### Commercial **Airplanes** 

# 767 Service Bulletin **Number: 767-78-0096** Original Issue: August 07, 2008 Revision 1: December 10, 2009 ATA System: 7834 **SUBJECT:** EXHAUST - Thrust Reverser Control System - Rolls Royce Powered Thrust Reverser Logic, Change Export of this technology is controlled under the United States Export Administration Regulations (EAR) (15 CFR 730-774). An export license may be required before it is used for development, production or use by foreign persons from specific countries. The controller of this data has the individual responsibility to abide by all export laws. 9E991 ECCN: 

## BOEING PROPRIETARY, CONFIDENTIAL, AND/OR TRADE SECRET Copyright © 2008 The Boeing Company Unpublished Work - All Rights Reserved Boeing claims copyright in each page of this document only to the extent that the page contains copyrightable subject matter. Boeing also claims copyright in this document as a compilation and/or collective work. This document includes proprietary information owned by The Boeing Company and/or one or more third parties. Treatment of the document and the information it contains is governed by contract with Boeing. For more information, contact The Boeing Company, P.O. Box 3707, Seattle, Washington 98124. Boeing, the Boeing signature, the Boeing symbol, 707, 717, 727, 737, 747, 757, 767, 777, 787, Dreamliner, BBJ, DC-8, DC-9, DC-10, KC-10, KDC-10, MD-10, MD-11, MD-80, MD-88, MD-90, P-8A, Poseidon and the Boeing livery are all trademarks owned by The Boeing Company; and no trademark license is granted in connection with this document unless provided in writing by Boeing.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 07, 2008 767-78-0096 Revision 1: December 10, 2009 1 of 64 3.0BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 07, 2008 767-78-0096 Revision 1: December 10, 2009 2 of 64 **BOEING SERVICE BULLETIN 767-78-0096**

BLANK PAGE**Table of Contents** Revision Transmittal Sheet............................................ 5 Summary...................................................... 9 1. PLANNING INFORMATION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13 A. Effectivity. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13 1. Airplanes. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13 2. Spares Affected. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14 B. Concurrent Requirements. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14 C. Reason. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14 D. Description. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17 E. Compliance. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17 F. Approval. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17 G. Manpower. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18 H. Weight and Balance Changes. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20 I. Electrical Load Data. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20 J. References. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20 1. Existing Data:. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20 2. Data supplied with this Service Bulletin:. . . . . . . . . . . . . . . . . . . . . . . . . . . 20 3. Installation Drawings Used in the Preparation of this Service Bulletin:. . . . . . . . . . . 21 K. Publications Affected. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21 L. Interchangeability and Intermixability of Parts. . . . . . . . . . . . . . . . . . . . . . . . . . . 21 2. MATERIAL INFORMATION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23 A. Material - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23 B. Industry Support Information. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23 C. Parts Necessary For Each Airplane. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23 1. Kits/Parts:. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23 2. Parts and Materials Supplied by the Operator:. . . . . . . . . . . . . . . . . . . . . . . . 24 3. Parts Modified and Reidentified:. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25 4. Parts Removed and Not Replaced:. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25 D. Parts Necessary to Change Spares. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25 E. Special Tooling - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25 F. Special Tooling Necessary to do this Service Bulletin. . . . . . . . . . . . . . . . . . . . . . . 25 3. ACCOMPLISHMENT INSTRUCTIONS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27 A. GENERAL INFORMATION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27 B. WORK INSTRUCTIONS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 28 FIGURE 1: P36 PANEL-THRUST REVERSER CONTROL, ENGINE 1, RELAY INSTALLATION [Group 1, 3] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 35 FIGURE 2: P36 PANEL-THRUST REVERSER CONTROL, ENGINE 1, WIRE CHANGE [Group 1] . . 38 FIGURE 3: P36 PANEL-THRUST REVERSER CONTROL, ENGINE 1, WIRE CHANGE [Group 3] . . 41 FIGURE 4: P36 PANEL-THRUST REVERSER CONTROL, ENGINE 1, RELAY INSTALLATION [Group 2, 4] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 44 FIGURE 5: P36 PANEL-THRUST REVERSER CONTROL, ENGINE 1, WIRE CHANGE [Group 2, 4] . 47 FIGURE 6: P36 PANEL, RETURN ACCESS [Group 1-4]. . . . . . . . . . . . . . . . . . . . . . . . . 50 FIGURE 7: P37 PANEL-THRUST REVERSER CONTROL, ENGINE 2, RELAY INSTALLATION [Group 1-4] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 52 FIGURE 8: P37 PANEL-THRUST REVERSER CONTROL, ENGINE 2, WIRE CHANGE [Group 2, 4] . 55

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 07, 2008 767-78-0096 Revision 1: December 10, 2009 3 of 64 **BOEING SERVICE BULLETIN 767-78-0096**FIGURE 9: P37 PANEL-THRUST REVERSER CONTROL, ENGINE 2, WIRE CHANGE [Group 1, 3] . 58 FIGURE 10: P37, RETURN ACCESS [Group 1-4]. . . . . . . . . . . . . . . . . . . . . . . . . . . . . 61 FIGURE 11: P33 PANEL-THRUST REVERSER CONTROL, WIRE REMOVAL [Group 1-4]. . . . . . 63 FIGURE 12: P33 TO P36 PANEL-THRUST REVERSER, WIRE REMOVAL [Group 1-4]. . . . . . . . 64

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 07, 2008 767-78-0096 Revision 1: December 10, 2009 4 of 64 **BOEING SERVICE BULLETIN 767-78-0096**

### Commercial **Airplanes** 

# 767 Service Bulletin **Revision Transmittal Sheet Number: 767-78-0096**  Original Issue: August 07, 2008 Revision 1: December 10, 2009 ATA System: 7834 **SUBJECT:** EXHAUST - Thrust Reverser Control System - Rolls Royce Powered Thrust Reverser Logic, Change This revision includes all pages of the service bulletin. **COMPLIANCE INFORMATION RELATED TO THIS REVISION** No more work is necessary on the airplane changed in accordance with the original issue of this service bulletin. **REASON FOR REVISION** As a part of a service bulletin validation program, this change was completed on airplane VL873 by Service Bulletin 767-78-0096 Original Issue before the release of Revision 01 of this service bulletin. The change completed on airplane VL873 by Service Bulletin 767-78-0096 Original Issue is equivalent to the release of Revision 01 of this service bulletin. Airplane VL873 has the configuration of a Group 1 airplane. This service bulletin revision is sent to provide operators with the changed service bulletin after the incorporation of the validation findings. During the modification, it was found that a ground block and two terminal blocks were named incorrectly in wiring diagrams in the service bulletin.A ground location that was found to be full has been changed to another ground in the same panel. A wire in the wire kit has been changed because it was too short. Findings during testing led to a partial rewrite of the functional test to change the voltage check locations. It was also found that the EICAS message called out in the functional test of the Service Bulletin was not the correct one. A duplicate wire reference in the service bulletin is also corrected. A maintenance zones table has been added to the service bulletin. The Damage Tolerance Based Structural Inspections impact information was added. These sections were changed: 1. Paragraph 1.D: a maintenance zones table has been added to the service bulletin. 2. Paragraph 1.K, Publications Affected: The Damage Tolerance Based Structural Inspections impact information was added. 3. Figure 2, sheet 1: ground GDX17-DC has been changed to GDX3-DC. 4. Figure 3, sheet 1: ground GDX9-DC has been changed to GDX3-DC. 5. Figure 2, sheet 2: the wire between D11763, term A3, and GDX12, was changed to W176-26P-20. 6. Figure 3, sheet 2: the wire between D11763, term A3, and GDX12, was changed to W176-26P-20. 7. Figure 5, sheet 2: the wire between D11763, term A3, and GDX12, was changed to W176-26P-20.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 07, 2008 767-78-0096 Revision 1: December 10, 2009 5 of 648. Figure 8, sheet 3, and Figure 9, sheet 3, wire information table for 289T1156-102W: the length of wire W192-16S-22 was increased to 144 inches. 9. Figure 9, sheet 2: the terminal blocks were changed to TB314. 10. Paragraph 3.B, step 15.i: this step was changed to make sure that there are 0 to 3 volts DC between terminal block TB318, position Z26, and the ground in P36 panel. 11. Paragraph 3.B, step 15.j: the EICAS advisory message was changed to "REV ISLN VAL". 12. Paragraph 3.B, step 15.m: the EICAS advisory message was changed to "REV ISLN VAL". 13. Paragraph 3.B, step 15.o: this step was changed to make sure that there are 0 to 3 volts DC between terminal block TB318, position Z26, and the ground in P36 panel. 14. Paragraph 3.B, step 15.q: the EICAS advisory message was changed to "REV ISLN VAL". 15. Paragraph 3.B, step 15.r: this step was changed to disconnect the D14323P connector. 16. Paragraph 3.B, step 15.t: this step was changed to make sure that there are 25 to 32 volts DC between terminal block TB318, position Z26, and the ground in the P36 panel. 17. Paragraph 3.B, step 15.u and step 15.v: these steps were changed to connect the D14323P connector. 18. Paragraph 3.B, step 15.w: this step was changed to make sure that there are 0 to 3 volts DC between terminal block TB318, position Z26, and the ground in P36 panel. 19. Paragraph 3.B, step 15.ab: the EICAS advisory message was changed to "REV ISLN VAL". 20. Paragraph 3.B, step 15.ag: this step was changed to make sure that there are 0 to 3 volts DC between terminal block TB318, position Z26, and the ground in P36 panel. 21. Paragraph 3.B, step 16.i: this step was changed to make sure that there are 0 to 3 volts DC between terminal block TB274, position Z36, and the ground in the P37 panel. 22. Paragraph 3.B, step 16.j: the EICAS advisory message was changed to "ENG 2 REV ISLN VAL". 23. Paragraph 3.B, step 16.m: the EICAS advisory message was changed to "ENG 2 REV ISLN VAL". 24. Paragraph 3.B, step 16.o: this step was changed to make sure that there are 0 to 3 volts DC between terminal block TB274, position Z36, and the ground in the P37 panel. 25. Paragraph 3.B, step 16.q: the EICAS advisory message was changed to "ENG 2 REV ISLN VAL". 26. Paragraph 3.B, step 16.r: this step was changed to disconnect the D14323P connector. 27. Paragraph 3.B, step 16.t: this step was changed to make sure that there are 25 to 32 volts DC between terminal block TB274, position Z36, and the ground in the P37 panel. 28. Paragraph 3.B, step 16.u and step 16.v: these steps were changed to connect the D14323P connector.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 07, 2008 767-78-0096 Revision 1: December 10, 2009 6 of 64 **BOEING SERVICE BULLETIN 767-78-0096**29. Paragraph 3.B, step 16.w: this step was changed to make sure that there are 0 to 3 volts DC between terminal block TB274, position Z36, and the ground in the P37 panel. 30. Paragraph 3.B, step 16.ab: the EICAS advisory message was changed to "ENG 2 REV ISLN VAL". 31. Paragraph 3.B, step 16.ag: this step was changed to make sure that there are 0 to 3 volts DC between terminal block TB274, position Z36, and the ground in the P37 panel. Vertical lines are put on the left edge of each page, except in Paragraph 1.A., Effectivity, to show the location of important changes. Pages with no vertical lines have no important changes. The data given in Information Notice 767-78-0096 IN 01 and Information Notice 767-78-0096 IN02 are included in this revision. **REVISION HISTORY** August 07, 2008 Original Issue: December 10, 2009 Revision 1:

