A300B2 ATA 78

�� G E � � � � CF6 - 50 � �� HIGHLIGHTS __________

REVISION NO. 52 Mar 01/07

Pages which have been revised are outlined below, together with the Highlights of theRevision

--------------------------------------------------------------------------------------CH/SE/SU C REASON FOR CHANGE EFFECTIVITY PAGES--------------------------------------------------------------------------------------

CHAPTER 78__________

TEMPORARY REVISION CANCELLED 78-014

L.E.P. 1- 4 Revised to Reflect this revision indicating new,revised, and/or deleted pagesT. OF C. Revised to reflect this revision 2- 578-00-00 Added TLOD references to the deactivation/ ALL 402- 403, reactivation procedures as needed. 410 Minor additions and amplification ALL

78-30-00 Effectivity updated 502- 503, Inserted check stage and added CAUTION ALL 505- 523 para.?8.Thrust Reverser Operational Check?. Minor additions and amplification ALL Effectivity updated 001-103, 106-999, Due to SB 78-022

78-31-00 Effectivity updated 1- 4, Effectivity updated 001-103, 106-999, 7, 10, Due to SB 78-022 12- 14, 17, 30- 33

78-31-00 Effectivity updated 202- 203, Added Caution (instruction to inspect the ALL 205- 255 actuator clevis fitting before rigging the system). Minor additions and amplification ALL Effectivity updated 001-103, 106-999, Due to SB 78-022 Incorporation of Temporary Revision No.78-014 ALL Cancelled Temporary Revision No. 78-014

78-31-02 Effectivity updated 001-103, 106-999, 201- 204, Due to SB 78-022 206

78-HIGHLIGHTS REVISION NO. 52 of 2 JAS Mar 01/07

�� G E � � � � CF6 - 50 � ��--------------------------------------------------------------------------------------CH/SE/SU C REASON FOR CHANGE EFFECTIVITY PAGES--------------------------------------------------------------------------------------

78-31-12 Effectivity updated 201- 209 Effectivity updated 001-103, 106-999, Due to SB 78-022

78-31-13 02 Effectivity updated 201- 205 Effectivity updated 001-103, 106-999, Due to SB 78-022




78-32-00 Revised Fig. ?Translating cowl Bumper Lock ALL 823 Plate Replacement? Minor additions and amplification ALL

78-HIGHLIGHTS REVISION NO. 52 of 2 JAS Mar 01/07

�� G E � � � � CF6 - 50 � �� CHAPTER 78 __________

EXHAUST

LIST OF EFFECTIVE PAGES _______________________ N, R or D indicates pages which are New, Revised or Deleted respectively Remove and insert the affected pages and complete the Record of Revisions and the Record of Temporary Revisions as necessary

CH/SE/SU C PAGE DATE CH/SE/SU C PAGE DATE CH/SE/SU C PAGE DATE

RECORD 78-11-00 405 Oct01/93 78-30-00 R 512 Mar01/07OF TEMP. 78-11-00 406 Oct01/93 78-30-00 R 513 Mar01/07REVISION 78-11-00 601 Apr30/82 78-30-00 R 514 Mar01/07 78-11-00 602 Oct01/91 78-30-00 R 515 Mar01/07L.E.P. R 1- 4 Mar01/07 78-11-00 603 Apr30/82 78-30-00 R 516 Mar01/07T. of C. 1 Mar01/06 78-11-00 604 Oct01/91 78-30-00 R 517 Mar01/07T. of C. R 2 Mar01/07 78-11-00 605 Oct01/95 78-30-00 R 518 Mar01/07T. of C. R 3 Mar01/07 78-11-00 606 Oct01/97 78-30-00 R 519 Mar01/07T. of C. R 4 Mar01/07 78-11-00 607 Oct01/95 78-30-00 R 520 Mar01/07T. of C. R 5 Mar01/07 78-30-00 N 521 Mar01/07T. of C. 6 Mar01/06 78-12-00 1 Jul30/83 78-30-00 N 522 Mar01/07T. of C. 7 Mar01/06 78-12-00 2 Jul30/83 78-30-00 N 523 Mar01/07 78-12-00 401 Oct01/9378-00-00 1 Mar01/01 78-12-00 402 Jul30/80 78-31-00 R 1 Mar01/0778-00-00 2 Apr30/80 78-12-00 403 Jul30/81 78-31-00 R 2 Mar01/0778-00-00 101 Jul30/82 78-12-00 404 Oct01/93 78-31-00 R 3 Mar01/0778-00-00 401 Oct01/94 78-12-00 601 Jan01/88 78-31-00 R 4 Mar01/0778-00-00 R 402 Mar01/07 78-12-00 602 Jan01/88 78-31-00 5 Mar01/0678-00-00 R 403 Mar01/07 78-12-00 603 Jan01/87 78-31-00 6 Mar01/0678-00-00 404 Oct01/94 78-12-00 604 Oct01/92 78-31-00 R 7 Mar01/0778-00-00 405 Oct01/94 78-12-00 605 Oct01/92 78-31-00 8 Mar01/0678-00-00 406 Oct01/94 78-31-00 9 Mar01/0678-00-00 407 Oct01/94 78-30-00 1 Apr30/80 78-31-00 R 10 Mar01/0778-00-00 408 Oct01/94 78-30-00 2 Apr30/80 78-31-00 11 Mar01/0678-00-00 409 Oct01/94 78-30-00 3 Apr30/80 78-31-00 R 12 Mar01/0778-00-00 R 410 Mar01/07 78-30-00 4 Apr30/80 78-31-00 R 13 Mar01/0778-00-00 411 Mar01/06 78-30-00 5 Apr30/80 78-31-00 R 14 Mar01/0778-00-00 412 Mar01/06 78-30-00 6 Apr30/80 78-31-00 15 Mar01/0678-00-00 413 Mar01/06 78-30-00 7 Apr30/80 78-31-00 16 Mar01/0678-00-00 414 Mar01/06 78-30-00 8 Oct30/83 78-31-00 R 17 Mar01/0778-00-00 415 Mar01/06 78-30-00 101 Jul30/82 78-31-00 18 Mar01/0678-00-00 416 Mar01/06 78-30-00 501 Mar01/99 78-31-00 19 Mar01/0678-00-00 417 Mar01/06 78-30-00 R 502 Mar01/07 78-31-00 20 Mar01/0678-00-00 418 Mar01/06 78-30-00 R 503 Mar01/07 78-31-00 21 Mar01/0678-00-00 419 Mar01/06 78-30-00 504 Mar01/06 78-31-00 22 Mar01/06 78-30-00 R 505 Mar01/07 78-31-00 23 Mar01/0678-11-00 1 Jul30/81 78-30-00 R 506 Mar01/07 78-31-00 24 Mar01/0678-11-00 2 Jul30/81 78-30-00 R 507 Mar01/07 78-31-00 25 Mar01/0678-11-00 401 Oct01/93 78-30-00 R 508 Mar01/07 78-31-00 26 Mar01/0678-11-00 402 Jul30/81 78-30-00 R 509 Mar01/07 78-31-00 27 Mar01/0678-11-00 403 Jul30/81 78-30-00 R 510 Mar01/07 78-31-00 28 Mar01/0678-11-00 404 Jul30/81 78-30-00 R 511 Mar01/07 78-31-00 29 Mar01/06

78-L.E.P. Page 1 JAS Mar 01/07

�� G E � � � � CF6 - 50 � ��CH/SE/SU C PAGE DATE CH/SE/SU C PAGE DATE CH/SE/SU C PAGE DATE

78-31-00 R 30 Mar01/07 78-31-00 R 222 Mar01/07 78-31-01 218 Mar01/0078-31-00 R 31 Mar01/07 78-31-00 R 223 Mar01/07 78-31-01 219 Mar01/0078-31-00 R 32 Mar01/07 78-31-00 R 224 Mar01/07 78-31-01 220 Mar01/0078-31-00 R 33 Mar01/07 78-31-00 R 225 Mar01/07 78-31-02 R 201 Mar01/0778-31-00 34 Mar01/06 78-31-00 R 226 Mar01/07 78-31-02 R 202 Mar01/0778-31-00 35 Mar01/06 78-31-00 R 227 Mar01/07 78-31-02 R 203 Mar01/0778-31-00 36 Mar01/06 78-31-00 R 228 Mar01/07 78-31-02 R 204 Mar01/0778-31-00 37 Mar01/06 78-31-00 R 229 Mar01/07 78-31-02 205 Apr30/8178-31-00 38 Mar01/06 78-31-00 R 230 Mar01/07 78-31-02 R 206 Mar01/0778-31-00 39 Mar01/06 78-31-00 R 231 Mar01/07 78-31-03 201 Jul01/9878-31-00 40 Mar01/06 78-31-00 R 232 Mar01/07 78-31-03 202 Jul01/9878-31-00 41 Mar01/06 78-31-00 R 233 Mar01/07 78-31-03 203 Oct01/9478-31-00 42 Mar01/06 78-31-00 R 234 Mar01/07 78-31-03 204 Oct01/9378-31-00 43 Mar01/06 78-31-00 R 235 Mar01/07 78-31-03 205 Apr30/8178-31-00 44 Mar01/06 78-31-00 R 236 Mar01/07 78-31-03 206 Jan30/8278-31-00 45 Mar01/06 78-31-00 R 237 Mar01/07 78-31-04 201 Mar01/0178-31-00 46 Mar01/06 78-31-00 R 238 Mar01/07 78-31-04 202 Oct01/9078-31-00 47 Mar01/06 78-31-00 R 239 Mar01/07 78-31-04 203 Oct01/9078-31-00 48 Mar01/06 78-31-00 R 240 Mar01/07 78-31-04 204 Oct01/9078-31-00 49 Mar01/06 78-31-00 R 241 Mar01/07 78-31-05 201 Mar01/9978-31-00 50 Mar01/06 78-31-00 R 242 Mar01/07 78-31-05 202 Oct01/9678-31-00 51 Mar01/06 78-31-00 R 243 Mar01/07 78-31-05 203 Mar01/9978-31-00 52 Mar01/06 78-31-00 R 244 Mar01/07 78-31-05 204 Jan01/8878-31-00 53 Mar01/06 78-31-00 R 245 Mar01/07 78-31-05 205 Jan01/8878-31-00 54 Mar01/06 78-31-00 R 246 Mar01/07 78-31-05 206 Oct01/9678-31-00 55 Mar01/06 78-31-00 R 247 Mar01/07 78-31-05 207 Apr30/8378-31-00 56 Mar01/06 78-31-00 R 248 Mar01/07 78-31-06 201 Jul30/8278-31-00 57 Mar01/06 78-31-00 R 249 Mar01/07 78-31-06 202 Jul01/8978-31-00 58 Mar01/06 78-31-00 R 250 Mar01/07 78-31-06 203 Jul01/8978-31-00 59 Mar01/06 78-31-00 R 251 Mar01/07 78-31-06 204 Oct01/9278-31-00 201 Mar01/99 78-31-00 R 252 Mar01/07 78-31-06 205 Mar01/0678-31-00 R 202 Mar01/07 78-31-00 N 253 Mar01/07 78-31-07 201 Jan01/8878-31-00 R 203 Mar01/07 78-31-00 N 254 Mar01/07 78-31-07 202 Oct30/8178-31-00 204 Jan30/81 78-31-00 N 255 Mar01/07 78-31-07 203 Jul30/8178-31-00 R 205 Mar01/07 78-31-01 201 Jan01/88 78-31-07 204 Oct30/8178-31-00 R 206 Mar01/07 78-31-01 202 Jul01/98 78-31-08 201 Jan01/8878-31-00 R 207 Mar01/07 78-31-01 203 Mar01/03 78-31-08 202 Oct30/8178-31-00 R 208 Mar01/07 78-31-01 204 Jul01/98 78-31-08 203 Oct30/8278-31-00 R 209 Mar01/07 78-31-01 205 Mar01/03 78-31-08 204 Oct30/8178-31-00 R 210 Mar01/07 78-31-01 206 Mar01/03 78-31-09 201 Mar01/9978-31-00 R 211 Mar01/07 78-31-01 207 Mar01/99 78-31-09 202 Mar01/9978-31-00 R 212 Mar01/07 78-31-01 208 Mar01/99 78-31-09 203 Apr30/8278-31-00 R 213 Mar01/07 78-31-01 209 Mar01/99 78-31-09 204 Oct01/9678-31-00 R 214 Mar01/07 78-31-01 210 Mar01/99 78-31-09 205 Oct30/8178-31-00 R 215 Mar01/07 78-31-01 211 Mar01/99 78-31-09 206 Jul01/8578-31-00 R 216 Mar01/07 78-31-01 212 Mar01/99 78-31-09 207 Jul01/8578-31-00 R 217 Mar01/07 78-31-01 213 Mar01/99 78-31-09 208 Oct01/9678-31-00 R 218 Mar01/07 78-31-01 214 Mar01/03 78-31-11 201 Jul30/8178-31-00 R 219 Mar01/07 78-31-01 215 Mar01/03 78-31-11 202 Jul30/8178-31-00 R 220 Mar01/07 78-31-01 216 Mar01/00 78-31-11 203 Jul01/8978-31-00 R 221 Mar01/07 78-31-01 217 Mar01/00 78-31-11 204 Jul01/89



78-31-11 205 Jul01/89 78-31-53 R 404 Mar01/07 78-32-00 801 Mar01/0678-31-11 206 Jul01/89 78-31-53 R 405 Mar01/07 78-32-00 802 Mar01/0678-31-12 R 201 Mar01/07 78-31-53 R 406 Mar01/07 78-32-00 803 Oct30/8078-31-12 R 202 Mar01/07 78-31-54 R 401 Mar01/07 78-32-00 804 Mar01/0678-31-12 R 203 Mar01/07 78-31-54 R 402 Mar01/07 78-32-00 805 Mar01/0678-31-12 R 204 Mar01/07 78-31-54 R 403 Mar01/07 78-32-00 806 Mar01/0678-31-12 R 205 Mar01/07 78-31-54 R 601 Mar01/07 78-32-00 807 Mar01/0678-31-12 R 206 Mar01/07 78-31-54 R 602 Mar01/07 78-32-00 808 Mar01/0678-31-12 R 207 Mar01/07 78-31-54 R 603 Mar01/07 78-32-00 809 Oct01/9578-31-12 R 208 Mar01/07 78-31-54 R 604 Mar01/07 78-32-00 810 Mar01/0678-31-12 R 209 Mar01/07 78-32-00 811 Mar01/0678-31-13 01 201 Mar01/06 78-32-00 1 Apr30/81 78-32-00 812 Oct01/9578-31-13 01 202 Mar01/06 78-32-00 2 Apr30/81 78-32-00 813 Oct01/9578-31-13 01 203 Mar01/06 78-32-00 3 Apr30/81 78-32-00 814 Oct01/9578-31-13 01 204 Mar01/06 78-32-00 4 Apr30/81 78-32-00 815 Mar01/0678-31-13 01 205 Mar01/06 78-32-00 5 Apr30/81 78-32-00 816 Oct01/9478-31-13 02 R 201 Mar01/07 78-32-00 601 Mar01/99 78-32-00 817 Oct01/9478-31-13 02 R 202 Mar01/07 78-32-00 602 Oct01/93 78-32-00 818 Oct01/9478-31-13 02 R 203 Mar01/07 78-32-00 603 Jul30/81 78-32-00 819 Mar01/0678-31-13 02 R 204 Mar01/07 78-32-00 604 Jan30/81 78-32-00 820 Oct01/9578-31-13 02 R 205 Mar01/07 78-32-00 605 Jan30/81 78-32-00 821 Mar01/0678-31-14 201 Mar01/99 78-32-00 606 Oct01/93 78-32-00 822 Oct01/9578-31-14 202 Mar01/99 78-32-00 607 Jan01/88 78-32-00 R 823 Mar01/0778-31-14 203 Oct30/82 78-32-00 608 Oct01/94 78-32-00 824 Mar01/0678-31-14 204 Mar01/99 78-32-00 609 Oct01/93 78-32-00 825 Mar01/0678-31-30 201 Jan30/81 78-32-00 610 Oct01/93 78-32-00 826 Mar01/0678-31-30 202 Oct30/81 78-32-00 611 Mar01/99 78-32-00 827 Mar01/0678-31-30 203 Jan30/81 78-32-00 612 Mar01/99 78-32-00 828 Mar01/0678-31-30 204 Oct30/81 78-32-00 613 Mar01/99 78-32-00 829 Mar01/0678-31-31 201 Jan01/88 78-32-00 614 Mar01/99 78-32-00 830 Mar01/0678-31-31 202 Oct30/81 78-32-00 615 Mar01/99 78-32-00 831 Mar01/0678-31-31 203 Jan30/82 78-32-00 616 Mar01/03 78-32-00 832 Mar01/0678-31-31 204 Jan30/82 78-32-00 617 Mar01/03 78-32-00 833 Mar01/0678-31-32 201 Jan01/88 78-32-00 618 Mar01/03 78-32-00 834 Mar01/0678-31-32 202 Oct30/81 78-32-00 619 Mar01/00 78-32-00 835 Mar01/0678-31-32 203 Jul30/81 78-32-00 620 Mar01/03 78-32-00 836 Mar01/0678-31-32 204 Oct30/81 78-32-00 621 Mar01/03 78-32-00 837 Mar01/0678-31-32 205 Jul30/81 78-32-00 622 Mar01/03 78-32-00 838 Mar01/0678-31-51 401 Jul01/89 78-32-00 623 Mar01/03 78-32-00 839 Mar01/0678-31-51 402 Jul01/89 78-32-00 624 Mar01/03 78-32-11 401 Oct30/8378-31-51 403 Jul01/89 78-32-00 625 Mar01/03 78-32-11 402 Oct30/8378-31-51 404 Jul30/82 78-32-00 626 Mar01/06 78-32-11 403 Oct30/8378-31-51 405 Jul30/82 78-32-00 627 Mar01/06 78-32-12 401 Oct01/8978-31-51 406 Jul30/82 78-32-00 628 Mar01/06 78-32-12 402 Oct30/8378-31-51 407 Jul30/82 78-32-00 629 Mar01/06 78-32-12 403 Oct30/8378-31-52 201 Jan01/88 78-32-00 630 Mar01/06 78-32-12 404 Oct30/8378-31-52 202 Oct30/81 78-32-00 631 Mar01/06 78-32-12 405 Oct30/8378-31-52 203 Jul30/81 78-32-00 632 Mar01/06 78-32-13 401 Oct30/8378-31-53 R 401 Mar01/07 78-32-00 633 Mar01/06 78-32-13 402 Oct30/8378-31-53 R 402 Mar01/07 78-32-00 634 Mar01/99 78-32-13 403 Oct30/8378-31-53 R 403 Mar01/07 78-32-00 635 Mar01/99 78-32-14 401 Oct30/83



78-32-14 402 Oct30/8378-32-14 403 Oct30/8378-32-15 401 Oct01/9378-32-15 402 Oct01/9378-32-15 601 Oct01/9378-32-15 602 Oct01/9378-32-15 603 Oct01/93

78-36-00 1 Apr30/8178-36-00 2 Apr30/8178-36-00 3 Apr30/8178-36-00 4 Apr30/8178-36-00 5 Apr30/8178-36-00 6 Apr30/8178-36-00 7 Apr30/8178-36-00 8 Apr30/8178-36-00 9 Apr30/8178-36-00 201 Oct01/9778-36-00 202 Oct01/9778-36-00 203 Oct30/8178-36-00 204 Oct30/8178-36-00 205 Apr30/8278-36-00 206 Apr30/8278-36-00 207 Apr30/8278-36-00 208 Apr30/8278-36-01 201 Jul30/8178-36-01 202 Oct30/8178-36-01 203 Jul30/8178-36-01 204 Oct30/8178-36-01 205 Apr30/8278-36-01 206 Oct30/8178-36-02 201 Jan01/8878-36-02 202 Jul30/8278-36-02 203 Oct30/8178-36-02 204 Oct30/8178-36-02 205 Oct30/81


�� G E � � � � CF6 - 50 � �� CHAPTER 78 __________

EXHAUST

TABLE OF CONTENTS _________________

SUBJECT CH/SE/SU C PAGE EFFECTIVITY _______ ________ _ ____ ________ GENERAL 78-00-00 _______ Description and Operation 1 ALL Fault Isolation Manual 101 ALL Deactivation Procedure 401 ALL Ref.:MMEL Sect.1-78, Item 1 401 ALL Fan Reverser Deactivation Procedure 401 ALL Fan Thrust Reverser System 403 ALL Reactivation and Unlocking Electrical (Stow) Indicator Switch 411 ALL and Pressure Regulating and Shut-off Valve Visual Check, Prior to each Flight Ref.:MMEL Sect.1-78, Item 2 411 ALL Electrical (Deploy) Indicator 416 ALL Switch and Throttle and Thrust Reverser Interlock Valve Operational Test Ref.:MMEL Sect.1-78, Item 3 416 ALL LONG FIXED CORE EXHAUST NOZZLE 78-11-00 Description and Operation 1 ALL General 1 ALL Component Location 1 ALL Description 1 ALL Removal/Installation 401 ALL Procedure 401 ALL Inspection/Check 601 ALL Procedure 601 ALL Long Fixed Exhaust Nozzle 601 ALL Centerbody Fwd/Aft for : 601 ALL Baffle 605 ALL Fixed Nozzle Cowl for : 605 ALL

SHORT FIXED CORE EXHAUST NOZZLE 78-12-00 Description and Operation 1 ALL General 1 ALL Component Location 1 ALL Description 1 ALL Removal/Installation 401 ALL Procedure 401 ALL Inspection/Check 601 ALL Procedure 601 ALL Short Fixed Exhaust Nozzle 601 ALL Centerbody Fwd/Aft Sheet 601 ALL Metal for : 601 ALL Baffle 603 ALL Fixed Nozzle Cowl for 604 ALL

78-CONTENTSR Page 1 JAS Mar 01/06

�� G E � � � � CF6 - 50 � �� SUBJECT CH/SE/SU C PAGE EFFECTIVITY _______ ________ _ ____ ________ Fwd Centerbody to Turbine Rear 605 ALL Frame (TRF) THRUST REVERSER 78-30-00 _______________ Description and Operation 1 ALL Component Location 1 ALL Description 1 ALL Operation 6 ALL Thrust Reverser Deployment 6 ALL Thrust Reverser Stowage 6 ALL Indicating 6 ALL Fault Isolation Manual 101 ALL Adjustment/Test 501 ALL Thrust Reverser Translating Cowl 505 ALL Auto Re-Stow Function Check (Three-light Indication Circuit Only) Thrust Reverser Translating Cowl 512 ALL Auto Re-Stow Function Check (Two-light Indication Circuit Only) Overpressure Shutoff Valve 516 ALL (OPSOV) Indication Check Thrust Reverser Operational Check 518 ALL

THRUST REVERSER SYSTEM CONTROL 78-31-00 Description and Operation 1 ALL Component Location 1 ALL Thrust Reverser Deployment 14 ALL Thrust Reverser Stowage 17 ALL Pneumatic Drive Actuator 18 ALL Center Gearbox 27 ALL Upper and Lower Gearboxes 28 ALL Fan Reverser Ball-Screw Actuators 29 ALL Pressure Regulating and Shut Off 30 ALL Valve Directional Control Valve 36 ALL Pneumatic Switcher Valve 37 ALL Throttle and Thrust Reverser 38 ALL Interlock Valve Overpressure and Shut Off Valve 39 ALL Fan Reverser Indicator Switches 41 ALL Fan Reverser Flexible Drive Shafts 42 ALL Fan Reverser Electrical Cable 43 ALL Pneumatic Check Valve 44 ALL Bleed Air Regulator Valve 45 ALL Throttle Interlock Actuator 45 ALL Safety Valve 49 ALL Feedback System 51 ALL Thrust Reverser Control and 51 ALL Indicating Nacelle Temperature Sensor 59 ALL Nacelle Temperature Sensor 59 ALL


�� G E � � � � CF6 - 50 � �� SUBJECT CH/SE/SU C PAGE EFFECTIVITY _______ ________ _ ____ ________ Electrical Cable Maintenance Practices 201 ALL Procedure 203 ALL Miscellaneous Operations 203 ALL Fan Reverser Translation 203 ALL Adjustment/Test 206 ALL Thrust Reverser System 206 ALL Rigging Thrust Reverser System 216 ALL Functional Test Thrust Reverser Speed Trimming 220 ALL Thrust reverser functional test 220 ALL and indicating/warning sensors test Landing Gear Ground Function Test 223 ALL Adjust Feedback Assemblies 226 ALL Maintenance Plan 233 ALL Fan Reverser Structural 233 ALL Inspection Controls, Drives and System 236 ALL Inspections and Service Requirements PNEUMATIC DRIVE ACTUATOR 78-31-01 Maintenance Practices 201 ALL Procedure 202 ALL Servicing 202 ALL Removal 206 ALL Installation 206 ALL Inspection/Check 217 ALL Approved Repairs 218 ALL CENTER GEARBOX AND BALLSCREW ACTUATOR 78-31-02 Maintenance Practices 201 ALL Procedure 202 ALL Removal 202 ALL Installation 202 ALL Inspection/Check 203 ALL Approved Repairs 204 ALL UPPER AND LOWER GEARBOXES AND 78-31-03 BALLSCREW ACTUATORS Maintenance Practices 201 ALL Procedure 202 ALL Removal 203 ALL Installation 203 ALL Inspection/Check 206 ALL Approved Repairs 206 ALL FAN REVERSER BALL-SCREW ACTUATORS 78-31-04 Maintenance Practices 201 ALL Procedure 201 ALL Removal 201 ALL Inspection/Check 201 ALL PRESSURE REGULATING AND SHUT OFF VALVE 78-31-05 Maintenance Practices 201 ALL


�� G E � � � � CF6 - 50 � �� SUBJECT CH/SE/SU C PAGE EFFECTIVITY _______ ________ _ ____ ________ Procedure 202 ALL Removal/Installation 202 ALL Inspection/Check 206 ALL DIRECTIONAL CONTROL VALVE 78-31-06 Maintenance Practices 201 ALL Procedure 202 ALL Removal 202 001-003,102-102,105-105, Removal 202 004-101,103-104,106-999, Inspection/Check 205 ALL Adjustment 205 ALL PNEUMATIC SWITCHER VALVE 78-31-07 Maintenance Practices 201 ALL Procedure 202 ALL Removal 202 ALL Inspection/Check 202 ALL THROTTLE AND THRUST REVERSER INTERLOCK 78-31-08 VALVE Maintenance Practices 201 ALL Procedure 202 ALL Removal 202 ALL Inspection/Check 202 ALL OVERPRESSURE SHUT OFF BUTTERFLY VALVE 78-31-09 Maintenance Practices 201 ALL Procedure 202 ALL Removal 202 ALL Inspection/Check 205 ALL Tests 208 ALL FAN REVERSER INDICATOR SWITCHES 78-31-11 Maintenance Practices 201 ALL Procedure 203 ALL Removal 203 ALL Installation 203 ALL Inspection/Check 203 ALL Approved Repairs 206 ALL Test 206 ALL FAN REVERSER FLEXIBLE SHAFT ASSY 78-31-12 Maintenance Practices 201 ALL Procedure 201 ALL Procedure 201 001-103,106-999, Removal 204 ALL Inspection/Check 205 ALL Approved Repairs 208 ALL FAN REVERSER ELECTRICAL CABLE ASSY 78-31-13 01 Maintenance Practices 201 ALL Procedure 202 ALL Removal 202 ALL Inspection/Check 202 ALL FAN REVERSER AND TRAS LOCK ELECTRICAL 78-31-13 02 CABLE ASSY Maintenance Practices 201 001-103,106-999, Procedure 202 001-103,106-999, Removal 202 001-103,106-999,


�� G E � � � � CF6 - 50 � �� SUBJECT CH/SE/SU C PAGE EFFECTIVITY _______ ________ _ ____ ________ Inspection/Check 204 001-103,106-999, PNEUMATIC CHECK VALVE 78-31-14 Maintenance Practices 201 ALL Procedure 202 ALL Removal 202 ALL Inspection/Check 204 ALL BLEED AIR REGULATOR VALVE 78-31-30 Maintenance Practices 201 ALL Procedure 202 ALL Removal 202 ALL Inspection/Check 202 ALL Approved Repairs 202 ALL NACELLE TEMPERATURE SENSOR 78-31-31 Maintenance Practices 201 ALL Procedure 202 ALL Removal 202 ALL Inspection/Check 203 ALL Electrical Tests 204 ALL NACELLE TEMPERATURE ELECTRICAL CABLE 78-31-32 Maintenance Practices 201 ALL Procedure 202 ALL Removal 202 ALL Installation 202 ALL Inspection/Check 204 ALL THROTTLE INTERLOCK ACTUATOR 78-31-51 Removal/Installation 401 ALL Procedure 401 001-003,102-102,105-105, Removal 402 001-003,102-102,105-105, Installation 403 001-003,102-102,105-105, Procedure 403 004-101,103-104,106-999, Test 403 ALL OVERPRESSURE SAFETY VALVE ASSY 78-31-52 Maintenance Practices 201 ALL Procedure 202 ALL Removal 202 ALL Installation 202 ALL THRUST REVERSER ELECTRO-MECHANICAL 78-31-53 BRAKE (TRAS LOCK) Removal/Installation 401 001-103,106-999, THRUST REVERSER TRAS LOCK AND SWITCHER 78-31-54 VALVE Removal/Installation 401 001-103,106-999, Inspection/Check 601 001-103,106-999,

FAN REVERSER ASSEMBLY 78-32-00 Description and Operation 1 ALL Component Location 1 ALL Inspection/Check 601 ALL Procedure 602 ALL Inspection/Check of the 602 ALL Following Areas Hold-Open Rod Inspection 633 ALL


�� G E � � � � CF6 - 50 � �� SUBJECT CH/SE/SU C PAGE EFFECTIVITY _______ ________ _ ____ ________ Approved Repairs 801 ALL Procedure 802 ALL Replacement of Vaned Deflectors 802 ALL Replacement of Blocker Doors 804 ALL Translating Cowl Gap Rigging 804 ALL Translating Cowl 805 ALL Removal/Replacement Transcowl Bulb Seal Removal/ 806 ALL Installation Precooler Seal Assembly 808 ALL Intumescent Fireproof Coating 808 ALL Teflon Paint Coating on Fretting 811 ALL Surfaces of Fan Reverser Translating Cowl Bumper 821 ALL Replacement Lower Blocker Door Trim 821 ALL Standard Blocker Door Trim 824 ALL Replacement of Link Box Assembly 824 ALL Sealed Reverser Sealant 824 ALL Reapplication Fairing Repair 826 ALL Upper/Lower Aft Fairing 827 ALL (Beaver Tail) Removal Replacement of Worn/Damaged 829 ALL Tee Hinge Wear Strips THRUST REVERSER TRANSLATING COWL 78-32-11 Removal/Installation 401 ALL Procedure 401 ALL THRUST REVERSER CASCADES 78-32-12 Removal/Installation 401 ALL THRUST REVERSER BLOCKER DOORS 78-32-13 Removal/Installation 401 ALL BLOCKER DOOR LINK ASSEMBLY 78-32-14 Removal/Installation 401 ALL THRUST REVERSER TRANSLATING COWL AFT 78-32-15 SOUND PANELS Removal/Installation 401 ALL Procedure 401 ALL Inspection/Check 601 ALL Procedure 601 ALL

FAN REVERSER COWL DOOR OPENING SYSTEM 78-36-00 Description and Operation 1 ALL Component Location 2 ALL Maintenance Practices 201 ALL Procedure 201 ALL Fan Reverser Opening and Closing 201 ALL Cowl Door Opening System 206 ALL Deactivation (Mechanical System) COWL DOOR OPENING SYSTEM BALL SCREW 78-36-01 ACTUATORS AND HYDRAULIC ACTUATORS Maintenance Practices 201 ALL


�� G E � � � � CF6 - 50 � �� SUBJECT CH/SE/SU C PAGE EFFECTIVITY _______ ________ _ ____ ________ Procedure 202 ALL Removal 202 ALL Installation 202 ALL Inspection/Check 204 ALL Approved Repairs 205 ALL COWL DOOR OPENING SYSTEM FLEXIBLE 78-36-02 SHAFTS Maintenance Practices 201 ALL Procedure 202 ALL Removal 202 ALL Installation 202 ALL Inspection/Check 202 ALL Approved Repairs 203 ALL


�� G E � � � � CF6 - 50 � �� GENERAL - DESCRIPTION AND OPERATION ___________________________________

1. General (Ref. Fig. 001 ) _______

A. Part of the air absorbed by the fan is directly evacuated to the outside the remaining part is sent to the engine combustion chamber and is rejected as burnt gases through an exhaust nozzle.

B. The engine exhaust section directs fan discharge air for either normal or reverse thrust operation.

C. In forward thrust mode, fan air flow and burnt gases are evacuated directly at the back.

D. Each engine is equipped with a fan thrust reverser system which deflects the gas flow laterally by deploying blocker doors in the flow path and redirects the flow towards the front of the engine via vaned deflectors.

2. Description and Operation _________________________ The exhaust section comprises : - the exhaust nozzle - the thrust reverser system

A. Exhaust Nozzle (Ref. 78-12-00) The exhaust nozzle forms the rear part of the engine. The exhaust nozzle front flange is bolted to the rear flange of the turbine casing.

B. Thrust Reverser (Ref. 78-30-00) - The thrust reverser system uses part of engine exhaust power to provide additional aerodynamic braking during aircraft landing. - The thrust reverser system is controlled fron the flight compartment by a lever hinged to corresponding throttle control lever. - The thrust reverser system is basically made up of translating cowls and blocker doors. - An electrical indicating system monitors operation of the thrust reverser.

�� EFFECTIVITY: ALL �� 78-00-00 � � � �R Page 1 � � JAS Mar 01/01

�� G E � � � � CF6 - 50 � ��

Exhaust - Fixed Exhaust Nozzle - SchematicR Figure 001

�� EFFECTIVITY: ALL �� 78-00-00 � � � � Page 2 � � JAS Apr 30/80

�� G E � � � � CF6 - 50 � �� GENERAL - FAULT ISOLATION _________________________

Refer to FI/MM 78-00-00, P. Block 101.

�� EFFECTIVITY: ALL �� 78-00-00 � � � � Page 101 � � JAS Jul 30/82

�� G E � � � � CF6 - 50 � �� THRUST REVERSERS - DEACTIVATION PROCEDURE _________________________________________

REFERENCE : MMEL SECTION 1-78, ITEM 1 CAUTION : ON COMPLETION OF ANY THRUST REVERSER SYSTEM MAINTENANCE, VISUALLY _______ CHECK SURROUNDING AREAS FOR COMPONENTS SECURITY. SPECIFICALLY, CHECK FLEXIBLE SHAFT CONNECTIONS AT GEARBOXES AND BALLSCREW ACTUATORS, PNEUMATIC DRIVE ACTUATOR AND PNEUMATIC TUBE CONNECTIONS. USE CORE COWL MAINTENANCE STEP IF REQUIRED WHEN PERFORMING MAINTENAN- CE INSIDE REVERSER HALF. STEPPING ON OTHER AREAS OF CORE COWL COULD RESULT IN DAMAGE TO FIRE PROTECTION COATING.

1. Equipment and Materials _______________________ ------------------------------------------------------------------------------- ITEM DESIGNATION ------------------------------------------------------------------------------- A. Access Platform 3 m (10 ft.) B. Starting Pneumatic Ground Power Unit C. Electrical Ground Power Unit, 3-Phase, 115/200V, 400Hz, 90KVA D. Torque Wrench E. Square Drive, 3/8 in. dia. F. 2C6105 Adapter Drive G. 2C6900 Tool - Installation H. Circuit Breaker Safety Clips J. Corrosion-Resistant Steel Lockwire Dia. 0.032 in. (0.8 mm) K. Corrosion-Resistant Steel Lockwire Dia. 0.020 in. (0.5 mm) L. Warning Notices M. 29644-1 Spanner Wrench Adapter N. Paint, Finch 443-3-1022 or Equivalent Referenced Procedures - 71-13-00, P. Block 301 Cowl Doors - 36-00-00, P. Block 1 Pneumatic System - 24-41-00, P. Block 301 External Power - 78-31-00, P. Block 201 Thrust ReverserR - 78-36-00, P. Block 201 Fan Reverser Cowl Door Opening System

R 2. Fan Reverser Deactivation Procedure ___________________________________R CAUTION : THE FAN REVERSER DEACTIVATION PROCEDURE HAS BEEN WRITTEN TO MAKE _______R SURE THAT THE FAN REVERSER DOES NOT OPERATE DURING FLIGHT. MAKER SURE YOU COMPLETE ALL THE STEPS BECAUSE THIS IS THE MINIMUMR REQUIREMENT PERMITTED.R (Ref. Fig. 401, 402 and 403)R (Ref. Fig. 404, 405 and 406)R The following procedure is the preferred procedure to deactivate/lock a FanR Reverser. CAUTION : WHEN DEACTIVATING THE FAN REVERSER, CONSULT AIRFRAME MAINTENANCE _______ MANUAL AND OPERATION MANUALS FOR PLACARDING REQUIREMENTS AND POSSIBLE FLIGHT RESTRICTIONS.

�� EFFECTIVITY: ALL �� 78-00-00 � � � � Page 401 � � JAS Oct 01/94

�� G E � � � � CF6 - 50 � �� A. Open Fan Cowls 435AL (445AL), 436AR (446AR)

B. Deactivate Electrical Supply (1)Disconnect the right-hand electrical cable at the deploy switch (aft electrical switch). Secure cable and cap the deploy switch for protection against contamination (Ref. Fig. 401 )

C. Deactivate MechanicallyR FOR FAN RESERVERS WITHOUT TRAS LOCK NOTE : The translating cowl can be manually stowed using the unused drive ____ spline on the center gearbox. To relieve brake pressure, either the main drive cable must first be removed or the brake manually released on the pneumatic drive motor. If manual release of the brake is necessary, opening of the fan reverser halves is required. The following procedures should be accomplished : (1)Remove the two bolts securing the main drive cables to the center gearboxes (Ref. Fig. 402 ). Attempt to disconnect the main drive cables from the center gearboxes and secure the cables to prevent them from sliding out of the sheath. (a)If removal of the main drive cable cannot be accomplished due to wind- up torque, the fan reverser halves must be opened and the brake manually released on the pneumatic drive motor. (b)Manually ensure that the translating cowl is at the stowed position before proceeding to (2).R END FOR FAN REVERSERS WITHOUT TRAS LOCKR FOR FAN REVERSERS WITH TRAS LOCKR NOTE : The translating cowl can be manually stowed using the unused ____R drive spline on the center gearbox. To relieve brake pressure,R either the main drive cable must first be removed or both theR TRAS Locks and the brake on the pneumatic drive motor manuallyR released.R The following procedure should be accomplished.R (2)Remove the two bolts securing the main drive cables to the centerR gearboxes (Ref. Fig. 402 ). Attempt to disconnect the main drive cablesR from the center gearboxes and secure the cables to preven them fromR sliding out of the sheath.R (a)If removal of the main drive cable cannot be accomplished due toR wind-up torque, the fan reverser halves must be opened and both theR pneumatic drive motor brake and the TRAS lock must be released.R (b)To manually release the TRAS lock, pull the T-handle approximatelyR 0.35 inch (8.9 mm), remove the lever from the retaining clip andR rotate the lever to engage the collar, then release the T-handle.R (c)Manually ensure that the translating cowl is at the stowed positionR before proceeding to step (2).R END FOR REVERSERS WITH TRAS LOCKR (3)Lockout center gearboxes. PRE GE SB 78-081 * * * (FAN REVERSERS WITHOUT LOCKOUT SPLINES) (a)If no lockout spline is available on the unused pad, a spline may be locally manufactured using the information shown in (Ref. Fig. 403 ). Apply one coat of orange paint to the surface indicated in (Ref. Fig. 403 ).

�� EFFECTIVITY: ALL �� 78-00-00 � � � � Page 402 � � JAS Mar 01/07

�� G E � � � � CF6 - 50 � �� END PRE GE SB 78-081 POST GE SB 78-081 * * * (FAN REVERSERS WITH LOCKOUT SPLINES) (b)If not yet accomplished, remove the lockout splines from the unused pads of both center gearboxes. END POST GE SB 78-081 (c)While manually holding the gearboxes on full stow, insert the lockout splines into the unused pads of the center gearbox and secure with two bolts (Ref. Fig. 404 ).R (4)Secure translating cowls to fixed structure. CAUTION : CHECK THE INTEGRITY OF NUT PLATES AT EACH LOCKOUT PAD PRIOR _______ TO LOCKOUT BOLT INSTALLATION. (a)Secure the translating cowls to the fixed structure by installing lockout bolts through the holes in the forward support ring and into the lockout plates of the translating cowls (Ref. Fig. 405 ) NOTE : Standard 10-32 steel aircraft bolts 0.75 in. (19 mm) long may ____ be used.R FOR FAN REVERSERS WITH TRAS LOCKR (5)Manually re-engage both TRAS locks as follows:R (a)Pull the T-handle approximately 0.1 inch (2.5 mm), rotate the leverR away from the fan cowl, engage the lever in the retaining clip, thenR release the T-handle.R (b)Verify that the T-handle has returned to the locked position.R END FOR FAN REVERSERS WITH TRAS LOCKR (6)Test fan reverser air supply NOTE : The test that follows is to detect a continuous stream of hot air ____ which could damage the pneumatic drive motor. (a)Pressurize the pneumatic system (Ref. 36-00-00, P. Block 001) or use APU. (b)With the aircraft electrical system energized, move thrust reverser control lever to deploy position. 1 Make certain that thrust reverser is not operating and that throttle _ interlock prevents the application of full reverse thrust. 2 Return the throttle control levers to the forward idle position. _ (c)Check for reverser indications in the cockpit. If any indication is present or if the OPS0V butterfly position switch is known inactive, deactivate the air supply to the fan reverser as follows : 1 Open the fan reverser (Ref. 78-36-00, P. Block 201). _ 2 Rotate the pressure regulator shutoff valve lockout hex nut to the _ closed position (Ref. Fig. 406 ). 3 Close and secure the fan reverser half. _R (7)Placard the fan reverser (a)Placard the fan reverser in the cockpit to indicate that the fan reverser is deactivated/locked.

3. Fan Thrust Reverser System Reactivation and Unlocking _____________________________________________________ (Ref. Fig. 401, 402 and 404) (Ref. Fig.405 and 406)

A. Fan thrust reverser system reactivation with fan reverser in the fully


�� G E � � � � CF6 - 50 � ��

Location of Deploy SwitchR Figure 401


�� G E � � � � CF6 - 50 � ��

Fan Reverser TranslationR Figure 402


�� G E � � � � CF6 - 50 � ��

Lockout Tool for Reverser SystemR Figure 403


�� G E � � � � CF6 - 50 � ��

Lockout Tool Installation/Reverser SystemR Figure 404


�� G E � � � � CF6 - 50 � ��

Fan Reverser Locking with BoltsR Figure 405


�� G E � � � � CF6 - 50 � ��

Thrust Reverser System DeactivationR Figure 406


�� G E � � � � CF6 - 50 � �� slowed position. (1)Open fan cowls 435AL (445AL), 436AR (446AR), core cowls 455AL (465AL), 456AR (466AR). NOTE : Unlock fan reverser cowls by removing locking bolts and ____ install gearbox manual input covers if fan reverser cowls are locked in translation. (2)Reconnect RH fan reverser electrical cable to the deploy switch (off switch) (Ref. Fig. 401 ).R FOR FAN REVERSERS WITH TRAS LOCKR (3)Manually release both TRAS locks as follows:R (a)Pull the T-handle approximately 0.35 inch (8.9 mm), remove the leverR from the retaining clip and rotate the lever to engage the collar,R then release the T-handle.R END FOR FAN REVERSERS WITH TRAS LOCKR (4)Reconnect the main drive cables to the center gearboxes with two bolts (Ref. Fig. 402 ). TORQUE to between 33 and 37 lbf.in (0.37 and 0.42 m.daN).R (5)Remove the splined lockout shaft in both RH and LH center gearbox unused pads of the fan reverser and install splined shaft in the opposite position (Ref. Fig. 404 )R (6)Remove lockout bolts that secured the translating cowl to the fixed structure outer ring (Ref. Fig. 405 ).R FOR FAN REVERSERS WITH TRAS LOCKR (7)Manually re-engage both TRAS locks as follows:R (a)Pull the T-handle approximately 0.1 inch (2.5 mm), rotate the leverR away from the fan cowl, engage the lever in the retaining clip, thenR release the T-handle.R (b)Verify that the T-handle has returned to the locked position.R END FOR FAN REVERSERS WITH TRAS LOCKR (8)If reactivation of the pneumatic system is necessary, open fan thrust reverser cowls 451AL (461AL), 452AR (462AR) and core cowls 455AL (465AL), 456AR (466AR).R (9)Activate the pneumatic system by rotating the pressure regulating shut- off valve lockout hex nut to the manual (open) position (Ref. Fig. 406 ).

B. Rig the fan reverser (Ref. 78-31-00, P. Block 201).

C. Test : Perform test after reactivation (Ref. 78-31-00, P. Block 201).

D. Close-Up (1)Make certain that working area is clean and clear of tools and miscellaneous items of equipment.


�� G E � � � � CF6 - 50 � ��R ELECTRICAL (STOW) INDICATOR SWITCH AND PRESSURE REGULATING AND ______________________________________________________________ SHUT-OFF VALVE VISUAL CHECK, PRIOR TO EACH FLIGHT _________________________________________________

REFERENCE : MMEL SECTION 1-78, ITEM 2 CAUTION : THIS PROCEDURE IS TO BE USED ACCORDING TO THE REQUIREMENTS OF THE _______ MMEL.

1. Reason for the Job __________________

A. Failure of ?REV UNLK? indicating circuit.

2. Equipment and Materials _______________________ ------------------------------------------------------------------------------- ITEM DESIGNATION ------------------------------------------------------------------------------- A. Circuit Breaker Safety Clips B. Access Platform 4 m (13 ft. 1 in.) C. Electrical Plugs/Blanks Referenced Procedure - 71-13-00, P. Block 301 Cowls

3. Procedure _________

A. Job Set-Up (1)Open, safety and tag circuit breakers for the appropriate engine and open core cowl fan cowl and thrust reverser doors (Ref. 71-13-00, P. Block 301). CAUTION : THE OPENING OF FAN THRUST REVERSER COWLS IS ONLY POSSIBLE WHEN _______ FAN AND CORE COWLS ARE OPEN. FOR ALL MAINTENANCE PROCEDURES INSIDE COWLS EXTEND HOLD-OPEN RODS TO HOLD COWLS OPEN.

(2)Position access platform.

B. Deactivation (Ref. Fig. 407 ) (1)Disconnect electrical connector (1), (2) from stow indicator switch P3 (P7). (2)Fit blanks/plugs to switch and electrical connector and stow and secure electrical connector with adhesive tape. (3)Check that stow indicator switch is in the locked position : - plunger retracted - stow cam follower resting an cam lobe. (4)Check: (a)On feedback assembly fitted with a cover that the rigging marks on the feedback cam lobe and the stow cam follower align. (b)On feedback assembly without a cover that the distance from the FWD end of the feedback cam lobe and the cam follower is 6.35±1.5 mm (0.25±0.06 in.) (Ref. Fig. 408 ). (5)Check that the pressure regulating and shut-off valve visual indicator shows valve is in the CLOSED position (Ref. Fig. 409 ).


�� G E � � � � CF6 - 50 � �� WARNING : THE PRESSURE REGULATING AND SHUT-OFF VALVE MUST NOT BE IN THE _______ ?LOCKED CLOSED? POSITION. IF IT IS THE THRUST REVERSER WILL NOT OPERATE WHEN SELECTED. (6)Close fan reverser cowl 452AL (462AL), core cowl 456AR (466AR) and fan cowls 435AL (445AL), 436AL (446AL) (Ref. 78-13-00, P. Block 301). (7)With fan thrust reverser translating cowl in the stowed position (cowl actuators an stow stops) check the gap between the cowl forward edge and the cowl support assembly. Gap must be 0.060 to 0.150 inch (1.52 to 3.81 mm). NOTE : Item (7) confirms that the translation cowl is correctly stowed. ____

C. Close-Up (1)Make certain that working area is clean and clear of tools and miscellaneous items of equipment. (2)Remove access platform. (3)Remove safety clips and tags, close circuit breakers for the appropriate engine and close fan cowl, core cowl and thrust reverser doors (Ref. 71-13-00, P. Block 301). (4)Install a temporary placard in the flight compartment to worn the aircrew that ?REV UNLK? light 9KM (10KM) is inoperative. (5)Make an entry in the aircraft technical log.


�� G E � � � � CF6 - 50 � ��

Fan Reverser Indicator Switches/Feedback System Figure 407


�� G E � � � � CF6 - 50 � ��

Thrust Reverser Stowed Position Check Figure 408


�� G E � � � � CF6 - 50 � ��

Thrust Reverser System Pressure Regulating and Shut-Off Valve Position Check Figure 409 �� EFFECTIVITY: ALL �� 78-00-00 � � � �R Page 415 � � JAS Mar 01/06

�� G E � � � � CF6 - 50 � �� ELECTRICAL (DEPLOY) INDICATOR SWITCH AND THROTTLE AND THRUST REVERSER _____________________________________________________________________ INTERLOCK VALVE OPERATIONAL TEST ________________________________

REFERENCE : MMEL SECTION 1-78, ITEM 3 CAUTION : THIS PROCEDURE IS TO BE USED ACCORDING TO THE REQUIREMENTS OF THE _______ MMEL. WARNING : THRUST REVERSER LEVER POSITION MUST CORRESPOND WITH ACTUAL THRUST _______ REVERSER POSITION, AND ALL PERSONNEL AND EQUIPMENT SHOULD BE CLEAR OF THRUST REVERSER BEFORE OPERATION, OR INJURY TO PERSONNEL CAN RESULT. The engines are equipped with a fan reverser system with the turbine reverser system replaced by a fixed exhaust nozzle.


A. Failure fo REV light circuit.

2. Equipment and Materials _______________________ ------------------------------------------------------------------------------- ITEM DESIGNATION ------------------------------------------------------------------------------- A. Access Platform 3 m (10 ft.) B. Pneumatic Ground Power Unit, Starting C. Electrical Ground Power Unit, 3-Phase, 115/ 200V, 400hz, 90KVA Referenced Procedures - 24-41-00, P. Block 301 External Power - 36-00-00, P. Block 1 Pneumatic System - 71-13-00, P. Block 301 Opening of Cowls


A. Job Set-Up (1)Pressurize pneumatic system (Ref. 36-00-00, P. Block 1). (2)Connect electrical ground power unit and energize the aircraft electrical network (Ref. 24-41-00, P. Block 301). (3)Ensure that the following circuit breakers are closed : ------------------------------------------------------------------------------ PANEL SERVICE IDENT. LOCATION ------------------------------------------------------------------------------ 123VU ENG1/REV/CONTRL 1KM 301/C 2 123VU ENG2/REV/CONTRL 2KM 302/C15 123VU ENG1/REV/WARN/LTS 3KM 302/C 3 123VU ENG2/REV/WARN/LTS 4KM 302/C16 128VU LDG GEAR/FE/WARN/RELAYS 1GB 805/A11 128VU LDG GEAR/RELAYS/RETRACT/CONTRL 2GB 805/A 9 128VU LDG GEAR/FE/WARN/IND 83GB 805/A10 22VU CTR PNL/LDG/GEAR/IND 3GB 207/G10 (4)Open fan cowls 435AL (436AR), 445AL (446AR) (Ref. 71-13-00, P. Block 301).


�� G E � � � � CF6 - 50 � �� B. Test (1)Move thrust reverser control lever to reverse full throttle position and check that (Ref. Fig.410 and 411). - Reverser moves to deployed position in approximately 2 seconds, - Amber REV UNLK warning light 9KM (10KM) comes on. REV UNLK warning light 9KM (10KM) goes off when reverser is fully deployed. (2)When reverser is fully deployed, check that deploy switch cam follower resting on cam lobe and deploy indicator switch plunger is in extended position. NOTE : It should not be possible to actuate thrust reverser control lever ____ past reverse idle position prior to time that deploy indicator switch plunger is in extended position (3)Move thrust reverser control lever back to reverse idle position and check that deploy switch cam follower is resting on cam lobe and deploy indicator switch plunger remains extended. NOTE : Paragraph (3) confirms throttle interlock is working. ____ (4)Move thrust reverser control lever to reversers stowed position and check that : - Reverser moves to fully stowed position in approximately 2 seconds, - Deploy switch cam follower has left the cam lobe and deploy indicator switch plunger is in retracted position and that amber REV UNLK warning light 9 KM (10 KM) comes on, - Amber REV UNLK warning light 9 KM (10 KM) goes off when reverser reaches fully stowed position.

C. Close-Up (1)De-energize the aircraft electrical network and disconnect electrical ground power unit. (2)Depressurize pneumatic system (Ref. 36-00-00, P. Block 1). (3)Close fan cowls (Ref. 71-13-00, P. Block 301). (4)Install a temporary placard in the flight compartment to warn the aircrew that ?REV? light 11 KM (12 KM) is imperative. (5)Make on entry in the aircraft technical log. (6)Make certain that throttle control levers are in idle position.


�� G E � � � � CF6 - 50 � ��

Thrust Reverser Control Figure 410


�� G E � � � � CF6 - 50 � ��

Thrust Reverser Deploy Switch Check Figure 411


�� G E � � � � CF6 - 50 � �� LONG FIXED CORE EXHAUST NOZZLE DESCRIPTION AND OPERATION ________________________________________________________

1. General _______ Long fixed core exhaust nozzle is an aerodynamically designed nozzle that provides a contoured flow path to contour the forward thrust output of the core engine and completes the outer profile of the engine.

2. Component Location __________________ (Ref. Fig. 001 )

Long Fixed Core Exhaust Nozzle Figure 001

------------------------------------------------------------------------------ ITEM NAME PANEL ZONE ACCESS DOOR ------------------------------------------------------------------------------ 1 Aft Center Body 457 2 Long Nozzle/Outer Cowl 458 3 Forward Center Body 467 4 Baffle 468

3. Description (Ref. Fig. 001 ) ___________


�� G E � � � � CF6 - 50 � �� Components of long fixed core exhaust nozzle are the outer cowl assembly, a two piece center body assembly and a baffle.


�� G E � � � � CF6 - 50 � �� LONG FIXED CORE EXHAUST NOZZLE - REMOVAL/INSTALLATION _____________________________________________________

1. General _______ Long fixed core exhaust nozzle is mounted on the turbine rear frame. This procedure covers removal and installation of the nozzle using a hoist and lift fixture. WARNING : MAKE CERTAIN THAT CIRCUIT BREAKERS ARE OPEN, SAFETIED AND TAGGED _______ AND THAT AIR PRESSURE IS NOT APPLIED THROUGH GROUND CONNECTIONS. INADVERTENT ENGINE START OR THRUST REVERSER OPERATION COULD RESULT IN DEATH OR SERIOUS INJURY TO PERSONNEL.

2. Equipment and Materials _______________________ NOTE : Equivalent substitutes may be used instead of the following items. ____ ------------------------------------------------------------------------------- ITEM DESIGNATION ------------------------------------------------------------------------------- A. Access Platform 2 m (6 ft. 7 in.) B. Torque Wrench 20-230 lbf.in. (0.23 - 2.60 m. daN) C. Circuit Breaker Safety ClipsR D. Material C02-058 Anti Seize Compounds, Lubricants and Oils (Ref. 20-32-00) E. Material C02-026 (Ref. 20-32-00) Anti Seize Components Lubricants and Oils 2C6825G01 Fixture, Lift - Turbine Reverser 2C6890G01 Stand, Support - Long Fixed Nozzle 2C8049G01 Fixture Lift - Long Fixed Nozzle Referenced Procedure - 71-13-00, P. Block 301 Cowl Doors


A. Job Set-Up (1)Open, safety and tag circuit breakers for the appropriate engine (Ref. 71-13-00, P. Block 301) (2)Position access platform (3)Open core cowls (Ref. 71-13-00, P. Block 301). WARNING : FOR ALL MAINTENANCE PROCEDURES INSIDE COWLS, EXTEND HOLD-OPEN _______ RODS TO HOLD COWLS OPEN. INADVERTENT CLOSURE OF COWLS COULD RESULT IN SERIOUS INJURY TO PERSONNEL.

R B. If SB GE 78-186 has been incorporated, accomplish the following:R (1)Remove bolt, spacer and nut at the lift brackets located at the 3 andR 9 oQclock positions.R (2)Remove eight bolts securing the secondary retention brackets to theR exhaust nozzle and the turbine rear frame at the 3 and 9 oQclockR positions.

R C. Remove long fixed nozzle assembly as follows : (Ref. Fig. 401, 402 and 403) (1)Remove bolts securing aft centerbody to forward centerbody, retain bolts.


�� G E � � � � CF6 - 50 � ��

Long Fixed Nozzle Removal/Installation Figure 401


�� G E � � � � CF6 - 50 � ��

Long Fixed Nozzle or Turbine Reverser Lift Fixture Figure 402

�� EFFECTIVITY: ALL �� 78-11-00 � � � � 3 � � JAS Jul 30/81

�� G E � � � � CF6 - 50 � ��

Fixture Lift - Long Fixed Nozzle Figure 403


�� G E � � � � CF6 - 50 � ��R Remove aft centerbody. (2)Attach adapters of long fixed nozzle lift fixture 2C8061G01 to 3 and 9 oQclock lift brackets and secure with ball lock pins. (3)Position fixture at rear of nozzle, move forward and attach fixtures to the adapters and secure. Secure the trailing edge of nozzle with clamps of fixture. Using a forklift install long fixed nozzle support stand 2C6890G01. (4)Remove slack with hoist, and remove bolts securing nozzles to T.R.F. aft flange. (5)Move nozzle to storage pallet, remove fixtures. (6)Remove bolts and nuts securing forward centerbody and baffle to T.R.F., place on storage pallet.R (7)Inspect the forward and aft centerbodies (Ref. 78-11-00, P. Block 601).

R D. Install long fixed nozzle assembly as follows : (Ref. Fig.401 and 402) (1)Install longt fixed nozzle lift fixture 2C6825G01 or 2C8049 and support stand 2C6890G01. (2)Engage and secure exhaust nozzle on lift fixture. (3)Position fixture at rear of nozzle, move forward and attach to adapters. Clamp fixture to the trailing edge of nozzle. (4)Adjust the nozzle to a horizontal position. (5)Install forward baffle to T.R.F. studs, secure inner diameter with (24) bolts; TORQUE bolts to between 55 and 70 lbf.in. (0.62 and 0.79 m.daN) (6)Install forward centerbody to T.R.F. flange and secure with (16) bolts and (8) nuts. TORQUE bolts to between 55 and 70 lbf.in. (0.62 and 0.79 m.daN) and nuts 190-230 lbf.in. (2.15 - 2.60 m.daN)R NOTE : Lubricate bolts and nuts with material C02-058 lubricant prior to ____ installation. (7)Lift exhaust nozzle assembly, engage the pylon pin with aircraft fairing socket. Move assembly forward and engage nozzle with aft flange of T.R.F.R (8)Install bolts through the T.R.F. and nozzle flange, except for four boltsR at the 3 and 9 oQclock lift bracket positions. The two bolt locationsR above the lift brackets and the two bolt locations below the liftR brackets should remain vacant at this time. TORQUE to between 55 andR 70 lbf.in. (0.62 and 0.79 m.daN).R NOTE : Lubricate bolts with material C02-058 lubricant prior to ____R installation. (9)Remove lift fixture, and adapters from nozzle and stow.R (10)Install the secondary retention brackets (locally-manufactured per SBR GE 78-186) at the 3 and 9 oQclock lift bracket positions with four bolts.R TORQUE to between 55 and 70 lbf.in. (0.62 and 0.79 m.daN).R NOTE : Lubricate bolts with material C02-058 lubricant prior to ____R installation.R (11)Install bolt, spacer and nut through each lift bracket at the 3 andR 9 oQclock positions. TORQUE nut to 50 lbf.in. (0.56 m.daN) above theR running TORQUE. Do not over TORQUE as this will distort the lift bracketR cross-section.R (12)Install aft centerbody to forward centerbody as follows : (a)Using an accepted unlubricated bolt, check the dry run-on torque in each of nuts (8 off).


�� G E � � � � CF6 - 50 � �� Any nut found to have less than 5 lbf. in. (0.06 m. daN) must be replaced prior to final bolt installation.R (b)Lubricate bolts with material C02-058 lubricant and install. (c)TORQUE bolts to between 55 and 70 lbf. in. (0.62 and 0.78 m. daN) using a cross torque sequence 12-6-3-9 oQclock positions. Continue until all bolts are tightened. NOTE : If a doubler and/or new nutplates have been installed, make ____ certain that (2) threads of bolts extend through nut after final torque application.R (13)Install the proper fairing cover as applicable with bolts. TORQUE bolts to between 55 and 70 lbf. in. (0.62 and 0.78 m.daN)

R E. Close-Up (1)Make certain that working area is clean and clear of tools and miscellaneous items of equipment. (2)Remove safety clips and tags and close circuit breakers for the appropriate engine and close core cowls (Ref. 71-13-00, P. Block 301).


�� G E � � � � CF6 - 50 � �� LONG FIXED CORE EXHAUST NOZZLE - INSPECTION/CHECK _________________________________________________

1. General _______ Long fixed core exhaust nozzle may be inspected while installed or removed. A spot fluorescent penetrant check should by used to confirm suspected cracks.

2. Equipment and Materials _______________________ ------------------------------------------------------------------------------- ITEM DESIGNATION ------------------------------------------------------------------------------- A. Access Platform 2 m (6 ft. 7 in.) B. Circuit Breaker Safety Clips C. Lint Free Cloth Referenced Procedure - 71-13-00, P. Block 301 Cowl Doors


A. Job Set-Up (1)Open, safety and tag circuit breakers for the appropriate engine and open core cowls (Ref. 71-13-00, P. Block 301).

B. Long Fixed Exhaust Nozzle (Ref. Fig.601 and 602) -------------------------------------------------------------------------------- INSPECTION/CHECK MAXIMUM SERVICEABLE LIMITS REMARKS --------------------------------------------------------------------------------R (1)Centerbody Fwd/Aft for :

(a)Cracks forward of mid- No cracks in circumferential Replace centerR stiffener (Forward direction permitted. Axial to body. Cracks may Center Body) diagonal cracks not exceeding be stop drilled 45• from axial allowed to if within limits 0.250 in. (6.35 mm) max. length. Total accumulated length not to exceed 1.0 in. (25.4 mm). Min. separation between cracks 6.0 in. (152.4 mm)

(b)Cracks aft of mid- Cracks 0.25 in. (6.35 mm) Replace center- stiffener (Forward max. length in any direction. body. Cracks may Center Body) Total accumulated length not be stop drilledR to exceed 2.5 in. (63.5 mm) if within limits Min. separation between cracks 4.0 in. (101.6 mm)

(c)Cracks forward of Cracks 0.50 in. (12.7 mm) max. Replace center- circumferential weld length in any direction. Total body. Cracks may (Aft Center Body) accumulated length not to be stop drilled exceed 2.0 in. (50.8 mm). if within limits


�� G E � � � � CF6 - 50 � ��

Long Fixed Core Exhaust NozzleR Figure 601


�� G E � � � � CF6 - 50 � ��

Long Fixed Nozzle - Area ?A? and Centerbody AssemblyR Figure 602


�� G E � � � � CF6 - 50 � �� Min. separation between cracks 4.0 in. (101.6 mm)

(d)Cracks aft of circum- (a)One crack 3 in. (76.2 mm) max. Stop drill all ferential weld (Aft length provided any additional cracks. Replace Center Body) cracks are 0.50 in. (12.7 mm) center body max. length and separated by a after max. of 10 min. of 2 in. (50.8 mm). cycles. (b)Cracks 0.75 in. (19.1 mm) max. Replace center length in any direction. Total body. Cracks may accumulated length not to be stop drilled exceed 3.0 in. (76.2 mm). if within limits Minimum separation between cracks 2 in. (50.8 mm).

(e)Forward flange to skin Max. crack indication dia. Replace weld line (Fwd. center- 0.040 in. (1.02 mm); centerbody. body) Max. accumulative indication length not to exceed 0.080 in. (2.03 mm) per inch of weld; total accumulative indication length not to exceed 6 percent of weld length.

