1 of 2) 72-00-01 ENGINE . 3045542 SYMPTOMS SUSPECT LRU BYPASS INDICATOR ACTIVATED 1. REDUCTION GEARBOX REFER TO MAIN OIL FILTER BYPASS INDICATOR ACTIVATION PROCEDURE YES MAIN OIL BYPASS INDICATOR ACTIVATED ? NO REMOVE RGB SCAVENGE FILTER.H FOR MAINTENANCE RECOMMENDATION REFER TO FAULT ISOLATION CHART FIG. NOTE 2: REVIEW/ADJUST OIL FILTER CLEANING OR REPLACEMENT INTERVAL BASED ON IMPENDING BYPASS EXPERIENCES. 128 OF DEBRIS IN OIL SYSTEM NOTE 1: THE MOST COMMON NON−METALLIC CONTAMINATION IS CARBON PARTICLES CAUSED BY THERMAL BREAKDOWN OF THE OIL DUE TO EXPOSURE TO HIGH TEMPERATURE. BYPASS INDICATOR 2.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO.FAULT ISOLATION Page 150 Nov 04/2005 . 3045542 C35213 RGB Scavenge Oil Filter Impending Bypass Indicator Activated Figure 125 (Sheet 2) 72-00-01 ENGINE . MFC 3. FUEL MANIFOLD TRANSFER TUBE PACKING 10.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. EEC 2. OK? YES 8. CONDITION LEVER RIGGING 5. ELECTRICAL HARNESS 4. P3 LINE 6. FUEL FLOWMETER 12.FAULT ISOLATION Page 151 Nov 04/2005 . 3045542 SYMPTOMS SUSPECT LRU ENGINE DOES NOT REACH GROUND IDLE SPEED WITHIN 30 SECONDS REPEAT START WITH EEC SELECTED OFF. STARTER REPLACE MFC (REF. FLOW DIVIDER & DUMP VALVE 9. FUEL PUMP 13. Py LINE 7. 72−01−40) START OK? NO NO CONTACT P&WC YES RECITIFY/REPLACE EEC. TURBOMACHINERY 15. START OK? YES SYSTEM NORMAL NO REPLACE ELECTRICAL HARNESS. START OK? YES NO 1. AIRCRAFT BOOSTER PUMPS 11. FUEL NOZZLES 14. OVERSPEED GOVERNOR CHECK EEC FAULT CODES. START OK? YES NO CONTACT P&WC FUEL FLOW HIGHER THAN 90 PPH WHEN CLA MOVED TO FEATHER? YES CONT’D ON SHEET 2 (A) NO CHECK CLA RIGGING OK? NO RECITIFY YES CONT’D ON SHEET 2 (B) C76749 Hung Start Figure 126 (Sheet 1 of 4) 72-00-01 ENGINE . START OK? YES REFER TO AMM FOR MOTIVE FLOW / JET PUMP INSPECTION REPLACE OVERSPEED GOVERNOR. START OK? FUEL FLOW DECREASES AFTER LIGHT UP? YES YES REPLACE Py LINE START OK? NO NO SYSTEM NORMAL YES PLUG MOTIVE FLOW LINE AT MFC. START OK? NO YES SYSTEM NORMAL CONTACT P&WC SYSTEM NORMAL NO CONT’D ON SHEET 3 (C) CONTACT P&WC C76750 Hung Start Figure 126 (Sheet 2) 72-00-01 ENGINE . START OK? NO REFER TO AMM FOR DRAIN SYSTEM INSPECTION YES YES CONTACT P&WC NO CONTACT P&WC CONT’D FROM SHEET 1 (B) YES FUEL DRAINING FROM FLOW DIVIDER AND DUMP VALVE DURING START? YES REPLACE FLOW DIVIDER AND DUMP VALVE. START OK? NO NO FUEL DRAINING FROM FUEL MANIFOLD DRAIN DURING START OK? YES REPLACE TRANSFER TUBE PACKINGS. 3045542 CONT’D FROM SHEET 1 (A) FUEL FLOW DOES NOT INCREASE OR INCREASES SLIGHTLY AFTER LIGHT UP? YES P3 LINE TO MFC BLOCKED OR LEAKING? REPAIR OR REPLACE NO NO CONT’D ON SHEET 4 (D) NO YES PLUG Py LINE AT MFC. START OK? NO DISCONNECT MFC DRAIN.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO.FAULT ISOLATION Page 152 Nov 04/2005 . 3045542 CONT’D FROM SHEET 2 (C) ARE LP/HP FUEL FILTER BYPASS INDICATORS ACTIVATED? YES CARRY OUT TROUBLESHOOTING CHARTS FOR LP/HP FUEL FILTER BYPASS INDICATORS ACTIVATED NO ARE AIRCRAFT BOOSTER PUMPS WORKING? NO REPAIR OR REPLACE (REF.FAULT ISOLATION Page 153 Nov 04/2005 .PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. AMM) YES REPLACE FUEL FLOWMETER START OK? YES SYSTEM NORMAL NO REPLACE FLOW DIVIDER AND DUMP VALVE START OK? YES SYSTEM NORMAL NO REPLACE MFC AND FUEL PUMP START OK? YES SYSTEM NORMAL NO REPLACE FUEL NOZZLES START OK? YES SYSTEM NORMAL NO CONTACT P&WC C76751 Hung Start Figure 126 (Sheet 3) 72-00-01 ENGINE . IS THERE EVIDENCE OF RUBBING? REPLACE TURBOMACHINERY MODULE YES NO NO REPLACE STARTER.FAULT ISOLATION Page 154 Nov 04/2005 . AMM) YES CONTACT P&WC C76752 Hung Start Figure 126 (Sheet 4) 72-00-01 ENGINE . 3045542 CONT’D FROM SHEET 2 (D) CHECK IF HP ROTOR IS HARD TO ROTATE OR MAKES NOISE? YES BORESCOPE HPT ROTOR. ROTATION/START OK? YES SYSTEM NORMAL NO REPLACE FUEL PUMP ROTATION/START OK? YES SYSTEM NORMAL NO CONTACT P&WC CHECK THE STARTER BRUSHES.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. POWER SUPPLY. STARTER OK? NO RECTIFY (REF. INSPECT ASSOCIATED OIL FILTER AND CHIP DETECTOR. TYPE AND ORIGIN OF DEBRIS. 3045542 REMOVE ASSOCIATED OIL FILTER AND CHIP DETECTOR. IF IT IS A NON−ALLOWABLE DEBRIS. DEBRIS ORIGINATED IN TURBOMACHINERY? YES YES SEE SHEET 2 REFER TO CHART "OIL DEBRIS FROM TURBOMACHINERY" NO REFER TO CHART "OIL DEBRIS FROM RGB" C74110 Debris in Oil System Figure 127 (Sheet 1 of 2) 72-00-01 ENGINE . SEND DEBRIS TO AN APPROVED LABORATORY. PENDING RESULT OF LABORATORY ANALYSIS.72−01−50). RECORD CATAGORY. RETURN ENGINE TO SERVICE. IS DEBRIS ALLOWABLE? YES NO IS DEBRIS NON−ALLOWABLE CATAGORY 1? NO CLEAN AND INSTALL OIL FILTERS. COLLECT DEBRIS FOUND. STRAINER. DETERMINE IF DEBRIS FOUND IS AN ALLOWABLE OR A NON−ALLOWABLE DEBRIS (REF. REFER TO CHART "EVALUATION OF LABORATORY REPORT" RECORD CATAGORY. DETERMINE THE CATAGORY (REF. SEND DEBRIS TO AN APPROVED LABORATORY. CHIP DETECTOR STRAINERS AND CHIP DETECTORS. TYPE AND ORIGIN OF DEBRIS.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO.FAULT ISOLATION Page 155 Nov 04/2005 .72−01−50). IS DEBRIS IDENTIFIABLE AS A NO. 3045542 CONT’D FROM SHEET 1 RECORD CATAGORY. IF THE AMOUNT OF MAGNETIC MATERIAL INCREASES OR IF MAGNETIC MATERIAL IS FOUND AFTER THE SECOND CLEAN PATCH CHECK. THIS IS TO ENSURE BEARING/GEAR MATERIAL FROM THE ORIGINAL FAILURE HAS NOT CONTAMINATED THE REPLACEMENT ENGINE DUE TO INCOMPLETE FLUSHING OF THE AIRFRAME/PROPELLER OIL SYSTEM(S). IF THE AMOUNT OF MATERIAL IS REDUCED. THE MAINTENANCE ACTION REQUIRED FOR DEBRIS IN OIL SYSTEM MUST BE CARRIED OUT. THE TIME BETWEEN PATCH CHECKS SHOULD REVERT TO THE STANDARD INTERVAL AFTER THE SECOND CONSECUTIVE CLEAN PATCH CHECK.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. THEREBY DAMAGING THE CONTACTING SURFACE? YES NO RGB MODULE MAY REMAIN IN SERVICE.FAULT ISOLATION Page 156 Nov 04/2005 . REPEAT PATCH CHECK AT 50−HOUR INTERVALS UNTIL NO MAGNETIC MATERIAL IS FOUND. TYPE AND ORIGIN OF DEBRIS. C74111A Debris in Oil System Figure 127 (Sheet 2) 72-00-01 ENGINE . REPEAT PATCH CHECK AFTER 50 HOURS. NO IS THERE EVIDENCE OF THE KEYWASHER FRAGMENT HAVING GONE THROUGH THE GEARTEETH.9 BEARING KEYWASHER DEBRIS? YES NO IS DEBRIS IDENTIFIABLE AS AS A TAB WASHER DEBRIS? NO REPLACE AFFECTED MODULE (SEE NOTE 1) YES HAS SIMILAR EVENT OCCURRED SINCE LAST MODULE OVERHAUL? YES REMOVE RGB. IF MAGNETIC MATERIAL IS FOUND. NOTE 1: AFTER AN ENGINE/MODULE CHANGE DUE TO BEARING/GEAR DISTRESS. IT IS RECOMMENDED THAT THE REPLACEMENT ENGINE HAVE AN OIL−FILTER PATCH CHECK CARRIED OUT AFTER 50 HOURS. (REF.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. CHIP DETECTOR STRAINERS AND CHIP DETECTORS. RUN ENGINE AT 80% TORQUE FOR 10 MINUTES. (REF. HAS TURBOMACHINERY A RECENT HISTORY (WITHIN 400 HOURS) OF GENERATING DEBRIS? YES REVIEW THE RESULTS OF LAST LABORATORY ANALYSIS. CLEAN AND REINSTALL FILTERS. IS DEBRIS FOUND? YES DRAIN AND FLUSH ENGINE AND POWERPLANT OIL SYSTEM. STRAINERS.FAULT ISOLATION Page 157 Nov 04/2005 . STRAINERS. CHIP DETECTOR STRAINERS AND CHIP DETECTORS. 3045542 NOTE: DO THE "DEBRIS IN OIL SYSTEM" CHART BEFORE YOU DO THIS PROCEDURE. (SEE NOTE 3) NO IS THE QUANTITY OF DEBRIS THE SAME OR INCREASED OR IS MODULE CONSISTENTLY GENERATING DEBRIS? YES REMOVE TURBOMACHINERY AT FIRST OPPORTUNITY OR WITHIN 10FH (SEE NOTE 3) NO NO REMOVE AND INSPECT OIL FILTERS. STRAINERS. AMM) YES REMOVE TURBOMACHINERY. SEE SHEET 2 (B) SEE SHEET 2 (C) SEE SHEET 2 (A) C74112 Debris in Oil System From the Tubomachinery Module Figure 128 (Sheet 1 of 3) 72-00-01 ENGINE . NOTE 2) NO WERE THE RESULTS OF THE PREVIOUS LABORATORY ANALYSIS BEARING MATERIAL? (NOTE 1) CLEAN AND INSTALL FILTERS. CHIP DETECTORS AND CHIP DETECTOR STRAINERS. (REF. RUN ENGINE AT 80% TORQUE FOR 10 MINUTES. REFER TO CHART "EVALUATION OF LABORATORY REPORT". STRAINERS. (SEE NOTE 3) NO CLEAN AND REINSTALL FILTERS. 3045542 CONT’D FROM SHEET 1 (B) CONT’D FROM SHEET 1 (C) CONT’D FROM SHEET 1 (A) FILL UP ENGINE AND POWERPLANT OIL SYSTEM. IS DEBRIS FOUND ? C74113A Debris in Oil System From the Tubomachinery Module Figure 128 (Sheet 2) 72-00-01 ENGINE . REVIEW THE RESULTS OF LAST LABORATORY ANALYSIS BEFORE NEXT DISPATCH. STRAINERS. NOTE 1) NO REFER TO CHART "EVALUATION OF LABORATORY REPORT" WHEN ANALYSIS RESULT OF MOST CURRENT DEBRIS IS AVAILABLE. NOTE 1) YES RETURN ENGINE TO SERVICE AND CHECK AIRFRAME CONDITION PANEL (IF APPLICABLE) FOR CHIP DETECTOR CIRCUIT COMPLETION OR REMOVE AND INSPECT CHIP DETECTOR/ COLLECTOR DAILY FOR 50 FH.FAULT ISOLATION Page 158 Nov 04/2005 . IS DEBRIS FOUND? YES REMOVE TURBOMACHINERY MODULE. AMM) REMOVE AND INSPECT OIL FILTERS. CHIP DETECTORS AND CHIP DETECTOR STRAINERS. CHIP DETECTOR STRAINERS AND CHIP DETECTORS.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. (REF. CHECK OIL FILTERS FOR DEBRIS AFTER 50 FH (REF. 3045542 NOTE 1: RESULTS OF PREVIOUS LABORATORY ANALYSIS AND ORIGIN OF DEBRIS SHOULD BE DETERMINED WITHIN 50 FLIGHT HOURS OF ORIGINAL DETECTION OF DEBRIS. THIS IS TO ENSURE BEARING/GEAR MATERIAL FROM THE ORIGINAL FAILURE DUE TO INCOMPLETE FLUSHING OF THE AIRFRAME/PROPELLER OIL SYSTEM(S) HAS NOT CONTAMINATED THE REPLACEMENT ENGINE. IF THE AMOUNT OF MATERIAL IS REDUCED. IF MAGNETIC IS FOUND. C74114 Debris in Oil System From the Tubomachinery Module Figure 128 (Sheet 3) 72-00-01 ENGINE . REPEAT PATCH CHECK AT 50−HOUR INTERVALS UNTIL NO MAGNETIC MATERIAL IS FOUND.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. IF THE AMOUNT OF MAGNETIC MATERIAL INCREASES OR IF MAGNETIC MATERIAL IS FOUND AFTER THE SECOND CLEAN PATCH CHECK. THE MAINTENANCE ACTION REQUIRED FOR DEBRIS IN OIL SYSTEM MUST BE CARRIED OUT. REPEAT PATCH CHECK AFTER 50 HOURS. THE TIME BETWEEN PATCH CHECKS SHOULD REVERT TO THE STANDARD INTERVAL AFTER THE SECOND CONSECUTIVE CLEAN PATCH CHECK. NOTE 3: AFTER AN ENGINE/MODULE CHANGE DUE TO BEARING/GEAR DISTRESS. NOTE 2: RESULTS OF LAST SAMPLE MUST BE KNOWN PRIOR TO CONTINUING. IT IS RECOMMENDED THAT THE REPLACEMENT ENGINE HAVE AN OIL−FILTER PATCH CHECK CARRIED OUT AFTER 50 HOURS.FAULT ISOLATION Page 159 Nov 04/2005 . (REF. (SEE NOTE 4) YES DRAIN AND FLUSH ENGINE AND POWERPLANT OIL SYSTEM. NOTE 2 : A HAIR−LIKE FILAMENT COMPOSED OF A SINGLE CHAIN OF METALLIC DUST (FUZZ) IS CONSIDERED ACCEPTABLE. STRAINERS. NOTE 3 & 5) RUN ENGINE AT 80% TORQUE FOR 10 MINUTES. STRAINERS. YES REMOVE AND INSPECT OIL FILTERS. DEBRIS ORIGINATES FROM THE RGB. CHIP DETECTOR STRAINERS AND CHIP DETECTORS. IS DEBRIS FOUND? NO REMOVE RGB WITHIN 50FH OF CURRENTLY REPORTED DEBRIS. SEE SHEET 2 (C) SEE SHEET 2 (B) SEE SHEET 2 (A) C74131A Debris in Oil System from the Reduction Gearbox Module Figure 129 (Sheet 1 of 3) 72-00-01 ENGINE .PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. CHIP DETECTOR STRAINERS AND CHIP DETECTORS. HAS RGB A RECENT HISTORY (WITHIN 400 HOURS) OF GENERATING DEBRIS? YES SCHEDULE RGB REMOVAL WITHIN 50FH OF CURRENTLY REPORTED DEBRIS.FAULT ISOLATION Page 160 Nov 04/2005 . NO ACTION REQUIRED. CLEAN AND REINSTALL FILTERS. STRAINERS. (REF. 3045542 NOTE 1 : DO THE "DEBRIS IN OIL SYSTEM" CHART BEFORE YOU DO THIS PROCEDURE. (SEE NOTE 4) REVIEW THE RESULTS OF LAST LABORATORY ANALYSIS. CHIP DETECTORS AND CHIP DETECTOR STRAINERS. AMM) NO REPLACE DEFECTIVE ACCESSORIES. NO / UNKNOWN IS THE QUANTITY OF DEBRIS THE SAME OR INCREASED OR IS RGB CONSISTENTLY GENERATING DEBRIS? NO YES IS DEBRIS ORIGINATING IN THE RGB AND NOT THE ACCESSORIES (PCU GENERATOR OR O/S GOVERNOR AND HYDRAULIC PUMP)? (REF. NOTE 2) NO YES WERE THE RESULTS OF THE PREVIOUS LABORATORY ANALYSIS BEARING MATERIAL? (NOTE 1 & 6) CLEAN AND INSTALL FILTERS. AMM) REPLACE DEFECTIVE ACCESSORIES. NO REFER TO CHART "EVALUATION OF LABORATORY REPORT" WHEN ANALYSIS RESULT OF MOST CURRENT DEBRIS IS AVAILABLE. CHIP DETECTORS AND CHIP DETECTOR STRAINERS.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. NOTE 1).FAULT ISOLATION Page 161 Nov 04/2005 . (REF. REMOVE RGB MODULE WITHIN 50 HOURS OF CURRENTLY REPORTED DEBRIS (REF. STRAINERS. SHEET 1 ) (SEE NOTE 4) REVIEW THE RESULTS OF LAST LABORATORY ANAYLSIS WITHIN 25 FH OF THE INITIAL FINDING OF THE CURRENT REPORTED DEBRIS. CHECK OIL FILTERS FOR DEBRIS AFTER 50 FH (REF. YES IS DEBRIS ORIGINATING FROM ACCESSORIES (PCU GENERATOR OR O/S GOVERNOR AND HYDRAULIC PUMP)? (REF. STRAINERS. NOTE 1. 3 & 5) YES NO NO CLEAN AND REINSTALL FILTERS. RUN ENGINE AT 80% TORQUE FOR 10 MINUTES. IS DEBRIS FOUND? YES RETURN ENGINE TO SERVICE AND CHECK AIRFRAME CONDITION PANEL (IF APPLICABLE) FOR CHIP DETECTOR CIRCUIT COMPLETION OR REMOVE AND INSPECT CHIP DETECTOR/COLLECTOR AFTER 10 FH AND AFTER 50 FH. REFER TO CHART "EVALUATION OF LABORATORY REPORT" (REF. IS DEBRIS FOUND ? C74132B Debris in Oil System from the Reduction Gearbox Module Figure 129 (Sheet 2) 72-00-01 ENGINE . CHIP DETECTOR STRAINERS AND CHIP DETECTORS. 3045542 CONT’D FROM SHEET 1 (C) CONT’D FROM SHEET 1 (B) CONT’D FROM SHEET 1 (A) FILL UP ENGINE AND POWERPLANT OIL SYSTEM. NOTE 1 AND 6) REMOVE AND INSPECT OIL FILTERS. PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. REPEAT PATCH CHECK AFTER 50 HOURS. HYDRAULIC PUMP OR FEATHERING PUMP. THIS IS TO ENSURE BEARING/GEAR MATERIAL FROM THE ORIGINAL FAILURE HAS NOT CONTAMINATED THE REPLACEMENT ENGINE DUE TO INCOMPLETE FLUSHING OF THE AIRFRAME/PROPELLER OIL SYSTEM(S). CHECK CHIP DETECTOR DAILY TO DETERMINE IF THE RGB IS STILL MAKING DEBRIS. REPEAT PATCH CHECK AT 50−HOUR INTERVALS UNTIL NO MAGNETIC MATERIAL IS FOUND. OVERSPEED GOVERNOR (O/S GOVERNOR). IT IS RECOMMENDED THAT THE REPLACEMENT ENGINE HAVE AN OIL−FILTER PATCH CHECK CARRIED OUT AFTER 50 HOURS. IN FACT. IF THE AMOUNT OF MAGNETIC MATERIAL INCREASES OR IF MAGNETIC MATERIAL IS FOUND AFTER THE SECOND CLEAN PATCH CHECK. RECORD AND REPORT RESULTS OF CHECK TO LOCAL P&WC FIELD REPRESENTATIVE. TO DETERMINE THE ACTUAL SOURCE OF THE DEBRIS. THE TIME BETWEEN PATCH CHECKS SHOULD REVERT TO THE STANDARD INTERVAL AFTER THE SECOND CONSECUTIVE CLEAN PATCH CHECK. THE MAINTENANCE ACTION REQUIRED FOR DEBRIS IN OIL SYSTEM MUST BE CARRIED OUT.15. NOTE 6: AMS6444 (52100) / AMS6491 (M50) MATERIAL IN RGB DEBRIS MAY BE CAUSED BY ELECTRO−EROSION OF THE NO. IF THE AMOUNT OF MATERIAL IS REDUCED.FAULT ISOLATION Page 162 Nov 04/2005 . ALTERNATELY. C74128 Debris in Oil System from the Reduction Gearbox Module Figure 129 (Sheet 3) 72-00-01 ENGINE . NOTE 2: RESULTS OF LAST SAMPLE MUST BE KNOWN PRIOR TO CONTINUING. NOTE 5: IT IS POSSIBLE THAT DEBRIS BELIEVED TO BE ORIGINATING FROM RGB MODULE IS. NOTE 4: AFTER AN ENGINE/MODULE CHANGE DUE TO BEARING/GEAR DISTRESS. CHECK PROPELLER DE−ICING SYSTEM IN ACCORDANCE WITH PROPELLER MAINTENANCE DOCUMENTATION. IDENTIFY THE SOURCE OF DEBRIS WITHIN 50 HOURS OF THE ORIGINALLY REPORTED DEBRIS. ORIGINATING FROM PROPELLER CONTROL UNIT (PCU). 