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 07, 2008 767-78-0096 Revision 1: December 10, 2009 7 of 64 **BOEING SERVICE BULLETIN 767-78-0096**BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 07, 2008 767-78-0096 Revision 1: December 10, 2009 8 of 64 **BOEING SERVICE BULLETIN 767-78-0096**

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### Commercial **Airplanes** 

# 767 Service Bulletin **Summary Number: 767-78-0096**  Original Issue: August 07, 2008 Revision 1: December 10, 2009 ATA System: 7834 **SUBJECT:** EXHAUST - Thrust Reverser Control System - Rolls Royce Powered Thrust Reverser Logic, Change **CONCURRENT REQUIREMENTS** Refer to Paragraph 1.B., Concurrent Requirements. **BACKGROUND** This service bulletin gives instructions to change the thrust reverser control logic in the P36 and the P37 panels. The change to the thrust reverser control logic will electrically isolate the number 2 and number 3 locking gear boxes from the air motor brake unlock proximity sensor. This change will prevent a gear box from unlocking when the air motor brake has an uncommanded disengagement. This is done by the removal of the air motor brake release relay from the thrust reverser control circuit. This change also installs a new unstow time delay relay for each engine. The position of the air motor brake, as sensed by the brake proximity sensor, will have no effect on the gear box unlock logic. If the change in this service bulletin is not done, then the number 2 locking gearbox can become unlocked with an associated air motor failure. One operator reported that during takeoff roll an RB211-524 powered 747-400 airplane, the flight crew received the ENG 4 REV LIMTD EICAS status message and the ENG 4 REVERSER advisory and status messages. During climb, the cabin crew saw sparks from the exhaust of the number 4 engine. As a precaution, the flight crew shutdown the number 4 engine and proceeded with an uneventful air turn-back and landing. The event was found to be caused by a failure of the o-rings in the air motor switcher or shutoff solenoid valves because of overheating. This let the air motor shutoff valve open, which released the air motor brake. This, in the ground mode, energized the number 2 and number 3 thrust reverser gear box unlock solenoids and unlocking the number 2 and number 3, gear boxes. As noted previously, the subject event occurred on a 747-400 airplane. However, the thrust reverser system on the RB211 powered 767 is similar to the 747-400 and the 767 thrust reverser system is likely to be susceptible to the same failure mode. Boeing Service Related Problem (SRP) 767-SRP-72-0029 is related to this service bulletin. **ACTION (PRR B12901-77S)** Get access to the P36, P37, and P33 Panels. Add eleven (11) wires, remove five (5), and install one (1) relay socket and one (1) relay, inside the P36 Panel. Add ten (10) wires and remove four (4), and install one (1) relay socket and one (1) relay, inside the P37 Panel. Remove four (4) wires inside the P33 Panel. Remove four (4) wires between the P36 and P37 Panels. Do operational test for each engine. Return access.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 07, 2008 767-78-0096 Revision 1: December 10, 2009 9 of 64**EFFECTIVITY** 767 airplanes powered by Rolls Royce RB211 engines. Refer to Paragraph 1.A.1., Airplanes for the list of affected airplanes. **COMPLIANCE** The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to this service bulletin. The Airworthiness Directive will make the compliance tasks and times given in this service bulletin mandatory. Federal Aviation Administration (FAA) Airworthiness Directive 94-17-03 is related to service bulletin 767-78-0059. Service bulletin 767-78-0059 is related to this service bulletin. Boeing recommends that the change given in this service bulletin be done within 60 months after the date on this service bulletin. **INDUSTRY SUPPORT INFORMATION** Boeing warranty remedies are not available for the configuration changes given in this service bulletin. **MANPOWER Elapsed Hours**  **Task-Hours Task**  18.80 31.30 Group 1 18.80 31.30 Group 2 18.80 31.30 Group 3 18.80 31.30 Group 4 **MATERIAL INFORMATION** Boeing Supplied Kits/Parts. Refer to Paragraph 2.A., Material - Price and Availability.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 07, 2008 767-78-0096 Revision 1: December 10, 2009 10 of 64 **BOEING SERVICE BULLETIN 767-78-0096**BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 07, 2008 767-78-0096 Revision 1: December 10, 2009 11 of 64 **BOEING SERVICE BULLETIN 767-78-0096**BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 07, 2008 767-78-0096 Revision 1: December 10, 2009 12 of 64 **BOEING SERVICE BULLETIN 767-78-0096**

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### Commercial **Airplanes** 

# 767 Service Bulletin **Number: 767-78-0096** Original Issue: August 07, 2008 Revision 1: December 10, 2009 ATA System: 7834 **SUBJECT:** EXHAUST - Thrust Reverser Control System - Rolls Royce Powered Thrust Reverser Logic, Change **1. PLANNING INFORMATION A. Effectivity**  1. Airplanes Refer to Service Bulletin Index Document D624T001 Part 3 for Airplane Variable Number, Line Number, and Serial Number data. This service bulletin is for the airplanes shown below. An equivalent change is on subsequent production airplanes. Refer to PRR B12901-77S for data about this change. **DESCRIPTION CONFIGURATION**  **GROUP** 767 Passenger airplanes powered by Rolls Royce RB211-524 engines. Intent of Boeing service bulletin 767-78-0059 done in production. - 1

767 Passenger airplanes powered by Rolls Royce RB211-524 engines. Prior or concurrent incorporation of Boeing serive bulletin 767-78-0059 is required. Uses a unique terminal track. - 2

767 Passenger airplanes powered by Rolls Royce RB211-524 engines. Intent of Boeing service bulletin 767-78-0059 done in production. Has a unique ground location. - 3

767 Passenger airplanes powered by Rolls Royce RB211-524 engines. Intent of Boeing service bulletin 767-78-0059 done in production. Uses a unique terminal track. - 4