(f)Cracks around spot or Any amount up to 0.25 in. Replace seam welds (6.4 mm) long. Cracks must centerbody. be separated by one in. (25.4 mm). No cracks allowed at aft hat stiffener to shell joint of shell joint of fwd centerbody.

(g)Cracks in flange bolt One crack per 0.250 in. (6.4 Replace fwd. holes or stud holes mm) dia. hole up to 0.100 in. centerbody (2.5 mm) long. No crack allowed in flange around 0.375 in. (9.5 mm) dia. hole.

(h)Cracks in FWD flange Not serviceable Replace fwd. (circumferential) 0.100 in. (2.5 mm) max. Total centerbody (axial) accumulation 2 in. (50.8 mm). Replace fwd. Cracks must be separated by centerbody one in. (25.4 mm)

(i)Dents in fwd. center Any amount up to 0.250 in. Replace fwd. body corrugations (6.4 mm) depth centerbody

(j)Other areas for dents/ 0.250 in. (6.4 mm) max. depth Replace cen- buckles terbody

(k)Deformed edge in aft Any amount, provided no cracks Replace fwd.

�� EFFECTIVITY: ALL �� 78-11-00 � � � �R Page 604 � � JAS Oct 01/91

�� G E � � � � CF6 - 50 � �� radial bolt access holes centerbody

(l)Fwd centerbody aft edge Any amount provided no cracks Replace fwd. for distortion or tears centerbody

(m)Missing/damaged nut Not serviceable Replace nut plates plates - running torque on nut Less than 5 lbf. in. (0.06 Replace nut plates m.daN). Not serviceable plate

(n)Missing bolts on fwd. Max of (3) missing in any Replace bolts as centerbody to TRF attach- 180 degree area. No (2) bolts required. ment allowed missing between adjacent studs.

(o)Missing nuts or studs on No missing nuts/studs allowed Replace parts as TRF required

(p)Missing bolts aft to fwd No missing bolts allowed Replace bolts. centerbody attachment

(q)Rolled edge in aft radial Any amount provided no cracks Replace center- bolt access hole exist body

(r)Cracks in link bracket One crack per hole in one Replace center- mount holes hole at each bracket location. body. Max length of crack 0.10 in. (2.5 mm)

(2)Baffle for :

(a)Cracks in skin Max. length 2 in. (50.8 mm). Replace baffle. Total accumulation 6 in. Stop drill cracks (152.4 mm). Cracks must be if within limits separated by one in. (25.4 mm)

(b)Cracks in bolt holes Three per hole, max. length Replace baffle. 0.50 in. (12.7 mm). Cracked Stop drill cracks hole must be separated by one if within limits good hole

(3)Fixed Nozzle Cowl for :

R (a)Cracks in sheet metal One in. (25 mm) max. length, Replace coreR outer skin total accumulation 6 in. cowlR (152 mm). Cracks must beR separated by 4 in. (102 mm)RR One in. (25 mm) maximum Stop drill theR length, but are spaced less cracks. InspectR than 4.0 in. (102 mm), with after 10


�� G E � � � � CF6 - 50 � �� a total accumulation less additional flight than 3.0 in. (76 mm) cycles. If additional cracks are found or if cracks do not stop at drill holes, replace the cowl. Inspect every 10 cycles or replace core cowl.

(b)Cracks in inner perfo- One in. (25.4 mm) max. total Replace cowl rated skin and hat accumulation 4 in. (101.6 mm). sections Cracks must be separated by 4 in. (101. 6 mm)

(c)Cracks in cowl stiffe- 0.75 in. (19.1 mm) max. length, Replace cowl or ner ring total accumulation 2 in. (50.8 stop drill if mm). Cracks must be separated within limits by 3 in. (76.2 mm)

(d)Missing/damaged rivets 10 % max. may be missing/ Replace rivets damaged. Must be separated by one good rivet

(e)Missing/damaged nut plate Max. of 4 may be missing/ Replace cowl or nut in gang channel damaged, no 2 adjacent allowed

1 Missing or broken Max. of 4 may be missing No.2 Replace bolts _ bolts at FCEN to adjacent allowed TRF flange

(f)Wear on tail fairing 0.03 in. (7.6 mm) max. depth Replace cowl mating surface

(g)Missing or damaged Not serviceable Replace pin tension pins

R (h)Dents or buckles in 0.500 in. (12.7 mm) max. depth Replace cowl area A provided no interference with mating component

(j)Dents or buckles in all 0.250 in. (6.4 mm) max. depth Replace cowl other areas provided no interference with mating component

(k)Cracks in OD of fwd Not serviceable if in circum- Replace cowl. flange ferential direction ; 0.5 in. Stop drill cracks (13 mm) max. length in axial if within limits direction. Total accumulation


�� G E � � � � CF6 - 50 � �� of one in. (25 mm). Cracks must be separated by two in. (51 mm)

(l)Distortion on OD of fwd Any amount provided cowl can Replace cowl flange be installed

(m)Wear 0.015 in. (0.38 mm) max. Replace cowl

(n)Cracks in ?C? channel Cracks up to 12 in. Replace cowl support ring (304.8 mm) max with reinspect every 50 flight cycles NOTE : The ?C? channel support has to be inspected for cracks by ____ RadiographicQs per Non-Destructive Test or by using a flexible borescope with a minimum length of 70 in. (177.8 mm) as an alternate.

**ON A/C 108-999,

After AMP LH 78-002 (o)Metal chips coming Any amount May be kept * only from insulator on the wing * foil (0.1 mm thick) if there is no * impact on LPT * blades *

**ON A/C ALL

(p)Wear on retention 0.060 in. (1.52 mm) maximum Replace bracket bracket depth

(q)Wear on retention 0.060 in. (1.52 mm) maximum Replace spacer bolt spacers depth

(4)Core Cowl Support for :

(a)Cracks in sheet metal One in. (25 mm) max. length, Replace core cowl outer skin total accumulation 6 in. support. (152 mm). Cracks must be separated by 4 in. (102 mm)

(b)Wear 0.015 in. (0.38 mm) max. Replace core cowl depth. support.

C. Close-Up (1)Make certain that working area is clean and clear of tools and miscellaneous items of equipment. (2)Remove safety clips and tags, and close circuit breakers for the appropriate engine and close core cowls (Ref. 71-13-00, P. Block 301). (3)Remove access platforms.


�� G E � � � � CF6 - 50 � �� SHORT FIXED CORE EXHAUST NOZZLE-DESCRIPTION AND OPERATION _________________________________________________________

1. General _______ Short fixed core exhaust nozzle is an aerodynamically designed nozzle that provides a contoured flow path to contour the forward thrust output of the core engine and completes the outer profile of the engine.

2. Component Location __________________ (Ref. Fig. 001 )

Short Fixed Core Exhaust NozzleR Figure 001

------------------------------------------------------------------------------ ITEM NAME PANEL ZONE ACCESS DOOR ------------------------------------------------------------------------------ 1 Aft Center Body 457 2 Short Fixed Nozzle/Outer Cowl 458 3 Forward Center Body 467 4 Baffle 468

3. Description (Ref. Fig. 001 ) ___________


�� G E � � � � CF6 - 50 � ��R A. Exhaust Nozzle CowlR The exhaust cowl provides the outer contour as well as the outer wall forR the core engine exhaust discharge and is bolted to the aft flange of theR turbine rear frame. The inner flow path surface is manufactured fromR perforated sound suppressing corrugated AMS 5599 that provides a smoothR surface.

R B. Center BodyR The center body consists of a two piece center plug mounted to the turbineR rear frame strut hub. The forward and aft center body provides the innerR flow path and is manufactured from perforated corrugated AMS 5599.R NOTE : The SFCEN as a system is physically interchangeable with the LFCEN ____R or Turbine Reverser, because it bolts to the Turbine Rear frameR flanges with same hardware.R Modifications to scavenge tubes, seal drain tubes, and fire wallR brackets must be accomplished prior to the use of a SFCEN.R New cowl door to nozzle interface is required between the pylon toR nozzle fairing and the outer contour of the SFCEN.


�� G E � � � � CF6 - 50 � �� SHORT FIXED CORE EXHAUST NOZZLE - REMOVAL/INSTALLATION ______________________________________________________

1. General _______ Short fixed core exhaust nozzle is mounted on the turbine rear frame. This procedure covers removal and installation of the nozzle using a hoist and lift fixture. WARNING : MAKE CERTAIN THAT CIRCUIT BREAKERS ARE OPEN, SAFETIED AND TAGGED _______ AND THAT AIR PRESSURE IS NOT APPLIED THROUGH GROUND CONNECTIONS. INADVERTENT ENGINE START OR THRUST REVERSER OPERATION COULD RESULT IN DEATH OR SERIOUS INJURY TO PERSONNEL.

2. Equipment and Materials _______________________ NOTE : Equivalent substitutes may be used instead of the following items. ____ ------------------------------------------------------------------------------- ITEM DESIGNATION ------------------------------------------------------------------------------- A. Access Platform 2 m (6 ft. 7 in.) B. Torque Wrench 20-230 lbf.in. (0.23 - 2.60 m. daN) C. Circuit Breaker Safety ClipsR D. Material C02-058 Anti Seize Compounds, Lubricants and Oils (Ref. 20-32-00) E. Material C02-026 (Ref. 20-32-00) 2C8061G01 Fixture, Lift - Short Fixed Nozzle Referenced Procedure - 71-13-00, P. Block 301 Cowl Doors


A. Job Set-Up (1)Open, safety and tag circuit breakers for the appropriate engine (Ref. 71-13-00, P. Block 301).

(2)Position access platform (3)Open core cowls (Ref. 71-13-00, P. Block 301). WARNING : FOR ALL MAINTENANCE PROCEDURES INSIDE COWLS, EXTEND HOLD-OPEN _______ RODS TO HOLD COWLS OPEN. INADVERTENT CLOSURE OF COWLS COULD RESULT IN SERIOUS INJURY TO PERSONNEL.

B. Remove short fixed nozzle assembly as follows : (Ref. Fig.401 and 402) (1)Remove bolts securing aft centerbody to forward centerbody, retain bolts. (2)Attach adapters of short fixed nozzle lift fixture 2C8061G01 to 3 and 9 oQclock lift brackets and secure with ball lock pins. (3)Position fixture at rear of nozzle, move forward and attach fixtures to the adapters and secure. Secure the trailing edge of nozzle with clamps of fixture. Using a forklift install short fixed nozzle support stand 2C6890G01. (4)Remove slack with hoist, and remove bolts securing nozzles to T.R.F. aft flange. (5)Move nozzle to storage pallet, remove fixtures.


�� G E � � � � CF6 - 50 � ��

Short Fixed Nozzle Removal/Installation Figure 401


�� G E � � � � CF6 - 50 � ��

Short Fixed Nozzle Lift FixtureR Figure 402


�� G E � � � � CF6 - 50 � �� (6)Remove bolts and nuts securing forward centerbody and baffle to T.R.F., place on storage pallet. (7)Inspect the entire centerbody assembly (Ref. 78-12-00, P. Block 601).

C. Install short fixed nozzle assembly as follows : (Ref. Fig.401 and 402) (1)Install short fixed nozzle lift fixture 2C8061G01 and support stand 2C6890G01. (2)Engage and secure exhaust nozzle on lift fixture. (3)Position fixture at rear of nozzle, move forward and attach to adapters. Clamp fixture to the trailing edge of nozzle. (4)Adjust the nozzle to a horizontal position. (5)Install forward baffle to T.R.F. studs, secure inner diameter with (24) bolts; TORQUE bolts to between 55 and 70 lbf.in. (0.62 and 0.79 m.daN) (6)Install forward centerbody to T.R.F. flange and secure with (16) bolts and (8) nuts. TORQUE bolts to between 55 and 70 lbf.in. (0.62 and 0.79 m.daN) and nuts 190-230 lbf.in. (2.15 - 2.60 m.daN)R NOTE : Lubricate bolts and nuts with material C02-058 lubricant prior to ____ installation. (7)Lift exhaust nozzle assembly, engage the pylon pin with aircraft fairing socket. Move assembly forward and engage nozzle with aft flange of T.R.F. (8)Install bolts through the T.R.F. and nozzle flange, TORQUE to between 55 and 70 lbf.in. (0.62 and 0.79 m.daN)R NOTE : Lubricate bolts with material C02-058 lubricant prior to ____ installation. (9)Remove lift fixture, and adapters from nozzle and stow. (10)Install aft centerbody to forward centerbody as follows : (a)Using an accepted unlubricated bolt, check the dry run-on torque in each of nuts (16 off). Any nut found to have less than 5 lbf. in. (0.06 m. daN) must be replaced prior to final bolt installation.R (b)Lubricate bolts with material C02-058 lubricant and install. (c)TORQUE bolts to between 55 and 70 lbf. in. (0.62 and 0.78 m. daN) using a cross torque sequence 12-6-3-9 oQclock positions. Continue until all bolts are tightened.

D. Close-Up (1)Make certain that working area is clean and clear of tools and miscellaneous items of equipment. (2)Remove access platform (3)Remove safety clips and tags, close circuit breakers for the appropriate engine and close core cowls (Ref. 71-13-00, P. Block 301).


�� G E � � � � CF6 - 50 � �� SHORT FIXED CORE EXHAUST NOZZLE - INSPECTION/CHECK __________________________________________________

1. General _______ Short fixed core exhaust nozzle may be inspected while installed or removed. A spot fluorescent penetrant check should by used to confirm suspected cracks.

2. Equipment and Materials _______________________ ------------------------------------------------------------------------------- ITEM DESIGNATION ------------------------------------------------------------------------------- A. Access Platform 2 m (6 ft. 7 in.) B. Circuit Breaker Safety Clips C. Lint Free Cloth Referenced Procedures - 71-13-00, P. Block 301 Cowl Doors - 72-00-00, P. Block 601 Engine - General - 72-58-00, P. Block 201 Turbine Rear Frame Assembly


A. Job Set-Up (1)Open, safety and tag circuit breakers for the appropriate engine and open core cowls (Ref. 71-13-00, P. Block 301).

B. Short Fixed Exhaust Nozzle (Ref. Fig. 601 ) -------------------------------------------------------------------------------- INSPECTION/CHECK MAXIMUM SERVICEABLE LIMITS REMARKS -------------------------------------------------------------------------------- (1)Centerbody Fwd/Aft Sheet Metal for :

(a)Cracks forward of mid- No cracks in circumferential Replace center stiffener mounts (For- direction permitted. Axial to body. Cracks may ward Center Body) diagonal cracks not exceeding be stop drilled 45• from axial allowed to if within limits 0.250 in. (6.35 mm) max. length. Total accumulated length not to exceed 1.0 in. (25.4 mm). Min. separation between cracks 6.0 in. (152.4 mm)

(b)Cracks aft of mid-stif- Cracks 0.25 in. (6.4 mm) max. Replace center- fener (Forward Center- length in any direction. Total body. Cracks may body) accumulated length not to be stop drilled exceed 1.5 in. (38.1 mm). Min. if within limits separation between cracks 4.0 in. (101.6 mm)

(c)Cracks forward of cir- Cracks 0.50 in. (12.7 mm) max. Replace center-

�� EFFECTIVITY: ALL �� 78-12-00 � � � �R Page 601 � � JAS Jan 01/88

�� G E � � � � CF6 - 50 � ��

Short Fixed Core Exhaust NozzleR Figure 601

cumferential weld (Aft length in any direction. Total body. Cracks may Center Body) accumulated length not to be stop drilled exceed 2.0 in. (50.8 mm). if within limits Min. separation between cracks 4.0 in. (101.6 mm)

(d)Cracks aft of circum- (a)One crack 3 in. (76.2 mm) max. Stop drill all ferential weld (Aft length provided any additional cracks. Replace Center Body) cracks are 0.50 in. (12.7 mm) centerbody after max. length and separated by max. of 10 a min. of 2 in. (50l8 mm). cycles (b)Cracks 0.75 in. (19.1 mm) Replace center max. length in any direction. body. Cracks Total accumulated length may be stop not to exceed 3.0 in. (76.2 drilled if mm). Minimum separation within limits between cracks 2 in. (50.8 mm)

(e)Forward flange to skin Max. crack indication dia. Replace

�� EFFECTIVITY: ALL �� 78-12-00 � � � � Page 602 � � JAS Jan 01/88

�� G E � � � � CF6 - 50 � �� weld line (Fwd. center- 0.040 in. (1.02 mm); centerbody body) Max. accumulative indication length not to exceed 0.080 in. (2.03 mm) per inch of weld; total accumulative indication length not to exceed 6 percent of weld length.

(f)Cracks around spot Any amount up to 0.50 in. Replace center or seam welds (12.7 mm) long. body. Cracks must be separated by one inch (25.4 mm). No cracks allowed at aft hat stiffener to shell joint of fwd center body

(g)Cracks in flange bolt One crack per 0.250 in. (6.4 Replace fwd. holes or stud holes mm) dia. hole up to 0.100 in. centerbody (2.5 mm) long. No crack allowed in flange around 0.375 in. (9.5 mm) dia. hole.

(h)Cracks in flange forward Not serviceable Replace fwd. flange (circumferential) centerbody (axial) 0.100 in. (2.5 mm) max. Total Replace fwd. accumulation 2 in. (50.8 mm). centerbody Cracks must be separated by one in. (25.4 mm)

(i)Dents in fwd. center body Any amount up to 0.250 in. Replace fwd. corrugations (6.4 mm) depth centerbody

(j)Other areas for dents/ 0.250 in. (6.4 mm) max. depth Replace center- buckles body half.

(k)Deformed edge in radial Any amount, except no cracks Replace fwd. bolt access holes allowed centerbody

(l)Fwd centerbody aft edge Any amount provided no cracks Replace fwd. for distortion or tears centerbody

(m)Missing/damaged nut Not serviceable Replace aft plates centerbody

(2)Baffle for :

(a)Cracks in skin Max. length 2 in. (50.8 mm). Replace baffle. Total accumulation 6 in. Stop drill cracks (152.4 mm). Cracks must be if within limits separated by one in. (25.4 mm)


�� G E � � � � CF6 - 50 � �� (b)Cracks in bolt holes Three per hole, max. length Replace baffle. 0.050 in. (12.7 mm). Cracked Stop drill cracks hole must be separated by one if within limits good hole

(3)Fixed Nozzle Cowl for

(a)Cracks in sheet metal One in. (25.4 mm) max. length, Replace cowl outer skin total accumulation 6 in. (152.4 mm). Cracks must be separated by 4 in. (101.6 mm)

(b)Cracks in inner perfo- One in. (25.4 mm) max. total Replace cowl rated skin and hat accumulation 4 in. (101.6 mm). sections Cracks must be separated by 4 in. (101. 6 mm)

(c)Missing/damaged rivets Max. of 2 may be missing/ Replace cowl in wear pads damaged. Must not be in same axial row

(d)Dents or buckles in all 0.250 in. (6.4 mm) max. depth Replace cowl other areas provided no interference with mating component

(e)Cracks in OD of fwd Not serviceable if in circum- Replace cowl. flange ferential direction ; 0.5 in. Stop drill cracks (12.7 mm) max. length in axial if within limits direction. Total accumulation of one in. (25.4 mm). Cracks must be separated by two in. (50.8 mm)

(f)Distortion on OD of fwd Any amount provided cowl can be flange installed

(g)Wear in wear pads No wear through allowed Replace cowl

R **ON A/C 108-999,

After AMP LH 78-002 (h)Metal chips coming Any amount May be kept * only from insulator on the wing if * foil (0.1 mm thick) there is no * impact on LPT * blades *

R **ON A/C ALL

�� EFFECTIVITY: ALL �� 78-12-00 � � � � 4 � � JAS Oct 01/92

�� G E � � � � CF6 - 50 � �� (4)Fwd Centerbody to Turbine Rear Frame for :

(a)Missing or broken bolts 3 missing or broken in any Replace missing on fwd centerbody to 180• segment except, No.2 or broken bolts turbine rear frame missing or broken between adjacent studs

(b)Missing or broken studs Not serviceable Remove, discard in turbine rear frame and replace all 8 studs per paragraph 3.C (Ref. 72-58-00, P. Block 201) or refer to 72-00-00, P. Block 601 Over- Serviceable- Limit-Extension.

C. Close-Up (1)Make certain that working area is clean and clear of tools and miscellaneous items of equipment. (2)Remove access platforms. (3)Remove safety clips and tags, close circuit breakers for the appropriate engine and close core cowls (Ref. 71-13-00, P. Block 301).


�� G E � � � � CF6 - 50 � �� THRUST REVERSER - DESCRIPTION AND OPERATION ___________________________________________

R 1. General _______ The thrust reverser system is used to deflect laterally and redirect part of the engine exhaust power to the front of the engine. This system is controlled from the flight compartment by a lever hinged onto throttle control lever and is operated by a pneumatic drive actuator supplied with air bled from the fourteenth stage of engine compressor, or from the pneumatic system. The pneumatic drive actuator is connected to ball screw actuators controlling thrust reverser operation via flexible drive shafts and gearboxes. Warning lights in the flight compartment indicate thrust reverser position.

R A. Fan Thrust Reverser (Ref. Fig. 001 ) The fan thrust reverser is composed of two halves hinged to the engine pylon. Each reverser half includes blocker doors, a translating cowl, a fixed cowl and vaned deflectors. The blocker doors are attached to the translating cowls and the blocker door links are attached to the inner cowls. The two fan thrust reverser halves when latched closed delimit the flow path.

2. Component Location __________________R (Ref. Fig.002 and 003) ------------------------------------------------------------------------------ ITEM NAME PANEL ZONE ACCESS DOOR ------------------------------------------------------------------------------ 1 Thrust Reverser - Fan, 451 451AL LH Side (Ref. 78-32-00, 461 461AL P. Block 1) 3 Thrust Reverser - Fan, 452 452AR RH Side (Ref. 78-32-00, 462 462AR P. Block 1) 5 Nozzle - Fixed Exhaust 457 (Ref. 78-33-00, 458 P. Block 1) 467 468

3. Description ___________R (Ref. Fig. 004 ) The thrust reverser system features : - a mechanical control system - a pneumatic supply system - a pneumatic drive actuator (Ref. 78-31-01, P. Block 201)R - a fan thrust reverser (Ref. 78-32-00, P. Block 1) - a feedback system (Ref. 78-31-00, P. Block 1) - a pneumatic switcher valve (Ref. 78-31-07, P. Block 201) - an indicating system (Ref. 78-31-00, P. Block 1)


�� G E � � � � CF6 - 50 � ��

Fan Thrust ReverserR Figure 001


�� G E � � � � CF6 - 50 � ��

Thrust Reverser System with Fixed Exhaust Nozzle - Fixed Exhaust NozzleR Figure 002 �� EFFECTIVITY: ALL �� 78-30-00 � � � � Page 3 � � JAS Apr 30/80

�� G E � � � � CF6 - 50 � ��

Fixed Exhaust Nozzle - LocationR Figure 003


�� G E � � � � CF6 - 50 � ��

Thrust Reverser System with Fixed Exhaust Nozzle - Block DiagramR Figure 004 �� EFFECTIVITY: ALL �� 78-30-00 � � � � Page 5 � � JAS Apr 30/80

�� G E � � � � CF6 - 50 � �� 4. Operation _________

A. Thrust Reverser Deployment Moving thrust reverser control lever up to the locking position opens the pneumatic valve which supplies the pneumatic drive actuator with pressurized air from the engine or from the aircraft pneumatic system. A directional control valve controls the directional butterfly in the pneumatic drive actuator which starts to operate. The pneumatic drive actuator power is transmitted to the thrust reverser ball screw actuators via flexible drive shafts. The ball screw actuators convert the rotational movement of the flexible drive shafts into a linear movement transmitted directly to the translating cowls. When moving, the translating cowls drive the blocker doors in the flow path and uncover the vaned deflectors. As soon as the translating cowls are deployed 90• the interlock valve opens, with the following results : - the interlock actuator is energized, and frees the thrust reverser control lever, which can then be moved until reverse full throttle position (67•50Q) is reached. - a pneumatic, correction signal is sent to VBV (Variable By-pass Valves) control device. NOTE : The correction signal increases valve opening, in order to prevent ____ the compressor stalling At the end of cowl translation, the blocker doors are fully deployed in the flow path, thereby deflecting laterally part of the engine exhaust power onto the vaned deflectors which redirect and evacuate the exhaust to the front of the engine. The engine therefore operates in reverse thrust mode.

B. Thrust Reverser Stowage Moving thrust reverser control lever back to the 0• position causes opening of the directional control valve. This operation causes deflection of the butterfly thereby reversing pneumatic drive actuator rotation. The pneumatic supply system delivers pressurized air to the pneumatic drive actuator during thrust reverser stowage sequence. When moving, the cowls gradually drive the blocker doors back to the stow position and cover the vaned deflectors. When the thrust reversers are fully stowed, the pneumatic supply system closes the air supply to the pneumatic drive actuator. Fan air flow and exhaust gases are directly evacuated towards the rear of the engine : the engine then operates in forward thrust mode. NOTE : The feedback system is composed of cam followers controlling ____ throttle and thrust reverser interlock valve, pneumatic switcher valve and indicator switches.

5. Indicating __________

A. The thrust reverser indicating system features :R (Ref. Fig. 005 )R - a green REV indicator light 11KM (12KM) located on panel 230VU - an amber REV UNLK warning light 9KM (10KM) located on panel 230VU - indicator switches When the thrust reversers are fully stowed, the green REV indicator lightR 11KM (12KM) and the amber REV UNLK warning light 9KM (10KM) go off


�� G E � � � � CF6 - 50 � �� As soon as the overpressure and shut-off valve is open, the amber REV UNLKR warning light 9KM (10KM) comes on and remains on during the whole displacement. When the fan reversers are 90% deployed, the green REV indicator light 11KMR (12KM) comes on and the full reverse thrust can be selected. When the fan reversers are fully deployed and the overpressure and shut-offR valve is closed, the amber REV UNLK warning light 9KM (10KM) goes off During stowage, as soon as the overpressure and shut-off valve is open, theR amber REV UNLK warning light 9KM (10KM) comes on and the green REVR indicator light 11KM (12KM) goes off.R The amber REV UNLK warning light 9KM (10KM) remains on during the wholeR thrust reverser stowage sequence, and goes off when the overpressure and shut-off valve closes, and the thrust reversers are locked in stowed position. NOTE : During this operation, the amber REV UNLK warning light 9KM (10KM) ____R is on when at least one of the fan reverser halves is moving.


�� G E � � � � CF6 - 50 � ��

Thrust Reverser System with Fixed Exhaust Nozzle - IndicatingR Figure 005 �� EFFECTIVITY: ALL �� 78-30-00 � � � � Page 8 � � JAS Oct 30/83

�� G E � � � � CF6 - 50 � �� THRUST REVERSER - FAULT ISOLATION _________________________________

Refer to FI/MM 78-30-00, P. Block 101.

�� EFFECTIVITY: ALL �� 78-30-00 � � � �R Page 101 � � JAS Jul 30/82

�� G E � � � � CF6 - 50 � �� THRUST REVERSER - ADJUSTMENT/TEST _________________________________

NOTE : Adjustment/test procedures for LH and RH thrust reverser controls are ____ identical.

The thrust reverser uses the same cable system as the throttle system for which complete rigging instructions are contained in 76-11-00, P. Block 501. All thrust reverser adjustment/test procedures are accomplished with the assumption that the throttle system is properly adjusted.


A. Adjustment/test after removal of major components.

2. Equipment and Materials _______________________ ------------------------------------------------------------------------------- ITEM DESIGNATION ------------------------------------------------------------------------------- A. Access Platform 3 m (10ft.) B. Pneumatic Ground Power Unit, Starting C. Electrical Ground Power Unit, 3-Phase, 115/200V, 400 Hz, 90KVA D. Torque Wrench - 20-40 lbf.in. (0.22-045 m.daN) E. 2C-6900 Splined Adapter (5/16 inch, 12 point-drive) F. Circuit Breaker Safety Clips G. Corrosion-Resistant Steel Lockwire Dia. 0.032 in. (0.813 mm) Referenced ProceduresR - 23-41-00, P. Block 1 Service Interphone - 24-41-00, P. Block 301 External Power - 36-00-00, P. Block 1 Pneumatic - 71-13-00, P. Block 301 Cowl Doors


�� G E � � � � CF6 - 50 � �� 3. Procedure _________

A. Job Set-Up (1)Open, safety and tag circuit breakers for the appropriate engine and open engine cowls (Ref. 71-13-00, P. Block 301). (2)Display warning notice on panel 123VU to prohibit maneuvers. (3)Position access platforms under engine. (4)Position and connect pneumatic ground power unit (Ref. 36-00-00, P. Block 1) on pneumatic Hp ground connections. (5)Position and connect electrical ground power unit (Ref. 24-41-00, P. Block 301).

4. Adjustment __________ CAUTION : FOR ALL MAINTENANCE PROCEDURES INSIDE COWLS EXTEND HOLD-OPEN RODS _______ TO HOLD COWLS OPEN. MAKE CERTAIN CIRCUIT BREAKERS ARE OPEN, SAFETIED AND TAGGED BEFORE ATTEMPTING MAINTENANCE PROCEDURES. INADVERTENT ENGINE START OR THRUST REVERSER OPERATION COULD RESULT IN DEATH OR SERIOUS INJURY TO PERSONNEL.

A. Adjustment of Fan Thrust Reverser System (Ref. Fig.501 and 502) (1)Remove flexible drive shaft clamps adjacent to fan reverser center actuators. (2)On both sides of fan thrust reverser cowl, disconnect fan reverser flexible drive shaft (1) from center ballscrew actuator gearbox. (3)Note applicable.

R **ON A/C 001-103, 106-999,

A. Adjustment of Fan Thrust Reverser System (Ref. Fig.501 and 503) (1)Remove flexible drive shaft clamps adjacent to fan reverser center actuators. (2)On both sides of fan thrust reverser cowl, disconnect fan reverser flexible drive shaft (1) from center ballscrew actuator gearbox. (3)Manually release the TRAS lock. (a)Pull the T-handle approximately 0.35 inch (8.9 mm). (b)Remove the manual release lever from the retaining clip, and turn the lever to engage the collar. (c)Release the T-handle.

R **ON A/C ALL

(4)Remove cover from bottom of fan reverser center ballscrew actuator gearbox. Discard gasket. (5)Insert splined adapter 2C-6900 in fan reverser center ballscrew actuator gearbox socket and hold gearbox on stow stop. (6)Rotate flexible drive shaft core a maximum of one spline tooth in deploy direction to align with gearbox and insert flexible drive shaft. CAUTION : DO NOT ROTATE FLEXIBLE DRIVE SHAFT CORE MORE THAN ONE SPLINE _______ TOOTH IN DEPLOY DIRECTION TO ALIGN WITH GEARBOX SOCKET.


�� G E � � � � CF6 - 50 � �� (7)TORQUE flexible drive shaft flange bolts to between 24 and 27 lbf.in. (0.27 and 0.30 m.daN). Safety bolt with 0.032 in. (0.813 mm) dia. corrosion-resistant steel lockwire. (8)Install cover and new gasket on gearbox. TORQUE bolt to between 24 and 27 lbf.in. (0.27 and 0.30 m.daN). Safety bolts with 0.032 in. (0.813 mm) dia. corrosion-resistant steel lockwire. CAUTION : IF FLEXIBLE DRIVE SHAFT BETWEEN PNEUMATIC DRIVE ACTUATOR _______ AND CENTER BALLSCREW ACTUATOR GEARBOX ON ONE FAN REVERSER HALF IS DISCONNECTED, GEARBOX TO DRIVE ACTUATOR FLEXIBLE DRIVE SHAFT ON BOTH REVERSER HALVES MUST BE RIGGED TO PREVENT PRELOAD. (9)Install flexible drive shaft clamps adjacent to fan reverser center actuator.

B. Close-Up (1)Check that all connections and fittings are secure and safetied. (2)Not applicable.

R **ON A/C 001-103, 106-999,

(2)Manually engage the TRAS lock. (a)Pull the T-handle approximately 0.1 inch (2.54 mm). (b)Turn the manual release lever away from the fan cowl. (c)Engage the manual release lever in the retaining clip. (d)Release the T-handle.

R **ON A/C ALL

(3)Close engine cowls (Ref. 71-13-00, P.Block 301). (4)Remove access platforms WARNING : THRUST REVERSER LEVER POSITION MUST CORRESPOND WITH _______ ACTUAL THRUST REVERSER POSITION, AND ALL PERSONNEL AND EQUIP- SHOULD BE CLEAR OF THRUST REVERSER BEFORE OPERATION, OR INJURY TO PERSONNEL CAN RESULT.

C. Tests (1)Pressurize pneumatic system (Ref. 36-00-00, P. Block 1). (2)Connect electrical ground power unit and energize the aircraft electrical network (Ref. 24-41-00, P. Block 301). (3)Remove safety clips and tags, and close circuit breakers 1KM and 2KM.

(4)Move throttle control lever to idle position. (5)Move thrust reverser control lever to reverse idle position and check that (Ref. Fig. 502 ) :

R **ON A/C 001-103, 106-999,

(5)Move thrust reverser control lever to reverse idle position and check that (Ref. Fig. 503 ) :


�� G E � � � � CF6 - 50 � ��

Engine Equipped with Fixed Exhaust Nozzle - Adjustment Points Figure 501


�� G E � � � � CF6 - 50 � ��

R **ON A/C ALL

- the reversers move towards the fully deployed position in 6 seconds max. (the reversers reach 90% of their travel in 2 seconds approximately). - amber REV/UNLK warning light 9KM (10KM) comes on then goes off when the reversers are fully deployed. - green REV indicator light 11KM (12KM) comes on when the reversers reach 90% of the deploy travel. NOTE : Thrust reverser control lever cannot be moved beyond reverse ____ idle position as long as REV indicator light 11KM (12KM) is not on.

R **ON A/C 001-103, 106-999,

R **ON A/C ALL

(6)Move thrust reverser control lever beyond reverse idle position and check that green REV indicator light 11KM (12KM) remains on. NOTE : Step (6) confirms that throttle interlock is operating. ____ (7)Move thrust reverser control lever towards reverser stowed position and check that : - the reversers move towards the stowed position in 7 seconds max. (the reversers reach 90% of the stow travel in 3 seconds approximately). - amber REV UNLK warning light 9KM (10KM) comes on then goes off when the reversers are in stowed position. - green REV indicator light 11KM (12KM) goes off when the reversers reach 10% of the stow travel.

E. Close-Up (1)De-energize the aircraft electrical network and disconnect electrical ground power unit. (2)Depressurize pneumatic system (Ref. 36-00-00, P. Block 1). (3)Remove warning notice from panel 123VU. Remove safety clips and tags, and close circuit breakers 2KG, 1JH and 2JH (4)Make certain that throttle control levers are in idle position.

5. Thrust Reverser Translating Cowl Auto Re-Stow Function Check (Three-light _________________________________________________________________________ Indication Circuit Only) ________________________ NOTE : The auto re-stow function check is done two times. To provide ____ sufficient time for correct verification of the flight compartment light indications, the first check of the auto re-stow function is done with the translating cowl deployed 10.0 in. (254 mm). To make sure that the auto re-stow function is prompt, the second check is done with the translating cowl deployed 1.0 in. (25.4 mm). WARNING : MAKE SURE YOU OPEN, TAG AND SAFETY THE APPLICABLE CIRCUIT BREAKERS _______ BEFORE YOU START THE MAINTENANCE PROCEDURES. THIS WILL PREVENT


�� G E � � � � CF6 - 50 � ��

Thrust Reverser Control Figure 502


�� G E � � � � CF6 - 50 � ��

Thrust Reverser Control - Post SB 78-022 Figure 503 ��R �EFFECTIVITY: 001-103, 106-999, �� 78-30-00 � � � � Page 507 � � JAS Mar 01/07

�� G E � � � � CF6 - 50 � �� ACCIDENTAL ENGINE START OR THRUST REVERSER OPERATION WHICH CAN CAUSE INJURIES TO PERSONS AND DAMAGE TO EQUIPMENT.

A. Open, safety and tag the circuit breakers for the appropriate engine.

B. To check the auto re-stow system on the right reverser half, disconnect the electrical cable from the left stow switch (Ref. Fig. 504 ). NOTE : The stow switch is the forward-most plunger-type switch mechanism ____ on the underside of each feedback mechanism.

C. Not applicable.

R **ON A/C 001-103, 106-999,

C. Manually release the TRAS lock (Ref. Fig. 503 ) (1)Pull the T-handle approximately 0.35 inch (8.9 mm). (2)Remove the manual release lever from the retaining clip, and turn the lever to engage the collar. (3)Release the T-handle.

R **ON A/C ALL

D. While one person manually releases the brake on the Pneumatic Drive Motor (PDM), manually deploy the translating cowl approximately 10.0 in. (254 mm) from the stowed position (Ref. Fig. 505 ).

E. Connect the interphone system between the flight compartment and the applicable engine area (Ref. 23-41-00, P. Block 1). WARNING : MOVE PERSONS AND EQUIPMENT AWAY FROM THE AREA AROUND THE THRUST _______ REVERSER. THIS WILL PREVENT INJURY TO PERSONS OR DAMAGE TO EQUIPMENT IF THERE IS UNCOMMANDED THRUST REVERSER OPERATION. CAUTION : BEFORE YOU OPERATE THE THRUST REVERSER SYSTEM, MAKE SURE THE _______ TRANSLATING COWLS ARE CLEAR TO DEPLOY AND STOW.

F. Connect electrical ground power unit and energize the aircraft electrical network (Ref. 24-41-00, P. Block 301). WARNING : BEFORE YOU DO INSPECTION OR MAINTENANCE PROCEDURES WITH THE _______ TRANSLATING COWL DEPLOYED, MAKE SURE YOU REMOVE THE AIR SUPPLY FROM THE THRUST REVERSER SYSTEM. IF THE AIR SUPPLY IS CONNECTED, LOSS OF ELECTRICAL POWER WILL CAUSE THE THRUST REVERSER TO STOW. INADVERTENT STOW CAN CAUSE DEATH OR SERIOUS INJURY. WARNING : MOVE PERSONS AND EQUIPMENT AWAY FROM THE AREA AROUND THE THRUST _______ REVERSER. THIS WILL PREVENT INJURY TO PERSONS OR DAMAGE TO EQUIPMENT IF THERE IS UNCOMMANDED THRUST REVERSER OPERATION.

G. Connect pneumatic ground power unit to the aircraft ground air connection or Auxiliary Power Unit (APU) (Ref. 36-00-00, P. Block 1). Make sure the thrust reverser levers are in the forward thrust position.


�� G E � � � � CF6 - 50 � ��

Stow Switch Location Figure 504


�� G E � � � � CF6 - 50 � ��

Pneumatic Drive Motor Figure 505


�� G E � � � � CF6 - 50 � �� Close the applicable circuit breakers and check that in flight compartment the amber REV UNLK indication on the center instrument panel and the amber REVERSER VALVE OPEN indication on the flight engineerQs panel are on. The translating cowls must go back to the stowed position and the amber REV UNLK and the amber REVERSER VALVE OPEN indications must go off. If necessary, refer to the A300 Fault Isolation Manual for troubleshooting instructions.

H. Disconnect the pneumatic ground power unit from the aircraft ground air connection or APU (Ref. 36-00-00, P. Block 1).

I. Open, safety and tag the applicable circuit breakers.

J. De-energize the aircraft electrical network and disconnect electrical ground power unit (Ref. 24-41-00, P. Block 301).

K. Not applicable.

R **ON A/C 001-103, 106-999,

K. Manually release the TRAS lock (Ref. Fig. 503 ) (1)Pull the T-handle approximately 0.35 inch (8.9 mm). (2)Remove the manual release lever from the retaining clip, and turn the lever to engage the collar. (3)Release the T-handle.

R **ON A/C ALL

L. While one person manually releases the brake on the Pneumatic Drive Motor (PDM), manually deploy the translating cowl at least 1.0 in. (25.4 mm) from the stowed position (Ref. Fig. 505 ). WARNING : MOVE PERSONS AND EQUIPMENT AWAY FROM THE AREA AROUND THE THRUST _______ REVERSER. THIS WILL PREVENT INJURY TO PERSONS OR DAMAGE TO EQUIPMENT IF THERE IS UNCOMMANDED THRUST REVERSER OPERATION. CAUTION : BEFORE YOU OPERATE THE THRUST REVERSER SYSTEM, MAKE SURE THE _______ TRANSLATING COWLS ARE CLEAR TO DEPLOY AND STOW.

M. Connect electrical ground power unit and energize the aircraft electrical network (Ref. 24-41-00, P. Block 301). WARNING : BEFORE YOU DO INSPECTION OR MAINTENANCE PROCEDURES WITH THE _______ TRANSLATING COWL DEPLOYED, MAKE SURE YOU REMOVE THE AIR SUPPLY FROM THE THRUST REVERSER SYSTEM. IF THE AIR SUPPLY IS CONNECTED, LOSS OF ELECTRICAL POWER WILL CAUSE THE THRUST REVERSER TO STOW. INADVERTENT STOW CAN CAUSE DEATH OR SERIOUS INJURY. WARNING : MOVE PERSONS AND EQUIPMENT AWAY FROM THE AREA AROUND THE THRUST _______ REVERSER. THIS WILL PREVENT INJURY TO PERSONS OR DAMAGE TO EQUIPMENT IF THERE IS UNCOMMANDED THRUST REVERSER OPERATION.

N. Connect pneumatic ground power unit to the aircraft ground air connection


�� G E � � � � CF6 - 50 � �� or Auxiliary Power Unit (APU) (Ref. 36-00-00, P. Block 1).

O. Make sure the thrust reverser levers are in the forward thrust position. Close the applicable circuit breakers and check that the translating cowls go back to the stowed position. If necessary, refer to the A300 Fault Isolation Manual for troubleshooting instructions.

P. Disconnect pneumatic ground power unit from the aircraft ground air connection or APU (Ref. 36-00-00, P. Block 1).

Q. Open, safety and tag the applicable circuit breakers.

R. De-energize the aircraft electrical network and disconnect electrical ground power unit (Ref. 24-41-00, P. Block 301).

S. Connect the electrical cable to the left stow switch (Ref. Fig. 504 )

T. To check the auto re-stow system on the left reverser half, disconnect the electrical cable from the right stow switch (Ref. Fig. 504 ).

U. Note applicable.

R **ON A/C 001-103, 106-999,

U. Manually release the TRAS lock (Ref. Fig. 503 ) (1)Pull the T-handle approximately 0.35 inch (8.9 mm). (2)Remove the manual release lever from the retaining clip, and turn the lever to engage the collar. (3)Release the T-handle.

R **ON A/C ALL

V. While one person manually releases the brake on the Pneumatic Drive Motor (PDM), manually deploy the translating cowl approximately 10.0 in. (254 mm) from the stowed position (Ref. Fig. 505 ).

W. Do steps 5.E. through 5.Q. again.

X. Connect the electrical cable to the right stow switch (Ref. Fig. 504 ).

Y. Remove the locally made splined adapter tool from the manual input socket of the center gearbox. Do not install the pad cover and gasket or the splined lock.

Z. Do an operational check of the thrust reverser. Refer to paragraph 8.

6. Thrust Reverser Translating Cowl Auto Re-Stow Function Check (Two-light _______________________________________________________________________ Indication Circuit Only) ________________________ NOTE : The auto re-stow function check is done two times. To provide ____


�� G E � � � � CF6 - 50 � �� sufficient time for correct verification of the flight compartment light indications, the first check of the auto re-stow function is done with the translating cowl deployed 10.0 in. (254 mm). To make sure that the auto re-stow function is prompt, the second check is done with the translating cowl deployed 1.0 in. (25.4 mm). WARNING : MAKE SURE YOU OPEN, TAG AND SAFETY THE APPLICABLE CIRCUIT BREAKERS _______ BEFORE YOU START THE MAINTENANCE PROCEDURES. THIS WILL PREVENT ACCIDENTAL ENGINE START OR THRUST REVERSER OPERATION WHICH CAN CAUSE INJURIES TO PERSONS AND DAMAGE TO EQUIPMENT.

A. Open, safety and tag the circuit breakers for the appropriate engine.

B. Disconnect the electrical cable from the Over Pressure Shutoff Valve (OPSOV) position switch (Ref. Fig. 506 ). NOTE : The OPSOV is found below the Pneumatic Drive Motor (PDM). Get ____ access from the left thrust reverser side.

C. To check the auto re-stow system on the right reverser half, disconnect the electrical cable from the left stow switch (Ref. Fig. 504 ). NOTE : The stow switch is the forward-most plunger-type switch mechanism ____ on the underside of each feedback mechanism.

D. Not applicable.

R **ON A/C 001-103, 106-999,

D. Manually release the TRAS lock (Ref. Fig. 503 ) (1)Pull the T-handle approximately 0.35 inch (8.9 mm). (2)Remove the manual release lever from the retaining clip, and turn the lever to engage the collar. (3)Release the T-handle.

R **ON A/C ALL

E. While one person manually releases the brake on the Pneumatic Drive Motor (PDM), manually deploy the translating cowl approximately 10.0 in. (254 mm) from the stowed position (Ref. Fig. 505 ).

F. Connect the interphone system between the flight compartment and the applicable engine area (Ref. 23-41-00, P. Block 1). WARNING : MOVE PERSONS AND EQUIPMENT AWAY FROM THE AREA AROUND THE THRUST _______ REVERSER. THIS WILL PREVENT INJURY TO PERSONS OR DAMAGE TO EQUIPMENT IF THERE IS UNCOMMANDED THRUST REVERSER OPERATION. CAUTION : BEFORE YOU OPERATE THE THRUST REVERSER SYSTEM, MAKE SURE THE _______ TRANSLATING COWLS ARE CLEAR TO DEPLOY AND STOW.

G. Connect electrical ground power unit and energize the aircraft electrical network (Ref. 24-41-00, P. Block 301). WARNING : BEFORE YOU DO INSPECTION OR MAINTENANCE PROCEDURES WITH THE _______


�� G E � � � � CF6 - 50 � ��

Over Pressure Shutoff Valve Figure 506


�� G E � � � � CF6 - 50 � �� TRANSLATING COWL DEPLOYED, MAKE SURE YOU REMOVE THE AIR SUPPLY FROM THE THRUST REVERSER SYSTEM. IF THE AIR SUPPLY IS CONNECTED, LOSS OF ELECTRICAL POWER WILL CAUSE THE THRUST REVERSER TO STOW. INADVERTENT STOW CAN CAUSE DEATH OR SERIOUS INJURY. WARNING : MOVE PERSONS AND EQUIPMENT AWAY FROM THE AREA AROUND THE THRUST _______ REVERSER. THIS WILL PREVENT INJURY TO PERSONS OR DAMAGE TO EQUIPMENT IF THERE IS UNCOMMANDED THRUST REVERSER OPERATION.

H. Connect the pneumatic ground power unit to the aircraft ground air connection or Auxiliary Power Unit (APU) (Ref. 36-00-00, P. Block 1).

I. Make sure the thrust reverser levers are in the forward thrust position. Close the applicable circuit breakers and check that in flight compartment the amber REV UNLK indication on the center instrument panel is on. The translating cowls must go back to the stowed position and the amber REV UNLK indication must go off. If necessary, refer to the A300 Fault Isolation Manual for troubleshooting instructions.

J. Disconnect the pneumatic ground power unit from the aircraft ground air connection or APU (Ref. 36-00-00, P. Block 1).

K. Open, safety and tag the applicable circuit breakers.

L. De-energize the aircraft electrical network and disconnect electrical ground power unit (Ref. 24-41-00, P. Block 301).

M. While one person manually releases the brake on the Pneumatic Drive Motor (PDM), manually deploy the translating cowl at least 1.0 in. (25.4 mm) from the stowed position (Ref. Fig. 505 ). WARNING : MOVE PERSONS AND EQUIPMENT AWAY FROM THE AREA AROUND THE THRUST _______ REVERSER. THIS WILL PREVENT INJURY TO PERSONS OR DAMAGE TO EQUIPMENT IF THERE IS UNCOMMANDED THRUST REVERSER OPERATION. CAUTION : BEFORE YOU OPERATE THE THRUST REVERSER SYSTEM, MAKE SURE THE _______ TRANSLATING COWLS ARE CLEAR TO DEPLOY AND STOW.

N. Connect electrical ground power unit and energize the aircraft electrical network (Ref. 24-41-00, P. Block 301). WARNING : BEFORE YOU DO INSPECTION OR MAINTENANCE PROCEDURES WITH THE _______ TRANSLATING COWL DEPLOYED, MAKE SURE YOU REMOVE THE AIR SUPPLY FROM THE THRUST REVERSER SYSTEM. IF THE AIR SUPPLY IS CONNECTED, LOSS OF ELECTRICAL POWER WILL CAUSE THE THRUST REVERSER TO STOW. INADVERTENT STOW CAN CAUSE DEATH OR SERIOUS INJURY. WARNING : MOVE PERSONS AND EQUIPMENT AWAY FROM THE AREA AROUND THE THRUST _______ REVERSER. THIS WILL PREVENT INJURY TO PERSONS OR DAMAGE TO EQUIPMENT IF THERE IS UNCOMMANDED THRUST REVERSER OPERATION.

O. Connect the pneumatic ground power unit to the aircraft ground air connection or Auxiliary Power Unit (APU) (Ref. 36-00-00, P. Block 1).

P. Make sure the thrust reverser levers are in the forward thrust position. Close the applicable circuit breakers and check that the translating cowls


�� G E � � � � CF6 - 50 � �� go back to the stowed position. If necessary, refer to the A300 Fault Isolation Manual for troubleshooting instructions.

Q. Disconnect the pneumatic ground power unit from the aircraft ground air connection or APU (Ref. 36-00-00, P. Block 1).

R. Open, safety and tag the applicable circuit breakers.

S. De-energize the aircraft electrical network and disconnect electrical ground power unit (Ref. 24-41-00, P. Block 301).

T. Connect the electrical cable to the left stow switch (Ref. Fig. 504 ).

U. To check the auto re-stow system on the left reverser half, disconnect the electrical cable from the right stow switch (Ref. Fig. 504 ).

V. While one person manually releases the brake on the Pneumatic Drive Motor (PDM), manually deploy the translating cowl approximately 10.0 in. (254 mm) from the stowed position (Ref. Fig. 505 ).

W. Do steps 6.G. through 6.S. again.

X. Connect the electrical cable to the right stow switch (Ref. Fig. 504 ).

Y. Connect the electrical cable to the Overpressure Shutoff Valve (OPSOV) position switch (Ref. Fig. 506 ).

Z. Do the Overpressure Shutoff Valve (OPSOV) indication check. Refer to paragraph 7.

7. Overpressure Shutoff Valve (OPSOV) Indication Check ___________________________________________________ NOTE : Do this check after the translating cowl auto re-stow function check ____ on aircraft with a two-light indication circuit only.

A. Disconnect the electrical cable from the left and right stow switches (Ref. Fig. 504 ) NOTE : The stow switch is the forward-most plunger-type switch mechanism ____ on the underside of each feedback mechanism. WARNING : MOVE PERSONS AND EQUIPMENT AWAY FROM THE AREA AROUND THE THRUST _______ REVERSER. THIS WILL PREVENT INJURY TO PERSONS OR DAMAGE TO EQUIPMENT IF THERE IS UNCOMMANDED THRUST REVERSER OPERATION. CAUTION : BEFORE YOU OPERATE THE THRUST REVERSER SYSTEM, MAKE SURE THE _______ TRANSLATING COWLS ARE CLEAR TO DEPLOY AND STOW.

B. Connect electrical ground power unit and energize the aircraft electrical network (Ref. 24-41-00, P. Block 301). WARNING : BEFORE YOU DO INSPECTION OR MAINTENANCE PROCEDURES WITH THE _______ TRANSLATING COWL DEPLOYED, MAKE SURE YOU REMOVE THE AIR SUPPLY FROM THE THRUST REVERSER SYSTEM. IF THE AIR SUPPLY IS CONNECTED, LOSS OF ELECTRICAL POWER WILL CAUSE THE THRUST REVERSER TO STOW. INADVERTENT STOW CAN CAUSE DEATH OR SERIOUS INJURY.


�� G E � � � � CF6 - 50 � �� WARNING : MOVE PERSONS AND EQUIPMENT AWAY FROM THE AREA AROUND THE THRUST _______ REVERSER. THIS WILL PREVENT INJURY TO PERSONS OR DAMAGE TO EQUIPMENT IF THERE IS UNCOMMANDED THRUST REVERSER OPERATION.

C. Connect the pneumatic ground power unit to the aircraft ground air connection or Auxiliary Power Unit (APU) (Ref. 36-00-00, P. Block 1).

D. Remove the safety clips and tags and close the applicable circuit breakers.

E. Use the thrust reverser levers to command deployment of the translating cowls. Check that in flight compartment the amber REV UNLK indication on the center instrument panel is on. The amber REV UNLK indication on the center instrument panel will go off and the green REV indication on the center instrument panel will come on. If necessary, refer to the A300 Fault Isolation Manual for troubleshooting instructions.

F. Disconnect the pneumatic ground power unit from the aircraft ground air connection or APU (Ref. 36-00-00, P. Block 1).

G. Open, safety and tag the applicable circuit breakers.

H. De-energize the aircraft electrical network and disconnect electrical ground power unit (Ref. 24-41-00, P. Block 301).

I. Connect the electrical cable to the left and right stow switches (Ref. Fig. 504 ). WARNING : MOVE PERSONS AND EQUIPMENT AWAY FROM THE AREA AROUND THE THRUST _______ REVERSER. THIS WILL PREVENT INJURY TO PERSONS OR DAMAGE TO EQUIPMENT IF THERE IS UNCOMMANDED THRUST REVERSER OPERATION. CAUTION : BEFORE YOU OPERATE THE THRUST REVERSER SYSTEM, MAKE SURE THE _______ TRANSLATING COWLS ARE CLEAR TO DEPLOY AND STOW.

J. Connect electrical ground power unit and energize the aircraft electrical network (Ref. 24-41-00, P. Block 301). WARNING : BEFORE YOU DO INSPECTION OR MAINTENANCE PROCEDURES WITH THE _______ TRANSLATING COWL DEPLOYED, MAKE SURE YOU REMOVE THE AIR SUPPLY FROM THE THRUST REVERSER SYSTEM. IF THE AIR SUPPLY IS CONNECTED, LOSS OF ELETRICAL POWER WILL CAUSE THE THRUST REVERSER TO STOW. INADVERTENT STOW CAN CAUSE DEATH OR SERIOUS INJURY. WARNING : MOVE PERSONS AND EQUIPMENT AWAY FROM THE AREA AROUND THE THRUST _______ REVERSER. THIS WILL PREVENT INJURY TO PERSONS OR DAMAGE TO EQUIPMENT IF THERE IS UNCOMMANDED THRUST REVERSER OPERATION.

K. Connect the pneumatic ground power unit to the aircraft ground air connection or Auxiliary Power Unit (APU) (Ref. 36-00-00, P. Block 1).

L. Make sure the thrust reverser levers are in the forward thrust position. Close the applicable circuit breakers to stow the translating cowls.

M. Disconnect the pneumatic ground power unit from the aircraft ground air


�� G E � � � � CF6 - 50 � �� connection or APU (Ref. 36-00-00, P. Block 1).

N. Open, safety and tag the applicable circuit breakers.

O. De-energize the aircraft electrical network and disconnect electrical ground power unit (Ref. 24-41-00, P. Block 301).

P. Remove the locally made splined adapter tool from the manual input socket of the center gearbox. Do not install the pad cover and gasket or the splined lock.

Q. Do an operational check of the thrust reverser. Refer to paragraph 8.

8. Thrust Reverser Operational Check _________________________________

A. Make sure that the two translating cowls are in the stow rig position. If the translating cowls are not in the stow rig positions: (1)Manually release the disc brake on the pneumatic drive motor. (2)Not applicable.

R **ON A/C 001-103, 106-999,

(2)Manually release the TRAS locks (Ref. Fig. 503 ) (a)Pull the T-handle approximately 0.35 inch (8.9 mm). (b)Remove the manual release lever from the retaining clip, and turn the lever to engage the collar. (c)Release the T-handle.

R **ON A/C ALL

(3)Translate the translating cowls through the right center gearbox as necessary to move the translating cowls to the stow rig positions.R (4)Manually engage the TRAS locks (Ref. Fig. 503 )R (a)Pull the T-handle approximately 0.1 inch (2.54 mm).R (b)Turn the manual release lever away from the fan cowl and insertR the lever in the retaining clip.R (c)Release the T-handle.R (5)Manually engage the disc brake on the pneumatic drive motor.

B. Remove the cap from the stow tube and remove the bleed air regulator valve from the deploy tube on the left reverser half (Ref. Fig. 504 ). NOTE : With the cap and bleed air regulator valve removed, the translating ____ cowls will move at slow speed. This will help check for interference and smoothness of operation. WARNING : MOVE PERSONS AND EQUIPMENT AWAY FROM THE AREA AROUND THE THRUST _______ REVERSER. THIS WILL PREVENT INJURY TO PERSONS OR DAMAGE TO EQUIPMENT IF THERE IS UNCOMMANDED THRUST REVERSER OPERATION. CAUTION : BEFORE YOU OPERATE THE THRUST REVERSER SYSTEM, MAKE SURE THE _______ TRANSLATING COWLS ARE CLEAR TO DEPLOY AND STOW.

C. Connect electrical ground power unit and energize the aircraft electrical


�� G E � � � � CF6 - 50 � �� network. Close the applicable circuit breakers for the thrust reverser system. WARNING : BEFORE YOU DO INSPECTION OR MAINTENANCE PROCEDURES WITH THE _______ TRANSLATING COWL DEPLOYED, MAKE SURE YOU REMOVE THE AIR SUPPLY FROM THE THRUST REVERSER SYSTEM. IF THE AIR SUPPLY IS CONNECTED, LOSS OF ELECTRICAL POWER WILL CAUSE THE THRUST REVERSER TO STOW. INADVERTENT STOW CAN CAUSE DEATH OR SERIOUS INJURY. WARNING : MOVE PERSONS AND EQUIPMENT AWAY FROM THE AREA AROUND THE THRUST _______ REVERSER. THIS WILL PREVENT INJURY TO PERSONS OR DAMAGE TO EQUIPMENT IF THERE IS UNCOMMANDED THRUST REVERSER OPERATION.

D. Connect the pneumatic ground power unit to the aircraft ground air connection or Auxiliary Power Unit (APU) (Ref. 36-00-00, P. Block 1).R WARNING : WHEN YOU HOLD OPEN THE MANUAL RELEASE LEVERS OF THE TRAS _______R LOCKS, STAND CLOSE TO THE FAN CASE AREA AND AWAY FROM THER TRANSLATING COWLS TO PREVENT INJURY WHEN THE TRANSLATING COWLSR ARE CYCLED.

R E. Unlock and manually hold open the manual release lever on the TRAS locksR (1)Pull the T-handle approximately 0.35 inch (8.9 mm).R (2)Remove the manual release lever from the retaining clip, and turn theR lever to engage the collar.R (3)Release the T-handle.R (4)Manually hold the manual release lever in the unlocked position whileR the translating cowls are cycled during the slow speed operationalR check. CAUTION : WHEN YOU OPERATE THE TRANSLATING COWLS, DO NOT MAKE MORE THAN _______ SIX STROKES IN A THREE-MINUTE PERIOD. THIS LIMIT IS NECESSARY SO THAT THE PNEUMATIC DRIVE ACTUATOR DOES NOT OVERHEAT. A STROKE IS THE MOVEMENT OF THE TRANSLATING COWL IN ONE DIRECTION.

R F. Operate the translating cowls for three full cycles. Do a visual check for smooth operation at slow speed. Do a check to make sure that the cockpit indications come in the correct sequence. If necessary, refer to the A300 Fault Isolation Manual for troubleshooting instructions.

R G. Manually engage the TRAS locks (Ref. Fig. 503 )R (1)Pull the T-handle approximately 0.1 inch (2.54 mm).R (2)Turn the manual release lever away from the fan cowl and insert theR lever in the retaining clip.R (3)Release the T-handle.

R H. Disconnect the pneumatic ground power unit from the aircraft ground air connection or APU (Ref. 36-00-00, P. Block 1).

R I. De-energize the aircraft electrical network and disconnect electrical ground power unit (Ref. 24-41-00, P. Block 301).

R J. Install the bleed air regulator valve on the deploy tube and install the cap on the stow tube. TORQUE the bleed air regulator valve and the cap to between 270 and 300 lbf.in. (3.05 and 3.39 m.daN). Safety the valve and


�� G E � � � � CF6 - 50 � �� the cap with lockwire. WARNING : MOVE PERSONS AND EQUIPMENT AWAY FROM THE AREA AROUND THE THRUST _______ REVERSER. THIS WILL PREVENT INJURY TO PERSONS OR DAMAGE TO EQUIPMENT IF THERE IS UNCOMMANDED THRUST REVERSER OPERATION. CAUTION : BEFORE YOU OPERATE THE THRUST REVERSER SYSTEM, MAKE SURE THE _______ TRANSLATING COWLS ARE CLEAR TO DEPLOY AND STOW.

R K. Connect electrical ground power unit and energize the aircraft electrical network. Close the applicable circuit breakers for the thrust reverser system. WARNING : BEFORE YOU DO INSPECTION OR MAINTENANCE PROCEDURES WITH THE _______ TRANSLATING COWL DEPLOYED, MAKE SURE YOU REMOVE THE AIR SUPPLY FROM THE THRUST REVERSER SYSTEM. IF THE AIR SUPPLY IS CONNECTED, LOSS OF ELECTRICAL POWER WILL CAUSE THE THRUST REVERSER TO STOW. INADVERTENT STOW CAN CAUSE DEATH OR SERIOUS INJURY. WARNING : MOVE PERSONS AND EQUIPMENT AWAY FROM THE AREA AROUND THE THRUST _______ REVERSER. THIS WILL PREVENT INJURY TO PERSONS OR DAMAGE TO EQUIPMENT IF THERE IS UNCOMMANDED THRUST REVERSER OPERATION.

R L. Connect the pneumatic ground power unit to the aircraft ground air connection or Auxiliary Power Unit (APU) (Ref. 36-00-00, P. Block 1).

CAUTION : WHEN YOU OPERATE THE TRANSLATING COWLS, DO NOT MAKE MORE THAN SIX _______ STROKES IN A THREE-MINUTE PERIOD. THIS LIMIT IS NECESSARY SO THAT THE PNEUMATIC DRIVE ACTUATOR DOES NOT OVERHEAT. A STROKE IS THE MOVEMENT OF THE TRANSLATING COWL IN ONE DIRECTION.

R M. Operate the translating cowls for three full cycles. Do a visual check for smooth operation at normal (fast) speed. Do a visual check to make sure that the translating cowls change from fast mode to slow mode near the end of the stroke. Do a check to make sure that the cockpit indications come in the correct sequence. If necessary, refer to the A300 Fault Isolation Manual for troubleshooting instructions.

R N. Put the two translating cowls in the stow rig position. (1)Manually release the disc brake on the pneumatic drive motor. (2)Not applicable.

R **ON A/C 001-103, 106-999,

(2)Manually release the TRAS lock (Ref. Fig. 503 ) (a)Pull the T-handle approximately 0.35 inch (8.9 mm). (b)Remove the manual release lever from the retaining clip, and turn the lever to engage the collar. (c)Release the T-handle.

R **ON A/C ALL

(3)Translate the translating cowls through the right center gearbox as necessary to move the translating cowls to the stow rig position.R (4)Manually engage the disc brake on the pneumatic drive motor.


�� G E � � � � CF6 - 50 � ��R O. Disconnect the pneumatic ground power unit from the aircraft ground air connection or APU (Ref. 36-00-00, P. Block 1).

R P. Open, safety and tag the applicable circuit breakers.

R Q. De-energize the aircraft electrical network and disconnect electrical ground power unit (Ref. 24-41-00, P. Block 301).

R R. Install the splined adapter tool into the manual input socket on the center gearbox. Apply a torque of 50 lbf.in. (0.57 m.daN) in the deploy direction only, to make sure the pneumatic drive motor disc brake is engaged. There must be no visible movement of the brake. If necessary, refer to the A300 Fault Isolation Manual for troubleshooting instructions.