3045542 NOTE 1: RESULTS OF PREVIOUS LABORATORY ANALYSIS AND ORIGIN OF DEBRIS SHOULD BE DETERMINED WITHIN 50 FLIGHT HOURS OF ORIGINAL DETECTION OF DEBRIS. REMOVE THESE COMPONENTS INDIVIDUALLY BASED ON THE MOST PROBABLE SOURCE OF DEBRIS. REFER TO THE LIST OF MATERIAL AND IDENTIFY MOST PROBABLE SOURCE. IF MAGNETIC MATERIAL IS FOUND. 18 AND 19 BEARINGS. NOTE 3: IT SHOULD HAVE ALREADY BEEN DETERMINED THAT THE RGB AND NOT RGB MOUNTED ACCESSORIES ARE GENERATING THE DEBRIS. PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. NOTE 2 & 5) NO REPLACE MODULE (REF. EMM). INSPECT RGB CHIP DETECTOR AFTER 50 FLIGHT HOURS. C74129A Oil Debris . NO WAS DEBRIS BEARING MATERIAL AMS6444 (52100) / AMS6491 (M50) / AMS6414 / AMS6415? YES WAS THE RGB GENERATING DEBRIS? NO YES IS DEBRIS ORIGINATING FROM ACCESSORIES (PCU GENERATOR OR YES O/S GOVERNOR AND HYDRAULIC PUMP)? (REF. NOTE 1 & 7) REPLACE DEFECTIVE ACCESSORIES.FAULT ISOLATION Page 163 Nov 04/2005 . NOTE 2) YES CONTINUE IN SERVICE REPLACE RGB WITHIN 50 FLIGHT HOURS OF MOST CURRENTLY REPORTED DEBRIS.Evaluation of Laboratory Report Figure 130 (Sheet 1 of 3) 72-00-01 ENGINE . IS DEBRIS FOUND? NO CONTINUE IN SERVICE. 3045542 DEBRIS ANALYZED AT LABORATORY (TABLE MATERIAL SPECIFICATIONS SHOULD BE CONSULTED TO DETERMINE WHICH COMPONENT IS GENERATING DEBRIS). NOTE 4) CARRY OUT AN INSPECTION (BORESCOPE) OF THE FOLLOWING COMPONENTS DEPENDING WHICH MODULE THE DEBRIS WAS FOUND IN YES WAS DEBRIS (RGB: FIRST−STAGE GEARS. (REF. OIL PUMP DRIVE GEARS. (REF. NOTE 2 & 5) NOTE : REFER TO CHAPTER 72−01−50 FOR A LIST OF THE MOST FREQUENT NON−MAGNETIC MATERIALS FOUND IN OIL FILTER DEBRIS. (REF. FUEL PUMP NO DRIVE GEARS AND STARTER GENERATOR DRIVE GEARS). NOTE 2) CONTINUE IN SERVICE. GEAR MATERIAL? TURBOMACHINERY: ANGLE DRIVE GEARBOX GEARS. (REF. (REF. NO WAS DEBRIS ALLOWABLE? YES WAS THE TURBOMACHINERY GENERATING DEBRIS? CONTINUE IN SERVICE YES HAS RGB A RECENT HISTORY (WITHIN 400 HOURS) OF GENERATING DEBRIS? NO YES REPLACE RGB WITHIN 50 FLIGHT HOURS OF MOST CURRENTLY REPORTED DEBRIS. NOTE 4) YES IS MODULE IN ACCEPTABLE CONDITION? NO SEE SHEET 2 REMOVE MODULE (REF. (REF. MAINTENANCE PRACTICES. OVERHAULED OR REPAIRED ENGINE (MAJOR OR MINOR CONTAMINANT)? (REF. AS NECESSARY. RETURN MODULE TO AN OVERHAUL FACILITY. NOTE 3) NO YES WAS DEBRIS FOUND AT FIRST FILTER OR PATCH CHECK FROM NEW.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. IS DEBRIS FOUND ? RETURN MODULE TO SERVICE. CHECK OIL FILTER FOR DEBRIS AFTER 50 FH. OTHERWISE.FAULT ISOLATION Page 164 Nov 04/2005 . WAS LABYRINTH SEAL MATERIAL FOUND? RETURN MODULE TO SERVICE. NOTE 6) RESTART THIS PROCEDURE FROM SHEET 1 TO IDENTIFY MOST PROBABLE SOURCE OF DEBRIS YES REMOVE MODULE. (REF. MATERIAL SPECIFICATIONS AND COMMON CONTAMINANTS (ORGANIC AND NON−ORGANIC) TABLES AND DETERMINE POSSIBLE SOURCE(S) OF DEBRIS ORIGINATOR(S). NOTE 7) IS MODULE IN ACCEPTABLE CONDITION? NO REMOVE MODULE. YES IS LABYRINTH SEAL MATERIAL FOUND (MAJOR NO OR MINOR CONTAMINANT)? (REF.Evaluation of Laboratory Report Figure 130 (Sheet 2) 72-00-01 ENGINE . YES BORESCOPE ENGINE AS REQUIRED. NOTE 6) REFER TO 72−00−00. NOTE 2) YES ENGINE MAY REMAIN IN SERVICE. 3045542 CONT’D FROM SHEET 1 WAS LABYRINTH SEAL MATERIAL AMS5504 / AMS5613 / AMS5663? (REF. CHECH AIRFRAME CONDITION PANEL (IF APPLICABLE) FOR CHIP DETECTOR CIRCUIT COMPLETION OR REMOVE NO AND INSPECT CHIP DETECTOR/ COLLECTOR DAILY FOR 50 FH. C74121A Oil Debris . DETERMINE THE SOURCE OF CONTAMINATION PER APPLICABLE MAINTENANCE MANUAL. NO YES CARRY OUT AN ADDITIONAL FILTER PATCH CHECK AFTER NO 50 FLIGHT HOURS. 4 A BORESCOPE INSPECTION THROUGH THE BOTTOM T6 THERMOCOUPLE PORT (REF. THE TIP OF THE PICKUP PROBE MUST BE CHECKED FOR MAGNETIC MATERIAL WHICH COULD INDICATE NO.15.FAULT ISOLATION Page 165 Nov 04/2005 . CARRY OUT A BORESCOPE INSPECTION OF THE NO. BEARING AND BEARING CAGE DETERIORATION. EMM) PORT TO CHECK FOR LABYRINTH SEAL. NOTE 6: THE AMOUNTS OF INDIVIDUAL CONSTITUENTS IN OIL FILTER PATCH DEBRIS AFTER ANALYSIS IS. NOTE 5: AMS6444 (52100) / AMS6491 (M50) MATERIAL IN RGB DEBRIS MAY BE CAUSED BY ELECTRO−EROSION OF NO. THE SEAL MATERIAL FOUND MAY HAVE BEEN GENERATED AFTER THE RUNNING−IN PERIOD.3 OR 4 BEARING. OVERSPEED GOVERNOR (O/S GOVERNOR). EMM) TO CHECK FOR SOOT. NOTE 8: IT IS POSSIBLE THAT DEBRIS BELIEVED TO BE ORIGINATING FROM RGB MODULE IS.6 AND 7 BEARING HOUSING AND AT THE BOTTOM OF THE INTERTURBINE DUCT.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. AN ADDITIONAL PATCH CHECK MUST BE CARRIED OUT AFTER APPROXIMATELY ONE WEEK (50 FLIGHT HOURS). IF THE AMOUNT OF MATERIAL IS REDUCED. IN FACT. IT IS RECOMMENDED THAT THE REPLACEMENT ENGINE HAVE AN OIL−FILTER PATCH CHECK CARRIED OUT AFTER 50 HOURS. MAJOR − WHEN WEIGHT OF THE CONSTITUENT IS MORE THAN 50% OF THE TOTAL DEBRIS WEIGHT. IF MAGNETIC MATERIAL IS FOUND. REMOVE THESE COMPONENTS INDIVIDUALLY BASED ON MOST PROBABLE SOURCE OF DEBRIS. EMM). NOTE 3: IF THE INITIAL PATCH CHECK OR FILTER CHANGE IS CARRIED OUT AT MORE THAN 100 FLIGHT HOURS. MINOR − WHEN WEIGHT OF THE CONSTITUENT IS LESS THAN 50% BUT MORE THAN 5% OF THE TOTAL DEBRIS WEIGHT. BLADE SHIFT. 5 TO MINIMIZE THE POSSIBILITY OF BEARING FAILURE AND TO FACILITATE DECISION−MAKING WHEN THE ORIGIN OF THE SEAL MATERIAL IS NOT DISCOVERED DURING THE ABOVE INSPECTIONS. NOTE 2: AFTER AN ENGINE/MODULE CHANGE DUE TO BEARING/GEAR DISTRESS. REPEAT PATCH CHECK AT 50−HOUR INTERVALS UNTIL NO MAGNETIC MATERIAL IS FOUND. HYDRAULIC PUMP OR FEATHERING PUMP. CHECK CHIP DETECTOR DAILY TO DETERMINE IF THE RGB IS STILL MAKING DEBRIS. CARBON OR OIL IN THE AREA AROUND NO. 18 AND 19 BEARINGS. OR BEVEL GEARS DISTRESS. EMM). NOTE 4: KEEPING A DEBRIS−GENERATING REDUCTION GEARBOX OR TURBOMACHINERY MODULE IN SERVICE WHILE A REMOVAL IS PLANNED MAY SUBSTANTIALLY INCREASE THE COST OF REPAIR/REFURBISHMENT DUE TO FURTHER GEAR AND/OR BEARING DAMAGE. OPERATORS MAY. THIS IS TO ENSURE BEARING/GEAR MATERIAL FROM THE ORIGINAL FAILURE HAS NOT CONTAMINATED THE REPLACEMENT ENGINE DUE TO INCOMPLETE FLUSHING OF THE AIRFRAME/PROPELLER OIL SYSTEM(S).Evaluation of Laboratory Report Figure 130 (Sheet 3) 72-00-01 ENGINE .5 BEARING CAVITY THROUGH THE OIL SCAVENGE (REF. THE MAINTENANCE ACTION REQUIRED FOR DEBRIS IN OIL SYSTEM MUST BE CARRIED OUT. EMM). C74130 Oil Debris . IDENTIFY THE SOURCE OF DEBRIS WITHIN 50 HOURS OF THE ORIGINALLY REPORTED DEBRIS. ORIGINATING FROM PROPELLER CONTROL UNIT (PCU). 2 A BORESCOPE INSPECTION OF THE HIGH AND LOW PRESSURE TURBINE BLADES AND THE FIRST AND SECOND STAGE POWER TURBINE BLADES TO CHECK FOR SEVERE RUBS (TIPS. THEREFORE. REPEAT PATCH CHECK AFTER 50 HOURS. CORROSION/ SULFIDATION AND BURNED OR MISSING TIPS (REF. CARRY OUT THE INSPECTIONS SHOWN FOR LABYRINTH SEAL MATERIAL (AMS5504 OR AMS5613 OR AMS5663). 3045542 NOTE 1: IT SHOULD HAVE ALREADY BEEN DETERMINED THAT THE RGB AND NOT RGB MOUNTED ACCESSORIES ARE GENERATING THE DEBRIS.). TRACES − WHEN WEIGHT OF THE CONSTITUENT IS LESS THAN 5% OF THE TOTAL DEBRIS WEIGHT. CHECK PROPELLER DE−ICING SYSTEM IN ACCORDANCE WITH PROPELLER MAINTENANCE DOCUMENTATION. ETC. RECORD AND REPORT RESULTS OF CHECK TO LOCAL P&WC FIELD REPRESENTATIVE. REFER TO THE LIST OF MATERIAL AND IDENTIFY MOST PROBABLE SOURCE. THE TIME BETWEEN PATCH CHECKS SHOULD REVERT TO THE STANDARD INTERVAL AFTER THE SECOND CONSECUTIVE CLEAN PATCH CHECK. IN ADDITION. 3 A BORESCOPE INSPECTION THROUGH THE NL PULSE PICKUP PROBE PORT AT THE BOTTOM OF THE INTERCOMPRESSOR CASE AIR PLENUM TO CHECK FOR ABRADABLE SEAL MATERIAL (REF. NOTE 7: BORESCOPE INSPECTION: 1 A BORESCOPE INSPECTION OF THE LOW PRESSURE (LP) AND HIGH PRESSURE (HP) IMPELLERS TO CHECK FOR SEVERE RUBS OR FOREIGN OBJECT DAMAGE (FOD) (REF. TO DETERMINE THE ACTUAL SOURCE OF THE DEBRIS. AT THEIR DISCRETION. IF THE AMOUNT OF MAGNETIC MATERIAL INCREASES OR IF MAGNETIC MATERIAL IS FOUND AFTER THE SECOND CLEAN PATCH CHECK. PLATFORMS. ALTERNATELY. REPLACE PROP SHAFT SEAL AND INSPECT I. PROPELLER THRUST BEARING COVER 3. 3045542 SYMPTOMS SUSPECT LRU OIL LEAK FROM PROPELLER SHAFT 1. REDUCTION GEARBOX MODULE EXTERNAL ? LESS THAN 5cc/hr FROM SHAFT SEAL DRAIN ? NO YES SYSTEM NORMAL YES NO AIRFRAME DRAIN LINE IS CLEAR ? NO CLEAR LINE AND VERIFY FUNCTION CLEAN SEAL RUNNER. OF SHAFT AND VISIBLE CRACK (REF. REPLACE PROP SHAFT AND INSPECT INSIDE DIA. PROPELLER SHAFT SEAL 2. 72−10−00) OK ? NO NO SCHEDULE MODULE REMOVAL YES SYSTEM NORMAL C26239B Oil Leak From Propeller Shaft Area Figure 131 (Sheet 1 of 2) 72-00-01 ENGINE . 72−10−00) OK ? YES YES SYSTEM NORMAL NO SCHEDULE MODULE REMOVAL VERIFY LOCATION OF LEAK PROPELLER TO PROP SHAFT MATING FLANGE ? YES REFER TO PROPELLER SYSTEM CMM THRUST BEARING COVER TO RGB FRONT HOUSING MATING SURFACE ? FRONT FACE OF THRUST BEARING COVER ? YES YES EVIDENCE OF CORROSION ON NO THRUST BEARING COVER ? CONT’D ON SHEET 2 YES REPAIR CORROSION.D. OF SHAFT FOR VISIBLE CRACK (REF.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. CLEAN SEAL RUNNER. REPLACE PROP SHAFT SEAL AND INSPECT INSIDE DIA. 72−10−00) OK ? YES SYSTEM NORMAL CLEAN SEAL RUNNER.FAULT ISOLATION Page 166 Nov 04/2005 . OF THE SHAFT FOR VISIBLE CRACK (REF. PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. OK ? SCHEDULE MODULE REMOVAL YES SYSTEM NORMAL C24927 Oil Leak From Propeller Shaft Area Figure 131 (Sheet 2) 72-00-01 ENGINE . OK ? YES NO SCHEDULE MODULE REMOVAL YES SYSTEM NORMAL REPAIR CORROSION (REF. 3045542 CONT’D FROM SHEET 1 THRUST BEARING COVER TO RGB FRONT HOUSING MATING SURFACE OK ? NO EVIDENCE OF CORROSION ? NO REPLACE THRUST BEARING COVER GASKET AND PACKING.FAULT ISOLATION Page 167 Nov 04/2005 . 72-10-00) NO REPLACE THRUST BEARING COVER GASKET AND PACKING. 72−01−50. 72−00−00.FAULT ISOLATION Page 168 Nov 04/2005 . 3045542 SYMPTOMS OIL ON FLANGE (S) E AND/OR F − REFER TO INTERCOMPRESSOR CASE AIR PLENUM BORESCOPE (REF. 05−10−00) ? REFER TO FIGURE "SMOKE FROM EXHAUST ON START−UP OR SHUTDOWN/ ENGINE FLOODED WITH OIL/ OIL ODOR IN COCKPIT" REFER TO FIGURE "HIGH OIL CONSUMPTION" NO BORESCOPE ICC AIR PLENUM.5 CAVITY (REF. 72−01−50) OK? YES SYSTEM NORMAL SYSTEM NORMAL C61583B Oil on Flange(s) E and/or F Figure 132 72-00-01 ENGINE .5 CAVITY INSPECTION (REF. ENGINE−INSPECTION/CHECK) AND INTERCOMPRESSOR CASE P2. INSPECTION/CHECK) OIL ODOR IN COCKPIT ? YES NO OIL CONSUMPTION ABOVE YES LIMIT (REF.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. OIL FOUND ? NO YES CARRY OUT INSPECTION OF THE ICC P2. CARRY OUT VISUAL INSPECTION ARE HP & FUEL PUMP INLET FILTERS CONTAMINATED ? YES AIRCRAFT SYSTEM OK ? NO NO REPLACE THE PRESSURE DIFFERENTIAL SWITCH (REF. AIRCRAFT SYSTEM 4. AMM) YES REMOVE LP FUEL FILTER. 3045542 SYMPTOMS SUSPECT LRU IMPENDING BYPASS INDICATOR ACTIVATED 1.FAULT ISOLATION Page 169 Nov 04/2005 . CARRY OUT VISUAL INSPECTION IS LP FUEL FILTER CONTAMINATED ? NO IS THE PRESSURE DIFFERENTIAL SWITCH OK ? YES YES REMOVE HP AND FUEL PUMP INLET FILTER. AMM) CLEAN OR REPLACE ENGINE LP. AMM) CHANGE THE FUEL HEATER & THE FUEL PUMP NO IS AIRCRAFT FUEL SYSTEM CONTAMINATED ? NO YES DRAIN. HP AND INLET FUEL FILTERS GROUND RUN ENGINE & CHECK FOR FUEL LEAKS C82791 LP Fuel Filter Impending Bypass Indicator Activated Figure 133 72-00-01 ENGINE . CARRY OUT HP FUEL FILTER BYPASS INDICATOR ACTIVATED TROUBLESHOOTING REPAIR SYSTEM (REF. PRESSURE DIFFERENTIAL SWITCH 3. FUEL PUMP IS THE HP FUEL FILTER BYPASS INDICATOR ACTIVATED? YES NO CHECK THE AIRFRAME LP FUEL FILTER IMPENDING NO BYPASS INDICATING SYSTEM (REF. AMM) OK? CHANGE FUEL HEATER AND PUMP. FUEL HEATER 5. 72−01−40 SERVICING) REPAIR SYSTEM (REF. FUEL 2. FLUSH & CLEAN AIRCRAFT FUEL SYSTEM (REF.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. AMM) SYSTEM NORMAL YES REPLACE FUEL HEATER (REF.AMM) OK? NO RECTIFY (REF.72−01−40) SEE SHEET 2 C72642 Fuel Temperature Too High or Too Low Figure 134 (Sheet 1 of 2) 72-00-01 ENGINE .72−01−60) OK? REPLACE PROBE (REF. AMM) YES CHECK ELECTRICAL HARNESS AND NO FUEL INDICATOR CONNECTORS (REF. FUEL COOLED OIL COOLER FUEL TEMPERATURE TOO HIGH OR TOO LOW WITH ENGINE RUNNING REFER TO CHART "LP FUEL FILTER IMPENDING BY−PASS INDICATOR ACTIVATED" IS LP FUEL FILTER IMPENDING BY−PASS YES INDICATOR ACTIVATED ? NO REFER TO CHART "MAIN OIL FILTER IMPENDING BY−PASS INDICATOR ACTIVATED" IS MAIN OIL FILTER IMPENDING BY−PASS YES INDICATOR ACTIVATED ? NO CHECK FUEL TEMPERATURE INDICATOR SYSTEM (REF. 72−01−10) OK? YES RECTIFY/REPLACE HARNESS (REF. 72−01−40) NO RUN ENGINE UNTIL OIL NO TEMPERATURE STABILIZES BETWEEN 70 TO 80 C(158−176 F) IS TEMPERATURE STILL HIGH? IS FUEL TEMPERATURE LOW ? (REF. 72−01−60) YES IS FUEL TEMPERATURE HIGH ? YES (REF. NOTE 2) YES IS OIL TEMPERATURE NO ABOVE 40 C (104 F) ? SEE SHEET 2 CHECK/RECTIFY OIL COOLER SYSTEM (REF.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. FUEL HEATER THERMOSTATIC ELEMENT 3. NOTE 1) REPLACE FUEL HEATER THERMOSTATIC ELEMENT (REF. 3045542 SYNPTOMS SUSPECT LRU 1. FUEL TEMPERATURE PROBE 2. 72−01−10) CARRY OUT RESISTANCE CHECK ON THE NO FUEL TEMPERATURE PROBE (REF. FUEL HEATER 4.FAULT ISOLATION Page 170 Nov 04/2005 . 3045542 SEE SHEET 1 SEE SHEET 1 REPLACE FUEL HEATER THERMOSTATIC ELEMENT (REF. C72643 Fuel Temperature Too High or Too Low Figure 134 (Sheet 2) 72-00-01 ENGINE . THE FUEL TEMPERATURE MAY BE LOWER THAN THE LIMIT AFTER THE FUEL GOES THROUGH THE FUEL HEATER. 72−01−40) RUN ENGINE UNTIL OIL TEMPERATURE STABILIZES BETWEEN 70 TO 80 C (158−176 F) IS TEMPERATURE STILL LOW? NO SYSTEM NORMAL NOTE 1: NOTE 2: IF THE TEMPERATURE IN THE AIRCRAFT FUEL TANK IS EXCEEDING 57 C (135 F). THE FUEL TEMPERATURE MAY EXCEED THE LIMIT AFTER THE FUEL GOES THROUGH THE FUEL HEATER.72−01−40) RUN ENGINE UNTIL OIL TEMPERATURE STABILIZES BETWEEN 70 TO 80 C (158−176 F) IS TEMPERATURE STILL HIGH? NO RUN ENGINE UNTIL OIL NO TEMPERATURE STABILIZES BETWEEN 70 TO 80 C (158−176 F) IS TEMPERATURE STILL LOW? SYSTEM NORMAL SYSTEM NORMAL YES REPLACE FUEL HEATER (REF.