Airplane Models: 767-300 **Group Variable Number**  1 VL871 - VL873

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 07, 2008 767-78-0096 Revision 1: December 10, 2009 13 of 64**Group Variable Number**  2 VN111 - VN123 4 VN124 - VN127 2 VN130 - VN132 4 VN133 1 VN134 - VN137 1 VS246 - VS247 3 VS248 2. Spares Affected None. **B. Concurrent Requirements** The service bulletin listed below must be done before or at the same time as this service bulletin: **Group 2: Description**  **Service Bulletin Company**  Gives instructions to install a second locking gearbox system on the thrust reversers. 767-78-0059 Original Issue, Revision 01, Revision 02, Revision 03. Boeing
The intent of Boeing service bulletin 767-78-0059 was done during production on Group 1, Group 3 and Group 4 airplanes. **C. Reason** This service bulletin gives instructions to change the thrust reverser control logic in the P36 and the P37 panels. The change to the thrust reverser control logic will electrically isolate the number 2 and number 3 locking gear boxes from the air motor brake unlock proximity sensor. This change will prevent a gear box from unlocking when the air motor brake has an uncommanded disengagement. This is done by the removal of the air motor brake release relay from the thrust reverser control circuit. This change also installs a new unstow time delay relay for each engine. The position of the air motor brake, as sensed by the brake proximity sensor, will have no effect on the gear box unlock logic. If the change in this service bulletin is not done, then the number 2 locking gearbox can become unlocked with an associated air motor failure. One operator reported that during takeoff roll an RB211-524 powered 747-400 airplane, the flight crew received the ENG 4 REV LIMTD EICAS status message and the ENG 4 REVERSER advisory and status messages. During climb, the cabin crew saw sparks from the exhaust of the number 4 engine. As a precaution, the flight crew shutdown the number 4 engine and proceeded with an uneventful air turn-back and landing. The event was found to be caused by a failure of the o-rings in the air motor switcher or shutoff solenoid valves because of overheating. This let the air motor shutoff valve open, which released the air motor brake. This, in the ground mode, energized the number 2 and number 3 thrust reverser gear box unlock solenoids and unlocking the number 2 and number 3, gear boxes.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 07, 2008 767-78-0096 Revision 1: December 10, 2009 14 of 64 **BOEING SERVICE BULLETIN 767-78-0096**As noted previously, the subject event occurred on a 747-400 airplane. However, the thrust reverser system on the RB211 powered 767 is similar to the 747-400 and the 767 thrust reverser system is likely to be susceptible to the same failure mode. Boeing Service Related Problem (SRP) 767-SRP-72-0029 is related to this service bulletin. As a part of a service bulletin validation program, this change was completed on airplane VL873 by Service Bulletin 767-78-0096 Original Issue before the release of Revision 01 of this service bulletin. The change completed on airplane VL873 by Service Bulletin 767-78-0096 Original Issue is equivalent to the release of Revision 01 of this service bulletin. Airplane VL873 has the configuration of a Group 1 airplane. Revision 01 is sent to provide operators with the changed service bulletin after the incorporation of the validation findings. During the modification, it was found that a ground block and two terminal blocks were named incorrectly in wiring diagrams in the service bulletin. A wire in the wire kit has been changed because it was too short. Findings during testing led to a partial rewrite of the functional test to change the voltage check locations. It was also found that the EICAS message called out in the functional test of the Service Bulletin was not the correct one. A duplicate wire reference in the service bulletin is also corrected. A maintenance zones table has been added to the service bulletin. The Damage Tolerance Based Structural Inspections table was added. These sections were changed: 1. Paragraph 1.D: a maintenance zones table has been added to the service bulletin. 2. Paragraph 1.K, Publications Affected: The Damage Tolerance Based Structural Inspections impact information was added. 3. Figure 2, sheet 1: ground GDX17-DC has been changed to GDX3-DC. 4. Figure 3, sheet 1: ground GDX9-DC has been changed to GDX3-DC. 5. Figure 2, sheet 2: the wire between D11763, term A3, and GDX12, was changed to W176-26P-20. 6. Figure 3, sheet 2: the wire between D11763, term A3, and GDX12, was changed to W176-26P-20. 7. Figure 5, sheet 2: the wire between D11763, term A3, and GDX12, was changed to W176-26P-20. 8. Figure 8, sheet 3, and Figure 9, sheet 3, wire information table for 289T1156-102W: the length of wire W192-16S-22 was increased to 144 inches. 9. Figure 9, sheet 2: the terminal blocks were changed to TB314. 10. Paragraph 3.B, step 15.i: this step was changed to make sure that there are 0 to 3 volts DC between terminal block TB318, position Z26, and the ground in P36 panel. 11. Paragraph 3.B, step 15.j: the EICAS advisory message was changed to "REV ISLN VAL". 12. Paragraph 3.B, step 15.m: the EICAS advisory message was changed to "REV ISLN VAL". 13. Paragraph 3.B, step 15.o: this step was changed to make sure that there are 0 to 3 volts DC between terminal block TB318, position Z26, and the ground in P36 panel.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 07, 2008 767-78-0096 Revision 1: December 10, 2009 15 of 64 **BOEING SERVICE BULLETIN 767-78-0096**14. Paragraph 3.B, step 15.q: the EICAS advisory message was changed to "REV ISLN VAL". 15. Paragraph 3.B, step 15.r: this step was changed to disconnect the D14323P connector. 16. Paragraph 3.B, step 15.t: this step was changed to make sure that there are 25 to 32 volts DC between terminal block TB318, position Z26, and the ground in the P36 panel. 17. Paragraph 3.B, step 15.u and step 15.v: these steps were changed to connect the D14323P connector. 18. Paragraph 3.B, step 15.w: this step was changed to make sure that there are 0 to 3 volts DC between terminal block TB318, position Z26, and the ground in P36 panel. 19. Paragraph 3.B, step 15.ab: the EICAS advisory message was changed to "REV ISLN VAL". 20. Paragraph 3.B, step 15.ag: this step was changed to make sure that there are 0 to 3 volts DC between terminal block TB318, position Z26, and the ground in P36 panel. 21. Paragraph 3.B, step 16.i: this step was changed to make sure that there are 0 to 3 volts DC between terminal block TB274, position Z36, and the ground in the P37 panel. 22. Paragraph 3.B, step 16.j: the EICAS advisory message was changed to "ENG 2 REV ISLN VAL". 23. Paragraph 3.B, step 16.m: the EICAS advisory message was changed to "ENG 2 REV ISLN VAL". 24. Paragraph 3.B, step 16.o: this step was changed to make sure that there are 0 to 3 volts DC between terminal block TB274, position Z36, and the ground in the P37 panel. 25. Paragraph 3.B, step 16.q: the EICAS advisory message was changed to "ENG 2 REV ISLN VAL". 26. Paragraph 3.B, step 16.r: this step was changed to disconnect the D14323P connector. 27. Paragraph 3.B, step 16.t: this step was changed to make sure that there are 25 to 32 volts DC between terminal block TB274, position Z36, and the ground in the P37 panel. 28. Paragraph 3.B, step 16.u and step 16.v: these steps were changed to connect the D14323P connector. 29. Paragraph 3.B, step 16.w: this step was changed to make sure that there are 0 to 3 volts DC between terminal block TB274, position Z36, and the ground in the P37 panel. 30. Paragraph 3.B, step 16.ab: the EICAS advisory message was changed to "ENG 2 REV ISLN VAL". 31. Paragraph 3.B, step 16.ag: this step was changed to make sure that there are 0 to 3 volts DC between terminal block TB274, position Z36, and the ground in the P37 panel. Vertical lines are put on the left edge of each page, except in Paragraph 1.A., Effectivity, to show the location of important changes. Pages with no vertical lines have no important changes. The data given in Information Notice 767-78-0096 IN 01 and Information Notice 767-78-0096 IN02 are included in this revision.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 07, 2008 767-78-0096 Revision 1: December 10, 2009 16 of 64 **BOEING SERVICE BULLETIN 767-78-0096 D. Description**  Get access to the P36, P37, and P33 Panels. Add eleven (11) wires, remove five (5), and install one (1) relay socket and one (1) relay, inside the P36 Panel. Add ten (10) wires and remove four (4), and install one (1) relay socket and one (1) relay, inside the P37 Panel. Remove four (4) wires inside the P33 Panel. Remove four (4) wires between the P36 and P37 Panels. Do functional test. Return access. No more work is necessary on the airplane changed in accordance with the original issue of this service bulletin. The work in this service bulletin is done in the maintenance zone(s) given below. **Affected Maintenance Zones Zone**  **Model** 119 767-300 **E. Compliance** The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to this service bulletin. The Airworthiness Directive will make the compliance tasks and times given in this service bulletin mandatory. Federal Aviation Administration (FAA) Airworthiness Directive 94-17-03 is related to service bulletin 767-78-0059. Service bulletin 767-78-0059 is related to this service bulletin. Boeing recommends that the change given in this service bulletin be done within 60 months after the date on this service bulletin. **F. Approval** This service bulletin was examined by the Federal Aviation Administration (FAA). The changes specified in this service bulletin comply with the applicable regulations and are FAA approved, as well as European Aviation Safety Agency (EASA)/Joint Aviation Authorities (JAA) approved for all EASA/JAA approved airplanes listed in the service bulletin effectivity. This service bulletin and its approval were based on the airplane in its original Boeing delivery configuration or as modified by other approved Boeing changes. This service bulletin has been approved by the FAA. In addition, the Manager of the FAA Seattle Aircraft Certification Office approves the action (i.e. inspection or modification) defined in this service bulletin as an alternative method of compliance to the requirements of paragraph (c) of FAA AD 94-17-03. All provisions of FAA AD 94-17-03 that are not specifically referenced in the above statement remain fully applicable and must be complied with. If an airplane has a non-Boeing modification or repair that affects a component or system also affected by this service bulletin, the operator is responsible for obtaining appropriate regulatory agency approval before incorporating this service bulletin.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 07, 2008 767-78-0096 Revision 1: December 10, 2009 17 of 64 **BOEING SERVICE BULLETIN 767-78-0096 G. Manpower**  The table below shows an estimate of the task-hours necessary to do this change for each airplane. This estimate is for direct labor only, done by an experienced crew. Adjust the estimate with operator task-hour data if necessary. The estimate does not include lost time. These are some examples of lost time: — Time to adjust to the workplace — Time to schedule the work — Time to examine the work — Time to cure the materials — Time to make the parts — Time to find the tools. This estimate does not include the task-hour data given in the service bulletins in Paragraph 1.B., Concurrent Requirements. **Group 1: Elapsed Hours**  **Task-Hours Number of Per-**  **sons Task** 
0.25 0.25 1 Open Access 1.25 1.25 1 Figure 1 6.35 12.70 2 Figure 2 0.75 0.75 1 Figure 6 1.25 1.25 1 Figure 7 6.15 12.30 2 Figure 9 0.75 0.75 1 Figure 10 0.40 0.40 1 Figure 11 0.40 0.40 1 Figure 12 0.25 0.25 1 Close Access 1.00 1.00 1 Test 18.80 31.30 TOTAL FOR EACH AIRPLANE **Group 2: Elapsed Hours**  **Task-Hours Number of Per-**  **sons Task** 
0.25 0.25 1 Open Access 1.25 1.25 1 Figure 4 6.35 12.70 2 Figure 5 0.75 0.75 1 Figure 6 1.25 1.25 1 Figure 7 6.15 12.30 2 Figure 8

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 07, 2008 767-78-0096 Revision 1: December 10, 2009 18 of 64 **BOEING SERVICE BULLETIN 767-78-0096 Group 2:**  **Elapsed Hours Task-Hours**  **Number of Per- sons**  **Task**
0.75 0.75 1 Figure 10 0.40 0.40 1 Figure 11 0.40 0.40 1 Figure 12 0.25 0.25 1 Close Access 1.00 1.00 1 Test 18.80 31.30 TOTAL FOR EACH AIRPLANE **Group 3: Elapsed Hours**  **Task-Hours Number of Per-**  **sons Task** 
0.25 0.25 1 Open Access 1.25 1.25 1 Figure 1 6.35 12.70 2 Figure 3 0.75 0.75 1 Figure 6 1.25 1.25 1 Figure 7 6.15 12.30 2 Figure 9 0.75 0.75 1 Figure 10 0.40 0.40 1 Figure 11 0.40 0.40 1 Figure 12 0.25 0.25 1 Close Access 1.00 1.00 1 Test 18.80 31.30 TOTAL FOR EACH AIRPLANE **Group 4: Elapsed Hours**  **Task-Hours Number of Per-**  **sons Task** 
0.25 0.25 1 Open Access 1.25 1.25 1 Figure 4 6.35 12.70 2 Figure 5 0.75 0.75 1 Figure 6 1.25 1.25 1 Figure 7 6.15 12.30 2 Figure 8 0.75 0.75 1 Figure 10 0.40 0.40 1 Figure 11

