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

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ECCN: 9E991

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Copyright © 2008 The Boeing Company

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3.0
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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

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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

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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.

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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.

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.

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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

Original Issue: August 07, 2008

Revision 1: December 10, 2009

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BOEING SERVICE BULLETIN 767-78-0096

BLANK PAGE
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.

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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

Task Task-Hours Elapsed Hours

Group 1 31.30 18.80

Group 2 31.30 18.80

Group 3 31.30 18.80

Group 4 31.30 18.80

MATERIAL INFORMATION

Boeing Supplied Kits/Parts.

Refer to Paragraph 2.A., Material - Price and Availability.

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BOEING SERVICE BULLETIN 767-78-0096
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BOEING SERVICE BULLETIN 767-78-0096
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BLANK PAGE
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.

GROUP CONFIGURATION DESCRIPTION

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

Variable Number Group

VL871 - VL873 1

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Variable Number Group

VN111 - VN123 2

VN124 - VN127 4

VN130 - VN132 2

VN133 4

VN134 - VN137 1

VS246 - VS247 1

VS248 3

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:

Company Service Bulletin Description

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.

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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.

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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.

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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

Model Zone

767-300 119

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.

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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:

Number of Per- Task-Hours Elapsed Hours

sons

Task

Open Access 1 0.25 0.25

Figure 1 1 1.25 1.25

Figure 2 2 12.70 6.35

Figure 6 1 0.75 0.75

Figure 7 1 1.25 1.25

Figure 9 2 12.30 6.15

Figure 10 1 0.75 0.75

Figure 11 1 0.40 0.40

Figure 12 1 0.40 0.40

Close Access 1 0.25 0.25

Test 1 1.00 1.00

TOTAL FOR EACH AIRPLANE 31.30 18.80

Group 2:

Number of Per- Task-Hours Elapsed Hours

sons

Task

Open Access 1 0.25 0.25

Figure 4 1 1.25 1.25

Figure 5 2 12.70 6.35

Figure 6 1 0.75 0.75

Figure 7 1 1.25 1.25

Figure 8 2 12.30 6.15

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Group 2:

Number of Per- Task-Hours Elapsed Hours

sons

Task

Figure 10 1 0.75 0.75

Figure 11 1 0.40 0.40

Figure 12 1 0.40 0.40

Close Access 1 0.25 0.25

Test 1 1.00 1.00

TOTAL FOR EACH AIRPLANE 31.30 18.80

Group 3:

Number of Per- Task-Hours Elapsed Hours

sons

Task

Open Access 1 0.25 0.25

Figure 1 1 1.25 1.25

Figure 3 2 12.70 6.35

Figure 6 1 0.75 0.75

Figure 7 1 1.25 1.25

Figure 9 2 12.30 6.15

Figure 10 1 0.75 0.75

Figure 11 1 0.40 0.40

Figure 12 1 0.40 0.40

Close Access 1 0.25 0.25

Test 1 1.00 1.00

TOTAL FOR EACH AIRPLANE 31.30 18.80

Group 4:

Number of Per- Task-Hours Elapsed Hours

sons

Task

Open Access 1 0.25 0.25

Figure 4 1 1.25 1.25

Figure 5 2 12.70 6.35

Figure 6 1 0.75 0.75

Figure 7 1 1.25 1.25

Figure 8 2 12.30 6.15

Figure 10 1 0.75 0.75

Figure 11 1 0.40 0.40

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Group 4:

Number of Per- Task-Hours Elapsed Hours

sons

Task

Figure 12 1 0.40 0.40

Close Access 1 0.25 0.25

Test 1 1.00 1.00

TOTAL FOR EACH AIRPLANE 31.30 18.80

H. Weight and Balance Changes

Change in Moment

(Pound-Inches)

Change in Weight

(Pounds)

Airplane

All + 2.3 lbs + 443.9 lbs-in

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.

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3. Installation Drawings Used in the Preparation of this Service Bulletin:

Drawing Number Title

284T0187 EQUIP ASSY - LEFT P36 PANEL

284T3601 EQUIP ASSY - MISC ELEC PANEL LEFT P36 PANEL

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:

Publication Chapter-Section

767 Maintenance Manual 78-34-11, 78-34-21

767 Wiring Diagram Manual 78-36

767 Fault Isolation Manual 78-34

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.