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO.FAULT ISOLATION Page 171 Nov 04/2005 . IF THE TEMPERATURE IN THE AIRCRAFT FUEL TANK IS LOWER THAN −54 C (−65 F). TORQUE AND NO DURATION OF THE OVERTORQUE KNOWN? YES REFER TO CHAPTER 05−50−00. PARA. UNSCHEDULED MAINTENANCE INSPECTIONS (REF. "ENGINE OVERTORQUE ESTIMATION") REFER TO CHAPTER 05−50−00. UNSCHEDULED MAINTENANCE INSPECTIONS (REF. "OVERTORQUE") C89602 Engine Overtorque Figure 135 72-00-01 ENGINE .FAULT ISOLATION Page 172 Nov 04/2005 . PARA. 3045542 SYMPTOMS ENGINE OVERTORQUE IS THE MAX.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. Faults in the system are detected by the built-in test (BIT) circuits in the electronic engine control (EEC). Consumable Materials Not Applicable 3. B.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. Special Tools Not Applicable 4. (a) ARINC Reader Technique 1 To check the fault codes. Reference should be made to the flight log and engine log for any entry relating to the current problem. 72-00-02 ENGINE . Fixtures. Electronic Fuel Control System A. When a problem with the engine occurs: (2) Record the fault codes displayed on the ARINC 429 receiver (if applicable). select label 240 on the ARINC reader or FDEP (Ref. 3045542 ENGINE . equipment and supplier tools listed below are referred to in procedural text.Thermofit minigun (with reflector) Electronic fuel control system (EFCS) tester EET 4000 Insulation tester (standard) ARINC 429 receiver (Sfena Microdits model M56CRMO or equivalent) DELETED 5. 2. Procedures (1) The actions required to locate and rectify problems with the engine electronic control system are detailed in the following figures. The EEC records up to eight faults in the system. An ARINC 429 receiver or the Flight Entry Data Panel (FDEP) is used to interrogate the EEC and display the faults as a fault code.FAULT ISOLATION Page 101 Oct 20/2000 . which indicates an LRU code. Equipment and Supplier Tools The fixtures. Name Heat gun . This section provides a series of checks to enable problems that occur in the electronic control system to be isolated and rectified. General A. AMM).FAULT ISOLATION 1. 2 Push the LRU advance and record all messages between the start data message 01 and end data message 02. 72-00-02 ENGINE . but not at connector P1. 72-01-40 and Aircraft Maintenance Manual). NOTE: (f) Refer to Fault Isolation electrical schematics for resistance values of sensors and accessories. inspect and install connectors (Ref. any leg. (b) Pull EEC and AFU circuit breaker as necessary.5 ohm. DO NOT INSERT TEST PROBE INTO CONNECTOR SOCKETS OR ATTACH TEST CLIPS TO CONNECTOR PINS. Individually measure the sensor/accessory resistance and then the line resistance of each leg (wiring harness). (e) If any individual resistance value is out of specified range. 72-01-10). (g) If the individual resistance values are within specified range and the loop resistance matches the sum of individual resistances. (c) Do not disturb or touch the connector at the suspect sensor or accessory. (h) Clean. (j) Carry out an operational check. NOTE: Inspect all connectors which are disassembled for corrosion. repair or replace as required (Ref. 3045542 CAUTION: ENSURE AIRFRAME ELECTRICAL POWER IS OFF WHEN CONNECTING AND DISCONNECTING RECEPTACLES AND PLUGS. (4) Isolating defective components: (a) Determine which components and associated lines are suspect using Fault Isolation electrical schematics and applicable troubleshooting figure. (3) Check that power and condition levers are set and rigged correctly (Ref. contamination and distorted pins. Remove connector P1 from EEC or connector from AFU as necessary. If the individual resistance values are within specified range.FAULT ISOLATION Page 102 Sep 03/99 . 72-01-10). Line resistance should be equal to or less than 0. (d) Remove the connector at the suspect sensor or accessory. Clean. but the loop resistance and sum of individual resistance values do not match. step (5)). CAUTION: DISCONNECT THE EEC AND AUTOFEATHER UNIT (AFU) OF BOTH ENGINES BEFORE USING THE EFCS TEST SET OR OTHER EQUIPMENT. fault was possibly generated by connector interface (pin/socket) damage. Check loop resistance (LINE plus SENSOR/ACCESSORY plus LINE) at connector P1 or connector at AFU. fault was possibly generated by connector interface (pin/socket) damage at connector P1. (i) Erase fault code from EEC (Ref. replace that item (sensor/component or wiring harness).PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. Fault code stored in memory: 28 and 29 (2) If required. 3045542 (5) When the EEC fault codes are rectified. Para. the following faults may be stored in the EEC memory: (a) MFCU P8 is disconnected. Fault code stored in memory: 74 (c) T1. The primary means of fault detection is through an open circuit. Procedure (1) Pull EEC circuit breaker before disconnecting connectors. (6) Electronic test set EET 4000 can be used to test the following components: v AFU v Electrical wiring harness v NL probe v NH probe v NP probe v Torque probe v MFC (torque motor) v HBV (Servo valve) v EEC Refer to the vendor’s manual (supplied with test set) for connecting the test set and the method of use. A. (c) Hold the ENGINE TRIM switch ON for at least 10 seconds. (7) 6. DELETED Servicing Connectors with Aircraft Electrical Power On A.8 Temperature Sensor (P4) is disconnected. erased fault codes from memory after reconnecting connectors (Ref. therefore.FAULT ISOLATION Page 103 Oct 20/2000 . (b) Cycle the EEC MANUAL switch ON and OFF. the codes should be erased as follows: NOTE: The engine must be shut down and the electrical power ON.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. if the EEC circuit breaker is not pulled before disconnecting connectors. Fault code stored in memory: 89 and 90 (b) Torque Sensor No. (a) Set the power lever at GROUND IDLE. 2 (P7) is disconnected.). 72-00-02 ENGINE . Refer to Table 101. for a summary of faults. Fault Index. Fault Isolation Fault Index A. 3045542 7.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO.FAULT ISOLATION Page 104 Oct 20/2000 . Fault Code Index LRU Fault Code (HEX) Figure Fault Description 06 102 PLA Bias 07 103 PLA Gain 08 104 Loss of Intercompressor Bleed Valve Control 09 105 Torque Test Failure 10 106 NPT Interface (F/D conversion) 11 107 Stepper Motor W/A Circuit 12 108 Dual NH 14 109 Dual Temperature 15 110 Dual Altitude (Static Pressure) 17 111 Nacelle Static Pressure Sensor 18 112 Sensor Calibration (EEPROM) 19 113 Nacelle Delta-P Pressure Sensor 20 114 Low Level Gain 21 115 Low Level Drift 22 116 Sensor Calibration (Cold Junction) 25 117 High Level Gain 26 118 High Level Drift 28 119 Torque Gain Trim 29 120 Torque Bias Trim 31 121 EEROM Fault 32 122 ARINC Output 34 123 UART Interface 39 124 IBV W/A Interface Fault 40 125 Configuration Trim Fault 41 126 Loss of Engine Configuration Signal 43 127 MFCU Identification 44 128 EEC Internal Fault 49 129 ARINC Input Fault 72-00-02 ENGINE . TABLE 101. 2 High Torque Fault 71 145 Torque Sensor Coil No. 1 High Torque Fault 64 139 Torque Sensor Coil No. 1 Sensor High Range Fault 81 153 NH No. 2 Low Torque Fault 72 146 Torque Sensor Coil No. 1 High NPT Fault 66 141 Torque Sensor Coil No. 3 61 136 TAT Crosscheck Fault 62 137 ALT Crosscheck Fault 63 138 Torque Sensor Coil No. 2 High NPT Fault 73 147 Torque Sensor Coil No.FAULT ISOLATION Page 105 Sep 03/99 . 2 Sensor Low Range Fault 72-00-02 ENGINE . 2 Sensor High Range Fault 82 154 NH No. 1 Sensor Low Range Fault 83 155 NH No. 1 58 134 Engine/Gearbox Torque Fault No. 1 Low NPT Fault 67 142 Connector Failure 69 143 Total Torque (A/D Conversion) Fault 70 144 Torque Sensor Coil No. 2 Low NPT Fault 74 148 Torque Compensation Fault 75 149 Dual Coil Torque Probe Cross-check 76 150 Dual NP Cross-check 78 151 Inlet Temperature Probe Fault 80 152 NH No. 2 59 135 Engine/Gearbox Torque Fault No. 3045542 TABLE 101.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 1 Low Torque Fault 65 140 Torque Sensor Coil No. Fault Code Index (Cont’d) LRU Fault Code (HEX) Figure Fault Description 52 130 ARINC Label 211 Fault 53 131 ARINC Label 203 Fault 54 132 ARINC Label 206 Fault 57 133 Engine/Gearbox Torque Fault No. LRU Fault Code (HEX) Figure Fault Description 84 156 Dual NH Cross-check 85 157 Fail Fixed Wraparound Fault 86 158 Auto Ignition Wraparound Fault 87 159 IBV Wraparound Fault 89 160 PLA E1 Signal Fault 90 161 PLA E2 Signal Fault 91 162 PLA Total Fault 92 163 Stepper Motor Phase Fault 93 164 Stepper Motor Intermittent Phase Fault - 165 UPTRIM Lamp Wraparound LAB 166 Incorrect EEC Configuration Installed - 167 Throttle Stagger - 168 Dual Airspeed Input - 169 Unable to Trim Actual Power to Torque Bug - 170 Noisy Engine Surges at Intermediate Power - 171 Instability or Engine Runaway - 172 Autofeather System Faults - 173 Autofeather System Does not Arm on Takeoff - 174 Engine Power Increases as Propeller is Feathered Fault Isolation Steps Figures 102 through 174 list the steps for isolating and rectifying fault(s). 72-00-02 ENGINE . Fault Code Index (Cont’d) 8.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO.FAULT ISOLATION Page 106 Sep 03/99 . 3045542 TABLE 101. TEMP LO TORQUE 1 SENSOR RTN TORQUE 1 SENSOR HI 163 164 K J d COIL 1 P2 NH SIGNAL HI NH SIGNAL RTN 160 161 162 b U c 36−45 Ω T1. 3045542 JX P16 R P5 C A B E F PVM (LOCAL) .0 Ω NOM. E s a D L M N V 188 189 190 191 102 101 100 W TORQUE 2 SENSOR HI TORQUE 2 SENSOR RTN TOR. SEN.8 SENSOR LO T1. IGNITION NH SIGNAL HI NH SIGNAL RTN u t w COIL 2 G F S T H A B C P R J L N M 186 187 U j X n k F a c b G COIL 2 H 135 133 134 132 131 130 129 121 122 123 124 125 126 127 128 LL j UPTRIM LAMP UPTRIM DISC FROM OPP. STEP MOTOR A STEP MOTOR B STEP MOTOR C STEP MOTOR D RVDT EXC RVDT RTN RVDT RTN (E1 & E2) RVDT E1 RVDT E2 MFC ID LOOP MFC ID LOOP RTN 172 173 118 119 120 117 f CC DD F−G/S−G/T−G/H−G 115−155 Ω BLEED VALVE TM HI BLEED VALVE TM RTN PROP. SEN.0 Ω NOM.8 SENSOR RTN 100 101 102 JX 108. TEMP HI TOR.Schematic Diagram Figure 101 (Sheet 1 of 2) Page 107/108 Sep 03/99 c U b 1 2 3 4 5 COIL 1 EEC (LOCAL) S T H J K L A B G F E C D H J K E F A P a B N AFU (LOCAL) J16 P16 P1 P10 P6 R 157 158 159 J11 FEATHER SOL HI A P a B N 156 151 152 153 154 155 149 150 148 147 E F HI TORQUE FROM OPP RELAY 145 146 T A/F ARMED RELAY A/F TEST A/F ENABLE OPP.0 Ω NOM. SEN.FAULT ISOLATION 72-00-02 C68079 Electrical Wiring Harness and EEC . TEMP HI TOR. LOW TORQUE IND A/F ENABLE LOCAL AFU POWER 28VDC AFU POWER RTN UPTRIM OUTPUT HI TORQUE TO OPP RELAY A/F RELAY RTN A/F RELAY HI S 612−664 Ω D Y C V COIL 2 W 108.8 SENSOR HI T1. TORQUE SIGNAL HI TORQUE SIGNAL RTN TORQUE SIGNAL REF. TORQUE SIGNAL RTN TORQUE SIGNAL HI 141 142 143 144 U T EE q 557−589 Ω P9 COIL 1 NP SIGNAL HI NP SIGNAL RTN NP SIGNAL HI NP SIGNAL RTN L K 30−50 Ω P5 C D V W 65−95 Ω 3 4 1 2 5 139 140 136 137 138 B n R MANUAL SOL. ENGINE FEATHER DISC (CANCEL NP COVERING) FAIL FIXED RELAY RTN FAIL FIXED RELAY HI INHIBIT / RESET DISC DISCRETE RTN EEC POWER RTN EEC POWER RTN EEC POWER 28VDC EEC POWER 28VDC ECS FAULT RTN PW127H ENGINE TRIM DISC SPARE LRU SELECTOR b 72−88 Ω P7 P8 EE u c 184 185 136 i W g F v COIL 1 A C B p x X HH AA NH SIGNAL HI NH SIGNAL RTN K J X Y MM r 36−45 Ω A B G E F D C m a Z M S HH g F A−B 52−78 Ω P−C/R−C 76−114Ω r q L p e R P 174 175 176 177 178 179 180 181 182 183 BB h C STEP MOTOR EXC. SEN. TEMP RTN TOR. BRAKE DISC BLEED SWITCH NO 1 BLEED SWITCH NO 2 GROUND TEST DISC i N−M 32−55 Ω P14 Z 133−166 Ω G w COIL 2 3 4 1 2 5 115 116 114 y NN FF 612−664 Ω Z E COIL 1 P T S GG z k m AA V r U q A y W CC DISCRETE RTN GROUND TEST RTN RATING LOGIC BIT 2 DISC 112 113 103 104 105 106 107 108 109 110 111 KK x 108. EXC.ENGINE . TEMP LO TORQUE SIGNAL REF. SEN. RTN MANUAL SOL. PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. P4 165 166 167 168 169 170 171 SPARE RATING LOGIC BIT 1 DISC SPARE FROM AC DATA BUS ARINC (RTN) FROM AC DATA BUS ARINC (SIG) TEST SERIAL INPUT UART (SIG) TEST SERIAL INPUT UART (RTN) TEST SERIAL OUTPUT UART (SIG) TEST SERIAL OUTPUT UART (RTN) TO AC DATA BUS ARINC (SIG) TO AC DATA BUS ARINC (RTN) t z h E e d c G H 557−589 Ω 3 2 1 4 5 TORQUE 2 SENSOR HI TORQUE 2 SENSOR RTN TOR. . 2 C68209 Electrical Wiring Harness and EEC . 3045542 P36 HP FUEL FILTER IMPENDING BYPASS SWITCH (PUMP) SPARK IGNITION SYSTEM (SINGLE EXCITERS SINGLE OUTPUT) 1 2 P24 IGNITION EXCITER HP FUEL FILTER SIG HP FUEL FILTER RTN 201 202 G F P B A IGNITER PLUGS IGNITION BOX #1 RTN 192 193 IGNITION BOX #1 HI B A P32 ENGINE OIL INLET TEMP 90.3 Ω @ 20°C P24 IGNITION EXCITER B A IGNITION BOX #2 RTN 194 195 IGNITION BOX #2 HI A B OIL TEMPERATURE SIG OIL TEMPERATURE RTN 203 204 B P F G P35 LP FUEL FILTER IMPENDING BYPASS SWITCH A B LP FUEL FILTER SIG LP FUEL FILTER RTN 205 206 V C P P25 ENGINE OIL LP SWITCH B C P A P37 FUEL INLET TEMP OIL PRESSURE 28 VDC 196 197 198 OIL PRESSURE RTN OIL PRESSURE LOW SIG M D R 90.FAULT ISOLATION Page 109/110 Sep 03/99 213 214 R E D S .4 Ω @ 0°C 97.Schematic Diagram Figure 101 (Sheet 2) 72-00-02 ENGINE .4 Ω @ 0°C 97.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO.1 INSTRUMENTATION HARNESS NO.3 Ω @ 20°C A B FUEL TEMPERATURE SIG FUEL TEMPERATURE RTN 207 208 M A P27 ENGINE OIL PRESSURE TRANSMITTER + VE (CR) BUS TERMINAL − VE (AL) BUS TERMINAL 199 200 B A D E V K U OIL PRESSURE 10 VDC HI OIL PRESSURE 10 VDC RTN OIL PRESSURE RTN OIL PRESSURE SIG 209 210 211 212 H J L K N U P33 NL SENSOR THERMOCOUPLE TRIM CIRCUIT 1 2 NL SIGNAL HI NL SIGNAL RTN T6 THERMOCOUPLES INSTRUMENTATION HARNESS NO. . PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. C64036A EEC Fault Isolation Figure 102 72-00-02 ENGINE .FAULT ISOLATION Page 111 Sep 03/99 . 3045542 LRU FAULT CODE FAILURE 06 PLA BIAS (PLABIF) SYMPTOMS SUSPECT LRU 1. 