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 07, 2008 767-78-0096 Revision 1: December 10, 2009 19 of 64 **BOEING SERVICE BULLETIN 767-78-0096 Group 4:**  **Elapsed Hours Task-Hours**  **Number of Per- sons**  **Task**
0.40 0.40 1 Figure 12 0.25 0.25 1 Close Access 1.00 1.00 1 Test 18.80 31.30 TOTAL FOR EACH AIRPLANE **H. Weight and Balance Changes Change in Moment**  **(Pound-Inches) Change in Weight**  **(Pounds) Airplane** 
+ 443.9 lbs-in + 2.3 lbs All **I. Electrical Load Data** Not applicable. **J. References** 1. Existing Data: a. Engineering Change Memo PRR B12901-77S b. 767 Aircraft Maintenance Manual (AMM) 24-22-00, 36-00-00, 78-30-00, 78-31-00, 78-31-15, 78-36-04 c. 767 Wiring Diagram Manual (WDM) 78-34-11, 78-34-21 d. Boeing Service Related Problem (SRP) 767-SRP-72-0029 e. Boeing Service Bulletin 767-78-0059 f. Standard Wiring Practices Manual (SWPM) 20-10-11, 20-10-12, 20-10-19, 20-20-00, 20-20-11, 20-61-11, 20-81-12, 20-81-22, 20-90-11 g. Standard Overhaul Practices Manual (SOPM) 20-50-05, 20-50-10 h. Boeing Parts Standards Document D-590 i. Federal Aviation Administration (FAA) Airworthiness Directive 94-17-03 2. Data supplied with this Service Bulletin: None.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 07, 2008 767-78-0096 Revision 1: December 10, 2009 20 of 64 **BOEING SERVICE BULLETIN 767-78-0096**3. Installation Drawings Used in the Preparation of this Service Bulletin: **Title Drawing Number**  EQUIP ASSY - LEFT P36 PANEL 284T0187 EQUIP ASSY - MISC ELEC PANEL LEFT P36 PANEL 284T3601 These drawings were used to prepare this service bulletin. These drawings are not necessary to make the specified changes, and are not supplied with this service bulletin. These drawings may not be applicable to all airplane configurations or operators. **K. Publications Affected** 1. Publications: **Chapter-Section Publication**  78-34-11, 78-34-21 767 Maintenance Manual 78-36 767 Wiring Diagram Manual 78-34 767 Fault Isolation Manual 2. Damage Tolerance Based Structural Inspections: Boeing has evaluated the repairs and/or changes in this service bulletin for effects on Fatigue Critical Structure (FCS) and for changes to Damage Tolerance Inspections (DTI) required in the Maintenance Program. This service bulletin does not affect FCS, therefore DTIs are not necessary.
**L. Interchangeability and Intermixability of Parts** Accomplishment of this service bulletin does not affect interchangeability or intermixability of parts.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 07, 2008 767-78-0096 Revision 1: December 10, 2009 21 of 64 **BOEING SERVICE BULLETIN 767-78-0096**BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 07, 2008 767-78-0096 Revision 1: December 10, 2009 22 of 64 **BOEING SERVICE BULLETIN 767-78-0096**

BLANK PAGE**2. MATERIAL INFORMATION A. Material - Price and Availability**  Boeing can supply the kits shown in Paragraph 2.C., Parts Necessary For Each Airplane. If there is a limit to the quantity (QTY) of available kits, a supply sequence is given by Spares. More kits become available as shown in the Reorder Lead Time (ROLT). ROLT is calculated from the date Boeing gets the purchase order. The kits are subject to the terms and conditions of the Boeing standard purchase order acknowledgment. After the Unit Price date, new price and ROLT data is applicable. Prices are in United States dollars. Terms: Net 30 days. **Reference this service bulletin and submit your purchase order by one of the methods that follow:**  1. Order on-line via ATA Spec 2000 or Boeing Part Page 2. Fax to (206) 662-7145 3. Spares Customer Support - MC 36-65 Boeing Spares Department P.O. Box 3707 Seattle, Washington 98124-2207 USA **Unit Price thru April 30, 2008**  **ROLT (Weeks)**  **QTY Date**  **Name Kit Number**  $2,245 18 1 Aug 1, 2007 Top Kit - RR Powered 767 Un- commanded Thrust Reverser Unlock Events 015T1806-1
$2,245 18 4 Aug 18, 2009 Top Kit - RR Powered 767 Un- commanded Thrust Reverser Unlock Events 015T1806-1

**B. Industry Support Information** Boeing warranty remedies are not available for the configuration changes given in this service bulletin. **C. Parts Necessary For Each Airplane** 1. Kits/Parts: **NOTE:** One top kit is necessary for each airplane. To get the kits/parts shown below, refer to Paragraph 2.A., Material - Price and Availability.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 07, 2008 767-78-0096 Revision 1: December 10, 2009 23 of 64 **BOEING SERVICE BULLETIN 767-78-0096 Kit 015T1806**  **Notes Name**  **QTY New Part Number** **-1** TOP KIT - RR POWERED 767 UNCOMMANDED THRUST REVERSER UNLOCK EVENTS - 015T1806-1
ASSY -101 (W0176) 1 289T1156-101 ASSY -102 (W0192) 1 289T1156-102 LACING TAPE - RED (135C) 100 FT 1 289T9001-21 LACING TAPE - GREEN (135C) 100 FT 1 289T9001-51 TAPE, ID 4 BACT19J4 TIME DELAY RELAY 2 TDH-8120-1001 (a) There are more parts than are necessary.
**Kit 289T1156 Notes**  **Name QTY**  **New Part Number -101**  **-102** ASSY -101 (W0176)
- . 289T1156-101 ASSY -102 (W0192)

. - 289T1156-102 WIRE - RAW MATERIAL 1

. 289T1156-101W WIRE - RAW MATERIAL

. 1 289T1156-102W ID TAPE - CONNECTOR 1

. 289T1156-10101 ID TAPE - CONNECTOR

. 1 289T1156-10102 (a) CONTACT, PIN 3 2 BACC47CN1S (a) CONTACT 4 4 BACC47DE7A (a) CONTACT, SOCKET 12 12 BACC47DJ1 RELAY SOCKET 1 1 BACS16W5A (b) POLYOLEFIN HEAT SHRINKABLE SLEEVE RAW MATERIAL 1 1 M23053/5-106-4 (a) CONTACT, PIN 8 5 M39029-11-145 (a) There are more parts than are necessary. (b) Cut into two inch lengths. 2. Parts and Materials Supplied by the Operator: None.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 07, 2008 767-78-0096 Revision 1: December 10, 2009 24 of 64 **BOEING SERVICE BULLETIN 767-78-0096**3. Parts Modified and Reidentified: None. 4. Parts Removed and Not Replaced: None. **D. Parts Necessary to Change Spares** None. **E. Special Tooling - Price and Availability** None. **F. Special Tooling Necessary to do this Service Bulletin** No special tools or equipment are necessary to do the change in this service bulletin. But, maintenance and overhaul tools in the manuals given in Paragraph 1.J., References, can be necessary. Examine operator tool supply to make sure all necessary tools are available.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 07, 2008 767-78-0096 Revision 1: December 10, 2009 25 of 64 **BOEING SERVICE BULLETIN 767-78-0096**BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 07, 2008 767-78-0096 Revision 1: December 10, 2009 26 of 64 **BOEING SERVICE BULLETIN 767-78-0096**