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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)

Kit Number Name Date QTY

Top Kit - RR Powered 767 Un- Aug 1, 2007 1 18 $2,245

commanded Thrust Reverser

Unlock Events

015T1806-1

Top Kit - RR Powered 767 Un- Aug 18, 2009 4 18 $2,245

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.

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BOEING SERVICE BULLETIN 767-78-0096
Kit 015T1806

New Part Number QTY Name Notes

-1

TOP KIT - RR POWERED 767 UNCOMMANDED THRUST REVERSER UNLOCK

EVENTS

015T1806-1 -

289T1156-101 1 ASSY -101 (W0176)

289T1156-102 1 ASSY -102 (W0192)

289T9001-21 1 LACING TAPE - RED (135C) 100 FT

289T9001-51 1 LACING TAPE - GREEN (135C) 100 FT

BACT19J4 4 TAPE, ID

TDH-8120-1001 2 TIME DELAY RELAY

(a) There are more parts than are necessary.

Kit 289T1156

New Part Number QTY Name Notes

-102 -101

289T1156-101 . - ASSY -101 (W0176)

289T1156-102 - . ASSY -102 (W0192)

289T1156-101W . 1 WIRE - RAW MATERIAL

289T1156-102W 1 . WIRE - RAW MATERIAL

289T1156-10101 . 1 ID TAPE - CONNECTOR

289T1156-10102 1 . ID TAPE - CONNECTOR

BACC47CN1S 2 3 CONTACT, PIN (a)

BACC47DE7A 4 4 CONTACT (a)

BACC47DJ1 12 12 CONTACT, SOCKET (a)

BACS16W5A 1 1 RELAY SOCKET

POLYOLEFIN HEAT SHRINKABLE (b)

SLEEVE RAW MATERIAL

M23053/5-106-4 1 1

M39029-11-145 5 8 CONTACT, PIN (a)

(a) There are more parts than are necessary.

(b) Cut into two inch lengths.

2. Parts and Materials Supplied by the Operator:

None.

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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.

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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.

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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.

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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

Circuit Breaker Number Name

C1482 T/R CONT ENG 1

C1491 T/R CONT ALT ENG 1

C1480 T/R IND ENG 1

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

Circuit Breaker Number Name

C1482 T/R CONT ENG 1

C1491 T/R CONT ALT ENG 1

C1480 T/R IND ENG 1

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.

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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

Circuit Breaker Number Name

C1482 T/R CONT ENG 1

C1491 T/R CONT ALT ENG 1

C1480 T/R IND ENG 1

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

Circuit Breaker Number Name

C1482 T/R CONT ENG 1

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P11 Circuit Breaker Panel

Circuit Breaker Number Name

C1491 T/R CONT ALT ENG 1

C1480 T/R IND ENG 1

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

Circuit Breaker Number Name

C1483 T/R CONT ENG 2

C1479 T/R CONT ALT ENG 2

C1481 T/R IND ENG 2

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P11 Circuit Breaker Panel

Circuit Breaker Number Name

C1478 T/R IND ALT ENG 2

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

Circuit Breaker Number Name

C1483 T/R CONT ENG 2

C1479 T/R CONT ALT ENG 2

C1481 T/R IND ENG 2

C1478 T/R IND ALT ENG 2

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.

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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

Circuit Breaker Number Name

C1483 T/R CONT ENG 2

C1479 T/R CONT ALT ENG 2

C1481 T/R IND ENG 2

C1478 T/R IND ALT ENG 2

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

Circuit Breaker Number Name

C1483 T/R CONT ENG 2

C1479 T/R CONT ALT ENG 2

C1481 T/R IND ENG 2

C1478 T/R IND ALT ENG 2

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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.

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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)

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35 of 64

BOEING SERVICE BULLETIN 767-78-0096
FIGURE 1: P36 PANEL-THRUST REVERSER CONTROL, ENGINE 1, RELAY INSTALLATION

(SHEET 2 OF 3)

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Original Issue: August 07, 2008

Revision 1 December 10, 2009 767-78-0096

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.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

1 Access P36 Panel - 1 -

2 Open P36 Panel Door - 1 -

3 Remove/Keep Screws - 4 -

Note the orientation of the

bonding strap fasteners as

they will be installed back onto

the panel.

Ground Strap - 1

Fasteners

4 Remove/Keep

Disconnect Ground Strap - 1 from the relay panel.

to get access to the back of

the relay panel. Support the

relay panel as necessary to

not put strain on the wire bundle.

