May 03, 2006

Revision 1: April 26, 2007 767-28A0084

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 1 of 44

Commercial

Airplane

Group 767

Service Bulletin

Number: 767-28A0084

Date: May 03, 2006

Revision 1: April 26, 2007

ATA System: 2822 2842

SUBJECT: FUEL SYSTEM - Engine Fuel Feed System - Fuel Pump Inlet Protection - Auxiliary 

Fuel Tank Pump Automatic Shut Off Installation

BOEING PROPRIETARY, CONFIDENTIAL, AND/OR TRADE SECRET

Copyright © 2006 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Unpublished Work - All Rights Reserved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, 707, 717, 727, 737, 747, 757, 767, 777, BBJ, BOEING BUSINESS JET, DC-8, DC-9, DC-10, MD-10, 

MD-11, MD-80, MD-90, the Boeing logo and the Boeing livery are among the trademarks owned by Boeing or 

its subsidiaries. No intellectual property license (express or implied) is granted in connection with this document 

or otherwise.
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 Table of Contents

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BOEING SERVICE BULLETIN 767-28A0084

Table of Contents

Revision Transmittal Sheet . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5

Summary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7

1. PLANNING INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11

A. Effectivity . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11

1. Airplanes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11

2. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12

B. Concurrent Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12

C. Reason . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12

D. Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13

E. Compliance. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13

F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13

G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13

H. Weight and Balance Changes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14

I. Electrical Load Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14

J. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14

1. Existing Data: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14

2. Data supplied with this Service Bulletin: . . . . . . . . . . . . . . . . . . . . . . . . . 14

3. Installation Drawings Used in the Preparation of this Service Bulletin: . . . . . . . . . . 14

K. Publications Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

L. Interchangeability and Intermixability of Parts . . . . . . . . . . . . . . . . . . . . . . . . . 15

2. MATERIAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

A. Material - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

B. Industry Support Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

C. Parts Necessary For Each Airplane . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

1. Kits/Parts: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

2. Parts and Materials Supplied by the Operator: . . . . . . . . . . . . . . . . . . . . . . 21

3. Parts Modified and Reidentified: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21

4. Parts Removed and Not Replaced: . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21

D. Parts Necessary to Change Spares . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21

E. Special Tooling - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21

F. Special Tooling Necessary to do this Service Bulletin . . . . . . . . . . . . . . . . . . . . . 21

3. ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23

A. GENERAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23

B. WORK INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23

FIGURE 1: Relay Bracket Installation P36 PANEL, Group 1 Airplanes . . . . . . . . . . . . . . . . . 25

FIGURE 2: Relay Bracket Installation P37 Panel, Group 1 Airplanes . . . . . . . . . . . . . . . . . . 28

FIGURE 3: Wire Bundle W0176 Changes P36 Panel, Group 1 Airplanes. . . . . . . . . . . . . . . . 31

FIGURE 4: Wire Bundle W0184 Changes P36 Panel, Group 1 Airplanes. . . . . . . . . . . . . . . . 33

FIGURE 5: Relay Installation P36 Panel, Groups 1 Airplanes. . . . . . . . . . . . . . . . . . . . . . 34

FIGURE 6: Wire Bundle W0192 Changes P37 Panel, Group 1 Airplanes. . . . . . . . . . . . . . . . 36

FIGURE 7: Wire Bundle W0188 Changes P37 Panel, Group 1 Airplanes. . . . . . . . . . . . . . . . 38

FIGURE 8: Relay Installation P37 Panel, Groups 1 Airplanes. . . . . . . . . . . . . . . . . . . . . . 39

FIGURE 9: Wire Bundle W0942 Changes P36 Panel to P37 Panel, Group 1 Airplanes . . . . . . . . 41

FIGURE 10: Wire Bundle W0942 routing, P36 panel to P37 panel . . . . . . . . . . . . . . . . . . . 42

FIGURE 11: Wire Bundle W1118 Changes P37 Panel, Group 1 Airplanes . . . . . . . . . . . . . . . 44
 Table of Contents

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BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 5 of 44

Commercial

Airplane

Group 767

Service Bulletin

Number: 767-28A0084 Revision Transmittal Sheet

Date: May 03, 2006

Revision 1: April 26, 2007

ATA System: 2822 2842

SUBJECT: FUEL SYSTEM - Engine Fuel Feed System - Fuel Pump Inlet Protection - Auxiliary 

Fuel Tank Pump Automatic Shut Off Installation

This Revision includes all pages of the service bulletin.

COMPLIANCE INFORMATION RELATED TO THIS REVISION

No more work is necessary on airplanes changed as shown in the initial release of this service bulletin.