BLANK PAGE**3. ACCOMPLISHMENT INSTRUCTIONS A. GENERAL INFORMATION**  **CAUTION:** KEEP THE WORK AREA, WIRES AND ELECTRICAL BUNDLES CLEAN OF METAL PARTICLES OR CONTAMINATION WHEN YOU USE TOOLS. UNWANTED MATERIAL, METAL PARTICLES OR CONTAMINATION CAUGHT IN WIRE BUNDLES CAN CAUSE DAMAGE TO THE BUNDLES. DAMAGED WIRE BUNDLES CAN CAUSE SPARKS OR OTHER ELECTRICAL DAMAGE. **NOTE:** 1. Manual titles are referred to by acronyms. Refer to Paragraph 1.J., References, for definition of the acronyms. 2. Obey all of the warnings and cau tions given in the specified manual sections. 3. Unless shown differently, these dimensions and tolerances are used: — Linear dimensions are in inches — Tolerance on linear dimensions, other than rivet and bolt edge margins, is plus or minus 0.03 inch. — Tolerance on rivet and bolt edge margin is plus or minus 0.05 inch — Angular tolerance is plus or minus 2 degrees — Hole dimensions for standard solid rivets are given in 767 Structural Repair Manual, Chapter 51 — Torque limits to tighten nuts and bolts are given in 767 Structural Repair Manual, Chapter 51. 4. For approved fastener and process material substitutions, refer to 767 Structural Repair Manual, Chapter 51. Alternate fasteners are given in 767 Structural Repair Manual Chapter 51 and Boeing Drawing 012W6100. 5. Refer to the Boeing Standard Wiring Practices Manuals SWPM 20-10-11 and SWPM 20-10-12 for the wire installation procedures. 6. If the length of fasteners specified in this service bulletin do not meet the installation standards, fasteners of the same specification, or an approved substitute, one grip length longer or shorter may be used. 7. These work instructions refer to procedures included on other Boeing documents. When the words "refer to" are used and the operator has an accepted alternative procedure, the accepted alternative procedure can be used. When the words "as given in" are included in the instruction, the procedure in the Boeing document must be used.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 07, 2008 767-78-0096 Revision 1: December 10, 2009 27 of 64 **BOEING SERVICE BULLETIN 767-78-0096 B. WORK INSTRUCTIONS**  1. Remove the electrical power from airplane. Refer to Airplane Maintenance Manual 767 AMM 24-22-00 as an accepted procedure. 2. **Group 1, 3:** Get access to the P36 Panel and install one relay socket and one relay, as given in Figure 1. 3. **Group 1:** Do the W176 wiring changes in the P36 Panel, as given in Figure 2. 4. **Group 3:** Do the W176 wiring changes in the P36 Panel, as given in Figure 3. 5. **Group 2, 4:** Get access to the P36 Panel and install one relay socket and one relay, as given in Figure 4. 6. **Group 2, 4:** Do the W176 wiring changes in the P36 Panel, as given in Figure 5. 7. **Group 1-4:** Return access to the P36 Panel, as given in Figure 6. 8. **Group 1-4:** Get access to the P37 Panel and install one relay socket and one relay, as given in Figure 7. 9. **Group 2, 4:** Do the W192 wiring changes in the P37 Panel, as given in Figure 8. 10.**Group 1, 3:** Do the W192 wiring changes in the P37 Panel, as given in Figure 9. 11.**Group 1-4:** Return access to the P37 Panel, as given in Figure 10. 12.**Group 1-4:** Do W144 wiring removal in P33 Panel, as given in Figure 11. 13.**Group 1-4:** Do W572 wiring removal, as given in Figure 12. 14. Return power to airplane. Refer to Airplane Maintenance Manual 767 AMM 24-22-00 as an accepted procedure. 15. Do the following operational test for Engine #1. a. Make sure that there is electrical power applied to the airplane. Refer to 767 AMM 24-22-00 as an accepted procedure. b. Make sure that pneumatic power is not applied to the airplane. Refer to 767 AMM 36-00-00 as an accepted procedure. c. Make sure that the Engine 1 thrust reverser lever is in the stow position.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 07, 2008 767-78-0096 Revision 1: December 10, 2009 28 of 64 **BOEING SERVICE BULLETIN 767-78-0096**d. Deactivate the Engine 1 thrust reverser in the forward thrust position. Refer to 767 AMM 78-31-00 as an accepted procedure. e. Open these circuit breakers on the P11 Circuit Breaker Panel and install DO-NOT-CLOSE tags. **P11 Circuit Breaker Panel**
**Name Circuit Breaker Number**  T/R CONT ENG 1 C1482 T/R CONT ALT ENG 1 C1491 T/R IND ENG 1 C1480 f. Disconnect the connector D14320P from the V225 thrust reverser #3 gear box lock valve solenoid on Engine 1. g. Close these circuit breakers on the P11 Panel and remove the DO-NOT-CLOSE tags. **P11 Circuit Breaker Panel**
**Name Circuit Breaker Number**  T/R CONT ENG 1 C1482 T/R CONT ALT ENG 1 C1491 T/R IND ENG 1 C1480 h. Make sure that there is 0 volts to 3 volts DC between pin number 1 and pin number 2 of connector D14320P. i. Make sure that there is 0 volts to 3 volts DC between terminal block TB318, position Z26, and the ground in the P36 panel. Refer to 767 WDM 78-34-11. j. Make sure the "REV ISLN VAL" EICAS advisory message does not display on the upper EICAS display. k. Release the Engine 1 air motor brake. Pull the air motor brake manual release handle forward and rotate counterclockwise to lock it in the released position. Refer to Airplane Maintenance Manual 767 AMM 78-31-15 as an accepted procedure. l. Wait 15 seconds. m. Make sure the "REV ISLN VAL" EICAS advisory message does display on the upper EICAS display. n. Make sure that there is 0 volts to 3 volts DC between pin number 1 and pin number 2 of connector D14320P. o. Make sure that there is 0 volts to 3 volts DC between terminal block TB318, position Z26, and the ground in the P36 panel.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 07, 2008 767-78-0096 Revision 1: December 10, 2009 29 of 64 **BOEING SERVICE BULLETIN 767-78-0096**p. Manually engage the air motor brake. Pull the air motor brake manual release handle forward and rotate clockwise to lock in the engaged position. Refer to Airplane Maintenance Manual 767 AMM 78-31-15 as an accepted procedure. q. Make sure the "REV ISLN VAL" EICAS advisory message is no longer displayed on the upper EICAS display. r. Disconnect the D14323P connector to the T598 thrust reverser cowl unstowed proximity sensor. Refer to 767 AMM 78-36-04 "STOW PROXIMITY SWITCH SENSOR - REMOVAL/INSTALLATION", as an accepted procedure. s. Make sure that there is 25 volts to 32 volts DC between pin number 1 and pin number 2 of connector D14320P. t. Make sure that there is 25 volts to 32 volts DC between terminal block TB318, position Z26, and the ground in the P36 panel. u. Connect the D14323P connector to the T598 thrust reverser cowl unstowed proximity sensor. Refer to 767 AMM 78-36-04, as an accepted procedure. v. Make sure that there is 0 volts to 3 volts DC between pin number 1 and pin number 2 of connector D14320P. (There will be a one second time delay after connecting the D14323P connector) w. Make sure that there is 0 volts to 3 volts DC between terminal block TB318, position Z26, and the ground in the P36 panel. (There will be a one second time delay after connecting the D14323P connector) x. Do a wiring continuity check between pin number 1 and pin number 2 of connector D14320P to verify that the hot short protection resistance is 10 ohms or less. y. Open these circuit breakers on the P11 Panel and install DO-NOT-CLOSE tags. **P11 Circuit Breaker Panel**
**Name Circuit Breaker Number**  T/R CONT ENG 1 C1482 T/R CONT ALT ENG 1 C1491 T/R IND ENG 1 C1480 z. Connect the connector D14320P to the V225 thrust reverser #3 gear box lock valve solenoid on Engine 1. aa. Close these circuit breakers on the P11 Panel and remove the DO-NOT-CLOSE tags. **P11 Circuit Breaker Panel**
**Name Circuit Breaker Number**  T/R CONT ENG 1 C1482

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 07, 2008 767-78-0096 Revision 1: December 10, 2009 30 of 64 **BOEING SERVICE BULLETIN 767-78-0096 P11 Circuit Breaker Panel** 
**Name Circuit Breaker Number**  T/R CONT ALT ENG 1 C1491 T/R IND ENG 1 C1480 ab. Make sure the "REV ISLN VAL" EICAS advisory message does not display on the upper EICAS display. ac. Install the HP/IP power plant air duct and access panels used to gain access to the T598 thrust reverser unstow proximity sensor. Refer to 767 AMM 78-36-04 as an accepted procedure. ad. Activate the thrust reverser in the forward thrust position. Refer to 767 AMM 78-31-00 as an accepted procedure. ae. Clear thrust reverser EICAS faults. af. Do the operational test of the thrust reverser system using ground or airplane pneumatics (engine not running). Refer to 767 AMM 78-30-00 as an accepted procedure. ag. Make sure that there is 0 volts between terminal block TB318, position Z26, and the ground in the P36 panel. ah. Deploy and stow the ENG 1 thrust reverser three times. ai. Make sure that there are no thrust reverser EICAS faults. 16. Do the following operational test for Engine #2. a. Make sure that there is electrical power applied to the airplane. Refer to 767 AMM 24-22-00 as an accepted procedure. b. Make sure that pneumatic power is not applied to the airplane. Refer to 767 AMM 36-00-00 as an accepted procedure. c. Make sure that the Engine 2 thrust reverser lever is in the stow position. d. Deactivate the Engine 2 thrust reverser in the forward thrust position. Refer to 767 AMM 78-31-00 as an accepted procedure. e. Open these circuit breakers on the P11 Circuit Breaker Panel and install DO-NOT-CLOSE tags. **P11 Circuit Breaker Panel**
**Name Circuit Breaker Number**  T/R CONT ENG 2 C1483 T/R CONT ALT ENG 2 C1479 T/R IND ENG 2 C1481

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 07, 2008 767-78-0096 Revision 1: December 10, 2009 31 of 64 **BOEING SERVICE BULLETIN 767-78-0096 P11 Circuit Breaker Panel** 
**Name Circuit Breaker Number**  T/R IND ALT ENG 2 C1478 f. Disconnect the connector D14320P from the V225 thrust reverser #3 gear box lock valve solenoid on Engine 2. g. Close these circuit breakers on the P11 Panel and remove the DO-NOT-CLOSE tags. **P11 Circuit Breaker Panel**
**Name Circuit Breaker Number**  T/R CONT ENG 2 C1483 T/R CONT ALT ENG 2 C1479 T/R IND ENG 2 C1481 T/R IND ALT ENG 2 C1478 h. Make sure that there is 0 volts to 3 volts DC between pin number 1 and pin number 2 of connector D14320P. i. Make sure that there is 0 volts to 3 volts DC between terminal block TB274, position Z36, and the ground in the P37 panel. Refer to 767 WDM 78-34-21. j. Make sure the "ENG 2 REV ISLN VAL" EICAS advisory message does not display on the upper EICAS display. k. Release the Engine 2 air motor brake. Pull the air motor brake manual release handle forward and rotate counterclockwise to lock it in the released position. Refer to Airplane Maintenance Manual 767 AMM 78-31-15 as an accepted procedure. l. Wait 15 seconds. m. Make sure the "ENG 2 REV ISLN VAL" EICAS advisory message does display on the upper EICAS display. n. Make sure that there is 0 volts to 3 volts DC between pin number 1 and pin number 2 of connector D14320P. o. Make sure that there is 0 volts to 3 volts DC between terminal block TB274, position Z36, and the ground in the P37 panel. p. Manually engage the air motor brake. Pull the air motor brake manual release handle forward and rotate clockwise to lock in the engaged position. Refer to Airplane Maintenance Manual 767 AMM 78-31-15 as an accepted procedure. q. Make sure the "ENG 2 REV ISLN VAL" EICAS advisory message is no longer displayed on the upper EICAS display.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 07, 2008 767-78-0096 Revision 1: December 10, 2009 32 of 64 **BOEING SERVICE BULLETIN 767-78-0096**r. Disconnect the D14323P connector to the T598 thrust reverser cowl unstowed proximity sensor. Refer to 767 AMM 78-36-04 "STOW PROXIMITY SWITCH SENSOR - REMOVAL/INSTALLATION", as an accepted procedure. s. Make sure that there is 25 volts to 32 volts DC between pin number 1 and pin number 2 of connector D14320P. t. Make sure that there is 25 volts to 32 volts DC between terminal block TB274, position Z36, and the ground in the P37 panel. u. Connect the D14323P connector to the T598 thrust reverser cowl unstowed proximity sensor. Refer to 767 AMM 78-36-04, as an accepted procedure. v. Make sure that there is 0 volts to 3 volts DC between pin number 1 and pin number 2 of connector D14320P. (There will be a one second time delay after connecting the D14323P connector) w. Make sure that there is 0 volts to 3 volts DC between terminal block TB274, position Z36, and the ground in the P37 panel. (There will be a one second time delay after connecting the D14323P connector) x. Do a wiring continuity check between pin 1 and pin 2 of connector D14320P to verify that the hot short protection resistance is 10 ohms or less. y. Open these circuit breakers on the P11 Circuit Breaker Panel and install DO-NOT-CLOSE tags. **P11 Circuit Breaker Panel**
**Name Circuit Breaker Number**  T/R CONT ENG 2 C1483 T/R CONT ALT ENG 2 C1479 T/R IND ENG 2 C1481 T/R IND ALT ENG 2 C1478 z. Connect the connector D14320P to the V225 thrust reverser #3 gear box lock valve solenoid on Engine 2. aa. Close these circuit breakers on the P11 Panel and remove the DO-NOT-CLOSE tags. **P11 Circuit Breaker Panel**
**Name Circuit Breaker Number**  T/R CONT ENG 2 C1483 T/R CONT ALT ENG 2 C1479 T/R IND ENG 2 C1481 T/R IND ALT ENG 2 C1478