R NOTE: The TRAS locks must be disengaged during the PDM brake check ____

R S. Remove the splined adapter tool from the manual input socket of the center gearbox.

R T. Install the pad cover and the gasket or the splined lock (P/N 9149M85G01) with the splined end out, on the manual input socket on the lower side of the center gearbox. Attach the pad cover and the gasket or the splined lock with two bolts. TORQUE the bolts to between 33 and 37 lbf.in. (0.37 and 0.42 m.daN) (Ref. Fig. 507 ).

R U. Not applicable.

R **ON A/C 001-103, 106-999,

R V. Do the steps that follow to engage the TRAS locks.R (1)Pull the T-handle approximately 0.1 inch (2.54 mm). (2)Turn the manual release lever away from the fan cowl. (3)Engage the manual release lever in the retaining clip. (4)Release the T-handle.

R **ON A/C ALL

R W. Disconnect the interphone system between the flight compartment and the applicable engine area (Ref. 23-41-00, P. Block 1).

9. Close-Up ________

A. Make sure the work area is clean and clear of tools and miscellaneous items of equipment.

B. Close the fan cowl doors (Ref. to 71-13-00, P. Block 301).


�� G E � � � � CF6 - 50 � ��

Splined Lock (P/N 9149M85G01) or Pad Cover and Gasket on the Center Gearbox Figure 507 �� EFFECTIVITY: ALL �� 78-30-00 � � � � Page 522 � � JAS Mar 01/07

�� G E � � � � CF6 - 50 � �� C. Remove the safety clips and tags and close the circuit breakers that were open.


�� G E � � � � CF6 - 50 � �� THRUST REVERSER SYSTEM CONTROL - DESCRIPTION AND OPERATION __________________________________________________________

1. General _______ The thrust reverser is controlled from the flight compartment by means of a lever hinged on the throttle control handle. This control lever allows the thrust reverser to be deployed or stowed via a pneumatic drive actuator. Pneumatic energy required for driving the drive actuator is bled off at the engine compressor or in the aircraft pneumatic system. An electrical circuit associated with the control lever opens the valves which supply air to the pneumatic drive actuator. The thrust reverser operating sequences are monitored by an indicating system.

2. Component Location __________________ THRUST_REVERSE________________ (Ref. Fig.001 and 002)

R **ON A/C 001-103, 106-999,

(Ref. Fig.001 and 003)

R **ON A/C ALL

(Ref. Fig. 004 ) (Ref. Fig. 005 ) ------------------------------------------------------------------------------ ITEM NAME PANEL ZONE ACCESS DOOR ------------------------------------------------------------------------------

1EB Circuit Breaker - ENG1/OIL 123VU 212 FUEL/FILTER/NACELLE/TEMP IND 2EB Circuit Breaker - ENG2/OIL 123VU 212 FUEL/FILTER/NACELLE/TEMP IND 3EB Indicator - Nacelle Temperature - 55VU 212 (TEMP - NACELLE 1) 4EB Indicator - Nacelle Temperature 55VU 212 (TEMP - NACELLE 2) 125GB Relay - LH Gear Shock Absorber 104VU 121/122 124GB Relay - RH Gear Shock Absorber 104VU 121/122 1KM Circuit Breaker - ENG 1/REV/ 123VU 212 CONTRL 2KM Circuit Breaker - ENG 2/REV/ 123VU 212 CONTRL 3KM Circuit Breaker - ENG 1/REV/ 123VU 212 WARN LTS 4KM Circuit Breaker - ENG 2/REV/ 123VU 212 WARN LTS 5KM Relay - Eng 1 Reverse 105VU 122 Configurations 6KM Relay - Eng 2 Reverse 105VU 122 Configurations


�� G E � � � � CF6 - 50 � �� ------------------------------------------------------------------------------ ITEM NAME PANEL ZONE ACCESS DOOR ------------------------------------------------------------------------------ 7KM Microswitch - ENG 1 Thrust 113VU 121 Reverser Control 8KM Microswitch - ENG 2 Thrust 112VU 122 Reverser Control 9KM Warning Light - REV UNLK, Eng 1 230VU 212 10KM Warning Light - REV UNLK, Eng 2 230VU 212 11KM Indicator Light - REV, Eng 1 230VU 212 12KM Indicator Light - REV, Eng 2 230VU 212 13KM Indicator Switch - ENG 1, RH 452 436AR Fan Thrust Reverser Stow Position 13VU Eectrical Connector 452 436AR 14KM Indicator Switch - ENG 2, RH 462 446AR Fan Thrust Reverser Stow Position 14KMA Electrical Connector 462 446AR 15KM Indicator Switch - ENG 1, LH 451 435AL Fan Thrust Reverser Stow Position 15KMA Electrical Connector 451 435AL 16KM Indicator Switch - ENG 2, LH 461 445AL Fan Thrust Reverser Stow Position 16KMA Electrical Connector 461 445AL 17KM Indicator Switch - ENG 1, LH 451 435AL Fan Thrust Reverser Deploy Position 17KMA Electrical Connector 451 435AL 18KM Indicator Switch - ENG 2, LH 461 445AL Fan Thrust Reverser Deploy Position 18KMA Electrical Connector 461 445AL 19KM Indicator Switch - ENG 1, RH 452 436AR Fan Thrust Reverser Deploy Position 19KMA Electrical Connector 452 436AR 20KM Indicator Switch - ENG 2, RH 462 446AR Fan Thrust Reverser Deploy Position 20KMA Electrical Connector 462 446AR 21KM Solenoid - ENG 1, Overpressure and 451 451AL Shut Off Valve Control 21KMA Electrical Connector 451 451AL 22KM Soleniod - ENG 2, Overpressure and 461 461AL Shut Off Valve Control 22KMA Electrical Connector 461 461AL 23KM Indicator Switch - ENG 1, 451 451AL Overpressure and Shut Off Valve Position 23KMA Electrical Connector 451 451AL 24KM Indicator Switch - ENG 2, 461 461AL Overpressure and Shut Off Valve Position 24KMA Electrical Connector 461 461AL 1 Feedback System - 452 436AR 462 446AR 3 Valve - Throttle and Thrust 452 436AR


�� G E � � � � CF6 - 50 � �� ------------------------------------------------------------------------------ ITEM NAME PANEL ZONE ACCESS DOOR ------------------------------------------------------------------------------ Reverser Interlock 462 446AR 5 Gearbox - Center, RH Fan Thrust 452 436AR Reverser 462 446AR 7 Ball Screw Actuators - 452 436AR Fan Thrust Reverser 462 446AR 9 Control Valve - Directional 414 413DR 414FL 424 424DR 423FL 11 Actuator - Throttle Interlock 414 414DR 413FL 424 424DR 423FL 13 Actuator - Pneumatic Drive 451 451AL 452 452AR 461 461AL 462 462AR 15 Ball Screw Actuators - 451 435AL LH Fan Thrust Reverser 461 445AL 17 Gearbox - Center, LH Fan 451 435AL Thrust Reverser 461 445AL 19 Shaft - Synchronous Flexible 451 435AL Drive, LH Fan Thrust Reverser 461 445AL 21 Switcher Valve - Pneumatic 451 435AL 461 445AL 23 Feedback System - LH side 451 435AL 461 445AL 25 Angle Gearbox - LH Fan 451 435AL Thrust Reverser 461 445AL 27 Flexible Drive Shaft - 451 435AL LH Fan Thrust Reverser 461 445AL 29 Valve - Overpressure and 451 451AL Shut Off 452 452AR 461 461AL 462 462AR 31 Angle Gearbox - RH Fan 452 436AR Thrust Reverser 462 446AR 33 Flexible Drive Shaft 452 436AR RH Fan Thrust Reverser 462 446AR 35 Shaft - Synchronous Flexible 452 436AR Drive, RH Fan Thrust Reverser 462 446AR 39 Valve - Pressure Regulating 454 452AR and Shut Off 464 462AR 41 Check Valve - Pneumatic 454 452AR 464 462AR 53 Safety Valve 453 451AL 463 461AL 55 Sensor - Nacelle Temperature 451 451DL


�� G E � � � � CF6 - 50 � �� ------------------------------------------------------------------------------ ITEM NAME PANEL ZONE ACCESS DOOR ------------------------------------------------------------------------------ 461 461DL

R **ON A/C 001-103, 106-999,

X1 Thrust Reverser Actuation System 452 436AR (TRAS) lock RH Fan Thrust Reverser 462 446AR X3 Thrust Reverser Actuation System 451 435AL (TRAS) lock LH Fan Thrust Reverser 461 446AL X5 Dual Switcher Valve 452 436AR 462 446AR


�� G E � � � � CF6 - 50 � ��

Zones and Access Doors - Location Figure 001


�� G E � � � � CF6 - 50 � ��

Component Location - Zones Engine Figure 002


�� G E � � � � CF6 - 50 � ��

Component Location - Zones Engine - Post SB 78-022 Figure 003 ��R �EFFECTIVITY: 001-103, 106-999, �� 78-31-00 � � � � Page 7 � � JAS Mar 01/07

�� G E � � � � CF6 - 50 � ��

Nacelle Temperature Sensor Figure 004


�� G E � � � � CF6 - 50 � ��

Component Location - Zones 121-122-212 Figure 005


�� G E � � � � CF6 - 50 � ��

R **ON A/C ALL

3. Description (Ref. Fig. 006 ) ___________ The thrust reverser control system is made up of : - A lever hinged on the throttle control handle - A directional control valve - A throttle and thrust reverser interlock valve - A throttle interlock actuator - A safety valve - A pneumatic check valve - A pressure regulating and shut off valve - An overpressure and shut off valve - A pneumatic drive actuator - Flexible drive shafts - Gearbox assemblies - Ball screw actuators - A PNEUMATIC SWITCHER VALVE - A feedback system - A control and indicating system


�� G E � � � � CF6 - 50 � ��

Thrust Reverser Control - Block Diagram Figure 006


�� G E � � � � CF6 - 50 � ��

R **ON A/C 001-103, 106-999,

3. Description (Ref. Fig. 007 ) ___________ The thrust reverser control system is made up of : - A lever hinged on the throttle control handle - A directional control valve - A throttle and thrust reverser interlock valve - A throttle interlock actuator - A safety valve - A pneumatic check valve - A pressure regulating and shut off valve - An overpressure and shut off valve - A pneumatic drive actuator - Flexible drive shafts - Gearbox assemblies - Ball screw actuators - A PNEUMATIC SWITCHER VALVE - A feedback system - A control and indicating system - A dual switcher valve - Thrust reverser actuation system (TRAS) locks

��R �EFFECTIVITY: 001-103, 106-999, �� 78-31-00 � � � � Page 12 � � JAS Mar 01/07

�� G E � � � � CF6 - 50 � ��

Thrust Reverser Control - Block Diagram - Post SB 78-022 Figure 007 ��R �EFFECTIVITY: 001-103, 106-999, �� 78-31-00 � � � � Page 13 � � JAS Mar 01/07

�� G E � � � � CF6 - 50 � ��

R **ON A/C ALL

4. Operation _________ (Ref. Fig.008 and 009) NOTE : The thrust reverser control lever can be operated only when the throt- ____ tle control handle is in the forward idle throttle position. Relay 125GB (124GB) operated by the main gear proximity sensor allows the thrust reversers to be operated in ground configuration only.

A. Thrust Reverser Deployment The thrust reverser control lever moved to the stop position given by the throttle interlock actuator causes the overpressure and shut-off valve control solenoid (P8) to be energized. This enables air from the engine to be admitted to the overpressure and shut-off valve and to the pressure regulating and shut-off valve. These two valves open. Indicator switch (P1) makes the ?open? contact. Amber REV UNLK warning light comes on. The pressure regulating and shut-off valve limits the supply of air pressure to the pneumatic dirve actuator to 55 psi (3.79 bars) with a tolerance of ± 5 psi (0.34 bar). The overpressure and shut-off valve allows the supply airflow, with the present pressure, to be directed to the pneumatic drive actuator and protects the system against possible overpressure. Moreover the thrust reverser control lever causes the directional control valve to close. Directional control valve closure causes displacement of the actuator which orients the directional butterfly. The energy developed by the pneumatic drive actuator is transmitted to the ball screw actuators by means of the flexible drive shafts and gearbox assemblies. The ball-screw actuators convert the rotational movement which is directly transmitted to the thrust reverser translating cowls. Indicator switches (P3) and (P7) make the ?unlocked? contacts. When the RH fan thrust reverser is 90% desployed, the throttle and thrust reverser interlock valve unlocks the throttle interlock actuator. The thrust reverser control lever is then free to move. The reverse full throttle can be applied. Indicator switch (P6) makes the ?desployed? contact. The green REV indicator light comes on. The pneumatic switcher valve sends a signal to the pneumatic drive actuator to reduce the rotational speed. When the LH fan thrust reverser is 98% desployed, indicator switch (P4) makes the ?desployed? contact, solenoid (P8) is no longer energized, the overpressure and shut-off valve and the pressure regulating and shut-off valve close. The pneumatic supply to the pneumatic drive actuator is then interrupted. Indicator switch (P1) makes the ?close? contact. Amber REV UNLK warning light goes off. The residual torque of the flexible drive shafts completes the action on the ball-screw actuators and consequently presses the thrust reversers on the travel stops. The thrust reversers are locked in the desployed position by means of the disk brake of the pneumatic drive actuator.


�� G E � � � � CF6 - 50 � ��

Thrust Reverser Control - Schematic Figure 008


�� G E � � � � CF6 - 50 � ��

Thrust Reverser Control and Indicating Figure 009


�� G E � � � � CF6 - 50 � �� B. Thrust Reverser Stowage This displacement of the thrust reverser control lever toward the 0• position (reversers stowed) causes the directional control valve to open. After the end of deployment the directional control valve actuator returns to the initial position under the action of the directional control shuttle valve return spring and orients the directional butterfly plate in order to power the pneumatic drive actuator for thrust reverser stowage. The displacement of the thrust reverser control lever also causes solenoid (P8) to be energized. The overpressure and shut-off valve and the pressure regulating and shut-off valve open. Indicator switch (P1) makes the ?open? contact. Amber REV UNLK warning light comes on.

The pneumatic drive actuator is supplied. The disk brake is no longer operative and thus releases the thrust reversers which begin stowage sequence. Indicator switches (P4) and (P6) make the ?stowed? contact. Green REV indicator light goes off. When the thrust reversers 90% stowed, the pneumatic switcher valve sends a signal to the pneumatic drive actuator in order to reduce the rotational speed. Indicator switches (P3) and (P7) make the ?locked? contacts.

Solenoid (P8) is no longer energized. The overpressure and shut-off valve and the pressure regulating and shut-off valve close. They cut off the drive actuator pneumatic supply. Indicator switch (P1) makes the ?closed? contact. Amber REV UNLK warning light extinguishes. The residual torque of the flexible drive shafts completes the action on the ball-screw actuators and consequently presses the thrust reversers on to the travel stops. The fan thrust reverser is locked in the stowed position by means of the disk brake of the pneumatic drive actuator.


�� G E � � � � CF6 - 50 � �� 5. Pneumatic Drive Actuator ________________________

A. General The pneumatic drive actuator supplies power required for driving the thrust reverser assembly both to desployed or stowed position according to orders from the control system. The pneumatic drive actuator also comprises two speed control systems : - A high speed control system (which limits speed to 20,000 RPM) used during the main displacement. - A low speed control system (which limits speed to 1100 RPM) used at the end of displacement. When not operating, the pneumatic drive actuator is held in the stop position by means of an internal disc brake.

B. Description (Ref. Fig.010 and 011) The pneumatic drive actuator is made up of : (1)Two helical rotors installed in a casing accommodating one inlet port and one outlett port. (2)A gearbox assembly connected at one end to one of the rotors and at the other end to the thrust reverser ball screw actuators through flexible drive shafts. (3)A brake system with : - A disk brake - An actuator - A control valve - An air vent valve (4)A snubber control system which comprises : - A speed control servo - A servo supply regulator - A pressure relief valve - A snubber butterfly plate - An actuator (5)A fluid regulating system which comprises : - A speed sensor connected to one of the rotors - A fluidic control box accommodating a frequency/analog converter and a differential pressure indicating system. - A fluidic supply regulator - A pressure relief valve which maintains differential pressure deter- mined between port D and port E of the fuidic control box (6)A high speed control system (7)A directional control system which comprises : - A directional control valve actuator - A directional control shuttle valve - A stow and a deploy logic valve (8)A directional butterfly plate

C. Operation (Ref. Fig. 012 ) (1)Pressurization The initial displacement of the thrust reverser control levers allows the pneumatic drive actuator to be pressurized through the pressure regulating and shut off valve and the overpressure and shut off valve. At the

��R �EFFECTIVITY: ALL �� 78-31-00 � � � � Page 18 � � JAS Mar 01/06

�� G E � � � � CF6 - 50 � ��

Pneumatic Drive Actuator - Schematic Figure 010

�� EFFECTIVITY: ALL �� 78-31-00 � � � �R Page 19- 20 � � JAS Mar 01/06

�� G E � � � � CF6 - 50 � ��

Pneumatic Drive Actuator Figure 011


�� G E � � � � CF6 - 50 � ��

INTENTIONALLY BLANK

��R � �� 78-31-00 � � � � Page 22 � � JAS Mar 01/06

�� G E � � � � CF6 - 50 � ��

Pneumatic Drive Actuator Schematic Figure 012

�� EFFECTIVITY: ALL �� 78-31-00 � � � �R Page 23- 24 � � JAS Mar 01/06

�� G E � � � � CF6 - 50 � �� same time, the brake control valve chamber (2) is pressurized and disc-brake release is selected. (2)Direction of Rotation The initial displacement of the thrust reverser control levers is reverse thrust direction closes directional control valve. The air pressure moves the directional control shuttle valve in the direction which allows the directional control valve actuator to be controlled in deploy position. Both the directional butterfly plate and the logic valve are driven by means of the actuator rod. NOTE : When the directional control valve is not closed the directional ____ control shuttle valve is repositioned by means of its spring. This return to initial position moves both the directional butterfly plate and the logic valve to stow position. (3)Starting of rotation The actuator is initially held in stop position by means of the brake and by means of the snubber valve closing the actuator exhaust. As the initial displacement of the thrust reverser levers closes directional control valve, the air pressure increases in the snubber valve actuator. The snubber valve opens. The air pressure increases in the brake control system. the air pressure passes through the brake control valve (previously selected). The brake is no longer applied. The pneumatic drive actuator starts operating. (4)Speed regulation NOTE : The pneumatic drive actuator must drive the thrust reversers in ____ high speed mode through 90% of their displacement and in low-speed mode through the last 10%. Speed selection and speed regulation are accomplished through the speed servo-control. As popplished through the speed servo-control. As popped valve (1) moves away from its seat, a leak is created in the snubber valve control pneumatic system. The snubber valve closes and the brake is applied. (a)High speed mode During the initial displacement of the thrust reverser control levers, the directional control valve allows the speed servo control override chamber to be pressurized. Poppet valve (1) is held in closed position. The pneumatic drive actuator speed increases. The maximum speed is limited by means of a differential pressure high speed control, which at a speed greater than 20,000 RPM creates a leak both in the snubber valve and the disc-brake pneumatic system. Both the snubber valve and the brake slow the pneumatic drive actuator speed. (b)Low speed mode When the direction of rotation is selected, the directional control valve actuator drives the directional butterfly plate and the logic valve simultaneously. The logic valve allows pressurization of the pneumatic switcher valve which receives the same pressure as the speed servo control override chamber. When the thrust reversers reach 90% of their displacement, a cam linked to the thrust reversers causes the pneumatic switcher valve to open. Pneumatic switcher valve opening creates a leak in the override chamber pneumatic system.


�� G E � � � � CF6 - 50 � �� Poppet valve (1) leaves its seat. The air pressure rapidly decreases both in the snubber valve actuator control chamber and in the brake actuator control chamber. The snubber valve closes and the brake holds the pneumatic drive actuator in stop position for approximately 1 second. The speed sensor detects a low speed signal which is sent immediately to the low speed fluidic control which in turn sends a pneumatic signal through ports ?F? and ?G? to the speed servo control to close poppet valve (1). The air pressure increases both in the brake and snubber valve control system. The pneumatic drive actuator starts again. The speed is now constantly monitored by means of the speed sensor which now sends a signal to the speed servo control either to open or close popped (1). The speed is regulated at 1100 RPM. (5)Deactivation When the thrust reversers reach 98% of their displacement, the overpressure and shut off valve solenoid is deactivated. Both the pressure regulating and shut off valve and the overpressure and shut off valve are time delayed in order to allow pneumatic drive actuator operation till the thrust reversers achieve full displacement. With the thrust reversers on stops, the pneumatic drive actuator stops operating. The low speed fluidic control receives the low speed signal and closes speed servo control poppet valve (1) in order to increase the pneumatic drive actuator torque. With the pneumatic drive actuator held in stop position the differential pressure increases upstream and down-stream of the pneumatic drive actuator. The differential pressure sensed through the low speed fluidic control ports ?E? and ?D? overrides the low speed signal. The output signal from ?E? and ?D? ports enables the torque to be limited to prevent and over-load on thrust reverser flexible drive shafts. When the pressure regulating and shut off valve and overpressure and shut off valve are fully closed, the brake is applied and the snubber valve closes. NOTE : A preload is held on thrust reverser flexible drive shafts. ____


�� G E � � � � CF6 - 50 � �� 6. Center Gearbox ______________

A. Description (Ref. Fig. 013 ) The center gearboxes transmit torque to the angle gearboxes, and provide speed reduction from flexible drive shafts to the ball-screw actuators. This is accomplished through a bevel gear set.

B. Operation Power from the flexible drive shafts is transmitted to the gearbox, reduced and transmitted through the ballscrew actuators.

Center Gearbox Figure 013


�� G E � � � � CF6 - 50 � �� 7. Upper and Lower Gearboxes _________________________

A. Description (Ref. Fig. 014 ) Upper and lower gearboxes receive power from the center gearboxes and flexible drive shafts, reduce the speed and transmit the torque to the ball-screw actuators through a bearing-mounted shaft and bevel gear arrangment.

B. Operation Power from the center gearboxes and flexible drive shafts is transmitted to upper and lower gearboxes, reduced and transmitted through the ballscrew actuators.

Upper and Lower Gearbox Figure 014


�� G E � � � � CF6 - 50 � �� 8. Fan Reverser Ball-Screw Actuators _________________________________

A. Description (Ref. Fig. 015 ) Ball-screw actuators consist of a ball shaft, balls and a translating nut attached to a tubular member. A spherical rod-end bearing is installed as part of the tubular member for attachment to the fan translating cowl clevis.

B. Operation Power from the pneumatic drive actuator is transmitted to the center and angle gearboxes by flexible shafts, reduced and transmitted to the ballscrew actuators. The ball-screw actuators move to position the fan reverser deflectors to stow or deploy position within 2 seconds.

Fan Reverser Ball-Screw Actuator Figure 015


�� G E � � � � CF6 - 50 � �� 9. Not applicable

R **ON A/C 001-103, 106-999,

9. Thrust Reverser Actuation System (TRAS) Lock and Dual Switcher Valve ____________________________________________________________________

A. General The TRAS Lock is an electro-mechanical locking device that prevents inadvertent and uncommanded movement of the thrust reverser sleeves. The TRAS Lock is also known as Electro-Mechanical Brake. The TRAS Lock system consists of the components that follow (Ref. Fig. 016 ): - TRAS lock - Dual switcher valve - Lock control switches. (1)The TRAS Locks are solenoid controlled and pneumatically operated locks. The locks are installed on the upper side of the center ballscrew gearboxes, one on each thrust reverser half (Ref. Fig. 017 ). (2)The Dual Switcher Valve is installed on the right hand thrust reverser. The valve receives air pressure signals fromm the two TRAS Locks and sends a pneumatic signal to open the PRSOV when both TRAS Locks are unlocked. (3)The lock control switches are installed in the micro switch pack assembly in the forward section of the pilot control stand. The lock control switches, one for each engine, are a part of a separate electrical circuit that controls the TRAS Lock system.

R **ON A/C ALL

10. Pressure Regulating and Shut Off Valve ______________________________________

A. General During thrust reverser operation the pressure regulating and shut off valve limits the air pressure which powers the pneumatic drive actuator to 55 psi (3.79 bars) with a tolerance of ± 5 psi (0.34 bars). The pressure regulating and shut off valve also prevents bleed air leakage during other operating sequences. The pressure regulating and shut off valve is located in the forward compartment of the engine compressor in the oQclock position (Z 454/464).

B. Description (Ref. Fig.018 and 019) The pressure regulating and shut off valve comprises : - A pneumatic actuator - A butterfly plate - A return spring - A self-cleaning filter - A ratchet wheel assembly - A shut off valve - A pyro check valve - A pilot regulator - An overpressure valve


�� G E � � � � CF6 - 50 � ��

TRAS Lock and Dual Switcher Valve Figure 016


�� G E � � � � CF6 - 50 � ��

TRAS Lock Control System Schematic Figure 017


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Pressure Regulating and Shut off Valve Figure 018

- An air vent valve.


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Pressure Regulating and Shut off Valve - Schematic Figure 019


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C. Operation The pressure regulating and shut off valve is operated when the overpressure and shut off valve control solenoid (P8) is energized. Air pressure from the engine is routed to the pressure regulating and shut off valve through the filter, the air vent valve, the pyro check valve, the pilot regulator and the pneumatic switch inside the overpressure and shut off valve. The air pressure enters chamber A and acts upon the diaphragm of the pneumatic actuator. The butterfly plate opens. As the pressure increases in chamber B, this compensates the pressure in chamber A and modulates the position of the butterfly plate. Air pressure downstream of the pressure regulating and shut off valve is maintained at a constant specific value. When the overpressure and shut off valve control solenoid is no longer energized, the pressure regulating and shut off valve closes. Air pressure in chamber A falls to zero psig. The return spring closes the butterfly plate automatically. The overpressure and shut off valve functions in the event of pilot regulator failure. In the event of overtemperature, the stem of the pyro check valve melts. The supply pressure pushes the valve against its seat, thus stopping air flowing toward the pilot regulator. The manual control override hex of the ratchet wheel is mounted on the butterfly shaft ; it allows the butterfly plate to be locked in the closed position. The air vent valve operated by the ratchet wheel assembly prevents the pressurized air from flowing toward the pilot regulator and vents chamber A of the pneumatic actuator to atmosphere before the butterfly plate closes.


�� G E � � � � CF6 - 50 � ��R 11. Directional Control Valve _________________________

A. Description (Ref. Fig. 020 ) The directional control valve is a mechanically actuated, normally open popped valve. Components of the valve include 2 housings, a pull arm, a spring-loaded slide valve, a poppet valve seat and 2 pull arm links.

B. Operation The valve is closed by movement of the control lever to the deploy position. Pilot valve closure permits pressure to build up in the directional control valve actuator within the pneumatic drive actuator, and causes actuation of the directional control valve to the deploy position. Upon reversal of the control lever, the pilot valve opens to vent the directional control valve actuator, and thereby permits the actuator spring to move the directional control valve to the stow position.

Directional Control Valve Figure 020


�� G E � � � � CF6 - 50 � ��R 12. Pneumatic Switcher Valve ________________________

A. Description (Ref. Fig. 021 ) The pneumatic switcher valve is a mechanically actuated, normally closed poppet type vent valve. Components of the valve include a housing, a mounting plate containing 2 spring-loaded rods, 2 spring-loaded poppet valves, and 2 poppet valve seats.

B. Operation When the fan reverser reaches a point approximately 4 in. from end of stroke, the switcher valve is actuated by a cam moving at the same rate as the fan cowl. When actuated, the switcher valve resets the pneumatic drive actuator to a low speed setting and limits torque output. At the beginning of stroke, deactivation of the switcher valve allows reset of the drive actuator to full speed and torque output. One poppet valve functions during reverser deployment and the other functions during stowing.

Pneumatic Switcher Valve Figure 021


�� G E � � � � CF6 - 50 � ��R 13. Throttle and Thrust Reverser Interlock Valve ____________________________________________

A. Description (Ref. Fig. 022 ) The throttle and thrust reverser interlock valve is a mechanically actuated, 2-way pneumatic selector valve. Components of the valve are an actuator arm, 2 sliding poppet valves and a body containing a vent port, throttle lock actuator port and a supply pressure port.

B. Operation The valve is designed to supply a pneumatic signal to the throttle interlock actuator, preventing the pilot from applying full engine power until the fan reverser is within 95 per-cent of the fully deployed position. The valve is spring-loaded to a position exposing the throttle lock actuator port to vent while sealing the supply pressure port. When actuated to the second position, the poppet valve closes the vent port, thereby pressurizing the throttle lock actuator port.

Throttle and Thrust Reverser Interlock Valve Figure 022


�� G E � � � � CF6 - 50 � ��R 14. Overpressure and Shut Off Valve _______________________________

A. Description (Ref. Fig. 023 ) The overpressure and shut off valve is a pneumatically operated, solenoid controlled butterfly valve. Components of the valve include a housing with closure element, actuator switcher valve, orverpressure control switch with a manual knob and latching switch and mechanically controlled indicator switch, and a relief valve.

B. Operation The valve functions to prevent system overpressure in the event of failure of the primary system pressure regulating valve by closing to shut off engine bleed air-flow when pressure exceeds 145 psi. (9.99 bars). The valve is installed in the duct between the pneumatic drive actuator and the pressure regulating and shut off valve. When the valve control solenoid is energized the valve opens to permit the flow of pressure regulated bleed air through the system. The valve closes when the solenoid is de-energized or upon loss of electrical power. If an overpressure condition has occurred, the valve is incapable of re- opening until the latching mechanism is manually reset.


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Overpressure and Shut Off Valve Figure 023


�� G E � � � � CF6 - 50 � ��R 15. Fan Reverser Indicator Switches _______________________________

A. Description (Ref. Fig. 024 ) Fan reverser indicator switches are double-pole, double-throw, plunger- actuated switches used to actuate aircraft stow and deploy indicator and warning lights. In addition, the switches complete a circuit to the inlet shut off valve when the stow signal is given. Two switches are mounted at each fan reverser feedback bracket.

B. Operation The indicator snap switches are normally engaged in the actuated position by a compression spring. As force is applied to the switch plunger by a cam action of the feed-back system, the actuator beam releases the snap switches and de-actuates the circuit. Releasing the plunger reactuates the snap switches.

Fan Reverser Indicator Switch Figure 024


�� G E � � � � CF6 - 50 � ��R 16. Fan Reverser Flexible Drive Shafts __________________________________

A. Description (Ref. Fig. 025 ) The fan reverser flexible drive shafts are 6 carbon steel core shafts of varying lengths. These shafts are enclosed by conduits with end-coupling plates for fastening the units to the gearbox mounting pads.

B. Operation The flexible drive shafts are used to transmit power from the system drive actuator to the gearboxes and to maintain system synchronization.

Fan Reverser Flexible Drive Shafts Figure 025


�� G E � � � � CF6 - 50 � ��R 17. Fan Reverser Electrical Cable _____________________________

A. Description The fan reverser electrical cable assemblies are approximately 110 in. (2.794 m) long and consist of 3 connectors joined by a Y-type flexible lead.

B. Operation The fan reverser cables connect the fan reverser indicator switches (2 on each reverser half) with the aircraft interface connectors. This circuit, when completed, transmits a signal to the flight compartment which indicates fan reverser position. The cable also provides a circuit from indicator switches, on the fan reverser left half, to the overpressure and shut off valve. When the fan reverser is in the deployed or stowed position, this circuit de-energizes the valve solenoid thus shutting off CDP (compressor discharge pressure) air to the fan reverser pneumatic drive actuator.


�� G E � � � � CF6 - 50 � ��R 18. Pneumatic Check Valve _____________________

A. Description (Ref. Fig. 026 ) The pneumatic check valve is a single-flapper gate type check valve, and consists of a housing provided with a compressor discharge pressure (CDP) air port, outlet to the fan reverser system, and filter.

B. Operation During aircraft engine operation, the flapper is pressurized against the environmental control system (ECS) air port preventing fan reverser flow into the environmental control system, while engine bleed air is permitted to flow from the compressor discharge pressure (CDP) air port to the fan reverser actuation system. For ground check-out of the fan reverser actuation system (engine not operating), pressurized air from the environmental control system (ECS) will swing the flapper to the opposite air port, permitting airflow into the fan reverser system, while preventing reverser-flow into compressor discharge pressure (CDP) air port.

Pneumatic Check Valve Figure 026


�� G E � � � � CF6 - 50 � ��R 19. Bleed Air Regulator Valve _________________________

A. Description The bleed air regulator valve consists of a housing and adjustable bleed orifice. The valve is installed in the deploy tube between the pneumatic drive actuator and pneumatic switcher valve.

B. Operation The bleed air regulator valve is used to time and synchronize the flight compartment deploy indicating lights. The deploy indicating lights are controlled by the deploy switch on the left hand feedback mechanism. The deploy switch is actuated approximately in the same reverser position that the pneumatic drive actuator changes from high speed to low speed operation. Due to normal system tolerances, The pneumatic drive actuator may change speeds before or after the switch is actuated. Adjustment of the valve varies the point at which the pneumatic drive actuator changes speeds such that it occurs at the point that the indicator switch is actuated.

R 20. Throttle Interlock Actuator ___________________________

A. General The throttle interlock actuator, located in the engine pylon (Z414/424), opposes engine full thrust operation by stopping the displacement of the thrust reverser control lever further than the idle position as long as the thrust reversers are not 90% deployed.

B. Description (Ref. Fig.027 and 028) The throttle interlock actuator is made up of : - A cylinder - A return spring - A stop ring - A stop shoulder - A piston with a return spring - A rod - A locking cup - A lock bushing attached to the rod - A dog - An air pressure inlet port.

C. Operation When the thrust reversers are deployed without reaching the 90% deployed position, the piston rod is immobilized by means of the lock bushing engaged in the dog teeth. A stop on the secondary transmission pulley coming into contact with a crank lever linked to the shaft of the throttle interlock actuator thus blocks off the thrust reverser control lever in the reverse idle position. As soon as the thrust reversers are 90% deployed, the throttle and thrust reverser interlock valve, operated by the RH fan thrust reverser cowl, directs air pressure towards chamber A. The air pressure pushes the piston which moves up to the stop shoulder.


�� G E � � � � CF6 - 50 � ��

Throttle Interlock Actuator Figure 027


�� G E � � � � CF6 - 50 � ��

Throttle Interlock Actuator Figure 028


�� G E � � � � CF6 - 50 � �� Under air pressure, the piston rod is released from the dog teeth. The piston and rod assembly moves compressing the return spring. The secondary transmission pulley is then released and the thrust reverser control lever can move up to the reverse full throttle position. NOTE : The return spring load is sufficient to draw the thrust reverser ____ control lever to the idle position in the event of noticeable pressure drop in chamber A. During thrust reverser retraction, air pressure falls to zero psig in chamber A. The return spring extends, the lock bushing is engaged in the dog teeth and the piston and rod assembly returns to the initial position.


�� G E � � � � CF6 - 50 � ��R 21. Safety Valve ____________

A. General The safety valve is located in the pneumatic duct which connects the air conditioning system to the pneumatic drive actuator, upstream of the pneumatic check valve (Z 454/464). The safety valve is operated pneumatically.

B. Description (Ref. Fig. 029 ) The safety valve is made up of : - A body - A valve and its housing - Springs - A cover

C. Operation The safety valve prevents overpressurized air from flowing from the 14th stage of the engine compressor to the aircraft pneumatic system. The safety valve is normally open. It is automatically closed by the overpressurized flow. Safety valve reset is performed manually from the ground.


�� G E � � � � CF6 - 50 � ��

Safety Valve Figure 029


�� G E � � � � CF6 - 50 � ��R 22. Feedback System _______________

A. General The feedback system is the mechanical means required for operating the throttle interlock valve, the pneumatic switcher valve and the control and indicator switches during thrust reverser operation.

B. Description (Ref. Fig. 030, 031 and 032) The feedback system comprises : (1)On the LH side of the fan thrust reverser : - A feedback system attached to the forward structure of the thrust reverser in the 7 oQclock position - cams - Two levers which operate the pneumatic switcher valve - Two levers which operate the indicator switches - A cam control lever fixed on the translating cowl - Return springs. (2)On the RH side of the fan thrust reverser : - A feedback system attached to the forward structure of the thrust reverser in the 5 oQclock position. - Cams which operate the levers actuating the indicator switches. - Two levers which operate the indicator switches - A cam which operates the throttle and thrust reverser - Interlock valve - A cam control lever attached to the translating cowl - Return springs.

C. Operation During thrust reverser operation, the translating cowls displace the cams by means of the control levers. The cams act upon the indicator switches, the pneumatic switcher valve and the throttle and thrust reverser interlock valve by means of levers. Cam-operated Accessories - Summary Table --------------------------------------------------------------------------- Translating cowl displacement Accessories operated --------------------------------------------------------------------------- Between 1% and 2% position Indicator switches (P3) and (P7) 10% position Pneumatic switcher valve Push-rod in the ?stowed? position 90% position Throttle and thrust reverser interlock valvee Indicator switch (P6) Pneumatic switcher valve Push-rod in the ?deployed? position Above the 98% position Indicator switches (P4) and (P6)

R 23. Thrust Reverser Control and Indicating ______________________________________

A. General The thrust reverser electrical control system energizes the solenoid which


�� G E � � � � CF6 - 50 � ��

Fan Thrust Reverser - LH Side - Feedback System Figure 030


�� G E � � � � CF6 - 50 � ��

Fan Thrust Reverser - RH Side - Feedback System Figure 031


�� G E � � � � CF6 - 50 � ��

Feedback System - Schematic Figure 032


�� G E � � � � CF6 - 50 � �� opens the overpressure and shut off valve on the pneumatic supply. The thrust reverser operational sequences are monitored from the flight compartment by an indicating system. NOTE : The thrust reverser control lever can be operated only when the ____ respective throttle control lever is in idle position.

B. Description (Ref. Fig. 005 ) (Ref. Fig. 033 ) The electrical control and indicating system is made up of : - Circuit breaker 1KM (2KM) located on Panel 123VU (zone 212), - Circuit breaker 3KM (4KM) located on Panel 123VU (zone 212), - Microswitch 7KM (8KM) located on microswitch unit 113VU (112VU) (zone 121/122), - Relay 125GB located in the forward relay box 104VU and operated by the proximity sensor on the corresponding main gear torque links, - Relay 3LT (6LT) which dims the indicator lights, - A two-pole fan thrust reverser stow position indicator swithc 13KM (14KM) on the RH side (zone 452/462), - A two-pole fan thrust reverser stow position indicator switch 15KM (16KM), on the LH side (zone 451/461), - A two-pole fan thrust reverser deploy position indicator switch 17KM (18KM) on the LH side (zone 451/461), - A two-pole fan thrust reverser deploy position indicator switch 19KM (20KM), on the RH side (zone 436/446), - An overpressure and shut off valve position indicator switch 23KM (24KM) (zone 452/462), - An overpressure and shut off valve control solenoid 21KM (22KM) (zone 452/462), - A green REV indicator light 11KM (12KM) located on panel 230VU, - An amber REV UNLK warning light 9KM (10KM) located on panel 230VU.

C. Operation (1)Aircraft in Flight The main landing gear shodk-absorber is extended, relay 125GB (124GB) is in the non-energized position. This displacement of the thrust reverser control lever is without effect as solenoid 21KM (22KM) is not energized. (2)Aircraft on thr Ground The main landing gear shodk-absorber is compressed, relay 125GB-124GB is energized. (a)Thrust reverser is deployment This displacement of the thrust reverser control lever rotates microswitch 7KM (8KM) to the ?deployed? position. Solenoid 21KM (22KM) is energized through indicator switch 19KM (20KM) which is in the ?stowed? position. The overpressure and shut off valve opens and supplies air to the pneumatic drive actuator (in deployment direction). Operation of the pneumatic drive actuator unlocks thrust reverser assembly which moves towards the deployed position. As soon as the thrust reverser assembly is unlocked, indicator switches 13KM (14KM) and 15KM (16KM) make the ?unlocked? position.


�� G E � � � � CF6 - 50 � ��

Location of Thrust Reverser Indicator Switches Figure 033


�� G E � � � � CF6 - 50 � �� Amber REV UNLK warning light connected to ground via the contacts of indicators switches 17KM (18KM) and 19KM (20KM) comes on remains on during thrust reverser deployment. When the thrust reverser has fully deployed, indicator switches 17KM (18KM) and 19KM (20KM) make the ?deployed? contacts. Solenoid 21KM (22KM) is de-energized and the overpressure and shut off valve closes. - Amber REV UNLK warning light goes off - Green REV indicator light comes on - Thrust reversers are ?locked deployed? - Reverse full throttle can be applied. (b)Thrust reverser stowage (Ref. Fig. 034 ) When the thrust reverser control lever returns to the 0• (reversers stowed) position, microswitch 7KM (8KM) makes the ?stowed? contact. Solenoid 21KM (22KM) is energized via indicator switches 13KM (14KM) and 15KM (16KM). The overpressure and shut off valve opens and supplies air to the pneumatic drive actuator (in the ?stowed? direction). Operation of tha pneumatic drive actuator causes the thrust reversers to unlock and initiate stowage sequence. As soon as the thrust reversers start moving, indicator switches 17KM (18KM) and 19KM (20KM) make the ?stowed? contacts. - Amber REV UNLK warning light comes on and remains on during stowage sequence. - Green REV indicator light goes off. - When the thrust reversers are fully stowed, indicator switches 13KM (14KM) and 15KM (16KM) make the ?locked? contact. - Solenoid 21KM (22KM) is de-energized and the overpressure and shut off valve closes. - Amber REV UNLK warning light goes off. The thrust reversers are in the ?locked - stowed? position NOTE : During operation, amber REV UNLK warning light comes on if ____ one thrust reverser half at least is in intermediate position. ------------------------------------------------------------------------------ THRUST REVERSER INDICATING - SUMMARY TABLE ------------------------------------------------------------------------------ Overpressure | closed | open | cloded | open | closed | open | and shut-off | | | | | | | valve | | | | | | | | | | | | | | Fan reverser | stowed | stowed |unlocked|unlocked|deployed |deployed| | | | | | | | REV UNLK war- | off | on | on | on | off | off | ning light | | | | | | | | | | | | | | REV indicator | off | off | off | off | on | on | light | | | | | | | | | | | | | | Full reverse | No | No | No | No | No | No | throttle applied | | | | | | | ------------------------------------------------------------------------------


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Thrust Reverser Electrical Control and Indicating Figure 034


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R 24.Nacelle Temperature Sensor __________________________ A. General (Ref. 78-31-31, P. Block 201) The nacelle temperature sensor is attached to the lower section of the LH half thrust reverser cowl of each engine and measures temperature variation in the cavity between the compressor casing and the fan reverser cowl. The sensor resistance varies as temperature changes and this generates a signal that is transmitted to the aircraft data system and to the crew members on panel 55VU by means of indicators 3EB and 4EB. Data from this system provides information on possible excessive duct leakage.

R 25.Nacelle Temperature Sensor Electrical Cable ___________________________________________

A. Description The nacelle temperature sensor electrical cable is approximately 170 in. (4.30 m) long and consists of two connectors joined by a flexible lead and attached to the front face of the LH half thrust reverser cowl of each engine.

B. Operation Sensor resistance variation signals, which are proportional to nacelle air temperature, are transmitted through the electrical cable to the aircraft data system. This data is used to determine excessive pneumatic duct leakage.


�� G E � � � � CF6 - 50 � �� THRUST REVERSER SYSTEM CONTROL - MAINTENANCE PRACTICES ______________________________________________________

NOTE : The engines may be equipped with one of the following thrust reverser ____ system variants : - either a fan reverser system and deactivated turbine reverser system - or only a fan reverser system with a fixed exhaust nozzle. The following maintenance practices apply to fan reverser systems and are identical for LH and RH thrust reverser systems. A functional test (Ref. 78-30-00, P. Block 501) is required after repair, removal, replacement or adjustment of any thrust reverser component, including pneumatic drive actuator or control system components.

CAUTION : ON COMPLETION OF ANY THRUST REVERSER SYSTEM MAINTENANCE, VISUALLY _______ CHECK SURROUNDING AREAS FOR COMPONENTS SECURITY. SPECIFICALLY, CHECK FLEXIBLE SHAFT CONNECTIONS AT GEAR-BOXES AND BALLSCREW ACTUATORS, PNEUMATIC DRIVE ACTUATOR AND PNEUMATIC TUBE CONNECTIONS. USE CORE COWL MAINTENANCE STEP IF REQUIRED WHEN PERFORMING MAINTENANCE INSIDE REVERSER HALF. STEPPING ON OTHER AREAS OF CORE COWL COULD RE- SULT IN DAMAGE TO FIRE PROTECTION COATING.

NOTE : Check the cowl door ring and latch assembly dimensional requirements per ____ chapter 78-36-00, prior to any functional checks of the thrust reverser.

1. Reason for the Job __________________ Repair, removal, replacement or adjustment of any thrust reverser component.

2. Equipment and Materials _______________________ ------------------------------------------------------------------------------- ITEM DESIGNATION ------------------------------------------------------------------------------- A. Access Platform 3 m (10 ft.) B. Starting Pneumatic Ground Power Unit C. Electrical Ground Power Unit, 3-Phase, 115/200V, 400Hz, 90KVA D. Torque Wrench E. Square Drive, 3/8 in. dia. F. 98A78303500000 Extension - Flexible G. 2C6105 Adapter Drive H. 2C6900 Tool - Installation J. Circuit Breaker Safety Clips K. Corrosion-Resistant Steel Lockwire Dia. 0.032 in. (0.8 mm) L. Corrosion-Resistant Steel Lockwire Dia. 0.020 in. (0.5 mm) M. Warning Notices N. 29644-1 Spanner Wrench AdapterR O. Material C02-004 Anti-Seize Compounds, Lubricants, Oils (Ref. 20-32-00) P. Material C02-014 Anti-Seize Compounds, Lubricants, Oils (Ref. 20-32-00) Q. Material C02-015 Anti-Seize Compounds, Lubricants, Oils (Ref. 20-32-00)


�� G E � � � � CF6 - 50 � �� ------------------------------------------------------------------------------- ITEM DESIGNATION ------------------------------------------------------------------------------- R. Material C02-017 Anti-Seize Compounds, Lubricants, Oils (Ref. 20-32-00) S. Material C02-023 Oils (Ref. 20-32-00) T. Material C02-037 Anti-Seize Compounds, Lubricants, Oils (Ref. 20-32-00) U. Material C02-041 Anti-Seize Compounds, Lubricants, Oils (Ref. 20-32-00) V. Material C02-043 Common Greases (Ref. 20-32-00) W. Material C02-044 Anti-Seize Compounds, Lubricants, Oils (Ref. 20-32-00) X. G. Rapid Spray Y. Paint, Finch 443-3-1022 or Equivalent Referenced Procedures - 24-41-00, P. Block 301 External Power - 36-00-00, P. Block 1 Pneumatic System - 71-13-00, P. Block 301 Cowl Doors - 78-00-00, P. Block 401 Exhaust - 78-30-00, P. Block 501 Thrust ReverserR - 78-32-11, P. Block 401 Translating Cowl

R **ON A/C 001-103, 106-999,

- 78-31-53, P. Block 401 TRAS Lock - 78-32-00, P. Block 801 Fan Reverser Assembly - Approved Repairs


�� G E � � � � CF6 - 50 � ��

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A. Job Set-Up (1)Open, safety and tag the circuit breakers for the appropriate engine (Ref. 71-13-00, P. Block 301) and open the fan cowl doors. (2)Display a warning notice on the panel 123VU prohibiting maneuvers. (3)Position access platforms. (4)Connect pneumatic ground power unit at HP ground connections (Ref. 36-00-00, P. Block 1). (5)Connect electrical ground power unit and energize the aircraft electrical network (Ref. 24-41-00, P. Block 301).

B. Miscellaneous Operations (1)Fan Reverser Translation (Ref. Fig. 201 ) CAUTION : THE FAN REVERSER TRANSLATION IS NORMALLY ACCOMPLISHED WITH THE _______ HALVES CLOSED. IF TROUBLESHOOTING REQUIRES TRANSLATION WITH THE REVERSER HALVES OPEN, THE FOLLOWING PRECAUTIONS MUST BE TAKEN OR DAMAGE TO THE EQUIPMENT CAN OCCUR. DO NOT TRANSLATE FAN REVERSER WITH EITHER HALF OPEN MORE THAN 20 DEGREES. THE TRANSLATION MUST BE ACCOMPLISHED MANUALLY OR USE THE LOW SPEED MODE. FOR ALL MAINTENANCE PROCEDURES INSIDE THE COWLS, EXTEND THE HOLD-OPEN RODS TO HOLD THE COWLS OPEN. Translate fan reverser for troubleshooting, maintenance or inspection purposes as follows : CAUTION : AFTER SB 78-207 THE 5/16 INCH FLEXSHAFT IS LESS TOLERANT OF _______ SHORT RADIUS TURNS THAN THE 1/4 INCH FLEXSHAFT. (a)Disconnect flexible shaft between pneumatic drive actuator and center gearbox from center gearbox input socket. NOTE : Remove the clamp adjacent to the center gearbox before ____ disconnecting shaft. (b)Not applicable.

R **ON A/C 001-103, 106-999,

(b)Manually release the TRAS lock. 1 Pull the T-handle approximately 0.35 inch (9 mm). _ 2 Remove the manual release lever from the retaining clip and turn the _ lever to engage the collar. 3 Release the T-handle. _

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(c)Remove cover plate and gasket from lower side of center gearbox. (d)Insert flexible extension 98A78303500000 in gearbox socket and translate reverser half as necessary. (e)With reverser stowed and maintenance action complete, adjust drive


�� G E � � � � CF6 - 50 � ��

Fan Reverser Translation Figure 201


�� G E � � � � CF6 - 50 � �� shaft (Ref. Adjustment/Test para. C). (f)Install gasket and cover plate at lower side of center gearbox. (g)Close fan cowl. (2)Fan reverser deactivation (Ref. 78-00-00, P. Block 401). (3)Fan reverser reactivation (Ref. 78-00-00, P. Block 401).


�� G E � � � � CF6 - 50 � ��

C. Adjustment/Test NOTE : The following thrust reverser adjustment/test procedures apply to ____ engines equipped with a fan reverser system. (1)Thrust reverser system riggingR CAUTION : BEFORE YOU RIG (ADJUST) THE TRANSLATING COWL, YOU MUST DO A _______R VISUAL INSPECTION OF THE ACTUATOR CLEVIS FITTINGS AND THER SURROUNDING STRUCTURE. IF YOU DO NOT DO THIS INSPECTION, DAMAGER THAT IS THERE WILL NOT BE SEEN AND MORE DAMAGE CAN OCCUR.R (2)Do a visual inspection of the three actuator clevis fittings and theR surrounding structure.R (a)Do a visual check of the integrity of the clevises to which theR actuator rod end bearings attach. There must be no indication of theR clevises pulling away from their attaching surfaces. If there areR indications, replace the translating cowl (Ref. Fig. 202 ) andR (Ref. 78-32-11, P. Block 401). CAUTION : IF THE DRIVESHAFT FROM DRIVE ACTUATOR TO EITHER THE FAN _______ REVERSER HALF IS DISCONNECTED, ALL DRIVESHAFTS MUST BE RIGGED TO PREVENT UNBALANCED PRELOAD BUILDUP, ALSO POSSIBLE CABLE OR SHEAR SECTION FAILURES.R (b)Translating cowl gap rigging NOTE : If gap between fan reverser translating cowl and support assem- ____ bly is not less than 0.060-0.150 in. (1.52-3.81 mm) proceed as follows : 1 Disconnect fan reverser drive shaft at center gearbox. _ NOTE : Remove shaft clamp adjacent to gearbox before disconnecting ____ shaft. 2 Remove plate and gasket opposite center gearbox input shaft and insert _ locally manufactured splined adapter or 5/16 inch (7.9 mm) hexhead wrench. Rotate shaft socket until actuator hits stop or cowl motion ceases. 3 Not applicable. _ 4 Not applicable. _ 5 Not applicable. _ 6 Not applicable. _ 7 Not applicable. _ 8 Not applicable. _

R **ON A/C 001-103, 106-999,

3 Manually translate the translating cowl a minimum of 1 inch (25.4 mm) _ in the deploy direction. NOTE : This procedure uses a splined adapter tool that you insert ____ into the manual drive pad on the center ballscrew gearbox assembly. You can attach a torque wrench to the splined adapter. If necessary, you can make the splined adapter tool for the end of a discarded flexshaft cable (Ref. Fig. 203 ). NOTE : To prevent the incorrect torque reading, make sure you deploy ____ the translating cowl a minimum of 1 inch (25.4 mm). This will remove all torque that can be the result of contact between the translating cowl bumpers and the fixed structure.


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Rigs Marks on Cam and Cam FollowerR Figure 202


�� G E � � � � CF6 - 50 � �� 4 Manually engage the TRAS lock. _ a Pull the T-handle approximately 0.1 inch (2.54 mm). _ b Turn the manual release lever away from the fan cowl. _ c Engage the manual release lever in the retaining clip. _ d Release the T-handle. _ 5 With the manual drive lockout cover removed, install the locally made _ splined adapter tool and a dial-type torque wrench into the manual drive pad of the center ballscrew gearbox assembly (Ref. Fig. 204 ). 6 Make sure the pneumatic drive motor brake is applied. _ 7 Turn the torque wrench in the deploy direction until the torque is _ 180 lbf.in. (2.03 m.daN). NOTE : Put a mark on the point where you start to apply torque. This ____ will help you know how far turned the wrench in the next step. a The TRAS lock system operates correctly if you reach 180 lbf.in. _ (2.03 m.daN) of torque before you turn the wrench one-half of a turn. b If you so not reach 180 lbf.in. (2.03 m.daN) of torque, make sure _ you turned the wrench in the deploy direction. If you turn the wrench in the deploy direction and can not reach 180 lbf.in. (2.03 m.daN) of torque, you must replace the TRAS (Ref. 78-31-53, P. Block 401). c Record the results of the holding torque check. _ d Turn the wrench slowly in the stow direction to release the torque. _ Turn the wrench until you reach 0.0 lbf.in. (0.0 m.daN) of torque. e Install the pad cover and the gasket (or the splined lock) on the _ lower side of the center ballscrew gearbox assembly with the two bolts. 8 Manually release the TRAS lock. _ a Pull the T-handle approximately 0.35 in. (8.9 mm). _ b Remove the manual release lever from the retaining clip, and turn _ the lever to engage the collar. c Release the T-handle. _

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9 With reverser on stow stops, disconnect flexible shafts at center _ gearboxes. CAUTION : AFTER SB 78-207 THE 5/16 INCH FLEXSHAFT IS LESS TOLERANT OF _______ SHORT RADIUS TURNS THAN THE 1/4 INCH FLEXSHAFT. NOTE : Remove shaft clamps adjacent to gearboxes before disconnecting ____ shafts. 10 With actuators on stow stops, measure gap between support assembly and _ translating cowl gap must be 0.060 to 0.150 in. (1.5-3.8 mm) at centerline of all 3 actuators. NOTE : To hold angle gearboxes on stow stops, use adapter, 2C6105, in ____ gearbox sockets opposite shafts or disconnect the interconnecting flex shaft conduit from the angle gearboxes and retract sufficiently to permit insertion of an adjustable or 5 mm wrench on square end of core. The core must remain inserted into the angle gearbox. (Ref. Fig. 220 )


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Splined Lock (P/N9149M85G01) or Pad Cover and Gasket on the Center Gearbox (TRAS Lock Not Shown) Figure 203 ��R �EFFECTIVITY: 001-103, 106-999, �� 78-31-00 � � � � Page 209 � � JAS Mar 01/07

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Splined Adapter Tool Figure 204


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R **ON A/C 001-103, 106-999,

(Ref. Fig. 205 )

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11 If gap is still not within limits ; adjust ballscrew rod end bearing __ until gap is within limits. To adjust rod end bearings, loosen jam-nut and rotate CCW to lengthen AND CW to shorten. (Ref. Fig. 206 ) CAUTION : AFTER ROD END BEARING ADJUSTMENT, A 0.055 IN. (1.40 MM) _______ DIA. PIN MUST NOT PASS THROUGH ACTUATOR WITNESS HOLE. NOTE : Each revolution of rod end bearing equals approximately 0.042 ____ in. (1.06 mm). (b)Before SB 78-207 rig fan reverser interconnecting flex shafts (Ref. Fig. 220 )

R **ON A/C 001-103, 106-999,

(Ref. Fig. 205 )

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1 Engage shaft in end gearbox. TORQUE flange bolts to between _ 33 and 37 lbf.in. (0.37 and 0.42 m.daN). 2 Hold end gearbox and center gearbox on stow stops. _ 3 Insert shaft into the center gearbox. If the shaft square drive _ end is not aligned to gearbox drive, relax the gearbox only enough to permit the shaft drive to enter. NOTE : The absolute maximum that the center gearbox should be relaxed ____ is one flat of the drive square into which the shaft is being inserted.

R **ON A/C 001-103, 106-107, 109-999,

3 Insert shaft into the TRAS lock socket. If the shaft square drive _ end is not aligned to the socket, relax the gearbox only enough to permit the shaft drive to enter. NOTE : The absolute maximum that the center gearbox should be relaxed ____ is one flat of the drive square into which the shaft is being inserted.

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4 TORQUE flange bolts to between 33 and 37 lbf.in. (0.37 and 0.42 _ m.daN). 5 Repeat for other interconnecting shafts. _ 6 Partially translate the cowl and restow using center gearbox _ input socket. Running torque must not exceed 25 lbf.in. (0.28 m.daN) to translate cowl within gap limits.


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LH and RH Shaft Engagement - Post SB 78-022 Figure 205


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Actuator Rod End Bearing Adjustment Figure 206


�� G E � � � � CF6 - 50 � �� 7 If the torque limit is exceeded, check the following and correct as _ necessary: a actuator lubrication, _ b interference between the cowl and support, _ c interference between the cowl bumpers and the outer ring. Shim as _ necessary (Ref. 78-32-00, P. Block 801, Step 3.L., Translating Cowl Bumper Replacement). 8 With reverser stowed and translating cowl gap within limits, rig _ fan reverser main (motor-to-center gearbox) flexshaft.


�� G E � � � � CF6 - 50 � �� (c)After SB 78-207 alternate rig reverser flexible shafts (Ref. Fig. 208 ). NOTE : The pneumatic drive motor brake must be manually released before ____ removing the main drive shaft from the center gearbox. After SB 78-207 it is acceptable to have 5/16 inch cables installed on one reverser half at a given position with 1/4 inch cables on the other half.

R **ON A/C 001-103, 106-999,


�� G E � � � � CF6 - 50 � �� (c)After SB 78-207 alternate rig reverser flexible shafts (Ref. Fig. 207 ). NOTE : The pneumatic drive motor brake must be manually released before ____ moving the main drive shaft from the TRAS lock assembly. After SB 78-207 it is acceptable to have 5/16 inch cables installed on one reverser half at a given position with 1/4 inch cables on the other half.

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1 Remove attaching hardware and cover plates from the spline opposite _ the driven spline in the end gearboxes. 2 Insert a 0.20 in. (5.08 mm) square tool in the exposed end and rotate _ until the actuator engages its stow stop. 3 Maintain actuator position against stow stop. _ NOTE : When the true stow stop is reached, a positive, metallic ?click? ____ will be heard when the ballscrew reaches the fully forward position. CAUTION : DURING SPLINE INSERTION, DO NOT PERMIT THE WRENCH TO ROTATE _______ MORE THAN 30• WHICH IS ONLY ONE TOOTH OF THE 12 POINT SPLINE. 4 While the end actuator is being held against the stow stops, using _ a 5/16 inch allen wrench inserted in the center gearbox lockout spline socket, drive the center gearbox against the stow stop and insert the interconnecting flexshaft 12 point spline in the adapter already installed on the center gearbox. If the spline does not drop in freely, slowly relax the wrench in the center gearbox to drive the center actuator in the deploy direction until insertion is possible. 5 Release the torque on the end gearbox and replace the end gearbox _ cover with previously removed attaching hardware. - TORQUE the bolts to between 33 and 37 lbf.in. (0.37 and 0.42 m.daN) and wirelock. 6 Assemble the flexshaft flange to the adapter with the bolts and _ washers. - TORQUE the bolts to between 33 and 37 lbf.in. (0.37 and 0.42 m.daN) and wirelock. 7 Repeat the above procedure for the remaining interconnecting _ flexshafts on the reverser. 8 Install the flexshaft in its applicable quick-opening clamp. _ - Close the clamp and engage the butterfly bolt/captured nut assembly in the slot in the clamp assembly. 9 Partially translate the cowl and restow using center gearbox input _ socket. Running torque must not exceed 25 lbf.in. (0.28 m.daN) to translate cowl within gap limits. 10 If torque limit is exceeded, check for actuator lubrication or inter- __ ference between cowl and support. Correct as necessary. 11 With reverser stowed and translating cowl gap within limits, rig fan __ reverser main (motor-to-center gearbox) flexshaft. (2)Thrust reverser system functional test (a)Perform functional test of thrust reverser system after maintenance as follows : 1 Close core cowls 455AL (465AL) or 456AR (466AR) (Ref. 71-13-00, P. _


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Rigging the Flex Shafs - Post SB 78-022 Figure 207


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Rigging the Flex Shafts Figure 208


�� G E � � � � CF6 - 50 � �� Block 301). CAUTION : CORE COWLS MUST BE CLOSED AND SECURED BEFORE INITIATION OF _______ ANY THRUST REVERSER SYSTEM OPERATION. WARNING : BEFORE CARRYING OUT ANY WORK ON THE FAN REVERSER SYSTEM, OR _______ WHEN PERFORMING THE FAN REVERSER FUNCTIONAL TEST, MAKE CERTAIN THAT THE AREA IS CLEAR OF PERSONNEL BEFORE CONNECTING OR DISCONNECTING THE APU OR PNEUMATIC GROUND POWER UNIT, TO THE THRUST REVERSER GROUND TEST CONNECTION, TO PREVENT DEATH OR SERIOUS INJURY TO PERSONNEL. CAUTION : BEFORE CONNECTING APU OR PNEUMATIC GROUND POWER UNIT TO _______ THRUST REVERSER GROUND TEST POINT, MAKE CERTAIN THE AREA AROUND THE TRANSCOWLS ARE CLEAR TO DEPLOY. 2 Remove cap and bleed air regulator valve from pneumatic switcher valve _ stow and deploy tubes. NOTE : With cap and valve removed, reverser system will translate at ____ slow speed. This will permit check for interference and smoothness of operation. 3 Remove safety clips and tags, and close circuit breakers for _ the appropriate engine (Ref. 71-13-00, P. Block 301). 4 Make certain that thrust reversers are clear of personnel and _ equipment.

5 Apply air to aircraft HP ground connections (Ref. 36-00-00, P. _ Block 1).

6 Energize aircraft electrical network (Ref. 24-41-00, P. Block 301). _R WARNING : WHEN YOU HOLD OPEN THE MANUAL RELEASE LEVERS OF THE _______R TRAS LOCKS, STAND CLOSE TO THE FAN CASE AREA AND AWAY FROMR THE TRANSLATING COWLS TO PREVENT INJURY WHEN THE TRANSLATINGR COWLS ARE CYCLED.

R 7 Unlock and manually hold open the manual release lever on the TRAS _R locks.R a Pull the T-handle approximately 0.35 inch (8.9 mm). _R b Remove the manual release lever from the retainig clip, and turn _R the lever to engage the collar.R c Release the T-handle. _R d Manually hold the manual release lever in the unlocked position _R while the translating cowls are cycled during the slow speedR operational check.

R 8 Proceed with 3 complete cycles of thrust reverser system. Check for _ proper operation. CAUTION : WHEN CYCLING THE FAN REVERSER DO NOT EXCEED 5 STROKES OF THE _______ TRANSLATING COWL WITHIN ANY 3 MINUTE PERIOD. THIS IS NECES- SARY TO PREVENT OVERHEATING THE PNEUMATIC DRIVE MOTOR. NOTE : A stroke is considered to be the movement of the cowl in any ____ direction.