5 Move Relay Panel - 1

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

7 Install (New) Relay (K10707) TDH-8120-1001 1 -

above the new relay. Refer to

SOPM 20-50-05, as an accepted procedure.

8 Install (New) I.D. Tape BACT19J4 2

to the I.D. Tape. Refer to

SOPM 20-50-10, as an accepted procedure.

9 Apply Relay Number K10707 1

to the I.D. Tape. Refer to

SOPM 20-50-10, as an accepted procedure.

Relay Socket D11763 1

Number

10 Apply

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)

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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)

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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.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-81-12, as an

accepted procedure.

1 CONTACT, SOCKET BACC47DJ1 10

FIGURE 2: P36 PANEL-THRUST REVERSER CONTROL, ENGINE 1, WIRE CHANGE

(SHEET 2 OF 3)

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39 of 64

BOEING SERVICE BULLETIN 767-78-0096
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-90-11, as an

accepted procedure.

2 CONTACT, PIN M39029-11-145 7

Refer to SWPM 20-61-11, as an

accepted procedure.

3 CONTACT, PIN BACC47CN1S 2

Refer to SWPM 20-20-11, as an

accepted procedure.

4 CONTACT, PIN BACC47DE7A 3

5 SLEEVE, HEAT SHRINK M23053/5-106-4 16 Cut 16 lengths of 2 inches each.

6 ID TAPE - CONNECTOR 289T1156-10101 1 "D11763 M/W K10707"

BMS13-54, color red. Operator

can use an equivalent material.

Refer to SWPM 20-10-19, as an

accepted procedure.

7 LACING TAPE 289T9001-21 -

WIRE INFORMATION TABLE FOR 289T1156-101W

WIRE NUMBER MATERIAL SPECIFICATION TYPE CODE CUT LENGTH (inches)

W176-26N-20 BMS 13-48, TYPE 10, CLASS 1, AWG 20 PA 60

W176-26P-20 BMS 13-48, TYPE 10, CLASS 1, AWG 20 PA 84

W176-26Q-20 BMS 13-48, TYPE 10, CLASS 1, AWG 20 PA 84

W176-26R-22 BMS 13-48, TYPE 3, CLASS 1, AWG 22 PQ 24

W176-26S-22 BMS 13-48, TYPE 3, CLASS 1, AWG 22 PQ 60

W176-26T-22 BMS 13-48, TYPE 3, CLASS 1, AWG 22 PQ 84

W176-26U-22 BMS 13-48, TYPE 3, CLASS 1, AWG 22 PQ 84

W176-26V-22 BMS 13-48, TYPE 3, CLASS 1, AWG 22 PQ 84

W176-26W-22 BMS 13-48, TYPE 3, CLASS 1, AWG 22 PQ 108

W176-26X-22 BMS 13-48, TYPE 3, CLASS 1, AWG 22 PQ 108

W176-26Y-22 BMS 13-48, TYPE 3, CLASS 1, AWG 22 PQ 108

FIGURE 2: P36 PANEL-THRUST REVERSER CONTROL, ENGINE 1, WIRE CHANGE

(SHEET 3 OF 3)

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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)

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Original Issue: August 07, 2008

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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.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-81-12, as an

accepted procedure.

1 CONTACT, SOCKET BACC47DJ1 10

FIGURE 3: P36 PANEL-THRUST REVERSER CONTROL, ENGINE 1, WIRE CHANGE

(SHEET 2 OF 3)

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42 of 64

BOEING SERVICE BULLETIN 767-78-0096
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-90-11, as an

accepted procedure.

2 CONTACT, PIN M39029-11-145 7

Refer to SWPM 20-61-11, as an

accepted procedure.

3 CONTACT, PIN BACC47CN1S 2

Refer to SWPM 20-20-11, as an

accepted procedure.

4 CONTACT, PIN BACC47DE7A 3

5 SLEEVE, HEAT SHRINK M23053/5-106-4 1 Cut 20 lengths of 2 inches each.

6 ID TAPE - CONNECTOR 289T1156-10101 1 "D11763 M/W K10707"

BMS13-54, color red. Operator

can use an equivalent material.

Refer to SWPM 20-10-19, as an

accepted procedure.