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 07, 2008 767-78-0096 Revision 1: December 10, 2009 33 of 64 **BOEING SERVICE BULLETIN 767-78-0096**ab. Make sure the "ENG 2 REV ISLN VAL" EICAS advisory message does not display on the upper EICAS display. ac. Install the HP/IP power plant air duct and access panels used to gain access to the T598 thrust reverser unstow proximity sensor. Refer to 767 AMM 78-36-04 as an accepted procedure. ad. Activate the thrust reverser in the forward thrust position. Refer to 767 AMM 78-31-00 as an accepted procedure. ae. Clear thrust reverser EICAS faults. af. Do the operational test of the thrust reverser system using ground or airplane pneumatics (engine not running). Refer to 767 AMM 78-30-00 as an accepted procedure. ag. Make sure that there is 0 volts between terminal block TB274, position Z36, and the ground in the P37 panel. ah. Deploy and stow the ENG 2 thrust reverser three times. ai. Make sure that there are no thrust reverser EICAS faults. 17. Put the airplane back to a serviceable condition.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 07, 2008 767-78-0096 Revision 1: December 10, 2009 34 of 64 **BOEING SERVICE BULLETIN 767-78-0096 This Figure applies only to: Group 1, 3.** 

**FIGURE 1: P36 PANEL-THRUST REVERSER CONTROL, ENGINE 1, RELAY INSTALLATION (SHEET 1 OF 3)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 07, 2008 767-78-0096 Revision 1 December 10, 2009 35 of 64 **BOEING SERVICE BULLETIN 767-78-0096 FIGURE 1: P36 PANEL-THRUST REVERSER CONTROL, ENGINE 1, RELAY INSTALLATION**  **(SHEET 2 OF 3)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 07, 2008 767-78-0096 Revision 1 December 10, 2009 36 of 64 **BOEING SERVICE BULLETIN 767-78-0096**The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary for each airplane. The parts necessary to do this figure are found in Top Kit 015T1806-1, wire kit 289T1156-101. **NOTE:**The relay panel assemblies that hold the relays must not be installed when this figure is completed, because there are wiring changes done behind these panels. The return access to the P36 Panel will do this work in a separate figure. **MORE DATA QTY**  **IDENTIFICATION NAME**  **TASK STEP** 

- 1
- P36 Panel Access 1

- 1
- P36 Panel Door Open 2

- 4
- Screws Remove/Keep 3 Note the orientation of the bonding strap fasteners as they will be installed back onto the panel. 1
- Ground Strap Fasteners Remove/Keep 4

from the relay panel. 1
- Ground Strap Disconnect to get access to the back of the relay panel. Support the relay panel as necessary tonot put strain on the wire bundle. 1
- Relay Panel Move 5

(a) 1 BACS16W5A Relay socket Install (New) 6

- 1 TDH-8120-1001 Relay (K10707) Install (New) 7 above the new relay. Refer toSOPM 20-50-05, as an accepted procedure. 2 BACT19J4 I.D. Tape Install (New) 8
to the I.D. Tape. Refer toSOPM 20-50-10, as an accepted procedure. 1 K10707 Relay Number Apply 9
to the I.D. Tape. Refer toSOPM 20-50-10, as an accepted procedure. 1 D11763 Relay Socket Number Apply 10
The fasteners necessary to install the relay socket and the relay are provided with the new relay socket. Refer to SWPM 20-81-22, as an accepted procedure. (a)

**FIGURE 1: P36 PANEL-THRUST REVERSER CONTROL, ENGINE 1, RELAY INSTALLATION (SHEET 3 OF 3)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 07, 2008 767-78-0096 Revision 1 December 10, 2009 37 of 64 **BOEING SERVICE BULLETIN 767-78-0096 This Figure applies only to: Group 1.** 

**FIGURE 2: P36 PANEL-THRUST REVERSER CONTROL, ENGINE 1, WIRE CHANGE (SHEET 1 OF 3)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 07, 2008 767-78-0096 Revision 1 December 10, 2009 38 of 64 **BOEING SERVICE BULLETIN 767-78-0096**REFERENCE: 767 WDM 78-34-11 The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure. The parts necessary to do this figure are found in top kit 015T1806-1 and wire kit 289T1156-101. **MORE DATA QTY**  **IDENTIFICATION NAME**  **FLAG NOTE**  Refer to SWPM 20-81-12, as an accepted procedure. 10 BACC47DJ1 CONTACT, SOCKET 1

**FIGURE 2: P36 PANEL-THRUST REVERSER CONTROL, ENGINE 1, WIRE CHANGE (SHEET 2 OF 3)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 07, 2008 767-78-0096 Revision 1 December 10, 2009 39 of 64 **BOEING SERVICE BULLETIN 767-78-0096 MORE DATA**  **QTY IDENTIFICATION**  **NAME FLAG**  **NOTE** Refer to SWPM 20-90-11, as an accepted procedure. 7 M39029-11-145 CONTACT, PIN 2 Refer to SWPM 20-61-11, as an accepted procedure. 2 BACC47CN1S CONTACT, PIN 3 Refer to SWPM 20-20-11, as an accepted procedure. 3 BACC47DE7A CONTACT, PIN 4 Cut 16 lengths of 2 inches each. 16 M23053/5-106-4 SLEEVE, HEAT SHRINK 5 "D11763 M/W K10707" 1 289T1156-10101 ID TAPE - CONNECTOR 6 BMS13-54, color red. Operator can use an equivalent material. Refer to SWPM 20-10-19, as an accepted procedure. - 289T9001-21 LACING TAPE 7

**WIRE INFORMATION TABLE FOR 289T1156-101W CUT LENGTH (inches)**  **TYPE CODE MATERIAL SPECIFICATION**  **WIRE NUMBER** 60 PA BMS 13-48, TYPE 10, CLASS 1, AWG 20 W176-26N-20 84 PA BMS 13-48, TYPE 10, CLASS 1, AWG 20 W176-26P-20 84 PA BMS 13-48, TYPE 10, CLASS 1, AWG 20 W176-26Q-20 24 PQ BMS 13-48, TYPE 3, CLASS 1, AWG 22 W176-26R-22 60 PQ BMS 13-48, TYPE 3, CLASS 1, AWG 22 W176-26S-22 84 PQ BMS 13-48, TYPE 3, CLASS 1, AWG 22 W176-26T-22 84 PQ BMS 13-48, TYPE 3, CLASS 1, AWG 22 W176-26U-22 84 PQ BMS 13-48, TYPE 3, CLASS 1, AWG 22 W176-26V-22 108 PQ BMS 13-48, TYPE 3, CLASS 1, AWG 22 W176-26W-22 108 PQ BMS 13-48, TYPE 3, CLASS 1, AWG 22 W176-26X-22 108 PQ BMS 13-48, TYPE 3, CLASS 1, AWG 22 W176-26Y-22

**FIGURE 2: P36 PANEL-THRUST REVERSER CONTROL, ENGINE 1, WIRE CHANGE (SHEET 3 OF 3)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 07, 2008 767-78-0096 Revision 1 December 10, 2009 40 of 64 **BOEING SERVICE BULLETIN 767-78-0096 This Figure applies only to: Group 3.** 

**FIGURE 3: P36 PANEL-THRUST REVERSER CONTROL, ENGINE 1, WIRE CHANGE (SHEET 1 OF 3)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 07, 2008 767-78-0096 Revision 1 December 10, 2009 41 of 64 **BOEING SERVICE BULLETIN 767-78-0096**REFERENCE: 767 WDM 78-34-11 The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure. The parts necessary to do this figure are found in top kit 015T1806-1 and wire kit 289T1156-101. **MORE DATA QTY**  **IDENTIFICATION NAME**  **FLAG NOTE**  Refer to SWPM 20-81-12, as an accepted procedure. 10 BACC47DJ1 CONTACT, SOCKET 1

**FIGURE 3: P36 PANEL-THRUST REVERSER CONTROL, ENGINE 1, WIRE CHANGE (SHEET 2 OF 3)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 07, 2008 767-78-0096 Revision 1 December 10, 2009 42 of 64 **BOEING SERVICE BULLETIN 767-78-0096 MORE DATA**  **QTY IDENTIFICATION**  **NAME FLAG**  **NOTE** Refer to SWPM 20-90-11, as an accepted procedure. 7 M39029-11-145 CONTACT, PIN 2 Refer to SWPM 20-61-11, as an accepted procedure. 2 BACC47CN1S CONTACT, PIN 3 Refer to SWPM 20-20-11, as an accepted procedure. 3 BACC47DE7A CONTACT, PIN 4 Cut 20 lengths of 2 inches each. 1 M23053/5-106-4 SLEEVE, HEAT SHRINK 5 "D11763 M/W K10707" 1 289T1156-10101 ID TAPE - CONNECTOR 6 BMS13-54, color red. Operator can use an equivalent material. Refer to SWPM 20-10-19, as an accepted procedure. - 289T9001-21 LACING TAPE 7