72−01−10) NOTE : THIS FAULT MAY ALSO OCCUR DUE TO AN EEC ELECTRICAL POWER INTERRUPTION. EEC NO NPT GOVERNING ARINC "TRIMMED" PLA (133) = 0 DEGREE ARINC "RAW" PLA (134) = 0 DEGREE ARINC "COMMANDED TORQUE" (341) = 0% ENGINE CONTROL SYSTEM FAULT (ECSF) INDICATOR ON STEPPER MOTOR FAIL FIXED − DEGRADED EEC MODE REPLACE EEC (REF. 3045542 LRU FAULT CODE FAILURE 07 PLA GAIN (PLAGIF) SYMPTOMS SUSPECT LRU NO NPT GOVERNING ARINC "TRIMMED" PLA (133) = 0 DEGREE ARINC "RAW" PLA (134) = 0 DEGREE ARINC "COMMANDED TORQUE" (341) = 0% ENGINE CONTROL SYSTEM FAULT (ECSF) INDICATOR ON STEPPER MOTOR FAIL FIXED − DEGRADED EEC MODE 1.FAULT ISOLATION Page 112 Sep 03/99 . C64037 EEC Fault Isolation Figure 103 72-00-02 ENGINE . EEC REPLACE EEC (REF. 72−01−10) NOTE: THIS FAULT MAY ALSO OCCUR DUE TO AN EEC ELECTRICAL POWER INTERRUPTION.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. C64038 EEC Fault Isolation Figure 104 72-00-02 ENGINE .FAULT ISOLATION Page 113 Sep 03/99 . THIS FAULT SENDS A "DASH−DASH" OUTPUT TO THE COCKPIT ON ARINC LABEL 343 TO TELL THE PILOT THAT THE INTERCOMPRESSOR BLEED VALVE IS NOT OPERATIONAL. 3045542 LRU FAULT CODE FAILURE 08 LOSS OF INTERCOMPRESSOR BLEED VALVE CONTROL (HBOVIF) SYMPTOMS SUSPECT LRU INTERCOMPRESSOR BLEED VALVE CLOSED NO NPT U/S GOVERNING SEE LRU 12 ARINC LABEL 270 BIT 25 SET ENGINE CONTROL SYSTEM FAULT (ECSF) INDICATOR ON THIS FAULT IS CAUSED BY A DUAL NH FAILURE AND THE MAINTENANCE PROCEDURE FOR LRU 12 IS TO BE FOLLOWED. THE CHECK WILL DETECT AN INTERNAL EEC FAILURE OF THE TORQUE / NPT CONVERSION PROCESS.FAULT ISOLATION Page 114 Sep 03/99 .PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. C64039 EEC Fault Isolation Figure 105 72-00-02 ENGINE . 3045542 LRU FAULT CODE FAILURE 09 TORQUE TEST FAILURE (QTSTSW) SYMPTOMS SUSPECT LRU 1. EEC NO NPT U/S GOVERNING ARINC TORQUE INDICATION (343) = 0% ARINC BUG TORQUE INDICATION (344) = 0% ARINC "COMMANDED TORQUE" (341) = 0% ARINC "NPT" INDICATION (346) = 0% ARINC TORQUE INDICATION TO FDAU (254) = −− (NO READING) ENGINE CONTROL SYSTEM FAULT (ECSF) INDICATOR ON STEPPER MOTOR FAIL FIXED − DEGRADED EEC MODE REPLACE EEC (REF. 72−01−10) NOTE: THIS FUNCTION PERFORMS A GENERAL CHECK ON THE EEC TORQUE CONVERSION PROCESS. INSULATION RESISTANCE OF PINS P2 −s AND J11 − j TO OTHER PINS AND BACKSHELL ON CONNECTORS GREATER THAN OR EQUAL TO 2 MEGOHMS AT 45 VDC? REPAIR / REPLACE ENGINE HARNESS (REF. CONTINUITY ON LINE 134 LESS THAN OR EQUAL TO 0.5 OHM? PROPELLER CONTROL SYSTEM HARNESS TORQUE SENSOR EEC REPAIR / REPLACE ENGINE HARNESS (REF.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. NO NPT U/S GOVERNING ARINC TORQUE INDICATION (343) = 0% ARINC BUG TORQUE INDICATION (344) = 0% DIGITAL NPT INDICATION (346) = 0% ARINC TORQUE INDICATION TO FDAU (254) = −− (NO READING) ENGINE CONTROL SYSTEM FAULT (ECSF) INDICATOR ON STEPPER MOTOR FAIL FIXED − DEGRADED EEC MODE PROPELLER COMES OUT OF FEATHER WITHIN 20 SECONDS WHEN CONDITION LEVER MOVED TO UNFEATHER POSITION? CHECK HIGH PRESSURE OIL PUMP. 3045542 FAILURE LRU FAULT CODE 10 NPT INTERFACE (FREQUENCY TO DIGITAL CONVERSION) (NPTSW) SYMPTOMS SUSPECT LRU 1. PROPELLER ACTUATOR AND PROPELLER CONTROL UNIT (REF AMM) NO YES CHECK ENGINE HARNESS. 4. 72−01−10) NO YES CHECK ENGINE HARNESS. 2. 3.FAULT ISOLATION Page 115 Sep 03/99 . PROPELLER TRANSFER TUBE. 72−01−10) NO YES CONTINUED ON SHEET 2 C64040 EEC Fault Isolation Figure 106 (Sheet 1 of 2) 72-00-02 ENGINE . 2. 4. FEATHER IS NOT COMMANDED FOR 20 SECONDS AND NH IS ABOVE 72% BOTH FAULT CODES LRU 66 AND 73 ARE SET BOTH FAULT CODES LRU 65 AND 72 ARE SET BOTH FAULT CODES LRU 66 AND 72 ARE SET BOTH FAULT CODES LRU 65 AND 73 ARE SET C26353 EEC Fault Isolation Figure 106 (Sheet 2) 72-00-02 ENGINE . 3.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. NP IS BELOW 30%. 72−01−10) NOTE: FAULT CODE LRU 10 EXISTS IF: 1. 5.FAULT ISOLATION Page 116 Sep 03/99 . 3045542 CONTINUED FROM SHEET 1 ARE BOTH FAULT CODES LRU 66 AND 73 SET? YES CARRY OUT CHECKS AS PER LRU FAULT CODES 66 AND 73 YES CARRY OUT CHECKS AS PER LRU FAULT CODES 65 AND 72 YES CARRY OUT CHECKS AS PER LRU FAULT CODES 66 AND 72 YES CARRY OUT CHECKS AS PER LRU FAULT CODES 65 AND 73 NO ARE BOTH FAULT CODES LRU 65 AND 72 SET? NO ARE BOTH FAULT CODES LRU 66 AND 72 SET? NO ARE BOTH FAULT CODES LRU 65 AND 73 SET? NO REPLACE EEC (REF. 3045542 FAILURE LRU FAULT CODE 11 STEPPER MOTOR W/A CIRCUIT (SMSVIF) SYMPTOMS SUSPECT LRU 1.FAULT ISOLATION Page 117 Sep 03/99 . 175. 72−01−10) YES CHECK MFCU STEPPER MOTOR. LESS THAN 0. NO CONTINUITY BETWEEN PINS J8−G AND J8−F. 72−01−10) C68382 EEC Fault Isolation Figure 107 72-00-02 ENGINE .5 OHMS? REPAIR / REPLACE HARNESS (REF. 72−01−10) YES REPLACE EEC (REF. CONTINUITY ON LINES 174. EEC ENGINE CONTROL SYSTEM FAULT (ECSF) INDICATOR ON NO CHECK HARNESS. HARNESS 2.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. MFCU STEPPER MOTOR 3. BETWEEN 115 AND 155 OHMS? REPLACE MFCU (REF. 4.FAULT ISOLATION Page 118 Sep 03/99 . 4. 3. C64042 EEC Fault Isolation Figure 108 72-00-02 ENGINE . 3045542 FAILURE LRU FAULT CODE 12 DUAL NH (NHTIF) SYMPTOMS SUSPECT LRU 1. 3. INTERCOMPRESSOR BLEED VALVE CLOSED NO NPT GOVERNING NO AUTO−IGNITION DIGITAL NH INDICATOR (245) = 0% ENGINE CONTROL SYSTEM FAULT (ECSF) INDICATOR ON STEPPER MOTOR FAIL FIXED − DEGRADED EEC MODE NH OVERSPEED ABNORMAL ENGINE SHUTDOWN HARNESS NH SENSORS EEC HAS NH EXCEEDED 110% AND YES FAULT CODES LRU 80 AND 81 ALSO SET? TAKE APPROPRIATE ACTION FOR NH OVERSPEED NO WAS ENGINE SHUT DOWN BY INTERRUPTING FUEL SUPPLY WITH CONDITION LEVER IN UNFEATHER POSITION AND FAULT CODES LRU 82 AND 83 ALSO SET? YES SYSTEM NORMAL NO ARE ONLY LRU 81 AND 82 YES ALSO SET? CARRY OUT CHECK AS PER LRU FAULT CODES 81 AND 82 NO ARE ONLY LRU 80 AND 83 ALSO SET? YES CARRY OUT CHECK AS PER LRU FAULT CODES 80 AND 83 NO NOTE: REPLACE EEC (REF. 72−01−10) THIS FAULT IS SET IF: 1. 5. LRU 80 AND 81 ARE BOTH SET LRU 82 AND 83 ARE BOTH SET LRU 81 AND 82 ARE BOTH SET LRU 80 AND 83 ARE BOTH SET END OF CONVERSION IS FOUND FOR EITHER PROBE.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 2. 2. 5. 8 (211) = 0 ° ARINC "TORQUE BUG" (344) = 0% ARINC "COMMANDED TORQUE" (341) = 0% STEPPER MOTOR FAIL FIXED − DEGRADED EEC MODE REPLACE EEC (REF. NOT ON THE GROUND). ADC ECSF INDICATOR ON NO NPT U/S GOVERNING ARINC "ADC" TAT (211) = 0 ° ARINC "EEC" T1.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. T1. 72−01−10) NO AND RERUN ENGINE. 3045542 FAILURE LRU FAULT CODE 14 DUAL TEMP (TATIF) SYMPTOMS SUSPECT LRU 1.FAULT ISOLATION Page 119 Sep 03/99 .8 SENSOR AS PER LRU FAULT CODE 78 YES RECTIFY TAT ADC AS PER LRU FAULT CODE 52 NO IS FAULT CODE LRU 52 FOR ADC TOTAL AIR TEMPERATURE SET? NO SYSTEM NORMAL NOTE: THIS FAULT IS SET IF BOTH SOURCES SUPPLYING TEMPERATURE TO THE EEC ARE DETERMINED TO BE INVALID AND NPT IS ABOVE 60% (I.E. EEC 2. C64043 EEC Fault Isolation Figure 109 72-00-02 ENGINE .8 SENSOR 3. FAULT PERSISTS? SYSTEM NORMAL YES IS FAULT CODE LRU 78 FOR ENGINE INLET TEMPERATURE SENSOR SET? YES RECTIFY T1. 3045542 LRU FAULT CODE FAILURE 15 DUAL PRESSURE (ALTIF) SYMPTOMS SUSPECT LRU 1. EEC 2. ADC ECSF INDICATOR ON INTERCOMPRESSOR BLEED VALVE CONTROL DEGRADED NO NPT U/S GOVERNING ARINC "ADC" ALTITUDE (203) = 0 FOOT ARINC "EEC" ALTITUDE (203) = 0 FOOT ARINC "SELECTED" ALTITUDE (203) = 0 FOOT ARINC "TORQUE BUG" (344) = 0% ARINC "COMMANDED TORQUE" (341) = 0% STEPPER MOTOR FAIL FIXED − DEGRADED EEC MODE REPLACE EEC (REF. 72−01−10) NO AND RERUN ENGINE.FAULT ISOLATION Page 120 Sep 03/99 . NOT ON THE GROUND).PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. FAULT PERSISTS? SYSTEM NORMAL YES IS FAULT CODE LRU 53 FOR ALTITUDE ADC SET? YES RECTIFY ALTITUDE ADC AS PER LRU FAULT CODE 53 NO SYSTEM NORMAL NOTE: THIS FAULT IS SET IF BOTH SOURCES SUPPLYING AMBIENT PRESSURE TO THE EEC ARE DETERMINED TO BE INVALID AND NPT IS ABOVE 60% (I. C64045 EEC Fault Isolation Figure 110 72-00-02 ENGINE .E. THE STATIC PRESSURE TRANSDUCER IS LOCATED ON THE EEC AND IS CONTINUOUSLY CHECKED OVER A SPECIFIC PRESSURE RANGE. THIS FAULT WILL ALSO SET LRU = 44. 2. 72−01−10) NOTE: 1. C64046 EEC Fault Isolation Figure 111 72-00-02 ENGINE .FAULT ISOLATION Page 121 Sep 03/99 .PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. EEC REPLACE EEC (REF. 3045542 LRU FAULT CODE FAILURE 17 NACELLE STATIC PRESSURE (PSIF) SYMPTOMS SUSPECT LRU ARINC "EEC" ALTITUDE (203) = 0 FOOT ECSF INDICATOR ON 1. 3045542 LRU FAULT CODE FAILURE 18 SENSOR CALIBRATION (EDATIF) SYMPTOMS SUSPECT LRU ARINC "EEC" ALTITUDE (203) = 0 FOOT ARINC "EEC" AIRSPEED (206) = 0 KNOT ECSF INDICATOR ON 1. THE EEC LOCATED PRESSURE TRANSDUCER CALIBRATION DATA IS VERIFIED. C64047 EEC Fault Isolation Figure 112 72-00-02 ENGINE . THIS FAULT IS FLAGGED AND THE EEC ASSUMES DEFAULT VALUES.FAULT ISOLATION Page 122 Sep 03/99 . THIS FAULT WILL ALSO SET LRU = 44. 72−01−10) NOTE: 1. 2.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. DURING INITIALIZATION. EEC REPLACE EEC (REF. IF INVALID. FAULT ISOLATION Page 123 Sep 03/99 .PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 2. EEC ARINC "EEC" AIRSPEED (206) = 0 KNOT REPLACE EEC (REF. 72−01−10) NOTE: 1. THIS FAULT WILL ALSO SET LRU = 44. C26427 EEC Fault Isolation Figure 113 72-00-02 ENGINE . 3045542 FAILURE LRU FAULT CODE 19 NACELLE DELTA−P PRESSURE SENSOR (DELPIF) SYMPTOMS SUSPECT LRU 1. THIS DELTA−P PRESSURE TRANSDUCER IS LOCATED ON THE EEC AND IS CONTINUOUSLY CHECKED OVER A SPECIFIC PRESSURE RANGE. C64048 EEC Fault Isolation Figure 114 72-00-02 ENGINE . 2. THIS GAIN CORRECTION ACCOUNTS FOR STRAIN GAGE EXCITATION VARIATIONS. 3045542 LRU FAULT CODE FAILURE 20 LOW LEVEL GAIN (SGCIF) SYMPTOMS SUSPECT LRU NO PHYSICAL SYMPTOMS OTHER THAN FAULT CODE INDICATION AND ECSF INDICATOR ON 1.FAULT ISOLATION Page 124 Sep 03/99 . EEC REPLACE EEC (REF. LOW LEVEL INPUTS (mV) COMING FROM AMBIENT AND DIFFERENTIAL PRESSURE TRANSDUCERS ARE GAIN CORRECTED WITHIN THE EEC.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. THIS FAULT WILL ALSO SET LRU = 44. 72−01−10) NOTE: 1. THIS FAULT WILL ALSO SET LRU = 44. 2. C64049 EEC Fault Isolation Figure 115 72-00-02 ENGINE .PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO.8 (211) = 0 ° ECSF INDICATOR ON 1. THIS DRIFT CORRECTION TO LOW LEVEL (mV) INPUTS IS TO ACCOUNT FOR HARDWARE AMPLIFIER DRIFT. EEC REPLACE EEC (REF. 72−01−10) NOTE: 1.FAULT ISOLATION Page 125 Sep 03/99 . 3045542 LRU FAULT CODE FAILURE 21 LOW LEVEL DRIFT (DRFTIF) SYMPTOMS SUSPECT LRU ARINC "EEC" ALTITUDE (203) = 0 FOOT ARINC "EEC" AIRSPEED (206) = 0 KNOT ARINC "EEC" T1. 3045542 LRU FAULT CODE FAILURE 22 SENSOR CALIBRATION (CJIF) SYMPTOMS SUSPECT LRU NO PHYSICAL SYMPTOMS OTHER THAN FAULT CODE INDICATION 1.FAULT ISOLATION Page 126 Sep 03/99 .PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 72−01−10) NOTE: 1. AN INTERNAL EEC COLD JUNCTION IS USED TO CORRECT THE GAIN AND THE DRIFT OF THE EEC PRESSURE TRANSDUCERS FOR THERMAL VARIATIONS. EEC REPLACE EEC (REF. C26430 EEC Fault Isolation Figure 116 72-00-02 ENGINE . 2. THIS FAULT WILL ALSO SET LRU = 44. C64050 EEC Fault Isolation Figure 117 72-00-02 ENGINE .PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3045542 FAILURE LRU FAULT CODE 25 HIGH LEVEL GAIN (GAINIF) SYMPTOMS SUSPECT LRU NO PHYSICAL SYMPTOMS OTHER THAN FAULT CODE INDICATION AND ECSF INDICATOR ON IS FAULT CODE LRU 28 ALSO SET? 1.FAULT ISOLATION Page 127 Sep 03/99 . VALUES OUTSIDE THIS RANGE ARE CONSIDERED INVALID AND THIS FAULT IS FLAGGED. EACH SIGNAL IS GAIN COMPENSATED FOR VARIATIONS IN EXCITATION VOLTAGE. THE GAIN SIGNAL IS CONTINUOUSLY RANGE CHECKED. EEC YES CARRY OUT CHECK AS PER LRU FAULT CODE 28 YES CARRY OUT CHECK AS PER LRU FAULT CODE 29 NO IS FAULT CODE LRU 29 ALSO SET? NO ARE BOTH FAULT CODES LRU 28 AND 29 YES ALSO SET? CARRY OUT CHECK AS PER LRU FAULT CODE 28 AND 29 NO REPLACE EEC (REF. 72−01−10) NOTE: HIGH LEVER SIGNALS (I. TORQUE SHAFT CHARACTERIZATION PLUG 2.E. VDC) ARE PROCESSED AND CONVERTED TO DIGITAL SIGNALS FOR USE BY THE EEC. EEC PROCEED AS FOR FAULT CODE LRU 25 NOTE: HIGH LEVER SIGNALS (I. TORQUE SHAFT CHARACTERIZATION PLUG 2. 3045542 FAILURE LRU FAULT CODE 26 HIGH LEVEL DRIFT (DRFCIF) SYMPTOMS SUSPECT LRU NO PHYSICAL SYMPTOMS OTHER THAN FAULT CODE INDICATION AND ECSF INDICATOR ON 1. THIS FAULT MAY ALSO OCCUR DUE TO AN ELECTRICAL POWER INTERRUPTION OR POWER SUPPLY VOLTAGE REDUCTION. C64051 EEC Fault Isolation Figure 118 72-00-02 ENGINE .PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO.E. VDC) ARE DRIFT COMPENSATED FOR VARIATIONS IN TEMPERATURE.FAULT ISOLATION Page 128 Sep 03/99 . FAULT ISOLATION Page 129 Sep 03/99 . EEC ECSF INDICATOR ON TORQUE SHAFT CHARACTERIZATION PLUG NO IN PLACE (J4 OF EEC)? ENSURE IT IS IN PLACE YES REPLACE CHARACTERIZATION PLUG WITH RESISTOR VALUES R3 AND R4 AS PER DATA PLATE (REF. TORQUE SHAFT CHARACTERIZATION PLUG 2. 72−01−10) CHECK CONTINUITY RESISTANCE BETWEEN NO PINS. 3045542 FAILURE LRU FAULT CODE 28 Q2 GAIN (TGTIF) SYMPTOMS SUSPECT LRU TORQUE INDICATION MAY BE INACCURATE EEC WILL USE EEROM STORED VALUE 1. C TO E WITHIN ± 1.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 72−01−10) C64053 EEC Fault Isolation Figure 119 72-00-02 ENGINE .0% OF VALUE SHOWN ON PLUG DATA PLATE (R4)? YES REPLACE EEC (REF. EEC TORQUE SHAFT CHARACTERIZATION PLUG NO IN PLACE (J4 OF EEC)? ENSURE IT IS IN PLACE YES CHECK CONTINUITY RESISTANCE BETWEEN PINS. 72−01−10) C64054 EEC Fault Isolation Figure 120 72-00-02 ENGINE .FAULT ISOLATION Page 130 Sep 03/99 . TORQUE SHAFT CHARACTERIZATION PLUG 2.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO.0% OF VALUE SHOWN ON PLUG DATA PLATE (R3)? REPLACE CHARACTERIZATION PLUG WITH RESISTOR VALUES R3 AND R4 AS PER DATA PLATE (REF. 3045542 FAILURE LRU FAULT CODE 29 Q2 GAIN (TBTIF) SYMPTOMS SUSPECT LRU TORQUE INDICATION MAY BE INACCURATE EEC WILL USE EEROM STORED VALUE ECSF INDICATOR ON 1. 72−01−10) NO YES REPLACE EEC (REF. C TO D WITHIN ± 1. PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. EEC REPLACE EEC (REF.FAULT ISOLATION Page 131 Sep 03/99 . THE NON−VOLATILE MEMORY CANNOT BE ERASED WITH STANDARD PROCEDURES USING THE INHIBIT/RESET SWITCH. C26368 EEC Fault Isolation Figure 121 72-00-02 ENGINE . 3045542 LRU FAULT CODE FAILURE 31 EEPROM (EROMIF) SYMPTOMS SUSPECT LRU NO PHYSICAL SYMPTOMS OTHER THAN FAULT CODE INDICATION 1. 72−01−10) NOTE: THIS FAULT IS FLAGGED IN THE EVENT OF A FAILURE IN THE NON−VOLATILE MEMORY OF THE EEC. 3045542 LRU FAULT CODE FAILURE 32 ARINC OUTPUT (AROIF) SYMPTOMS SUSPECT LRU ALL ARINC OUTPUTS SET TO DEFAULT VALUES EXCEPT FOR DISCRETE OUTPUTS (270) ECSF INDICATOR ON 1. EEC REPLACE EEC (REF.