7 LACING TAPE 289T9001-21 -

WIRE INFORMATION TABLE FOR 289T1156-101W

WIRE NUMBER MATERIAL SPECIFICATION TYPE CODE CUT LENGTH (inches)

W176-26N-20 BMS 13-48, TYPE 10, CLASS 1, AWG 20 PA 60

W176-26P-20 BMS 13-48, TYPE 10, CLASS 1, AWG 20 PA 84

W176-26Q-20 BMS 13-48, TYPE 10, CLASS 1, AWG 20 PA 84

W176-26R-22 BMS 13-48, TYPE 3, CLASS 1, AWG 22 PQ 24

W176-26S-22 BMS 13-48, TYPE 3, CLASS 1, AWG 22 PQ 60

W176-26T-22 BMS 13-48, TYPE 3, CLASS 1, AWG 22 PQ 84

W176-26U-22 BMS 13-48, TYPE 3, CLASS 1, AWG 22 PQ 84

W176-26V-22 BMS 13-48, TYPE 3, CLASS 1, AWG 22 PQ 84

W176-26W-22 BMS 13-48, TYPE 3, CLASS 1, AWG 22 PQ 108

W176-26X-22 BMS 13-48, TYPE 3, CLASS 1, AWG 22 PQ 108

W176-26Y-22 BMS 13-48, TYPE 3, CLASS 1, AWG 22 PQ 108

FIGURE 3: P36 PANEL-THRUST REVERSER CONTROL, ENGINE 1, WIRE CHANGE

(SHEET 3 OF 3)

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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)

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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

Revision 1 December 10, 2009 767-78-0096

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.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

1 Access P36 Panel - 1 -

2 Open P36 Panel Door - 1 -

3 Remove/Keep Screws - 4 -

Note the orientation of the

bonding strap fasteners as

they will be installed back onto

the panel

Ground Strap - 1

Fasteners

4 Remove/Keep

Disconnect Ground Strap - 1 from the relay panel.

to get access to back of the

relay panel. Support the relay

panel as necessary to not put

strain on the wire bundle.

5 Move Relay Panel - 1

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

7 Install (New) Relay (K10707) TDH-8120-1001 1 -

below the new relay. Refer to

SOPM 20-50-05, as an accepted procedure.

8 Install (New) I.D. Tape BACT19J4 2

to the I.D. Tape. Refer to

SOPM 20-50-10, as an accepted procedure.

9 Apply Relay Number K10707 1

to the I.D. Tape. Refer to

SOPM 20-50-10, as an accepted procedure.

Relay Socket D11763 1

Number

10 Apply

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)

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Revision 1 December 10, 2009 767-78-0096

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

Revision 1 December 10, 2009 767-78-0096

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.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-81-12, as an

accepted procedure.

1 CONTACT, SOCKET BACC47DJ1 10

FIGURE 5: P36 PANEL-THRUST REVERSER CONTROL, ENGINE 1, WIRE CHANGE

(SHEET 2 OF 3)

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Original Issue: August 07, 2008

Revision 1 December 10, 2009 767-78-0096

48 of 64

BOEING SERVICE BULLETIN 767-78-0096
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-90-11, as an

accepted procedure.

2 CONTACT, PIN M39029-11-145 7

Refer to SWPM 20-61-11, as an

accepted procedure.

3 CONTACT, PIN BACC47CN1S 2

Refer to SWPM 20-20-11, as an

accepted procedure.

4 CONTACT, PIN BACC47DE7A 4

5 SLEEVE, HEAT SHRINK M23053/5-106-4 1 Cut 20 lengths of 2 inches each.

6 ID TAPE - CONNECTOR 289T1156-10101 1 "D11763 M/W K10707"

BMS13-54, color red. Operator

can use an equivalent material.

Refer to SWPM 20-10-19, as an

accepted procedure.

7 LACING TAPE 289T9001-21 -

WIRE INFORMATION TABLE FOR 289T1156-101W

WIRE NUMBER MATERIAL SPECIFICATION TYPE CODE CUT LENGTH (inches)