R 9 Manually engage the TRAS locks _R a Pull the T-handle approximately 0.1 inch (2.54 mm). _


�� G E � � � � CF6 - 50 � ��R b Turn the manual release lever away from the fan cowl and insert _R the lever in the retaining clip.R c Release the T-handle. _R 10 Install regulator valve on deploy tube and cap on stow tube ; TORQUE _ to between 270 and 300 lbf.in. (22.5 and 25 lbf.ft.) (3.05 and 3.39 m.daN). Safety with 0.032 in. (0.813 mm) Dia. corrosion-resistant steel lockwire.R 11 Proceed with 3 complete cycles of thrust reverser system. _ (3)Deploy indicating light timing (Ref. Fig. 209 ) The reverser stroke position, at which the pneumatic drive motor changes from high speed operation to low speed operation, can be adjusted so that flight compartment deploy indicating lights will be synchronized. (a)Using 35-45 psig (2.41-3.10 bars) air at aircraft ground supply connection, deploy reverser. (b)Observe position of LH side feedback cam and indicator switch deploy cam follower for relative position during pause between high to low speed modes (Ref. Fig. 209 ). NOTE : Repeat deployment 3 times before adjustments to verify cam/cam ____ follower relative position. Pause between modes is approximately one second. (c)If reverser position is not within acceptable limits as verified by observing cam/cam follower position, adjust regulator as follows : CAUTION : BEFORE EACH RIGGING OPERATION, STOP GROUND AIR SUPPLY. _______ 1 Remove valve from housing. _ 2 While holding valve poppet with a 5/64 in. (2.0 mm) hex head wrench _ to prevent rotation, rotate nut at opposite end with a 3/16 in. (4.78 mm) wrench in the direction indicated in (Ref. Fig. 209 ). Rotate as required to bring travel within limits. NOTE : One turn of the adjustment screw equals about 0.1 in. (2.54 mm) ____ of feedback cam travel. Normally three turns will provide the required adjustment for a serviceable drive motor. 3 Install valve in housing ; TORQUE nut to betweem 270 and 300 lbf.in. _ (22.5 and 25 lbf.ft.) (3.05 and 3.39 m.daN). 4 Deploy reverser. Observe relative position of indicator switch cam _ and cam follower. Repeat three times. If further adjustment is required, remove valve and repeat paragraphs (c) 2 3 and 4. _ _ _ 5 If travel is within limits, safety with 0.032 in. (0.813 mm) dia. _ corrosion-resistant steel lockwire. (4)Thrust reverser functional test and indicating/warning sensors test. (Ref. Fig.210 and 211) WARNING : BEFORE YOU DO WORK ON THE THRUST REVERSER SYSTEM, OR WHEN YOU _______ DO THE THRUST REVERSER FUNCTIONAL TEST, MAKE SURE THAT THE WORK AREA IS CLEAR OF PERSONS BEFORE YOU CONNECT OR DISCONNECT THE APU OR PNEUMATIC GROUND POWER UNIT TO OR FROM THE THRUST REVERSER GROUND TEST CONNECTION, TO PREVENT DEATH OR SERIOUS INJURY TO PERSONS. CAUTION : BEFORE YOU CONNECT THE APU OR PNEUMATIC GROUND POWER UNIT TO _______ THE THRUST REVERSER GROUND TEST CONNECTION, MAKE SURE THE AREA AROUND THE THRUST REVERSER IS CLEAR OF PERSONS AND EQUIPMENT SO THAT THE TRANSLATING COWLS ARE FREE TO STOW AND DEPLOY. (a)Pressurize the pneumatic system (Ref. 36-00-00, P. Block 1) or use the


�� G E � � � � CF6 - 50 � ��

Deploy Indicating Light Timing Figure 209


�� G E � � � � CF6 - 50 � �� APU. (b)Test 1 Right sleeve stow and deploy switches test : _ - Disconnect plugs 15KM, 17KM, 23KM (16KM, 18KM, 24KM). - Connect the electrical ground power unit and energize the aircraft electrical system (Ref. 24-41-00, P. Block 301). ------------------------------------------------------------------------------- ACTION RESULT ------------------------------------------------------------------------------- - Move the thrust reverser control lever Check that : to the Rev idle position - REV UNLK warning light comes on when the translating sleeves move from the stowed position - REV UNLK warning light goes off when the translating sleeves are fully deployed

- Move the thrust reverser control lever Check that : to the reverser stowed position - REV UNLK warning light comes on when the translating sleeves move to the stowed position - REV UNLK warning light goes off when the translating sleeves are fully stowed

2 Left sleeve stow and deploy switches test : _ - De-energize the aircraft and disconnect the electrical ground power unit (Ref. 24-41-00, P. Block 301). - Disconnect plugs 13KM and 19KM (14KM and 20KM). - Connect plugs 15KM and 17KM (16KM and 18KM). - Install a locally manufactured shunt between pins B and C of plug 19KM (20KM). - Connect the electrical ground power unit and energize the aircraft electrical system (Ref. 24-41-00, P. Block 301). CAUTION : WITH THE SHUNT INSTALLED ON PLUG 19KM (20KM), THE _______ AIRCRAFT ELECTRICAL AND PNEUMATIC SYSTEMS ENERGIZED, AND THE THRUST REVERSER CONTROL LEVERS IN THE REV IDLE POSITION, PNEUMATIC PRESSURE WILL BE SUPPLIED CONTINUOUSLY TO THE THRUST REVERSER PNEUMATIC DRIVE MOTOR (PDM) UNTIL THE THRUST REVERSER IS RETURNED TO THE STOWED POSITION. AFTER YOU DEPLOY THE THRUST REVERSER AND VERIFY THE CORRECT LIGHT INDICATIONS, MAKE SURE TO RETURN THE THRUST REVERSER CONTROL LEVERS TO THE STOWED POSITION AS QUICKLY AS POSSIBLE TO PREVENT DAMAGE FROM PROLONGED OPERATION OF THE PDM. ------------------------------------------------------------------------------- ACTION RESULT ------------------------------------------------------------------------------- - Move the thrust reverser control lever Check that : to the Rev idle position - REV UNLK warning light comes on when the translating sleeves move from the stowed position


�� G E � � � � CF6 - 50 � �� ------------------------------------------------------------------------------- ACTION RESULT ------------------------------------------------------------------------------- - REV UNLK warning light goes off and REV indicator light comes on when reversers reach the deploy position

- Move the thrust reverser control lever Check that : to the reverser stowed position - REV indicator light goes off as the translating sleeves move from the fully deployed position - REV UNLK warning light comes on when the translating sleeves move to the stowed position - REV UNLK warning light goes off when the translating sleeves are fully stowed

- De-energize the aircraft and disconnect the electrical ground power unit (Ref. 24-41-00, P. Block 301). - Disconnect plugs 15KM and 17KM (16KM and 18KM). - Disconnect the shunt from pins B and C of plug 19KM (20KM).

3 Valve position test : _ - Connect plugs 19KM and 23KM (20KM and 24KM). - Connect the electrical ground power unit and energize the aircraft electrical system (Ref. 24-41-00, P. Block 301). NOTE : Plugs 13KM and 15KM (14KM and 16KM) must stay disconnected ____ to verify correct operation of the 23KM (24KM) valve position microswitch. ------------------------------------------------------------------------------- ACTION RESULT ------------------------------------------------------------------------------- - Move the thrust reverser control lever Check that : to the Rev idle position - REV UNLK warning light comes on when the translating sleeves move from the stowed position - REV UNLK warning light goes off when the translating sleeves are fully deployed

- Move the thrust reverser control lever Check that : to the reverser stowed position - REV UNLK warning light comes on when the translating sleeves move from the fully deployed position - REV UNLK warning light goes off when the translating sleeves are fully stowed (5)Landing gear ground function test


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Location of Thrust Reverser Indicator Switches Figure 210


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Thrust Reverser Indicator Switches Figure 211


�� G E � � � � CF6 - 50 � �� ------------------------------------------------------------------------------- ACTION RESULT ------------------------------------------------------------------------------- - On panel 128VU, open circuit breaker 2GB - Move thrust control lever to idle position - Move thrust reverser control lever Check that : to idle position - Translating sleeves remain in stowed position - REV UNLK warning light remains off - On panel 128VU, close circuit Check that : breaker 2GB - REV UNLK warning light comes on and translating sleeves move from stowed position.

(6)Adjust feedback assemblies as follows : (Ref. Fig. 212, 213 and 221) NOTE : The adjustments and functional inspection/checks listed in the ____ following paragraphs are for all feedback assemblies, whether ___ the assemblies have been modified to include the slotted cover or not. (a)Position translating cowl at neutral position, (deploy the cowl 4 to 4 1/2 in. (101.6 to 114.5 mm) aft of fully stowed position). (b)Disconnect feedback rod end bearing fitting. (c)Push cam forward or away from translating cowl until it bottoms, then retract a minimum of 0.10 in. (2.54 mm) and hold in this position. (d)Stow translating cowl and hold on stops. Push feedback rod aft until it contacts yoke. This positions forward feedback rod stop against the forward face of the feedback yoke. 1 While holding rod in this position, adjust rod end bearing fitting _ until holes align, and connect rod to feedback cam.R NOTE : Feedback rod should be centered in yoke bracket during the ____R deploy/stow operation. If the clearance is inadequate, shim theR yoke with washers, part no. NAS1252-10L, as necessary toR attain clearance (Ref. Fig. 218 ) (e)Release cam and deploy translating cowl. 1 Check for cam free play movement of a minimum of 0.10 in. (2.54 mm) _ 2 Stow cowl and recheck to assure that minimum of 0.10 in. (2.54 mm) _ over travel exists in stowed position. NOTE : If insufficient end play exists, adjust cam to equally divide ____ free play between ends. 3 On left side reverser, stow cam follower must rest on top of cam lobe, _ 0.250 in. (6.35 mm) from edge, within one revolution of rod end bearing (Ref. Fig. 212 ). NOTE : On the latest configuration feedback assemblies, rig marks are ____ provided on the cam and cam follower. If available align the marks on cam with marks on follower for correct adjustment.R (Ref. Fig. 202 ) NOTE : On RH feedback system the cam follower should rest on top ____


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Feedback Cam Adjustment Figure 212


�� G E � � � � CF6 - 50 � ��

Cam Follower Shimming and Lobe Height Figure 213


�� G E � � � � CF6 - 50 � �� of the cam in both the stow and deploy positions. Translate the cowl in both directions stow/deploy to assure the cam follower is equidistant from the cam edges. NOTE : With feedback system properly rigged, indicator switches will ____ be tripped at approximately equal points in cam stroke. (f)Secure feedback arm to cam ; TORQUE bolt to between 55 and 70 lbf.in. (0.62-0.79 m.daN) and lockwire. TORQUE rod end fitting jam nuts to between 40 and 50 lbf.in. (0.45 and 0.566 m.daN). NOTE : After installation of lockwire in the feedback rod arm to the ____ feedback cam, check to make certain that the rod arm stops have not been rotated in anyone extreme direction. Extremely rotated stops could possibly cause an interference with the vespel bullet of the feedback rod guide and subsequently cause shearing of the bullet during reverser operation. (g)On RH feedback only, adjust cam follower set screws, with follower in non-cammed position, so that follower contacts switch plunger within minus 0.000 to plus 0.004 in. (0. to plus 0.101 mm). (h)On LH feedback system, ensure that cam follower bolts are installed as shown (Ref. Fig. 212 ) (7)Feedback indicator switch pretravel check. NOTE : There are two switch configurations (A and B) in use and ____ therefore two methods of checking and adjusting their pretravel. (Ref. Fig. 214 ) (a)In case of configuration A 1 To shim the feedback switches remove from bracket. _ 2 Add five (5) 0.013-0.019 in. (0.3-0.5 mm) thick shims to each switch _ mounting surface so the shims will be between the electrical switch and the feedback mating surfaces. NOTE : Standard AN thin aluminum washers for 10-32 bolts may ____ be used as shims. 3 Reinstall the switches. _ 4 With the switches in the cammed position, measure the gap between _ the cam follower and cam lobe. The gap must be as follows : L/H switches 0.001-0.032 in. (0.03-0.81 mm). R/H switches 0.001-0.016 in. (0.03-0.41 mm). 5 If the gap is less than 0.001 in. (0.03 mm) additional shims are _ required until the correct gap is attained. 6 If gap is greater than 0.016 in. (0.41 mm), cam followers are _ probably discrepant, due to wear, and should be reinspected and/or replaced. 7 If gap meets requirements, no additional shimming is necessary. _ 8 When the required gap is attained, remove five (5) shims ; the _ remaining shims must be installed with the switches to provide proper plunger travel. 9 Reinstall the switch ; TORQUE mounting bolts to between 24 and _ 27 lbf. in. (0.27 and 0.28 m.daN) (b)In case of configuration B 1 Install reworked/new switches to mounting surface of bracket and _ tighten nuts sufficiently to seat each switch in the cammed position. 2 Perform Go.No.Go check between each cam and cam follower at each _ switch. Use the following limits.


�� G E � � � � CF6 - 50 � ��

Fan Reverser Indicator Switch Figure 214

L/H Switch R/H Switches Go 0.002 (0.52 mm) Go 0.002 (0.05 mm) No-Go 0.032 (0.81 mm) No-Go 0.016 (0.41 mm) 3 If Go gauge will not pass between the cam and cam follower when _ follower is raised against the switch stop, add shims as required between switch and switch base. 4 If No-Go gauge will pass between the cam and cam follower, check _ follower for wear. 5 Repair or replace as necessary. _ 6 Reinstall switch, TORQUE bolts to between 24 and 27 lbf. in. (0.27 _ and 0.30 m.daN) 7 Functional check R/L hand feedback bracket assemblies per _ Maintenance Manual. (c)Install switch ; TORQUE bolts to between 24 and 27 lbf. in. (0.27 and 0.3 m.daN). (8)RH feedback bracket assembly functional inspection/check (a)With cam in fully stowed position. 1 Check both ?stow? and ?deploy? switches for continuity between con- _ nector pins.


�� G E � � � � CF6 - 50 � �� NOTE : Continuity shall exist on ?stow? switch only between plus A to ____ B and E to F. Continuity shall exist on ?deploy? switch only between pins B to C and D to E. Any other readings are unac- ceptable. 2 Attempt to lift ?stow? switch cam follower off the cam lobe to fur- _ ther a discernible amount 0.001 in. (0.03 mm) of overtravel. 3 Inspect for gap between ?deploy? switch cam follower and the cam. _ There must be a discernible gap 0.01 in. (0.03 mm). (b)With cam in fully deployed position. 1 Check both ?stow? and ?deploy? switches for continuity between connec- _ tor pins. NOTE : Continuity shall exist on ?deploy? switch only between pins A ____ to B and E to F. Continuity shall exist on ?stow? switch only between pins B to C and D to E. Any other readings are unaccep- table. 2 Attempt to lift ?deploy? switch cam follower off cam lobe to further _ depress plunger. Plunger must depress a discernible amount 0.001 in. (0.03 mm) of overtravel. 3 Inspect gap between ?stow? switch cam follower and cam. There must be _ a discernible gap 0.001 in. (0.03 mm). (c)If all the above continuity checks are not acceptable, replace switch/ switches and re-shim/check as required. (d)If gap and/or overtravel checks are not acceptable, re-shim and recheck as required. (9)Left hand feedback bracket assembly functional inspection/check (a)With cam in fully stowed position. 1 Check both ?stow? and ?deploy? switches for continuity between connec- _ tor pins. NOTE : Continuity shall exist on ?stow? switch only between pins A to ____ B and E to F. Continuity shall exist on ?deploy? switch only between pins B to C and D to E. Any other readings are unaccep- table. 2 Attempt to lift ?stow? switch cam follower off cam lobe to further _ depress the plunger. Plunger must depress a discernible amount 0.001 in. (0.03 mm) of over travel. 3 Inspect for gap between ?deploy? switch cam follower and cam. There _ must be a discernible gap 0.001 in. (0.03 mm). (b)With cam in fully deployed position. 1 Check both ?stow? and ?deploy? switches for continuity between connec- _ tor pins. NOTE : There is continuity on ?deploy? switch only between pins A to ____ B and E to F. There is continuity on ?stow? switch only between pins B to C and D to E. Any other readings are unaccep- ble. 2 Attempt to lift ?deploy? switch cam follower off cam lobe to further _ depress the plunger. Plunger must depress a discernible amount 0.001 in. (0.03 mm) of overtravel. 3 Inspect gap between ?stow? cam follower and the cam. There must be a _ discernible gap 0.001 in. (0.03 mm). nible gap 0.001 in. (0.03 mm). (c)If all the above continuity checks are not acceptable, replace switch/


�� G E � � � � CF6 - 50 � �� switches and re-shim/check as required. (d)If gap and/or overtravel checks are not acceptable, re-shim and recheck as required. (10)Main Drive Cable Integrity Check. (a)At center gearbox, measure the gap between translating cowl leading edge and support assembly. Allowable gap is 0.060-0.150 in. (1.5- 3.8 mm) if larger proceed as follows : 1 Open fan cowl half. Remove cap from center actuator gearbox redundant _ pad. Using a gearbox splined adapter or 5/16 in. (7.9 mm) hex head wrench attempt to manually deploy reverser transcowl half. CAUTION : DO NOT EXCEED 70 LBF.IN. OR TORQUE INTO THE REDUNDANT PAD. _______ If the transcowl will not deploy, the integrity of the main drive cable is assured. At first opportunity, preferably at a reverser maintenance base, the reverser half must be re-rigged including adjustment of the actuator rod unibals to obtain the acceptable 0.060- 0.150 in. (1.5-3.8 mm) gap. 2 If while attempting to manually deploy reverser through redundant pad, _ the translating cowl half does deploy, this indicates a failed main ____ drive cable. The main drive cable must be replaced and the reverser re-rigged or the fan reverser must be appropriately deactivated and locked out. Lockout splined adapters should be used at each reverser half center gearbox and the RH aft deploy switch electrical connector disconnected and secured. Applicable flight compartment placards should be installed.


�� G E � � � � CF6 - 50 � �� 4. Maintenance Plan ________________

A. Fan Reverser Structural Inspection (1)Make certain that retaining covers (1,2 and 3) for pins attaching actuator rod end bearings to transcowl clevises are in place. If not, check for presence for pin (4) and replace cover. (Ref. Fig. 217 ). (2)Check actuator mount casting forward support bracket for cracks. None permitted. Replace mount casting. (3)Check actuator mount castings for cracks in mounting feet. Non permitted. Replace mount casting. (4)Check aft cone for cracks adjacent to cutouts for actuator. Stop drill and add a local doubler. (Ref. Fig. 215 ). (5)Check arrowhead extension (5) for gouges indicating transcowl has rammed a core cowl. No delamination permitted. Replace translating cowl (Ref. Fig. 217 ). (6)Check for cracked translating cowl Tee Hinges. With the translating cowl fully deployed, determine if old or new Tee Hinges are installed by the presence of a name plate on the upper forward corner of the transcowl or inspection of the hinge itself (Ref. Fig. 216 ). On intermediate or new hinges, if any lugs are cracked, replace the translating cowl. (No cracks allowed). (7)Check for missing upper and lower guides and brackets. Replace guide and/ or bracket. (8)Check upper and lower guide for gouges, loose or missing teflon. None permitted. Replace guides. (9)Check upper and lower guide bracket for loose or missing attaching fasteners. None permitted. Retorque bolts/replace rivets. (10)Check the integrity of the bulb seal. Cracked or missing sections of the seal may not exceed 20 percent of the total seal length. Replace the translating cowl if the maximum limit is exceeded. (11)Visually check the integrity of the clevises to which the actuator rod end bearings attach (6). There must be no indications of the clevises pulling away from their attaching surfaces. If there are any indications, replace the transcowl. (Ref. Fig. 217 ). (12)Check forward latch ring with fan reverser fully closed and latched. Ac- tuate latches and inspect upper latch hook to see if it opens and clears U-bolt. Upper hook must open and clear U-bolt. (13)Check deflection limiters and bumper tubes. (Non-bolted design only). No delamination of deflection limiters permitted. No deflection or bending of bumper tubes permitted. (14)Check for missing blocker doors. No more than one door per reverser half is permitted, provided the reverser is deactivated. Remove the affected door link and replace reverser as soon as practicable. Check the associated hardware of blocker doors as follows : (a)Hinge lugs and bearings. (b)Air seal/wear strip for delamination or cracking. (c)Link housing for cracks or separations. (d)Wear in link sleeve bearings.R (15)Check clearance between feedback rod and yoke. Rod should be centeredR (not touching yoke bracket). if rod is touching bracket, shim the yokeR bracket with washers, part no. NAS1252-10L, as necessary to attain proper


�� G E � � � � CF6 - 50 � ��

Fan Reverser Aft Cone Section Figure 215


�� G E � � � � CF6 - 50 � ��

New/Intermediate/Old Hinges Figure 216


�� G E � � � � CF6 - 50 � ��R alignment (Ref. Fig. 218 ) (16)Check to make certain all appropriate areas of the fan reverser halves are in a sealed condition. Repair any discrepant areas as necessary. (17)Check blocker door hinge lug bearings as follows : (a)Deploy - translating cowl 4 to 6 in. (101.6 - 152.4 mm) and check for bearing looseness by attempting to move door radially and axially. Relative motion should be less than 0.010 in. (0.25 mm) total along any line. (18)Check fan reverser hinges and adjacent structure for condition and security. ------------------------------------------------------------------------------- COMPONENT/SERVICE LUBE MATERIAL ------------------------------------------------------------------------------- B. Controls, Drives and System Inspections and Service Requirements (1)Pneumatic drive actuator Engine Oil (a)Top off oil cavity to overflowing. (Ref. 78-31-01 for ?Quick Fill? techni- ques) NOTE : If less than 25 cc (1.52 in³ of ____ oil is added at first 250 cycles check point, then do not recheck until an additional 500 cycles point has been accumulated.

If more than 25 cc (1.52 in³) but less than 50 cc (3.6 in³) is required to fill, then retop at each 250 cycles point until 1500 cycles point is reached. (b)Drain, flush and refill with 110 cc (6.71 in³) of oil. (c)Loosen thrust reverser drive cables and check shaft seals for leakage. NOTE : If leakage is apparent, replace ____ drive actuator. If no leakage is apparent, recheck at 1500 cycles.

**ON A/C 001-107,

(d)Check temperature decals for exposure temperature. NOTE : If abnormal or maximum temperature ____ change is noted check pneumatic drive motor oil level and examine the surrounding areas for any leakage that could have caused the decal color change. NOTE : 275•F normal (135•C) ____ 425•F abnormal (218•C)


�� G E � � � � CF6 - 50 � ��

Attaching Actuator Rod End Bearings Figure 217


�� G E � � � � CF6 - 50 � ��

Right/Left Side Feedback Yoke Alignment Figure 218


�� G E � � � � CF6 - 50 � �� 500•F maximum (260•C) 550•F mandatory replacement (287•C) NOTE : The 4 silver colored dots on the ____ temperature decal will change to black upon being exposed to the temperature shown below each dot. CAUTION : CONTACT WITH OIL WILL ALSO CHAN- _______ GE THE COLOR TO BLACK. CHECK THE DECAL CLOSELY TO ASSURE THAT THE PNEUMATIC DRIVE ACTUATOR HAS NOT BEEN SUBJECTED TO AN OVERTEMPERA- TURE CONDITION.

**ON A/C 108-999,

Superseded by AMP LH78-001 (d)Check temperature decals for exposure temperature. NOTE : If abnormal or maximum temperature change ____ is noted check pneumatic drive motor oil level and examine the surrounding areas for any leakage that could have caused the decal color change. NOTE : 275•F normal (135•C) ____ 425•F abnormal (218•C) 500•F maximum (260•C) 550•F mandatory replacement (287•C) NOTE : The 4 silver colored dots on the ____ temperature decal will change to black upon being exposed to the temperature shown below each dot. CAUTION : CONTACT WITH OIL WILL ALSO CHAN- _______ GE THE COLOR TO BLACK. CHECK THE DECAL CLOSELY TO ASSURE THAT THE PNEUMATIC DRIVE ACTUATOR HAS NOT BEEN SUBJECTED TO AN OVERTEMPERA- TURE CONDITION.

��R �EFFECTIVITY: 001-999, �� 78-31-00 � � � � Page 239 � � JAS Mar 01/07

�� G E � � � � CF6 - 50 � �� After AMP LH78-001 (d)Check temperature decals for exposure temperature. * When the 4 silver colored dots on the temperature decal are changed * to black the pneumatic drive actuator will be continued in service * provided there is : * 1 No oil leak. * _ 2 No metal particles on magnetic plug. * _ 3 No abnormal oil lever. * _ 4 No report of system malfunctioning. * _ However, whenever the pneumatic drive actuator is continued in * service : * 5 The 4 silver colored dots will be replaced. * _ 6 The pneumatic drive actuator will be inspected at every ?A? check. * _ CAUTION : IF DURING INSPECTION AT ?A? CHECK THE 4 DOTS ARE FOUND * _______ COLORED AGAIN TO BLACK, THE PNEUMATIC DRIVE ACTUATOR WILL * MANDATORILY BE REPLACED. *

��R �EFFECTIVITY: 108-999, �� 78-31-00 � � � � Page 240 � � JAS Mar 01/07

�� G E � � � � CF6 - 50 � ��

**ON A/C ALL

(e)Replace missing temperature decal if pneumatic drive actuator has been inspected and accepted as serviceable. NOTE : After replacement of a missing decal, check the new decal at ____ 10-15 cycles for abnormal, maximum or over maximum temperatures. (f)Replace inlet filter screen. (2)Fan reverser ballscrew actuator - Material C02-043 or Lubricate ballnuts with a quantity of grea- C02-015 or se equal to 2 pumps of a grease gun. C02-014 (a)Check Interlock nut for looseness using spanner wrench adapter 29644-1 (b)Check for loose or missing nuts that secure the tube clamp. (c)Check for ballscrew shaft and gearbox shaft nut looseness by attempting to move the ballscrew in an axial direction. NOTE : If any discrepancies are detected in the above checks, replace ____ the parts. (3)Fan reverser actuator gearboxes Material C02-043 or Remove and return to overhaul facility for C02-015 or grease packing. C02-014 (4)Feedback mechanism - Lubricate all moving C02-004 parts. CAUTION : DO NOT LUBRICATE FEEDBACK ROD NOR GUIDED BRACKET VESPEL BULLET. _______ (5)Fan reverser main and interconnecting drive cables (a)Check main drive cable. Replace if defective. (Ref. Fig. 219 ) (b)Pull all cores and inspect for 1 Broken wires - none permitted - replace _ casing and core 2 Separated wires - none permitted replace _ core 3 Deformation (kinks) - none permitted _ replace core 4 Local bowing - none permitted - replace _ core 5 Wear - 1/2 wire diameter max. - replace _ casing and core CAUTION : REMOVE SHAFT CLAMPS CLOSEST TO THE GEARBOXES PRIOR TO DIS- _______ CONNECTING THE SHAFT FROM THE GEARBOXES. (c)Lubricate after wiping exterior of core Material C02-043 or with lint free cloth wetted with solvent. C02-015 or C02-014.

(d)Check to ensure that the main drive cables are seated in guide channels above firewalls. (e)Check to ensure firewall grommets are in place. (Ref. Fig. 219 ).


�� G E � � � � CF6 - 50 � ��

Drive Cable Casing Check Figure 219


�� G E � � � � CF6 - 50 � �� (6)Fan reverser translating cowl gap check - Check the gap between the transcowl and support assembly with the actuators held on their stow stops. Gap must be 0.060 - 0.150 in. (1.52-3.81 mm). Adjust rod-end bearings on ballscrew actuators to obtain the correct gap. (7)Rig fan reverser interconnecting and main flex shafts (Ref. paragraph 3(c)(1)(b)). (Ref. Fig. 220 )


�� G E � � � � CF6 - 50 � ��

LH and RH Shaft Engagement Figure 220


�� G E � � � � CF6 - 50 � ��

(8)Fan reverser running torque - Partially deploy and stow each reverser half by driving through the center gearbox redundant pad. Torque shall not exceed 25 lbf.in. (0.28 m.daN) when the reverser is outside the gap limits. If the torque is above 25 lbf.in. (0.28 m.daN), check for binding and correct as necessary. (9)Feedback assembly. (a)Check RH and LH electrical switch cam followers and LH pneumatic switcher valve cam followers for wear. Minimum heights of follower lobes are as follows : (Ref. Fig. 213 ) step 2. Replace cam followers that do not meet the dimensions. NOTE : If LH switch cam follower does not have a 0.030 inch (0.76 mm) ____ step in the area that makes contact with the indicator switches, add shim(s) (Ref. Fig. 213 ) step 1. 1 RH indicator switch cam follower - 0.736 in. min. (18.69 mm) _ 2 LH indicator switch cam follower - 0.624 in. min. (15.85 mm) _ 3 LH pneumatic switcher valve cam follower - 0.396 in. min. (10.05 mm). _ (b)Cam followers must rotate freely by hand. Accumulative gap in the shoulder bolt/washer/cam follower assembly must not exceed 0.030 in. (0.762 mm). If gap exceeds 0.030 in. (0.762 mm), add (2) wave washers (ASC WO492-007-S, Associated Spring Corp., P.O. Box 231, Gardena, Calif. 90248) and replace washer with locally manufactured spacer as shown in figure (Ref. Fig. 212 ) NOTE : After installation of wave washers and spacer, recheck assembly ____ to assure that followers rotate freely. If assembly is excessi- vely preloaded, prohibiting movement, remove (1) wave washer. (c)With the cam followers in the non-cammed position (transcowl deployed approx. 4 to 6 inches (101.6 - 152.4 mm) measure the gap between the lobe of follower and feedback cam ; insert shim stock to fill the gap and then add an additional shim stock (0.005 in. (0.127 mm) on the LH side and 0.002 in. (0.05 mm) on RH side) to slightly preload the follower. Adjust the locking screw until contact is made with follower. Then lock in place with locknut and remove shim stock. The switches will be preloaded approximately 0.002 in. (0.050 mm). CAUTION : DO NOT ADD EXCESSIVE SHIM STOCK, AS THIS MAY RESULT IN ACTI- _______ VATING THE SWITCHES IN A STATIC CONDITION. NOTE : The locking screws have been replaced by springs on later model ____ switch brackets, therefore adjustments are not required as sta- ted above. (d)Check rigging of the indicator switch cam followers. If necessary, adjust the rod-end bearing on the feedback rod to obtain the required dimensions. With the fan reverser in the fully stowed position, the LH stow cam follower shall be 0.25 ± 0.60 in. (6.35 ± 1.5 mm) on top of the cam lobe. The RH stow cam follower shall be at least 0.03 in. (0.76 mm) on top of the cam lobe. With the fan reverser in the fully deployed position, the LH deploy cam follower shall be


�� G E � � � � CF6 - 50 � �� least 0.25 in. (6.35 mm) on top of the cam lobe. The RH deploy cam follower shall be at least 0.03 in. (0.76 mm) on top of the cam lobe (Ref. Fig. 221 ). (e)Check to insure the cam followers do not contact the cam when in non- cammed position. Also check to insure the switch plunger is not ?Bottomed out? when cam followers are in the cammed position.

Feedback System Rigging Check Figure 221

1 Measure indicator switch plunger height in both positions as shown _ (Ref. Fig. 222 ). NOTE : Plunger travel must exceed 0.060 in. (1.5 mm). ____ 2 If any of the three conditions are not attained add/subtract shims _ or flat washers to/from the switch feedback bracket interface. (10)Flight compartment indicator lights (a)With aircraft power on and the thrust reverser fully stowed, no reverser indicator or warning lights should be on the flight compartment. NOTE : Wiggle and twist both the LH and RH feedback cams to insure that ____ they do not cause flickering of the indicator and warning lights.


�� G E � � � � CF6 - 50 � ��

Plunger Travel of Switches Figure 222


�� G E � � � � CF6 - 50 � �� If an indicator or warning light is on, determine and correct the cause per trouble shooting section. (b)Independently deploy each half of the fan reverser 0.50 in. (12.7 mm) or 8 turns of the center gearbox redundant drive. Fan reverser half must be fully stowed. REV UNLK warning light should be on in flight compartment. If the light is not on, check stow switch continuity at pins B and C. - If continuity does not exist, deploy fan reverser half an additional 1/2 in. (12.7 mm). If continuity exists, check rigging of feedback assembly. - If continuity still does not exist, replace switch. - If continuity exists, check aircraft wiring. (c)Completely deploy LH fan reverser half. RH fan reverser must be fully stowed. CAUTION : MAKE CERTAIN THAT CORE COWL IS CLOSED. _______ (d)Both green REV indicator light and amber REV UNLK warning light should be on in flight compartment. If the indicator and warning lights are not on, check LH deploy switch continuity at pins A and B and pins E and F. NOTE : On engines equipped with a fixed exhaust nozzle, there will ____ not be an amber REV UNLK warning light and no continuity between pins E and F. - If continuity does not exist, replace switch. - If continuity exists, check aircraft wiring. (e)Overpressure valve indicating switch 1 Make certain that thrust reverser is fully stowed. (REV UNLK warning _ light should be off in flight compartment). 2 Make certain that thrust reverser main drive cables are not connected _ and pull core out of drive actuator. 3 Remove speed trimming regulator valve from the deploy pneumatic _ switcher valve line. 4 Pressurize reverser system and select reverse thrust. Make certain _ that overpressure valve is energized and air is being supplied to drive actuator. 5 REV UNLK warning light should be on in flight compartment. If it is _ not on check overpressure valve switch continuity at pins A and B. - If continuity does not exist, replace valve. - If continuity exists, check aircraft wiring. (11)Rig thrust reverser (a)Rig main fan reverser flexshafts 1 With shaft installed in drive actuator and center gearbox held on _ its stow stop, engage shaft in center gearbox. If necessary, rotate shaft one (1) spline tooth in a direction opposite to that of the wrench holding the center gearbox on its stow stop. TORQUE flange bolts to between 24 and 27 lbf. in. (0.27 and 0.30 m.daN). 2 Install shaft clamps and TORQUE bolts to between 24 and 27 lbf. in. _ (0.27 and 0.30 m.daN). (12)Power opening system check (Mechanical) (a)Inspect flanged spherical bearing of power opening actuator for cracks. (Use dye penetrant method). No cracks permitted. (b)Measure peak torque during closing. Max. allowable is 70 lbf.in.


�� G E � � � � CF6 - 50 � �� (0.79 m.daN). When torque exceeds 60 lbf.in. (0.67 m.daN), the actuator should be scheduled for replacement. (c)Remove and return to overhaul facility for grease packing : Royco C.201 (13)Power opening system check (Hydraulic) (a)Inspect actuator mount cup and bracket for cracks. (b)Check all connections and fittings in system for leaks. Correct as necessary. (14)Check for loose bolts around pressure regulator valve actuator housing flange (8 bolts). Use finger pressure for checking. If a loose bolt is present, TORQUE all bolts around the flange to 35 lbf.in. (0.39 m.daN) above running torque. NOTE : If loose bolts are found, check the pneumatic system for leaks ____ and correct all leaks detected. Also check for worn 5th and 6th stage stator vane bushing and washers (Ref. 72-32-00) (15)Check torque on (5) V-band clamps in the reverser air system as follows : NOTE : Lubricate the inner surface of the ?V? clamp with Material ____ No.C02-004 prior to installation. (a)Pneumatic check valve at inlet duct. 70-80 lbf. in. (0.79-0.90 m.daN). (b)Pressure regulator and shutoff valve at pneumatic check valve flange. 70-80 lbf. in. (0.79-0.90 m.daN). (c)Pressure regulator valve at outlet duct. 70-80 lbf. in. (0.79-0.90 m.daN). (d)Overpressure shutoff valve at inlet duct. 70-80 lbf. in. (0.79-0.90 m.daN). (e)Overpressure shutoff valve at pneumatic drive actuator 70-80 lbf. in. (0.79-0.90 m.daN).

R **ON A/C 001-103, 106-999,

5. Electro-Mechanical Brake Holding Torque Check _____________________________________________ NOTE : Do this check after the TRAS lock assembly has been replaced or the ____ flexible drive shafts have been re-rigged.

A. Open, safety and tag the circuit breakers for the appropriate engine and open engine cowls (Ref. 71-13-00, P. Block 301).

B. Manually release the left and right TRAS locks (Ref. Fig. 223 ) (1)Pull the T-handle approximately 0.35 inch (8.9 mm). (2)Remove the manual release lever from the retaining clip, and turn the lever to engage the collar. (3)Release the T-handle.

C. Do the TRAS lock holding torque check on the right thrust reverser half. (1)On the right thrust reverser half, remove the two bolts that attach the pad cover and the gasket (or the splined lock) to the manual drive pad on the center ballscrew gearbox assembly (Ref. Fig. 203 ). (2)Remove the pad cover and the gasket or the splined lock (Ref. Fig. 203 ). (3)Manually release and hold the brake on the pneumatic drive motor. CAUTION : DO NOT DEPLOY THE THRUST REVERSER WITH THE SIDE COWL PANEL _______ OPEN. DAMAGE TO THE THRUST REVERSER AND COWL PANELS CAN OCCUR.


�� G E � � � � CF6 - 50 � �� CAUTION : THRUST REVERSER TRANSLATION IS USUALLY DONE WITH THE REVERSER _______ HALVES CLOSED. IF IT IS NECESSARY TO DEPLOY THE TRANSLATING COWL WITH THE REVERSER HALVES OPEN, MAKE SURE THE REVERSER HALVES ARE NOT OPEN MORE THAN 20 DEGREES. (4)Manually translate the translating cowl of the right thrust reverser half a minimum of 1 inch (25.4 mm) in the deploy direction. NOTE : This procedure uses a splined adapter tool that you insert into ____ the manual drive pad on the center ballscrew gearbox assembly. You can attach a torque wrench to the splined adapter. If necessary, you can make the splined adapter tool for the end of a discarded flexshaft cable (Ref. Fig. 204 ). NOTE : To prevent the incorrect torque reading, make sure you deploy the ____ translating cowl a minimum of 1 inch (25.4 mm). This will remove all torque that can be the result of contact between the translating cowl bumpers and the fixed structure. (5)Manually engage the TRAS lock on the right thrust reverser half (Ref. Fig. 223 ). (a)Pull the T-handle approximately 0.1 inch (2.54 mm). (b)Turn the manual release lever away from the fan cowl. (c)Engage the manual release lever in the retaining clip. (d)Release the T-handle. (6)With the manual drive lockout cover removed, install the locally made splined adapter tool and a dial-type torque wrench into the manual drive pad of the center ballscrew gearbox assembly (Ref. Fig. 203 ). (7)Make sure the pneumatic drive motor brake is applied. (8)Turn the torque wrench in the deploy direction until the torque is 180 lbf.in. (2.03 m.daN). NOTE : Put a mark on the point where you start to apply torque. This ____ will help you know how far you turned the wrench in the next step. (a)The TRAS lock system operates correctly if you reach 180 lbf.in. (2.03 m.daN) of torque before you turn the wrench one-half of a turn. (b)If you do not reach 180 lbf.in. (2.03 m.daN) of torque, make sure you turned the wrench in the deploy direction. If you turn the wrench in the deploy direction and cannot reach 180 lbf.in. (2.03 m.daN) of torque, you must replace the TRAS lock (Ref. 78-31-53, P. Block 401). (c)Record the results of the holding torque check. (d)Turn the wrench slowly in the stow direction sto release the torque. Turn the wrench until you reach 0.0 lbf.in. (0.0 m.daN) of torque. (e)Install the pad cover and the gasket (or the splined lock) on the lower side of the center ballscrew gearbox assembly with the two bolts. (9)Manually release the TRAS lock on the right hand thrust reverser half (Ref. Fig. 223 ). (a)Pull the T-handle approximately 0.35 in. (8.9 mm). (b)Remove the manual release lever from the retaining clip, and turn the lever to engage the collar. (c)Release the T-handle.

D. Do the TRAS lock holding torque check on the left thrust reverser half. (1)On the left thrust reverser half, remove the two bolts that attach the pad cover and the gasket (or the splined lock) to the manual drive pad


�� G E � � � � CF6 - 50 � �� on the center ballscrew gearbox assembly (Ref. Fig. 203 ). (2)Remove the pad cover and the gasket or the splined lock (Ref. Fig. 203 ). (3)Manually release and hold the brake on the pneumatic drive motor. CAUTION : DO NOT DEPLOY THE THRUST REVERSER WITH THE SIDE COWL PANEL _______ OPEN. DAMAGE TO THE THRUST REVERSER AND COWL PANELS CAN OCCUR. CAUTION : THRUST REVERSER TRANSLATION IS USUALLY DONE WITH THE REVERSER _______ HALVES CLOSED. IF IT IS NECESSARY TO DEPLOY THE TRANSLATING COWL WITH THE REVERSER HALVES OPEN MAKE SURE THE REVERSER HALVES ARE NOT OPEN MORE THAN 20 DEGREES. (4)Manually translate the translating cowl of the left thrust reverser half a minimum of 1 inch (25.4 mm) in the deploy direction. NOTE : To prevent the incorrect torque reading, make sure you deploy the ____ translating cowl a minimum of 1 inch (25.4 mm). This will remove all torque that can be the result of contact between the translating cowl bumpers and the fixed structure. (5)Manually engage the TRAS lock on the right thrust reverser half. (a)Pull the T-handle approximately 0.1 inch (2.54 mm). (b)Turn the manual release lever away from the fan cowl. (c)Engage the manual release lever in the retaining clip. (d)Release the T-handle. (6)With the manual drive lockout cover removed, install the locally made splined adapter tool and a dial-type torque wrench into the manual drive pad of the center ballscrew gearbox assembly (Ref. Fig. 203 ). (7)Make sure the pneumatic drive motor brake is applied. (8)Turn the torque wrench in the deploy direction until the torque is 180 lbf.in. (2.03 m.daN). NOTE : Put a mark on the point where you start to apply torque. ____ This will help you know how far you turned the wrench in the next step. (a)The TRAS lock system operates correctly if you reach 180 lbf.in. (2.03 m.daN) of torque before you turn the wrench one-half of a turn. (b)If you do not reach 180 lbf.in. (2.03 m.daN) of torque, make sure you turned the wrench in the deploy direction. If you turn the wrench in the deploy direction and cannot reach 180 lbf.in (2.03 m.daN) of torque, you must replace the TRAS lock (Ref. 78-31-53, P. Block 401). (c)Record the results of the holding torque check. (d)Turn the wrench slowly in the stow direction to release the torque. Turn the wrench until you reach 0.0 lbf.in. (0.0 m.daN) of torque. (e)Install the pad cover and the gasket (or the splined lock) on the lower side of the center ballscrew gearbox assembly with the two bolts. (9)Manually release the TRAS lock on the right thrust reverser half (Ref. Fig. 223 ). (a)Pull the T-handle approximately 0.35 in. (8.9 mm). (b)Remove the manual release lever from the retaining clip, and turn the lever to engage the collar. (c)Release the T-handle.

E. Close-up (1)Manually stow the translating cowls on the left and right thrust reverser half. (2)Manually engage the pneumatic drive motor brake.


�� G E � � � � CF6 - 50 � �� (3)Manually engage the left and right TRAS lock brake (***//ATNZ//***). (a)Pull the T-handle approximately 0.1 in. (2.54 mm). (b)Turn the lever away from the fan cowl. (c)Engage the manual release lever in the retaining clip. (d)Release the T-handle. (4)Close the fan cowl doors (Ref. 71-13-00, P. Block 301). (5)Remove the safety clips and tags and close the circuit breakers that were opened.

F. Do an operational check of the thrust reverser (Ref. 78-30-00, P. Block 501).

R **ON A/C ALL

6. Close-Up ________ - Make certain that working area is clean and clear of tools and miscellaneous items of equipment - Remove access platforms


�� G E � � � � CF6 - 50 � ��

TRAS Lock (Sheet 1/3) Figure 223

�� EFFECTIVITY: 001-103, 106-999, �� 78-31-00 � � � � Page 253 � � JAS Mar 01/07

�� G E � � � � CF6 - 50 � ��



�� G E � � � � CF6 - 50 � �� PNEUMATIC DRIVE ACTUATOR - MAINTENANCE PRACTICES ________________________________________________

WARNING : MAKE CERTAIN THAT CIRCUIT BREAKERS ARE OPEN, SAFETIED AND TAGGED AND _______ THAT AIR PRESSURE IS NOT APPLIED THROUGH GROUND CONNECTIONS. INADVERTENT ENGINE STARTOR THRUST REVERSER OPERATION COULD RESULT IN DEATH OR SERIOUS INJURY TO PERSONNEL.

1. Reasons for the Job ___________________

A. Removal for Replacement

B. Servicing

2. Equipment and Materials _______________________ NOTE : Equivalent substitutes may be used instead of the following items ____ ------------------------------------------------------------------------------- ITEM DESIGNATION ------------------------------------------------------------------------------- A. Material C02-019 Anti-Seize Compounds, Lubricants, Oils (Ref. 20-32-00) B. Material C01-007 Adhesives, Plastics, Sealants (Ref. 20-32-00) C. Material C03-006 Finishes and Protective Coatings (Ref. 20-32-00) D. Material 11-002 Cleaning Agents (Ref. 20-32-00) E. Access Platform 3 m (10 ft.) F. Torque Wrench - 24-300 lbf.in. (0.27-3.39 m.daN) G. 2C6639G01 Puller, Filter Pneumatic Drive Actuator H. Corrosion-Resistant Steel Lockwire Dia. 0.032 in. (0.813 mm) I. Corrosion-Resistant Steel Lockwire Dia. 0.020 in. (0.508 mm) J. Lint-Free Cloth K. Circuit Breaker Safety Clips L. Lever Actuated Oil Squirt Can with Flexible Spout 1/2 Pint (0.24 liters) Capacity M. Temperature Indicator Decal Referenced Procedures - 71-13-00, P. Block 301 Cowl Doors - 78-31-00, P. Block 201 Thrust Reverser System


�� G E � � � � CF6 - 50 � �� 3. Procedure _________

A. Job Set-Up (1)Position access platform. (2)Open, safety and tag circuit breakers for the appropriate engine and open core cowl, fan cowl and thrust reverser doors (Ref. 71-13-00, P. Block 301)

CAUTION : FOR ALL MAINTENANCE PROCEDURE INSIDE COWLS, EXTEND HOLD-OPEN _______ RODS TO HOLD COWLS OPEN. INADVERTENT CLOSURE OF COWLS COULD RESULT IN SERIOUS INJURY TO TO PERSONNEL.

B. Servicing CAUTION : THE INTERMIXING OF DIFFERENT BRANDS OR TYPES OF OIL MUST BE _______ AVOIDED. IN THE EVENT OF INADVERTENT MIXING OF APPROVED OILS, OILS, THE PNEUMATIC DRIVE ACTUATOR SHOULD BE DRAINED, FLUSHED AND REFILLE WITH NORMALLY USED OIL AT EARLIEST OPPORTUNITY. RECORD TYPE OF OILS INTERMIXED TO DETERMINE POSSIBLE EFFECTS ON SEALS ETC. ENSURE THAT OIL CAN IS CLEAN BEFORE FILLING CAN OR SERVICING DRIVE ACTUATOR.

NOTE : Right side fan reverser half must be open and actuator exposed for ____ servicing.

NOTE : Drive actuator oil capacity is approximately 1/4 pint. For ease of ____ filling, servicing oil should be at room temperature.

(1)Service drive actuator by removing fill plug and slowly filling actuator to overflowing using squirt can and oil Material C02-019. Assemble new lubricated 0-ring on fill plug and install ; TORQUE to between 90 and 100 lbf.in. (1.01 and 1.13 m.daN) (7.55 and 8.33lbf.ft), safety with 0.032 in. (0.813 mm) dia. corrosion resistant steel lockwire. (2)Drain and replenish drive actuator oil as follows : (a)Remove drain and fill plugs and drain oil from actuator. Install drain plug and new lubricated 0-ring; TORQUE to between 155 and 175 lbf.in. (13 and 14.58 lbf.ft) (1.75-1.97 m.daN) safety with 0.032 in. (0.813 mm) dia. corrosion resistant steel lockwire. (b)Using squirt can, slowly fill actuator to overflowing with oil Material C02-019. (c)Assemble new lubricated O-ring on fill plug and install plug; TORQUE to between 90 and 100 lbf.in. (7.55 and 8.33 lbf.ft.) (1.01 and 1.13 m.daN), safety with 0.032 in. (0.813 mm) dia. corrosion resistant steel lockwire. NOTE : The figure shows three (3) methods that can greatly reduce ____ the time required to fill the pneumatic drive actuator, during periodic maintenance. (Ref. Fig. 203 ) (3)Drain and flush drive actuator as follows : (a)Remove drain and fill plugs; drain oil from actuator. Install drain plug and O-ring; tighten fingertight plus one-half turn. (b)Using squirt can, slowly fill unit to overflowing with oil Material


�� G E � � � � CF6 - 50 � �� C02-019 (c)Drain flushing oil NOTE : If unit is to be flushed concurrently with engine oil system, ____ install fill plug and drain flushing oil after engine run. (d)Assemble new lubricated O-ring on drain plug and install; TORQUE to between 155 and 175 lbf.in. (13 and 14.58 lbf.ft.) (1.75 and 1.97 m.daN), safety with 0.032 in. (0.81 mm) dia. corrosion resistant steel lockwire. (e)Using squirt can, slowly fill unit to overflowing with oil, Material C02-019 (f)Assemble new lubricated O-ring on fill plug and install ; TORQUE to between 99 and 100 lbf.in.(7.55 and 8.33 lbf.ft) (1.02 and 1.13 m.daN), safety with 0.032 in. (0.81 mm) dia. corrosion resistant steel lockwire.R Pre SB LM 78-3002 (4)Remove and replace the inlet filter. (a)Remove the overpressure and shutoff valve. CAUTION : TO PREVENT DAMAGE TO THE FILTER, MAKE SURE THE SPRING-LOADED _______ FINGERS OF PULLER 2C6639 ARE FULLY RETRACTED INTO THE PROTECTIVE CYLINDER BEFORE YOU INSERT THE PULLER INTO THE INLET DUCT. (b)Use puller 2C6639 to remove the filter from the inlet duct of the pneumatic drive motor. Return the filter to an overhaul facility to be cleaned (Ref. Fig. 202 ). WARNING : USE THERMAL OR INSULATED GLOVES TO PREVENT HAND INJURY WHEN _______ YOU TOUCH DRY ICE OR COLD PARTS. (c)Chill a new or cleaned filter in dry ice for a minimum of 10 minutes. (d)Install the chilled filter into the pneumatic drive motor inlet. (e)Install the overpressure and shutoff valve.R End Pre SB LM 78-3002 Post SB LM 78-3002 (5)Replace the in-line air filter (Ref. Fig. 201 ) (a)Remove the two bolts and the two washers that attach the air filter cap to the filter housing, and remove the air filter cap. (b)Examine the preformed packing on the filter housing for wear or damage, and replace if necessary. (c)Remove the air filter from the filter housing. (d)Remove the preformed packing from the filter. Examine the preformed packing for wear or damage. If necessary, get a new preformed packing. (e)Send the air filter to an overhaul shop to be cleaned. (f)Install the preformed packing on the new or cleaned air filter. (g)Install the air filter in the filter housing. (h)Install the air filter cap on the filter housing with the two bolts and the two washers. End Post SB LM 78-3002 (6)Do a check of the holding torque of the pneumatic drive motor (PDM) brake. NOTE : You must use a locally made splined adapter tool to do the ____ procedure that follows. You can use the end of a discarded cable (flex shaft) to make the tool (Ref. Fig. 204 ). CAUTION : BEFORE YOU OPEN THE THRUST REVERSER HALVES, MAKE SURE THE WING _______


�� G E � � � � CF6 - 50 � ��

In-Line Air Filter (Post SB LM 78-3002)R Figure 201


�� G E � � � � CF6 - 50 � �� LEADING EDGE SLATS ARE FULLY RETRACTED TO PREVENT DAMAGE TO THE THRUST REVERSER AND THE SLATS. CAUTION : DO NOT OPEN THE THRUST REVERSER HALF TO MORE THAN THE _______ 34-DEGREE (FIRST STICK) POSITION, OR DAMAGE TO THE TRANSLATING COWL CAN OCCUR DURING TRANSLATING COWL DEPLOYMENT OR STOW. CAUTION : DURING DEPLOYMENT, MAKE SURE THE TRANSLATING COWLS DO NOT _______ TOUCH THE PYLON OR THE WING STRUCTURE. (a)Open the right thrust reverser half to the first stick hold open rod position (Ref. 71-13-00, P. Block 301). (b)On the right thrust reverser half, remove the two bolts that attach the pad cover and the gasket or the splined lock (P/N 9149M85G01) to the manual input socket on the lower side of the center gearbox on the right reverser half. (c)Remove the pad cover and the gasket or the splined lock (Ref. Fig. 205 ). (d)Install the locally made splined adapter tool into the manual input socket (Ref. Fig. 206 ). NOTE : Make sure the gearbox actuators are not on their stow stops. If ____ the gearbox actuators are on their stow stops, and you do not apply torque in the deploy direction, you will get an incorrect holding torque reading. (e)Make sure the two translating cowls are in the stow rig position. If the translating cowls are not in the stow rig position, manually release the disc brake on the PDM (Ref. Fig. 207 ) and translate the translating cowls through the right center gearbox as necessary to move the translating cowls to the stow rig position. (f)Manually engage the PDM disc brake. (g)Do a check of the PDM disc brake holding torque. 1 With the disc brake engaged on the PDM, attach a dial-type torque _ wrench to the splined adapter tool. CAUTION : DO NOT USE MORE THAN 100 LBF.IN. (1.13 M.DAN) OF TORQUE WHEN _______ YOU DO THE CHECK. EXCESSIVE TORQUE WILL DAMAGE THE FLEX SHAFT. 2 Apply a minimum torque of 50 lbf.in. (0.57 m.daN). The PDM disc brake _ must not slip. NOTE : When you first apply the torque, you may not feel resistance ____ immediately. There can be some initial movement of the torque wrench as the flex shaft twists in its casing. This is normal. When you first feel the resistance, you will continue to feel resistance as you apply the torque, until the brake slips. Make sure you do not use more than 100 lbf.in. (1.13 m.daN) of torque. 3 The brake must reach 50 lbf.in. (0.57 m.daN) of holding torque with _ no slippage of the disc brake. If the brake does not reach 50 lbf.in. (0.57 m.daN) of holding torque, replace the pneumatic drive motor. Refer to paragraphs 3.C. and 3.D. 4 If the brake holds 50 lbf.in. (0.57 m.daN) of torque, increase the _ torque until the brake slips, or until the brake has a maximum of 100 lbf.in. (1.13 m.daN) of holding torque. Do not exceed 100 lbf.in. (1.13 m.daN). If the brake does not slip when it reaches 100 lbf.in. (1.13 m.daN) of torque, record 100 lbf.in. (1.13 m.daN) on the inspection record.


�� G E � � � � CF6 - 50 � �� (h)Put the translating cowls back in stow rig position. 1 Manually release the disc brake on the PDM (Ref. Fig. 207 ). _ 2 Translate the translating cowls through the right center gearbox as _ necessary to move the translating cowls to the stow rig position. (i)Remove the splined adapter tool from the manual input socket of the center gearbox (Ref. Fig. 206 ). (j)Install the pad cover and the gasket or the splined lock (P/N 9149M85G01), with the splined end out, on the manual input socket on the lower side of the center gearbox. Attach the pad cover and the gasket, or the splined lock, with two bolts. TORQUE the bolts to between 33 and 37 lbf.in. (0.37 and 0.42 m.daN) (Ref. Fig. 205 ).

C. Removal (Ref. Fig. 208 ) (1)Make certain that circuit breakers are open, safetied and tagged. NOTE : Cap, plug or cover all tubes and connectors upon removal. ____ (2)Remove pneumatic drive actuator as follows : (a)Disconnect : 1 Flexible shafts (13) at center gearboxes and pneumatic actuator. _ NOTE : Remove clamps adjacent to shaft ends before disconnecting shaft. ____ 2 Pneumatic switcher valve tubes (2) and (3). _ 3 Directional pilot valve tube (1). _ 4 Reference tube at overpressure shut off valve (7). _ 5 Electrical connectors (6) and clamps at overpressure shut off valve _ (10). 6 Control tube (4) at overpressure shut off valve. _ (b)Remove clamps and disconnect pneumatic drive actuator supply duct (8) from pressure regulating shut off valve and overpressure shut off valve and overpressure shut off valve. WARNING : SUPPORT PNEUMATIC DRIVE ACTUATOR AND OVERPRESSURE SHUT OFF _______ VALVE ADEQUATELY WHEN REMOVING. PNEUMATIC DRIVE ACTUATOR AND OVERPRESSURE SHUT OFF VALVE WEIGHS APPROXIMATELY 48 LBS (21.76 KG). (c)Remove bolts and remove pneumatic drive actuator with overpressure shut off valve from pylon. (d)Disconnect brake release tube (5) from pneumatic drive actuator and overpressure shut off valve. (e)Separate overpressure shut off valve (10) from pneumatic drive actuator. (f)Remove fittings from pneumatic switcher tubes (2) and (3) and directional pilot valve ports; discard O-ring.

D. Installation (Ref. Fig. 208 ) (1)Install pneumatic drive actuator as follows : (a)Check for correct condition of tube end-fittings and electrical connectors. (b)Assemble new lubricated O-rings on unions, and install in pneumatic switcher valve and directional pilot valve ports. TORQUE unions to between 180 and 200 lbf.in. (2.03 and 2.26m.daN), (15 and 16.66 lbf.ft). Safety with 0.032 in (0.813 mm) dia. corrosion resistant steel lockwire (c)Connect overpressure shut off valve to air motor with a spacer between


�� G E � � � � CF6 - 50 � ��

Inlet Filter Screen Removal Figure 202


�� G E � � � � CF6 - 50 � ��

Quick Fill Methods for Pneumatic Drive Actuator Figure 203


�� G E � � � � CF6 - 50 � ��

Splined Adapter Tool Figure 204


�� G E � � � � CF6 - 50 � ��

Splined Lock (P/N 9149M85G01) or Pad Cover and Gasket on the Center GearboxR Figure 205 �� EFFECTIVITY: ALL �� 78-31-01 � � � � Page 210 � � JAS Mar 01/99

�� G E � � � � CF6 - 50 � ��

Use of Splined Adapter Tool Figure 206


�� G E � � � � CF6 - 50 � ��

Manual Release of the PDM Disc BrakeR Figure 207


�� G E � � � � CF6 - 50 � ��

Pneumatic Drive Actuator Figure 208


�� G E � � � � CF6 - 50 � �� the mating flanges. Secure with V clamp and TORQUE lock nut to between 70 and 80 lbf. in. (0.79 and 0.90 m.daN). Safety with 0.032 in (0.813 mm) dia. corrosion resistant steel lockwire. NOTE : Dimples on spacer position into rabbet of pressure shut off ____ valve. NOTE : Tap V clamp and retorque, continue until no change is ____ noted in torque value. (d)Connect brake release tube (5) to pneumatic actuator and overpressure shut off valve; TORQUE coupling nuts to between 270 and 300 lbf.in. (3.05 and 3.39 m.daN) (22.5 and 25 lbf.ft.). Safety with 0.032 in. (0.813 mm) dia. corrosion resistant steel lockwire. WARNING : SUPPORT PNEUMATIC DRIVE ACTUATOR AND OVERPRESSURE SHUT OFF _______ VALVE ADEQUATELY WHEN INSTALLING. PNEUMATIC DRIVE ACTUATOR AND OVERPRESSURE SHUT OFF VALVE WEIGHS APPROXIMATELY 48 LBS (21.76 KG). (e)Install pneumatic drive actuator and side brackets on pylon mounting surface and secure with bolts and washers. TORQUE to between 55 and 70 lbf.in. (0.62 and 0.79 m.daN). (f)Secure supply air duct at pressure regulator shut off valve with clamps; TORQUE lock nut to between 70 and 80 lbf.in. (0.79 and 0.90m.daN). NOTE : Tap V clamp and retorque, continue until no change is noted ____ in torque value. NOTE : Position clamp so interface between clamp bolt and duct sidewall ____ does not exist when reverser is closed. (g)Connect directional pilot valve tube (1); TORQUE to between 270 and 300 lbf.in. (3.05 and 3.39 m.daN) (22.5 and 25 lbf.ft.) (h)Connect pneumatic switcher tubes (2) (3); TORQUE to between 270 and 300 lbf.in. (3.05 and 3.39 m.daN) (22.5 and 25 lbf.ft.) Safety with 0.032 in. (0.813 mm) dia. corrosion resistant steel lockwire. (i)Connect control tube (4) at overpressure shut off valve; TORQUE to between 180 and 200 lbf.in. (2.03 and 2.26 m.daN) (15 and 16.66 lbf.ft.) (j)Connect reference tube (7) at overpressure shut off valve; TORQUE to between 270 and 300 lbf.in. (22.5 and 25 lbf.ft.) (3.05 and 3.39 m.daN), safety with 0.032 in (0.813 mm) dia. corrosion resistant steel lockwire. (k)Connect electrical connector (6) at overpressure shut off valve; tighten fingertight. Clamp lower lead at lower, overpressure shut off valve bracket ; TORQUE clamp bolt to between 24 and 27 lbf.in. (0.27- 0.30 m.daN). CAUTION : ELECTRICAL CONNECTOR MUST BE TIGHTENED BY HAND ONLY. USE OF _______ TOOL COULD RESULT IN DAMAGE TO CONNECTOR IN DAMAGE TO CONNECTOR OR WIRING. (l)Connect flexible shafts (13), TORQUE bolts and nuts to between 24 and 27 lbf.in. (0.27 and 0.30 m.daN). Safety with 0.032 in. (0.813 mm) dia. corrosion resistant steel lockwire. (m)Install shafts clamps; TORQUE clamp bolts to between 24 and 27 lbf.in. (0.27 and 0.30 m.daN). NOTE : Check drive cable guide to assure the proprer guide has been ____ installed for application being assembled (Ref. Fig. 210 )


�� G E � � � � CF6 - 50 � �� NOTE : For proper routing of main drive cable (Ref. Fig. 209 ) ____ (n)Rig flexible shafts as directed in 78-31-00. (o)Service drive actuator as required (Ref. paragraph, 2.A.


�� G E � � � � CF6 - 50 � ��

Main Drive Cable Routing Figure 209


�� G E � � � � CF6 - 50 � ��

Drive Cable Guide Installation Figure 210

E. Inspection/Check Visually inspect pneumatic drive actuator as follows : -------------------------------------------------------------------------- INSPECTION/CHECK MAXIMUM SERVICEABLE LIMITS REMARKS -------------------------------------------------------------------------- (1) Thread damage 30 percent damage on one entrance Repair per thread or 10 percent damage on paragraph F each of two entrance threads

(2) Nicks, dents and Any amount 0.010 in. (0.25 mm) deep Removal high scratches after removal of high metal metal

(3) Bolt holes for None allowed Replace pneu- cracks matic drive actuator

(4) Loose or bent name Not serviceable Straighten plate to original


�� G E � � � � CF6 - 50 � �� -------------------------------------------------------------------------- INSPECTION/CHECK MAXIMUM SERVICEABLE LIMITS REMARKS -------------------------------------------------------------------------- contour and secure with screws

(5) Oil leakage at Not serviceable Replace pneu- flexible shaft matic drive connections actuator

(6) Damaged or missing Not serviceable Inspect pneu- temperature decal mactic drive actuator for over temperature indications

(7) Over temperature Replace pneu- indications matic drive actuator if any indications are (a) Discoloration evident (Straw-color)

(b) Deformation or warpage

(c) Case cracking and/or oil leakage

(8) Air supply duct for :

(a) Evidence of None permitted Replace air leakage duct

(b) Looseness at None permitted Replace air joint duct

(9) Brake torque Minimum 50 lbf.in. If below (0.57 m.daN) minimum torque, replace pneumatic drive motor NOTE : If no overtemperature conditions are found, replace the decal and ____ permanently attach a tag indicating the date of decal replacement. See paragraph F.(4) of approved repairs below.