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO.FAULT ISOLATION Page 132 Sep 03/99 . 72−01−10) NOTE: NO FAULT CODE IS SET IF THE INTERNAL ARINC DRIVER IS FOUND TO BE DEFECTIVE. C64056 EEC Fault Isolation Figure 122 72-00-02 ENGINE . FAULT ISOLATION Page 133 Sep 03/99 .PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. THIS LINK IS ONLY USED BY PWC PERSONNEL AND MAY BE IGNORED AT THE DISCRETION OF THE OPERATOR. 72−01−10) NOTE: THE UNIVERSAL ASYNCHRONOUS RECEIVER/TRANSMITTER (UART) IS A DATA BUS USED FOR MONITORING EEC PARAMETER. THIS FAULT WILL RESULT DUE TO AN INTERNAL EEC FAULT ONLY. EEC REPLACE EEC (REF. 3045542 LRU FAULT CODE FAILURE 34 UART INTERFACE (UARTIF) SYMPTOMS SUSPECT LRU NO PHYSICAL SYMPTOMS OTHER THAN FAULT CODE INDICATION AND ECSF INDICATOR ON 1. C64057 EEC Fault Isolation Figure 123 72-00-02 ENGINE . THE INDICATION TO THE EEC COMES FROM A RANGE CHECK PERFORMED ON THE OUTPUT WRAPAROUND CIRCUITRY. CONTINUITY ON NO LINES 172 AND 173 LESS THAN 0. 133 TO 161 OHMS? CONTINUITY BETWEEN PINS B AND C AND ALSO PIN F AND GROUND. 72−01−30). HARNESS 2. EEC ENGINE SURGE MAY OCCUR ARINC LABEL 270 BIT 25 SET ECSF INDICATOR ON REPAIR / REPLACE ENGINE HARNESS (REF. YES REPLACE EEC (REF. P1− i.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. IBV TORQUE MOTOR 3.FAULT ISOLATION Page 134 Sep 03/99 . 72−01−10) NOTE: THIS FAULT IS SET IF THE EEC DOES NOT YET GIVE A POSITIVE INDICATION THAT EITHER PWM NO. C68390 EEC Fault Isolation Figure 124 72-00-02 ENGINE . 1 OR 3 IS ACTIVE. INSULATION RESISTANCE OF PINS P10−A. LESS THAN 100 MILLI−OHMS? REPLACE IBV TORQUE MOTOR AND RECHECK IBV (REF. 3045542 FAILURE LRU FAULT CODE 39 INTERCOMPRESSOR BLEED VALVE WRAPAROUND INTERFACE (HBWAIF) SYMPTOMS SUSPECT LRU 1. 72−01−10) YES CHECK IBV TORQUE MOTOR.5 OHM? YES CHECK ENGINE HARNESS. NO AND P1−W TO OTHER PINS AND BACKSHELL ON CONNECTORS GREATER THAN 2 MEGOHMS AT 45 VDC? REPAIR / REPLACE ENGINE HARNESS (REF. P10−C. NO CONTINUITY BETWEEN PINS J10−A AND J10−C. 72−01−10) CHECK ENGINE HARNESS. EEC ECSF INDICATOR ON STEPPER MOTOR FAIL FIXED − DEGRADED EEC MODE TORQUE SHAFT CHARACTERIZATION PLUG NO IN PLACE (J4 OF EEC)? ENSURE IT IS IN PLACE YES REPLACE CHARACTERIZATION PLUG WITH RESISTOR VALUES R1. 72−01−10) C64083 EEC Fault Isolation Figure 125 72-00-02 ENGINE . R3 AND R4 AS PER DATA PLATE (REF.0% OF VALUE SHOWN ON PLUG DATA PLATE (R1) YES REPLACE EEC (REF. 72−01−10) CHECK CONTINUITY RESISTANCE BETWEEN NO PINS.FAULT ISOLATION Page 135 Sep 03/99 . 3045542 FAILURE LRU FAULT CODE LOSS OF ENGINE CONFIGURATION SIGNAL 40 SYMPTOMS SUSPECT LRU 1. TORQUE SHAFT / CONFIG. C TO A WITHIN +− 1. CHARACTERIZATION PLUG 2.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. R3 AND R4 AS PER DATA PLATE (REF. CHARACTERIZATION PLUG 2.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. TORQUE SHAFT / CONFIG.FAULT ISOLATION Page 136 Sep 03/99 . 72−01−10) CHECK CONTINUITY RESISTANCE BETWEEN NO PINS. C TO A WITHIN +− 1.0% OF VALUE SHOWN ON PLUG DATA PLATE (R1) YES REPLACE EEC (REF. 3045542 FAILURE LRU FAULT CODE LOSS OF ENGINE CONFIGURATION SIGNAL 41 SYMPTOMS SUSPECT LRU 1. EEC NO PHYSICAL SYMTOMS OTHER THAN ECSF INDICATOR ON TORQUE SHAFT CHARACTERIZATION PLUG NO IN PLACE (J4 OF EEC)? ENSURE IT IS IN PLACE YES REPLACE CHARACTERIZATION PLUG WITH RESISTOR VALUES R1. 72−01−10) C64084 EEC Fault Isolation Figure 126 72-00-02 ENGINE . 4. 72−01−40) NO YES REPAIR / REPLACE ENGINE HARNESS (REF.5 OHM? YES CHECK HARNESS. CONTINUITY BETWEEN PINS J8−J AND J8−L LESS THAN 1 OHM? NO REPLACE MFCU (REF. 72−01−10) NOTE: THIS FAULT IS SET IF THE EEC DOES NOT ACKNOWLEDGE CONTINUITY BETWEEN PINS J2 − a AND J2−D OF THE MFCU. THESE CONNECTED PINS WITHIN THE MFCU ARE A WAY FOR THE EEC TO IDENTIFY A PW127H MFCU. INSULATION RESISTANCE OF PINS P8−J.FAULT ISOLATION Page 137 Sep 03/99 . P8−L. THE PW127H MFCU’s PROVIDE HIGHER FLOWS FOR OPERATION AT PW127H POWERS THAN THE MFCU’s INSTALLED ON LOWER POWER ENGINES. 72−01−40) YES REPLACE EEC (REF. CONTINUITY ON LINES 186 NO AND 187 LESS THAN 0. P2−D AND P2− a TO OTHER PINS AND BACKSHELL ON CONNECTOR GREATER THAN 2 MEGOHMS? NO REPAIR / REPLACE ENGINE HARNESS (REF. 3. 3045542 FAILURE LRU FAULT CODE 43 MFCU IDENTIFICATION FAULT (MFCID) SYMPTOMS SUSPECT LRU 1. C64060 EEC Fault Isolation Figure 127 72-00-02 ENGINE .PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. INSULATION RESISTANCE OF PINS NO J8−J AND J8−L TO ALL OTHER PINS (EXCEPT TO EACH OTHER) AND BACKSHELL ON CONNECTOR GREATER THAN 2 MEGOHMS AT 45 VDC? REPLACE MFCU (REF. 2. 72−01−10) CHECK HARNESS. 72−01−10) YES CHECK MFCU. ECSF INDICATOR ON STEPPER MOTOR FAIL FIXED − DEGRADED EEC MODE HAS A PW127H MFCU BEEN INSTALLED? TYPE OF MFCU HARNESS MFCU EEC REPLACE WITH CORRECT MFCU (REF. 72−01−40) YES CHECK MFCU. LRU NO. 1. EEC REPLACE EEC (REF.FAULT ISOLATION Page 138 Sep 03/99 . 72−01−10) C26373 EEC Fault Isolation Figure 128 72-00-02 ENGINE . 3045542 LRU FAULT CODE FAILURE 44 EEC INTERNAL FAILURE (ECINTF) SYMPTOMS SUSPECT LRU PHYSICAL SYMPTOMS WILL DEPEND ON THE CAUSE OF THE FAULT. 17−22/31/32/34 CAN INDIVIDUALLY SET "ECINTF" WHICH WILL SHOW THE SPECIFIC ASSOCIATED SYMPTOMS.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. EEC YES CARRY OUT CHECK OF AIRCRAFT ADC SYSTEM (REF. 3045542 FAILURE LRU FAULT CODE 49 ARINC INPUT (ARINSW) SYMPTOMS SUSPECT LRU ARINC "ADC" ALTITUDE (203) = 0 FOOT ARINC "ADC" AIRSPEED (206) = 0 KNOT ARINC "ADC" TAT (211) = 0 ° ENGINE TORQUE MAY NOT MATCH BUG TORQUE AT 75 DEGREES PLA WHEN AT THERMALLY RATED POWER POSSIBLE LEFT AND RIGHT TORQUE BUG SPLIT ECSF INDICATOR ON FAULT OCCURS ON BOTH ENGINES? 1. AMM) NO RECTIFY PROBLEM WITH ORIGINAL ADC NO SELECT OTHER ADC AND RUN ENGINE TO CHECK FOR FAULT. HARNESS 3.5 OHM? REPAIR / REPLACE ENGINE HARNESS (REF. ADC 2. CONTINUITY ON LINES 104 AND 105 LESS THAN OR EQUAL TO 0. FAULT STILL EXISTS (REF. 72−01−10) NO YES CONTINUED ON SHEET 2 C68389 EEC Fault Isolation Figure 129 (Sheet 1 of 2) 72-00-02 ENGINE .PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO.FAULT ISOLATION Page 139 Sep 03/99 . NOTE)? YES CHECK ENGINE HARNESS. FAULT ISOLATION Page 140 Sep 03/99 . J11− z. THIS FAULT IS SET IF THE ARINC INPUT LINK IS FOUND TO BE INVALID WITH NPT ABOVE 60%.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 72−01−10) NO YES REPLACE EEC (REF. 72−01−10) NOTE: INITIAL SYSTEM CHECKS MUST BE CARRIED OUT WHEN THE ENGINE IS RUNNING AND OUT OF FEATHER SINCE ALL ADC FAULT ACTIONS AND INDICATIONS ARE INHIBITED WHEN THE ENGINE IS NOT RUNNING. INSULATION RESISTANCE OF PINS J11− h. C26375 EEC Fault Isolation Figure 129 (Sheet 2) 72-00-02 ENGINE . P2−S AND P2−T TO ALL OTHER PINS ON SAME CONNECTOR AND BACKSHELL GREATER THAN OR EQUAL TO 2 MEGOHMS AT 45 VAC OR VDC? REPAIR / REPLACE ENGINE HARNESS (REF. 3045542 CONTINUED FROM SHEET 1 CHECK ENGINE HARNESS. PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. EEC CARRY OUT CHECK OF AIRCRAFT ADC SYSTEM (REF. 3045542 LRU FAULT CODE FAILURE 52 ARINC LABEL 211 (A211SW) SYMPTOMS SUSPECT LRU ARINC "ADC" TAT (211) = 0 ° ENGINE TORQUE MAY NOT MATCH BUG TORQUE AT 75 DEGREES PLA WHEN AT THERMALLY RATED POWER POSSIBLE LEFT AND RIGHT TORQUE BUG SPLIT ECSF INDICATOR ON 1. HARNESS 3. ADC 2. C64063 EEC Fault Isolation Figure 130 72-00-02 ENGINE . AMM) FAULT OCCURS ON YES BOTH ENGINES? NO SELECT OTHER ADC AND RUN ENGINE TO CHECK FOR FAULT.FAULT ISOLATION Page 141 Sep 03/99 . NOTE)? NO RECTIFY PROBLEM WITH ORIGINAL ADC YES DOES FAULT CODE YES LRU 49 (ARINC INPUT) EXIST? CARRY OUT CHECK AS PER LRU FAULT CODE 49 NO SYSTEM NORMAL NOTE: INITIAL SYSTEM CHECKS MUST BE CARRIED OUT WHEN THE ENGINE IS RUNNING AND OUT OF FEATHER WITH NPT ABOVE 60% SINCE ALL ADC FAULT ACTIONS AND INDICATIONS ARE INHIBITED WHEN THE ENGINE IS NOT RUNNING. FAULT STILL EXISTS (REF. PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. NOTE)? NO RECTIFY PROBLEM WITH ORIGINAL ADC YES DOES FAULT CODE YES LRU 49 (ARINC INPUT) EXIST? CARRY OUT CHECK AS PER LRU FAULT CODE 49 NO SYSTEM NORMAL NOTE: INITIAL SYSTEM CHECKS MUST BE CARRIED OUT WHEN THE ENGINE IS RUNNING AND OUT OF FEATHER WITH NPT ABOVE 60% SINCE ALL ADC FAULT ACTIONS AND INDICATIONS ARE INHIBITED WHEN THE ENGINE IS NOT RUNNING. EEC ARINC "ADC" ALTITUDE (203) = 0 FEET ENGINE TORQUE MAY NOT MATCH BUG TORQUE AT 75 DEGREES PLA WHEN AT THERMALLY RATED POWER POSSIBLE LEFT AND RIGHT TORQUE BUG SPLIT ECSF INDICATOR ON CARRY OUT CHECK OF AIRCRAFT ADC SYSTEM (REF.FAULT ISOLATION Page 142 Sep 03/99 . 3045542 LRU FAULT CODE FAILURE 53 ARINC LABEL 203 (A203SW) SYMPTOMS SUSPECT LRU 1. AMM) FAULT OCCURS ON YES BOTH ENGINES? NO SELECT OTHER ADC AND RUN ENGINE TO CHECK FOR FAULT. FAULT STILL EXISTS (REF. ADC 2. C64065 EEC Fault Isolation Figure 131 72-00-02 ENGINE . HARNESS 3. 3045542 LRU FAULT CODE FAILURE 54 ARINC LABEL 206 (A206SW) SYMPTOMS SUSPECT LRU 1.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. HARNESS 3. NOTE)? NO RECTIFY PROBLEM WITH ORIGINAL ADC YES DOES FAULT CODE YES LRU 49 (ARINC INPUT) EXIST? CARRY OUT CHECK AS PER LRU FAULT CODE 49 NO SYSTEM NORMAL NOTE: INITIAL SYSTEM CHECKS MUST BE CARRIED OUT WHEN THE ENGINE IS RUNNING AND OUT OF FEATHER WITH NPT ABOVE 60% SINCE ALL ADC FAULT ACTIONS AND INDICATIONS ARE INHIBITED WHEN THE ENGINE IS NOT RUNNING. AMM) FAULT OCCURS ON YES BOTH ENGINES? NO SELECT OTHER ADC AND RUN ENGINE TO CHECK FOR FAULT. EEC ARINC "ADC" AIRSPEED (206) = 0 KNOT ENGINE TORQUE MAY NOT MATCH BUG TORQUE AT 75 DEGREES PLA WHEN AT THERMALLY RATED POWER POSSIBLE LEFT AND RIGHT TORQUE BUG SPLIT ECSF INDICATOR ON CARRY OUT CHECK OF AIRCRAFT ADC SYSTEM (REF. FAULT STILL EXISTS (REF.FAULT ISOLATION Page 143 Sep 03/99 . C64066 EEC Fault Isolation Figure 132 72-00-02 ENGINE . ADC 2. NOTE: THIS FAULT OCCURS WHEN THE ENGINE TORQUE IS BETWEEN 122% AND 137% (12800 −14440 LB.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 1 (Q22TQE) SYMPTOMS SUSPECT LRU NO PHYSICAL SYMPTOMS OTHER THAN FAULT CODE INDICATION ECSF INDICATOR ON RECORD OVERTORQUE IN LOG BOOK CARRY OUT MAINTENANCE ACTIONS SPECIFIED IN CHAPTER 05−50−00. 3045542 FAILURE LRU FAULT CODE 57 ENGINE/GEARBOX OVER TORQUE FAULT NO.) FOR A CONTINUOUS PERIOD OF TIME GREATER THAN 600 SECONDS. ) FOR A CONTINUOUS PERIOD OF TIME GREATER THAN 20 AND LESS THAN 300 SECONDS. FT. C64068 EEC Fault Isolation Figure 133 72-00-02 ENGINE .FAULT ISOLATION Page 144 Sep 03/99 . OR WHEN THE ENGINE TORQUE IS BETWEEN 100% AND 122% (10504−12800 LB. FT. FAULT ISOLATION Page 145 Sep 03/99 .8 161.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO.6 OR LESS THAN 217.6 − 152.8 − 166.8 142.) TORQUE PERIOD (SEC) 137.5 − 142.9 OR LESS THAN 179.1 OR LESS THAN 140. 3045542 LRU FAULT CODE FAILURE 58 ENGINE / GEARBOX OVERTORQUE FAULT NO.3 152.7 OR LESS THAN 62.9 OR LESS THAN 20 C64070 EEC Fault Isolation Figure 134 72-00-02 ENGINE .1 − 161.6 166.1 157.3 − 157. NOTE: THIS FAULT IS SET IF THE FOLLOWING TORQUE LEVELS ARE MAINTAINED FOR THE CONTINUOUS PERIODS INDICATED: TORQUE BETWEEN (%) TORQUE VAL (LB.6 147. FT.8 14440 − 15000 15000 − 15500 15500 − 16000 16000 − 16500 16500 − 17000 17000 − 17500 17500 − 18054 LESS THAN 256. 2 (Q37TQE) SYMPTOMS SUSPECT LRU NO PHYSICAL SYMPTOMS OTHER THAN FAULT CODE INDICATION ECSF INDICATOR ON RECORD OVERTORQUE IN LOG BOOK CARRY OUT MAINTENANCE ACTIONS SPECIFIED IN CHAPTERS 05−50−00.8 − 147.4 OR LESS THAN 101.6 − 171. 3 − 157.7 OR GREATER THAN 62.5 137.89% (18054 LB.1 OR GREATER THAN 140.8 − 137.FAULT ISOLATION Page 146 Sep 03/99 . FT.3 152.5 − 142.) C64073 EEC Fault Isolation Figure 135 72-00-02 ENGINE .8 − 147.9 OR GREATER THAN 20 OR ❉ ❉ TORQUE GREATER THAN 171.8 142.9 OR GREATER THAN 179.6 − 171.6 − 152.6 OR GREATER THAN 217.1 − 161.8 12794 − 14443 14443 − 15000 15000 − 15500 15500 − 16000 16000 − 16500 16500 − 17000 17000 − 17500 17500 − 18054 TORQUE PERIOD (SEC) GREATER THAN 300.4 OR GREATER THAN 101.1 157.0 OR GREATER THAN 256.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO.8 − 166.8 161.6 166. 3 (Q47TQE) SYMPTOMS SUSPECT LRU NO PHYSICAL SYMPTOMS OTHER THAN FAULT CODE INDICATION ECSF INDICATOR ON RECORD OVERTORQUE IN LOG BOOK REMOVE RGB MODULE AND RETURN TO AN OVERHAUL FACILITY FOR INSPECTION NOTE: THIS FAULT IS SET FOR THE FOLLOWING TORQUE LEVELS: TORQUE BETWEEN (%) TORQUE VAL (LB.) 121.6 147. FT. 3045542 LRU FAULT CODE FAILURE 59 ENGINE / GEARBOX OVERTORQUE FAULT NO. C64074 EEC Fault Isolation Figure 136 72-00-02 ENGINE . EEC ENGINE TORQUE MAY NOT MATCH BUG TORQUE AT 75 DEGREES PLA WHEN AT THERMALLY RATED POWER POSSIBLE LEFT AND RIGHT TORQUE BUG SPLIT ECSF INDICATOR ON CARRY OUT CHECK OF AIRCRAFT TAT MEASUREMENT SYSTEM (REF. FAULT STILL EXISTS? (REF. ADC 2.7 ° C (14 ° F) FOR OTHER RATINGS. T1. AMM) FAULT OCCURS ON YES BOTH ENGINES? NO SELECT OTHER ADC AND RUN ENGINE TO CHECK FOR FAULT.5 ° C (28 ° F) IN MCL AND MCR RATINGS AND +− 7. NOTE)? NO SYSTEM NORMAL YES REPLACE EEC (REF. 72−01−10) NOTE: INITIAL SYSTEM CHECKS MUST BE CARRIED OUT WHEN THE ENGINE IS RUNNING AND OUT OF FEATHER SINCE ALL ADC FAULT ACTIONS AND INDICATIONS ARE INHIBITED WHEN THE ENGINE IS NOT RUNNING.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO.FAULT ISOLATION Page 147 Sep 03/99 .8 SENSOR 3. AND PLA IS GREATER THAN 40 DEGREES. THIS FAULT IS SET IF ADC AND EEC PROBES DIFFER BY MORE THAN +− 15. FAULT STILL EXISTS (REF. NOTE)? NO RECTIFY PROBLEM WITH ORIGINAL ADC YES REPLACE T1. 3045542 LRU FAULT CODE FAILURE 61 TAT CROSS−CHECK (TATXIF) SYMPTOMS SUSPECT LRU 1. TORQUE OUTPUT IS 90% OF TQBUG.8 SENSOR ON ENGINE WITH FAULT. C64075 EEC Fault Isolation Figure 137 72-00-02 ENGINE .PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO.5 PSIA FOR OTHER RATINGS WITH PLA ABOVE 40 DEGREES. FAULT STILL EXISTS (REF. EEC ENGINE TORQUE MAY NOT MATCH BUG TORQUE AT 75 DEGREES PLA WHEN AT THERMALLY RATED POWER POSSIBLE LEFT AND RIGHT TORQUE BUG SPLIT ECSF INDICATOR ON CARRY OUT CHECK OF AIRCRAFT TAT MEASUREMENT SYSTEM (REF. ADC 2.FAULT ISOLATION Page 148 Sep 03/99 . NOTE)? NO RECTIFY PROBLEM WITH ORIGINAL ADC YES REPLACE EEC (REF. AMM) FAULT OCCURS ON YES BOTH ENGINES? NO SELECT OTHER ADC AND RUN ENGINE TO CHECK FOR FAULT. 3045542 FAILURE LRU FAULT CODE 62 ALT CROSS−CHECK (ALTXIF) SYMPTOMS SUSPECT LRU 1. THIS FAULT IS SET IF ADC AND EEC PROBES DIFFER BY MORE THAN +− 1 PSIA IN MCL AND MCR RATINGS AND +− 0. 