W176-26N-20 BMS 13-48, TYPE 10, CLASS 1, AWG 20 PA 60

W176-26P-20 BMS 13-48, TYPE 10, CLASS 1, AWG 20 PA 84

W176-26Q-20 BMS 13-48, TYPE 10, CLASS 1, AWG 20 PA 84

W176-26R-22 BMS 13-48, TYPE 3, CLASS 1, AWG 22 PQ 24

W176-26S-22 BMS 13-48, TYPE 3, CLASS 1, AWG 22 PQ 60

W176-26T-22 BMS 13-48, TYPE 3, CLASS 1, AWG 22 PQ 84

W176-26U-22 BMS 13-48, TYPE 3, CLASS 1, AWG 22 PQ 84

W176-26V-22 BMS 13-48, TYPE 3, CLASS 1, AWG 22 PQ 84

W176-26W-22 BMS 13-48, TYPE 3, CLASS 1, AWG 22 PQ 108

W176-26X-22 BMS 13-48, TYPE 3, CLASS 1, AWG 22 PQ 108

W176-26Y-22 BMS 13-48, TYPE 3, CLASS 1, AWG 22 PQ 108

FIGURE 5: P36 PANEL-THRUST REVERSER CONTROL, ENGINE 1, WIRE CHANGE

(SHEET 3 OF 3)

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BOEING SERVICE BULLETIN 767-78-0096
This Figure applies only to: Group 1-4.

FIGURE 6: P36 PANEL, RETURN ACCESS

(SHEET 1 OF 2)

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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.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

Refer to SWPM 20-20-00, as an

accepted procedure.

1 Prepare Ground Surface - 4

Make sure the ground strap fasteners are put back to their original

configuration or refer to SWPM 20-

20-00, as an accepted procedure.

2 Connect Ground Strap - 1

Ground Strap - 1

Fasteners

Install (Kept)

3 Put Relay Panel - 1 back to its original position.

4 Install (kept) Screws - 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.

5 Measure Resistance - 1

6 Close P36 Panel Door - 1 -

FIGURE 6: P36 PANEL, RETURN ACCESS

(SHEET 2 OF 2)

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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)

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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

Revision 1 December 10, 2009 767-78-0096

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.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

1 Access P37 Panel - 1 -

2 Open P37 Panel Door - 1 -

3 Remove/Keep Screws - 4 -

Note the orientation of the

bonding strap fasteners as

they will be installed back

onto the panel.

Ground Strap - 1

Fasteners

4 Remove/Keep

4 Disconnect Bonding Strap - 1 from the relay panel.

to get access to back of the

panel. Support the relay

panel as necessary to not

put strain on the wire bundle.

5 Move Panel Assembly - 1

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

7 Install (New) Relay (K10708) TDH-8120-1001 1 -

above the new relay. Refer

to SOPM 20-50-05, as an

accepted procedure.

8 Install (New) I.D. Tape BACT19J4 2

to the I.D. Tape. Refer to

SOPM 20-50-10, as an accepted procedure.

9 Apply Relay Number K10708 1

to the I.D. Tape. Refer to

SOPM 20-50-10, as an accepted procedure.

Relay Socket D11763 1

Number

10 Apply

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)

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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

Revision 1 December 10, 2009 767-78-0096

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.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-81-12, as an

accepted procedure.

1 CONTACT, SOCKET BACC47DJ1 11

FIGURE 8: P37 PANEL-THRUST REVERSER CONTROL, ENGINE 2, WIRE CHANGE

(SHEET 2 OF 3)

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Original Issue: August 07, 2008

Revision 1 December 10, 2009 767-78-0096

56 of 64

BOEING SERVICE BULLETIN 767-78-0096
FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-90-11, as an

accepted procedure.

2 CONTACT, PIN M39029-11-145 5

Refer to SWPM 20-61-11, as an

accepted procedure.

3 CONTACT, PIN BACC47CN1S 1

Refer to SWPM 20-20-11, as an

accepted procedure.

4 CONTACT, PIN BACC47DE7A 3

5 SLEEVE, HEAT SHRINK M23053/5-106-4 14 Cut 20 lengths of 2 inches each.

6 ID TAPE - CONNECTOR 289T1156-10102 1 "D31546 M/ZW K10708"

BMS13-54, color green. Operator

can use an equivalent material.

Refer to SWPM 20-10-19, as an

accepted procedure.