**WIRE INFORMATION TABLE FOR 289T1156-101W CUT LENGTH (inches)**  **TYPE CODE MATERIAL SPECIFICATION**  **WIRE NUMBER** 60 PA BMS 13-48, TYPE 10, CLASS 1, AWG 20 W176-26N-20 84 PA BMS 13-48, TYPE 10, CLASS 1, AWG 20 W176-26P-20 84 PA BMS 13-48, TYPE 10, CLASS 1, AWG 20 W176-26Q-20 24 PQ BMS 13-48, TYPE 3, CLASS 1, AWG 22 W176-26R-22 60 PQ BMS 13-48, TYPE 3, CLASS 1, AWG 22 W176-26S-22 84 PQ BMS 13-48, TYPE 3, CLASS 1, AWG 22 W176-26T-22 84 PQ BMS 13-48, TYPE 3, CLASS 1, AWG 22 W176-26U-22 84 PQ BMS 13-48, TYPE 3, CLASS 1, AWG 22 W176-26V-22 108 PQ BMS 13-48, TYPE 3, CLASS 1, AWG 22 W176-26W-22 108 PQ BMS 13-48, TYPE 3, CLASS 1, AWG 22 W176-26X-22 108 PQ BMS 13-48, TYPE 3, CLASS 1, AWG 22 W176-26Y-22

**FIGURE 3: P36 PANEL-THRUST REVERSER CONTROL, ENGINE 1, WIRE CHANGE (SHEET 3 OF 3)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 07, 2008 767-78-0096 Revision 1 December 10, 2009 43 of 64 **BOEING SERVICE BULLETIN 767-78-0096 This Figure applies only to: Group 2, 4.** 

**FIGURE 4: P36 PANEL-THRUST REVERSER CONTROL, ENGINE 1, RELAY INSTALLATION (SHEET 1 OF 3)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 07, 2008 767-78-0096 Revision 1 December 10, 2009 44 of 64 **BOEING SERVICE BULLETIN 767-78-0096 FIGURE 4: P36 PANEL-THRUST REVERSER CONTROL, ENGINE 1, RELAY INSTALLATION**  **(SHEET 2 OF 3)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 07, 2008 767-78-0096 Revision 1 December 10, 2009 45 of 64 **BOEING SERVICE BULLETIN 767-78-0096**The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary for each airplane. The parts necessary to do this figure are found in Top Kit 015T1806-1 wire kit 289T1156-101. **NOTE:**The relay panel assemblies that hold the relays must not be installed when this figure is completed, because there are wiring changes done behind these panels. The return access to the P36 Panel will do this work in a separate figure. **MORE DATA QTY**  **IDENTIFICATION NAME**  **TASK STEP** 

- 1
- P36 Panel Access 1

- 1
- P36 Panel Door Open 2

- 4
- Screws Remove/Keep 3 Note the orientation of the bonding strap fasteners as they will be installed back onto the panel 1
- Ground Strap Fasteners Remove/Keep 4

from the relay panel. 1
- Ground Strap Disconnect to get access to back of the relay panel. Support the relay panel as necessary to not put strain on the wire bundle. 1
- Relay Panel Move 5

(a) 1 BACS16W5A Relay socket Install (New) 6

- 1 TDH-8120-1001 Relay (K10707) Install (New) 7 below the new relay. Refer toSOPM 20-50-05, as an accepted procedure. 2 BACT19J4 I.D. Tape Install (New) 8
to the I.D. Tape. Refer toSOPM 20-50-10, as an accepted procedure. 1 K10707 Relay Number Apply 9
to the I.D. Tape. Refer toSOPM 20-50-10, as an accepted procedure. 1 D11763 Relay Socket Number Apply 10
The fasteners necessary to install the relay socket and the relay are provided with the new relay socket. Refer to SWPM 20-81-22, as an accepted procedure. (a)

**FIGURE 4: P36 PANEL-THRUST REVERSER CONTROL, ENGINE 1, RELAY INSTALLATION (SHEET 3 OF 3)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 07, 2008 767-78-0096 Revision 1 December 10, 2009 46 of 64 **BOEING SERVICE BULLETIN 767-78-0096 This Figure applies only to: Group 2, 4.** 

**FIGURE 5: P36 PANEL-THRUST REVERSER CONTROL, ENGINE 1, WIRE CHANGE (SHEET 1 OF 3)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 07, 2008 767-78-0096 Revision 1 December 10, 2009 47 of 64 **BOEING SERVICE BULLETIN 767-78-0096**REFERENCE: 767 WDM 78-34-11 The parts necessary to do this figure are found in Top Kit 015T1806-1, wire kit 289T1156-101. **MORE DATA QTY**  **IDENTIFICATION NAME**  **FLAG NOTE**  Refer to SWPM 20-81-12, as an accepted procedure. 10 BACC47DJ1 CONTACT, SOCKET 1

**FIGURE 5: P36 PANEL-THRUST REVERSER CONTROL, ENGINE 1, WIRE CHANGE (SHEET 2 OF 3)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 07, 2008 767-78-0096 Revision 1 December 10, 2009 48 of 64 **BOEING SERVICE BULLETIN 767-78-0096 MORE DATA**  **QTY IDENTIFICATION**  **NAME FLAG**  **NOTE** Refer to SWPM 20-90-11, as an accepted procedure. 7 M39029-11-145 CONTACT, PIN 2 Refer to SWPM 20-61-11, as an accepted procedure. 2 BACC47CN1S CONTACT, PIN 3 Refer to SWPM 20-20-11, as an accepted procedure. 4 BACC47DE7A CONTACT, PIN 4 Cut 20 lengths of 2 inches each. 1 M23053/5-106-4 SLEEVE, HEAT SHRINK 5 "D11763 M/W K10707" 1 289T1156-10101 ID TAPE - CONNECTOR 6 BMS13-54, color red. Operator can use an equivalent material. Refer to SWPM 20-10-19, as an accepted procedure. - 289T9001-21 LACING TAPE 7

**WIRE INFORMATION TABLE FOR 289T1156-101W CUT LENGTH (inches)**  **TYPE CODE MATERIAL SPECIFICATION**  **WIRE NUMBER** 60 PA BMS 13-48, TYPE 10, CLASS 1, AWG 20 W176-26N-20 84 PA BMS 13-48, TYPE 10, CLASS 1, AWG 20 W176-26P-20 84 PA BMS 13-48, TYPE 10, CLASS 1, AWG 20 W176-26Q-20 24 PQ BMS 13-48, TYPE 3, CLASS 1, AWG 22 W176-26R-22 60 PQ BMS 13-48, TYPE 3, CLASS 1, AWG 22 W176-26S-22 84 PQ BMS 13-48, TYPE 3, CLASS 1, AWG 22 W176-26T-22 84 PQ BMS 13-48, TYPE 3, CLASS 1, AWG 22 W176-26U-22 84 PQ BMS 13-48, TYPE 3, CLASS 1, AWG 22 W176-26V-22 108 PQ BMS 13-48, TYPE 3, CLASS 1, AWG 22 W176-26W-22 108 PQ BMS 13-48, TYPE 3, CLASS 1, AWG 22 W176-26X-22 108 PQ BMS 13-48, TYPE 3, CLASS 1, AWG 22 W176-26Y-22

**FIGURE 5: P36 PANEL-THRUST REVERSER CONTROL, ENGINE 1, WIRE CHANGE (SHEET 3 OF 3)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 07, 2008 767-78-0096 Revision 1 December 10, 2009 49 of 64 **BOEING SERVICE BULLETIN 767-78-0096 This Figure applies only to: Group 1-4.** 

**FIGURE 6: P36 PANEL, RETURN ACCESS (SHEET 1 OF 2)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 07, 2008 767-78-0096 Revision 1 December 10, 2009 50 of 64 **BOEING SERVICE BULLETIN 767-78-0096**The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure. **MORE DATA QTY**  **IDENTIFICATION NAME**  **TASK STEP**  Refer to SWPM 20-20-00, as an accepted procedure. 4
- Ground Surface Prepare 1 Make sure the ground strap fasteners are put back to their original configuration or refer to SWPM 20- 20-00, as an accepted procedure. 1
- Ground Strap Connect 2 1
- Ground Strap Fasteners Install (Kept)
back to its original position. 1
- Relay Panel Put 3

- 4
- Screws Install (kept) 4 Make sure that the maximum resistance between an unpainted surface of the P36 Panel and the ground strap on the relay panel is .001 ohm. Prepare the ground surface again if the maximum resistance is higher than .001 ohm. 1
- Resistance Measure 5

- 1
- P36 Panel Door Close 6

**FIGURE 6: P36 PANEL, RETURN ACCESS (SHEET 2 OF 2)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 07, 2008 767-78-0096 Revision 1 December 10, 2009 51 of 64 **BOEING SERVICE BULLETIN 767-78-0096 This Figure applies only to: Group 1-4.** 

**FIGURE 7: P37 PANEL-THRUST REVERSER CONTROL, ENGINE 2, RELAY INSTALLATION (SHEET 1 OF 3)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 07, 2008 767-78-0096 Revision 1 December 10, 2009 52 of 64 **BOEING SERVICE BULLETIN 767-78-0096 FIGURE 7: P37 PANEL-THRUST REVERSER CONTROL, ENGINE 2, RELAY INSTALLATION**  **(SHEET 2 OF 3)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 07, 2008 767-78-0096 Revision 1 December 10, 2009 53 of 64 **BOEING SERVICE BULLETIN 767-78-0096**The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary for each airplane. The parts necessary to do this figure are found in Top Kit 015T1806-1 and wire kit 289T1156-102. **NOTE:**The relay panel assemblies that hold the relays must not be installed when this figure is completed, because there are wiring changes done behind these panels. The return access to the P37 Panel will do this work in a separate figure. **MORE DATA QTY**  **IDENTIFICATION NAME**  **TASK STEP** 