72−01−10) NOTE: INITIAL SYSTEM CHECKS MUST BE CARRIED OUT WHEN THE ENGINE IS RUNNING AND OUT OF FEATHER SINCE ALL ADC FAULT ACTIONS AND INDICATIONS ARE INHIBITED WHEN THE ENGINE IS NOT RUNNING. 2. 72−01−60) NO YES CHECK TORQUE SENSOR NO. TORQUE SENSOR NO. 72−01−10) NOTE: TO SET THIS FAULT. 2. THIS FAULT IS SPECIFIC TO COIL NO. 2 COIL NO. 3045542 LRU FAULT CODE FAILURE 63 TORQUE SENSOR NO. FEATHER NOT COMMANDED AND TORQUE OVER 230%. P7−D. INSULATION RESISTANCE OF PINS P7−C.2. 72−01−10) NO YES CHECK TORQUE SENSOR NO. 72−01−60) YES REPLACE EEC (REF. INSULATION RESISTANCE OF PIN J7−C TO ALL OTHER PINS NO (EXCEPT J7−D) AND BACKSHELL.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. C68384 EEC Fault Isolation Figure 138 72-00-02 ENGINE . P1−R TO OTHER PINS AND BACKSHELL ON CONNECTORS GREATER THAN 2 MEGOHMS AT 45 VDC? REPAIR / REPLACE HARNESS (REF. NPT MUST BE BETWEEN 21% AND 135%. 1 OF TORQUE SENSOR NO. AND PIN J7−D TO ALL OTHER PINS (EXCEPT J7−C) AND BACKSHELL GREATER THAN 2 MEGOHMS AT 45 VDC? REPLACE TORQUE SENSOR NO. 2 3. CONTINUITY ON LINES 170 AND 171 LESS THAN 0. P1−P. 2 (REF.5 OHM? REPAIR / REPLACE HARNESS (REF. 1 HIGH TORQUE (Q1IF) SYMPTOMS SUSPECT LRU NO PHYSICAL SYMPTOMS OTHER THAN FAULT CODE INDICATION AND ECSF INDICATOR ON 1. CONTINUITY BETWEEN PINS J7−C AND J7−D HAVE A RESISTANCE BETWEEN 612 AND 664 OHMS? REPLACE TORQUE SENSOR NO. EEC CHECK HARNESS. 72−01−10) NO YES CHECK HARNESS. HARNESS 2. 2 (REF.FAULT ISOLATION Page 149 Sep 03/99 . PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3045542 LRU FAULT CODE FAILURE 64 TORQUE SENSOR NO. 2 COIL NO. 1 LOW TORQUE (Q1LIF) SYMPTOMS SUSPECT LRU NO PHYSICAL SYMPTOMS OTHER THAN FAULT CODE INDICATION AND ECSF INDICATOR ON 1. HARNESS 2. TORQUE SENSOR NO. 2 3. EEC CHECK HARNESS. CONTINUITY ON LINES 170 AND 171 LESS THAN 0.5 OHM? REPAIR / REPLACE HARNESS (REF. 72−01−10) NO YES CHECK HARNESS. INSULATION RESISTANCE OF PINS P7−C, P7−D, P1−P, P1−R TO OTHER PINS AND BACKSHELL ON CONNECTORS GREATER THAN 2 MEGOHMS AT 45 VDC? REPAIR / REPLACE HARNESS (REF. 72−01−10) NO YES CHECK TORQUE SENSOR NO. 2. CONTINUITY BETWEEN PINS J7−C AND J7−D HAVE A RESISTANCE BETWEEN 612 AND 664 OHMS? REPLACE TORQUE SENSOR NO. 2 (REF. 72−01−60) NO YES CHECK TORQUE SENSOR NO. 2. INSULATION RESISTANCE OF PIN J7−C TO ALL OTHER PINS (EXCEPT J7−D) AND BACKSHELL, AND PIN J7−D TO ALL OTHER PINS (EXCEPT J7−C) AND BACKSHELL GREATER THAN 2 MEGOHMS AT 45 VDC? REPLACE TORQUE SENSOR NO. 2 (REF. 72−01−60) NO YES REPLACE EEC (REF. 72−01−10) NOTE: TO SET THIS FAULT, NPT MUST BE BETWEEN 21% AND 135%, FEATHER NOT COMMANDED AND TORQUE LOWER THAN −20%. THIS FAULT IS SPECIFIC TO COIL NO. 1 OF TORQUE SENSOR NO.2. C68385 EEC Fault Isolation Figure 139 72-00-02 ENGINE - FAULT ISOLATION Page 150 Sep 03/99 PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3045542 LRU FAULT CODE FAILURE 65 TORQUE SENSOR NO. 2 COIL NO. 1 H1 NPT (NP1IF) SYMPTOMS SUSPECT LRU NO PHYSICAL SYMPTOMS OTHER THAN FAULT CODE INDICATION AND ECSF INDICATOR ON DID NP EXCEED 135%? 1. 2. 3. 4. FOLLOW APPROPRIIATE MAINTENANCE ACTION FOR NP OVERSPEED (REF. 05−50−00) YES NO CHECK HARNESS. CONTINUITY ON LINES 170 AND 171 LESS THAN 0.5 OHM? NP OVERSPEED HARNESS TORQUE SENSOR NO. 2 EEC NO REPAIR / REPLACE HARNESS (REF. 72−01−10) YES CHECK HARNESS. INSULATION RESISTANCE OF PINS P7−C, P7−D, P1−P, P1−R TO OTHER PINS AND BACKSHELL ON CONNECTORS GREATER THAN 2 MEGOHMS AT 45 VDC? NO REPAIR / REPLACE HARNESS (REF. 72−01−10) YES CHECK TORQUE SENSOR NO. 2. CONTINUITY BETWEEN PINS J7−C AND J7−D HAVE A RESISTANCE BETWEEN 612 AND 664 OHMS? NO REPLACE TORQUE SENSOR NO. 2 (REF. 72−01−60) YES CHECK TORQUE SENSOR NO. 2. INSULATION RESISTANCE OF PIN J7−C TO ALL OTHER PINS NO (EXCEPT J7−D) AND BACKSHELL, AND PIN J7−D TO ALL OTHER PINS (EXCEPT J7−C) AND BACKSHELL GREATER THAN 2 MEGOHMS AT 45 VDC? REPLACE TORQUE SENSOR NO. 2 (REF. 72−01−60) YES REPLACE EEC (REF. 72−01−10) NOTE: THIS FAULT IS SET IF NPT EXCEEDS 135% AND FEATHER IS NOT COMMANDED. C68387 EEC Fault Isolation Figure 140 72-00-02 ENGINE - FAULT ISOLATION Page 151 Sep 03/99 PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3045542 LRU FAULT CODE FAILURE 66 TORQUE SENSOR NO. 2 COIL NO. 1 LOW NPT (NP1LIF) SYMPTOMS SUSPECT LRU NO PHYSICAL SYMPTOMS OTHER THAN FAULT CODE INDICATION AND ECSF INDICATOR ON 1. HARNESS 2. TORQUE SENSOR NO. 2 3. EEC CHECK HARNESS. CONTINUITY ON LINES 170 AND 171 LESS THAN 0.5 OHM? REPAIR / REPLACE HARNESS (REF. 72−01−10) NO YES CHECK HARNESS. INSULATION RESISTANCE OF PINS P7−C, P7−D, P1−P, P1−R TO OTHER PINS AND BACKSHELL ON CONNECTORS GREATER THAN 2 MEGOHMS AT 45 VDC? REPAIR / REPLACE HARNESS (REF. 72−01−10) NO YES CHECK TORQUE SENSOR NO. 2. CONTINUITY BETWEEN PINS J7−C AND J7−D HAVE A RESISTANCE BETWEEN 612 AND 664 OHMS? REPLACE TORQUE SENSOR NO. 2 (REF. 72−01−60) NO YES CHECK TORQUE SENSOR NO. 2. INSULATION RESISTANCE OF PIN J7−C TO ALL OTHER PINS NO (EXCEPT J7−D) AND BACKSHELL, AND PIN J7−D TO ALL OTHER PINS (EXCEPT J7−C) AND BACKSHELL GREATER THAN 2 MEGOHMS AT 45 VDC? REPLACE TORQUE SENSOR NO. 2 (REF. 72−01−60) YES REPLACE EEC (REF. 72−01−10) NOTE: THIS FAULT IS SET IF FOLLOWING ENGINE START, NPT GOES ABOVE 25%, FEATHER IS NOT COMMANDED (CLA OUT OF FEATHER POSITION) AND A SUBSEQUENT NPT VALUE IS LOWER THAN 21%. C68388 EEC Fault Isolation Figure 141 72-00-02 ENGINE - FAULT ISOLATION Page 152 Sep 03/99 PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3045542 LRU FAULT CODE FAILURE 67 CONNECTOR FAILURE (CONNIF) SYMPTOMS SUSPECT LRU 1. EEC CONNECTOR P1 2. EEC INTERCOMPRESSOR BLEED VALVE CLOSES NO AUTO−IGNITION NO NPT U/S GOVERNING ARINC "RAW" PLA (134) = 0 DEGREE ARINC "EEC" T1.8 (211) = 0 ° ARINC NH INDICATION (245) = 0% ARINC "COMMANDED TORQUE" (341) = 0% ARINC "NPT" INDICATION (346) = 0% ARINC LABEL 270 BIT 25 SET ECSF INDICATOR ON STEPPER MOTOR FAIL FIXED IS CONNECTOR P1 SECURELY MATED TO J1? NO RECONNECT P1 TO EEC YES REPAIR / REPLACE (REF. 72−01/10) YES IS ENGINE HARNESS VISUALLY DAMAGED? NO REPLACE EEC (REF. 72−01−10) NOTE: THIS FAULT IS SET IF LRU 74/78/84/90 ARE ALL SIMULTANEOUSLY LATCHED. THESE LRU’s CORRESPOND TO THE TORQUE SHAFT TEMPERATURE, NACELLE AMBIENT TEMPERATURE AND E1 AND E2 SIGNALS FROM THE RVDT IN THE MFC. C64082 EEC Fault Isolation Figure 142 72-00-02 ENGINE - FAULT ISOLATION Page 153 Sep 03/99 PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3045542 FAILURE LRU FAULT CODE 69 TOTAL TORQUE (FREQUENCY / DIGITAL CONVERSION) (QTOTSW) SYMPTOMS SUSPECT LRU EEC FAULT LAMP ON (FAIL FIX) NO NPT U/S GOVERNING ARINC "TORQUE" INDICATION (343) = 0% ARINC BUG TORQUE INDICATION (344) = 0% ARINC "COMMANDED TORQUE" (341) = 0% ARINC "NPT" INDICATION (346) = 0% FAULT CODES SET INCLUDE ONLY LRU 63 AND 71? 1. 2. 3. 4. HARNESS TORQUE SENSOR, NO. 2 TORQUE SHAFT EEC YES CARRY OUT CHECKS AS PER LRU FAULT CODES 63 AND 71 YES CARRY OUT CHECKS AS PER LRU FAULT CODES 64 AND 70 NO FAULT CODES SET INCLUDE ONLY LRU 64 AND 70? NO FAULT CODES SET INCLUDE YES LRU 64 AND 71 OR 63 AND 70? CHECK TORQUE SHAFTS NO REPLACE EEC (REF. 72−01−10) NOTE: THIS FAULT IS SET IF: 1. 2. 3. 4. LRU 63 AND 70 ARE BOTH SET LRU 64 AND 71 ARE BOTH SET LRU 63 AND 71 ARE BOTH SET LRU 64 AND 70 ARE BOTH SET C26437 EEC Fault Isolation Figure 143 72-00-02 ENGINE - FAULT ISOLATION Page 154 Sep 03/99 PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3045542 LRU FAULT CODE FAILURE 70 TORQUE SENSOR NO. 2 COIL NO. 2 HIGH TORQUE (Q2IF) SYMPTOMS SUSPECT LRU NO PHYSICAL SYMPTOMS OTHER THAN FAULT CODE INDICATION 1. HARNESS 2. TORQUE SENSOR NO. 2 3. EEC CHECK HARNESS. CONTINUITY ON LINES 165 AND 166 LESS THAN 0.5 OHM? REPAIR / REPLACE HARNESS (REF. 72−01−10) NO YES CHECK HARNESS. INSULATION RESISTANCE OF PINS P7−A, P7−B, P1− r, P1− q TO OTHER PINS AND BACKSHELL ON CONNECTORS GREATER THAN 2 MEGOHMS AT 45 VDC? REPAIR / REPLACE HARNESS (REF. 72−01−10) NO YES CHECK TORQUE SENSOR NO. 2. CONTINUITY BETWEEN PINS J7−A AND J7−B HAVE A RESISTANCE BETWEEN 557 AND 589 OHMS? REPLACE TORQUE SENSOR NO. 2 (REF. 72−01−60) NO YES CHECK TORQUE SENSOR NO. 2. INSULATION RESISTANCE OF PIN J7−A TO ALL OTHER PINS NO (EXCEPT J7−B) AND BACKSHELL, AND PIN J7−B TO ALL OTHER PINS (EXCEPT J7−A) AND BACKSHELL GREATER THAN 2 MEGOHMS AT 45 VDC? REPLACE TORQUE SENSOR NO. 2 (REF. 72−01−60) YES REPLACE EEC (REF. 72−01−10) NOTE: TO SET THIS FAULT, NPT MUST BE BETWEEN 21% AND 135%, FEATHER NOT COMMANDED AND TORQUE OVER 230%. THIS FAULT IS SPECIFIC TO COIL NO. 2 OF TORQUE SENSOR NO.2. C68358 EEC Fault Isolation Figure 144 72-00-02 ENGINE - FAULT ISOLATION Page 155 Sep 03/99 PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3045542 LRU FAULT CODE FAILURE 71 TORQUE SENSOR NO. 2 COIL NO. 2 LOW TORQUE (Q2LIF) SYMPTOMS SUSPECT LRU NO PHYSICAL SYMPTOMS OTHER THAN FAULT CODE INDICATION 1. HARNESS 2. TORQUE SENSOR NO. 2 3. EEC CHECK HARNESS. CONTINUITY ON LINES 165 AND 166 LESS THAN 0.5 OHM? REPAIR / REPLACE HARNESS (REF. 72−01−10) NO YES CHECK HARNESS. INSULATION RESISTANCE OF PINS P7−A, P7−B, P1− r, P1− q TO OTHER PINS AND BACKSHELL ON CONNECTORS GREATER THAN 2 MEGOHMS AT 45 VDC? REPAIR / REPLACE HARNESS (REF. 72−01−10) NO YES CHECK TORQUE SENSOR NO. 2. CONTINUITY BETWEEN PINS J7−A AND J7−B HAVE A RESISTANCE BETWEEN 557 AND 589 OHMS? REPLACE TORQUE SENSOR NO. 2 (REF. 72−01−60) NO YES CHECK TORQUE SENSOR NO. 2. INSULATION RESISTANCE OF PIN J7−A TO ALL OTHER PINS NO (EXCEPT J7−B) AND BACKSHELL, AND PIN J7−B TO ALL OTHER PINS (EXCEPT J7−A) AND BACKSHELL ON CONNECTOR GREATER THAN 2 MEGOHMS AT 45 VDC? REPLACE TORQUE SENSOR NO. 2 (REF. 72−01−60) YES REPLACE EEC (REF. 72−01−10) NOTE: TO SET THIS FAULT, NPT MUST BE BETWEEN 21% AND 135%, FEATHER NOT COMMANDED AND TORQUE LOWER THAN −20%. THIS FAULT IS SPECIFIC TO COIL NO. 2 OF TORQUE SENSOR NO. 2. C68359 EEC Fault Isolation Figure 145 72-00-02 ENGINE - FAULT ISOLATION Page 156 Sep 03/99 PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3045542 LRU FAULT CODE FAILURE 72 TORQUE SENSOR NO. 2 COIL NO. 2 HIGH NPT (NP2IF) SUSPECT LRU SYMPTOMS NO PHYSICAL SYMPTOMS OTHER THAN FAULT CODE INDICATION NP EXCEEDS 135% 1. 2. 3. 4. FOLLOW APPROPRIATE MAINTENANCE ACTION FOR NP OVERSPEED (REF. 05−50−00) YES NO CHECK HARNESS. CONTINUITY ON LINES 165 AND 166 LESS THAN 0.5 OHM? NP OVERSPEED HARNESS TORQUE SENSOR NO. 2 EEC REPAIR / REPLACE HARNESS (REF. 72−01−10) NO YES CHECK HARNESS. INSULATION RESISTANCE OF PINS P7−A, P7−B, P1−r, P1 −q TO OTHER PINS AND BACKSHELL ON CONNECTORS GREATER THAN 2 MEGOHMS AT 45 VDC? REPAIR / REPLACE HARNESS (REF. 72−01−10) NO YES CHECK TORQUE SENSOR NO. 2. CONTINUITY BETWEEN PINS J7−A AND J7−B TO HAVE A RESISTANCE BETWEEN 557 AND 589 OHMS? REPLACE TORQUE SENSOR NO. 2 (REF. 72−01−60) NO YES CHECK TORQUE SENSOR NO. 2. INSULATION RESISTANCE OF PIN J7−A TO ALL OTHER PINS (EXCEPT J7−B) AND BACKSHELL, AND PIN J7−B TO ALL OTHER PINS (EXCEPT J7−A) AND BACKSHELL GREATER THAN 2 MEGOHMS AT 45 VDC? NO REPLACE TORQUE SENSOR NO. 2 (REF. 72−01−60) YES REPLACE EEC (REF. 72−01−10) NOTE: THIS FAULT IS SET IF NPT EXCEEDS 135% AND FEATHER IS NOT COMMANDED. C68360 EEC Fault Isolation Figure 146 72-00-02 ENGINE - FAULT ISOLATION Page 157 Sep 03/99 PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3045542 LRU FAULT CODE FAILURE 73 TORQUE SENSOR NO. 2 COIL NO. 2 LOW NPT (NP2LIF) SYMPTOMS SUSPECT LRU NO PHYSICAL SYMPTOMS OTHER THAN FAULT CODE INDICATION 1. HARNESS 2. TORQUE SENSOR NO. 2 3. EEC CHECK CONTINUITY OF ENGINE HARNESS. DISCONNECT P1 AND P7 CONNECTORS. RESISTANCE ON LINES 165 AND 166 LESS THAN OR EQUAL TO 0.5 OHM? REPAIR / REPLACE ENGINE HARNESS (REF. 72−01−10) NO YES CHECK INSULATION OF ENGINE HARNESS. RESISTANCE BETWEEN P7−A, P7−B, P1− r, P1− q AND OTHER PINS AND BACKSHELL ON CONNECTORS GREATER THAN OR EQUAL TO 2 MEGOHMS AT 45 VDC? NO REPAIR / REPLACE ENGINE HARNESS (REF. 72−01−10) YES CHECK CONTINUITY OF TORQUE SENSOR NO. 2. PINS J7−A AND J7−B HAVE A RESISTANCE BETWEEN 557 AND 589 OHMS? REPLACE TORQUE SENSOR NO. 2 (REF. 72−01−60) NO YES CHECK TORQUE SENSOR NO. 2. INSULATION RESISTANCE OF PIN J7−A TO ALL OTHER PINS NO (EXCEPT J7−B) AND BACKSHELL, AND PIN J7−B TO ALL OTHER PINS (EXCEPT J7−A) AND BACKSHELL GREATER THAN 2 MEGOHMS AT 45 VDC? REPLACE TORQUE SENSOR NO. 2 (REF. 72−01−60) YES REPLACE EEC (REF. 72−01−10) NOTE: THIS FAULT IS SET IF FOLLOWING ENGINE START, NPT GOES ABOVE 25%, FEATHER IS NOT COMMANDED (CLA OUT OF FEATHER POSITION) AND A SUBSEQUENT NPT VALUE IS LOWER THAN 21%. C68361 EEC Fault Isolation Figure 147 72-00-02 ENGINE - FAULT ISOLATION Page 158 Sep 03/99 PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3045542 FAILURE LRU FAULT CODE 74 TEMPERATURE COMPENSATION TORQUE SENSOR NO. 2 (TQ1F) SYMPTOMS SUSPECT LRU TORQUE INDICATION AND OUTPUT COULD DIFFER BETWEEN LHS AND RHS ENGINE AS A FUNCTION OF ENGINE OIL TEMPERATURE CHECK CONTINUITY OF ENGINE HARNESS. RESISTANCE ON LINES 167, 168 AND 169 LESS THAN OR EQUAL TO 0.5 OHM? 1. HARNESS 2. TORQUE SENSOR NO. 2 3. EEC REPLACE ELECTRICAL HARNESS (REF. 72−01−10) NO YES CHECK HARNESS. INSULATION RESISTANCE OF PINS P1−L, P1 −e, P1 − p, P7−E, P7−F NO AND P7−G TO OTHER PINS ON BACKSHELL AND CONNECTORS GREATER THAN OR EQUAL TO 2 MEGOHMS AT 45 VDC? REPLACE ELECTRICAL HARNESS (REF. 72−01−10) YES CHECK TORQUE SENSOR NO. 2. CONTINUITY OF NO PINS J7−G TO J7−E, AND J7−G TO J7−F, 109 OHMS NOMINAL (REF. 72−01−60). J7−E TO J7−F LESS THAN OR EQUAL TO 1 OHM? REPLACE TORQUE SENSOR NO. 2 (REF. 72−01−60) YES CHECK TORQUE SENSOR NO. 2. INSULATION RESISTANCE OF PINS J7−E, J7−F AND J7−G TO ALL OTHER PINS (EXCEPT TO EACH OTHER) AND BACKSHELL ON CONNECTOR GREATER THAN 2 MEGOHMS AT 45 VDC? REPLACE TORQUE SENSOR NO. 2 (REF. 72−01−60) NO YES REPLACE EEC (REF. 72−01−10) NOTE: WHEN THIS SIGNAL FAILS, THE EEC WILL DEFAULT TO A TORQUE SHAFT TEMPERATURE OF 80.5 ° C (176.6 ° F). THIS FAULT IS SET IF THE TORQUE TEMPERATURE SIGNAL FAILS TO PASS A RANGE CHECK. C68362 EEC Fault Isolation Figure 148 72-00-02 ENGINE - FAULT ISOLATION Page 159 Sep 03/99 PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3045542 LRU FAULT CODE FAILURE 75 DUAL TORQUE CROSS−CHECK (QXIF) SYMPTOMS SUSPECT LRU NO PHYSICAL SYMPTOMS OTHER THAN FAULT CODE INDICATION 1. TORQUE SENSOR NO. 