REASON FOR REVISION

This revision is sent to address the comments received from operators since the initial release of the service 

bulletin and incorporate differences identified during the the validation of the service bulletin.

As a part of a service bulletin validation program, this change was completed on airplane VQ076 by initial 

release of Service Bulletin 767-28A0084 and before the release of Revision 1 of this service bulletin. The 

change was completed on airplane VQ076 by Service Bulletin 767-28A0084 is equivalent to the Revision 1 of 

this service bulletin. Airplane VQ076 has the configuration of a Group 1 airplane.

The following sections of the service bulletin are changed:

— Weight and Balance table Section1.H, to show new information.

— Material Section 2.A, to show new availability and pricing.

— Accomplishment Instructions Section 3. added Airplane Maintenance Manual (AMM) for Functional Test 

Requirements.

— Figures 1 and 2 removed the bonding requirement for the relay mounting bracket.

— Figures 5 and 8 to clarify the relay location.

Paragraph 1.A., Effectivity, shows changes of airplane operators. Each operator should examine the Effectivity 

paragraph for changes.

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.

REVISION HISTORY

Original Issue: May 03, 2006

Revision 1: April 26, 2007
 

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BOEING SERVICE BULLETIN 767-28A0084

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BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 7 of 44

Commercial

Airplane

Group 767

Service Bulletin

Number: 767-28A0084 Summary

Date: May 03, 2006

Revision 1: April 26, 2007

ATA System: 2822 2842

SUBJECT: FUEL SYSTEM - Engine Fuel Feed System - Fuel Pump Inlet Protection - Auxiliary 

Fuel Tank Pump Automatic Shut Off Installation

CONCURRENT REQUIREMENTS

None.

BACKGROUND

This service bulletin is the result of the safety assessments conducted by Boeing under SFAR 88, "Fuel Tank 

System Fault Tolerance Evaluation Requirements".

Initial results from the Fuel System Safety Analysis show that fuel pumps that run dry could cause an overheat 

condition external of the pump explosion resistance area that is open to the pump inlet. An overheat condition 

in this area could possibly cause an unwanted ignition source for the fuel vapors in the fuel tank. Ignition of 

flammable fuel vapors could cause a fire or explosion which could put the airplane in an unsafe condition. 

Installation of the automatic shut off system adds fuel pump inlet protection against sparks caused by friction 

overheat damage in the fuel tanks.

This service bulletin gives the instructions and a kit of parts to install an automatic shut off system for the center 

wing tank override boost pumps. Installation of the automatic system will prevent a potential ignition source in 

the tank by making sure the pumps do not run for an extended period of time when the fuel level is below pump 

inlet or the pump has failed.

Currently the flight crew turns off the pumps when a pump low pressure message is displayed on EICAS. The 

automatic shut off system installed by this service bulletin will make sure that the pumps will not run for more 

than 15 seconds with continuous low fuel pressure if the flight crew does not respond to the EICAS message 

sooner. The flight crew remains in primary control, with this automatic shut off system as a backup, to turn the 

pumps off after continuous low pressure indication.

This change affects Section 9 of the Maintenance Planning Data (MPD) Document. New Airworthiness 

Limitations (AWL) "28-AWL-20" will be added to Section 9 of the MPD to include a functional check of the center 

tank fuel boost pump automatic shut off system. This change also affects Section 1 and 3.1 of the FAA 

Approved Airplane Flight Manual.

As a part of a service bulletin validation program, this change was completed on airplane VQ076 by initial 

release of Service Bulletin 767-28A0084 and before the release of Revision 1 of this service bulletin. The 

change was completed on airplane VQ076 by Service Bulletin 767-28A0084 is equivalent to the Revision 1 of 

this service bulletin. Airplane VQ076 has the configuration of a Group 1 airplane.
 

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BOEING SERVICE BULLETIN 767-28A0084

ACTION (PRR B13421-4)

In the P36 panel, install a new relay bracket and two new relays. In the P37 panel, install a new relay bracket 

and two new relays. Change the wiring in the P36 panel and P37 panel. Install wiring between the P36 panel 

and P37 panel. Do a functional test.

EFFECTIVITY

All 767-400ER Airplanes. See Service Bulletin Paragraph 1.A.1 for effectivity.

COMPLIANCE

Boeing warranty recommends that the operators incorporate this service bulletin within 36 months after the 

release date on this service bulletin.

INDUSTRY SUPPORT INFORMATION

Boeing warranty remedies are not available for the configuration changes given in this service bulletin.

MANPOWER

MATERIAL INFORMATION

Boeing Supplied Kits/Parts.