- 1
- P37 Panel Access 1

- 1
- P37 Panel Door Open 2

- 4
- Screws Remove/Keep 3 Note the orientation of the bonding strap fasteners as they will be installed back onto the panel. 1
- Ground Strap Fasteners Remove/Keep 4

from the relay panel. 1
- Bonding Strap Disconnect 4 to get access to back of the panel. Support the relay panel as necessary to notput strain on the wire bundle. 1
- Panel Assembly Move 5

(a) 1 BACS16W5A Relay socket Install (New) 6

- 1 TDH-8120-1001 Relay (K10708) Install (New) 7 above the new relay. Refer to SOPM 20-50-05, as an accepted procedure. 2 BACT19J4 I.D. Tape Install (New) 8
to the I.D. Tape. Refer toSOPM 20-50-10, as an accepted procedure. 1 K10708 Relay Number Apply 9
to the I.D. Tape. Refer toSOPM 20-50-10, as an accepted procedure. 1 D11763 Relay Socket Number Apply 10
The fasteners necessary to install the relay socket and the relay are provided with the new relay socket. Refer to SWPM 20-81-22, as an accepted procedure. (a)

**FIGURE 7: P37 PANEL-THRUST REVERSER CONTROL, ENGINE 2, RELAY INSTALLATION (SHEET 3 OF 3)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 07, 2008 767-78-0096 Revision 1 December 10, 2009 54 of 64 **BOEING SERVICE BULLETIN 767-78-0096 This Figure applies only to: Group 2, 4.** 

**FIGURE 8: P37 PANEL-THRUST REVERSER CONTROL, ENGINE 2, WIRE CHANGE (SHEET 1 OF 3)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 07, 2008 767-78-0096 Revision 1 December 10, 2009 55 of 64 **BOEING SERVICE BULLETIN 767-78-0096**REFERENCE: 767 WDM 78-34-21 The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure. The parts necessary to do this figure are found in top kit 015T1806-1 and wire kit 289T1156-102. **MORE DATA QTY**  **IDENTIFICATION NAME**  **FLAG NOTE**  Refer to SWPM 20-81-12, as an accepted procedure. 11 BACC47DJ1 CONTACT, SOCKET 1

**FIGURE 8: P37 PANEL-THRUST REVERSER CONTROL, ENGINE 2, WIRE CHANGE (SHEET 2 OF 3)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 07, 2008 767-78-0096 Revision 1 December 10, 2009 56 of 64 **BOEING SERVICE BULLETIN 767-78-0096 MORE DATA**  **QTY IDENTIFICATION**  **NAME FLAG**  **NOTE** Refer to SWPM 20-90-11, as an accepted procedure. 5 M39029-11-145 CONTACT, PIN 2 Refer to SWPM 20-61-11, as an accepted procedure. 1 BACC47CN1S CONTACT, PIN 3 Refer to SWPM 20-20-11, as an accepted procedure. 3 BACC47DE7A CONTACT, PIN 4 Cut 20 lengths of 2 inches each. 14 M23053/5-106-4 SLEEVE, HEAT SHRINK 5 "D31546 M/ZW K10708" 1 289T1156-10102 ID TAPE - CONNECTOR 6 BMS13-54, color green. Operator can use an equivalent material. Refer to SWPM 20-10-19, as an accepted procedure. - 289T9001-51 LACING TAPE 7

**WIRE INFORMATION TABLE FOR 289T1156-102W CUT LENGTH (inches)**  **TYPE CODE MATERIAL SPECIFICATION**  **WIRE NUMBER** 36 PA BMS 13-48, TYPE 10, CLASS 1, AWG 20 W192-16K-20 36 PA BMS 13-48, TYPE 10, CLASS 1, AWG 20 W192-16L-20 36 PA BMS 13-48, TYPE 10, CLASS 1, AWG 20 W192-16M-20 24 PQ BMS 13-48, TYPE 3, CLASS 1, AWG 22 W192-16N-22 84 PQ BMS 13-48, TYPE 3, CLASS 1, AWG 22 W192-16P-22 84 PQ BMS 13-48, TYPE 3, CLASS 1, AWG 22 W192-16Q-22 84 PQ BMS 13-48, TYPE 3, CLASS 1, AWG 22 W192-16R-22 144 PQ BMS 13-48, TYPE 3, CLASS 1, AWG 22 W192-16S-22 120 PQ BMS 13-48, TYPE 3, CLASS 1, AWG 22 W192-16T-22 132 PQ BMS 13-48, TYPE 3, CLASS 1, AWG 22 W192-16U-22

**FIGURE 8: P37 PANEL-THRUST REVERSER CONTROL, ENGINE 2, WIRE CHANGE (SHEET 3 OF 3)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 07, 2008 767-78-0096 Revision 1 December 10, 2009 57 of 64 **BOEING SERVICE BULLETIN 767-78-0096 This Figure applies only to: Group 1, 3.** 

**FIGURE 9: P37 PANEL-THRUST REVERSER CONTROL, ENGINE 2, WIRE CHANGE (SHEET 1 OF 3)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 07, 2008 767-78-0096 Revision 1 December 10, 2009 58 of 64 **BOEING SERVICE BULLETIN 767-78-0096**767 WDM 78-34-21 The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure. The parts necessary to do this figure are found in top kit 015T1806-1 and wire kit 289T1156-102. **MORE DATA QTY**  **IDENTIFICATION NAME**  **FLAG NOTE**  Refer to SWPM 20-81-12, as an accepted procedure. 11 BACC47DJ1 CONTACT, SOCKET 1

**FIGURE 9: P37 PANEL-THRUST REVERSER CONTROL, ENGINE 2, WIRE CHANGE (SHEET 2 OF 3)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 07, 2008 767-78-0096 Revision 1 December 10, 2009 59 of 64 **BOEING SERVICE BULLETIN 767-78-0096 MORE DATA**  **QTY IDENTIFICATION**  **NAME FLAG**  **NOTE** Refer to SWPM 20-90-11, as an accepted procedure. 5 M39029-11-145 CONTACT, PIN 2 Refer to SWPM 20-61-11, as an accepted procedure. 1 BACC47CN1S CONTACT, PIN 3 Refer to SWPM 20-20-11, as an accepted procedure. 3 BACC47DE7A CONTACT, PIN 4 Cut 20 lengths of 2 inches each. 14 M23053/5-106-4 SLEEVE, HEAT SHRINK 5 "D31546 M/W K10708" 1 289T1156-10102 ID TAPE - CONNECTOR 6 BMS13-54, color green. Operators can use an equivalent material. Refer to SWPM 20-10-19, as an accepted procedure. - 289T9001-51 LACING TAPE 7

**WIRE INFORMATION TABLE FOR 289T1156-102W CUT LENGTH (inches)**  **TYPE CODE MATERIAL SPECIFICATION**  **WIRE NUMBER** 36 PA BMS 13-48, TYPE 10, CLASS 1, AWG 20 W192-16K-20 36 PA BMS 13-48, TYPE 10, CLASS 1, AWG 20 W192-16L-20 36 PA BMS 13-48, TYPE 10, CLASS 1, AWG 20 W192-16M-20 24 PQ BMS 13-48, TYPE 3, CLASS 1, AWG 22 W192-16N-22 84 PQ BMS 13-48, TYPE 3, CLASS 1, AWG 22 W192-16P-22 84 PQ BMS 13-48, TYPE 3, CLASS 1, AWG 22 W192-16Q-22 84 PQ BMS 13-48, TYPE 3, CLASS 1, AWG 22 W192-16R-22 144 PQ BMS 13-48, TYPE 3, CLASS 1, AWG 22 W192-16S-22 120 PQ BMS 13-48, TYPE 3, CLASS 1, AWG 22 W192-16T-22 132 PQ BMS 13-48, TYPE 3, CLASS 1, AWG 22 W192-16U-22

**FIGURE 9: P37 PANEL-THRUST REVERSER CONTROL, ENGINE 2, WIRE CHANGE (SHEET 3 OF 3)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 07, 2008 767-78-0096 Revision 1 December 10, 2009 60 of 64 **BOEING SERVICE BULLETIN 767-78-0096 This Figure applies only to: Group 1-4.** 

**FIGURE 10: P37, RETURN ACCESS (SHEET 1 OF 2)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 07, 2008 767-78-0096 Revision 1 December 10, 2009 61 of 64 **BOEING SERVICE BULLETIN 767-78-0096**The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure. **MORE DATA QTY**  **IDENTIFICATION NAME**  **TASK STEP**  Refer to SWPM 20-20-00, as an accepted procedure. 4
- Ground Surface Prepare 1 Make sure the ground strap fasteners are put back to their original configuration or refer to SWPM 20- 20-00, as an accepted procedure. 1
- Ground Strap Connect 2 1
- Ground Strap Fasteners Install (Kept)
back to its original position. 1
- Relay Panel Put 3

- 4
- Screws Install (kept) 4 Make sure that the maximum resistance between an unpainted surface of the P37 Panel and the ground strap on the relay panel is .001 ohm. Prepare the ground surface again if the maximum resistance is higher than .001 ohm. 1
- Resistance Measure 5

- 1
- P37 Panel Door Close 6

**FIGURE 10: P37, RETURN ACCESS (SHEET 2 OF 2)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 07, 2008 767-78-0096 Revision 1 December 10, 2009 62 of 64 **BOEING SERVICE BULLETIN 767-78-0096 This Figure applies only to: Group 1-4.** 

767 WDM 78-34-11 Remove the selected wires.

**FIGURE 11: P33 PANEL-THRUST REVERSER CONTROL, WIRE REMOVAL (SHEET 1 OF 1)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 07, 2008 767-78-0096 Revision 1 December 10, 2009 63 of 64 **BOEING SERVICE BULLETIN 767-78-0096 This Figure applies only to: Group 1-4.** 

767 WDM 78-34-11 Remove the selected wires.

**FIGURE 12: P33 TO P36 PANEL-THRUST REVERSER, WIRE REMOVAL (SHEET 1 OF 1)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 07, 2008 767-78-0096 Revision 1 December 10, 2009 64 of 64 **BOEING SERVICE BULLETIN 767-78-0096**