2 2. HARNESS CHECK TORQUE SENSOR NO. 2. RESISTANCE NO BETWEEN PINS J7−A AND J7−B 557−589 OHMS AND BETWEEN PINS J7−C AND J7−D 612−664 OHMS? REPLACE TORQUE SENSOR NO. 2 (REF. 72−01−60) YES CHECK TORQUE SENSOR NO. 2. INSULATION RESISTANCE OF PIN J7−A AND J7−B TO ALL OTHER PINS (EXCEPT TO EACH OTHER) AND BACKSHELL, AND OF PINS J7−C AND J7−D TO ALL OTHER PINS (EXCEPT TO EACH OTHER) AND BACKSHELL ON CONNECTOR GREATER THAN 2 MEGOHMS AT 45 VDC? NO REPLACE TORQUE SENSOR NO. 2 (REF. 72−01−60) YES CHECK HARNESS. IS CONTINUITY ON LINES 165, 166, 170 AND 171 LESS THAN 0.5 OHM? REPAIR / REPLACE HARNESS (REF. 72−01−10) NO YES CHECK HARNESS. INSULATION RESISTANCE OF PINS P7−A, P7−B, P7−C, P7−D, P1− r, P1− q , P1−P AND P1−R TO OTHER PINS AND BACKSHELL ON CONNECTOR GREATER THAN 2 MEGOHMS AT 45 VDC? NO REPAIR / REPLACE HARNESS (REF. 72−01−10) YES SYSTEM NORMAL NOTE: THIS FAULT IS SET IF NPT IS ABOVE 30%, FEATHER IS NOT COMMANDED, NO FAULTS ARE SET FOR ANY COILS AND THE DIFFERENCE BETWEEN THE TWO TORQUE COIL READINGS EXCEEDS 5%. C68363 EEC Fault Isolation Figure 149 72-00-02 ENGINE - FAULT ISOLATION Page 160 Sep 03/99 PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3045542 FAILURE LRU FAULT CODE 76 DUAL NP CROSS−CHECK TORQUE SENSOR NO. 2 (NPXIF) SYMPTOMS SUSPECT LRU NO PHYSICAL SYMPTOMS OTHER THAN FAULT CODE INDICATION 1. TORQUE SENSOR NO. 2 2. HARNESS PROCEED WITH CHECK AS PER LRU FAULT CODE 75 NOTE: THIS FAULT IS SET IF NPT IS ABOVE 30%, FEATHER IS NOT COMMANDED, NO FAULT CODES FOR THE COILS ARE SET AND THE DIFFERENCE BETWEEN THE TWO NPT COIL READINGS EXCEEDS 5%. C26393 EEC Fault Isolation Figure 150 72-00-02 ENGINE - FAULT ISOLATION Page 161 Sep 03/99 PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3045542 FAILURE LRU FAULT CODE 78 INLET TEMPERATURE (T18IF) SYMPTOMS SUSPECT LRU ARINC "EEC" TI.8 (211) = 0 ° 1. T1.8 SENSOR 2. HARNESS 3. EEC REPLACE ELECTRICAL HARNESS (REF. 72−01−10) CHECK HARNESS CONTINUITY. LINES 160, 161 NO AND 162 LESS THAN OR EQUAL TO 0.5 OHM? YES CHECK HARNESS. INSULATION RESISTANCE OF PINS P1−K, P1−J, P1−d, P4−3, P4−2 AND NO P4−1 TO OTHER PINS AND BACKSHELL ON CONNECTOR GREATER THAN OR EQUAL TO 2 MEGOHMS AT 45 VDC? REPLACE ELECTRICAL HARNESS (REF. 72−01−10) YES CHECK T1.8 SENSOR. CONTINUITY ON LINES J4−3 TO J4−2 AND J4−3 TO J4−1 108 OHMS NOMINAL (REF. 72−01−60)? J4−2 TO J4−1 LESS THAN OR EQUAL TO 1 OHM? REPLACE T1.8 SENSOR (REF. 72−01−60) NO YES CHECK T1.8 SENSOR. INSULATION RESISTANCE NO OF PINS J4 TO PROBE BODY GREATER THAN OR EQUAL TO 2 MEGOHMS AT 45 VDC? REPLACE T1.8 SENSOR (REF. 72−01−60) YES REPLACE EEC (REF. 72−01−10) NOTE: THIS FAULT IS SET IF THE INLET TEMPERATURE SENSOR LOCATED ON THE REAR INLET CASE DOES NOT PASS A RANGE CHECK WHEN NH IS ABOVE 66% (I.E. THE ENGINE RUNNING). C68364 EEC Fault Isolation Figure 151 72-00-02 ENGINE - FAULT ISOLATION Page 162 Sep 03/99 PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3045542 LRU FAULT CODE FAILURE 80 NH NO. 1 SENSOR HIGH RANGE (NH1IF) SYMPTOMS SUSPECT LRU NO PHYSICAL SYMPTOMS OTHER THAN FAULT CODE INDICATION 1. 2. 3. 4. NH EXCEEDS 110% AND FAULT CODES LRU 12 AND 81 EXIST? TAKE APPROPRIATE ACTION FOR NH OVERSPEED (REF. 05−50−00) YES NO CHECK HARNESS CONTINUITY. RESISTANCE ON LINES 163 AND 164 LESS THAN OR EQUAL TO 0.5 OHM? NH OVERSPEED HARNESS NH SENSOR NO. 1 EEC NO REPAIR / REPLACE ENGINE HARNESS (REF. 72−01−10) NO REPAIR / REPLACE ENGINE HARNESS (REF. 72−01−10) NO REPLACE NH SENSOR NO. 1 (REF. 72−01−60) YES CHECK ENGINE HARNESS. INSULATION RESISTANCE OF PINS P14−3, P14−4, P1−Z P1−E TO OTHER PINS AND BACKSHELL ON CONNECTORS GREATER THAN OR EQUAL TO 2 MEGOHMS AT 45 VDC? YES CONTINUITY OF NH SENSOR NO. 1, PINS J5−3 TO J14−4, 36 TO 45 OHMS (COIL RESISTANCE)? YES REPLACE EEC (REF. 72−01−10) NOTE: THIS FAULT IS AUTOMATICALLY SET IF NH EXCEEDS 110%. C68365 EEC Fault Isolation Figure 152 72-00-02 ENGINE - FAULT ISOLATION Page 163 Sep 03/99 PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3045542 LRU FAULT CODE FAILURE 81 NH NO. 2 SENSOR HIGH RANGE (NH2IF) SYMPTOMS SUSPECT LRU NO PHYSICAL SYMPTOMS OTHER THAN FAULT CODE INDICATION 1. 2. 3. 4. NH EXCEEDS 110% AND FAULT CODES LRU 12 AND 80 EXIST? NH OVERSPEED HARNESS NH SENSOR NO. 2 EEC TAKE APPROPRIATE ACTION FOR NH OVERSPEED (REF. 05−50−00) YES NO CHECK HARNESS CONTINUITY. RESISTANCE ON LINES 184 AND 185 LESS THAN OR EQUAL TO 0.5 OHM? NO REPAIR / REPLACE ENGINE HARNESS (REF. 72−01−10) NO REPAIR / REPLACE ENGINE HARNESS (REF. 72−01−10) YES CHECK ENGINE HARNESS. INSULATION RESISTANCE OF PINS P5−3, P5−4, P1−D, P1−Y TO OTHER PINS AND BACKSHELL ON CONNECTORS GREATER THAN OR EQUAL TO 2 MEGOHMS AT 45 VDC? YES REPLACE NH SENSOR NO. 2 (REF. 72−01−60) CONTINUITY OF NH SENSOR NO. 2, PINS J5−3 NO TO J5−4, 36 TO 45 OHMS (COIL RESISTANCE)? YES CHECK NH SENSOR NO. 2. INSULATION RESISTANCE OF PINS J5−3 AND J5−4 TO OTHER PINS (EXCEPT TO EACH OTHER) AND BACKSHELL ON CONNECTOR GREATER THAN 2 MEGOHMS AT 45 VDC? REPLACE NH SENSOR NO. 2 (REF. 72−01−60) NO YES REPLACE EEC (REF. 72−01−10) C68366 EEC Fault Isolation Figure 153 72-00-02 ENGINE - FAULT ISOLATION Page 164 Sep 03/99 PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3045542 LRU FAULT CODE FAILURE 82 NH NO. 1 SENSOR LOW RANGE (NHECS1) SYMPTOMS SUSPECT LRU NO PHYSICAL SYMPTOMS OTHER THAN FAULT CODE INDICATION 1. 2. 3. 4. WAS ENGINE SHUT DOWN BY INTERRUPTING FUEL SUPPLY WITH CONDITION LEVER IN UNFEATHERED POSITION? FAULT CODES LRU 12 AND 83 EXIST? YES IMPROPER ENGINE SHUTDOWN HARNESS NH SENSOR NO. 1 EEC SYSTEM NORMAL NO CHECK HARNESS CONTINUITY. RESISTANCE ON LINES 163 AND 164 LESS THAN OR EQUAL TO 0.5 OHM? NO REPAIR / REPLACE ENGINE HARNESS (REF. 72−01−10) NO REPAIR / REPLACE ENGINE HARNESS (REF. 72−01−10) YES CHECK ENGINE HARNESS. INSULATION RESISTANCE OF PINS P14−3, P14−4, P1−Z, P1−E AND OTHER PINS AND BACKSHELL ON CONNECTORS GREATER THAN OR EQUAL TO 2 MEGOHMS AT 45 VDC? YES CONTINUITY OF NH SENSOR NO. 1, PINS J14−3 TO J14−4, 36 TO 45 OHMS (COIL RESISTANCE)? REPLACE NH SENSOR NO. 1 (REF. 72−01−60) NO YES REPLACE EEC (REF. 72−01−10) NOTE: THIS FAULT WILL BE SET ONCE A LOW RANGE FAILURE IS DETECTED (NH<30%), NPT IS ABOVE 30% AND FEATHER IS NOT COMMANDED. C68367 EEC Fault Isolation Figure 154 72-00-02 ENGINE - FAULT ISOLATION Page 165 Sep 03/99 PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3045542 FAILURE LRU FAULT CODE 83 NH NO. 2 SENSOR LOW RANGE (NHECS2) SYMPTOMS SUSPECT LRU 1. 2. 3. 4. NO PHYSICAL SYMPTOMS OTHER THAN FAULT CODE INDICATION WAS ENGINE SHUT DOWN BY INTERRUPTING FUEL YES SUPPLY WITH CONDITION LEVER IN UNFEATHERED POSITION? DO FAULT CODES LRU 12 AND 82 EXIST? IMPROPER ENGINE SHUTDOWN HARNESS NH SENSOR NO. 2 EEC SYSTEM NORMAL NO CHECK HARNESS CONTINUITY. RESISTANCE ON LINES 184 AND 185 LESS THAN OR EQUAL TO 0.5 OHM? NO REPAIR / REPLACE ENGINE HARNESS (REF. 72−01−10) YES CHECK ENGINE HARNESS. INSULATION RESISTANCE BETWEEN PINS P5−3, P5−4, P1−D, P1−Y AND OTHER PINS AND BACKSHELL ON CONNECTORS GREATER THAN OR EQUAL TO 2 MEGOHMS AT 45 VDC? NO REPAIR / REPLACE ENGINE HARNESS (REF. 72−01−10) YES REPLACE NH SENSOR NO. 2 (REF. 72−01−60) NO CONTINUITY OF NH SENSOR NO. 2, J5−3 TO J5−4, 36 TO 45 OHMS (COIL RESISTANCE)? YES CHECK NH SENSOR NO. 2. INSULATION RESISTANCE OF PINS J5−3 AND J5−4 TO OTHER PINS (EXCEPT TO EACH OTHER) AND BACKSHELL ON CONNECTOR GREATER THAN 2 MEGOHMS AT 45 VDC? NO REPLACE NH SENSOR NO. 2 (REF. 72−01−60) YES REPLACE EEC (REF. 72−01−10) NOTE: THIS FAULT WILL BE SET ONCE A LOW RANGE FAILURE IS DETECTED (NH <30%), NPT IS ABOVE 30% AND FEATHER IS NOT COMMANDED. C68368 EEC Fault Isolation Figure 155 72-00-02 ENGINE - FAULT ISOLATION Page 166 Sep 03/99 PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3045542 LRU FAULT CODE FAILURE 84 DUAL NH CROSS−CHECK (NHXIF) SYMPTOMS SUSPECT LRU NO PHYSICAL SYMPTOMS OTHER THAN FAULT CODE INDICATION 1. HARNESS 2. NH SENSORS REPAIR / REPLACE HARNESS (REF. 72−01−60) CHECK HARNESS. CONTINUITY ON LINES 163, NO 164, 184 AND 185 LESS THAN 0.5 OHM? YES CHECK HARNESS. INSULATION RESISTANCE OF PINS P14−3, P14−4, P5−3, P5−4, P1−Z, P1−E, P1−D AND P1−Y TO OTHER PINS AND BACKSHELL ON CONNECTORS GREATER THAN 2 MEGOHMS AT 45 VDC? NO REPAIR / REPLACE HARNESS (REF. 72−01−60) YES CHECK NH SENSORS. RESISTANCE BETWEEN PINS J14−3 AND J4−4 FOR SENSOR NO. 1 AND J5−3 AND J5−4 FOR SENSOR NO. 2 BETWEEN 36 AND 45 OHMS? REPLACE NH SENSOR NO. 1 AND / OR SENSOR NO. 2 (REF. 72−01−60) NO YES CHECK NH SENSOR NO. 2. INSULATION RESISTANCE OF PINS J5−3 AND J5−4 TO OTHER PINS (EXCEPT TO EACH OTHER) AND BACKSHELL ON CONNECTOR GREATER THAN 2 MEGOHMS AT 45 VDC? NO REPLACE NH SENSOR NO. 2 (REF. 72−01−60) YES SYSTEM NORMAL NOTE: THIS FAULT IS SET IF NPT IS ABOVE 30%, FEATHER IS NOT COMMANDED, NO PREVIOUS FAULT CODES ARE SET FOR ANY OF THE NH PROBES AND THE DIFFERENCE BETWEEN THE TWO READINGS EXCEEDS 0.9%. C68369 EEC Fault Isolation Figure 156 72-00-02 ENGINE - FAULT ISOLATION Page 167 Sep 03/99 PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3045542 LRU FAULT CODE FAILURE 85 FAIL FIXED WRAPAROUND (HSS1IF) SYMPTOMS SUSPECT LRU 1. EEC FAULT LAMP ON (FAIL FIX) WHEN EEC IS NOT FAILED 1. AIRCRAFT WIRING AND RELAY 2. ENGINE HARNESS 3. MFCU 4. EEC 2. EEC FAULT LAMP OFF WHEN EEC IS FAILED CHECK CONTINUITY OF AIRCRAFT FAIL FIXED RELAY. DISCONNECT P11. RESISTANCE BETWEEN PINS P11−AA AND P11− b EQUAL TO VALUE GIVEN IN AMM? NO REPAIR /REPLACE AIRCRAFT WIRING / RELAY (REF. AMM) YES NO REPAIR /REPLACE AIRCRAFT WIRING / RELAY (REF. AMM) NO REPAIR / REPLACE ENGINE HARNESS (REF. 72−01−10) APPLY 28 VDC TO PINS P11−AA (+) AND P11− b (−). MANUAL LAMP OFF? YES CHECK ENGINE HARNESS. CONTINUITY ON LINES 131 AND 132 LESS THAN OR EQUAL TO 0.5 OHM? YES CHECK ENGINE HARNESS. INSULATION RESISTANCE OF PINS J11−AA, J11− b, P2− c AND P2−H TO ALL OTHER PINS AND BACKSHELL ON CONNECTORS GREATER THAN OR EQUAL TO 2 MEGOHMS AT 45 VDC? NO REPAIR / REPLACE ENGINE HARNESS (REF. 72−01−10) YES FAULT CODE LRU 92 ALSO SET (FOR STEPPER MOTOR IN MFCU)? YES CARRY OUT CHECK AS PER LRU FAULT CODE 92 NO REPLACE EEC (REF. 72−01−10) NOTE: THE VOLTAGE SUPPLIED BY THE EEC TO THE FAIL FIXED RELAY AND THE MFCU STEPPER MOTOR COMES FROM THE SAME DRIVER. THEREFORE, A SHORT CIRCUIT TO GROUND ON ANY ONE OF THESE CIRCUITS WILL RESULT IN FAULT CODE LRU 85 BEING SET. C68370 EEC Fault Isolation Figure 157 72-00-02 ENGINE - FAULT ISOLATION Page 168 Sep 03/99 PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3045542 LRU FAULT CODE FAILURE 86 AUTO−IGNITION WRAPAROUND (LSS5IF) SYMPTOMS SUSPECT LRU AUTO−IGNITION MAY NOT BE COMMANDED IF REQUIRED 1. AIRCRAFT WIRING AND RELAY 2. ENGINE HARNESS 3. EEC CHECK CONTINUITY OF AIRCRAFT AUTO−IGNITION RELAY. DISCONNECT PIN P11. RESISTANCE BETWEEN PIN P11−B AND 28 VDC EQUAL TO VALUE GIVEN IN AMM? NO REPAIR /REPLACE AIRCRAFT WIRING / RELAY (REF. AMM) YES REPAIR /REPLACE AIRCRAFT WIRING / RELAY (REF. AMM) APPLY GROUND TO PIN P11−B (−). IGNITION NO COMES ON (ASSUMING GOOD IGNITERS)? YES CHECK ENGINE HARNESS. CONTINUITY OF LINE 136 LESS THAN 0.5 OHM? REPAIR / REPLACE ENGINE HARNESS (REF. 72−01−10) NO YES CHECK ENGINE HARNESS. INSULATION RESISTANCE OF PINS J11−B AND P1−C TO ALL OTHER PINS AND BACKSHELL ON CONNECTORS GREATER THAN 2 MEGOHMS AT 45 VDC? NO REPAIR / REPLACE ENGINE HARNESS (REF. 72−01−10) YES REPLACE EEC (REF. 72−01−10) NOTE: THIS FAULT IS SET IF EITHER THE AIRCRAFT / ENGINE SYSTEM IS NOT OPERATIONAL OR THE EEC IS DAMAGED INTERNALLY. C68371 EEC Fault Isolation Figure 158 72-00-02 ENGINE - FAULT ISOLATION Page 169 Sep 03/99 PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3045542 FAILURE LRU FAULT CODE 87 INTERCOMPRESSOR BLEED WRAPAROUND FAULT (HSS2IF) SYMPTOMS SUSPECT LRU ENGINE SURGE MAY OCCUR AT ALTITUDE DURING RAPID PLA MANOEUVER. 1. ENGINE HARNESS 2. INTERCOMPRESSOR BLEED VALVE TORQUE MOTOR 3. EEC FOLLOW CHECK AS PER LRU FAULT CODE 39 C26402A EEC Fault Isolation Figure 159 72-00-02 ENGINE - FAULT ISOLATION Page 170 Sep 03/99 PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 3045542 FAILURE LRU FAULT CODE 89 PLA PHASE 1 (PLA1IF) SYMPTOMS SUSPECT LRU EEC FAULT LAMP ON (FAIL FIX) INTERCOMPRESSOR BLEED VALVE CONTROL DEGRADED NO NPT GOVERNING ARINC "TRIMMED" PLA (135) = 0 DEGREE ARINC "RAW" PLA (134) = 0 DEGREE ARINC "COMMANDED TORQUE" (341) = 0% CHECK HARNESS. CONTINUITY ON LINES 179, 180, 181 AND 182 LESS THAN OR EQUAL TO 0.5 OHM? 1. HARNESS 2. MFCU 3. EEC NO REPLACE ELECTRICAL HARNESS (REF. 72−01−10) YES CHECK HARNESS. INSULATION RESISTANCE OF PINS P8−A, P8−B, P8−P, P8−C, P1−F, P1− a, P1−b NO AND P1− c TO OTHER PINS AND BACKSHELL ON CONNECTORS GREATER THAN 2 MEGOHMS AT 45 VDC? REPLACE ELECTRICAL HARNESS (REF. 72−01−10) YES CHECK MFCU RVDT. CONTINUITY BETWEEN PINS J8−A AND J8−B 45 TO 85 OHMS, BETWEEN PINS J8−P AND J8−C 70 TO 150 OHMS AND BETWEEN PINS J8−R NO AND J8−C TO 76 TO 114 OHM? REPLACE MFCU (REF. 72−01−40) YES CHECK MFCU RVDT. INSULATION RESISTANCE OF PINS J8−A AND J8−B TO OTHER PINS (EXCEPT TO EACH OTHER) NO AND BACKSHELL, AND PINS J8−P AND J8−C TO OTHER PINS (EXCEPT TO EACH OTHER) AND BACKSHELL ON CONNECTOR GREATER THAN 2 MEGOHMS AT 45 VDC? REPLACE MFCU (REF. 72−01−40) YES REPLACE EEC (REF. 72−01−10) NOTE: THIS FAULT IS SET IF THE PLA NO. 2 SIGNAL FROM THE MFCU RVDT FAILS A RANGE CHECK. C68372 EEC Fault Isolation Figure 160 72-00-02 ENGINE - FAULT ISOLATION Page 171 Sep 03/99 P8−C. P8−R. HARNESS 2. P8−B/P1− a.FAULT ISOLATION Page 172 Sep 03/99 . AND PINS J8−R AND J8−C TO ALL OTHER PINS (EXCEPT TO EACH OTHER AND P) AND BACKSHELL ON CONNECTOR GREATER THAN 2 MEGOHMS AT 45 VDC? NO REPLACE MFCU (REF. 72−01−10) NOTE: THIS FAULT IS SET IF THE PLA NO. 72−01−40) YES REPLACE EEC (REF. CONTINUITY ON LINES P8−A / P1−F. 3045542 FAILURE LRU FAULT CODE 90 PLA PHASE 2 (PLA2IF) SYMPTOMS SUSPECT LRU EEC FAULT LAMP ON (FAIL FIX) INTERCOMPRESSOR BLEED VALVE CONTROL DEGRADED NO NPT GOVERNING ARINC "TRIMMED" PLA (133) = 0 DEGREE ARINC "RAW" PLA (134) = 0 DEGREE ARINC "COMMANDED TORQUE" (341) = 0% CHECK HARNESS. C26404 EEC Fault Isolation Figure 161 72-00-02 ENGINE . 