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

Airplanes Total Task Hours Elapsed Hours

Group 1 27 13.5
 

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BOEING SERVICE BULLETIN 767-28A0084

CHANGE THE PANEL WIRING.

RELAY BRACKET AND TWO RELAYS.

IN THE P37 PANEL, INSTALL A NEW

CHANGE THE PANEL WIRING.

RELAY BRACKET AND TWO RELAYS.

IN THE P36 PANEL, INSTALL A NEW

MAIN EQUIPMENT CENTER

FWD

498795
 

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Revision 1: April 26, 2007 767-28A0084

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 11 of 44

Commercial

Airplane

Group 767

Service Bulletin

Number: 767-28A0084

Date: May 03, 2006

Revision 1: April 26, 2007

ATA System: 2822 2842

SUBJECT: FUEL SYSTEM - Engine Fuel Feed System - Fuel Pump Inlet Protection - Auxiliary 

Fuel Tank Pump Automatic Shut Off Installation

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 B13421-4 for data about this change.

Airplane models:

767-400ER

IDENTIFICATION BY CUSTOMER, CUSTOMER CODE, GROUP AND VARIABLE NUMBER

CONTINENTAL AIRLINES (CAL)

1 VQ071–VQ086

DELTA AIR LINES (DAL)

1 VQ001–VQ021

IDENTIFICATION BY VARIABLE NUMBER

GROUP CONFIGURATION DESCRIPTION

1 - VQ001-VQ021, VQ071-VQ086 airplanes

Variable Group

VQ001–VQ021 1

VQ071–VQ086 1
 

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BOEING SERVICE BULLETIN 767-28A0084

2. Spares Affected

None.

B. Concurrent Requirements

None.

C. Reason

This service bulletin is the result of the safety assessments conducted by Boeing under SFAR 88, 

"Fuel Tank System Fault Tolerance Evaluation Requirements".

Initial results from the Fuel System Safety Analysis show that fuel pumps that run dry could cause an 

overheat condition external of the pump explosion resistance area that is open to the pump inlet. An 

overheat condition in this area could possibly cause an unwanted ignition source for the fuel vapors 

in the fuel tank. Ignition of flammable fuel vapors could cause a fire or explosion which could put the 

airplane in an unsafe condition. Installation of the automatic shut off system adds fuel pump inlet 

protection against sparks caused by friction overheat damage in the fuel tanks.

This service bulletin gives the instructions and a kit of parts to install an automatic shut off system for 

the center wing tank override boost pumps. Installation of the automatic system will prevent a 

potential ignition source in the tank by making sure the pumps do not run for an extended period of 

time when the fuel level is below pump inlet or the pump has failed.

Currently the flight crew turns off the pumps when a pump low pressure message is displayed on 

EICAS. The automatic shut off system installed by this service bulletin will make sure that the pumps 

will not run for more than 15 seconds with continuous low fuel pressure if the flight crew does not 

respond to the EICAS message sooner. The flight crew remains in primary control, with this automatic 

shut off system as a backup, to turn the pumps off after continuous low pressure indication.

This change affects Section 9 of the Maintenance Planning Data (MPD) Document. New 

Airworthiness Limitations (AWL) "28-AWL-20" will be added to Section 9 of the MPD to include a 

functional check of the center tank fuel boost pump automatic shut off system. This change also 

affects Section 1 and 3.1 of the FAA Approved Airplane Flight Manual.

As a part of a service bulletin validation program, this change was completed on airplane VQ076 by 

initial release of Service Bulletin 767-28A0084 and before the release of Revision 1 of this service 

bulletin. The change was completed on airplane VQ076 by Service Bulletin 767-28A0084 is 

equivalent to the Revision 1 of this service bulletin. Airplane VQ076 has the configuration of a Group 

1 airplane.

Revision 1 is sent to address the comments received from operators since the initial release of the 

service bulletin and incorporate differences identified during the the validation of the service bulletin.

The following sections of the service bulletin are changed:

— Weight and Balance table Section1.H, to show new information.

— Material Section 2.A, to show new availability and pricing.

— Accomplishment Instructions Section 3. added Airplane Maintenance Manual (AMM) for 

Functional Test Requirements.

— Figures 1 and 2 removed the bonding requirement for the relay mounting bracket.

— Figures 5 and 8 to clarify the relay location.
 

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BOEING SERVICE BULLETIN 767-28A0084

D. Description

In the P36 panel, install a new relay bracket and two new relays. In the P37 panel, install a new relay 

bracket and two new relays. Change the wiring in the P36 panel and P37 panel. Install wiring 

between the P36 panel and P37 panel. Do a functional test.