F. Approved Repairs (Ref. Fig. 211 )


�� G E � � � � CF6 - 50 � ��

Pneumatic Drive Actuator Shuttle Valve Figure 211

(1)Thread damage within serviceable limits may be repaired by blending with a fine file. Protect bare areas with Alodine (C03-006). (2)Cleaning of pneumatic drive actuator shuttle valve. Remove and clean sticking shuttle valve as follows : (a)Remove screws; release retainer plate (14), compression spring (15) and shuttle valve (16). (b)Wipe valve and pneumatic drive actuator port with clean, lint-free cloth. (c)Install shuttle valve (16) compression spring (15) and retainer plate (14) in pneumatic drive actuator. Install screws; TORQUE to between 24 and 27 lbf.in (0.27 and 0.30 m.daN). (3)Replace missing temperature decal as follows : (a)Clean pneumatic drive actuator casing with solvent (C04-005) or equivalent. (b)Remove backing strip from new decal and place on pneumatic drive actuator as shown in (Ref. Fig. 212 ) (c)Apply a 0.125 in. (3.2 mm) bead of RTV106 (C-007) around edges of decal to seal from oil intrusion. (d)Install a permanent tag indicating decal replacement and date.


�� G E � � � � CF6 - 50 � �� NOTE : Decals (P/N 3230604-1) are available from Airesearch. ____

Pneumatic Drive Actuator - Temperature Indicator Decal Location Figure 212

G. Close-Up (1)Make certain that working area is clean and clear of tools and miscellaneous items of equipment. (2)Remove access platform. (3)Remove safety clips and tags, and close circuit breakers for the appropriate engine and close fan cowl, core cowl and thrust reverser doors (Ref. 71-13-00, P. Block 301).


�� G E � � � � CF6 - 50 � �� CENTER GEARBOX AND BALLSCREW ACTUATOR - MAINTENANCE PRACTICES _____________________________________________________________

WARNING : MAKE CERTAIN THAT CIRCUIT BREAKERS ARE OPEN, SAFETIED AND TAGGED, AND _______ THAT AIR PRESSURE IS NOT APPLIED THROUGH GROUND CONNECTIONS. INADVER- TENT ENGINE START OR THRUST REVERSER OPERATION COULD RESULT IN DEATH OR SERIOUS INJURY TO PERSONNEL.


A. Servicing

B. Removal/Installation

C. Inspection/Check

D. Repair

NOTE : Equivalent substitutes may be used instead of the following items. ____

2. Equipment and Materials _______________________ ------------------------------------------------------------------------------- ITEM DESIGNATION ------------------------------------------------------------------------------- A. ?Piggy-Back? or ?Twin-Serts? B. Wrench 5/6 in. Hex End C. Material C01-087 Anti-Seize Compounds, Lubricants, Oils (Ref. 20-32-00) D. Torque Wrench 24-27 lbf.in. (0.27-0.30 m.daN) E. 2C6367G01 Tool, Actuator Pin Removal and Installation F. Corrosion-Resistant Steel Lockwire, Dia. 0.032 in. (0.813 mm) G. Corrosion-Resistant Steel Lockwire, Dia. 0.020 in. (0.508 mm) H. Circuit Breaker Safety Clips J. Lint-Free Cloth K. Access Platform 3 m (10 ft.) Referenced Procedures - 71-13-00, P. Block 301 Cowl Doors - 78-31-00, P. Block 201 Thrust Reverser System Control - 78-31-04, P. Block 201 Fan Reverser Ball-Screw Actuators

R **ON A/C 001-103, 106-999,

- 78-31-53, P. Block 401 Thrust Reverser Electro-Mechanical Brake (TRAS Lock)


�� G E � � � � CF6 - 50 � ��

R **ON A/C ALL

3. Procedure (Ref. Fig. 201 ) _________

A. Job Set-Up (1)Position access platform. (2)Open, safety and tag circuit breakers for the appropriate engine and open fan cowl doors (Ref. 71-13-00, P. Block 301) CAUTION : FOR ALL MAINTENANCE PROCEDURES INSIDE COWLS, EXTEND HOLD OPEN _______ RODS TO HOLD COWLS OPEN. INADVERTENT CLOSURE OF COWLS COULD RESULT IN SERIOUS INJURY TO PERSONNEL.

B. Servicing (1)Lubricate gearbox by packing with grease C02-014, C02-015 or C02-043.

C. Removal (1)Make certain that circuit breakers are open, safetied and tagged NOTE : Center gearbox and ball-screw actuator must be removed and instal- ____ led as an assembly. (2)Remove the center gearbox and ball-screw actuator as follows : (a)Release pneumatic drive actuator brake. (b)Not applicable.

R **ON A/C 001-103, 106-999,

(b)Remove the TRAS lock assembly (Ref. 78-31-53, P. Block 401).

R **ON A/C ALL

(c)Remove shaft flange mounting bolts. (d)Remove shaft clamps adjacent to gearbox. (e)Slightly bend shafts (8), (1), (2) and remove from gearbox drive sockets. (f)Remove translating cowl retention pin and cover plate (4) from the translating cowl, and pull the pin from actuator rod-end bearing. Use tool, 2C6367G01 with adapter or any 10 - 32 threaded puller. (g)Remove bolts from actuator mounting pin clips. (h)Remove retaining clips (5) and mounting pins (7). (j)Remove bolts (6) and nuts ; remove assembly. (k)Record distance from centerline of gearbox gimbal mounting hole to centerline of ball-screw rod-end bearing. (l)Remove ball-screw actuator from gearbox in accordance with 78-31-04, P. Block 201).

D. Preparation of Replacement Component (1)Clean parts retained from removed ball-screw actuator. Check for correct condition.

E. Installation


�� G E � � � � CF6 - 50 � �� (1)Install ball-screw actuator in gearbox as directed in 78-31-04. (2)Install center gearbox and ball-screw actuator as follows : (a)Adjust ball-screw actuator to same length as the removed actuator by rotating rod-end bearing ; TORQUE the nut to between 180 and 220 lbf.in. (2.03 and 2.49 m.daN). Safety with 0.032 in. dia. (0.813 mm) corrosion resistant steel lockwire. CAUTION : AFTER ROD-END BEARING ADJUSTMENT, A 0.055 IN. (1.40 MM) DIA. _______ PIN MUST NOT PASS THROUGH WITNESS HOLE.

(b)Position rod-end bearing through protective pan at translating cowl clevis. Install translating cowl retention pin and cover plate (4) ; tighten plate screws. Use tool, 2C6367, with adapter to insert pin.

NOTE : Insert translating cowl retention pin with threads toward cover ____ plate. (c)Align actuator with stationary clevis and insert mounting pins (7).

(d)Install retaining clips (5) at mounting pins and secure with washers and bolts. Position washers between clip and actuator mounting bracket ; TORQUE to between 24 and 27 lbf.in. (0.27 and 0.30 m.daN). (e)Not applicable.

R **ON A/C 001-103, 106-999,

(e)Install the TRAS lock assembly (Ref. 78-31-53, P. Block 401).

R **ON A/C ALL

(f)With upper, lower and center gearboxes held on their stow stop using 30-60 lbf.in. (0.34-0.67 m.daN) torque, rotate upper and lower gearbox shaft ends up to 90• in stow direction to align with center gearbox square sockets. Insert shafts ; TORQUE flange bolts to 24 and 27 lbf. in. (0.27 and 0.30 m.daN). Safety with 0.032 in. (0.813 mm) dia. corrosion resistant steel lockwire. CAUTION : DO NOT ROTATE SHAFT ENDS MORE THAN 90• TO ALIGN WITH CENTER _______ GEARBOX SOCKETS. NOTE : To hold gearboxes at stow stops, use locally manufactured spli- ____ ned adapter at center gearbox socket and adapter 2C6105P01 at upper and lower gearboxes sockets opposite shafts. (g)Rig drive shafts as directed in 78-31-00, P. Block 201). (h)Service actuator as required (use grease C02-016).

F. Inspection/Check Visually inspect center gearbox as follows : -------------------------------------------------------------------------------- INSPECT MAXIMUM SERVICEABLE LIMITS REMARKS -------------------------------------------------------------------------------- (1)Drive sockets 0.005 in. max. (0.12 mm) Replace for end play allowable gearbox (2)Flexible shaft Any amount that can be blend Replace mating flanges repaired gearbox for nicks,


�� G E � � � � CF6 - 50 � �� -------------------------------------------------------------------------------- INSPECT MAXIMUM SERVICEABLE LIMITS REMARKS -------------------------------------------------------------------------------- dents or scratches (3)Bolt holes for None allowed Replace cracks gearbox (4)Mounting gim- None allowed Replace bals for wear gearbox (5)Gimbal bushing for wear (a)Upper Any amount, provided 75 per- Replace bushing cent of bushing length does gearbox not exceed 0.3760 in. (9.55 mm) diameter and surface finish of 63 microinches rms. (b)Lower Any amount, provided 75 per- Replace bushing cent of bushing length does gearbox not exceed 0.4380 in. (11.13 mm) diameter and surface finish of 63 microinches rms. (6)Housing for Any number not exceeding 10 Replace nicks, dents percent of housing thickness gearbox or scratches after removal of high metal

G. Adjacent Area Inspection (1)Perform a visual inspection on the exposed areas of all removed components. Also visually inspect the exposed area of the fan reverser. Visual inspection to be only for overall part condition.

H. Approved Repairs (1)Repair damaged inserts as follows : (a)Remove damaged insert. (b)Install new insert coated with primer (C01-087). (c)Remove insert tang when insert is 1/4 to 1/2 turn below countersink. (d)Allow primer to cure at room temperature for 24 hours before using insert. (2)Replace damaged inserts using ?Piggy-back? or ?Twin-serts? as follows : NOTE : ?Piggy-back? or ?Twin-serts? restore damaged or enlarged holes ____ to the original thread size through the utilization of two inserts. The outer insert is free-running and the inner insert may either be free-running or the locking type. (a)With the damaged insert removed, redrill and thread tap the hole for new insert. WARNING : CLEANING SOLVENTS ARE HIGHLY FLAMMABLE. USE PROPER PRECAU- _______ TIONS. AVOID PROLONGED INHALATION OF FUMES. (b)Clean the hole and insert with solvent (C04-001) or (C04-003), then air dry. (c)Apply a thin, even coat of primer (C01-087) to both the hole and


�� G E � � � � CF6 - 50 � ��

Center Gearbox Figure 201

�� EFFECTIVITY: ALL �� 78-31-02 � � � �R Page 205 � � JAS Apr 30/81

�� G E � � � � CF6 - 50 � �� insert. (d)Install the insert while primer is wet, using the appropriate tool, seating from three forths to one and one half turns below the countersink. (e)Remove all excess primer. (f)Touch up all scratches and adjacent areas around the insert. (g)Allow primer to cure at room temperature for 24 hours or one hour at 180-275•F (82-135•C).

J. Close-Up (1)Make certain that working area is clean and clear of tools and miscellaneous items of equipment. (2)Close fan cowls 435AL (445AL), 436AR (446AR). (Ref. 71-13-00, P. Block 301). (3)Remove access platform. (4)Remove safety clips and tags and close circuit breakers for the appropriate engine (Ref. 71-13-00, P. Block 301).


�� G E � � � � CF6 - 50 � �� UPPER AND LOWER GEARBOXES AND BALLSCREW ACTUATORS _________________________________________________ MAINTENANCE PRACTICES _____________________

WARNING : MAKE CERTAIN THAT CIRCUIT BREAKERS ARE OPEN, SAFETIED AND TAGGED, AND _______ THAT AIR PRESSURE IS NOT APPLIED THROUGH GROUND CONNECTIONS. INAD- VERTENT ENGINE START OR THRUST REVERSER OPERATION COULD RESULT IN DEATH OR SERIOUS INJURY TO PERSONNEL.


A. Servicing


C. Inspection/Check

D. Repair

2. Equipment and Materials _______________________

NOTE : Equivalent substitutes may be used instead of the following items. ____ ------------------------------------------------------------------------------- ITEM DESIGNATION ------------------------------------------------------------------------------- A. Material C01-087 Adhesives, Plastics, Sealants (Ref. 20-32-00)R B. Material C02-014 Anti-Seize Compounds, Lubricants, OilsR (Ref. 20-32-00)R C. Material C02-015 Anti-Seize Compounds, Lubricants, OilsR (Ref. 20-32-00)R D. Material C02-016 Anti-Seize Compounds, Lubricants, OilsR (Ref. 20-32-00)R E. Material C02-043 Anti-Seize Compounds, Lubricants, OilsR (Ref. 20-32-00)R F. 2C6105 Adapter, Drive - Turbine Reverser GearboxR G. 2C6367 Tool, Install/Remove - Fan Reverser ActuatorR H. Access Platform 3 m (10 ft.)R I. Corrosion-Resistant Steel Lockwire, Dia. 0.032 in. (0.813 mm)R J. Corrosion-Resistant Steel Lockwire, Dia. 0.020 in. (0.508 mm)R K. Circuit Breaker Safety ClipsR L. Lint-Free ClothR M. Torque Wrench 24-300 lbf.in. (0.27-3.39 m.daN) Referenced Procedures - 71-13-00, P. Block 301 Cowl Doors - 78-31-00, P. Block 201 Thrust Reverser System Control - 78-31-04, P. Block 201 Fan Reverser Ball-Screw Actuator


�� G E � � � � CF6 - 50 � �� 3. Procedure (Ref. Fig. 201 ) _________

A. Job Set-Up (1)Position access platform. (2)Open, safety and tag the following circuit breakers for the appropriate engine and open fan cowl doors (Ref. 71-13-00, P. Block 301). CAUTION : FOR ALL MAINTENANCE PROCEDURES INSIDE COWLS, EXTEND HOLD-OPEN _______ RODS TO HOLD COWLS OPEN. INADVERTENT CLOSURE OF COWLS COULD RESULT IN SERIOUS INJURY TO PERSONNEL.

B. Servicing (1)Lubricate upper and lower gearboxes by packing with grease C02-014,R C02-015, C02-016 or C02-043 (Ref. 20-32-00).


�� G E � � � � CF6 - 50 � �� C. Removal NOTE : Upper gearbox or lower gearbox must be removed with its actuator as ____ an assembly. (1)Make certain that circuit breakers are open, safetied and tagged. (2)Remove upper or lower gearbox and ball-screw actuator as follows. (a)Release the pneumatic drive actuator brake. (b)Remove shaft flange mounting bolts. (c)Remove shaft clamp nearest gearbox. (d)Bend flexible shaft (1) slightly and remove from gearbox drive socket. (e)Release assembly. 1 Remove translating cowl retention pin and cover _ plate (3) from the translating cowl, and pull the pin from actuator rod-end bearing. Use tool, 2C6367G01 with adapter or any 10-32 threaded puller. 2 Remove bolts from actuator retaining clips _ (4). 3 Remove retaining clips (4) and mounting pins _ (6). 4 Remove bolts (5) and nuts ; remove actuator _ assembly. (f)Record distance from centerline of gearbox gimbal mounting hole to centerline of ball-screw rod-end bearing. (g)Remove ball-screw actuator from gearbox as directed in 78-31-04, P. Block 201.

D. Installation (1)Install upper or lower gearbox and ball-screw actuator as follows. (a)Install ball-screw actuator (2) in gearbox (7) per 78-31-04, P. Block 201. (b)Adjust ball-screw actuator to same length as the removed actuator by adjusting rod-end bearing. Then, TORQUE nut to between 180 and 220 lbf.in. (2.03 and 2.49 m.daN). Safety with 0.032 in. Dia. (0.813 mm) corrosion resistant steel lockwire. CAUTION : AFTER ROD-END BEARING ADJUSTMENT A 0.055 IN. (1.40 MM) DIA. _______ PIN MUST NOT PASS THROUGH WITNESS HOLE.

(c)Position rod-end bearing through protective pan and at translating cowl clevis. Install translating cowl retention pin (3) and cover plate ; tighten plate screws. Use tool 2C6367G01, with adapter to install pin. NOTE : Install pin with puller threads toward cover plate. ____ (d)Align actuator with stationary clevis and insert mounting pins (6). CAUTION : THE GEARBOX NAMEPLATE MUST FACE OUTWARD TO ASSURE PROPER _______ INSTALLATION (e)Install retaining clips (4) at mounting pins (6) and secure with washers and bolts ; (position washers between clip and actuatorR mounting bracket) TORQUE to between 33 and 37 lbf.in. (0.37 andR 0.42 m.daN). (f)Insert square drive adapter, 2C6105P01, and rotate gearbox to stow stop ; slowly release applied torque. (g)Rotate shaft end up to 90 degrees in deploy direction to align shaft


�� G E � � � � CF6 - 50 � �� end with gearbox socket, and insert shaft. (h)Rig shafts per 78-31-00, P. Block 201. (j)Install shaft clamp ; TORQUE clamp bolt to between 24 and 27 lbf.in. (0.27 and 0.30 m.daN). Safety with 0.032 in. (0.813 mm) dia. corrosion- resistant steel lockwire. CAUTION : DO NOT ROTATE SHAFT END MORE THAN 90• TO ALIGN WITH GEARBOX _______ SOCKET. (4)Lubricate gearbox as required (use grease C02-015, C02-014 or C02-043) (Ref. 20-32-00).


�� G E � � � � CF6 - 50 � ��

Upper and Lower Gearboxes and Ballscrew Actuators Figure 201


�� G E � � � � CF6 - 50 � �� E. Inspection/Check Visually inspect gearboxes as follows --------------------------------------------------------------------------- INSPECT MAXIMUM SERVICEABLE LIMITS REMARKS --------------------------------------------------------------------------- (1)Drive socket for end 0.005 in. max. (0.127 mm) Replace gearbox (2)Mounting gimbals for None allowed Replace gearbox wear (3)Flexible shaft mating Any amount that can be blend Replace gearbox flanges for nicks, or repaired scratches (4)Bolt holes for cracks None allowed Replace gearbox (5)Housing for nicks, Any number not exceeding 10 Replace gearbox dents or scratches percent of housing thickness after removal of high metal (6)Gimbal bushings for wear : (a)Upper bushing Any amount, provided 75 percent Replace gearbox bushing length does not exceed 0.3760 in. (9.55 mm) diameter and surface finish of 63 microinches rms. (b)Lower bushing Any amount, provided 75 percent Replace gearbox bushing length does not exceed 0.4380 in. (11.13 mm) diameter and surface finish of 63 microinches rms.

F. Adjacent Area Inspection (1)Visually inspect the exposed areas of all removed components. Also visually inspect the exposed area of the fan reverser. Visual inspection to be only for overall part condition.

G. Approved Repairs (1)Repair damaged insert as follows (a)Remove damaged insert (b)Install new insert coated with primer (C01-087) (c)Remove insert tang when insert is 1/4 to 1/2 turn below countersink. (d)Allow primer to cure at room temperature for 24 hours before using insert.

H. Close-Up (1)Make certain that working area is clean and clear of tools and miscellaneous items of equipment. (2)Remove access platform. (3)Remove, safety clips and tags and close circuit breakers for the appropriate engine and close fan cowls (Ref. 71-13-00, P. Block 301).


�� G E � � � � CF6 - 50 � �� FAN REVERSER BALL-SCREW ACTUATORS - MAINTENANCE PRACTICES _________________________________________________________

NOTE : As gearboxes and ball-screw actuators must be removed as an assembly, ____ it is therefore assumed that the removal has been carried out per 78-31-02 or 78-31-03.

1. Equipment and Materials _______________________ NOTE : Equivalent materials may be used instead of the following items : ____ ------------------------------------------------------------------------------- ITEM DESIGNATION ------------------------------------------------------------------------------- A. Material C02-014 Anti-Seize Compounds, Lubricants, Oils B. Material C02-015 Anti-Seize Compounds, Lubricants, Oils C. Material C02-016 Anti-Seize Compounds, Lubricants, Oils D. Material C02-043 Anti-Seize Compounds, Lubricants, Oils E. Material C05-003 Marker (Ref. 20-32-00) F. Torque Wrench - 150-210 lbf.in. (1.70-2.37 m.daN)


A. Servicing (1)Fittings are provided for lubrication purposes. Lubricate ball-screw actuators with material C02-014, C02-015, C02-016 or C02-043. NOTE : When gearboxes and ball-screw actuators are installed on fan cowl, ____ access to lubricator on actuator ball nut is gained by partially deploying fan reverser.

B. Removal NOTE : Gearboxes and ball-screw actuators must be removed and installed ____ as an assembly. (1)Remove gearbox and ball-screw actuator as directed in 78-31-02 or 78-31-03 (2)Remove ball-screw actuator from gearbox as follows : CAUTION : BEFORE MOVING STOP, MARK RADIAL AND AXIAL LOCATION OF STOP WITH _______ RESPECT TO BALL-SCREW. (a)Remove set screw ; carefully slide actuator stop toward rodend. (b)Remove nut from actuator ; release actuator.

C. Inspection/Check Visually inspect fan reverser ball-screw actuators as follows : ---------------------------------------------------------------------------- INSPECTION/CHECK MAXIMUM SERVICEABLE LIMITS REMARKS ---------------------------------------------------------------------------- (1)Rod end bearings for : (a)Wear 0.010 in. (0.25 mm) Replace rod end bearing end play max. wear limit is exceeded or is not free to rotate (b)Nicks, scratches Any amount of minor Minor damage may be po- scoring or cross damage provided unibal lished with abrasive threading rotates freely cloth ; no cross threading allowed, replace rod


�� G E � � � � CF6 - 50 � �� ---------------------------------------------------------------------------- INSPECTION/CHECK MAXIMUM SERVICEABLE LIMITS REMARKS ---------------------------------------------------------------------------- end bearing

(2)Ballscrews (a)Grooves in ballscrews None allowed Replace ballscrews for evidence of brin- actuator neling or pitting

(3)Actuator tube surfaces for : (a)Nicks, dents or Any amount of minor 0.030 in. (0.76 mm) max. scratches damage depth must not cause er- ratic actuator operation (b)Cracks None allowed Replace actuator (c)Loose castle nut Not serviceable Replace actuator

D. Testing of Ballscrew and Gearbox Assemblies (1)Test ballscrew and gearbox assemblies as follows : (a)Mount the trunnion of the gearbox onto a stationary mounting. (b)Mount the rod end bearing of the ballscrew onto an axially movable support. (c)Using a dial indicator, measure the run out of the ball nut at (3) locations (each end ± 2 in. (50.8 mm) and center) while translating the ball nut through the gearbox flexshaft output port. NOTE : Take the required readings at each location after 1 in. ____ (25.4 mm) of travel, or approximately 20 revolutions of the gearbox. (d)Runout should not exceed 0.020 in. (0.51 mm) at any one of the (3) locations checked. If limit is exceeded, return ballscrew to overhaul.

E. Adjacent Area Inspection (1)Visually inspect exposed areas of all removed components. Also visually, inspect exposed areas of fan reverser. Visual inspection to be only for overall part condition.

F. InstallationR CAUTION : THIS PROCEDURE IS FOR ASSEMBLY OF BALLSCREW TO GEARBOX _______R FOR THE PRE CF6-50 S/B 78-224 TWO-PIECE ANGLE GEARBOXR CONFIGURATION ONLY. (1)Install ball-screw actuator in gearbox : (a)Rotate ball nut to expose approximately 8 in. (203 mm) of ball-screw grooves between ball-screw actuator stop and ball nut and extension tube assembly (rod end) (b)Using Material C05-003, mark radial and axial location of ball-screw actuator stop with respect to ball-screw on the ball-screw grooves and on the body of the stop. NOTE : Ball-screw stroke length is preset to 22.14 ±.010 in. ____ (562.4 ±.0254 mm.) (88.56 revolutions ±6.0 degrees.)


�� G E � � � � CF6 - 50 � ��

Assembly of Ball-screw Actuator in GearboxR Figure 201


�� G E � � � � CF6 - 50 � �� (c)Remove actuator stop set screw and carefully slide stop toward rod end bearing. This will provide wrenching clearance. (d)Restrain the gearbox at the input so that torque applied to the gearbox locknut can be counteracted without causing gearbox movement. (e)Apply Material C02-015 to ball-screw actuator internal spline and external threaded splines and to the actuator stop external spline. (f)Slide the ball-screw onto the splined output shaft of the gearbox and thread gearbox locknut on to ball-screw actuator until locknut bottoms. Use wrench Item F and prevent the gearbox input shaft from rotating (or vice versa). CAUTION : ENSURE THAT ACTUATOR IS COMPLETELY BOTTOMED IN GEARBOX. _______ (g)Tighten gearbox locknut to 150 lbf.in. (1.70 m.daN) using wrench Item F. (h)Back off the locknut and RETORQUE to 150 lbf.in. (1.70 m.daN) a minimum 3 times to assure ballscrew is fully seated. (i)Slide actuator stop into serrated internal diameter of gearbox lock nut. Make certain that stop is on previously marked locations. (j)If stop serrations interfere with locknut serrations, slowly apply additional torque to maximum of 210 lbf.in (2.37 N.m) while tapping firmly on exposed end of stop, using a plastic of other soft rod and hammer, until stop serrations enter locknut serrations. Adjust stop position axially to be on previously marked locations. CAUTION : DO NOT TIGHTEN LOCKNUT MORE THAN 210 LBF-IN (2,37 m.daN) _______ (k)If stop and locknut do not assemble by 210 lbf.in. (2.37 m.daN) back off locknut to below 150 lbf.in. and repeat the procedure starting with step 3.C. (1) (e). (l)Install actuator stop set screw ; tighten until screw bottoms completely. (m)Lubricate actuator as required. (Use Material C02-014, C02-015, C02-016 or C02-43. (2)Install assembly (Ref. 78-31-02 or 78-31-03).


�� G E � � � � CF6 - 50 � �� PRESSURE REGULATING AND SHUT OFF VALVE - MAINTENANCE PRACTICES ______________________________________________________________

WARNING : MAKE CERTAIN THAT CIRCUIT BREAKERS ARE OPEN, SAFETIED AND TAGGED AND _______ THAT AIR SUPPLY IS NOT APPLIED AT THE GROUND CONNECTIONS. INADVERTENT ENGINE START OR THRUST REVERSER OPERATION COULD RESULT IN DEATH OR SERIOUS INJURY TO PERSONNEL.


A. Removal/Installation

B. Inspection/Check

2. Equipment and Materials _______________________ NOTE : Equivalent substitutes may be used instead of the following items. ____ ------------------------------------------------------------------------------- ITEM DESIGNATION -------------------------------------------------------------------------------R A. Material No. C02-004 Anti-Seize Compounds - Lubricants - Oils (Ref. 20-32-00) B. Material No. C03-006 Finishes and Protective Coatings (Ref. 20-32-00) C. Material No. C04-002 Cleaning Compounds and Solvents (Ref. 20-32-00) D. Material No. C04-004 Cleaning Compounds and Solvents (Ref. 20-32-00) E. Material No. C04-105 Cleaning Compounds and Solvents (Ref. 20-32-00) F. Access Platform 3 m (10 ft.) G. Torque Wrench 24-300 lbf.in. (0.27 - 3.39 m.daN) H. Circuit Breaker Safety Clips I. Lint-Free Cloth J. Blanking Caps K. Warning Notices Referenced Procedures - 71-13-00, P. Block 301 Cowl Doors - 78-31-00, P. Block 201 Thrust Reverser System


�� G E � � � � CF6 - 50 � �� 3. Procedure (Ref. Fig.201 and 202) _________

A. Job Set-Up (1)Position access platform (2)Open, safety and tag the circuit breakers for the appropriate engine and open core cowl, fan cowl and thrust reverser doors (Ref. 71-13-00, P. Block 301). (3)Open core cowls 456AR (466AR), fan cowls 436AR (446AR), fan thrust reverser cowls 452AR (462AR) (Ref. 71-13-00, P. Block 301).R (4)On panel 59VU :R - Make certain that APU Bleed Load Valve Control Switch (40HB) is inR CLOSE position and install a warning notice to tell persons not toR use it.R - Make certain that X BLEED VALVE Control Switch (39HB) is in CLOSER position and install a warning notice to tell persons not to use it.R (5)Make certain that a warning notice is installed on the HP GROUNDR connector to tell persons not to use it. WARNING : FOR ALL MAINTENANCE PROCEDURES INSIDE COWLS, EXTEND HOLD-OPEN _______ RODS TO HOLD COWLS OPEN. INADVERTENT CLOSURE OF COWLS COULD RESULT IN SERIOUS INJURY TO PERSONNEL.

B. Removal/Installation (1)Remove the pressure regulating and shut off valve as follows : (a)Disconnect reference tube (2) and control tube (5). (b)Loosen clamp nuts, and slide clamps (6) and (1) respectively onto flange of outlet duct (8) and check valve (7). (c)Remove mounting bolts and nuts; remove the assembly. (d)Cap open duct and tube ends. (e)Remove union (3) from reference port and remove union (4) from control port; discard O-rings.

C. Preparation of Replacement Component (1)Clean parts retained from removed component, check for correct condition.

D. Pressure Regulating and Shut Off Valve Installation NOTE : Flange alignment of the air supply tube is important in minimizing ____ air leakage and possible exposure of other components to heated air. To ensure optimum sealing conditions it is necessary to torque the air supply tube at the manifold end prior to tightening any of the regulating valve bracketing. (1)Install new lubricated O-rings on union (3) and (4), and install in reference and control ports. TORQUE control union (4) to between 155 and 175 lbf.in. (13 and 14.58 lbf.ft.) (1.75 and 1.97 m.daN), and reference union (3) to between 180 and 200 lbf.in. (15 and 16.66 lbf.ft.) (2.03 and 2.26 m.daN). Safety with 0.032 in. (0.813 mm) corrosion-resistant steel lockwire. (2)Position assembly at check valve (7), with spacer positioned between flanges (dimples/tangs to pressure regulator overpressure valve), and the outlet duct (8). CAUTION : SPACER MUST BE INSTALLED WITH THE FACES POSITIONED AS SPECIFIED _______ ON EACH FACE.


�� G E � � � � CF6 - 50 � �� CAUTION : THE DIMPLES IN THE SPACER FIT WITHIN THE GROOVE ON THE _______ PRESSURE REGULATOR AND SHUTOFF VALVE FLANGE WHEN PROPERLY INSTALLED. A MAJOR LEAK WILL RESULT IF SPACER IS REVERSED. _______________________________________________ (3)Secure to mounting bracket but leave the bolts that attach the angle brackets to the pressure regulator valve and pressure regulator valve bracket loose. Also have the bolts that attach the pressure regulator valve bracket to the engine loose.R (4)Lubricate the inner surfaces of the ?V? clamps using MaterialR No.C02-004. Position clamp (6) at the outlet duct flange, torque nut to 70-80 lbf.in.(0.79-0.9 m.daN) then position clamp (1) at the check valve flange,torque nut to 70-80 lbf.in. (0.79-0.9 m.daN).

NOTE : Tap ?V? clamp and retorque, continue until no change is noted ____ in torque value. (5)Connect reference tube (2) and control tube (5). TORQUE reference tube coupling nut to between 270 and 300 lbf.in. (22.5 and 25 lbf.ft) (3.05 and 3.39 m.daN) and control tube coupling nut to betwwen 180 and 200 lbf.in. (2.03 and 2.26 m.daN). (6)Tighten the bolts securing the pressure regulator valve bracket to the engine. TORQUE bolts to between 55 and 70 lbf.in. (0.62 and 0.79 m.daN). (7)Tighten the bolts securing the angle brackets to the pressure regulator valve. TORQUE bolts to between 55 and 70 lbf.in. (0.62 and 0.79 m.daN). NOTE : Configuration 2 : TORQUE bolts securing the angle brackets ____ together to between 24 and 27 lbf.in. (0.27 and 0.30 m.daN). (8)Tighten the bolts securing the angle brackets to the pressure regulator valve bracket. TORQUE bolts to between 55 and 70 lbf.in. (0.62 and 0.79 m.daN). NOTE : Following the above sequence will minimize residual stresses ____ in the brackets. (8)Check that all connections, fittings and clamps are secure and that all safetying has been accomplished.


�� G E � � � � CF6 - 50 � ��

Pressure Regulating and Shut Off Valve - Configuration 1R Figure 201


�� G E � � � � CF6 - 50 � ��

Pressure Regulating and Shut Off Valve - Configuration 2R Figure 202


�� G E � � � � CF6 - 50 � �� E. Inspection/Check (1)Visually inspect pressure regulating and shut off valve as follows : -------------------------------------------------------------------------------- INSPECTION/CHECK MAXIMUM SERVICEABLE LIMITS REMARKS -------------------------------------------------------------------------------- (a)Mating flanges for Any number 0.010 in. Replace valve nicks, dents or (0.254 mm) deep not complete- scratches. ly across mating surface. (b)Mounting surfaces Any amount that can be blended for nicks, dents or scratches. (c)Housing for nicks, Any amount not exceeding 10 Replace valve dents or scratches. percent of housing thickness. (d)Sensing filter Screen shall be free of If damaged assembly foreign matter and replace ; (visual). undamaged with screen obstructed, secure in plug. clean, per Paragraph F.

F. Approved Repairs (1)Obstructed screen (any method is acceptable) (a)Clean filter assembly as follows (Ref. Fig. 203 ) 1 Soak filter assembly in solvent, Stoddart Solvent (C04-002) and rinse _ in warn tap water. 2 Soak filter assembly for 24 hours in paint and carbon remover _ (Material C04-105). Rinse in cold water and dry with filtered compressed air at 20 psig maximum.

WARNING : USE ONLY STABILIZED TRICHLOROETHYLENE IN VAPOR DECREASING _______ MACHINES. AVOID BREATHING FUMES AND CONTACT WITH SKIN. 3 Immerse filter assembly in vapor degreasing machine containing _ stabilized trichloroethylene (C04-004) and flush thoroughly.

G. Tests (1)Check for correct operation per 78-31-00, P. Block 201.

H. Close-Up (1)Make certain that working area is clean and clear of tools and miscellaneous items of equipment. (2)Close circuit breakers for the appropriate engeine and close core cowl, fan cowl and thrust reverser doors (Ref. 71-13-00, P. Block 301).R (3)Remove warning notices from panel 59VU and HP GROUND connector.


�� G E � � � � CF6 - 50 � ��

Pressure Regulator Sense Line FilterR Figure 203


�� G E � � � � CF6 - 50 � �� DIRECTIONAL CONTROL VALVE - MAINTENANCE PRACTICES _________________________________________________

CAUTION : BEFORE ATTEMPTING MAINTENANCE PRACTICES FOR DIRECTIONAL CONTROL _______ VALVE, MAKE CERTAIN THROTTLE CONTROL LEVERS ARE IMMOBILIZED IN THE IDLE POSITION. AS A SAFETY PRECAUTION, DISPLAY WARNING NOTICES ON THROTTLE CONTROL LEVERS, FLAP AND SLAT CONTROL LEVER, PANEL 40VU AND APU CONTROL SWITCH (PANEL 59VU) TO PROHIBIT MANEUVERS. WARNING : MAKE CERTAIN THAT CIRCUIT BREAKERS ARE OPEN, SAFETIED AND TAGGED AND _______ THAT AIR PRESSURE IS NOT APPLIED THROUGH GROUND CONNECTIONS. INADVER- TENT ENGINE START OR THRUST REVERSER OPERATION COULD RESULT IN DEATH OR SERIOUS INJURY TO PERSONNEL.



B. Inspection/Check

C. Repair

2. Equipment and Materials _______________________ NOTE : Equivalent substitutes may be used instead of the following commer- ____ cially available items. ------------------------------------------------------------------------------- ITEM DESIGNATION ------------------------------------------------------------------------------- A. Access Platform 4.10 m (13 ft. 6 in.) B. 290.121-4 Test Set-Valve Actuating C. 98A27901022000 Tool-Locking, Flap and Slat Control Lever D. 98A27901023000 Tool-Locking, Throttle Control Lever E. Cotter Pins F. Corrosion-Resistant Steel Lockwire 0.032 in. Dia. (0.813 mm) G. Torque Wrench 24-300 lbf.in. (0.27 - 3.39 m.daN) H. Circuit Breaker Safety Clips J. Blanking Plugs/Caps Referenced ProcedureR - 78-31-00, P. Block 201 Thrust Reverser System Control


�� G E � � � � CF6 - 50 � �� 3. Procedure _________

A. Job Set-Up (1)Open, safety and tag circuit breakers for the appropriate engine (Ref. 71-13-00, P. Block 301).

(2)Install locking tool on throttle control levers. (3)Install locking tool on flap and slat control lever (4)Position access platforms. (5)Open access doors 413FL (423FL), 471AL (481AL). (6)Remove air supply duct and blank off both ends of the duct. (7)Blank off both open ends of air supply duct in pylon.

R **ON A/C 001-003, 102-102, 105-105,

B. Removal (Ref. Fig.201 and 202) (1)Remove directional control valve as follows : (a)Disconnect pneumatic line (5) from directional control valve (2). (b)Remove cotter pin, pin (8) and disconnect link rod (9). (c)Remove bolts (15), and remove directional control valve (2) from pylon mounting bracket (14). Retain shim washer (13). (d)Remove pin (6), remove lever (7) from directional control valve (2). Retain lever (7). (e)Clean parts retained from removed component, check for correct condition.

C. Installation (1)Install directional control valve as follows : (a)Install lever (7) into directional control valve clevis, install pin (6). (b)Install directional control valve on pylon mounting bracket (14) install shim washer (13) and secure with bolts (15). TORQUE to between 24 and 27 lbf. (0.27 and 0.30 m.daN). (c)Connect link-rod (9) to directional control valve level (7). Secure with pin (8), washer and nut. Tighten nut and insert new cotter pin. (d)Connect pneumatic line (5). TORQUE to between 270 and 300 lbf. in. (3.05 and 3.39 m.daN) (22.5 and 25 lbf.ft). Safety with 0.032 in. corrosion-resistant steel lockwire.

R **ON A/C 004-101, 103-104, 106-999,

B. Removal (Ref. 76-11-31, P. Block 401)

C. Installation (Ref. 76-11-31, P. Block 401)


�� G E � � � � CF6 - 50 � ��

Directional Control Valve - Location Figure 201

��R �EFFECTIVITY: 001-003, 102-102, 105-105, �� 78-31-06 � � � � Page 203 � � JAS Jul 01/89

�� G E � � � � CF6 - 50 � ��

Directional Control Valve - Support Assembly/AdjustmentR Figure 202

�� EFFECTIVITY: 001-003, 102-102, 105-105, �� 78-31-06 � � � � Page 204 � � JAS Oct 01/92

�� G E � � � � CF6 - 50 � ��

**ON A/C ALL

D. Inspection/Check Visually inspect directional control valve as follows : -------------------------------------------------------------------------------- INSPECT MAXIMUM SERVICEABLE LIMITS REMARKS -------------------------------------------------------------------------------- (1)Thread damage 30 percent damage on one entrance thread Repair per or 10 percent damage on each of 2 paragraph E entrance threads

(2)Actuation arm No flat spots allowed, lever must rotate Replace valve link for flat freely spots and freedom of rotation

(3)Valve piston for None allowed Replace valve scoring or wear

(4)Nicks, dents or Any amount not exceeding 0.020 in. Replace valve scratches on (0.508 mm) depth housing

(5)Cracks at moun- None allowed Replace valve ting bolt holes

(6)Corrosion on Any amount not exceeding 0.020 in. Replace valve housing external (0.508 mm) depth surface

E. Approved Repairs (1)Thread damage within serviceable limits may be repaired by blending with a fine file.

R F. AdjustmentR (Ref. 76-11-31, P. Block 401).


�� G E � � � � CF6 - 50 � �� PNEUMATIC SWITCHER VALVE - MAINTENANCE PRACTICES ________________________________________________

WARNING : MAKE CERTAIN THAT CIRCUIT BREAKERS ARE OPEN, SAFETIED AND TAGGED, _______ AND THAT AIR PRESSURE IS NOT APPLIED THROUGH GROUND CONNECTIONS. INADVERTENT ENGINE START OR THRUST REVERSER OPERATION COULD RESULT IN DEATH OR SERIOUS INJURY TO PERSONNEL.



B. Inspection/Check

C. Repair


NOTE : Equivalent substitutes may be used instead of the following ____ items. ------------------------------------------------------------------------------- ITEM DESIGNATION ------------------------------------------------------------------------------- A. Material C03-006 Finishes and Protective Coatings (Ref. 20-32-00) B. Access Platform 2 m (6 ft. 7 in.) C. Torque Wrench. 55-300 lbf.in. (0.62-3.39 m.daN) D. Circuit Breaker Safety Clips

E. Corrosion-Resistant Steel Lockwire Dia. 0.032 in. (0.813 mm) F. Blanking Caps Referenced Procedures - 71-13-00, P. Block 301 Cowl Doors - 78-31-00, P. Block 201 Thrust Reverser System



A. Job Set-Up (1)Position access platform.R (2)Open, safety and tag circuit breakers for the appropriate engine andR open fan cowl doors (Ref. 71-13-00, P. BLock 301).R WARNING : FOR ALL MAINTENANCE PROCEDURES INSIDE COWLS, EXTEND _______ HOLD-OPEN RODS TO HOLD COWLS OPEN. INADVERTENT CLOSURE OF COWLS COULD RESULT IN SERIOUS INJURY TO PERSONNEL.

B. Removal (1)Remove pneumatic switcher valve as follows : (a)Disconnect stow tube (6) and deploy tube (2). Cap open ends. (b)Remove mounting bolts (5) and release switcher valve (4) from feedback bracket (1). (c)Remove unions (3) and (7), respectively from deploy and stow ports. Discard O-rings.

C. Preparation of Replacement Component (1)Clean parts retained from removed component. Check for correct condition.

D. Installation (1)Install pneumatic switcher valve as follows : (a)Assemble new lubricated O-rings on unions (3) and (7) and respectively install in deploy and stow ports. TORQUE unions to between180 and 200 lbf. in. (15 and 16.66 lbf.ft.) (2.03 and 2.26 m.daN). Safety with 0.032 in. dia. (0.813 mm) corrosion-resistant steel lockwire. NOTE : An installed orifice nipple can be identified from a standard ____ nipple by a 0.030 in. (0.762 mm) groove in two opposing wrenching flats. (b)Install bolts (5) and lockwashers (8) in switcher valve body and install shims (9) as required between switcher valve and mounting bracket to ensure 0.040 in. (1.01 mm) pretravel of switcher valve poppets in the non-actuated position. NOTE : Make certain that switcher valve actuating push-rods (10) ____ are resting on cam followers (11). (c)TORQUE bolts (5) to between 55 and 70 lbf. in. (0.62 and 0.79 m.daN). Safety with 0.032 in. dia. (0.813 mm) corrosion-resistant steel lockwire. (d)Install stow tube (6) and deploy tube (2). TORQUE nuts to between 270 and 300 lbf.in. (22.5 and 25 lbf.ft.) (3.05 and 3.39 m.daN). Safety with 0.032 in. dia. (0.813 mm) corrosion-resistant steel lockwire. Fig. AAM0 Pneumatic Switcher Valve

E. Inspection/Check Visually inspect pneumatic switcher valve as follows :


�� G E � � � � CF6 - 50 � ��

Pneumatic Switcher Valve Figure 201


�� G E � � � � CF6 - 50 � �� -------------------------------------------------------------------------------- INSPECT MAXIMUM SERVICEABLE LIMITS REMARKS -------------------------------------------------------------------------------- (1)Thread damage 30 percent on one entrance thread Repair per or 10 percent damage on each of paragraph F. 2 entrance threads

(2)Push-rods for None allowed Replace switcher scoring valve

(3)Cracks at mounting None allowed Replace bolt holes switcher valve

(4)Nicks, dents or Any amount not exceeding 0.010 in. Replace switcher scratches on (0.25 mm) valve housing surface

(5)Push-rods for Must depress to within 0.050 in. Replace switcher freedom of motion (1.27 mm) of housing with maximum valve of 20 lbf. (0.23 m.daN) pressure and spring back freely when released

F. Approved Repairs (1)Thread damage within serviceable limits may be repaired by blending with a fine file. Protect bare areas with alodine (C03-006).

G. Tests (1)Check for correct operation per 78-31-00, P. Block 201.

H. Close-Up (1)Make certain that working area is clean and clear of tools and miscellaneous items of equipment.R (2)Remove access platform.R (3)Remove safety clips and tags, close circuit breakers for the appro-R priate engine and close fan cowl doors (Ref. 71-13-00, P. Block 301).


�� G E � � � � CF6 - 50 � �� THROTTLE AND THRUST REVERSER INTERLOCK VALVE MAINTENANCE PRACTICES __________________________________________________________________

WARNING : MAKE CERTAIN THAT CIRCUIT BREAKERS ARE OPEN, SAFETIED AND _______ TAGGED, AND THAT AIR PRESSURE IS NOT APPLIED THROUGH GROUND CONNECTIONS. INADVERTENT ENGINE START OR THRUST REVERSER OPERATION COULD RESULT IN DEATH OR SERIOUS INJURY TO PERSONNEL.



B. Inspection/Check

C. Repair

2. Equipment and Materials _______________________ NOTE : Equivalent substitutes may be used instead of the following items. ____ ------------------------------------------------------------------------------- ITEM DESIGNATION ------------------------------------------------------------------------------- A. Material C03-006 Finishes and Protective Coatings (Ref. 20-32-00) B. Access Platform 2 m (6 ft. 7 in.) C. Torque Wrench - 55-300 lbf.in. (0.62 - 3.39 m.daN). D. Circuit Breaker Safety Clips E. Lint-Free Cloth F. Corrosion-Resistant Steel Lockwire 0.032 in. (0.813 mm) Dia. G. Blanking Caps Referenced Procedures - 71-13-00, P. Block 301 Cowl Doors - 78-31-00, P. Block 201 Thrust Reverser System


�� G E � � � � CF6 - 50 � �� 3.Procedure (Ref. Fig. 201 ) _________

A. Job Set-Up (1)Position access platformR (2)Open, safety and tag circuit breakers for the appropriate engine and openR fan cowl doors (Ref. 71-13-00, P. Block 301) WARNING : FOR ALL MAINTENANCE PROCEDURES INSIDE COWLS, EXTEND HOLD-OPEN _______ RODS TO HOLD COWLS OPEN. INADVERTENT CLOSURE OF COWLS COULD RESULT IN SERIOUS INJURY TO PERSONNEL.

B. Removal (1)Remove interlock valve as follows : (a)Disconnect actuator and pressure lines (4) and (7) (b)Remove mounting bolts (1) and remove valve (2). (c)Remove unions (3) and (6), respectively from actuator and pressure ports ; discard O-rings.


D. Installation (1)Install interlock valve as follows : (a)Assemble new lubricated O-rings on unions (3) and (6), and install in actuator and pressure ports. TORQUE unions to between 180 and 200 lbf.in. (15 and 16.66 lbf. ft.) (2.03 and 2.26 m.daN). Safety with 0.032 in. (0.813 mm) dia. corrosion-resistant steel lockwire. (b)Install valve (2) on mounting bracket (5). Secure with bolts (1). TORQUE bolts to between 55 and 70 lbf.in. (0.62 and 0.79 m.daN). Safety with 0.032 in. (0.813 mm) dia. corrosion-resistant steel lockwire. (c)Connect actuator line (4) and pressure line (7). TORQUE nuts to between 270 and 300 lbf.in. (22.5 and 25 lbf.ft.) (3.05 and 3.39 m.daN). Safety with 0.032 in. (0.813 mm) dia. corrosion- resistant steel lockwire.

E. Inspection/Check Visually inspect interlock valve as follows : -------------------------------------------------------------------------------- INSPECT MAXIMUM SERVICEABLE LIMITS REMARKS -------------------------------------------------------------------------------- (1)Thread damage 30 percent on one entrance Repair per paragraph F thread or 10 percent damage on each of 2 entrance threads

(2)Housing for nicks, Any amount not exceeding 10 Replace valve dents or scratches percent of material thickness.

(3)Actuator arm for Any amount up to 0.010 in. Replace valve nicks, dents or (0.25 mm) after removal of scratches high metal


�� G E � � � � CF6 - 50 � �� -------------------------------------------------------------------------------- INSPECT MAXIMUM SERVICEABLE LIMITS REMARKS -------------------------------------------------------------------------------- (4)Actuator arm roller Roller must rotate freely Replace valve for freedom of rotation

(5)Mounting holes for None allowed Replace valve cracks

(6)Actuator arm for Must rotate with 10 lbf. Replace valve freedom of motion (0.113 daN) max. force, and spring back freely when released

(7)Actuator poppet Must not extend beyond Adjust screw in extending from rear 0.025 in. (0.635 mm) arm as necessary to of housing ensure poppet isR (9037M89P01, 02 or flush with end ofR 03 valves only) housing

R (8)Actuator poppet Must not extend beyond Adjust screw inR extending from rear 0.025 in. (0.635 mm) arm as necessary toR of housing ensure poppet isR (9037M89P04 valve) 0.008 to 0.010 in.R (0.020-0.25 mm)R away from washer onR end of housing

F. Approved Repairs (1)Thread damage within serviceable limits may be repaired by blending with a fine file. Protect bare areas with Alodine (C03-006).

G. Close-Up (1)Make certain that working area is clean and clear of tools and miscellaneous items of equipment. (2)Remove access platform. (3)Remove safety clips and tags, close circuit breakers for the appropriate engine and close fan cowl doors (Ref. 71-13-00, P. Block 301)

H. Test WARNING : MAKE CERTAIN THAT ENGINE THRUST REVERSER MOVING PARTS ARE _______ CLEAR OF PERSONNEL AND MISCELLANEOUS ITEMS OF EQUIPMENT. (1)Check thrust reverser system per 78-31-00, P. Block 201.


�� G E � � � � CF6 - 50 � ��

Throttle and Thrust Reverser Interlock Valve Figure 201


�� G E � � � � CF6 - 50 � �� OVERPRESSURE SHUT OFF BUTTERFLY VALVE - MAINTENANCE PRACTICES _____________________________________________________________

WARNING : MAKE CERTAIN THAT CIRCUIT BREAKERS ARE OPEN, SAFETIED AND TAGGED _______ AND THAT AIR PRESSURE IS NOT APPLIED THROUGH GROUND CONNECTIONS. INADVERTENT ENGINE START OR THRUST REVERSER OPERATION COULD RESULT IN DEATH OR SERIOUS INJURY TO PERSONNEL.



B. Inspection/Check

C. Repair

2. Equipment and Materials _______________________ NOTE : Equivalent substitutes may be used instead of the following items. ____ ------------------------------------------------------------------------------- ITEM DESIGNATION -------------------------------------------------------------------------------R A. Material C02-004 Anti-seize Compounds-Lubricants-Oils (Ref. 20-32-00) B. Material C03-006 Finishes and Protective Coatings (Ref. 20-32-00) C. Material C04-003 Cleaning Compounds and Solvents (Ref. 20-32-00) D. Access Platform 3 m (10 ft.) E. Torque Wrench 24-300 lbf.in. (0.27-3.39 m.daN) F. Circuit Breaker Safety Clips G. Corrosion-Resistant Steel Lockwire, 0.032 in. (0.813 mm) Dia. H. Corrosion-Resistant Steel Lockwire, 0.020 in. (0.508 mm) Dia. I. Blanking Caps J. Warning Notices Referenced Procedures - 71-13-00, P. Block 301 Cowl Doors - 78-31-00, P. Block 201 Thrust Reverser System



A. Job Set-Up (1)Position access platforms. (2)Open, safety and tag circuit breakers for the appropriate engine and open core cowl, fan cowl and thrust reverser doors (Ref. 71-13-00, P. Block 301) (3)On panel 59VU : - Make certain that APU Bleed Load Valve Control Switch (40HB) is in CLOSE position and install a warning notice to tell persons not to use it. - Make certain that X BLEED VALVE Control Switch (39HB) is in CLOSE position and install a warning notice to tell persons not to use it. (4)Make certain that a warning notice is installed on the HP GROUND connector to tell persons not to use it. WARNING : FOR ALL MAINTENANCE PROCEDURES INSIDE COWLS, EXTEND _______ HOLD-OPEN RODS TO HOLD COWLS OPEN. INADVERTENT CLOSURE OF COWLS COULD RESULT IN SERIOUS INJURY TO PERSONNEL.

B. Removal (1)Remove overpressure shut off butterfly valve as follows : (a)Disconnect electrical connectors (9) and (10) and lead clamps. (b)Disconnect reference tube (8). (c)Disconnect brake release tube (7). (d)Disconnect control tube (5). (e)Loosen coupling locknuts and slide clamps (1) and (12) off valve. (f)Remove bolts (3) and nuts ; remove valve. (g)Cap open duct and tube ends. (h)Remove reducer (6) and O-ring from brake release port ; discard O-ring.


D. Installation (1)Install overpressure shut off butterfly valve as follows : (a)Install new lubricated O-ring on reducer (6), and install in brake release port. TORQUE reducer to between 180 and 200 lbf. in. (15 and 16.66 lbf.ft.) (2.03 and 2.26 m.daN). Safety with 0.032 in. (0.813 mm) dia. corrosion-resistant steel lockwire. (b)Install valve between pneumatic drive actuator port (2) and inlet duct (11) end. Install bolts (3) and nuts on mounting bracket (4). Tighten nuts finger-tight. (c)Install clamp (12) at inlet port. Install spacer (13) between flange of overpressure valve and pneumatic drive actuator, (dimples tang to rabbet in overpressure valve flange). (d)Lubricate the inner surface of the ?V? clamp, using materialR (C02-004). Then position clamp (1) to each flange. TORQUE nut on clamp to between 70 and 80 lbf. in. (0.79 and 0.90 m. daN). NOTE : Tap clamps and retorque, continue until no change is noted ____ in torque value.


�� G E � � � � CF6 - 50 � ��

Overpressure Shut Off Butterfly ValveR Figure 201


�� G E � � � � CF6 - 50 � �� NOTE : Position clamp so interference between clamp bolt and duct ____ sidewall does not exist when reverser is closed. (e)TORQUE valve mounting bolts (3) to between 24 and 27 lbf.in. (0.27 and 0.30 m.daN). (f)Connect control tube (5). TORQUE nut to between 180 and 200 lbf.in. (15 and 16.66 lbf.ft.)-(2.03 and 2.26 m.daN). Safety with 0.032 in. (0.813 mm) dia. corrosion resistant steel lockwire. (g)Connect release tube (7). TORQUE nut to between 135 and 150 lbf.in. (11.25 and 12.5 lbf.ft.) (1.53 and 1.69 m.daN) Safety with 0.032 in. (0.813 mm) dia. corrosionresistant steel lockwire. (h)Connect reference tube (8). TORQUE nut to between 270 and 300 lbf.in. (22.5 and 25 lbf.ft.) (3.50 and 3.39 m.daN). Safety with 0.032 in. (0.813 mm) dia. corrosionresistant steel lockwire. (i)Connect electrical connectors (9) and (10). Tighten finger-tight. Safety with 0.020 in. (0.508 mm) dia. corrosion-resistant steel lockwire. Install clamps on leads. TORQUE clamp bolts to between 24 and 27 lbf.in. (0.27 and 0.30 m.daN).

CAUTION : ELECTRICAL CONNECTORS MUST BE TIGHTENED BY HAND ONLY. USE _______ OF TOOL COULD RESULT IN DAMAGE TO CONNECTOR OR WIRING.


�� G E � � � � CF6 - 50 � �� E. Inspection/Check (Ref. Fig. 202 )

Clearance Check of Pressure Sensing Tube Figure 202

Visually inspect overpressure shut off valve as follows : ----------------------------------------------------------------------------- INSPECTION/CHECK MAXIMUM SERVICEABLE LIMITS REMARKS ----------------------------------------------------------------------------- (1) Mating flanges Any amount 0.010 in. (0.2 mm) Replace for nicks, deep not extending comple- valve dents or tely across flange scratches

(2) Mounting Any amount that can be surface for blend repaired nicks, dents or scratches

(3)Housing for nicks, Any amount not exceeding Replace valve dents or scratches 10 percent of housing


�� G E � � � � CF6 - 50 � �� thickness

(4)Electrical connector for (a)Bent pins None allowed Replace valve (b)Thread damage 30 percent on one entrance Repair per para. thread or 10 percent damage F. or replace on each of 2 entrance valve threads (c)Chipped insulation Any amount, provided pins Replace valve between pins are not shorted and are still in their relative positions

(5) Clearance between Minimum clearance of 0.250 Replace tube per left hand reverser in. (6.35 mm) S/B 78-63 cowl and the pressure sensing tube (Configuration 1 only)

F. Approved RepairsR (1)Thread damageR Thread damage within serviceable limits may be repaired by blending with a fine file. Protect bare areas with Alodine (C03-006).R (2)Removal/Installation of pressure relief valve at the reference port ofR shutoff valve (***//AEM0//***).R (a)Remove lockwire, discard.R (b)Remove relief valve, discard OQring.R (c)Clean valve as an assembly using solvent (C04-003) and soft bristleR brush.R (d)Place a new lubricated OQring onto relief valve and install valveR into reference port. (Ref. Fig. 203 )R (e)TORQUE relief valve to between 90 and 100 lbf.in. (1.02 and 1.13R m.daN) and wirelock.


�� G E � � � � CF6 - 50 � ��

Overpressure Shutoff Valve - Relief Valve InstallationsR Figure 203


�� G E � � � � CF6 - 50 � �� G. Tests (1)Check for correct operation per 78-31-00, P. Block 201.

H. Close-Up (1)Make certain that working area is clean and clear of tools and miscellaneous items of equipment. (2)Remove access platform (3)Remove safety clips and tags, close circuit breakers for the appropriate engine and close core cowl fan cowl and thrust reverser doors (Ref. 71-13-00, P. Block 301)R (4)Remove warning notices from panel 59VU and HP GROUND connector.


�� G E � � � � CF6 - 50 � �� FAN REVERSER INDICATOR SWITCHES - MAINTENANCE PRACTICES _______________________________________________________

NOTE : Maintenance practices for fan reverser indicator switches ____ located either on RH feedback bracket assembly or LH feed-back bracket assembly are identical. LH stow switch maintenance practices are described as a typical procedure.

WARNING : MAKE CERTAIN THAT CIRCUIT BREAKERS ARE OPEN, SAFETIED AND TAGGED, AND _______ THAT AIR PRESSURE IS NOT APPLIED THROUGH GROUND CONNECTIONS. INAD- VERTENT ENGINE START OR THRUST REVERSER OPERATION COULD RESULT IN DEATH OR SERIOUS INJURY TO PERSONNEL.



B. Inspection/Check

C. Repair

2. Equipment and Materials _______________________ ------------------------------------------------------------------------------- ITEM DESIGNATION ------------------------------------------------------------------------------- A. Access Platform 2 m (6 ft. 7 in.) B. Circuit Breaker Safety Clips C. Corrosion-Resistant Steel Lockwire 0.032 in. (0.813 mm) Dia. D. Torque Wrench 24 - 27 lbf.in. (0.27 - 030 m.daN) E. Blanking Caps F. Corrosion-Resistant Steel Lockwire 0.020 in. (0.508 mm) Dia. Referenced ProceduresR - 71-13-00, P. Block 301 Cowl Doors - 78-31-00, P. Block 201 Thrust Reverser System


�� G E � � � � CF6 - 50 � ��

Fan Reverser Indicator Switches Figure 201



A. Job Set-Up (1)Position access platform. (2)Open, safety and tag circuit breakers for the appropriate engine and open fan cowl doors (Ref. 71-13-00, P. Block 301).

WARNING : FOR ALL MAINTENANCE PROCEDURES INSIDE COWLS, EXTEND HOLD-OPEN _______ RODS TO HOLD COWLS OPEN. INADVERTENT CLOSURE OF COWLS COULD RESULT IN SERIOUS INJURY TO PERSONNEL.

B. Removal (1)Remove fan reverser indicator switch as follows : (a)Disconnect electrical connector (7). Cap switch plug and electrical connector. (b)Remove bolts (6). Remove stow switch (8) from feedback bracket assembly (4).


D. Installation (1)Install fan reverser indicator switch as follows : (a)Install stow switch (8) on feedback bracket assembly (4). Secure with bolts (6). TORQUE bolts to between 24 and 27 lbf. in. (0.27 and 0.30 m.daN). Safety with 0.032 in. (0.813 mm) dia. corrosion resistant steel lockwire.

(b)Install electrical connector (7), tighten fingertight. Safety with 0.020 in. (0.508 mm) Dia. corrosion resistant steel lockwire. CAUTION : ELECTRICAL CONNECTORS MUST BE TIGHTENED BY HAND ONLY. USE OF _______ TOOL COULD RESULT IN DAMAGE TO CONNECTOR OR WIRING.

E. Inspection/Check (Ref. Fig. 202 ) Visually inspect fan reverser indicator switch as follows :


�� G E � � � � CF6 - 50 � ��

Indicator Switch Pin Location Figure 202

------------------------------------------------------------------------- INSPECTION/CHECK MAXIMUM SERVICEABLE LIMITS REMARKS ------------------------------------------------------------------------- (1)Electrical connector for

(a)Thread damage Total of one full thread may be Chase threads missing after chasing or replace switch

(b)Pin damage None allowed Replace switch

(c)Chipped insula- Any amount, provided pins are Replace switch tion between not shorted and are still in pins their relative positions

(2)Switch electrical characteristics for : (a)Shorts between None allowed Replace switch pins and case


�� G E � � � � CF6 - 50 � �� ------------------------------------------------------------------------- INSPECTION/CHECK MAXIMUM SERVICEABLE LIMITS REMARKS ------------------------------------------------------------------------- (b)Continuity in Continuity should exist between Replace switch the free posi- pins B and C and pins D and E tion only

(c)Continuity with Continuity should exist between Replace switch the plunger de- pins A and B and pins E and F pressed only

(d)Actuation point Continuity should change from Replace switch pins B and C to pins A and B with the plunger depressed 0.020 to 0.040 in. (0.51-1.02 mm).


�� G E � � � � CF6 - 50 � �� E. Approved Repairs (1)Thread damage within serviceable limits may be repaired by blending with a fine file.

F. Test (1)Check for correct operation per 78-31-00, P. Block 201.

G. Close-Up (1)Make certain that working area is clean and clear of tools and miscellaneous items of equipment. (2)Remove access platform. (3)Remove safety clips and tags, close circuit breakers for the appropriate engine and close fan cowl doors (Ref. 71-13-00, P. Block 301).


�� G E � � � � CF6 - 50 � �� FAN REVERSER FLEXIBLE SHAFT ASSY - MAINTENANCE PRACTICES ________________________________________________________

NOTE : Maintenance practices are identical for fan reverser flexible shafts ____ located between the pneumatic drive actuator and center actuator or between the lower actuator and the center actuator or the upper actuator and the center actuator or TRAS Lock assembly (if installed). WARNING : MAKE CERTAIN THAT CIRCUIT BREAKERS ARE OPEN, SAFETIED AND TAGGED, _______ AND THAT AIR PRESSURE IS NOT APPLIED THROUGH GROUND CONNECTIONS. INADVERTENT ENGINE START OR THRUST REVERSER OPERATION COULD RESULT IN DEATH OR SERIOUS INJURY TO PERSONNEL.

1. Reason for the Job __________________ A. Removal/Installation

B. Inspection/Check

2. Equipment and Materials _______________________ NOTE : Equivalent substitutes may be used instead of the following items. ____ ------------------------------------------------------------------------------- ITEM DESIGNATION ------------------------------------------------------------------------------- A. Material No.C01-077 Adhesives, Plastics, Sealants (Ref. 20-32-00) B. Material No.C02-014 Anti-Seize Compounds, Lubricants, Oils (Ref. 20-32-00). C. Material No.C02-015 Anti-Seize Compounds, Lubricants, Oils (Ref. 20-32-00).

D. Material No.C04-001 Cleaning Compounds and Solvents MEK (Ref. 20-32-00) E. Material No.C04-003 Cleaning Compounds and Solvents (Ref. 20-32-00) F. Material No.C04-004 Cleaning Compounds and Solvents (Ref. 20-32-00) G. Material No.C10-079 Miscellaneous (Ref. 20-32-00). H. Access Platforms 3 m (10 ft.) I. Torque Wrench Range 24-70 lbf.in. (0.27-0.79 m.daN) J. Circuit Breaker Safety Clips K. 2C6105P01 Adapter Drive-Angle Gearbox L. Corrosion-Resistant Steel Lockwire, 0.032 in. (0.813 mm) dia. Referenced Procedures - 71-13-00, P. Block 301 Cowl Doors - 78-31-00, P. Block 201 Thrust Reverser System Control

3. Procedure (Ref. Fig.202 and 203) _________

R **ON A/C 001-103, 106-999,



�� G E � � � � CF6 - 50 � ��

Fan Reverser Flexible Shafts - Post SB 78-022 Figure 201


�� G E � � � � CF6 - 50 � ��

R **ON A/C ALL

A. Job Set-Up (1)Position access platforms (2)Open, safety and tag circuit breakers for the appropriate engine and open fan cowl door (Ref. 71-13-00, P. Block 301). WARNING : FOR ALL MAINTENANCE PROCEDURES INSIDE COWLS, EXTEND HOLD- _______ OPEN RODS TO HOLD COWLS OPEN. INADVERTENT CLOSURE OF COWLS COULD RESULT IN SERIOUS INJURY TO PERSONNEL

B. Servicing Service flexible shafts; clean core with cloth dampened with solvent, Material No.C04-003, flush conduit with solvent Material No.C04-003, then lubricate core lightly with Material (C02-014 or C02-015).