2 SIGNAL FROM THE MFCU RVDT FAILS A RANGE CHECK. P1− a. CONTINUITY BETWEEN PINS J8−A NO AND J8−B FROM 45 TO 85 OHMS AND BETWEEN PINS J8−R AND J8−C FROM 76 TO 114 OHMS? REPLACE MFCU (REF. INSULATION RESISTANCE OF PINS P8−A. P1−F. P8−R/P1−G AND P8−C/P1− c LESS THAN OR EQUAL TO 0. P1−G NO AND P1− c TO OTHER PINS AND BACKSHELL ON CONNECTORS GREATER THAN OR EQUAL TO 2 MEGOHMS AT 45 VDC? REPLACE ELECTRICAL HARNESS YES CHECK MFCU RVDT. MFCU 3. 72−01−40) YES CHECK MFCU RVDT. P8−B.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. INSULATION RESISTANCE OF PINS J8−A AND J8−B TO ALL OTHER PINS (EXCEPT TO EACH OTHER) AND BACKSHELL. EEC NO REPLACE ELECTRICAL HARNESS YES CHECK HARNESS.5 OHM? 1. MFCU 3.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. C26405 EEC Fault Isolation Figure 162 72-00-02 ENGINE . 3045542 LRU FAULT CODE FAILURE 91 PLA TOTAL (PLAIF) SYMPTOMS SUSPECT LRU EEC FAULT LAMP ON (FAIL FIX) INTERCOMPRESSOR BLEED VALVE CONTROL DEGRADED NO NPT GOVERNING ARINC "TRIMMED" PLA (135) = 0 DEGREE ARINC "RAW" PLA (134) = 0 DEGREE ARINC "COMMANDED TORQUE" (341) = 0% ONLY FAULT CODE LRU 89 ALSO SET? 1. EEC YES CARRY OUT CHECK AS PER LRU FAULT CODE 89 YES CARRY OUT CHECK AS PER LRU FAULT CODE 90 NO ONLY FAULT CODE LRU 90 ALSO SET? NO BOTH FAULT CODES LRU 89 AND 90 ALSO SET? CARRY OUT CHECK AS PER LRU FAULT CODE 89 AND 90 TAKING CARE NOT TO REPEAT THE SAME TESTS YES NO REPLACE EEC (REF. 72−01−10) NOTE: THIS FAULT IS SET IF THE PLA FAILS A RANGE CHECK. HARNESS 2.FAULT ISOLATION Page 173 Sep 03/99 . 3045542 FAILURE LRU FAULT CODE 92 STEPPER MOTOR PHASE FAULT (SMCFIF) SYMPTOMS SUSPECT LRU EEC FAULT LAMP ON (FAIL FIX) 1. P1− n AND P1− k TO OTHER PINS AND BACKSHELL ON CONNECTORS GREATER THAN 2 MEGOHMS? YES CHECK MFCU STEPPER MOTOR. 72−01−10) NO REPAIR / REPLACE HARNESS (REF. 72−01−40) YES CHECK MFCU STEPPER MOTOR. INSULATION RESISTANCE OF PINS J8−G. 72−01−10) YES CHECK HARNESS. J8−G AND J8−T AND J8−G AND J8−H BETWEEN 115 AND 155 OHMS? NO REPLACE MFCU (REF. P8−S. P1−U AND P1−j. INSULATION RESISTANCE OF PINS J8−F.5 OHM? NO REPAIR / REPLACE HARNESS (REF. 72−01−10) C68373 EEC Fault Isolation Figure 163 72-00-02 ENGINE .FAULT ISOLATION Page 174 Sep 03/99 . J8−H. J8−G. P1−X. CONTINUITY ON LINES 174. 175. 72−01−40) YES REPLACE EEC (REF. J8−S AND J8−T TO ALL OTHER PINS (EXCEPT TO EACH OTHER) AND BACKSHELL ON CONNECTOR GREATER THAN 2 MEGOHMS AT 45 VDC? NO REPLACE MFCU (REF. MFCU STEPPER MOTOR 3.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. HARNESS 2. J8−G AND J8−S. 177 AND 178 LESS THAN 0. P8−F. P8−H. 176. CONTINUITY BETWEEN PINS J8−G AND J8−F. EEC CHECK HARNESS. P8−T. HARNESS 2.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. PINS U TO j. EEC YES TROUBLESHOOT AS PER LRU FAULT CODE 92 NO ARE ANY OTHER FAULT CODES ALSO SET? YES NOTE CODES FOR APPROPRIATE TROUBLESHOOTING LATER NO POWER PU EEC / CLEAR FAULT CODES AND SHAKE P1 CONNECTOR YES IS FAULT CODE 93 SET? NO REPLACE HARNESS NO CHECK HARNESS AND MFCU CONTINUITY. U TO X. U TO n AND U TO k TO BE BETWEEN 115 AND 165 OHMS (EVEN WHEN SHAKING P1) CONTINUED ON SHEET 2 "B" CONTINUED ON SHEET 2 "A" C26407 EEC Fault Isolation Figure 164 (Sheet 1 of 2) 72-00-02 ENGINE . MFCU STEPPER MOTOR 3.FAULT ISOLATION Page 175 Sep 03/99 . 3045542 FAILURE LRU FAULT CODE 93 STEPPER MOTOR INTERMITTENT PHASE FAULT (SMINTF) SYMPTOMS SUSPECT LRU POSSIBLE RANDOM POWER OSCILLATIONS IS LRU FAULT CODE 92 ALSO SET? 1. FAULT ISOLATION Page 176 Sep 03/99 . CONNECT BOTH CONNECTORS BACK AND TORQUE THEM TO THE SPECIFIED TORQUE LEVELS C68374 EEC Fault Isolation Figure 164 (Sheet 2) 72-00-02 ENGINE . 72−01−10). 176. RECONNECT AND TORQUE CONNECTOR SHAKE P8 CONNECTOR YES IS FAULT CODE 93 SET? NO REPLACE HARNESS DISCONNECT P1 AND P8. j. 72−01−10). 177 AND 178 FOR CONTINUITY SHAKING P8 CONNECTOR NO YES REPLACE MFCU CHECK CONTINUITY AND RESISTANCE BETWEEN THE MFCU PINS G TO F. TEST HARNESS LINES 174. G TO T AND G TO H BETWEEN 115 AND 155 OHM WHILE GENTLY TAPPING THE SIDE OF THE MFCU CONNECTOR. X.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. G TO S. n AND k DIRTY CLEAN CONNECTOR PER MAINTENANCE PROCEDURE (REF. RECONNECT AND TORQUE CONNECTOR CLEAN P1 AND P8 CONNECTOR PER MAINTENANCE PROCEDURE (REF. 72−01−10). 3045542 CONTINUED FROM SHEET 1 "A" CONTINUED FROM SHEET 1 "B" REPLACE EEC CLEAN CHECK FOR CONTAMINATION OF PINS U. 175. NO YES CLEAN CONNECTOR PER MAINTENANCE PROCEDURE (REF. AND J11−w TO ALL OTHER PINS AND SHELL J11. 3045542 FAILURE UPTRIM LAMP WRAPAROUND (LSS4IF) SYMPTOMS SUSPECT LRU 1. UPTRIM LAMP OFF WHEN OPPOSITE ENGINE HAS AUTOFEATHERED UPTRIM LAMP RELAY OK (REF.5 OHM? YES INSULATION RESISTANCE OF PIN P2−N TO ALL OTHER PINS AND SHELL P−2. AMM) NO REPLACE WIRING HARNESS (REF. WIRING HARNESS 3. UPTRIM LAMP RELAY 2. 72−01−10) YES REPLACE EEC (REF. 72−01−10) YES CONTINUITY ON LINE 135 LESS THAN OR EQUAL TO 0. AMM)? NO REPAIR / REPLACE (REF. UPTRIM LAMP ON AT ALL TIMES 1. GREATER THAN OR EQUAL TO 2 MEGOHMS AT 45 VDC? NO REPLACE WIRING HARNESS (REF.FAULT ISOLATION Page 177 Sep 03/99 . 72−01−10) NOTE: THIS FAULT IS SET IF THE UPTRIM LAMP DRIVER SYSTEM IS FOUND TO BE INCORRECT.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. C68375 EEC Fault Isolation Figure 165 72-00-02 ENGINE . EEC 2. CHARACTERIZATION PLUG 2. 72−01−10) OK? YES SYSTEM NORMAL NO REPLACE EEC (REF.FAULT ISOLATION Page 178 Sep 03/99 . EEC REPLACE CHARACTERIZATION PLUG (REF. 3045542 FAILURE LRU FAULT CODE INCORRECT EEC CONFIGURATION INSTALLED LAB SYMPTOMS SUSPECT LRU EEC FAULT LAMP ON (FAIL FIX) 1. 72−01−10) OK? YES SYSTEM NORMAL C37697 EEC Fault Isolation Figure 166 72-00-02 ENGINE .PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. FAULT ISOLATION Page 179 Sep 03/99 . SELECT MANUAL MODE. TORQUE BUG MAY OR MAY NOT BE ACHIEVED BY ADJUSTING PLA. OVERSPEED GOVERNOR 3. ADJUST NO PLA TO TAKE−OFF OR FULL POWER LEVER TRAVEL. TORQUE INDICATED WILL NOT MATCH TORQUE BUG. 1. MFCU 2. 72−01−40) C26410 Throttle Stagger Figure 167 72-00-02 ENGINE . IN EEC MODE.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. REFERENCE PRESSURE LEAK − UNABLE TO ACHIEVE TAKE−OFF POWER) YES REPLACE MFCU (REF. PY AIR TUBE SET PLA AT FLIGHT IDLE. 72−00−01. IS POWER SELECTION ATTAINABLE? CHECK FOR REFERENCE PRESSURE LEAK (REF. 3045542 SYMPTOMS SUSPECT LRU AT TAKE−OFF PLA. 3045542 FAILURE DUAL AIRSPEED INPUT FAULT (IASIF) SYMPTOMS SUSPECT LRU POSSIBLE TORQUE SPLIT POSSIBLE DEGRADE ENGINE AND PROPELLER PERFORMANCE SYMPTOMS AFTER BOTH LRU = 54 OR LRU = 19 ARE SET 1.FAULT ISOLATION Page 180 Sep 03/99 . WIRING LRU 54 RECTIFY AS PER LRU FAULT CODE 54 LRU 19 REPLACE EEC (REF.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 72−01−10) NOTE: THIS FAULT IS SET WHEN BOTH ARINC AIRSPEED INPUT FAULT (LRU = 54) AND DELTA P SENSOR FAULT (LRU = 17) ARE SET. EEC AND 2. ADC 3. C26439 Dual Airspeed Input Fault Figure 168 72-00-02 ENGINE . HOLDING TRIM SWITCH ON.FAULT ISOLATION Page 181 Sep 03/99 . 72−01−10) YES NO REPAIR / REPLACE AIRCRAFT WIRING (REF.5 OHM? YES 1. DISCONNECT P11.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. TURN EEC POWER OFF. P2−v. CONTINUITY P11−g TO P11−MM LESS THAN OR EQUAL TO 0. INSULATION RESISTANCE OF PINS P2−X. 72−01−10) C68376 Unable to Trim Actual Power to Torque Bug Figure 169 72-00-02 ENGINE . CONTINUITY ON LINES 127 AND 129 OK? NO REPLACE WIRING HARNESS (REF. 3045542 SYMPTOMS SUSPECT LRU ACTUAL OUTPUT TORQUE AT TAKE−OFF DOES NOT MATCH BUG WITH MATCHED PLAs. J11 −g AND AND J11−MM TO ALL OTHER PINS AND BACKSHELL ON CONNECTORS GREATER THAN OR EQUAL TO 2 MEGOHMS AT 45 VDC? NO REPAIR / REPLACE HARNESS (REF. AMM) CHECK ENGINE HARNESS. SHUT DOWN ENGINE(S). WIRING HARNESS 2. AIRCRAFT WIRING CHECK WIRING HARNESS. IBV NO EEC FAULT CODES FAILURE OF INTERCOMPRESSOR BLEED VALVE (IBV) TO OPEN AT CORRECT TIME WILL RESULT IN VERY NOISY ENGINE OR SURGING DURING ACCELERATION IBV ORIFICE AND FILTER CHECK OK? (REF.FAULT ISOLATION Page 182 Sep 03/99 . 72−01−30) CLEAN ORIFICE AND FILTER (REF.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 72−01−30) NO YES REPLACE IBV (REF. IBV ORIFICE AND FILTER 2. 3045542 SYMPTOMS SUSPECT LRU 1. 72−01−30) C26412 Noisy Engine/Surges at Intermediate Power Figure 170 72-00-02 ENGINE . 5 OHM? REPLACE HARNESS (REF 72−01−10) YES AIRCRAFT SYSTEM OK? (REF. 32 TO 55 OHMS. AIRCRAFT SYSTEM MFCU REVERSION SYSTEM FAULT NO CHECK MFCU FOR DAMAGED PINS OK? REPLACE MFCU (REF. OK? NO REPLACE MFCU (REF. AMM) NO RECTIFY YES SYSTEM NORMAL C68377 Instability or Engine Runaway Figure 171 72-00-02 ENGINE . 72−01−40) YES CHECK MFCU SOLENOID PINS M TO N. MFCU 2.FAULT ISOLATION Page 183 Sep 03/99 . WIRING HARNESS 3.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 72−01−40) YES CONTINUITY LINES 139 NO AND 140 LESS THAN OR EQUAL TO 0. 3045542 SYMPTOMS SUSPECT LRU 1. 1. PRESS AUTOFEATHER TEST SWITCHES NO. 72−01−10) DOES ARMED LAMP ILLUMINATE? YES SYSTEM NORMAL YES SYSTEM NORMAL NO REINSTALL AFU NO. 3045542 SYMPTOMS SUSPECT LRU 1. 2. AFU ENGINE HARNESS AIRCRAFT WIRING TORQUE SENSOR NO. 72−01−10) DOES ARMED LAMP ILLUMINATE? NO CONTINUED ON SHEET 2 C26414 Autofeather System Faults Figure 172 (Sheet 1 of 5) 72-00-02 ENGINE . (REF. 2. DOES ARMED LAMP ILLUMINATE? YES SYSTEM NORMAL NO CHANGE AFU ON ENGINE NO. WHEN TEST SWITCH IS RELEASED. ARMED LAMP DOES NOT ILLUMINATE. 1. WHEN AUTOFEATHER TEST IS SELECTED. 1. SELECT ATO RATING. OPPOSITE ENGINE UPTRIM LAMP DOES NOT ILLUMINATE. 4.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. WHEN TEST SWITCHES 1 AND 2 ARE ON. (REF. 1 AND 2 ON. CHANGE AFU ON ENGINE NO. 2.FAULT ISOLATION Page 184 Sep 03/99 . 3. ANALOG NEEDLE OF TORQUE INDICATED DOES NOT INDICATE 60% TORQUE. 1 3. 1 AND 2 C26341 Autofeather System Faults Figure 172 (Sheet 2) 72-00-02 ENGINE . 2 (REF. 1. 3045542 CONT’D FROM SHEET 1 REINSTALL AFU NO. 1.FAULT ISOLATION Page 185 Sep 03/99 . 2. 1 AND 2. TURN TEST SWITCH NO. AMM) NO YES CHECK AIRCRAFT WIRING CONTINUITY ON BOTH ENGINES NO. 2. 1 AND 2 ON. P16−S OK ? REPAIR/ REPLACE AIRCRAFT WIRING (REF. CONNECTION BETWEEN AFU NO. P16−K AND P6−C. DISCONNECT P16 AND P6 ON AFU NO. 1 AND 2 TO TORQUE SENSOR NO. CONTINUITY BETWEEN P16−L AND P6−D. P16−J AND P6−B. P16−R TO AFU NO. P16− a AND P16−P TO BOTH AFU S ? REPAIR/ REPLACE AIRCRAFT WIRING (REF. AMM) NO YES CHECK AIRCRAFT WIRING FOR HIGH TORQUE SIGNAL. P16−S TO AFU NO. 1. 72−01−10). P16−R AND AFU NO. P16−H AND P6−A LESS THAN OR EQUAL TO 0.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. REINSTALL P16 AND P6 TO AIRCRAFT WIRING ON AFU NO.5 OHMS ? REPAIR/ REPLACE AIRCRAFT WIRING (REF. ARE THERE 28 VDC ON P16−N. AMM) NO YES CHECK AIRCRAFT WIRING FROM BOTH AFUS (P16−A). P16−J TO P6−B AND P16−H TO P6−A LESS THAN OR EQUAL TO 0.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. DO BOTH TORQUE INDICATOR ANALOG NEEDLES READ 60%? YES SYSTEM NORMAL NO REPLACE AFU ON ENGINE THAT DOES NOT READ 60% TORQUE.5 OHM? REPAIR / REPLACE AIRCRAFT WIRING (REF. CONTINUITY AFU TO TORQUE INDICATOR OK? REPAIR / REPLACE AIRCRAFT WIRING (REF. 3045542 WITH TEST SWITCHES NO. CONTINUITY P16−L TO P6−F. 1. 1 AND 2 TO TORQUE SENSOR NO. AMM) NO YES CONTINUED ON SHEET 4 C26415 Autofeather System Faults Figure 172 (Sheet 3) 72-00-02 ENGINE . 1 AND 2 ON.FAULT ISOLATION Page 186 Sep 03/99 . AMM) NO NO CHECK AIRCRAFT WIRING CONTINUITY ON BOTH ENGINES NO. OK? YES SYSTEM NORMAL NO REINSTALL AFU THAT WAS REMOVED. P16−K TO P6−G. 3045542 CONTINUED ON SHEET 4 CHECK TORQUE SENSOR NO. 1. AT 20 ° C (RTD RESISTANCE)? REPLACE TORQUE SENSOR NO. COIL RESISTANCE OF PINS J6−A TO J6−B BETWEEN 557 AND 589 OHMS? IS J6−G TO J6−F 108 OHMS NOM. 1 (REF. AMM) C26416 Autofeather System Faults Figure 172 (Sheet 4) 72-00-02 ENGINE . 72−01−60) NO YES REPLACE AIRCRAFT TORQUE INDICATOR (REF.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO.FAULT ISOLATION Page 187 Sep 03/99 . 1 P16−B (LOW TORQUE INDICATOR DRIVER) C68378 Autofeather System Faults Figure 172 (Sheet 5) 72-00-02 ENGINE . 2 UPTRIM LAMP ON WHEN TEST SWITCH NO. INSULATION RESISTANCE ENGINE NO. 3045542 ENGINE NO. 2. UPTRIM LAMP ENGINE NO.FAULT ISOLATION Page 188 Sep 03/99 .PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 2 HARNESS P2−N AND J11−w TO ALL OTHER PINS AND BACKSHELL ON CONNECTORS GREATER THAN OR EQUAL TO 2 MEGOHMS AT 45 VDC? REPAIR / REPLACE ENGINE HARNESS NO YES REPLACE EEC ON ENGINE NO. ENGINE NO. 2 ILLUMINATES? YES SYSTEM NORMAL NO YES REINSTALL EEC ON ENGINE NO. 2. 1. UPTRIM LAMP WORK? YES SYSTEM NORMAL NO INVESTIGATE AIRCRAFT WIRING AND SYSTEM FROM AFU NO. 2 HARNESS LINE 135 LESS THAN OR EQUAL TO 0. AIRCRAFT WIRING TO P11 − w OK? SYSTEM NORMAL NO REPLACE AFU ON ENGINE NO. 1 RELEASED YES SYSTEM NORMAL NO CHECK CONTINUITY.5 OHM? REPAIR / REPLACE ENGINE HARNESS NO YES CHECK ENGINE HARNESS. RETRY AUTOFEATHER TEST. 1 RUNNING AT GROUND IDLE. AFU 2. OK? YES SYSTEM NORMAL C26418 Autofeather System Does not Arm on Takeoff Figure 173 72-00-02 ENGINE . AMM).PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO. 1. AIRCRAFT WIRING CARRY OUT INVESTIGATION AS PER LRU FAULT CODE 91 NO YES ANALOG TORQUE INDICATION = 0? YES CHECK TORQUE SHAFT NO INVESTIGATE AIRCRAFT WIRING TO PLA ENABLE MICROSWITCHES (REF. ENGINE HARNESS 3. RELEASE TEST SWITCH NO. PRESS AUTOFEATHER TEST SWITHES NO. 3045542 SYMPTOMS SUSPECT LRU WITH ALL CONDITIONS PRESENT TO ARM AUTOFEATHER SYSTEM ON TAKEOFF.FAULT ISOLATION Page 189 Sep 03/99 . AUTOFEATHER OPERATES NORMALLY? 1. SYSTEM DOES NOT ARM SELECT ATO RATING. 1 AND 2 ON WITH ENGINE NO. ENGINE HARNESS LINE 134 LESS THAN OR EQUAL TO 0. REMOVE CONNECTOR P2 FROM EEC. 3045542 SYMPTOMS SUSPECT LRU WHEN PROPELLER IS FEATHERED. ARE THERE 28 VDC ON P2 − s OF ENGINE HARNESS? 1. 4.PRATT & WHITNEY CANADA MAINTENANCE MANUAL MANUAL PART NO.FAULT ISOLATION Page 190 Sep 03/99 . 2. TURN EEC POWER OFF. ENGINE POWER INCREASES. 3. ARE THERE 28 VDC ON ENGINE HARNESS DISCONNECT P11 − j WHEN PROPELLER IS FEATHERED? NO RECTIFY YES SYSTEM NORMAL C26419 Engine Power Increases as Propeller is Feathered Figure 174 72-00-02 ENGINE . YES AFU ENGINE HARNESS AIRCRAFT WIRING EEC REPLACE EEC NO CHECK CONTINUITY. INSULATION RESISTANCE OF PINS P2 −s AND J11 −j TO ALL OTHER PINS AND BACKSHELL ON CONNECTORS GREATER THAN OR EQUAL TO 2 MEGOHMS AT 45 VDC? REPAIR / REPLACE ENGINE HARNESS NO YES INVESTIGATE AIRCRAFT WIRING.5 OHM? REPAIR / REPLACE ENGINE HARNESS NO YES CHECK ENGINE HARNESS. CAUSED BY NPT GOVERNING NOT BEING CANCELLED WHEN PROPELLER IS FEATHERED SET CONDITION LEVER AT FUEL CUTOFF POSITION.