7 LACING TAPE 289T9001-51 -

WIRE INFORMATION TABLE FOR 289T1156-102W

WIRE NUMBER MATERIAL SPECIFICATION TYPE CODE CUT LENGTH (inches)

W192-16K-20 BMS 13-48, TYPE 10, CLASS 1, AWG 20 PA 36

W192-16L-20 BMS 13-48, TYPE 10, CLASS 1, AWG 20 PA 36

W192-16M-20 BMS 13-48, TYPE 10, CLASS 1, AWG 20 PA 36

W192-16N-22 BMS 13-48, TYPE 3, CLASS 1, AWG 22 PQ 24

W192-16P-22 BMS 13-48, TYPE 3, CLASS 1, AWG 22 PQ 84

W192-16Q-22 BMS 13-48, TYPE 3, CLASS 1, AWG 22 PQ 84

W192-16R-22 BMS 13-48, TYPE 3, CLASS 1, AWG 22 PQ 84

W192-16S-22 BMS 13-48, TYPE 3, CLASS 1, AWG 22 PQ 144

W192-16T-22 BMS 13-48, TYPE 3, CLASS 1, AWG 22 PQ 120

W192-16U-22 BMS 13-48, TYPE 3, CLASS 1, AWG 22 PQ 132

FIGURE 8: P37 PANEL-THRUST REVERSER CONTROL, ENGINE 2, WIRE CHANGE

(SHEET 3 OF 3)

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This Figure applies only to: Group 1, 3.

FIGURE 9: P37 PANEL-THRUST REVERSER CONTROL, ENGINE 2, WIRE CHANGE

(SHEET 1 OF 3)

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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.

FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-81-12, as an

accepted procedure.

1 CONTACT, SOCKET BACC47DJ1 11

FIGURE 9: P37 PANEL-THRUST REVERSER CONTROL, ENGINE 2, WIRE CHANGE

(SHEET 2 OF 3)

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FLAG NAME IDENTIFICATION QTY MORE DATA

NOTE

Refer to SWPM 20-90-11, as an

accepted procedure.

2 CONTACT, PIN M39029-11-145 5

Refer to SWPM 20-61-11, as an

accepted procedure.

3 CONTACT, PIN BACC47CN1S 1

Refer to SWPM 20-20-11, as an

accepted procedure.

4 CONTACT, PIN BACC47DE7A 3

5 SLEEVE, HEAT SHRINK M23053/5-106-4 14 Cut 20 lengths of 2 inches each.

6 ID TAPE - CONNECTOR 289T1156-10102 1 "D31546 M/W K10708"

BMS13-54, color green. Operators can use an equivalent material. Refer to SWPM 20-10-19, as

an accepted procedure.

7 LACING TAPE 289T9001-51 -

WIRE INFORMATION TABLE FOR 289T1156-102W

WIRE NUMBER MATERIAL SPECIFICATION TYPE CODE CUT LENGTH (inches)

W192-16K-20 BMS 13-48, TYPE 10, CLASS 1, AWG 20 PA 36

W192-16L-20 BMS 13-48, TYPE 10, CLASS 1, AWG 20 PA 36

W192-16M-20 BMS 13-48, TYPE 10, CLASS 1, AWG 20 PA 36

W192-16N-22 BMS 13-48, TYPE 3, CLASS 1, AWG 22 PQ 24

W192-16P-22 BMS 13-48, TYPE 3, CLASS 1, AWG 22 PQ 84

W192-16Q-22 BMS 13-48, TYPE 3, CLASS 1, AWG 22 PQ 84

W192-16R-22 BMS 13-48, TYPE 3, CLASS 1, AWG 22 PQ 84

W192-16S-22 BMS 13-48, TYPE 3, CLASS 1, AWG 22 PQ 144

W192-16T-22 BMS 13-48, TYPE 3, CLASS 1, AWG 22 PQ 120

W192-16U-22 BMS 13-48, TYPE 3, CLASS 1, AWG 22 PQ 132

FIGURE 9: P37 PANEL-THRUST REVERSER CONTROL, ENGINE 2, WIRE CHANGE

(SHEET 3 OF 3)

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This Figure applies only to: Group 1-4.

FIGURE 10: P37, RETURN ACCESS

(SHEET 1 OF 2)

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The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

Refer to SWPM 20-20-00, as an

accepted procedure.

1 Prepare Ground Surface - 4

Make sure the ground strap fasteners are put back to their original

configuration or refer to SWPM 20-

20-00, as an accepted procedure.

2 Connect Ground Strap - 1

Ground Strap - 1

Fasteners

Install (Kept)

3 Put Relay Panel - 1 back to its original position.

4 Install (kept) Screws - 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.

5 Measure Resistance - 1

6 Close P37 Panel Door - 1 -

FIGURE 10: P37, RETURN ACCESS

(SHEET 2 OF 2)

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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)

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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)

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BOEING SERVICE BULLETIN 767-78-0096