�� G E � � � � CF6 - 50 � �� C. Removal (1)Remove flexible shafts (1) or (2) or (3) as follows : (a)Remove clamps, drive shaft guide bracket, and channel bolt (b)Not applicable. (c)Not applicable.

R **ON A/C 001-103, 106-999,

(b)Remove flexible shaft (2) coupling bolts from the upper gearbox housing and the TRAS Lock Assembly. (c)Remove flexible shaft (2) from the upper gearbox and the TRAS Lock Assembly.

R **ON A/C ALL

(d)Remove shaft coupling bolts from gearbox housings (e)Remove shaft from each gearbox and drive actuator if applicable ; remove shaft assembly NOTE : For flexible shaft (1), disconnect at center gearbox and ____ pull shaft core out approximately three to five in. (76.2 to 127 mm) before disconnecting from drive actuator. (f)For flexible shaft (1), remove seal and seal cover from fire wall and release shaft. CAUTION : IF A FLEX DRIVE SHAFT ON ONE REVERSER HALF FAILS, _______ THE FLEX SHAFTS ON THE AFFECTED REVERSER HALF MUST BE INSPECTED FOR DAMAGE, WIRE STRAND SEPARATION OR BROKEN STRANDS, SINCE TORSIONAL LIMITS MAY HAVE BEEN EXCEEDED. IF THE MAIN FLEX DRIVE SHAFT HAS FAILED BECAUSE OF A FULL STROKE HIGH SPEED DEPLOY/STOW, THE OPPOSITE REVERSER HALF MAIN FLEX DRIVE SHAFT MUST BE REPLACED. CAUTION : IF SHAFT IS COILED, MAINTAIN MINIMUM BEND RADIUS OF _______ 48 in. (1219.2 MM). NOTE : Prior to cable removal, release pneumatic drive actuator ____ by applying a pressure between 2 and 3 bars (29 and 45.5 psi) to pneumatic brake release (Ref.78-31-00, P. Block 1). (g)Clean part retained from removed component, check for correct condition.

D. Installation NOTE : Shaft casings have a tendency to shorten when not installed. ____ Using 30 - 40 lbf (13.34 daN - 17.8 daN) load, stretch casing prior to installation. (1)Install flexible shafts (2) or (3) (Ref. 78-31-00, P. Block 201). (a)Install shaft clamps; TORQUE clamp bolts to between 24 and 27 lbf. in. (0.27 and 0.30 m.daN). (2)Install flexible shafts (1) as follows : (a)Pull core out of casing approximately 6 in. (152.4 mm) at gearbox end. NOTE : Check the drive cable guide to assure the proper guide has been ____ installed for the application being assembled. (Ref. Fig. 204 ) (b)Insert the end of the shaft from which the square end of the core


�� G E � � � � CF6 - 50 � �� normally extends, through the fire wall and into the drive motor socket. Install the bolts. Apply anti-seize compound (MIL-A-907 or equivalent) to the bolt threads before you install the bolts. TORQUE the bolts to between 33 and 37 lbf. in. (0.37 and 0.43 m.daN). Safety with 0.032 in. (0.813 mm) diameter corrosion-resistant steel lockwire. NOTE : Push and rotate the core to assure engagement with drive ____ actuator. (c)Install seal and seal cover at firewall. TORQUE nuts to between 24 and 27 lbf.in. (0.27-0.30 m.daN). (d)Rig fan reverser drive shafts as directed in 78-31-00, P. Block 201. (e)Install shaft clamps, and guide bracket. TORQUE clamp bolts to between 24 and 27 lbf.in. (0.27 and 0.30 m.daN), and bracket bolts to 55 and 70 lbf.in. (0.62 and 0.79 m.daN). (f)With shaft seated in guide channel above firewall, install bolt and spacer. TORQUE bolt to between 55 and 70 lbf.in. (0.62 and 0.79 m.daN).

Flexible Shafts. Figure 202

E. Inspection/Check Visually inspect flexible shafts as follows :


�� G E � � � � CF6 - 50 � ��

Fan Reverser Flexible Shafts Figure 203


�� G E � � � � CF6 - 50 � ��

Drive Cable Guide Installation Figure 204

------------------------------------------------------------------------------- INSPECTION/CHECK MAXIMUM SERVICEABLE LIMITS REMARK ------------------------------------------------------------------------------- (1)Mounting flanges for Any amount that can be blend Replace casing nicks, dents or repaired assembly scratches (2)Binding None allowed Replace flexible shaft assembly (3)Casing for : (a)Black (rings indicate Maximum of two rings allowed Replace casing leakage) assembly (b)Twisting Maximum of 30• allowed Replace casing assembly (c)Hot spots or discolo- None allowed Replace casing ration assembly (d)Broken wires in braid Three wires per lay per foot of Trim broken casing length or 2 complete lays wires if wi- in each direction may be broken. thin limits


�� G E � � � � CF6 - 50 � �� ------------------------------------------------------------------------------- INSPECTION/CHECK MAXIMUM SERVICEABLE LIMITS REMARK ------------------------------------------------------------------------------- (A lay is composed of 4 or 5 or replace individual wire stands) casing assembly (e)End collars for loose- None allowed Replace casing ness assembly (4)Core for : CAUTION : IF REMOVED, ENSURE THAT SHAFT CORE IS PROPERLY LUBRICATED BEFORE _______ INSTALLATION IN CASING. (a)End wear Corners must not show evidence Replace power of rounding. For splined end wear, core dia. must 0.452 in. (11.48 mm) min. over 0.06000 in. (1.52 mm) dia. pins. (b)Ends for residue None allowed Wipe with build-up clean dry cloth (c)Ends for nicks or Any amount up to 0.030 in. Replace power scratches (0.762 mm) deep provided part will core assemble without binding, after removal high metal (d)Other areas for wear For smooth wear transition, local Replace power wear shall not exceed 50• of core individual wire thickness (e)Broken wires None allowed Replace power core (f)Local bowing, wire None allowed Replace power separation or humps core (5)Installed shaft for : (a)Clamping and bend radii Clamp centerline must be aligned Reclamp as with shaft centerline. Bend radii necessary must exceed 10 in. (254 mm) (b)Bowing between clamps None allowed Re-rig shaft (indicate torque build- (Ref. 78-31-00, up) P. Block 201)

F. Approved Repairs : (1)Broken Wire Braid NOTE : Warning tag and spiral wrap may be moved to facilitate repair ____ and then moved back to original position. (a)Trim or bend broken wire strand ends flush with casing surface. (b)Vapor degrease casing surface using stabilized trichlorethylene or by wiping the surface with a clean cloth saturated with trichlorethylene Material No.C04-004. (c)Mix the required amount of high temperature sealing compound Material No.C01-077 per the manufacturerQs instructions. (d)Wipe repair area with MEK Material No.C04-001) or equivalent and immediately dry with a clean cloth. (e)Apply sealing compound to cover any exposed liner and secure all loose


�� G E � � � � CF6 - 50 � �� wire ends. (f)Wrap compound with glass fiber tape, Material No. C10-070 to prevent sealing compound from flowing during cure. (g)Cure compound at 248•F (120•C) for four hours or compound may be cured during regular service.

G. Close-Up (1)Make certain that working area is clean and clear of tools and miscellaneous items of equipment. (2)Remove safety clips and tags, close circuit breakers for the appropriate engine and close fan cowl door (Ref. 71-13-00, P. Block 301). (3)Remove access platform.

H. Test (1)Check for correct operation per 78-31-00, P. Block 201.


�� G E � � � � CF6 - 50 � �� FAN REVERSER ELECTRICAL CABLE ASSY - MAINTENANCE PRACTICES __________________________________________________________




B. Inspection/Check

C. Approved Repairs

2. Equipment and Materials _______________________ NOTE : Equivalent substitutes may be used instead of the following items. ____ ------------------------------------------------------------------------------- ITEM DESIGNATION ------------------------------------------------------------------------------- A. Material C03-006 Finishes and Protective Coatings (Ref. 20-32-00) B. Access Platform 2 m (6 ft. 7 in.) C. Torque Wrench 24-27 lbf.in. (0.27-0.30 m.daN) D. Circuit Breaker Safety Clips E. Corrosion-Resistant Steel Lockwire, Dia. 0.020 in. (0.508 mm) F. Blanking Plugs/Caps Referenced Procedures - 78-31-00, P. Block 201 Thrust Reverser System - 71-13-00, P. Block 301 Cowl Doors

�� EFFECTIVITY: ALL �� 78-31-13 � � CONF. 01 � � Page 201 � � JAS Mar 01/06


A. Job Set-Up (1)Position access platform. (2)Open, safety and tag circuit breakers for the appropriate engine and open fan cowl door (Ref. 71-13-00, P. Block 301).

WARNING : FOR ALL MAINTENANCE PROCEDURES INSIDE COWLS, EXTEND HOLD-OPEN _______ RODS TO HOLD COWLS OPEN. INADVERTENT CLOSURE OF COWLS COULD RESULT IN SERIOUS INJURY TO PERSONNEL.

B. Removal (1)Remove fan reverser electrical cables as follows : (a)Remove electrical connector mounting bolts. Release electrical connector from bracket (1). (b)Disconnect electrical connectors from indicator switches (3). (c)Remove cable clamps and remove electrical cable (2).


D. Installation (1)Install fan reverser electrical cables as follows : (a)Connect electrical connectors to indicator switches. Tighten connectors fingertight. Safety connectors with 0.020 in. (0.508 mm) dia. corrosion-resistant steel lockwire. CAUTION : ELECTRICAL CONNECTORS MUST BE TIGHTENED BY HAND ONLY. _______ USE OF TOOL COULD RESULT IN DAMAGE TO CONNECTOR OR WIRING. (b)Install electrical connector on fire wall bracket (1). Secure connector with bolts and nuts. (c)Install cable clamps. TORQUE clamp bolts to between 24 and 27 lbf.in. (0.27 and 0.30 m.daN).

E. Inspection/Check Visually inspect electrical cables as follows. -------------------------------------------------------------------------------- INSPECTION/CHECK MAXIMUM SERVICEABLE LIMITS REMARKS -------------------------------------------------------------------------------- (1)Metal braid for None allowed Repair (Ref. Fig. 202 ) frayed or broken strands (2)Connectors for : (a)Thread damage 30% on one entrance thread Repair per para. F or or 10% on each of two replace cable. entrance threads. (b)Bent, broken or None allowed Replace cable corroded pins. (c)Chipped insu- Any amount provided pins are Replace cable lation between not shorted and are still in pins. their relative positions.


�� G E � � � � CF6 - 50 � ��

Fan Reverser Electrical Cable Assy Figure 201


�� G E � � � � CF6 - 50 � ��

Shielding Repairs Figure 202


�� G E � � � � CF6 - 50 � �� F. Approved Repairs (1)Thread damage within serviceable limits may be repaired by blending with a fine file. Protect bare areas with Material C03-006.

G. Close-Up (1)Make certain that working area is clean and clear of tools and miscellaneous items of equipment. (2)Remove access platforms. (3)Remove safety clips and tags, and close circuit breakers for the appropriate engine and close fan cowl door (Ref. 71-13-00, P. Block 301).

H. Test WARNING : MAKE CERTAIN THAT ENGINE THRUST REVERSER MOVING PARTS ARE CLEAR _______ OF PERSONNEL AND MISCELLANEOUS ITEMS OF EQUIPMENT. (1)Check thrust reverser system (Ref. 78-31-00, P. Block 201).


�� G E � � � � CF6 - 50 � �� FAN REVERSER AND TRAS LOCK ELECTRICAL CABLE ASSY - __________________________________________________ MAINTENANCE PRACTICES _____________________




B. Inspection/Check

C. Approved Repairs

2. Equipment and Materials _______________________ NOTE : Equivalent substitutes may be used instead of the following items. ____ ------------------------------------------------------------------------------- ITEM DESIGNATION ------------------------------------------------------------------------------- A. Material C03-006 Finishes and Protective Coatings (Ref. 20-32-00) B. Access Platform 2 m (6 ft. 7 in.) C. Torque Wrench 24-27 lbf.in. (0.27-0.30 m.daN) D. Circuit Breaker Safety Clips E. Corrosion-Resistant Steel Lockwire, Dia. 0.020 in. (0.508 mm) F. Blanking Plugs/Caps Referenced Procedures - 78-31-00, P. Block 201 Thrust Reverser System - 71-13-00, P. Block 301 Cowl Doors

��R �EFFECTIVITY: 001-103, 106-999, �� 78-31-13 � � CONF. 02 � � Page 201 � � JAS Mar 01/07


A. Job Set-Up (1)Position access platform. (2)Open, safety and tag circuit breakers for the appropriate engine and open fan cowl door (Ref. 71-13-00, P. Block 301). WARNING : FOR ALL MAINTENANCE PROCEDURES INSIDE COWLS, EXTEND HOLD-OPEN _______ RODS TO HOLD COWLS OPEN. INADVERTENT CLOSURE OF COWLS COULD RESULT IN SERIOUS INJURY TO PERSONNEL.

B. Removal (1)Remove fan reverser electrical cables as follows: NOTE : It is not necessary to remove the fan reverser electrical cables ____ to replace of do maintenance on the TRAS Lock assembly electrical cable. (a)Remove electrical connector mounting bolts. Release electrical connector from bracket (1). (b)Disconnect electrical connectors from indicator switches (3). (c)Remove cable clamps and remove electrical cable (2). (2)Remove the TRAS Lock assembly electrical cable as follows: NOTE : It is not necessary to remove the TRAS Lock assembly cable when ____ the fan reverser electrical cables are removed. Remove the TRAS Lock assembly electrical cables only when replacement or maintenance of the cables is necessary. (a)Remove electrical connector mounting bolts. Release the electrical connector from the firewall bracket (1). (b)Disconnect the electrical connectors from the TRAS Lock (5). (c)Remove the cable clamps and remove the electrical cable (4).


D. Installation (1)Install fan reverser electrical cables as follows: (a)Connect electrical connectors to indicator switches. Tighten connectors fingertight. Safety connectors with 0.020 in. (0.508 mm) dia. corrosion-resistant steel lockwire. CAUTION : ELECTRICAL CONNECTORS MUST BE TIGHTENED BY HAND ONLY. _______ USE OF TOOL COULD RESULT IN DAMAGE TO CONNECTOR OR WIRING. (b)Install electrical connector on fire wall bracket (1). Secure connector with bolts and nuts. (c)Install cable clamps. TORQUE clamp bolts to between 24 and 27 lbf.in. (0.27 and 0.30 m.daN). (2)Remove the TRAS Lock assembly electrical cable as follows: (a)Connect the electrical connectors to the TRAS Lock assembly. CAUTION : ELECTRICAL CONNECTORS MUST BE TIGHTENED BY HAND ONLY, USE OF _______ TOOL COULD RESULT IN DAMAGE TO CONNECTOR OR WIRING. (b)Install the electrical connector on the firewall bracket (1). Secure connector with bolts and nuts. (c)Install cable clamps. TORQUE clamp bolts to between 24 and 27 lbf.in. (0.27 and 0.30 m.daN).


�� G E � � � � CF6 - 50 � ��

Fan Reverser Electrical and TRAS Lock Electrical Cable Assy - Post SB 78-022 Figure 201 ��R �EFFECTIVITY: 001-103, 106-999, �� 78-31-13 � � CONF. 02 � � Page 203 � � JAS Mar 01/07

�� G E � � � � CF6 - 50 � �� E. Inspection/Check Visually inspect electrical cables as follows. -------------------------------------------------------------------------------- INSPECTION/CHECK MAXIMUM SERVICEABLE LIMITS REMARKS -------------------------------------------------------------------------------- (1)Metal braid for None allowed Repair (Ref. Fig. 202 ) frayed or broken strands (2)Connectors for : (a)Thread damage 30% on one entrance thread Repair per para. F or or 10% on each of two replace cable. entrance threads. (b)Bent, broken or None allowed Replace cable corroded pins. (c)Chipped insu- Any amount provided pins are Replace cable lation between not shorted and are still in pins. their relative positions.

F. Approved Repairs (1)Thread damage within serviceable limits may be repaired by blending with a fine file. Protect bare areas with Material C03-006.

G. Close-Up (1)Make certain that working area is clean and clear of tools and miscellaneous items of equipment. (2)Remove access platforms. (3)Remove safety clips and tags, and close circuit breakers for the appropriate engine and close fan cowl door (Ref. 71-13-00, P. Block 301).

H. Test WARNING : MAKE CERTAIN THAT ENGINE THRUST REVERSER MOVING PARTS ARE CLEAR _______ OF PERSONNEL AND MISCELLANEOUS ITEMS OF EQUIPMENT. (1)Check thrust reverser system (Ref. 78-31-00, P. Block 201).


�� G E � � � � CF6 - 50 � ��

Shielding Repairs Figure 202


�� G E � � � � CF6 - 50 � �� PNEUMATIC CHECK VALVE - MAINTENANCE PRACTICES _____________________________________________

WARNING : MAKE CERTAIN THAT CIRCUIT BREAKERS ARE OPEN, SAFETIED AND TAGGED AND _______ THAT AIR PRESSURE IS NOT APPLIED THROUGH GROUND CONNECTIONS. INADVERTENT ENGINE START OR THRUST REVERSER OPERATION COULD RESULT IN DEATH OR SERIOUS INJURY TO PERSONNEL.



B. Inspection/Check

C. Approved Repairs

2. Equipment and Materials _______________________ NOTE : Equivalent substitutes may be used instead of the following items. ____ ------------------------------------------------------------------------------- ITEM DESIGNATION -------------------------------------------------------------------------------R A. Material C02-004 Anti Seizes Compounds, Lubricants - Oils (Ref. 20-32-00) B. Material C03-006 Finishes and Protective Coatings (Ref. 20-32-00) C. Access Platform 3 m (10 ft.) D. Torque Wrench 70-100 lbf.in. (0.79 - 1.13 m.daN) E. Circuit Breaker Safety Clips F. Blanking Plugs/Caps G. Warning Notices Referenced Procedures - 71-13-00, P. Block 301 Cowls Doors - 78-31-00, P. Block 201 Thrust Reverser System



A. Job Set-Up (1)Position access platform (2)Open, safety and tag circuit breakers for the appropriate engine and open core cowl, fan cowl and thrust reverser doors (Ref. 71-13-00, P. Block 301). (3)On panel 59VU : - Make certain that APU Bleed Load Valve Control Switch (40HB) is in CLOSE position and install a warning notice to tell persons not to use it. - Make certain that X BLEED VALVE Control Switch (39HB) is in CLOSE position and install a warning notice to tell persons not to use it. (4)Make certain that a warning notice is installed on the HP GROUND connector to tell persons not to use it. WARNING : FOR ALL MAINTENANCE PROCEDURES INSIDE COWLS, EXTEND HOLD-OPEN _______ RODS TO HOLD COWLS OPEN. INADVERTENT CLOSURE OF COWLS COULD RESULT IN SERIOUS INJURY TO PERSONNEL.

B. Removal (1)Remove pneumatic check valve as follows : (a)Loosen clamp bolts, slide clamps (1), (2) and (3) off check valve (4). Release check valve (4). (b)Cap open tube ends.


D. Installation (1)Install pneumatic check valve as follows : (a)Remove cap from tube ends. (b)Install check valve between overpressure safety valve, compressor discharge pressure tube and pressure regulating and shut off valve. (c)Lubricate the inner surfaces on the ?V? clamps using material (C02-003). Install clamps (1), (3) on tube and valve mating flanges. TORQUE clamp locking bolts to between 70 and 80 lbf.in. (0.79 and 0.90 m.daN).R (d)Lubricate the inner surfaces of ?V? clamp using material (C02-004). Install spacer between flanges of pneumatic check valve and pressure regulating and shut-off valve (dimples taugs forward to pressure regulating valve), and clamp (2) ; TORQUE clamp locking nut between 70 and 80 lbf.in. (0.79 - 0.90 m.daN). Wirelock. CAUTION : SPACER MUST BE INSTALLED WITH THE FACES POSITIONED AS _______ SPECIFIED ON EACH FACE.

CAUTION : THE DIMPLES IN THE SPACER FIT WITHIN THE GROOVE ON THE _______ PRESSURE REGULATOR AND SHUTOFF VALVE FLANGE WHEN PROPERLY INSTALLED. A MAJOR LEAK WILL RESULT IF SPACER IS REVERSED. ______________________________________________

NOTE : Disregard the 70-80 lbf. in. (0.79-0.90 m.daN) torque ____


�� G E � � � � CF6 - 50 � ��

Pneumatic Check Valve Figure 201


�� G E � � � � CF6 - 50 � �� requirement marked on clamp (2) and apply the 90-100 lbf.in. (1.02-1.13 m.daN) torque as specified in the Installation text.

NOTE : Tap clamp and retorque, continue until no change is ____ noted in torque value.

E. Inspection/Check Visually inspect pneumatic check valve as follows : ----------------------------------------------------------------------------- INSPECTION/CHECK MAXIMUM SERVICEABLE LIMITS REMARKS ----------------------------------------------------------------------------- (1)Mating flanges for Any number 0.010 in. (0.25mm) Replace valve nicks, dents or deep not completely extending scratches across mating flange

(2)Housing for nicks, Any number not exceeding Replace valve dents or scratches 0.010 in. (0.25 mm)

(3)Thread damage 30 percent of one entrance Repair per thread or 10 percent damage paragraph F. on each of 2 entrance threads

F. Approved Repairs (1)Thread damage within serviceable limits may be repaired by blending with a fine file. Protect bare areas with Material C03-006.

G. Close-Up (1)Make certain that working area is clean and clear of tools and miscellaneous items of equipment. (2)Remove access platform (3)Remove safety clips and tags, close circuit breakers for the appropriate and close core cowl, fan cowl and thrust reverser doors (Ref. 71-13-00, P. Block 301). (4)Remove warning notices from panel 59VU and HP GROUND connector.

H. Test (1)Check for correct operation (Ref. 78-31-00, P. Block 201).


�� G E � � � � CF6 - 50 � �� BLEED AIR REGULATOR VALVE - MAINTENANCE PRACTICES _________________________________________________




B. Inspection/Check

C. Approved Repairs

2. Equipment and Materials _______________________ NOTE : Equivalent substitutes may be used instead of the following items. ____ ------------------------------------------------------------------------------- ITEM DESIGNATION -------------------------------------------------------------------------------R A. Material C03-006 Finishes and Protective CoatingsR (Ref. 20-32-00) B. Access Platform 2 m (6 ft. 7 in.) C. Torque Wrench. 270-300 lbf. in. (3.05 - 3.99 m.daN). D. Circuit Breaker Safety Clips E. Corrosion-Resistant Steel Lockwire, Dia. 0.032 in (0.813 mm) F. Blanking Plugs/Caps Referenced ProceduresR - 71-13-00, P. Block 301 Cowl Doors - 78-31-00, P. Block 201 Thrust Reverser System



A. Job Set-Up (1)Position access platformR (2)Open, safety and tag circuit breakers for the appropriate engine andR open fan cowl door (Ref. 71-13-00, P. Block 301) WARNING : FOR ALL MAINTENANCE PROCEDURES INSIDE COWLS, EXTEND HOLD- _______ OPEN RODS TO HOLD COWLS OPEN. INADVERTENT CLOSURE OF COWLS COULD RESULT IN SERIOUS INJURY TO PERSONNEL.

B. Removal (1)Remove bleed air regulator valve as follows : (a)Loosen regulator valve hex body (1) and release valve from switcher deploy tube.

C. Installation (1)Install bleed air regulator valve as follows : (a)Install regulator valve on switcher deploy tube. TORQUE valve hex body (1) to between 270 and 300 lbf.in. (22.5 and 25 lbf.ft.) (3.05 and 3.99 m.daN). Safety with 0.032 in. (0.813 mm) dia. corrosion-resistant steel lockwire. NOTE : Prior to installation, adjust the valve to a nominal position ____ by turning the adjusting nut clockwise against its stop and then backing it out approximately 3 turns.

D. Inspection/Check Visually check regulator valve as follows : --------------------------------------------------------------------- INSPECTION/CHECK | MAXIMUM SERVICEABLE LIMITS | REMARKS --------------------------------------------------------------------- (1)All areas for | None allowed | Replace cracks | | valve | | (2)Coupling nut for | 30 percent on one entrance | Repair per thread damage | thread or 10 percent on each of| paragraph E. | 2 entrance threads |

E. Approved Repairs (1)Thread damage within serviceable limits may be repaired by blending with a fine file. Protect bare areas with Material C03-006.

F. Close-Up (1)Make certain that working area is clean and clear of tools and miscellaneous items of equipment.R (2)Remove access platformsR (3)Remove safety clips and tags, and close circuit breakers for the appro-R priate engine and close fan cowl door (Ref. 71-13-00, P. BLock 301)

G. Tests WARNING : MAKE CERTAIN THAT ENGINE THRUST REVERSER MOVING PARTS ARE CLEAR _______ OF PERSONNEL AND MISCELLANEOUS ITEMS OF EQUIPMENT.


�� G E � � � � CF6 - 50 � ��

Bleed Air Regulator Valve Figure 201


�� G E � � � � CF6 - 50 � �� (1)Check thrust reverser system (Ref. 78-31-00, P. Block 201).


�� G E � � � � CF6 - 50 � �� NACELLE TEMPERATURE SENSOR - MAINTENANCE PRACTICES __________________________________________________



A. Removal/Installation.

B. Inspection/Check.

C. Test.

2. Equipment and Materials _______________________ ------------------------------------------------------------------------------- ITEM DESIGNATION ------------------------------------------------------------------------------- A. Circuit Breaker Safety Clips B. Torque Wrench 492-570 lbf.in. (5.55-6.44 m.daN) Referenced Procedure - 71-13-00, P. Block 301 Cowl Doors


�� G E � � � � CF6 - 50 � �� 3. Procedure _________

A. Job Set-UpR (1)Open, safety and tag circuit breakers for the appropriate engine andR open fan cowl, core cowl and thrust reverser doors. (Ref. 71-13-00,R P. Block 301) and open, safety and tag the following circuit breakers ------------------------------------------------------------------------------ PANEL SERVICE IDENT. LOCATION ------------------------------------------------------------------------------ 123VU ENG 1/OIL FUEL/FILTER/NACELLE/TEMP IND 1EB 303/B 1 123VU ENG 2/OIL FUEL/FILTER/NACELLE/TEMP IND 2EB 303/B11

B. Removal (Ref. Fig. 201 ) (1)Disconnect electrical connector. (2)Remove locknut ; release sensor from mounting bracket.

C. Installation (1)Position sensor in mounting bracket and install locknut ; TORQUE to between 492 and 570 lbf.in. (5.55 and 6.44 m.daN) (40 and 47.5 lbf.ft.). (2)Install electrical connector ; tighten fingertight and safety with 0.020 in. dia. (0.508 mm) corrosion-resistant steel lockwire.

Nacelle Temperature Sensor - Removal/Installation Figure 201


�� G E � � � � CF6 - 50 � �� 4. Inspection/Check ________________ Visually check nacelle temperature sensor as follows : ---------------------------------------------------------------------------- INSPECTION/CHECK MAXIMUM SERVICEABLE LIMITS REMARKS ---------------------------------------------------------------------------- A. Electrical connector for : (1)Insulator damage Not serviceable Replace sensor (cracks or chips) (2)Bent, broken or Not serviceable Replace sensor corroded pins (3)Distortion or out Not serviceable Replace sensor of round (4)Thread damage Total of one full thread Chase threads or may be missing after chasing replace sensor

B. Probe for : (1)Nicks, scratches Any number 0.005 in. (0.127 mm) Replace sensor or abrasions deep and 0.10 in. (2.54 mm) long (2)Cracks, splits or Not serviceable Replace sensor missing piece (3)Bends Not serviceable Do not attempt to straighten bent probes, replace sensor

C. Body for : (1)Cracks or distor- Not serviceable Replace sensor tion (2)Thread damage 30% on one entrance thread or 10% Blend repair damage on each of two entrance threads (3)Rounded corners Acceptable if torque can be Replace sensor of hex head applied (wrench surfaces)

D. Operational check Must meet requirements of para- Replace sensor graph 5


�� G E � � � � CF6 - 50 � �� 5. Electrical Tests ________________ Perform electrical tests in the following order :

A. Insulation Resistance Resistance between connector pins (A and B) and case shall be al least 50 megohms when measured with a 100 volt megger at room temperature.

B. Functional Resistance With the sensor immersed to the mounting thread base in an agitated liquid bath, measure resistance between connector A to B at 0 and 100• as shown in the following table. NOTE : If complete checkout of sensor is desired, check at all temperature ____ points listed. -------------------------------------------------------------------------- BATH TEMPERATURE (DEGREES CENTRIGRADE) RESISTANCE - OHMS TOLERANCE - OHMS -------------------------------------------------------------------------- 300 242.70 ±1.50 250 208.00 ±1.00 200 177.95 ±1.00 150 151.91 ±0.60 100 128.85 ±0.50 50 108.39 ±0.40 0 90.38 ±0.40 -20 83.77 ±0.40

Nacelle Temperature Sensor Electrical Tests Nacelle Temperature Sensor Electrical Tests

6. Close-Up ________

A. Make certain that working area is clean and clear of tools and miscellaneous items of equipment.

B. Remove safety clips and tags, close circuit breakers for the appropriate engine and close 1EB and 2EB and close fan cowl, core cowl and thrust reverser doors (Ref. 71-13-00, P. Block 301).


�� G E � � � � CF6 - 50 � �� NACELLE TEMPERATURE ELECTRICAL CABLE - MAINTENANCE PRACTICES ____________________________________________________________

WARNING : MAKE CERTAIN THAT CIRCUIT BREAKERS ARE OPEN, SAFETIED AND TAGGED AND _______ THAT AIR PRESSURE IS NOT APPLIED THROUGH GROUND CONNECTIONS, INADVER- TENT ENGINE START OR THRUST REVERSER OPERATION COULD RESULT IN DEATH OR SERIOUS INJURY TO PERSONNEL.



B. Inspection/Check

2. Equipment and Materials _______________________ ------------------------------------------------------------------------------- ITEM DESIGNATION ------------------------------------------------------------------------------- A. Circuit Breaker Safety Clips B. Torque Wrench - 12-27 lbf.in. (0.14 - 0.30 m.daN) Referenced Procedure - 71-13-00, P. Block 301 Cowl Doors


�� G E � � � � CF6 - 50 � �� 3. Procedure _________

A. Job Set-UpR (1)Open, safety and tag circuit breakers for the appropriate engine andR open fan cowl, core cowl and thrust reverser doors (Ref. 71-13-00,R P. Block 301) and open, safety and tag the following circuit breakers : ------------------------------------------------------------------------------ PANEL SERVICE IDENT. LOCATION ------------------------------------------------------------------------------ 123VU ENG 1 OIL FUEL/FILTER/NACELLE/TEMP 1EB 303/B 1 123VU ENG 2 OIL FUEL/FILTER/NACELLE/TEMP 2EB 303/B11R B. Removal (Ref. Fig. 201 ) (1)Disconnect electrical cable at : (a)Interface bracket. (b)Lower fire seal (c)Temperature sensor. (2)Remove clamps. (3)Slide cable forward through fire seal and remove.

C. Installation (1)Slide lower end of cable aft through lower fire seal (2)Connect cable at : (a)Temperature sensor ; tighten connector fingertight and safety with 0.020 in. dia. (0.508 mm) corrosion-resistant steel lockwire. (b)Lower fire seal and interface bracket; TORQUE screws and nuts to between 10 and 12 lbf.in. (0.11 and 0.13 m.daN) (c)Distribute cable evenly around clamping brackets and install clamps; TORQUE clamp bolts to between 24 and 27 lbf.in. (0.27 and 0.30 m.daN).


�� G E � � � � CF6 - 50 � ��

Nacelle Temperature Electrical Cable Routing Figure 201


�� G E � � � � CF6 - 50 � �� 4. Inspection/Check ________________ Visually check nacelle temperature electrical cable as follows : ----------------------------------------------------------------------------- INSPECTION/CHECK MAXIMUM SERVICEABLE LIMITS REMARKS ----------------------------------------------------------------------------- A. Metal braid for frayed None allowed Repair or broken strands (Ref. Fig. 202 )

B. Connectors for : (1)Thread damage 30% of one entrance Chase threads thread or 10% on each of if within limits or two entrance threads replace cable (2)Insulator damage Not serviceable Replace cable (cracks or chips) (3)Socket contact Not serviceable Replace cable damaged

C. Close-Up (1)Make certain that working area is clean and clear of tools and miscellaneous items of equipment.R (2)Remove safety clips and tags close circuit breakers for the appropriateR engine and close 1EB, 2EB and close fan cowl, core cowl and thrustR reverser doors (Ref. 71-13-00, P. Block 301).


�� G E � � � � CF6 - 50 � ��

Shielding Repair Figure 202


�� G E � � � � CF6 - 50 � �� THROTTLE INTERLOCK ACTUATOR - REMOVAL/INSTALLATION __________________________________________________

CAUTION : BEFORE ATTEMPTING REMOVAL/INSTALLATION PROCEDURES FOR THROTTLE INTER- _______ LOCK ACTUATOR, MAKE CERTAIN THROTTLE CONTROL LEVERS ARE IMMOBILIZED IN THE ?IDLE? POSITION. AS A SAFETY PRECAUTION DISPLAY WARNING NOTICES ON THROTTLE CONTROL LEVERS, FLAP CONTROL LEVER, PANEL 40VU AND APU CONTROL SWITCH (PANEL 59VU) TO PROHIBIT MANEUVERS. DISPLAY A WARNING NOTICE TO PROHIBIT THE USE OF THE GROUND HP AIR SUPPLY CONNECTIONS.

NOTE : Removal/installation procedures for LH and RH throttle interlock actua- ____ tors are identical.

1. Equipment and Materials _______________________ ------------------------------------------------------------------------------- ITEM DESIGNATION ------------------------------------------------------------------------------- A. Access Platforms 4.10 m (13 ft. 8 in.)

B. 290121-4 Test Set - Valve Actuating C. 98A27901022000 Tool-Locking, Flap and Slat Control Lever D. 98A27901023000 Tool-Locking, Throttle Control Lever E. Self-Locking Nuts F. O-Ring G. Cotter Pins H. Corrosion-Resistant Steel Lockwire, Dia. 0.032 in. (0.813 mm) I. Circuit Breaker Safety Clips J. Blanking Plugs/Caps

R **ON A/C 001-003, 102-102, 105-105,


A. Job Set-Up (1)Open, safety and tag circuit breakers for the appropriate engine (Ref. 71-13-00, P. Block 301). (2)Install locking tool (98A27901023000) on throttle control levers. (3)Install locking tool (98A27901022000) on flap and slat control lever in flight compartment. (4)Position access platforms at the upper part of engine pylons. (5)Open access doors 413FL, 414DR and 471AL on LH pylon or 423FL, 424DR and 481AL on RH pylon. (6)Remove the air supply duct between RIB8 and RIB10A and blank off both ends. (7)Install blanking plugs to the air supply ducts at RIB8 and RIB10A.


�� G E � � � � CF6 - 50 � ��

Control in Pylon - Lock Tool Location Figure 401

B. Removal (Ref. Fig. 403 ) (1)Disconnect pressurized air duct (11) at union (1). (2)Install blanking plugs to duct (11) and union (1). (3)Remove and discard cotter pin (6). (4)Disconnect and disengage link (4) from actuator (5) fork. (5)Unscrew self-locking nuts (10), remove both attachment bolts from support plate (8). Discard self-locking nuts. (6)Remove support plate (8) and actuator (5) assembly. Disengage support plate (8) correctly from guide (7) (7)Unscrew locknut (2). (8)Unscrew union (1), disconnect it from actuator (5). (9)Install a blanking plug to replace union (1). (10)Remove and discard 0-ring (3) from union (1). (11)Install a blanking plug to union (1). (12)Cut and remove lockwire (9). (13)Remove the four bolts attaching actuator (5) to support plate (8). (14)Disengage actuator (5). (15)If necessary, remove guide (7).

��R �EFFECTIVITY: 001-003, 102-102, 105-105, �� 78-31-51 � � � � Page 402 � � JAS Jul 01/89

�� G E � � � � CF6 - 50 � �� (a)Remove the three attachment bolts. (b)Disengage guide (7).

C. Installation NOTE : Check that the actuator which is to be installed is in the ?locked? ____ position. (1)Install guide (7). (2)Secure actuator (5) on support plate (8). (3)Safety the four bolts with 0.032 in. dia. (0.813 mm) corrosion-resistant steel lockwire. (4)Remove blanking plug from union (1) and blanking plug from actuator (5). (5)Install union (1) with new O-ring (3). (6)Install union (1) on actuator (5). (7)Tighten locknut (2) without locking it. (8)Engage support plate (8) with guide (7). (9)Secure support plate (8) to pylon structure. (10)Remove locking tool from throttle control levers.

(11)Set the relevant thrust reverser control lever to the Reverse Idle position. The stop on secondary transmission pulley is therefore in Reverse Idle locked position. (12)Make certain that the warning notice prohibiting any operation of the throttle control levers is still in place. (13)Place the bellcrank in contact with the secondary transmission pulley stop. (14)Adjust the length of link (4). (15)Insert link (4) end fitting correctly into actuator (5) fork. (16)Install link (4). (17)Safety nut with cotter pin. (18)Set thrust reverser control lever to the 0• position.

R **ON A/C 004-101, 103-104, 106-999,

2. Procedure _________ (Ref. 76-11-31, P. Block 401)

**ON A/C ALL

D. Test (1)Remove blanking plug from union (1). (2)Connect valve actuating test set (290121-4) to union (1). (3)Tighten locknut (2). (4)Apply a 2-bars (29 psi) pressure to the actuator and maintain this pressure. (5)Move thrust reverser control lever between Reverse Idle and Reverse Full Throttle positions. (6)Check, during these operations, that control moves smoothly. (7)Shut off air supply to actuator (5). (8)Drop pressure in actuator (5).


�� G E � � � � CF6 - 50 � �� (9)Set thrust reverser control lever to the 0• position. (10)Shut off and disconnect valve actuating test set. (11)Untighten locknut (2). (12)Remove blanking plug from duct (11). (13)Connect duct (11) to union (1). (14)Duct (11) will be tightened at union (1) without creating tension. (15)Tighten locknut (2).


�� G E � � � � CF6 - 50 � ��

Throttle Interlock Actuator - Location Figure 402


�� G E � � � � CF6 - 50 � ��

Throttle Interlock Actuator/Support Plate Assembly Figure 403


�� G E � � � � CF6 - 50 � �� E. Close-Up (1)Remove blanking plugs from pipes and air supply duct. (2)Install the air supply duct. (3)Make certain that working area is clean and clear of tools and miscellaneous items of equipment. (4)Close access doors. (5)Remove locking tool from flap and slat control lever. (6)Remove all warning notices prohiting maneuvers and operations. (7)Remove valve actuating test set. (8)Remove access platforms. (9)Remove safety clips and tags and close circuit breakers for the appropriate engine (Ref. 71-13-00, P. Block 301).


�� G E � � � � CF6 - 50 � �� OVERPRESSURE SAFETY VALVE ASSY - MAINTENANCE PRACTICES ______________________________________________________


1. Equipment and Materials _______________________ ------------------------------------------------------------------------------- ITEM DESIGNATION ------------------------------------------------------------------------------- A. Access Platform 3 m (10 ft.) B. Torque Wrench C. Circuit Breaker Safety Clips D. Blanking Plugs/Caps Referenced Procedures - 71-13-00, P. Block 301 Cowl Doors - 78-31-00, P. Block 201 Thrust Reverser System


�� G E � � � � CF6 - 50 � �� 2. Procedure _________ (Ref. Fig. 201 )

A. Job Set-Up (1)Position access platform.R (2)Open, safety and tag circuit breakers for the appropriate engine andR open fan cowl, core cowl and thrust reverser doors (Ref. 71-13-00,R P. Block 301).R WARNING : FOR ALL MAINTENANCE PROCEDURES INSIDE COWLS, EXTEND HOLD-OPEN _______ RODS TO HOLD COWLS OPEN. INADVERTENT CLOSURE OF COWLS COULD RESULT IN SERIOUS INJURY TO PERSONNEL.

B. Removal CAUTION : OVERPRESSURE SAFETY VALVE CAN ONLY BE MANUALLY RESET BY _______ ROTATING RESET KNOB COUNTERCLOCKWISE. VALVE CANNOT BE MANUALLY CLOSED USING HAND FORCE WITHOUT INTERNAL DAMAGE TO VALVE. (1)Loosen clamp bolts, slide clamps (1) and (3) off safety valve (2). Release safety valve (2). (2)Cap open tube ends.


D. Installation (1)Remove caps from tube ends. (2)Secure safety valve (2) with clamps (1) and (3). TORQUE nuts to the value given on clamps (1) and (3).

E. Close-Up (1)Make certain that working area is clean and clear of tools and miscellaneous items of equipment.R (2)Remove safety clips and tags, close circuit breakers for the appropriateR engine and close fan cowl, core cowl and thrust reverser doorsR (Ref. 71-13-00, P. Block 301).R (3)Remove access platform.

F. Tests WARNING : MAKE CERTAIN THAT ENGINE THRUST REVERSER MOVING PARTS ARE _______ CLEAR OF PERSONNEL AND MISCELLANEOUS ITEMS OF EQUIPMENT.

G. Check thrust reverser system (Ref. 78-31-00, P. Block 201).


�� G E � � � � CF6 - 50 � ��

Overpressure Safety Valve Assy Figure 201


�� G E � � � � CF6 - 50 � �� THRUST REVERSER ELECTRO-MECHANICAL BRAKE (TRAS LOCK) - ______________________________________________________ REMOVAL/INSTALLATION ____________________

1. Equipment and Materials _______________________ ------------------------------------------------------------------------------- ITEM DESIGNATION ------------------------------------------------------------------------------- A. Access Platform B. Torque Wrench 20-140 lbf.in. C. Circuit Breaker Safety Clips D. Warning Notice E. Splined Adapter 5/16 in. 12 point Drive Referenced Procedures - 71-13-00, P. Block 301 Cowl Doors - 78-30-00, P. Block 501 Thrust Reverser - 78-31-00, P. Block 201 Thrust Reverser System Control


A. Job Set-Up (1)Open, safety and tag circuit breakers for the applicable engine. (2)Open the fan cowl doors, and open the thrust reverser cowl doors (Ref. 71-13-00, P. Block 301). (3)Put the access platform in position. (4)In the flight compartment, display warning notices prohibiting operation of the throttle and thrust reverser control levers.

B. Removal (Ref. Fig. 401 ) (1)Manually release the disc brake on the pneumatic drive motor. (2)Manually release the TRAS lock. (a)Pull the T-handle approximately 0.35 inch (9 mm). (b)Remove the manual release lever for the retaining clip, and return the lever to engage the collar. (c)Release the T-handle. (3)Disconnect the two flexible assemblies from the TRAS lock. (4)Disconnect the electrical cable from the TRAS lock solenoid electrical connector. (5)Disconnect the TRAS lock cable. (a)Remove the screw and the p-clamp from the mount tower support bracket. (b)Disconnect the TRAS lock cable from the electrical cable mounting bracket. (6)Disconnect the pneumatic supply tube and the pneumatic return tube from the TRAS lock. (7)Remove the retaining clips and trunion pins from the mount tower (Ref. Fig. 402 ). (8)Rotate the gearbox input drive approximately 10 revolutions to move the actuator gearbox away from the actuator support. (9)Remove the two screws that attach the TRAS lock bracket to the center ballscrew gearbox actuator. Keep the screws and washers for use at installation.


�� G E � � � � CF6 - 50 � �� (10)Remove the four bolts and four washers that attach the TRAS lock to the adapter plate. Keep the bolts and washers for use at installation. NOTE : The TRAS lock and bracket are now detached and can be removed ____ from the reverser. (11)Remove the four bolts and four washers that attach the adapter plate to the ballscrew gearbox assembly. Keep the bolts and the washers for use at installation. (12)Attach the adapter plate to the TRAS lock using the four bolts and washers removed in the step above.

C. Installation (Ref. Fig. 401 ) (1)If it is necessary, rotate the gearbox input drive approximately 10 revolutions to move the actuator gearbox away from the actuator support. (2)Install the brake assembly. (a)If installed, remove the adapter plate and the TRAS lock bracket from the TRAS lock. (b)Install the adapter plate on the center ballscrew gearbox assembly with four bolts and four washers and TORQUE the bolts to between 50 and 55 lbf.in. (0.57 and 0.62 m.daN). (c)Install the TRAS lock bracket to the center ballscrew gearbox actuator with two screws. Tighten the screws hand-tight. (d)Put the square drive of the TRAS lock into the center ballscrew gearbox assembly. (e)Attach the TRAS lock to the adapter plate with four bolts and four washers and TORQUE the bolts to between 50 and 55 lbf.in. (057 and 0.62 m.daN). (f)Attach the TRAS lock to the TRAS lock bracket with two bolts. Use shims as necessary between the TRAS lock and the bracket for a tight fit. TORQUE the bolts to between 110 and 120 lbf.in. (1.24 and 1.36 m.dan). (g)TORQUE the screws installed in step (c) above to between 110 and 120 lbf.in. (1.24 and 1.36 m.daN). (3)Turn the gearbox input drive approximately 10 revolutions toward the actuator support. (4)Align the gearbox trunion mounting holes with the mount tower clevis and insert the trunions pins (Ref. Fig. 402 ). (5)Install the retaining clips (Ref. Fig. 402 ). (a)Attach the clips with the washers and bolts. (b)Install the washers between the clips and the mount tower. (c)TORQUE the bolts to between 24 and 27 lbf.in. (0.27 and 0.31 m.daN). (6)Attach TRAS lock pneumatic tubes. (a)Attach the pneumatic return tube to the port identified as ?RETURN? on the TRAS lock and TORQUE to between 135 and 155 lbf.in. (1.53 and 1.75 m.daN). (b)Attach the pneumatic supply tube to the port identified as ?SUPPLY? on the TRAS lock and TORQUE to between 270 and 300 lbf.in. (3.05 and 3.39 m.daN). (7)Connect the TRAS lock cable. (a)Connect the TRAS lock cable to the electrical cable mounting bracket. (b)Use the screw and P-clamp to attach the TRAS lock cable to the mount tower support bracket at the nutplate. TORQUE the screw to between


�� G E � � � � CF6 - 50 � �� 33 and 37 lbf.in. (0.37 and 0.42 m.daN). (8)Attach the electrical cable to the TRAS lock solenoid electrical connector. (9)Adjust the thrust reverser flexible shaft assemblies (Ref. 78-30-00, P. Block 501). (10)Connect the two flexible shaft assemblies to the TRAS lock.

D. Test (1)Do the TRAS lock brake torque check (Ref. 78-30-00, P. Block 501).

E. Close-up (1)Make certain that the working area is clean and clear of tools and miscellaneous items of equipment. (2)Remove the access platform. (3)Remove safety and tags and close the applicable circuit breaker. (4)Close the fan cowl doors (Ref. 71-13-00, P. Block 301).


�� G E � � � � CF6 - 50 � ��

TRAS Lock Installation (Sheet 1/2) Figure 401


�� G E � � � � CF6 - 50 � ��

TRAS Lock Installation (Sheet 2/2) Figure 401


�� G E � � � � CF6 - 50 � ��

Center Gearbox/Actuator Mount Tower Figure 402


�� G E � � � � CF6 - 50 � �� THRUST REVERSER TRAS LOCK AND SWITCHER VALVE - ______________________________________________ REMOVAL/INSTALLATION ____________________

1. Equipment and Materials _______________________ ------------------------------------------------------------------------------- ITEM DESIGNATION ------------------------------------------------------------------------------- A. Access Platform B. Torque Wrench 100-200 lbf.in. C. Circuit Breaker Safety Clips D. Warning Notice Referenced Procedures - 71-13-00, P. Block 301 Cowl Doors - 78-31-00, P. Block 201 Thrust Reverser System Control


A. Job Set-Up (1)Open, safety and tag required circuit breakers for the appropriate engine and open the right hand fan cowl doors and partially open the thrust reverser cowl doors for the right hand thrust reverser half (Ref. 71-13-00, P. Block 301). (2)Put the access platform in position. (3)In the flight compartment, display warning notices prohibiting operation of the throttle and thrust reverser control levers.

B. Removal (Ref. Fig. 401 ) (1)Disconnect the three pneumatic tubes from the top of the switcher valve. (2)Disconnect the pneumatic return tube from the bottom of the switcher valve. (3)Remove the four bolts and four washers that attach the switcher valve to the two support brackets. Keep the bolts and washers for use at installation. (4)Remove the switcher valve. (5)If it is necessary, disconnect the flexshaft from the TRAS lock.

C. Installation (Ref. Fig. 401 ) (1)Attach the switcher valve to the two support brackets with the four bolts and four washers removed in step B.(3). (2)Connect the pneumatic return tube to the bottom of the switcher valve and TORQUE to between 135 and 155 lbf.in. (1.53 and 1.75 m.daN). (3)Connect the three pneumatic tubes to the top of the switcher valve and TORQUE to between 135 and 155 lbf.in. (1.53 and 1.75 m.daN).

D. Test (1)Do the Thrust Reverser Functional Test (Ref. 78-31-00, P. Block 201).

E. Close-up (1)Make certain that the working area is clean and clear of tools and miscellaneous items of equipment.


�� G E � � � � CF6 - 50 � �� (2)Remove the access platform. (3)Remove safety and tags and close the applicable circuit breaker. (4)Close the thrust reverser cowl doors and the fan cowl door (Ref. 71-13-00, P. Block 301).


�� G E � � � � CF6 - 50 � ��

Dual Switcher Valve Figure 401


�� G E � � � � CF6 - 50 � �� FAN THRUST REVERSER TRAS LOCK AND SWITCHER VALVE - __________________________________________________ INSPECTION/CHECK ________________

1. General _______ The TRAS Lock Assembly and the Dual Switcher Valve may be inspected while installed or removed. The TRAS Lock Assembly and the Dual Switcher Valve may be inspected with the fan thrust reverser cowls closed.

2. Equipment and Materials _______________________ ------------------------------------------------------------------------------- ITEM DESIGNATION ------------------------------------------------------------------------------- A. Access Platform 2 m (6 ft. 7 in.) B. Circuit Breaker Safety Clips Referenced Procedures - 71-13-00, P. Block 301 Cowl Doors - 78-31-00, P. Block 201 Thrust Reverser System Control - 78-31-53, P. Block 401 Thrust Reverser Electro-Mechanical Brake (TRAS Lock) - 78-31-54, P. Block 401 Dual Switcher Valve


A. Job Set-Up (1)Open, safety and tag circuit breakers for the appropriate engine and open the fan cowl doors (Ref. 71-13-00, P. Block 301).

B. Inspection/Check of the TRAS Lock Assembly and the Dual Switcher Valve: (Ref. Fig. 601 ) -------------------------------------------------------------------------------- INSPECT/CHECK MAXIMUM SERVICEABLE LIMITS REMARKS -------------------------------------------------------------------------------- (1)TRAS Lock Assembly for:

(a)Loose electrical Not serviceable Tighten connectors

(b)Loose flex shaft Not serviceable Tighten (Ref. 78-31-00, connections P. Block 201)

(c)Loose mounting Not serviceable Tighten (Ref. 78-31-53, hardware P. Block 401)

(d)Loose pneumatic Not serviceable Tighten (Ref. 78-31-53, tubes P. Block 401)

(e)Cracks in the TRAS Not serviceable Replace the TRAS lock Lock Assembly (Ref. 78-31-53, casting P. Block 401)


�� G E � � � � CF6 - 50 � �� -------------------------------------------------------------------------------- INSPECT/CHECK MAXIMUM SERVICEABLE LIMITS REMARKS --------------------------------------------------------------------------------

(2)Dual Switcher Valve

(a)Loose mounting Not serviceable Tighten (Ref. 78-31-54, hardware P. Block 401)

(b)Loose pneumatic Not serviceable Tighten (Ref. 78-31-54, tubes P. Block 401)

(c)Cracks in the Not serviceable Replace the switcher switcher valve valve (Ref. 78-31-54, casting P. Block 401)

C. Close-Up (1)Make sure that the work area is clean and clear of tools and miscellaneous items of equipment. (2)Remove the safety clips and tags, close circuit breakers for the applicable engine and close the fan cowl doors (Ref. 71-13-00, P. Block 301). (3)Remove the access platform.


�� G E � � � � CF6 - 50 � ��

TRAS Lock and Switcher Valve (Sheet 1/2) Figure 601


�� G E � � � � CF6 - 50 � ��

TRAS Lock and Switcher Valve (Sheet 2/2) Figure 601


�� G E � � � � CF6 - 50 � �� FAN REVERSER ASSEMBLY - DESCRIPTION AND OPERATION _________________________________________________

1. General _______ The fan reverser assembly is located directly aft of the fan frame. The reverser consists of the translating aft section of the fan cowl, hinged blocker doors, and fixed vaned deflectors. Six ball-screw actuators operate the fan reverser. In forward thrust configuration, the translating fan cowl is in the forward, stowed position covering the outer surface of the vaned deflectors. The blocker doors are faired into the outer fan duct wall so that they cover the inner surface of the deflectors. In reverse thrust configuration, the translating cowl is moved aft to expose the deflectors, while the blocker doors rotate inward against the inner wall of the fan air duct. Normal fan airflow is thus blocked and diverted through the deflectors.

2. Component Location __________________ (Ref. Fig. 001 ) ------------------------------------------------------------------------------ ITEM NAME PANEL ZONE ACCESS DOOR ------------------------------------------------------------------------------ 1 Latch Assembly - RH Cowl 452 436AR 462 446AR 3 Vaned Deflector Assembly, RH Side 452 452AR 462 462AR 5 Blocker Doors, RH Side (6 Elements) 452 452AR 462 462AR 7 Translating cowl, RH Side 452 452AR 462 462AR 9 Translating Cowl, LH Side 451 451AL 461 461AL 11 Vaned Deflector Assembly, LH Side 451 451AL 461 461AL 13 Air Temperatore Sensor (Ref. 75-41-11) 451 451CL 461 461CL 15 Blocker Doors, LH Side (6 Elements) 451 451AL 461 461AL 17 Support Assembly - Fan Reverser, LH Side 451 451AL 461 461AL 19 Latch Assembly, LH Cowl 451 435AL 461 445AL 21 Link Assembly - Blocker Doors, RH 452 452AR Side 462 462AR 23 Support Assembly - Fan Reverser, RH 452 452AR Side 462 462AR 25 link Assembly - Blocker Doors, LH 451 451AL Side 461 461AL 27 Access Door (451DL) (461DL) 451 461 29 Access and Blowout Door (451CL) (461CL) 451 31 Access Door (451BL) (461BL) 451 461


�� G E � � � � CF6 - 50 � ��

Fan Thrust Reverser - Component Location Figure 001


�� G E � � � � CF6 - 50 � �� 3. Description (Ref. Fig. 002 ) ___________ NOTE : Refer to 71-13-03, P. Block 401 for Removal/Installation. ____ CAUTION : BEFORE OPENING FAN THRUST REVERSER COWLS, IT IS IMPERATIVE _______ TO OPEN FAN AND CORE COWLS. BEFORE OPENING ACCESS DOORS 451BL AND 451DL (461BL AND 461DL), IT IS IMPERATIVE TO OPEN PRESSURE RELIEF DOOR 451CL (461CL). The fan reverser components are as follows : A. The Support Assembly (Fixed Structure) The support assembly on each side of the reverser consists of upper and lower end beams, which support the inner flow path structure and tee-hinge guides for the translating cowl assembly. Hinge brackets are attached to the upper end beam to support the reverser section from the aircraft pylon. Quick disconnect flanges are provided at the forward edge of the inner and outer flow paths. The lower end beams of the two sections are connected with latches.

B. Blocker Doors There are twelve (six in each half) blocker doors hinged at their leading edge to an extruded torque ring at the leading edge of the translating cowl. Forces applied to the blocker doors when the reverser is deployed are transmitted through the translating cowl structure to the actuators at the outer edge and through the link assemblies to the support assembly inner cowl at the inner edge. The blocker doors are constructed of acoustic panels. Clevis castings are fitted into each blocker door attachment of the actuation links. There are five different shaped blocker doors. Two doors on either side of the pylons are right and left handed and the remaining ones are identical.

C. Translating Cowl The translating cowl provides the outer contour as well as the outer wall of the fan discharge nozzle and consists of a combination of aluminum faced honeycomb and fiberglass sound suppression structure. The cavity between the inner and outer surfaces provides space for the thrust deflectors. The outer surface of the inner cavity is equipped with low friction support guide blocks. The inner surface of the cavity has tee- hinges on the edges to transmit hoop forces to the guides in the support assembly. The assembly also incorporates an extruded torque ring to which the twenty- four blocker door hinge fittings are attached. The inner surface of the translating cowl has pockets into which the blocker doors are recessed to form a smooth airflow surface when the fan reverser is in the stowed position.

D. Blocker Door Link Assemblies Each blocker door is actuated by a set of linkage and pin components. The Blocker door links are overcentered in the stowed position and are actuated by the deployment of the reverser translating cowls. The links are attached to the blocker doors at their outer ends. The inner ends of the links are mounted into recesses in the inner flow path surface of the support assembly. Springs apply a force approximalely 100 pounds to each


�� G E � � � � CF6 - 50 � �� blocker door while in the stowed position to prevent fretting and wear.


�� G E � � � � CF6 - 50 � ��

Fan Reverser Figure 002


�� G E � � � � CF6 - 50 � �� FAN REVERSER ASSEMBLY - INSPECTION/CHECK ________________________________________

1. General _______ The fan reverser assembly may be inspected while installed or removed. A spot fluorescent penetrant check should be used to confirm suspected cracks. WARNING : IF THE FAN THRUST REVERSER COWLS ARE INSTALLED ON AIRCRAFT, MAKE _______ CERTAIN THAT CIRCUIT BREAKERS ARE OPEN, SAFETIED AND TAGGED AND THAT AIR PRESSURE IS NOT APPLIED THROUGH GROUND CONNECTIONS BEFORE ATTEMPTING INSPECTION/CHECK. INADVERTENT ENGINE START OR THRUST REVERSER OPERATION COULD RESULT IN DEATH OR SERIOUS INJURY TO PERSONNEL. CAUTION : BEFORE OPENING FAN THRUST REVERSER COWLS, IT IS IMPERATIVE TO OPEN _______ FAN AND CORE COWLS. (REF.71-13-00, P. BLOCK 301). WARNING : FOR ALL INSPECTION/CHECK INSIDE COWLS, EXTEND HOLD-OPEN RODS TO _______ HOLD COWLS OPEN. INADVERTENT CLOSURE OF COWLS COULD RESULT IN SERIOUS INJURY TO PERSONNEL.

2. Equipment and Materials _______________________ ------------------------------------------------------------------------------- ITEM DESIGNATION ------------------------------------------------------------------------------- A. Material C01-007 Adhesives (Ref. 20-32-00) B. Material C01-062 Sealants (Ref. 20-32-00)R C. Material C02-004 Lubricants (Ref. 20-32-00)R D. Material C03-004 Finishes and Protective Coatings (Ref.20-32-00)R E. Material C03-006 Finishes and Protective Coatings (Ref.20-32-00)R F. Material C03-010 Finishes and Protective Coatings (Ref.20-32-00)R G. Access Platform 2 m (6 ft. 7 in.)R H. Circuit Breaker Safety Clips Referenced Procedures - 71-13-00, P. Block 301 Opening of Cowls - 78-32-00, P. Block 801 Fan Reverser Assembly - 78-00-00, P. Block 401 Thrust Reversers-Deactivation


�� G E � � � � CF6 - 50 � �� 3. Procedure _________

A. Job Set-Up (1)Open, safety and tag circuit breakers for the appropriate engine and open fan cowl, core cowl and thrust reverser doors (Ref. 71-13-00, P. Block 301).

B. Inspection/Check of the Following Areas : (Ref. Fig. 601, 602 and 603) (Ref. Fig. 604, 605 and 606)R (Ref. Fig. 607 ) ------------------------------------------------------------------------------- INSPECTION/CHECK MAXIMUM SERVICEABLE LIMITS REMARKS ------------------------------------------------------------------------------- (1)Translating cowl for :

(a)Cracks in honey Two in.(50.8 mm) max. length, Replace translating comb or sheet total accumulation of 12 in. cowl. metal (305 mm). Cracks must be Stop drill cracks separated by one in.(25.4 mm) 0.5 in. (12.7 mm) or longer

(b)Cracks in sheet Two in. (50.8 mm) max. lenght, Replace translating metal other than total accumulation of 12 in. cowl. Stop drill near beaver tail (304.8 mm). Cracks must be cracks 0.5 in. separated by one in. (25.4 mm). (12.7 mm) or longer

(c)Cracks in sheet Not serviceable Replace translating metal near beaver cowl tail in area of ?U? channel, with delamination

(d)Cracks in sheet Up to two in. (50.8 mm) max Check every 75 metal near beaver length cycles tail in area of ?U? channel,without delamination

(e)Cracks in sheet Over two in. (50.8 mm). Replace translating metal near beaver cowl tail in area of ?U? channel, with/ without delamination

(f)Cracks in ?U? Up to five in. (127.0 mm). Replace translating channel only cowl

(g)Holes in honeycomb One in. (25.4 mm) max. Dia. Replace translating one side only. Maximum of cowl.


�� G E � � � � CF6 - 50 � ��

Translating Cowl Inspection AreasR Figure 601


�� G E � � � � CF6 - 50 � ��

Translating Cowl (Inner/Outer Bondments)R Figure 602


�� G E � � � � CF6 - 50 � ��

Fan Reverser ComponentsR Figure 603


�� G E � � � � CF6 - 50 � ��

Right Side Feedback System Rigging Check Figure 604

eight holes separated by by one in. (25.4 mm).

R (h)Dents or buckles 0.25 in.(6.35 mm) max. depth. These limits can beR Up to 3 in. (76.2 mm) dia. extended if the dentR Max of 12 dents separated by is seen as aR one in. delamination andR conforms to theR limits given inR step (s)R Delamination.R Otherwise, replaceR the translatingR cowl.

(i)?T?-hinge teflon wear strips for : 1 Wear Wear through must not extend Replace translating _ into metal more than 0.030 in. cowl.


�� G E � � � � CF6 - 50 � ��

R/H and L/H Cam Follower Lobe DimensionsR Figure 605


�� G E � � � � CF6 - 50 � ��

Left Side Feedback System Rigging Check Figure 606

(0.76 mm) or a length exceeding 6 in. (152.4 mm).

2 Missing Not to exceed 6 in. (152.4 mm) Replace translating _ in length on two non-adjacent cowl. faces. Areas must be separated by 12 in. (304.8 mm) minimum. NOTE : ?T? hinge with teflon missing is excess of above limits up to and ____ including total absence of wear strips, may remain in service forR a maximum of fifty (50) flight hours provided the fan reverser isR deactivated (Ref. 78-00-00, P. Block 401).

3 Lifting and/or Two non-adjacent areas per Remove any free _ separation from hinge, separated by 12 in. teflon up to 6 in. hinge (304.8 mm) minimum and not (152.4 mm) max. on the same face, provided length. there is no detached/free end. Replace translating cowl.


�� G E � � � � CF6 - 50 � ��

Fan Reverser Inspection/Check (Sheet 1/2)R Figure 607


�� G E � � � � CF6 - 50 � ��

Fan Reverser Inspection/Check (Sheet 2/2)R Figure 607


�� G E � � � � CF6 - 50 � �� (j)Cracks in hinge 6 consecutive lugs may be Replace translating tracks cracked cowl 8 cracked lugs total per assembly (Hinge and Blade)

(k)?T? hinge (?T? 0.025 in. (0.64 mm) Replace translating portion) for air max depth cowl seal wear

(l)?T? hinge 0.30 in. (7.6 mm) transversely Replace ?T? hinge straightness 0.055 in. (1.40 mm) axially

(m)Wear on tension 0.06 in.(1.52 mm) max. depth Replace bumper bumper assemblies

(n)Cracks on tension Not serviceable Replace bumper bumper assemblies

(o)Lock bumper 0.020 in. (0.51 mm) min. gap Shim bumper as assembly radial must exist between outer side required to clearance with of bumper and support assembly achieve gap. support assembly with cowl in stowed position

(p)Cracks in blocker Not serviceable Replace clevis door clevis

(q)Missing rivets 11 percent may be missing Replace rivet as long as missing rivet is separated by four good rivets. End rivets may not be missing

R (r)Bulb seal damage :R 1 Radial cuts, Up to 5 cuts, splits, or tears Over 5 cuts, _R splits, or tears for each fan reverser half splits, or tears :R (5 total cuts, splits, or tears replace one or moreR for each four seal segments) seal segments untilR the total number ofR cuts, splits,R and/or tears forR each fan reverserR half is 5 or less ;R or, deactivate theR fan reverser

R 2 Circumferential Not serviceable Replace the seal _R cuts, splits, or segment orR tears deactivate the fanR reverser. An over-R serviceable-limitR extension of 100


�� G E � � � � CF6 - 50 � ��R flight hours isR permitted if totalR circumferentialR damage is less thanR 5.0 in. (127 mm)R for eachR translating cowl

R 3 Nicks that do Any amount up to a Replace the _R not go through maximum length or width applicable sealR the seal of 0.25 in. (6.35 mm) segment(s) orR if separated by 5 in. deactivate the fanR (127 mm) circumferentially reverser

R 4 Punctures and No visible holes or punctures Replace the _R pin holes that through the seal applicable sealR go through the segment(s) orR seal deactivate the fanR reverser

R 5 Missing Not serviceable Replace the _R sections missing sealR segment(s) orR deactivate the fanR reverser (s)Delamination (Ref. Fig. 602 )

1 Forward Outer Unbonded skin area not to Replace translating _ Bondment exceed 100 sq. in. (645 cm²) cowl

2 Aft Outer Bondment _

- Area of concern The maximum allowable defect Replace translating surrounding size is 2 in. (51 mm) in the cowl Actuator Clevis axial direction and 6 in. Area ?A? (152 mm) circumferential. This is a total of 12 sq.in. (77 cm²) and is the maximum allowable size within area ?A?.

- Area of concern The maximum allowable defect Replace translating adjacent to size is 10 in. (254 mm) in the cowl Close-Out axial direction and 2 in. Castings (51 mm) circumferential. Area ?B? This is a total of 20 sq.in. (129 cm²) and is the maximum allowable size within area ?B?.


�� G E � � � � CF6 - 50 � �� - All other areas Unbonded skin area not to Replace translating exceed 100 sq. in. (645 cm²). cowl

3 Forward Inner Unbonded skin area not to exceed Replace translating _ bondment 6 sq. in. (38.7 cm²) cowl Axial length not to exceed 1 in. (25.4 mm)

(t)Rigging 0.06 to 0.150 in.(1.5 to Re-rig 3.8 mm) gap between support per repair and cowl at center actuator section or no reflective tape showing

(u)Upper and lower No rivets or bolts missing. Replace translating cowl guide bracket No cracks in bracket or skin cowl. for security allowed.

(v)Corrosion on the Corrosion not to exceed Repair the forward flange 90 in. (2286 mm) forward flange cumulative length. (Ref. 78-32-00, No more than 24 in. P. Block 801) if the (610 mm) in length and limits are 0.020 in. (0.51 mm) deep exceeded. separated by 6.0 in. (152 mm) of non-corroded material. No more than 12 in. (305 mm) in length and 0.040 in. (1.02 mm) deep separated by 6 in. (152 mm) of non-corroded material.

(w)Corrosion on the 50 sq.in. (323 cm²) Repair the sheet metal of cumulative area up to torque box the torque box 0.021 in. (0.53 mm) (Ref. 78-32-00, remaining thickness. P. Block 801) Maximum depth of corrosion if the limits are 0.029 in. (0.74 mm). Any exceeded. amount up to 0.010 in. (0.25 mm) deep.

(x)Corrosion on the Any amount up to 0.020 in. Repair the upper upper splice (0.51 mm) deep. splice plate or plate replace (Ref. 78-32-00, P. Block 801) if the limits are exceeded.

(2)Sound panels for :


�� G E � � � � CF6 - 50 � �� (a)Cracks Two in.(50.8 mm) max. length, Replace panel total accumulation of 12 in.(304.8 mm). Cracks must be separated by one in. (25.4 mm)

(b)Holes Two in.(50.8 mm) max. Dia. Replace panel one side only. Maximum of four holes separated by one in. (25.4 mm).

(c)Delamination Two square in.(12.9 cm²) max. Replace panel area. Maximum of four areas separated by one in. (25.4 mm).

(d)Missing urethane Maximum of twelve square Replace panel coating inches (77.4 cm²) per panel may be missing

(e)Blisters or sur- Two square inches (12.9 cm²) Replace panel face voids area max. Four per panel

(f)Cording (bunching Any amount providing no Fillet in leading up of leading delamination is present edge of panel edge between with sealant screws) (C01-062)

(g)Loose panel Any number provided no Apply Material washers elongation of hole in (C01-062) panel is evident under washer

(3)Support assembly for :

(a)Cracks in honey- Two in.(50.8 mm) max. length, Replace reverser comb or sheet total accumulation of half. Stop metal 12 in.(305 mm). Cracks drill cracks must be separated by one 0.5 in. (12.7 in. (25.4 mm). mm) or longer

(b)Holes in honey- One in.(25.4 mm) max. Dia., Replace reverser comb one side only. Maximum of half. eight holes separated by one in. (25.4 mm).

(c)Delamination Not serviceable Replace reverser of core cowl half inner skin Check ducts for hot air leakage

(d)Cracks at for- One crack per hole, Replace reverser ward flange 4 holes max. half


�� G E � � � � CF6 - 50 � �� bolts holes Cracked holes must be separated by one good hole

(e)Cracks in for- 0.5 in.(12.7 mm) max. length. Replace reverser ward flange Total accumulation of half. four in.(101.6 mm). Cracks must be separated by one in.(25.4 mm)

(f)Forward flange None allowed Replace reverser for distortion half.

(g)Broken cooling One broken bracket per Replace bracket tube support reverser half permitted brackets

(h)Honeycomb dents 0.25 in.(6.35 mm) max. depth Repair dents.

(i)Buckles in honey- None allowed Repair buckles comb

(j)Torn or missing Sealing surface must be Replace seal seals 90 % effective.

(k)Cracks in pre- None allowed in seal Replace reverser cooler duct and spring leafs. In other half manifolds areas, 1 in.(25.4 mm) max. length. Total accumulation of 4 in.(101.6 mm)

(l)Torn, missing or Tear up to 2 in.(50.8 mm) Trim and fill holes in fairing long. Up to two square in with silico- at upper/lower inches (12.9 cm²) may be cone rubber RTV inner flow path. missing 106 (C01-007) or equivalent.

(m)Missing urethane 50 percent may be missing Replace reverser coating on fairing ser half

(n)Missing rivets 10 percent may be missing Replace rivet as long as missing rivet is separated by four good rivets

(o)Wear strips. 1 Aft end - core 0.03 in. (0.8 mm) max Replace reverser _ cowling to fan depth. half reverser support structure


�� G E � � � � CF6 - 50 � �� 2 Fwd end - fan Any amount of wear provided Replace wear strip _ cowling to fan no metal to metal exists ; reverser for any amount of bulge provided wear/bulging. no slippage of strip occurs.

(p)Core cowl sidewall Maximum area of 1 sq. Areas up to 4 or precooler duct in.(6.451 cm²) or area not sq. in. coating for peel- exceeding in average width (25.8 cm²) area ling, cracking, of 1/4 in.(6.35 mm) length not exceeding chipping or mis- of 12 in.(305 mm). Max. an average sing of 15 areas per reverser width of 1 in. half. Max. of 3 areas in (25.4 mm) or any 1 sq. foot (929 cm²) total length area of 12 in. (305 mm) to be repaired with silicone rubber RTV 106 (C01-007) Total area not to exceed 200 sq. in. (1290.3 cm²) reverser half.

(q)Intumescent fireproof coating for : 1 Top coat Any amount. Any amount may _ (Flame be repaired Control) (Ref. 78-32-00 (C03-024) P. Block 801.)

R 2 Fire proof Any amount of damaged or All uncoated areas _R coating missing coating, 1/8 in. may be repairedR peeling, (3.2 mm) maximum width at the (Ref. 78-32-00,R cracking outer surface, 1/16 in. P. Block 801)R chipping or (1.6 mm) maximum width at theR missing inner surface (bare metal),R any length, separated byR 1.0 in. (25.4 mm).R Any amount of damaged orR missing coating up to 1/4 in.R (6.4 mm) diameter separatedR by 1.0 in. (25.4 mm).

3 Fire proof Any munber of tears in outer Any amount may _ blankets for face sheet, 1/4 in. (6.4 mm) be repaired tears, punc- max. witdth, any length when only the face tures loose separated by 1 in (25.4 mm). sheet is torn. Re-


�� G E � � � � CF6 - 50 � �� sections, No bare metal showing. place blanket when separation 1/2 in (12.7 mm) diameter torn through and at overlaps area of face sheet with no bare metal is expo- bare metal exposed. sed.

(r)Chipped Any amount Touch up with or missing paint Alodine 1200 in other areas (C03-006) or exposy resin primer

(s)Loose brackets Not serviceable Tighten fasteners or replace brackets

(t)Deflection Any amount as long as Reform or re- limiter support contact exists between place bracket. brackets deformed, limiter and mating bent or buckled surface.

(u)Upper hinges and lower latch housings for :

1 Cracks Not serviceable Replace reverser _ half

2 Bolt wear 0.03 in.(0.76 mm) max. Replace reverser _ half

(v)Grooves in radial May be worn radially Replace or re- fire seal channel through channel side- position engine wall. Max. depth 0.025 radial fire in.(0.635 mm) for circum- shield wear ferential grooves blocks or replace reverser half

(w)Core cowl and Local rub through permitted : If damage within core cowl fairing maximum crack, dent or rub limits, trim for cracks, dents through not to exceed 2 in. blocker doors or rub marks from (50.8 mm) to provide 0.20 contact with 0.30 in. (5.08- blocker doors 7.62 mm) clearance maintaining a minimum of 0.30 in. (7.6 mm) wide bonded flat area on blocker door. Segment or the entire fairing may be replaced or


�� G E � � � � CF6 - 50 � �� cracks filled with filler material (C01-007). Apply corrosion protection Material C03-010 to cowl

(x)Precooler duct for Not serviceable Repair (Ref. pulled or missing P. Block bolts 801 Para 3.F)

(y)Lower sidewall Up to entire height Check ducts for delamination radially by 10 in. (254 mm) hot air leakage. axially. Replace reverser

(z)Upper sidewall Up to entire height radially Check ducts for delamination by 10 in. (254 mm) axially at hot air leakage. undoubled areas. None allowed Replace reverser in doubled areas adjacent to hinges and P.O. actuator mount bracket. (Ref. Fig. 608 ) (aa)Recoup duct ?Kiss? Seal for 1 Wear Any amount provided no Replace seal _ air leakage is evident with SPAD

2 Missing Not serviceable Replace seal _ with SPAD

(ab)Lower duct -Any amount. Repair per sidewall fwd -Not serviceable if approved and aft wear worn through in any repairs para. 20 strip wear area.

(4)Lower latches for :

(a)Housing cracks Not serviceable Replace reverser

(b)Fretting on latch Not serviceable if felt Replace latch hook contact with 0.030 in.(0.76 mm) areas radius scribe

(c)Missing lubricant Not serviceable if metal Lubricate with in latch hook visible through coating (C02-004) contact areas

(d)Latch pin Not serviceable if felt with Replace pin fretting a 0.030 in.(0.76 mm) radius scribe


�� G E � � � � CF6 - 50 � ��

Support Assembly Upper Sidewall Doubled/Undoubled AreasR Figure 608


�� G E � � � � CF6 - 50 � �� (e)Latch pin wear Max. wear 0.002 in. (0.05 mm) Replace pin Fwd. and mid latch mounting pin : min. dia. 0.495 in. (12.6 mm)

Max. wear 0.002 in. (0.05 mm) Replace pin Fwd. and mid latch hook pin : min. dia. 0.559 in. (14.2 mm)

Max. wear 0.002 in. (0.05 mm) Replace pin Both aft latch pins : min. dia. 0.434 in. (11.0 mm)

(f)Dents and scratches Max. depth of 0.060 in. Up to 0.060 max. on lower latch (1.52 mm) depth may be blend handle repaired per 70-42-00

(5)Mounting ring latch assembly for :

(a)Cracks on latch Not serviceable Replace latch

(b)Cracks in flange 0.5 in.(12.7 mm) max. length. Replace latch Total accumulation of assembly two in.(50.8 mm). Cracks must be separated by one in. (25.4 mm).

(c)Cracks at bolt One per hole, max. length Replace latch holes 0.5 in.(12.7 mm) assembly Cracked holes must be separated by one good hole

(d)Damaged Not serviceable Replace latch cables assembly

(e)Bent, cracked, Not serviceable Replace pin broken or missing mounting ring lower latch pins

(f)Fretting in con- Not serviceable if felt Replace latch tact area between with 0.030 in.(0.76 mm) assembly lower latch hook radius scribe and hinge bolt

(g)Missing lubricant Not serviceable if Lubricate with in contact area metal visible through (C02-004) between lower coating latch hook and hinge bolt


�� G E � � � � CF6 - 50 � �� (6)Actuator mount brackets for :

(a)Cracks Not serviceable Replace Bracket

(b)Bends/Dents 0.250 in. (6.35 mm) deep Replace Bracket dent. Bends any amount provided no interference is encountered

(c)Vertical bulkead where bracket is mounted

1 Missing rivets Not serviceable Replace Bracket _

2 Torn metal Not serviceable Replace Bracket _

(d)Actuator clevis Not serviceable Replace clevis for cracks

(7)Vaned deflectors for :

(a)Cracks in leading 0.25 in.(6.35 mm) max. Replace deflector or trailing edge length, max. of five cracks per vane. Crack on leading and trailing edge must not be aligned

(b)Broken or missing Maximum of three broken Replace deflec- vane or missing, must be tor. Broken va- separated by two good nes must be cut vanes out.

(c)Dents on leading 0.12 in.(3.05 mm) max. depth Replace deflector or trailing edge

(d)Cracks at mounting One per bolt hole, 0.5 Replace deflector bolt holes in.(12.7 mm) max. length. One cracked bolt hole per side allowed.

(8)Deflector beams for :

(a)Cracks 0.25 in.(6.35 mm) max. Replace beam length, total accumulation of one in. (25.4 mm)

(b)Wear Must not extend into metal Replace beam

(9)Blocker doors for :


�� G E � � � � CF6 - 50 � �� (a)Cracks None allowed in mounting Replace door areas. One in.(25.4 mm) max. length outside mounting areas. Total accumulation of four in.(101.6 mm) per door

(b)Holes 0.50 in.(12.7 mm) max. Dia. Replace door one side only. Maximum of four holes separated by one in. (25.4 mm)

(c)Dents 0.5 in.(12.7 mm) max.depth Replace door

(d)Wear in hinge 0.03 in.(0.76 mm) max. Replace door bearings ID 0.408 in.(10.4 mm)

(e)Missing urethane Maximum of six square Maximum of 12 coating in.(38.7 cm²) per door square in. may be missing (77.4 cm2) for maximum of 20 flt. hours replace door

(f)Cracked or sepa- Not serviceable Replace door rated link housing

(g)Air seals cracked Any amount Remove cracked or delaminated or delaminated portion or remove entire seal

(h)Deployed reverser Not serviceable Trim slot end for contact between as required to slot end and link eliminate in- arm terference

(i)Deployed reverser 90 percent may be Replace door for missing wear missing on any side strip on doors of door

(10)Link boxes for 0.5 in. (12.7 mm) max. Replace box cracks length, total accumulation of two in.(50.8 mm). Cracks must be separated by 0.5 in. (12.7 mm).

(11)Link assemblies for :

(a)Cracks None allowed within two Replace link inches of platform. In


�� G E � � � � CF6 - 50 � �� other areas, 0.25 in. (6.35 mm) max. length. Maximum of three cracks per link

(b)Nicks or dents in 0.12 in.(3.05 mm) max. depth Replace link leading or trailing edge

(c)Bent link Not serviceable Replace link

(d)Wear in sleeve 0.03 in.(0.76 mm) max Replace link bearing max.ID 0.408 in.(10.4 mm)

(e)Lateral play 0.050 in. (1.27 mm) Replace link/ of link arm total, measured link box from edge of core assembly skin opening

(f)Link arm platform Not serviceable Replace link/ contacting edge of link box core skin assembly

(12)Deflection limiters for : (Ref. Fig. 609 )

(a)Cracks Not serviceable Replace limiter

(b)Deleted

(c)Wear on wear Any amount as long as Shim limiters surface contact exists between as required limiter and mating surface

(d)Missing wear Not serviceable Replace limiter surface

(e)Missing elastomer Serviceable, provided the Replace limiter beading wear pad does not rotate

(13)Deflection limiter tubes for :

(a)Cracks Not serviceable Replace tube

(b)Wear on wear Any amount as long as Shim limiter as surface contact exists between required tube and limiter

(c)Bent or buckled Not serviceable Replace tube tube


�� G E � � � � CF6 - 50 � �� (14)Bumper Assembly-Deflection Limiter for:

(a)Cracked or missing Not serviceable Replace sleeve split sleeve on left-hand-side

(b)Freedom of movement Not serviceable Replace Bum- (laterally by per Assembly rotating)

(15)Wear pads for : (Ref. Fig. 609 )

(a)Wear 0.06 in.(1.524 mm) max. Replace pad

(b)Cracks Not serviceable Replace pad

(c)Rotation of Not serviceable TORQUE wear pad wear pad attaching bolt to between 55 and 70 lbf.in. (0.62 and 0.79 m.daN).

(d)Missing wear Not serviceable Replace limiter surface

(e)Missing elas- Serviceable, provided the wear Replace limiter tomer beading pad does not rotate

(16)Mounting brackets Not serviceable Replace reverser for cracks half

(17)Feedback assembly for :

(a)Broken springs Not serviceable Replace spring

(b)Wear on cams Must not extend through Replace component or cam followers coating

(c)Cracked or damaged Not serviceable Replace rod stops on feedback rod

(d)Wear on feedback Maximum of 0.030 in.(0.76 mm) Replace rod rod at slot edge. Any amount in other areas

(e)Cracks in feedback Not serviceable Replace bracket or guide brackets


�� G E � � � � CF6 - 50 � ��

Deflection Limiter Wear Pad Limits Figure 609

(f)Guide bracket 0.030 in.(0.76 mm) max. Replace bracket for wear depth in area of contact with feedback rod slot edge. Any amount in other areas.

(g)Feedback bracket 0.020 in.(0.508 mm) max. Replace bracket for wear depth

(h)Nicks, dents or 0.010 in.(0.25 mm) deep after Replace rod scratches on rod removal of high metal end bearing end bearing

(j)Missing lubricant Not serviceable Lubricate with on parts having (C02-004) relative motion

(k)Corrosion Not serviceable if on Replace assembly surfaces having rela-


�� G E � � � � CF6 - 50 � �� tive motion. In other areas, any amount not exceeding 0.020 in.(0.508 mm) depth.

(l)Right side feed- With reverser deployed Deploy or stow back system or stowed, stow or reverser par- rigging deploy cam follower must tially to re- rest equally on top of lieve spring cam lobe (See Dim. load and adjust X and Y) (Ref. Fig. 604 ) system by rotating rod end bearing

CAUTION : AFTER ROD END BEARING ADJUSTMENT, A 0.055 IN. (1.39 mm) _______ DIA. PIN MUST NOT PASS THROUGH WITNESS HOLE.

(m)Left side feed- With reverser stowed, Adjust system back system rig- indicator switch stow by rotating rod ging cam follower must rest end bearing on top of cam lobe, 0.25 in. (6.35 mm) from edge within one revolution of rod end bearing (See Dim. A) (Ref. Fig. 606 )

NOTE : After rod end bearing adjustment, a 0.055 in. (1.39mm) Dia. ____ pin must not pass through witness hole.

(n)Left and right Must be free to travel Re-rig as side feedback by hand with reverser required system cams for in stow or deploy overtravel capa- position bility

(o)Right side spring None allowed Replace retai- retainer bushing for ner assembly looseness

(p)Right/Left side No contact allowed Shim lower yoke feedback yoke throughout rod travel bolts as requi- clearance with (Ref. Fig. 610 ) red to provide feedback rod clearance

R (q)Right and left Not serviceable Replace yokeR hand feedbackR yoke for cracks

R (r)Right and left 0.050 in. (1.27 mm) maximum Repair the feedbackR hand feedback depth across the contact yoke (Ref. 78-32-00,R yoke for wear faces (includes the total wear P. Block 801) if the


�� G E � � � � CF6 - 50 � ��R on the front and back contact limits are exceededR surfaces)

R 0.050 in. (1.27 mm) maximum Blend and repair theR depth along the cut-out area feedback yoke (Ref.R for sliding wear between the 78-32-00, P. BlockR yoke and the feedback rod 801) if the limitsR are exceeded

R (s)Wear on cam fol- Minimum 0.396 in. (10.05 mm) Replace cam lower lobe l/H Dimension A follower pneumatic switcher Detail A (Ref. Fig. 605 ) valve

R (t)Wear on cam fol- Minimum 0.736 in. (18.69 mm) Replace cam lower lobe R/H Dimension B 0.510 in. follower indicator switch (12.95 mm) lobe R/H Dimension C Detail B or C (Ref. Fig. 605 )

R (u)Wear on cam fol- Minimum 0.624 in. (15.85 mm) Replace cam lower lobe L/H Dimension D or E follower indicator switch Details D-E (Ref. Fig. 605 )

NOTE : Wear on all followers is allowable provided the required ____ dimensions are met as referenced in 78-31-00 - Inspection section for feedback system.

(18)Access panel and blow out doors for :

(a)Cracks 0.5 in. (12.7 mm) max. Replace panel length, total accumulation of two in.(50.8 mm). Cracks must be separated by 0.5 in. (12.7 mm).

(b)Broken or missing Not serviceable Replace latch latches (c)Gap in plastic 1 in. (25.4 mm) gap indicates Replace cable. covering of the cable has been overstressed blowout door retaining cable

(19)Hold open Rod ball lockpin :

(a)Wear elongation Any amount provided ball Replace hold- lockpin remains engaged open rod

(20)Aft support ring ID for wear :

(a)From top of ring No wear grooves allowed. Replace


�� G E � � � � CF6 - 50 � �� to the end of Not serviceable reverser first deflector

(b)From the first Not serviceable Replace deflector to the reverser bottom adapter

(21)Dagmar fairing for (Ref. Fig. 612 ) : (a) Dents Up to 0.060 in. (1.52 mm) Within the in depth serviceable limits, no repair is necessary

Not serviceable over If the dents 0.060 in. (1.52 mm) in are 0.061- depth 0.120 in. (1.55-3.05 mm) in depth, straighten the dent with a dent puller, apply Alodine No. 1200 (C03-006), and fill with RTV 106 (C01-007). If the dents are more than 0.120 in. (3.05 mm) in depth, replace the Dagmar fairing or deactivate the fan reverser

(b) Cracks aft of the Any number of cracks are Stop-drill the rivet line, but not permitted, with each crack crack and fill within 0.25 in. up to 2.0 in. (50.8 mm) with RTV 106 (6.35 mm) of a in length, and a total length (C01-007) rivet in the rivet of all cracks less than line 12.0 in. (308.4 mm) and a minimum distance of 2.0 in. (50.8 mm) between the cracks

Cracks within Not serviceable Replace the 0.25 in. (6.35 mm) Dagmar fairing of a rivet in the or deactivate rivet line the fan reverser


�� G E � � � � CF6 - 50 � �� Cracks forward of Not serviceable Replace the the rivet line Dagmar fairing or deactivate the fan reverser

Cracks longer than Not serviceable Replace the 2.0 in. (50.8 mm) Dagmar fairing or deactivate the fan reverser

(c) Holes Up to 4 holes with a maximum Within the diameter of 0.10 in. serviceable (2.54 mm) and a minimum limits, no distance of 1.0 in. (25.4 mm) repair is between the holes necessary. If there are 5 or more holes, replace the Dagmar fairing or deactivate the fan reverser

(d) Loose fasteners Not serviceable Replace the loose fasteners or deactivate the fan reverser

(22)Aft frame for (Ref. Fig. 612 ) : (a) Cracks Not serviceable Replace the aft frame or deactivate the fan reverser

(b) Holes Not serviceable Replace the aft frame or deactivate the fan reverser

(c) Loose fasteners Not serviceable Replace the loose fasteners or deactivate the fan reverser

C. Visually inspect/check the following reverser/nacelle sealing hardware.


�� G E � � � � CF6 - 50 � ��

Right/Left Side Feedback Yoke Alignment Figure 610


�� G E � � � � CF6 - 50 � �� ------------------------------------------------------------------------------- INSPECTION/CHECK MAXIMUM SERVICEABLE LIMITS REMARKS ------------------------------------------------------------------------------- (1)Translating Cowl (a)Beavertail bracket for : 1 Cracks None allowed Replace parts _ 2 Missing, torn or com- None allowed Replace parts _ pressed foam pads. (b)Bulb seal damage : 1 Radial cuts, splits, Up to 5 cuts, splits, or Over 5 cuts, _ or tears tears for each fan reverser splits, or half (5 total cuts, splits, tears : or tears for each four replace one or seal segments) more seal segments until the total number of cuts, splits, and/or tears for each fan reverser half is 5 or less; or, deactivate the fan reverser

2 Circumferential Not serviceable Replace the _ cuts, splits, or seal segment or tears deactivate the fan reverser. An over- serviceable- limit extension of 100 flight hours is permitted if total circumferential damage is less than 5.0 in. (127 mm) for each translating cowl

3 Nicks that do Any amount up to a Replace the _ not go through maximum length or width applicable seal the seal of 0.25 in. (6.35 mm) segment(s) or if separated by 5 in. deactivate the (127 mm) circumferentially fan reverser

4 Punctures and pin No visible holes or Replace the _ holes that go through punctures through the applicable seal the seal seal segment(s) or deactivate the fan reverser


�� G E � � � � CF6 - 50 � �� ------------------------------------------------------------------------------- INSPECTION/CHECK MAXIMUM SERVICEABLE LIMITS REMARKS -------------------------------------------------------------------------------

5 Missing sections Not serviceable Replace the _ missing seal segment(s) or deactivate the fan reverser

(c)L-seal for : 1 Missing material None permitted Replace the seal _ 2 Torn areas None permitted Replace the seal _ 3 Flatness at contact 0.300 in. (7.62 mm) Replace the seal _ point maximum width (d)Missing or peeling sealant in the following areas : 1 Beaver tail brackets None permitted Reapply sealant _ per Approved Repairs 2 L-seal brackets None permitted Reapply sealant _ per Approved Repairs 3 ?T? hinges None permitted Reapply sealant _ per Approved Repairs 4 Joint line of fwd None permitted Reapply sealant _ seal Z bracket per Approved Repairs

(2)Support Assembly (a)Foam Blocks for : 1 Compression, distor- None allowed Replace block _ tion, missing or torn areas - At forward end of None allowed Replace block T-track - Aft LH fireseal None allowed Replace block channel close-out at 12 oQclock (b)Missing/Peeling sealant in following areas : 1 Seals to fwd end of None allowed Reapply sealant _ T-track 2 Corner voids on fwd None allowed Reapply sealant _ end at 6-12 oQclock 3 Link boxes None allowed Reapply sealant _ 4 Upper inner corner of None allowed Reapply sealant _ core cowl 5 Seams at LPT plenum None allowed Reapply sealant _

(3)Precooler Duct (a)Bellows support ring for : 1 Looseness None allowed Retorque retai- _


�� G E � � � � CF6 - 50 � �� ------------------------------------------------------------------------------- INSPECTION/CHECK MAXIMUM SERVICEABLE LIMITS REMARKS ------------------------------------------------------------------------------- ning bolts 2 Cracks None allowed Replace ring _ 3 Missing nut plates None allowed Replace nut plate _ (b)Bellows for : 1 Wear, torn areas, mis- None allowed Replace bellows _ sing material 2 Missing sealant at None allowed Reapply sealant _ seams per Approved Re- pairs

Post SB GE 78-22B

D. Hold-Open Rod Inspection (1)Inspection of hold-open rod assembly (Ref. Fig. 611 ). (a)Remove the ball-lock pin allowing hold-open rod assembly to extend. (b)Visually inspect hold-open rod assembly for a wear groove. The wear groove, if present, will be located on the rod assembly inner strut, just below the ball-lock pin hole. (c)Measure the wear groove depth and record. The maximum allowable wear depth is 0.030 in. (0.76 mm). If wear exceeds allowable limits, remove the hold-open rod and repair the worn area per the following steps. If the wear does not exceed allowable limits, stow the hold-open rod and continue service. (2)Hold-open rod assembly rework (Ref. Fig. 611 ) (a)Remove nut, washers and bolt securing hold-open rod assembly. (b)Weld repair rod assembly inner strut wear groove flush with adjacent area per chapter 70-41-00 of the referenced Standard Practices Manual using AMS 4190 Filler Material. (c)Grind excess weld material to achieve original contour. (d)Apply Surface Treatment (C03-006) to repair area. (e)Apply Epoxy Resin Primer (C03-005) to repair area. (f)Remove any obvious burrs or sharp edges found on the interior edge of the outer strut end. (g)Re-install hold-open rod assembly. Secure with bolt, washers and nut. TORQUE nut to between 190 and 230 lbf.in. (2.14 and 2.59 m.daN). End SB GE 78-228

E. Close-Up (1)Make certain that working area is clean and clear of tools and miscellaneous items of equipment. (2)Remove safety clips and tags, close circuit breakers for the appropriate engine and close fan cowl, core cowl and thrust reverser doors (Ref. 71-13-00, P. Block 301). (3)Remove access platform.


�� G E � � � � CF6 - 50 � ��

Hold-Open Rod Assembly Figure 611


�� G E � � � � CF6 - 50 � ��

Dagmar Fairing and Aft Frame InspectionR Figure 612


�� G E � � � � CF6 - 50 � �� FAN REVERSER ASSEMBLY - APPROVED REPAIRS ________________________________________

WARNING : MAKE CERTAIN THAT CIRCUIT BREAKERS ARE OPEN, SAFETIED AND TAGGED AND _______ THAT AIR PRESSURE IS NOT APPLIED THROUGH GROUND CONNECTIONS. INADVER- TENT ENGINE START OR THRUST REVERSER OPERATION COULD RESULT IN DEATH OR SERIOUS INJURY TO PERSONNEL.

CAUTION : WHEN REPLACING COMPONENTS WITH ANOTHER SERVICEABLE PART, MAKE CERTAIN _______ THAT THE CORRECT CONFIGURATION IS USED ; REFER TO THE APPLICABLE IL- LUSTRATED PARTS CATALOG (IPC).

1. Reason For the Job __________________

A. Replacement of Vaned Deflectors

B. Replacement of Blocker Doors

C. Translating Cowl Removal/Replacement

D. Precooler Seal Assembly

E. Repair of Corroded Areas (Forward Flange, Torque Box, Upper Splice Plate).

R F. Repair of Wear on the Right and Left Hand Feedback Yoke Brackets


NOTE : Equivalent substitutes may be used instead of the following items. ____ ------------------------------------------------------------------------------- ITEM DESIGNATION ------------------------------------------------------------------------------- A. Material No.C01-007 Adhesives, Plastics, Sealants (Ref. 20-32-00) B. Material No.C01-062 Adhesives, Plastics, Sealants (Ref. 20-32-00) C. Material No.C01-095 Adhesives, Plastics, Sealants (Ref. 20-32-00) D. Material No.C01-126 Adhesives, Plastics, Sealants (Ref. 20-32-00) E. Material No.C02-004 Anti-Seize Compounds, Lubricants, Oils (Ref. 20-32-00) F. Material No.C03-002 Finishes and Protective Coatings (Ref. 20-32-00) G. Material No.C03-005 Finishes and Protective Coatings (Ref. 20-32-00) H. Material No.C03-006 Finishes and Protective Coatings (Ref. 20-32-00) I. Material No.C03-010 Finishes and Protective Coatings (Ref. 20-32-00) J. Material No.C03-013 Finishes and Protective Coatings (Ref. 20-32-00) K. Material No.C03-014 Finishes and Protective Coatings (Ref. 20-32-00) L. Material No.C03-017 Finishes and Protective Coatings (Ref. 20-32-00) M. Material No.C03-024 Anti-Seize Compounds, Lubricants, Oils


�� G E � � � � CF6 - 50 � �� ------------------------------------------------------------------------------- ITEM DESIGNATION ------------------------------------------------------------------------------- (Ref. 20-32-00) N. Material No.C03-025 Anti-Seize Compounds, Lubricants, Oils (Ref. 20-32-00) O. Material No.C03-026 Anti Seize Compounds, Lubricants, Oils (Ref. 20-32-00) P. Material No.C04-001 Cleaning Compounds and Solvents (Ref. 20-32-00) Q. Material No.C04-003 Cleaning Compounds and Solvents (Ref. 20-32-00) R. Material No.C04-004 Cleaning Compounds and Solvents (Ref. 20-32-00) S. Material No.C04-005 Cleaning Compounds and Solvents (Ref. 20-32-00) T. Material No.C04-018 Cleaning Compounds and Solvents (Ref. 20-32-00) U. MS20426AD5 Blind Rivets V. NAS1398M6 Blind Rivets W. NAS1738B5 Blind RivetsR X. LMS0158 Feedback Yoke Bracket Doubler (Right/Left Side)R Y. MS9318-056 RivetsR Z. 9025M85P15 Tension PinR AA.2C6105P01 Adapter - driveR AB.2C6983P01 Hydraulic PumpR AC.2C6367G01 Tool - Install/Remove - Pin, F/R Actuator RodR AD.2C6955G01 Fixture - LiftR AE. Torque Wrench, 24-70 lbf.in. (0.7 - 0.79 m.daN) RangeR AF. Circuit Breaker Safety ClipsR AG.180-240 Grit Abrasive Paper Referenced Procedures - 71-13-00, P. Block 301 Cowl Doors - 78-31-00, P. Block 201 Thrust Reverser System Control - 78-32-13, P. Block 401 Thrust Reverser Blocker Doors


A. Job Set-Up (1)Open, safety and tag circuit breakers for the appropriate engine and open fan cowl and thrust reverser doors (Ref. 71-13-00, P. Block 301). (2)Position access platform.

B. Replacement of Vaned Deflectors CAUTION : WHEN REPLACING VANED DEFLECTORS, MAKE CERTAIN THAT REPLACEMENT _______ DEFLECTORS ARE STRICTLY IDENTICAL AND ARE MARKED WITH THE SAME PART NUMBER AS THOSE REMOVED. (Ref. Fig. 801 ) (1)Replace damaged deflectors as follows : (a)Deploy reverser (Ref. 78-31-00, P. Block 201).


�� G E � � � � CF6 - 50 � ��

Installation of Fan Reverser Vaned DeflectorsR Figure 801


�� G E � � � � CF6 - 50 � �� (b)Remove deflector. (c)Position new deflector in place and install bolts and washers ; tighten bolts to 24-27 lbf. in. (0.27 - 0.30 m.daN). Tighten inner deflector countersunk screws to 13-16 lbf.in. (0.14 - 0.18 m.daN). (d)Stow reverser.

C. Replacement of Blocker Doors (Ref. Fig. 802 ) (1)Replace damaged blocker doors as follows : (a)Deploy reverser (Ref. 78-31-00, P. Block 201) (b)Remove nuts at link housing and hinge lugs ; remove door. (c)Position new door at hinge lugs and install bolts, washers and nuts ; tighten nuts to 55-70 lbf.in. (0.62 - 0.79 m.daN) and install cotter pins. (d)Connect door link to link housing with bolt, washer and nut ; tighten fingertight and install cotter pin. (e)Stow reverser.

Blocker Door - Removal/Installation Figure 802

D. Translating Cowl Gap Rigging (1)If gap between fan reverser translating cowl and support assembly is not within 0.06 - 0.15 in. (1.5 - 3.8 mm) proceed as follows : (a)Disconnect fan reverser drive shaft at center gearbox.


�� G E � � � � CF6 - 50 � �� NOTE : Remove shaft clamp adjacent to gearbox before disconnecting ____ shaft. (b)Remove plate and gasket opposite center gearbox input shaft and insert locally manufactured splined adapter. Rotate shaft socket until actuator hits stop or cowl motion ceases. (c)With reverser on stow stops, disconnect flexible shafts at angle gearboxes. NOTE : Remove shaft clamps adjacent to gearboxes before discon- ____ necting shafts. (d)Using 30-60 lbf.in (0.339 - 0.67 m.daN) torque, hold all gearboxes on stow stops. Rotate shaft ends up to 90 degrees in deploy direction for alignment and insert in angle gearbox sockets ; release applied torque. NOTE : To hold angle gearboxes on stow stops, use adapter, 2C6105, in ____ gearbox sockets opposite shafts. (e)Install gearbox flange bolts ; tighten to 24-27 lbf. in. (0.27 - 0.30 m.daN) and wirelock. Install shaft clamps ; tighten bolts to 24-27 lbf.in. (0.27 - 0.30 m.daN). (f)With actuators on stow stops, measure gap between support assembly and translating cowl ; gap must be 0.060 to 0.150 in. (1.52 - 3.81 mm) along assembly. (g)If gap is still not within limits ; adjust ball screw rod end bearings until gap is within limits CAUTION : AFTER ROD END BEARING ADJUSTMENT, A 0.055 IN. (1.40 mm) DIA. _______ PIN MUST NOT PASS THROUGH ACTUATOR WITNESS HOLE : NOTE : Each revolution of rod end bearing equals approximately ____ 0.042 in. (1.07 mm). (h)Translate reverser half partially and restow using center gearbox input socket. Running torque must not exceed 25 lbf.in. (0.28 m.daN) to translate cowl within gap limits. (i)If torque limit is exceeded, check for actuator lubrication or interference between cowl and support. Correct as necessary. (j)With reverser stowed and translating cowl gap within limits, rig fan reverser to drive motor flexible shafts per 78-31-00.

E. Translating Cowl Removal/Replacement NOTE : If a sealed fan reverser has the translating cowl removed and/or ____ replaced, the T-hinge must be resealed, using RTV 106 (C01-007) prior to reinstallation. (1)Remove/replace translating cowl as follows : (a)Manually deploy translating cowl approximately 4 to 5 in. (101.6 - 127.0 mm) (until feedback systems are in neutral position). Remove LH and RH feedback yoke. (b)Disconnect blocker doors from link assemblies at link housing only. Secure doors to translating cowl to prevent doors from swinging freely during handling. (c)Secure blocker door links to the core cowl to prevent damage. (d)Remove pin and cover assemblies securing rod end bearing of actuators to translating cowl. Use tool 2C6367G01 with adapter for assemblies, then retain pins for reassembly. (e)Remove translating cowl from the support assembly, using lift fixture 2C6955G01.


�� G E � � � � CF6 - 50 � �� CAUTION : EACH COWL HALF WEIGHS APPROXIMATELY 150 POUNDS (68 KG). WHILE _______ REMOVING THE TRANSLATING COWL, ENSURE THAT BLOCKER DOORS DO NOT DAMAGE THE INNER CORE COWL. (f)Position translating cowl with leading edge down, on a clean surface. (2)Install Translating Cowl as follows : (a)Attach lift fixture 2C6955 to Translating Cowl at top actuator retaining pin cover attaching holes and the forward edge of the Translating Cowl. (b)Lift cowl and engage cowl tee hinges in support assembly guides. Carefully guide cowl until supports are engaged on support flange. CAUTION : MAKE CERTAIN COWL DOES NOT CONTACT FEEDBACK RODS AS IT IS _______ GUIDED ON SUPPORT. (c)Connect link assemblies to blocker doors. Tighten bolts and nuts finger tight and insert cotter pins. (d)Install feedback guide brackets and engage feedback rod : TORQUE screws to between 33 and 37 lbf.in. (0.37 and 0.42 m.daN)

NOTE : On left side reverser, no contact is allowed between rod and ____ feedback yoke during any portion of cowl translation. If contact exists, install shims as required under yoke screws to prevent contact. (3)Adjust actuator rod end bearings and align the anti-rotation lug with cowl clevis. (a)Set distance between support assembly structural stop and actuator rod end mounting hole center line at dimension ?A? plus 0.28-0.29 in. (7.1- 7.4 mm) within one half revolution of rod end bearing. (b)TORQUE rod end bearing jam nuts to between 180 and 220 lbf.in. (2.03 and 2.49 m.daN) and wirelock. NOTE : After final rod end adjustment, a 0.055 in. (13.9 mm) dia. pin ____ must not pass through witness hole. (c)Extend each actuator by driving through gearbox and align with cowl clevis. Insert pin and cover assembly using puller 2C6367 with adapter. TORQUE pin cover screws to between 33 and 37 lbf.in. (0.37 and 0.42 m.daN). CAUTION : IF TOOL IS NOT USED, MAKE CERTAIN PINS ARE INSTALLED WITH _______ THREADED ENDS OUTBOARD. NOTE : Hold actuator rod to prevent rotation until rod end is within ____ translating cowl clevis. (d)Remove the lift fixture and install the remaining pin and cover to the actuator rod end.

F. Transcowl Bulb Seal Removal/Installation (1)Remove/install the transcowl bulb as follows : (a)Manually deploy the translating cowl (Ref. 78-31-00, P. Block 201). NOTE : In area of damaged bulb seal, it may be necessary to remove the ____ blocker door to gain access. (b)Remove the blocker doors, as necessary, in the area of the damaged bulb seal (Ref. 78-32-13, P. Block 401). (2)If the bulb seal is attached with rivets, do the steps that follow to remove one section or remove all four sections of the bulb seal. If the bulb seal is attached with bolts, begin at paragraph (3).


�� G E � � � � CF6 - 50 � �� NOTE : If the bulb seal is attached using rivets, it is recommended that ____ all of the bulb seal be removed. (a)Use a small pencil grinder to remove all of the rivets that attach the bulb seal to the cowl Z bracket. Make sure you do not damage the parent metal. (Ref. Fig. 803 ) (b)Punch the rivets through the Z bracket of the seal and the seal retainer. (c)Remove and discard the damaged seal segments or all of the seal segments. (d)If the Z bracket touches the fixed structure, and does not permit the bracket to align with the holes correctly, trim the leading edge 0.045 in. (1.14 mm). NOTE : If the Z bracket does not touch the fixed structure, DO NOT ____ TRIM the leading edge. (e)If you find high metal, remove it. Clean all the bare metal. (f)Apply a thin layer of Material No.C03-005 to the bare metal. (g)Use the seal retainer as a template and make the drill holes through the bulb seal. NOTE : Make sure you align the aft end of the seal with the aft end of ____ the retainer to drill the holes. NOTE : You can segment the retainer and the seal to replace part of the ____ seal. (h)Clamp the new bulb seal, the Z bracket, and the seal retainer in position. NOTE : On the sealed reversers, the L seal and all leakage areas must ____ have a layer of Material No.C01-007 as shown in SB 78-190. (Ref. Fig. 803 ) (i)If you install the new bulb seal with bolts instead of rivets, increase the bolt hole diameter by a very small amount. Refer to paragraph (3)(h) for the installation instructions. If you install the new bulb seal with rivets, continue with step (j) below. (j)Apply a thin layer of Material No.C03-005 to the rivets. (k)Attach the Z bracket, the bulb seal, and the seal retainer with the rivets. (l)Use Material No.C01-007 to make a seal splice at the joints. Make the surface smooth. Permit the splice to air cure. (3)If the bulb seal is attached with bolts, do the steps that follow to remove one section or remove all four sections of the bulb seal. (a)Remove the bolts, washers, and nuts that attach the bulb seal to the cowl Z bracket. Keep the hardware and the seal retainer. (Ref. Fig. 803 ) (b)Remove and discard the damaged seal segments or all of the seal segments. (c)If the Z bracket touches the fixed structure, and does not permit the bracket to align with the holes correctly, trim the leading edge 0.045 in. (1.14 mm). NOTE : If the Z bracket does not touch the fixed structure, DO NOT ____ TRIM the leading edge. (d)If you find high metal, remove it. Clean all the bare metal.


�� G E � � � � CF6 - 50 � �� (e)Apply a thin layer of Material No.C03-005 to the bare metal. (f)Use the seal retainer as a template and make the drill holes through the bulb seal. NOTE : Make sure you align the aft end of the seal with the aft end of ____ the seal retainer to drill the holes. NOTE : You can segment the retainer and the seal to replace part of the ____ seal. (g)Clamp the new bulb seal, the Z bracket, and the seal retainer in position. NOTE : On the sealed reversers, the L seal and all leakage areas must ____ have a layer of Material No.C01-007 as shown in SB 78-190. (Ref. Fig. 803 ) (h)Apply a thin layer of Material No.C03-005 to the fasteners. NOTE : Install the bolts with the heads radially outboard and washers ____ under the heads. (i)Attach the Z bracket, the bulb seal, and the retainer brace with the bolts, washers, and nuts. (j)TORQUE the nuts to between 10 and 12 lbf.in. (0.11 and 0.14 m.daN). (k)Use Material No.C01-007 to make a seal splice at the joints. Make the surface smooth. Permit the splice to air cure.

G. Precooler Seal Assembly (1)Replace shear head bolts with tension head bolts as follows : (a)With reverser open, remove shear head bolts and nuts. (b)If countersunk holes in seal assembly exhibit significant wear, new holes may be drilled by reindexing seal assembly on precooler duct. (c)Drill holes 0.198 - 0.204 in. (5.03 - 5.18 mm) dia. and countersink 98• - 102• 0.42 - 0.46 in. (10.67 - 11.68 mm) dia. (d)Install new tension head bolts through duct with washer, sleeve, spring and nut. (e)Tighten and TORQUE nut to between 33 and 37 lbf.in. (0.37 and 0.42 m.daN).

H. Intumescent Fireproof Coating (Ref. Fig. 804 ) NOTE : This procedure provides for both lap and butt joint repair edges. ____ The lap joint is preferred. Butt joints are included for those edges where access or proximity to reverser hardware do not permit lap joint construction. (1)Clean the area to be repaired plus adjacent intact intumescent coating with a halogenated type solvent such as Trichloroethane Material C04-004, or equivalent. CAUTION : INTUMESCENT MATERIALS AND HYDROCARBON TYPE SOLVENTS ARE _______ INCOMPATIBLE AND THEREFORE MUST NOT BE USED TOGETHER. (a)Outline area to be repaired so that the damaged material can be removed. The remaining edge must be intact. (b)Using a sharp instrument, carefully cut through the polyurethane top coat without cutting through to the metal substrate. (c)Carefully scrape off the damaged intumescent coating using a sharp scraper. Take care so as not to mark or scratch the aluminium substrate or green primer.


�� G E � � � � CF6 - 50 � ��

Transcowl Bulb Seal Assembly Figure 803


�� G E � � � � CF6 - 50 � �� (d)Remove residual intumescent coating from the green primer with 200 grit or finer emery paper. (e)To construct a lap joint, cut through the polyurethane top coat ONLY at a distance of 1.0-1.5 (25.4-38.1 mm) from the repair edge. Remove the top coat without disturbing the intumescent coating. (f)Solvent Material C04-004 clean the repair area and adjacent top coat but do not apply the solvent to the exposed intumescent coating. (g)Around the repair area and on the polyurethane top coat, mask a 0.5-1.5 in. wide border. (2)Application of flame control coating Material C03-024 for patch repair (Ref. Fig. 804, 805 and 806) (a)Prepare primer Material C03-026 by mixing parts A and B in the ratio, by weight, of 5.5 part A to 1 part B. The pot life of a 100 gram mixture is 7 hours at 60•-85•F (15•-29•C). (b)Brush a cover coat of prepared primer onto the 0.5-1.5 in. (12.7-38.1 mm) wide border of polyurethane top coat. Allow to cure a minimum of 2 hours at 65•F (18•C) or one hour at 110•-120•F (43•-49•C). (c)Remove the border mask and re-mask over the primed border, plus protect surrounding area against overspray. Masking is not required when coating is applied with a brush. (d)Thoroughly stir the flame control coating Material C03-024 and apply a single wet spray coat to a thickness of 0.020-0.028 in. (0.51-071 mm) NOTE : The coating must be applied in a wet, glossy condition with an ____ orange peel surface appearance. Poor adherence and intolerable overspray are products of spraying the coating dry. NOTE : Flame control coating may be applied using a brush, ____ maintaining the same thickness as for spraying. (e)Remove masking and cure to the appropriate between coat requirement. Two cure cycles for the flame control coatings are provided ; airline operators have the option of using either cycle, as each is acceptable. 1 CYCLE I _ - dry one hour minimum at 110-120•F (43•-49•C) after coats 1 and 2. - Dry 16 hours minimum at 110-120•F (43•-49•C) after the third (final) coat. 2 CYCLE II _ - dry 20-35 minutes at a minimum temperature of 65•F (18•C) after coats 1, 2 and 3 (final). - final cure by placing in a room temperature oven, raise temperature to 150-170•F (66•-77•C) and hold for 6 hours minimum. (f)If a stringy hair-like condition is observed, particularly along bracket edges and areas susceptible to bridging, hand rub the area. (g)Repeat masking, spraying or brushing and curing until a total of 3 coats are applied. The total dried thickness of the 3 coats of (C03-024) should be 0.054-0.078 in. (1.4-1.9 mm). Each wet coat shrinks approximately 0.002 in. (0.05 mm) when cured. (h)Mask around the primer Material C03-026 border and protect surrounding area against overspray. No mask required if a brush is used.


�� G E � � � � CF6 - 50 � �� (i)Prepare the flame control Material C03-025 top coat by mixing parts A and B, 1 : 1 by volume of 463 gr. of part A with 494 gr. of part B. Spray a 0.001-0.003 in. (0.03-0.08 mm) thick cover coat over the cured Material C03-024 and Material C03-026 primed surfaces. As close as possible, maintain a thickness of 0.001 in. (0.03 mm). NOTE : Flame control topcoat (C03-025) may also be brushed, ____ using the same thickness as for spraying. (j)Cure for 3.5 hours minimum at a minimum temperature of 65•F (18•C) or cure for 20-30 minutes at a minimum temperature of 65•F (18•C), followed by a temperature of 150•-170•F (66•-77•C) for 15-30 minutes using a heat gun. (k)Apply a second coat of flame control Material C03-025 top coat and cure, except on a second coat, as close as possible, maintaining a thickness of 0.003 in. (0.08 mm).

I. Application of Intumescent Coating (C03-024) by Brushing to Patch Repair (1)Prepare primer (C03-026) by mixing parts A and B in the ratio, by weight, of 5.5 part A to 1 part B. The pot life of a 100 gram mixture is 7 hours at 60• - 85• F (15• - 29• C). (2)Brush a cover coat of prepared primer onto the 0.5-1.5 in. (12.7- 38.1 mm) wide border of polyurethane top coat. Allow to cure a minimum of one hour at 110• - 120• F (43• - 49• C) using a heat gun. (3)Remove the border mask. (4)Thoroughly stir the flame control coating (C03-024) and apply a single wet coat to a thickness of 0.020-0.028 in. (0.51-0.71 mm). NOTE : The coating must be applied in a wet, glossy condition with ____ an orange peel surface appearance. Poor adherence and intolerable conditions are caused by using dry coating. (5)Remove masking and cure to the appropriate between coat requirement. (6)Repeat brushing and curing until a total of 3 coats are applied. The total dried thickness of the 3 coats of (C03-024) should be 0.054- 0.078 in. (1.4-1.9 mm). Each wet coat shrinks approximately 0.002 in. (0.05 mm) when cured. (7)Prepare the flame control (C03-025)top coat by mixing parts A and B, 1:1 by volume of 463 gr. of part A with 494 gr. of part B. Spray or brush a 0.001-0.003 in. (0.03-0.08 mm) thick cover coat over the cured (C03-024) and (C03-026) primed surfaces. As close as possible, maintain a thickness of 0.001 in. (0.03 mm). (8)Cure for 3.5 hours minimum at a minumum temperature of 65• F (18• C) or cure for 20-30 minutes at a minimum temperature of 65• F (18• C) followed by a temperature of 150•-170• F (66•-77• C) for 15-30 minutes using a heat gun. (9)Apply a second coat of flame control (C03-025) top coat and cure, except on a second coat, as close as possible, maintaining a thickness of 0.003 in. (0.08 mm)

J. Teflon Paint Coating on Fretting Surfaces of Fan Reverser (1)Any surface exhibiting fretting may be coated as follows : (a)Clean the fretting area with a cloth dampened with material C04-001 or C04-003 to remove all oil, grease and dirt. WARNING : CLEANING SOLVENTS ARE HIGHLY FLAMMABLE. USE PROPER PRECAU- _______


�� G E � � � � CF6 - 50 � ��

Support Assembly Fireproof Coating Areas Figure 804


�� G E � � � � CF6 - 50 � ��

Construction of Repair Joints Figure 805


�� G E � � � � CF6 - 50 � ��

Coating Overspray Allowances Figure 806


�� G E � � � � CF6 - 50 � �� TIONS. AVOID PROLONGED INHALATION OF FUMES. NOTE : Any area of the fan reverser indicating a fretting condition ____ may be repaired using this procedure. (b)Lightly sand to remove all sharp burrs gouges or edges with 240-320 grit silicone carbide paper. (c)Wipe area clean per step (a) above. (d)Mix the required amount of materials C03-013 and C03-014 as directed by the manufacturer. (e)Brush the mixture in a light coat to an approximate thickness of 0.003- 0.005 in. (0.08-0.12 mm). (f)Cure a minimum of 4 hours at room temperature or 2 hours at 150•F (64•C).

K. Core Cowl Inner Skin Delamination (Temporary Fly Home Repair) NOTE : This procedure provides instructions for the temporary repair of ____ delaminated inner skin from the aft circumferential close-out forward to the Z ring immediately aft of the link boxes. Delamination to the recoup duct or cooling fan is not included in this repair. Reverser flight time, with this repair, is limited to fifty (50) __________ flight hours and must not be exceeded. (1)Prepare the repair area as follows : (Ref. Fig. 807 ) (a)Remove the insulation coating from delaminated area, using a plastic scraper or equivalent. Remove a sufficient amount to allow thorough inspection. (b)Tap test to determine the total delaminated area, then outline the area with a felt pen. NOTE : Maximum repairable delaminated area is limited to an enclosed ____ 20 x 20 in. (508 x 508 mm) square. (c)If the innerskin has bulged, gently push the skin back against the core. CAUTION : CAREFULLY PUSH THE BULGED SKIN BACK IN PLACE AGAINST THE CORE _______ SO THAT NO ADDITIONAL DAMAGE OCCURS. (2)Using Aluminum (2024T3) 0.060-0.080 in. (1.5-2.0 mm) thick, form a doubler, splice and bracket to meet the following requirements. (a)Delamination between Z rings. 1 Doubler should extend from Z ring doubler axially to Z ring doubler _ and circumferentially a minimum of 2 in. (50.8 mm) beyond the delamination at both ends. (b)Delamination between Z ring and aft circumferential close-out. 1 Doubler should extend a minimum of 2 in. (50.8 mm) beyond the delami- _ nation all around. If doubler extends to the aft ?Z? ring doubler, a splice and shim must be used. If doubler extends to the aft circumferential close-out, a splice and shim must be used. (Ref. Fig. 807, 808 and 809) 2 If doubler extends axially to the close-out attach angles, splice and _ shim per (Ref. Fig. 809 ) (3)Drill the hole patterns for doublers and splices as follows : (a)If a ?Z? ring forward splice or an axial attach angle splice is being used, remove the nuts, bolts and washers from the ?Z? ring or the fasteners from the attach angle. 1 Transfer the hole pattern to the appropriate splice. _


�� G E � � � � CF6 - 50 � ��

Fan Reverser Inner Core Cowl Figure 807


�� G E � � � � CF6 - 50 � ��

Doubler, Splice and Brackets Between ?Z? Rings Figure 808


�� G E � � � � CF6 - 50 � ��

Blind Rivet Patterns Figure 809


�� G E � � � � CF6 - 50 � �� 2 Layout and drill 0.125 in. (3.2 mm) diameter pilot holes in the splice _ for blind rivets. (Ref. Fig. 809 ) (b)If an aft circumferential close-out splice is being used, layout and drill 0.125 in. (3.2 mm) diameter pilot holes for the 2 rows of blind rivets (Ref. Fig. 809 ). (c)Layout and drill 0.125 in. (3.2 mm) diameter pilot holes in the doublers as follows : NOTE : When a splice is used/required, do not drill doubler pilot ____ holes, as the pattern will be transferred from the splice. 1 Axial blind rivet pattern per (Ref. Fig. 809 ) _ 2 Circumferential blind rivet pattern per (Ref. Fig. 809 ) _ 3 Through panel fastener pattern per (Ref. Fig. 810 ) _ (4)Clean faying surfaces of core cowl and doubler in preparation for bonding as follows : (a)Remove residual insulating coating from core cowl repair area, using material C10-010, cleanser, and water. 1 Rinse, wipe dry and scuff sand with 180-240 grit aluminum oxide cloth. _ 2 Wipe area clean with solvent C04-001 or C04-003 moistened cloth, then _ wipe dry. (b)Clean faying surface of doubler by wiping with solvent C04-001 or C04-003 moistened cloth. 1 Scuff sand with 180-240 grit aluminum oxide cloth. Wipe with solvent _ moistened cloth, then wipe dry. (5)Install the doubler at the proper location as follows : (a)Apply a uniform coat of material C01-011 or C01-082 to faying surfaces of core cowl and doubler. Position doubler, press down to ensure full contact, and secure with tape or equivalent. (b)Transfer rivet pattern to the inner skin of core cowl, starting at the center of the doublers axial row of blind rivet holes in the row nearest the center of reverser. (c)Drill 0.177 in. (4.5 mm) diameter rivet holes through the inner skin and install blind rivets. (d)Transfer the through fastener pattern to the inner skin of core cowl, by drilling 0.161 in. (4.1 mm) diameter holes. (e)Select a hole in the perforated core cowl outer skin that aligns with an inner skin hole, enlarge hole in outer skin and install tension pin (9025M85P15), washer (9019M94P13) and collar (9110M70P01). TORQUE locking collar to between 15 and 22 lbf.in. (0.17 and 0.25 m.daN) (Ref. Fig. 810 ). NOTE : Start near center of riveted edge, and working in a fan-shaped ____ pattern continue toward the remaining three edges. CAUTION : USE EXTREME CARE WHEN INSTALLING THROUGH PANEL FASTENERS AS _______ BUCKLING OF THE OUTER SKIN AND CORE NODE FAILURES CAN BE IN- DUCED WHICH CAN MAKE PERMANENT REPAIRS DIFFICULT OR IMPOSSI- BLE. STOP TIGHTENING IF ANY SNAPPING OR TEARING SOUNDS ARE HEARD. (f)Install remaining blind rivets NAS 1738B5 plus the splices and shims as required. NOTE : Rivets NAS 1398M6 are used at splice to axial close-out and ____ attach angle. Determine rivet length at assembly. (6)Cure the adhesives using a heat lamp or blanket at the indicated tempera-


�� G E � � � � CF6 - 50 � ��

Through Fastener Patterns Figure 810


�� G E � � � � CF6 - 50 � �� tures below. (a)(C01-011) 200•F ± 25•F(93•C ± 11•C) (b)(C01-082) 250•F ± 25•F(121•C ± 11•C) (7)Repair MA25s insulation coating per paragraph T of this section.

L. Translating Cowl Bumper Replacement. (1)Replace worn/damaged bumpers as follows : (a)Deploy translating cowl until bumpers are accessible. (b)Remove screws, washers and nuts securing damaged bumpers to cowl and retain for later use. (Discard if damaged). (c)Discard damaged bumper and clean area on translating cowl with solvent C04-003. WARNING : CLEANING SOLVENTS ARE HIGHLY FLAMMABLE. USE PROPER PRECAU- _______ TIONS. AVOID PROLONGED INHALATION OF FUMES. (d)Touch up exposed metal with material C03-005. (e)Position replacement bumper to translating cowl and secure with (3) screws, washers and nuts. Shim as required to obtain Dim. R. (Ref. Fig. 811 ) (f)Tighten nuts until screw heads are flush with outer surface of translating cowl. (g)Repeat the above operations for all damaged bumpers on both Right and Left side reverser halves.

R M. Translating Cowl Lock Plate ReplacementR (1)Replace worn/damaged translating bumper cowl lock plates as follows:R (a)Deploy the translating cowl until you get access to the bumper lockR plates.R (b)Remove the bolts, washers and nuts securing damaged bumper lock platesR to the cowl and keep for later use. Discard if damage.R (c)Discard the damaged bumper lock plate.R WARNING : CLEANING SOLVENTS ARE HIGHLY FLAMMABLE, USE PROPER _______R PRECAUTIONS. AVOID PROLONGED INHALATION OF FUMES.R (d)Clean the bumper lock plate installation area on translating cowl withR solvent (C04-003).R (e)Touch up exposed metal with primer (C03-005).R (f)Position the replacement bumper lock plate to translating cowl andR secure with the bolts, washers and nuts you removed. Shim as necessaryR to the Dim. R Ref. (Ref. Fig. 812 ).R (g)Tighten nuts until the screw heads are flush with the outer surface ofR the translating cowl.R (h)Do the above operations for all damaged bumper lock plates on both theR right and left side reverser halves.

R N. Lower Blocker Door Trim (Ref. Fig. 813 ) NOTE : Trimming of the inboard close-out lip of lower blocker doors G.E. ____ Part No. 9058M92G09 or G10 is covered in the following paragraph. (1)Trim lower blocker door corner as follows : (a)Within the 100•-110• area shown in figure (Ref. Fig. 813 ), to obtain door to fairing clearance remove material, as required, but maintain a minimum of 0.30 in. (7.6 mm) wide bonded flat area. CAUTION : DO NOT FILE OR CUT IN A DIRECTION THAT WOULD CAUSE _______


�� G E � � � � CF6 - 50 � ��

T/C Bumper to Support Assembly Clearance Figure 811


�� G E � � � � CF6 - 50 � ��

Translating Cowl Bumper Lock Plate ReplacementR Figure 812


�� G E � � � � CF6 - 50 � �� DELAMINATION. (b)Lightly sand the trimmed area using 180-240 grit abrasive paper. (See above CAUTION). (c)Wipe the repair area with a clean cloth moistened with Acetone (C04- 003) or equivalent. (d)Spray a light coat of primer MIL-P-23377, a thickness of 0.0005-0.0015 in. (0.013-0.038 mm). Allow to air dry for one hour, followed by one hour of heat gun cure at 225•-250•F (107•-121•C). (e)Spray a coat of Epoxy-Polyamide (C03-010) over the repair area, air dry for 30 minutes. (f)Apply a second coat of Epoxy-Polyamide, then cure at room temperature a minimum of 4 hours.

R O. Standard Blocker Door Trim. (1)Standard doors may be trimmed to obtain clearance over the ?z? ring core bushings as follows : CAUTION : DO NOT FILE OR CUT TO A DEPTH OR DIRECTION THAT COULD _______ CAUSE DELAMINATION. (a)Using a file or rotary file, trim the blocker door to the dimensions shown in figure (Ref. Fig. 814 ) NOTE : Trim dimensions will vary because of the tolerances of each ____ door. (b)Lightly sand the trimmed area using 180-240 grit abrasive paper. (c)Wipe repair area with a clean cloth moistened with solvent (C04-003) or equivalent. (d)Spray a coat of Polymide primer (C03-017) on repaired area. Air dry for one hour followed by heat gun cure at 225•-250•F (107•-121•C) for one hour. (e)Apply a coat of Epoxy-Polymide (C03-010) and air dry for 30 minutes followed by a second coat, then cure at room temperature for 4 hours.

R P. Replacement of Link Box Assembly

(1)Remove worn/damaged link box assembly as follows : (a)Remove (1) cotter pin, nut, (2) washers and bolt securing link to blocker door. Retain hardware. (b)Remove (10) bolts and washers securing link box housing assembly to support assembly. (c)Remove the link box assembly and place aside.

(2)Install replacement link box assembly as follows : (a)Carefully place link through support assembly and secure link box assembly using (10) bolts and washers. Thighten bolts to 24-27 lbf. in. (0.27 - 0.31 m.daN) of torque. (b)Install link to blocker door using (1) bolt (2) washers, nut and cotter pin. Tighten nut and install cotter pin to bolt.

R Q. Sealed Reverser Sealant Reapplication Reapply sealant (C01-007) as necessary to restore the sealed areas of the fan reverser.


�� G E � � � � CF6 - 50 � ��

Lower Blocker Door Corner Trim Figure 813


�� G E � � � � CF6 - 50 � ��

Standard Blocker Door Trim for Clearance at ?z? Ring Core Bushings Figure 814

NOTE : All areas must be clean and free of all contaminants by using MEK ____ C04-001, Acetone (C04-004) or equivalent to clean the affected areas prior to sealant application. WARNING : SOLVENTS ARE TOXIC AND HIGHLY FLAMMABLE. AVOID PROLONGED _______ INHALATION OF VAPORS OR CONTACT WITH THE SKIN. TAKE PRECAU- TIONS AGAINST FIRE. NOTE : RTV 106 (C01-007) requires 24 hours to cure at room temperature for ____ best results, but experience has shown that after 12 hours the cure is sufficient to permit operation.

R R. Fairing Repair (1)Replace damaged fairing as an assembly or damaged section only as follows : CAUTION : USE CARE NOT TO DAMAGE RIVET HOLES IN SUPPORT ASSEMBLY WHEN _______ REMOVING FAIRING (a)Remove rivets : NOTE : If only a section of fairing is being replaced, remove rivets ____ to end of damaged area only. 1 Use hand drill to shear off rivet heads. _


�� G E � � � � CF6 - 50 � �� 2 Using small punch, drive out rivet shanks to release damaged fairing. _ NOTE : Retain damaged fairing for use as template when drilling rivet ____ holes in new fairing. (b)If only a section of fairing is removed, cut from good section so that replacement fairing can be butted against the remaining section. (c)Clean rivet holes in support assembly duct sidewall with naptha (C04- 018). (d)Cut replacement fairing to length required if only a section is used. (e)Fabricate a doubler 1.0 inch (25.4 mm) wide and 3/4 the length of the edge and formed to fit the radius of the fairing. NOTE : Use aluminium QQ-A-250/5 2024T42 0.025 in. (0.64 mm) thick to ____ make the doubler. (f)Position the doubler on the inside of the remaining fairing section and drill 0.125 in. (3.18 mm) rivet holes on one inch centers. (g)Position replacement fairing even with forward edge of support assembly duct sidewall or butted against existing fairing section as applicable ; clamp in place. (h)Use a hole transfer tool to mark six rivet hole locations at one end of new fairing or fairing section. (i)Remove replacement fairing or section and drill 0.125 inch (3.18 mm) dia. holes in marked locations. (j)Reposition replacement fairing or section on duct sidewall and hold in place with clamping devices. (k)Using old fairing or section for template, drill remaining 0.125 inch (3.18 mm) dia. rivet holes in replacement part. (l)Install rivets and washers in all locations. Rivets must be installed while completely covered with a wet coating of epoxy resin primer (C03- 005). (2)Minor damage to fairings may be repaired using RTV (two inches on either side of damaged area). (a)Blend/trim damaged torn/fretted edges of fairing. (b)Apply RTV 106 (C01-007) to area. (c)Blend the RTV smooth with the adjacent contour.

R S. Upper/Lower Aft Fairing (Beaver Tail) Removal (1)Remove damaged aft section of fairing as follows : (Ref. Fig. 815 ) CAUTION : EXTREME CARE MUST BE EXERCISED DURING FAIRING CLOSE OUT TO _______ ENSURE THAT EPOXY DOES NOT SET INTO THE HINGE AREA. NOTE : The aft section of the fairing (Beaver Tail) may be cut off and ____ the U-channel closed out, rather than replaced, if so desired. (a)At station 255.8 as shown in figure (Ref. Fig. 815 ), remove the damaged section of fairing by cutting using a high speed hand grinder. NOTE : Choice of cutting tool is optional. ____ (b)Deburr all sharp edges, abrade surfaces with abrasive pads (C10-010) until clean, then wipe entire area with clean cloth dampened with MEK (C04-001) or acetone (C04-003). NOTE : Close out of the removed Beaver Tail can be accomplished by ____ using fiberglass and the same method as used for U-Channel repair.


�� G E � � � � CF6 - 50 � ��

Upper/Lower Aft Fairing Removal Figure 815


�� G E � � � � CF6 - 50 � ��R T. Replacement of Worn/Damaged Tee Hinge Wear Strips (1)With the Tee Hinge accessible, replace the worn/damaged wear strip as follows : (a)Remove the old wear strip and adhesive from the hinge. (b)Clean hinge surface with a cloth dampened in solvent (C04-001) (C04-003), also the SPD wear strip (3046M82P04). (c)Dry the wear strip and hinge repair area with clean cloths. NOTE : Handle parts with clean cotton gloves. ____ (2)Prepare adhesive for repair as follows : WARNING : ADHESIVE IN UNCURED STATE IS FLAMMABLE, USE PROPER PRECAUTIONS. _______ USE LATEX GLOVES AND ACID TYPE GOGGLES TO AVOID CONTACT WITH ADHESIVE. AVOID PROLONGED INHALATION OF FUMES AND USE IN A WELL VENTILATED AREA. NOTE : Epoxy resin and catalyst should be at room temperature before ____ opening container. (a)Weigh sufficient EPON and catalyst (C01-011) in accordance with the manufacturerQs intructions found on the containers. (b)Using a metal spatula or equivalent, blend resin and catalyst on a clean piece of aluminum until thoroughly mixed. NOTE : Apply adhesive before cure has progressed to a point that flow ____ is affected. A 100 gram batch must be applied within 35 minutes after initiation of mixing, and parts mated within 55 minutes. Larger volumes normally have a shorter pot life. (c)Using a spatula or stiff bristled brush, apply a uniform coat of adhesive to faying surfaces. Coat should be approximately 0.001 in. (0.18 mm) thick. (d)Place a strip of nylon netting (C01-126) in the adhesive on hinge surface. (e)Mate SPD wear strip (3046M82P04) with hinge then clamp lightly. Bond line thickness to be between 0.004 and 0.010 in. (0.10 and 0.34 mm). NOTE : Use wood or aluminum strip as pressure pad to prevent indenta- ____ tion of wear strip and provide uniform bond line thickness. (f)Remove excess adhesive with a non-metallic scraper and clean cloth dampened in methyl-ethyl-ketone (C04-001). WARNING : CLEANING SOLVENTS ARE HIGHLY FLAMMABLE. USE PROPER PRECAU- _______ TIONS. AVOID PROLONGED INHALATION OF FUMES. (g)Cure adhesive for five days at room temperature or one hour minimum at 200 ± 10•F (93• ± 6•C).

R U. Replacement of Damaged/Worn Lower Duct Sidewall Wear Strip (1)Remove the teflon wear strip as follows : (Ref. Fig. 816 ) (a)Prior to removal of the teflon wear strip, mark the outline on duct sidewall to aid in the replacement with a steel rub strip. (b)Carefully remove the teflon wear strip from bondment. NOTE : Dry ice may be used to facilitate removal. ____ (c)Remove adhesive residue, using 180 grit sandpaper. (d)Locally manufacture a steel wear strip from 321 stainless, 0.017- 0.023 in. (0.43-0.58 mm) thick to the size of removed strip. (e)Trial fit replacement wear strip to sidewall and trim as required for proper fit on previously marked out-line.


�� G E � � � � CF6 - 50 � �� (2)Prepare the sidewall repair area as follows : (a)Moisten Scotch Brite Pads (C10-010) with solvent (C04-005) and thoroughly clean the area, where steel strip will be bonded. Allow to air dry. (b)Water break test using demineralized water no hotter than 150• F (65• C) and pH no greater than 7.5. (c)If water breaks are evident, reclean and retest. (d)Thoroughly dry the bondment a minimum of 30 minutes, at a temperature no greater than 150• F (65• C). (3)Prepare stainless steel wear strip for bonding as follows : (a)Clean the strip with a cloth and solvent (C04-005). WARNING : NEVER ADD WATER TO ACIDS. ADD ACIDS TO WATER WHILE STIRRING _______ VIGOROUSLY. LOCALIZED HEAT OF SOLUTION CAN CAUSE BOILING AND SPATTERING. WEAR CLOSE-FITTING GOGGLES OR A FACE MASK, RUBBER OR NEOPRENE GLOVES, AND PROTECTIVE CLOTHING. (b)Immerse the strip in a solution of 96.6 percent by volume of concentrated sulphuric acid and 3.4 percent by volume of saturated water solution of sodium dichromate for 15 minutes at 150•-160• F (65•-71• C). (c)Rinse parts in demineralized water at a temperature no higher than 150• F (65• C) and with a pH no greater than 7.5. Observe immediately for water breaks. If water breaks occur, dry part thoroughly and repeat the operation. (d)Dry the rinsed parts for 30 minutes at a temperature no greater than 150• F (65• C). (4)Install stainless steel wear strip as follows : (a)Apply a coat of Epoxy Resin Adhesive (C01-011) or (C01-059) to doubler area on sidewall. (b)Align and secure the wear strip on duct sidewall then drill (3) 0.160-0.164 in. (4.07-4.17 mm) diameter holes through strip and skin. (c)Install (3) ref. No. 1 rivets, with a wet coat of Epoxy Resin Primer (C03-002 or C03-005) through wear strip and sidewall. NOTE : Netting may be used to obtain a uniform adhesive ____ thickness. (d)Bag the repaired sidewall in a Nylon Vacuum Hi-Temp Bag (C10-057) and seal with Prestite Sealant (C10-052). (e)Pull a vacuum of 10 psi (20.36 in Mercury (Hg)) minimum. (f)Cure for one hour at 250• F (121• C), using strip heaters or Heat Lamps (C10-055) or at room temperature for 24 hours.

R V. Repair of Damaged MA25s Insulation Coating NOTE : This procedure provides instructions for the minor repair ____ of damaged MA25s insulation on any portion of the fan reverser, using SPD material. (1)Repair of damaged coating on core cowl, side walls or precooler using SPD sheet material P/N 3040M40P01 as follows : (a)Cut insulation coating repair patch larger than damaged area and position over the damaged area. NOTE : On inside of core cowl, the repair patch should not exceed ____ 2 inches by 2 inches, because the repair surface is basically


�� G E � � � � CF6 - 50 � �� spherical. Use multiple patches as required to fill the repair area. On flat surfaces such as sidewalls, there is no restric- tion on patch size. (b)Using patch as a template, cut into but no through existing insulation coating, with a plastic knife. (c)Remove the patch and carefully deepen the cut down through the coating. (d)With a plastic scraper remove all damaged material so that patch will fit into repair cavity and contact all faying surfaces. (e)Sand repair area with 120 grit or finer sand paper and remove all insulation material. WARNING : CLEANING SOLVENTS ARE HIGHLY FLAMMABLE. USE PROPER _______ PRECAUTIONS. AVOID PROPLONGED INHALATION OF FUMES. (f)Using clean cloth moistened with Acetone (C04-003) or equivalent, wipe primed surface free of coating residue. (g)Wipe repair area with clean cloths and clean water. Dry immediately with clean dry cloths. (h)Dry surface one hour at a 150• F (65.5• C) prior to primer application. (i)Prepare adhesive primer DC 1200 (C01-14) by thoroughly mixing per manufacturerQs instructions. (j)Using a small paint brush, apply primer to repair area and allow to cure for one hour. (k)Prepare RTV560 (C01-008) by mixing 75 grams RTV560 and 11 drops Tin Octoate, using a tongue depressor. Multiple batches may be mixed using the same ration. NOTE : Pot life is approximately 20 minutes. ____ (l)Using acid brush and plastic spatula, coat repair surfaces of patch with adhesive primer mixture, and apply patch as follows : 1 Carefully position patch in repair area. Gently roll into position _ starting at center and rolling toward edges to avoid air entrapment. 2 Cure at room temperature for a minimum of 4 hours. _ (m)Sand insulation coat flush with adjacent surface using 50-80 grit abrasive cloth. (n)Wipe repair surface with Acetone (C04-003) or equivalent. (o)If necessary, mix another batch of RTV560 sealer and apply to edges that have been sanded, using a spatula and acid brush. Assure that all areas are covered 0.005-0.011 in. (0.127-0.279 mm) thickness with RTV560 sealer. (2)Repair of core cowl inside surface, side walls or precooler using trowelled method and MA 25s Class B (C01-015). NOTE : MA 25s Class B is same as MA 25s Class A, except proportions of ____ catalyst to base component are different. NOTE : This repair technique is unlimited as to size of repair area. ____ However, thickness requirements must be met. (a)Prepare area of damaged coating per steps (d) thru (h) above. (b)Prepare surface and apply primer per steps (i) and (j) above. (c)Using a plastic spatula, trowel the compound into the repair area, building up slightly higher than surrounding area to compensate for slight shrinkage during cure. (d)Lightly sand repair flush with surrounding area using 50-80 grit abrasive cloth.


�� G E � � � � CF6 - 50 � �� (e)If RTV560 sealer has been previously applied to the surrounding area, prepare a small amount of sealer. (f)Wipe insulation coating repair area free of dust with a clean cloth moistened with Acetone (C04-003) or equivalent. (g)Brush a light coat of RTV560 sealer on the entire repair area and allow to cure. (h)Upon completion of repair, check for pin holes, blisters, edge peel, tears and bare spots within the repair area and touch up as required.

R W. Repair of the Corroded Areas of the Forward Flange, Torque Box and Upper Splice Plate (Ref. Fig. 805, 817 and 818) (Ref. Fig. 819 ) (1)Remove the intumescent paint (Ref. Paragraph 3.G.). (2)Use an aluminum wire brush or wheel to clean the corroded area. Make sure you remove all of the corrosion. (3)Use a 0.125 in. (3.18 mm) dia. drill to remove all of the rivets from the damaged area. WARNING : CLEANING SOLVENTS ARE HIGHLY FLAMMABLE, VOLATILE AND TOXIC. _______ THEY SHOULD BE USED WITH ADEQUATE VENTILATION. AVOID PROLONGED BREATHING OF THE VAPORS AND REPEATED OR PROLONGED CONTACT WITH YOUR SKIN. (4)Clean the area with solvent (C04-005). (5)Mask around the damaged area to prevent the intumescent paint from touching the area that is not affected. (6)Optional. Apply Alodine (C03-006) to the exposed metal surfaces. NOTE : The Alodine (C03-006) application is optional because of the ____ limits of controlling the exposure. (7)Install the rivets (MS 20426AD5) in the places where they were removed. (8)Seal the lap joint with joint sealer (C01-095). (9)Apply the epoxy resin primer (C03-002) to the masked area. (10)Apply the intumescent flame control paint (C03-024) to the repair area (Ref. Paragraph 3.H.).

R X. Feedback Yoke Bracket RepairR (1)Use 321 stainless steel (AMS 5510) to make a repair doubler (LMS0158AR or LMS0158B) (Ref. Fig. 820 ).R NOTE : LMS0158A and LMS0158B are not spare parts. They must be made ____R locally.R NOTE : Both left hand and right hand feedback yoke brackets can be ____R repaired with a doubler.R (a)Remove the feedback yoke bracket before installing the doubler.R (b)Put the doubler on the bracket and drill two 0.097 - 0.102 in.R (2.46 - 2.59 mm) diameter holes through the doubler and the bracket.R Make sure that the holes have a minimum edge distance of 0.20 in.R (5.08 mm) (Ref. Fig.820 and 821).R (c)Remove the doubler and use a 100 degree countersink to countersinkR the holes on both sides of the doubler to 0.175 - 0.183 in.R (4.45 - 4.65 mm).R (d)Deburr all the holes to remove sharp edges.R (e)Apply Epoxy Resin Primer Material No. C03-005 to the rivets


�� G E � � � � CF6 - 50 � ��

Lower Sidewall Wear Strip Figure 816


�� G E � � � � CF6 - 50 � ��

Corrosion Repair Areas (LH) Fan Reverser Assembly Figure 817


�� G E � � � � CF6 - 50 � ��

Corrosion Repair Areas (RH) Fan Reverser Assembly Figure 818


�� G E � � � � CF6 - 50 � ��

Corrosion Areas Figure 819


�� G E � � � � CF6 - 50 � ��R (MS9318-056).R (f)Install the doubler with the rivets. Install the rivets flush on bothR sides.R (g)Apply Epoxy Resin Primer Material No. C03-005 to all surfaces of theR repaired bracket.R (h)Install the feedback yoke doubler.R (2)Rig the feedback system and check the clearance between the feedback rodR and the yoke (Ref. 78-31-00, P. Block 201).

R Y. Close-Up (1)Make certain that working area is clean and clear of tools and miscellaneous items of equipment. (2)Close engine cowls. (3)Remove safety clips and tags and close circuit breakers for the appropriate engine (Ref. 71-13-00, P. Block 301). (4)Remove access platform.


�� G E � � � � CF6 - 50 � ��

Feedback Yoke Bracket DoublerR Figure 820


�� G E � � � � CF6 - 50 � ��

Feedback Yoke Bracket Doubler RepairR Figure 821


�� G E � � � � CF6 - 50 � �� THRUST REVERSER TRANSLATING COWL - REMOVAL/INSTALLATION _______________________________________________________

1. Equipment and Materials _______________________ ------------------------------------------------------------------------------- ITEM DESIGNATION ------------------------------------------------------------------------------- A. Access Platform B. Pneumatic Ground Power Unit - 3-Phase 115/220 V, 400 Hz, 90 KVA D. Torque Wrench 2.71 to 7.91 lbf. in. (0.27 to 0.79 m.daN) E. Cotter Pin F. 2C6367 Tool - Actuator Pin, Removal and Installations G. 63403A4241M000 Dolly - Handling, Thrust Reverser Cowls H. 97102A4241M000 Sling - Handling, Thrust Reverser Cowls I. 98A71101008000 Portable Crane - Removal/Installation, Engine Cowls J. Corrosion Resistant Steel Lockwire 0.032 in. (0.813 mm) K. Circuit Breaker Safety Clips Referenced Procedures - 24-41-00, P. Block 301 External Power - 36-00-00, P. Block 301 Pneumatic - General - 71-13-00, P. Block 301 Cowls Doors - 78-31-00, P. Block 201 Thrust Reverser System Control - 78-32-14, P. Block 301 Blocker Door Link Assembly


A. Job Set-Up (1)Open, safety and tag the appropriate circuit breakers (Ref. 71-13-00, P. Block 301). (2)Open fan cowl doors (Ref. 71-13-00, P. Block 301). (3)Partially open thrust reverser (Ref. 71-13-00, P. Block 301). (4)Install access platform. (5)Deploy thrust reverser cowl of approximately 4 to 5 in. (101.6 - 127 mm) (Ref. 78-31-00, P. Block 201).

B. Removal (Ref. Fig. 401 ) (1)Disconnect blocker link from door (Ref. 78-32-14, P. Block 401). NOTE : Blocker doors should be secured to inner recesses of cowl. ____ (2)Secure blocker links to core cowl. (3)Connect sling and bracket, taking weight of cowl. (4)Remove actuator rod end cover plates from cowl. (5)Remove threaded pin from actuator rod end bearing using tool 2C6367601. (6)Remove cowl. WARNING : EACH TRANSLATING COWL HALF WEIGHS APPROXIMATELY 150 POUNDS _______ (68kg). CAUTION : WHEN REMOVING TRANSLATING COWL, MAKE CERTAIN THAT BLOCKER _______ DOORS DO NOT DAMAGE INNER CORE COWL. (7)Place cowl on a clean surface with leading edge down.


�� G E � � � � CF6 - 50 � ��

Thrust Reverser Cowl Doors Figure 401


�� G E � � � � CF6 - 50 � �� C. Installation (Ref. Fig. 401 ) (1)Connect sling and bracket, taking weight of cowl. (2)Raise cowl, slide forward to engage in fan reverser tracks. WARNING : EACH INSTALLING TRANSLATING COWL HALF WEIGHS APPROXIMATELY 150 _______ POUNDS (68kg). CAUTION : WHEN INSTALLING TRANSLATING COWL, MAKE CERTAIN THAT BLOCKER _______ DOORS DO NOT DAMAGE INNER CORE COWL. (3)Check that actuators are adjusted to same length. (4)Install threaded pin in actuator rod end bearings connecting actuators to cowl using tool 2C6367601. (5)Disconnect and remove sling and bracket. (6)Connect links to blocker doors. Safety nut with cotter pin (Ref. 78-32-14, P. Block 401).

D. Adjustment/Test (Ref. 78-31-00, P. Block 201)

E. Close-Up (1)Make certain that working area is clean and clear of tools and miscellaneous items of equipment. (2)Remove access platform. (3)Remove safety clips and tags and close the appropriate circuit breaker, close fan and thrust reverser cowl doors (Ref. 71-13-00, P. Block 301).


�� G E � � � � CF6 - 50 � �� THRUST REVERSER CASCADES - REMOVAL/INSTALLATION _______________________________________________

1. Equipment and Materials _______________________ ------------------------------------------------------------------------------- ITEM DESIGNATION ------------------------------------------------------------------------------- A. 98A78303500000 Speed Handle Adapter - Square Drive 5/16 in. B. 2C6105 Speed Handle Extension Flexible C. Torque Wrench 1.43 to 3.05 lbf. in. (0.14 to 0.30 m.daN) D. Material No. 05-009 Special Materials (Ref. 20-31-00) E. Access Platform F. Circuit Breaker Safety Clips G. Corrosion Resistant Steel Lockwire o.032 in. Referenced Procedures - 71-13-00, P. Block 301 Cowl Doors - 78-31-00, P. Block 201 Thrust Reverser System Control


A. Job Set-Up (1)Open, safety and tag the appropriate circuit breakers and open fan cowl doors (Ref. 71-13-00, P. Block 301). (2)Install access platform at engine.

B. Removal (Ref. Fig. 401 ) (1)Manually, translate thrust reverser door to deploy (extend) position (Ref. 78-31-00, P. Block 201). (2)Remove upper and lower coupler. Fittings, bolts, washers, and nuts and remove half ring from thrust reverser. (3)If removing top or bottom cascade, remove retainer.R CAUTION : CASCADES SHOULD BE REMOVED AND REPLACED A MAXIMUM OF THREE _______ AT A TIME. CASCADE ASSEMBLY AFT SUPPORT RING CONTOUR COULD BER ADVERSELY AFFECTED WHEN MORE THAN THREE CASCADES ARE REMOVED. (4)Remove deflector : NOTE : Deflector flanges overlap. To remove deflector, slide clear of ____ overlapping flange.

C. Preparation of Replacement Component CAUTION : WHEN REPLACING THRUST REVERSER CASCADES, MAKE CERTAIN THAT _______ REPLACEMENT CASCADES ARE STRICTLY IDENTICAL AND MARKED WITH THE SAME PART NUMBER AS THOSE REMOVED.

D. Installation (Ref. Fig. 401, 402 and 403) (1)Apply corrosion preventive compound, Material No. 05-009 on all surfaces of bolts and washers. (2)Install deflector. CAUTION : CASCADES ARE PHYSICALLY INTERCHANGEABLE BUT HAVE LIMITED _______ FUNCTIONAL INTERCHANGEABILITY BETWEEN POSITIONS. REFER TO FIGURE FOR CORRECT INSTALLATION POSITIONS. (3)Install deflector. TORQUE bolts to between 24 and 27 lbf. in. (0.271 and


�� G E � � � � CF6 - 50 � ��

Thrust Reverser Cascade Figure 401


�� G E � � � � CF6 - 50 � �� 0.305 m.daN). TORQUE inner deflector countersunk screws to between 13 and 16 lbf. in. (0.14 and 0.18 m.daN). NOTE : Deflector flanges overlap. To install deflector, slide deflector ____ under overlapping flange. (4)Manually translate thrust reverser cowl to stow (Retract) position (Ref. 78-31-00, P. Block 201).

E. Test Manually move thrust reverser translating cowl from stow position to deploy position check there is no binding while thrust reverser translating cowls are displaced (Ref.78-31-00, P. Block 201).

F. Close-Up (1)Make certain that working area is clean and clear of tools and miscellaneous items of equipment. (2)Remove access platform. (3)Remove safety and tags and close the appropriate circuit breaker. Close fan cowl doors (Ref.71-13-00, P. Block 301).


�� G E � � � � CF6 - 50 � ��

Installation of Fan Thrust Vaned Deflectors Figure 402


�� G E � � � � CF6 - 50 � ��

Thrust Reverser Deflector Pattern Figure 403


�� G E � � � � CF6 - 50 � �� THRUST REVERSER BLOCKER DOORS -REMOVAL/INSTALLATION ___________________________________________________

1. Equipment and Materials _______________________ ------------------------------------------------------------------------------- ITEM DESIGNATION ------------------------------------------------------------------------------- A. Access Platform B. 2C6105 Adapter-Drive 5/16 in. C. 98A78303500000 Extension - Flexible, 5/16 in. 12 - Point Drive D. Torque Wrench 55-70 lbf.in. (0.62 - 0.79 m.daN) E. Circuit Breaker Safety Clips F. Cotter Pin G. Warning Notice Referenced Procedures - 71-13-00, P. Block 301 Cowl Doors - 78-31-00, P. Block 201 Thrust Reverser System Control


A. Job Set-Up (1)Open, safety and tag the appropriate circuit breakers for the appropriate engine and open fan cowl doors (Ref. 71-13-00, P. Block 301). (2)Position access platform. (3)Deploy reverser (Ref. 78-31-00, P. Block 201).

B. Removal (Ref. Fig.401 and 402) (1)Remove and discard cotter pin (4), remove nut (3) and washer (2), remove bolt (1) and disengage end of link (13). (2)Remove and discard cotter pins (5) and (18), remove nuts (17), (6) and washers (7), (16) ; remove bolts (10), (20) with washers (9), (19) and remove blocker door (11).

C. Installation (Ref. Fig.401 and 402) (1)Position door in place and install bolts (10), (20) with washers (9), (19) and install nuts (6), (17) with washers (7), (16). TORQUE nuts to between 55 and 70 lbf. in. (0.62 and 0.79 m.daN) and install new cotter pins. (2)Engage end of link (13) in blocker door (11). (3)Install bolt (1) with washer (2) and nut (3), TORQUE nut to between 55 and 70 lbf. in. (0.62 and 0.79 m.daN). (4)Install new cotter pin.

D. Close-Up (1)Make certain that working area is clean and clear of tools and miscellaneous items of equipment. (2)Stow fan thrust reverser (Ref. 78-31-00, P. Block 201). (3)Remove access platform and close fan cowl doors (Ref. 71-13-00, P. Block 301). (4)Remove safety clips and tags and close circuit breakers corresponding to the appropriate engine (Ref. 71-13-00, P. Block 301).


�� G E � � � � CF6 - 50 � ��

Blocker Doors Figure 401


�� G E � � � � CF6 - 50 � ��

Blocker Door Figure 402


�� G E � � � � CF6 - 50 � �� BLOCKER DOOR LINK ASSEMBLY - REMOVAL/INSTALLATION _________________________________________________

1. Equipment and Materials _______________________ ------------------------------------------------------------------------------- ITEM DESIGNATION ------------------------------------------------------------------------------- A. Access Platform B. Torque Wrench 20-140 lbf.in. (0.22 - 1.58 m.daN) C. Corrosion Resistant Steel Lockwire Dia 0.032 in. (0.813 mm) D. Circuit Breaker Safety Clips E. Warning Notice F. Splined Adapter 5/16 in. 12 Point Drive G. Material No. 03-005 Oils (Ref. 20-32-00) Referenced Procedures - 71-13-00, P. Block 301 Cowl Doors - 78-31-00, P. Block 201 Thrust Reverser System Control


A. Job Set-Up (1)Open, safety and tag required circuit breakers for the appropriate engine and open fan cowl doors and open partially thrust reverser cowl doors (Ref. 71-13-00, P. Block 301). (2)Position access platform. (3)In flight compartment, display warning notices prohibiting operation of throttle and thrust reverser control levers. (4)Manually translate thrust reverser to partially deployed position (Ref. 78-31-00, P. Block 201).

B. Removal (Ref. Fig. 401 ) (1)Remove and discard cotter pin (6), remove nut (7) and washer (8), remove bolt (9) and disengage end of link (10) from blocker door (5). NOTE : Take care when removing pivot housing cover, the spring may ex- ____ pand and pop out of the recess together with the rest washers. (2)Remove pivot housing cover (20), bolt and washer (21) remove spring (2) with washer (3) and cap (1). (3)Remove nut (4) bolt (13) washer (12) remove spindle (11) and disengage blocker door link (10) from forked pivot crank (14). (4)If desired, disconnect pivot crank from pivot housing cover as follows : (a)Remove cotter pin (15) and discard it, remove nut (16), remove bolt (17) and disengage pivot crank (14) from pivot housing cover (21).

C. Installation (Ref. Fig. 401 ) (1)Coat threads and shanks of crank-to-link bolt, link-to-housing bolt and link-to-door bracket bolt with lubricating oil, Item G. (2)If removed, install pivot crank (14) in pivot housing cover (21), place bolt (17), and TORQUE bolt to between 100 and 140 lbf. in. (1.129 and 1.581 m.daN) on safety with new cotter pin. (3)Insert blocker door link (10) through inner barrel and in forked pivot


�� G E � � � � CF6 - 50 � ��

Blocker Link Figure 401


�� G E � � � � CF6 - 50 � �� crank (14), place spindle (11) through pivot crank (14) and link (10) place bolt (13) with washer (12) through spindle (11) TORQUE unit to between 100 and 140 lbf. in. (1.129 and 1.581 m.daN). (4)Insert cap (1), spring (2), washer (3) into pivot housing cover (21) and install bolt and nut (21). (5)With spring washer (3) engaged with pivot crank (14), install pivot housing cover with bolt (19) and washer (18). TORQUE to between 100 and 140 lbf. in. (1.129 and 1.581 m.daN). (6)Engage door link (10) in blocker door bracket (5), place bolt (9), washer (8), nut (7) and TORQUE to between 50 and 70 lbf. in. (0.569 and 0.791 m.daN). Safety with new cotter pin. (7)Manually translate thrust reverser to stow (retract) position (Ref. 78- 31-00, P. Block 201).

D. Test (1)Manually proceed with several complete cycles of thrust reverser translating cowl. Make certain there is no binding (Ref. 78-31-00, P. Block 201).

E. Close-Up (1)Make certain that working area is clean and clear of tools and miscellaneous items of equipment. (2)Remove access platform. (3)Close fan and thrust reverser cowl doors (Ref. 71-13-00, P. Block 301) and close circuit breakers. (4)Remove warning notice.


�� G E � � � � CF6 - 50 � �� THRUST REVERSER TRANSLATING COWL AFT SOUND PANELS _________________________________________________ REMOVAL/INSTALLATION ____________________

1. Equipment and Materials _______________________ ------------------------------------------------------------------------------- ITEM DESIGNATION ------------------------------------------------------------------------------- A. Material No.C01-089 Adhesives, Plastics, Sealants (Ref. 20-32-00) Referenced Procedure - 78-32-11, P. Block 401 Thrust Reverser Translating Cowl


A. Job Set-Up (1)Remove fan reverser translating cowls from the fan reverser (Ref. 78-31-11, P. Block 401).

B. Removal (1)Remove tri-wing screws from aft sound panels. (2)Remove panels.

C. Installation (1)Install 22 triwing screws to each of the 3 sound panels at the proper locations. NOTE : There are 14 short and 8 long screws per panel. ____ (2)Apply sealant (C01-089) along the leading edge and sides in a continuous bead. NOTE : Make sure the sealant is smooth to the contour of the ____ panels. This will minimize the potential of panel erosion/ separation.

D. Close-Up (1)Install translating cowls on the fan reverser (Ref. 78-32-11, P. Block 401).


�� G E � � � � CF6 - 50 � ��

Aft Sound Panels - Removal/Installation Figure 401


�� G E � � � � CF6 - 50 � �� THRUST REVERSER TRANSLATING COWL AFT SOUNDS PANELS - INSPECTION/CHECK _____________________________________________________________________

1. Equipment and Materials _______________________ ------------------------------------------------------------------------------- ITEM DESIGNATION ------------------------------------------------------------------------------- Referenced Procedures - 78-31-00, P. Block 201 Thrust Reverser System Control - 78-36-00, P. Block 201 Fan Reverser Cowl Door Opening System


A. Job Set-Up (1)Place the translating cowl in the fully stowed position (Ref. 78-36-00, P. Block 201). (2)Check the translating cowl rigging (Ref. 78-31-00, P. Block 201).

B. Inspection/Check (1)Position a straight edge on the flowpath side of the forward fairing and extend the straight edge over the forward fairing trailing edge. (a)Measure the gap between the straight edge and the leading edge flowpath surface of the blocker doors. (b)Gap measurement should be 0.000-0.045 in. (0.00-1.14 mm). (2)Measure the gap between the forward fairing trailing edge and the blocker door leading edge. (a)Gap measurement should be a minimum of 0.060 in. (1.52 mm). (3)If gap measurement in (1)(b) or (2)(a) is not meet, adjust the forward fairing height by adding or removing washers from the forward fairing fasteners. (4)If the forward fairing adjustment does not yield adequate movement to bring the gap within tolerance adjust the blocker door as follows : (a)Adjust the blocker door by altering the thickness of the laminated shims included as part of the blocker door hinge attaching fasteners.


�� G E � � � � CF6 - 50 � ��

First Gap Measurement Figure 601


�� G E � � � � CF6 - 50 � ��

Second Gap Measurement Figure 602


�� G E � � � � CF6 - 50 � �� FAN REVERSER COWL DOOR OPENING SYSTEM - DESCRIPTION AND OPERATION _________________________________________________________________

1. Cowl Door Opening System ________________________

A. General The cowl door opening system provides a means for opening the fan reverser cowl doors to allow engine maintenance or removal. NOTE : Two systems are available for cowl door opening, the mechanical ____ system or the hydraulic system. Both systems are defined in this section. (1)Mechanical Ballscrew Actuator System Components of this system include a ballscrew actuator and a flexible shaft with integral housing for each fan reverser cowl. The actuators are mounted at about the 12 oQclock position between the aircraft pylon and the cowl. Flexible shaft housing are mounted at about the 6 oQclock position on the cowl with the shafts routed and clamped from the housing to the actuator. WARNING : USE THE FAN REVERSER COWL DOOR HYDRAULIC POWER OPENING SYSTEM _______ ONLY FOR OPENING AND CLOSING THE REVERSER HALVES, THE SYSTEM _______ _______ SHOULD NEVER BE USED AS A HOLD OPEN DEVICE. ALWAYS SECURE EACH _____ OPENED REVERSER HALF WITH AN APPROVED BRACE OR HOLD OPEN ROD, AS ________ DIRECTED BY THE INSTRUCTIONS BELOW, TO PREVENT SERIOUS INJURY DUE TO ACCIDENTAL OR INADVERTENT CLOSURE. KEEP ALL PERSONNEL CLEAR OF AREAS UNDER AND BETWEEN REVERSER HALVES DURING OPENING AND CLOSING CYCLES. (2)Hydraulic Actuator System Components of this system include a hydraulic actuator, hard lines, multiple connector, quick disconnects, relief valves and a hand operated hydraulic pump with an oil reservoir. The actuator is mounted at about the 12 oQclock position between the aircraft pylon and the cowl. The multiple connector, with relief valve and quick disconnect fitting is mounted at about the 6 oQclock position, with the hard lines routed and clamped from the connector to the actuator.

B. Operation The two systems are similar and accomplish the same end results, but the hydraulic is more easily maintained and presents less/fewer problems. (1)Mechanical Ballscrew Actuator System. The mechanical cowl door opening system may be operated manually or with an air wrench (Non-impact). Input power is transmitted from the input housing to the ballscrew actuator through the flexible shaft. The actuator has an integral bevel gear set that provides speed reduction and a ballscrew that provides linear output, forcing the cowl door open or closed. (2)Hydraulic Actuator System The hydraulic cowl door opening system must be opened by using a GSE hydraulic pump 2C6983 or an equivalent (approved) pump. Input power is transmitted from the pump through hard line tubes and a flexible hose to hydraulic actuator. The actuator has a slow back orifice, to prevent rapid retraction, a twenty five micron filter, to protect against contamination, cooling air jacket and is a pre-set length requiring no rigging. This system will normally open the cowl door to 45 degrees in 70


�� G E � � � � CF6 - 50 � �� seconds, and can close the door at the operators option, because of a variable OPEN valve on the pump. 2. Component Location __________________ (Ref. Fig.001 and 002) ------------------------------------------------------------------------------ ITEM NAME PANEL ZONE ACCESS DOOR ------------------------------------------------------------------------------ 1 Flexible Cable or Hydraulic Tube - 452 452AR RH Cowl Opening (Ref. 78-36-02, 462 462AR P. Block 201) 3 Ball Screw Actuator or Hydraulic 452 452AR Actuator - RH Cowl Opening (Ref. 462 462AR 78-36-01, P. Block 201) 5 Ball Screw Actuator or Hydraulic 451 451AL Actuator - LH Cowl Opening (Ref. 461 461AL 78-36-01, P. Block 201) 7 Flexible Cable or Hydraulic Tube - 451 451AL LH Cowl Opening (Ref. 78-36-02, 461 461AL P. Block 201) 9 Multiple Connector 452 452AR 462 462AR 451 451AR 461 461AR


�� G E � � � � CF6 - 50 � ��

Cowl Opening System - Component Location Figure 001


�� G E � � � � CF6 - 50 � ��

Hydraulic Cowl Door Opening Figure 002


�� G E � � � � CF6 - 50 � �� 3. Cowl Door Opening System Ball Screw Actuators and Hydraulic Actuators _____________________________________________________________________

A. Description (1)Mechanical System (Ref. Fig. 003 ) Each actuator consists of a housing, bevel gear set, tubular member, translating nut and ball screw. A friction bra ke, combined with an anti- back drive mechanism is included on the nut to alleviate chatter during lowering of the door with maximum safety while preventing accidental back drive at the ball screw. A clevis separation from the ball screw feature allows door opening by over-riding the actuator. (2)Hydraulic System (Ref. Fig. 004 ) The actuators consists of a slow back orifice, a 25 micron filter, cooling jacket and a preset fixed length that requires no adjustments.

B. Operation (1)Mechanical System Input power from the flexible shaft is transmitted to the actuator, reduced and translated to linear output. This forces the cowl door open. Positive reverse rotation of the flexible shaft must be transmitted to the actuator to allow door closure. (2)Hydraulic System (Ref. Fig. 005 ) Input power from a hand operated hydraulic pump is transmitted to the actuator through hard line tubes and flex hose producing linear output. This forces the cowl door open. An OPEN-CLOSE valve, located on the hand pump, maintains the hydraulic pressure required to open or close the door.


�� G E � � � � CF6 - 50 � ��

Cowl Door Ball Screw Actuator Figure 003


�� G E � � � � CF6 - 50 � ��

Cowl Door Hydraulic Actuator Figure 004


�� G E � � � � CF6 - 50 � ��

Hydraulic Cowl Door Opening System Figure 005


�� G E � � � � CF6 - 50 � ��

4. Cowl Door Opening System Flexible Shafts ________________________________________

A. Description (Ref. Fig. 006 ) The cowl door opening flexible shafts are flexible shafts with input housings and bearing assemblies which transfer motion from input to the cowl door actuator. Each input housing is bolted directly to the core cowl and contains a crank input socket and needle bearing. Each flexible shaft is connected to the input drive by a spline drive and threaded coupling. The shaft is contained within a cover which is packed with lubricant.

B. Operation A manually operated crank or air wrench is connected directly to the square drive in the input socket. The flexible shaft is rotated by the input through a direct drive spline.

Cowl Door Opening System Flexible Shafts Figure 006


�� G E � � � � CF6 - 50 � �� FAN REVERSER COWL DOOR OPENING SYSTEM MAINTENANCE PRACTICES ___________________________________________________________

WARNING : MAKE CERTAIN THAT CIRCUIT BREAKERS ARE OPEN, SAFETIED AND TAGGED AND _______ THAT AIR PRESSURE IS NOT APPLIED THROUGH GROUND CONNECTIONS. INADVER- TENT ENGINE START OR THRUST REVERSER OPERATION COULD RESULT IN DEATH OR SERIOUS INJURY TO PERSONNEL. NOTE : The following provides instructions for maintenance associated with ____ either the mechanical or hydraulic actuation cowl door opening system.

1. Equipment and Materials _______________________ ------------------------------------------------------------------------------- ITEM DESIGNATION ------------------------------------------------------------------------------- A. Access Platform 2 m (6 ft. 7 in.) B. Torque Wrench C. Circuit Breaker Safety ClipsR D. 2C6983 Pump, Hydraulic Referenced Procedure - 71-13-00, P. Block 301 Cowl Doors


A. Job Set-Up (1)Open, safety and tag circuit breakers for the appropriate engine (Ref. 71-13-00, P. Block 301). (2)Position access platforms.

B. Fan Reverser Opening and Closing Open or close fan reverser half using cowl door opening system as follows: WARNING : USE THE FAN REVERSER COWL DOOR HYDRAULIC POWER OPENING SYSTEM _______ ONLY FOR OPENING AND CLOSING THE REVERSER HALVES, THE SYSTEM SHOULD NEVER BE USED AS A HOLD OPEN DEVICE. ALWAYS SECURE EACH OPENED REVERSER HALF WITH AN APPROVED BRACE OR HOLD OPEN ROD, AS DIRECTED BY THE INSTRUCTIONS BELOW, TO PREVENT SERIOUS INJURY DUE TO ACCIDENTAL OR INADVERTENT CLOSURE. KEEP ALL PERSONNEL CLEAR OF AREAS UNDER AND BETWEEN REVERSER HALVES DURING OPENING AND CLOSING CYCLES. CAUTION : WHEN OPENING OR CLOSING FAN REVERSER HALF, DO NOT EXCEED _______ 70 LBF.IN. (0.79 m.daN) INPUT TORQUE THROUGH FLEXIBLE DRIVE SHAFT. CAUTION : DO NOT USE ANY IMPACT TYPE AIR MOTOR/WRENCH TO OPEN/CLOSE THE REVERSER HALVES. A LOW RPM AIR MOTOR/WRENCH, PRESET AT 70 LBF. IN. (0.79 m.daN), MAY BE USED FOR THE OPERATION. (1)Open reverser half as follows (Mechanical System): (a)Open and secure fan and core cowl doors. (b)Open blow out and access door assemblies. (c)Release mounting ring latch assembly as follows: (Ref. Fig.201 and 202) 1 Pull lower latch handle outward approximately one inch until latch _ pin reaches bottom of slot in upper latch (step 1). 2 Rotate upper latch handle outward (step 2). _ 3 Rotate lower latch handle outward (step 3). _


�� G E � � � � CF6 - 50 � �� (d)Release fan reverser lower latches. 1 With interlock handle in full open position, check the following _ dimensions: - 0.020 - 0.080 in. (0.50 - 2.03 mm) clearance must exist when cross pin on lever latch disengages interlock handle. - 0.100 - 0.250 in. (2.54 - 6.35 mm) clearance must exist between upper latch and cable end fitting. - 0.050 - 0.100 in. (1.27 - 2.54 mm) clearance must exist in vertical direction between upper hook and engine attaching hardware (U-bolt). (e)Push reverser halves apart. Insert square drive in flexible drive shaft input shocket and translate reverser open as required. (f)Install hold-open rod.

Opening of Mounting Ring Latch Assembly Figure 201

(2)Open reverser half as follows (Hydraulic System): (a)Perform operations (a) through (d) of paragraph (1). (b)Remove the dust cap/accumulator from quick disconnect fitting at the multiple connector. (Ref. Fig. 203 )R (c)Connect hose from hydraulic pump 2C6983 to quick disconnect at the multiple connector.


�� G E � � � � CF6 - 50 � ��

Ring Latch Dimensions (open) Figure 202

(d)Close the valve at the pump and actuate until the reverser half is raised sufficiently to install the hold open rod or other approved hold opening device. (e)Install brace No.1 or any approved hold open device. (f)Slowly open the valve on pump to release the hydraulic pressure. (g)Disconnect the pump hose from connector and install the dust covers. (3)Close reverser half as follows (Mechanical System) : (a)Remove hold-open rod (b)Insert square drive in actuation system input socket and rotate (CCW) to close reverser half. Continue until reverser motion stops. CAUTION : DO NOT USE ANY IMPACT TYPE AIR MOTOT/WRENCH TO OPEN/CLOSE _______ THE REVERSER HALVES. A LOW RPM AIR MOTORE/WRENCH, PRESETR AT 70 LBF. IN. (0.79 M.DAN), MAY BE USED FOR THE OPERATION. (c)Reverser halves may not fully close due to fire seal compression loads. Push reverser halves in close direction and continue to rotate input drive closed. When each half is closed enough to be latched, continue rotating the drive until a definite increase in torque is noticed. (d)Close lower latches.


�� G E � � � � CF6 - 50 � ��

Hydraulic Cowl Door Opening System Figure 203


�� G E � � � � CF6 - 50 � �� (e)Close mounting ring latch assembly as follows: (Ref. Fig.204 and 205) 1 Rotate lower latch handle inward (step 1). _ 2 Rotate upper latch handle inward. Ensure that pin in lower latch _ handle engages slot in upper latch (step 2). 3 Push lower latch handle full in (step 3). _ 4 With interlock handle fully latched check the following dimensions: _ - 0.010 - 0.030 in. (0.25 - 0.76 mm) clearance between pin on lower latch and slide of slot in interlock handle - Upper latch hook must be in contact with mounting bolt. (4)Close reverser half as follows (Hydraulic System): WARNING : DO NOT REMOVE BRACE NO.1 OR APPROVED HOLD. OPEN DEVICE UNTIL _______ STEP B. BELOW IS COMPLETED. (a)Remove dust cap/accumulator from quick disconnect fitting on multiple connector (Ref. Fig. 203 ) (b)Connect pump hose to quick disconnect on connector. WARNING : ENSURE THAT THE PUMP TANK IS DRAINED TO A MINIMUM LEVEL OF _______ 6 INCHES (15 CM) BELOW FILL PORT TO ACCEPT THE OIL BEING RETURNED FROM THE ACTUATOR DURING A DOOR CLOSING OPERATION DAMAGE DUE TO OVERPRESSURE IN PUMP TANK CAN CAUSE INJURY. (c)Close the OPEN-CLOSE valve on pump and actuate the pump until the approved hold open device becomes unloaded. (d)Remove brace No.1 or approved hold open device. (e)Continue to operate the pump an additional 8-10 strokes, after the actuator is fully extended. (The increased force necessary to operate the pump is required to cause oil to internally by-pass or leak from the relief valve). 1 Reinstall the hold open device and inspect the entire system for oil _ leaks. no leaks permitted. 2 Correct each leak as required and recheck until the system is leack _ free. NOTE : If relief valve leaked or bled any oil during the above opera- ____ tion replace faulty and recheck the system. (f)Slowly open the OPEN-CLOSE valve on pump and lower cowl door. NOTE : The cowl door should operate in a smooth continued closing/ ____ opening direction and should close in 15 seconds minimum from a full open position. (g)Complete the cowl door closing by closing the 3 main latches and latch ring. (h)Disconnect the pump hose, replace dust covers on hose and multiple connector, then stow the hose on the bracket on pump. (i)Close pressure relief and access door assemblies. 1 Close access doors. _ CAUTION : ENSURE THAT ACCESS DOORS ARE CLOSED AND PROPERLY LATCHED _______ BEFORE CLOSING PRESSURE RELIEF DOOR. ENSURE THAT DOOR RETENTION PINS ARE ENGAGED WITH DOORS CLOSED. 2 Close pressure relief door. _ CAUTION : PRELOAD MUST NOT EXIST ON PRESSURE RELIEF DOOR LATCHES WITH _______ DOORS CLOSED.

PRESSURE RELIEF DOOR RETENTION CABLES MUST BE PROPERLY STOWED TO AVOID DOOR PRELOAD OR INTERFERENCE.


�� G E � � � � CF6 - 50 � �� (j)Close fan and core cowl doors.

Closing of Mounting Ring Latch Assembly Figure 204

C. Cowl Door Opening System Deactivation (Mechanical System) (1)If cowl door opening system becomes inoperative while opening or closing, pull door open manually outward until actuator clevis disengages from actuator. (Ref. Fig. 206 ) NOTE : Force required to disengage clevis is 100-200 lbf (44.5 - 89 daN) ____ applied at lower edge of door. (2)Continue to pull door open manually to approximately 4-5 feet (1.21- 1.51 m) in order to gain access to actuator clevis mount bolt and install hold-open rod. WARNING : WITH ACTUATOR CLEVIS DISENGAGED, DOOR IS FREE TO MOVE ON HINGES _______ ENSURE THAT HOLD-OPEN ROS IS INSTALLED OR PERSONAL INJURY COULD OCCUR. (3)Remove actuator clevis bolt. (Ref. Fig. 206 ) (4)Remove or secure loose components and manually close door. (5)Prior to reactivation of system, troubleshoot to isolate cause of malfunction.


�� G E � � � � CF6 - 50 � ��

Ring Latch Dimensions (closed) Figure 205

NOTE : Cowl door actuator clevis may be engaged in actuator end fitting ____ using approximately 1000 lbf (445 daN) force. Weight of door on actuator is sufficient to engage clevis.

D. Cowl Door Opening System Deactivation (Hydraulic System) (1)If the hydraulic cowl door opening system becomes inoperative during opening/closing operation, close the OPEN-CLOSE valve on pump. WARNING : ENGAGE BRACE NO.1 OR ANY APPROVED HOLD OPEN DEVICE, TO _______ ENSURE PERSONNEL SAFETY FROM SUDDEN DOOR CLOSURE. (a)Open the OPEN-CLOSE valve and allow oil to return to pump reservoir. (b)Disconnect the pump hose from multiple connector and place dust covers on hose and connector. (c)Remove suspected malfunctioning component and replace. (2)After component replacement, operate the system per the opening/closing procedure of this section. If the malfunction has been corrected, continue proper sequence of operations to completion.

E. Close-Up (1)Remove access platforms.


�� G E � � � � CF6 - 50 � ��

Disengagement of Clevis from Cowl Door Actuator Figure 206

(2)Remove safety clips and tags, and close circuit breakers for the appropriate engine (Ref. 71-13-00, P. Block 301)


�� G E � � � � CF6 - 50 � �� COWL DOOR OPENING SYSTEM BALL SCREW ACTUATORS AND HYDRAULIC ACTUATORS _____________________________________________________________________ MAINTENANCE PRACTICES _____________________

WARNING : MAKE CERTAIN THAT CIRCUIT BREAKERS ARE OPEN, SAFETIED AND TAGGED, AND _______ THAT AIR PRESSURE IS NOT APPLIED THROUGH GROUND CONNECTIONS. INADVERTENT ENGINE START OR THRUST REVERSER OPERATION COULD RESULT IN DEATH OR SERIOUS INJURY TO PERSONNEL.



B. Inspection/Check

C. Approved Repairs

2. Equipment and Materials _______________________ NOTE : Equivalent substitutes may be used instead of the following items. ____ ------------------------------------------------------------------------------- ITEM DESIGNATION -------------------------------------------------------------------------------R A. Material C03-006 Finishes and Protective Coatings (Ref.20-32-00) B. Access Platform 2 m (6 ft. 7 in.) C. Torque Wrench. 24-100 lbf.in. (0.27 - 1.13 m.daN) D. Circuit Breaker Safety Clips E. Corrosion-Resistant Steel Lockwire 0.032 in. (0.813 mm) Dia.


�� G E � � � � CF6 - 50 � �� 3. Procedure _________

A. Job Set-UpR (1)Open, safety and tag circuit breakers for the appropriate engine andR open fan cowl and thrust reverser doors (Ref. 71-13-00, P. Block 301).R B. Removal (Ref. Fig. 201 ) (1)Remove ball screw actuator as follows : (a)Install hold-open rod. WARNING : HOLD-OPEN ROD MUST BE INSTALLED DURING AND AFTER REMOVAL OF _______ ACTUATOR OR PERSONNEL INJURY COULD OCCUR. (b)Remove shaft clamp (5) adjacent to actuator; remove shaft (2). (c)Remove bolt (1) at pylon uniball. (d)Remove bolts (3) at cowl bracket; remove actuator. (e)Remove stop sleeves and key plate from actuator and retain for installation on replacement actuator.

C. Installation (1)Install ball screw actuator as follows : (a)Locate key plate over actuator so two actuator tie bolt nuts extend through the clearance holes of plate. (b)FLocate sleeve half having threaded inserts on the extended side of bearing mount and next to the tab on key plate. Position the mating half and secure with fan bolts TORQUED to between 30 and 35 lbf.in. (0.34 and 0.40 m.daN). (c)Position actuator in cowl bracket with input connector forward and install bolts and nuts ; TORQUE to between 55 and 70 lbf.in. (0.62 and 0.79 m.daN). (d)Extend actuator by rotating ball screw by hand until clevis holes align with hole in pylon bracket uniball. (e)Install bolt (1) and nut through clevis and uniball ; TORQUE to between 80 and 100 lbf.in. (0.90 and 1.13 m.daN) (f)Install flexible shaft (2) through deflector bracket (4) and insert in actuator input socket ; tighten coupling nut hand tight, then back off one half turn. (g)Rotate shaft core two revolutions to center shaft washer on actuator connection ; TORQUE coupling nut to between 25 and 45 lbf.in. (0.28 and 0.51 m.daN). Safety with 0.032 in. (0.813 mm) corrosion-resistant steel lockwire. (h)Install shaft clamp (5) adjacent to actuator ; TORQUE clamp bolt to between 24 and 27 lbf.in. (0.27 and 0.30 m.daN). (j)Remove hold open rod.


�� G E � � � � CF6 - 50 � ��

Cowl Door Ball Screw Actuator - Removal/Installation Figure 201


�� G E � � � � CF6 - 50 � �� D. Removal of Hydraulic Actuator (Ref. Fig. 202 ) (1)With reverser half opened, install brace No.1 or any approved hold open device. WARNING : BRACE MUST BE INSTALLED DURING AND AFTER REMOVAL OF ACTUATOR _______ OR PERSONNEL INJURY MAY OCCUR. (2)Remove flex hose from fitting on actuator. Cap opening on actuator and the hose fitting. (3)Remove bolt, washers and nut, securing actuator, at pylon mount. (4)Remove bolts, washers and nuts, securing actuator to cowl bracket ; remove actuator.

E. Installation of Hydraulic Actuators Follows : (1)Position actuator in cowl bracket with input fitting forward, install bolts through rod end mount and cowl bracket, TORQUE bolts to between 55 and 70 lbf.in. (0.62 and 0.79 m.daN). (2)Extend actuator (if necessary) until clevis holes align with hole in pylon mount uniball. (3)Install bolt, washers and nut through clevis and uniball. (2 washers under bolt head and 1 washer under nut). TORQUE nut to between 80 and 100 lbf.in. (0.90 and 1.13 m.daN). (4)Connect flex hose to actuator inlet fitting and TORQUE to between 135 and 150 lbf-in. (1.52 and 1.69 m.daN). WARNING : DO NOT REMOVE THE HOLD OPEN ROD OR BRACE NO.1 UNTIL THE _______ HYDRAULIC PUMP HAS BEEN INSTALLED AND THE SYSTEM ACTUATED FULL WITH OIL. SERIOUS INJURY COULD RESULT BY SUDDEN CLOSURE OF THE COWL HALF. (5)Connect hydraulic pump to the multiple connector inlet fitting. (6)Move OPEN-CLOSE valve to CLOSE position and activate pump handle until pump goes into by-pass. This indicates the system is full of oil. (7)Remove hold open rod or brace No.1. (8)Open hand pump valve and allow cowl half to close. Remove hydraulic hose and stow pump.

F. Inspection/Check (1)Visually inspect ballscrew actuators as follows : -------------------------------------------------------------------------------- INSPECT MAXIMUM SERVICEABLE LIMITS REMARKS -------------------------------------------------------------------------------- (a)All areas for None allowed Replace actuator cracks

(b)Bearings for None allowed Replace actuator roughness or binding

(c)Thread damage 30% on one entrance thread Repair per paragraph E or 10% on each of two entrance threads

(d)Ball screw as- None allowed Replace actuator sembly for


�� G E � � � � CF6 - 50 � �� -------------------------------------------------------------------------------- INSPECT MAXIMUM SERVICEABLE LIMITS REMARKS -------------------------------------------------------------------------------- fretting, gal- ling or wear

(e)Ball screw to 0.37 in. (9.4 mm) may be Replace actuator housing seal extruded from housing for extrusion

R (f)Drive torque at 45 lbf.in. (0.49 mdaN) max. Replace actuatorR input socket running torque in either directionR during opening or closing

(g)Lower housing Not serviceable Open to 0.060 in. drain hole (1.50 mm) dia. clogged

(2)Visually inspect the hydraulic actuators as follows : -------------------------------------------------------------------------------- INSPECT MAXIMUM SERVICABLE LIMITS REMARKS -------------------------------------------------------------------------------- (a)All areas for None allowed Replace actuator cracks

(b)Bearing for None allowed Replace actuator binding

(c)Oil leakage 2 drops per 25 cycles max. Replace actuator

G. Approved Repairs. (1)Thread damage. Thread damage within serviceable limits may be blending with a fine stone. Protect bare areas with Material C03-006.

H. Close-Up (1)Make certain that working area is clean and clear of tools and miscellaneous items of equipment. (2)Close fan cowl and thrust reverser doors. Remove safety clips and tags, and close circuit breakers for the appropriate engine (Ref. 71-13-00, P. Block 301). (3)Remove access platform.


�� G E � � � � CF6 - 50 � ��

Cowl Door Hydraulic Actuator - Removal/Installation Figure 202


�� G E � � � � CF6 - 50 � �� COWL DOOR OPENING SYSTEM FLEXIBLE SHAFTS - MAINTENANCE PRACTICES ________________________________________________________________



A. Servicing


C. Inspection/Check

D. Approved Repairs

2. Equipment and Materials _______________________ NOTE : Equivalent substitutes may be used instead of the following items. ____ ------------------------------------------------------------------------------- ITEM DESIGNATION ------------------------------------------------------------------------------- A. Material C02-012 Anti-Seize Compounds, Lubricants, Oils B. Material C02-017 Anti-Seize Compounds, Lubricants, Oils C. Material C02-041 Anti-Seize Compounds, Lubricants, Oils D. Material C03-006 Finishes and Protective Coatings(Ref. 20-32-00) E. Access Platform 2 m (6 ft. 7 in.) F. Torque Wrench 25-70 lbf.in. (0.28-0.79 m.daN) G. Corrosion-Resistant Steel Lockwire Dia. 0.032 (0.813 mm) H. Circuit Breaker Safety Clips

NOTE : Service flexible shafts by lubricating shaft core lightly with material ____ C only.


�� G E � � � � CF6 - 50 � �� 3. Procedure _________

A. Job Set-Up (1)Open, safety and tag circuit breakers for the appropriate engine and open fan cowl and thrust reverser doors (Ref. 71-13-00, P. Block 301).

(2)Position access platform (3)Open fan thrust reverser cowls

B. Removal (Ref. Fig. 201 ) CAUTION : HOLD SHAFT SWAGED FITTING TO KEEP SHAFT FROM ROTATING WHILE _______ LOOSENING OR TIGHTENING COUPLING NUT. (1)Remove flexible shaft as follows : (a)Install hold-open rod. WARNING : HOLD-OPEN ROD MUST BE INSTALLED DURING AND AFTER REMOVAL _______ OF FLEXIBLE SHAFT OR PERSONNEL INJURY COULD OCCUR. (b)Remove bolts at input housing. (c)Disconnect clamps. (d)Disconnect coupling nut at actuator; remove shaft.

C. Installation (1)Install flexible shaft as follows : (a)Insert shaft through deflector bracket and into actuator drive socket ; tighten coupling nut fingertight, then back off one half turn. (b)Rotate shaft core two revolutions to center shaft washer on actuator connection; TORQUE coupling nut to between 25 and 45 lbf.in. (0.28 and 0.50 m.daN) and safety with 0.032 in. (0.813 mm) dia. corrosion resistant steel lockwire. (c)Secure shaft input housing to cowl ; TORQUE bolts to between 55 and 70 lbf.in (0.62 and 0.79 mdaN). (d)Install clamps; TORQUE clamp bolts to between 24 and 27 lbf. in. (0.27 and 0.30 m.daN). NOTE : Install all clamps fingertight. Pull shaft snug and distri- ____ bute slack between third, fourth and fitth clamps from botton of reverser, then tighten successive clamps from top to botton. (e)Check shaft for sharp bends; kinks or damage. Adjust clamps to provide smooth drive line with no radius less than 6.5 in. (165 mm).R (f)Remove brace or approved hold-open rod.

D. Inspection/Check Visually inspect the following areas. ------------------------------------------------------------------------ INSPECTION/CHECK MAXIMUM SERVICEABLE LIMITS REMARKS ------------------------------------------------------------------------ (1)Shaft casing No holes through casing allowed Replace for wear shaft

(2)Thread damage 30 percent on one entrance thread or Repair per 10 percent on each of two entrance paragraph E threads

(3)Input housing None allowed Replace shaft


�� G E � � � � CF6 - 50 � �� ------------------------------------------------------------------------ INSPECTION/CHECK MAXIMUM SERVICEABLE LIMITS REMARKS ------------------------------------------------------------------------ square drive for wear or deformation

(4)Installed shaft Clamp center line must be aligned with Reclamp as clamping and bend shaft center line. Bend radius must required radii exceed 6.5 in. (165 mm)

(5)Spline coupling Not serviceable Replace sheared coupling

E. Approved Repairs (1)Thread damage. Thread damage within serviceable limits may be repaired by blending with a fine stone. Protect bares areas with Alodine (C03-006). (2)Replacement of flexible shaft spline coupling. Replace damaged spline coupling as follows : (Ref. Fig. 202 ) (a)Expose coupling retaining pin and drive out coupling from end without groove using 0.092 in. (2.33 mm) dia. drift pin. CAUTION : USE CARE TO PREVENT WASHER DAMAGE WHEN REPLACING COUPLING. _______ (b)Pull coupling and washers from shaft end fitting. (c)Position new coupling on shaft end fitting and align pin holes. Clean up hole alignment using a 0.094-0.097 in. (2.39-2.46 mm) dia. drill. (d)Remove the coupling and pull the core out of the casing. (e)Apply a light coating of grease (C02-041) to the core, washers and internal spline of coupling. Reassemble the core, washers and spline coupling. (f)Press in new retaining pin. Set pin flush with coupling surface and remove any burrs from around pin hole on both sides. (g)Check the following : 1 Large washer must be flat, no burrs and must turn freely. _ 2 Coupling must tight on shaft. _ 3 Coupling pin must be tight and flush with coupling OD on both sides. _ 4 Coupling nut must turn on casing. _ 5 End fitting flare must appear round and uniform. _ (h)Connect shaft to input housing if required. Tighten nut hand tight and back off one half turn. Rotate shaft two revolutions to center large washer on housing connection ; TORQUE coupling nut to between 25 and 45 lbf.in. (0.28 and 0.50 m.daN) and wirelock.

F. Close-Up (1)Make certain that working area is clean and clear of tools and miscellaneous items of equipment.R (2)Remove access platform.R (3)Remove safety clips and tags and close circuit breakers for the appro-R priate engine and close fan cowl and thrust reverser doorsR (Ref. 71-13-00, P. Block 301).


�� G E � � � � CF6 - 50 � ��

Cowl Door Opening System Figure 201


�� G E � � � � CF6 - 50 � ��

Replacement of Flexible Shaft Spline Coupling Figure 202


A300B2 ATA 78

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