Revision 1 - No more work is necessary on airplanes changed as shown in the initial release of this 

service bulletin.

E. Compliance

Boeing recommends operators incorporate this service bulletin within 36 months after the release date 

on the 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.

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.

G. Manpower

The table below shows an estimate of the task-hours necessary to do this modification 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.

GROUP 1 AIRPLANES

Task

Number of 

Persons Task-Hours Elapsed Hours

Open Access 2 1.0 0.50

Change 2 23 11.5

Close Access 2 1.0 0.50

Test 2 2.0 1.0

TOTAL FOR EACH AIRPLANE 27 13.5
 

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BOEING SERVICE BULLETIN 767-28A0084

H. Weight and Balance Changes

I. Electrical Load Data

Not changed.

J. References

1. Existing Data:

a. Engineering Change Memo PRR B13421-4

b. 767 Aircraft Maintenance Manual (AMM) 24-22-00, 28-22-00, 28-31-00

c. 767 Maintenance Planning Data (MPD) Section 9

d. 767 Structural Repair Manual (SRM), Chapter 51

e. 767 Wiring Diagram 28-22-12, 28-42-12

f. Boeing Drawing 012W6100 

g. Boeing Parts Standards Document D-590

h. Standard Wiring Practices Manual (SWPM) 20-10-11, 20-10-12, 20-10-19, 20-20-00, 

20-30-11, 20-74-12, 20-81-12, 20-81-19, 20-90-11

2. Data supplied with this Service Bulletin:

None.

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

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.

Airplane

Change in Weight 

(Pounds)

Change in Moment 

(Pound-Inches)

Group 1 +2.5 +152.5

Drawing Number Title

284T3600 Panel Installation Left P36 Panel

284T3601 Equip Assy Left P36 Panel

284T3700 Panel Installation Right P37 Panel

284T3701 Equip Assy Right P37 Panel
 

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BOEING SERVICE BULLETIN 767-28A0084

K. Publications Affected

L. Interchangeability and Intermixability of Parts

Accomplishment of this service bulletin does not affect interchangeability or intermixability of parts.

Publication Chapter-Section

767 FAA Approved Airplane Flight Manual *

767 Maintenance Planning Data (MPD) Document Section 6, Section 9

767 Maintenance Manual 28-22

767 Wiring Diagram Manual 28-22-12; 28-42-12

767 Fault Isolation Manual 28-22

767 Schematic Diagram Manual 28-22-01

767 Illustrated Parts Catalog 28-22

* This Change affects Section 1 and 3.1 of the FAA Approved Airplane Flight Manual. Operators 

will receive applicable data.
 

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BOEING SERVICE BULLETIN 767-28A0084

2. MATERIAL INFORMATION

A. Material - Price and Availability

Boeing can supply the kits shown in Paragraph 2.C., Parts Necessary For Each Airplane as shown 

below. 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

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:

To get the kits/parts shown below, refer to Paragraph 2.A., Material - Price and Availability.

Kit Number Name Date QTY

ROLT 

(Weeks)

Unit Price thru

July 31, 07

015T1775-1 Top Kit, Auxiliary Fuel 

Tank Pump Inlet 

Protection Installation, 

Group 1 Airplanes.

AVAILABLE 10 20 $8,311.00
 

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BOEING SERVICE BULLETIN 767-28A0084

NOTE: One top kit and the items shown in Paragraph 2.C.2., Parts and Materials Supplied by

the Operator, are necessary for each airplane.

Kit 015T1775

New Part Number

QTY

Name

Existing Part 

-1 Number Notes

015T1775-1 - Top Kit, Auxiliary Fuel Tank 

Pump Inlet Protection 

Installation, Group 1 Airplanes.

-- --

289T1144-1 1 Wire Kit -- --

284T0378-233 1 Bracket -- --

284T0378-234 1 Bracket -- --

BACR13CD2 2 Relay -- --

TDH-1852-1402 2 Relay -- --

BACS12GU3K7 4 Screw -- (a)

NAS1149D0332H 4 Washer -- --

(a) If grip length shown is not available at Boeing, fasteners supplied in kits may be one grip length 

longer than indicated. Also, if any fasteners part numbers listed are not available or have been 

superseded, substitute fasteners may be supplied in kits. Boeing Document D-590 and Boeing 

Drawing 012W6100 are used to determine the part numbers used as substitutes.

Kit 289T1144

New Part 

Number

QTY

Name

Existing Part 

-104 -103 -102 -1 Number Notes

289T1144-1 . . . - Wire Kit -- (a)

289T1144-102 . . - 1 Subkit (W0176) -- (a)

289T1144-103 . - . 1 Subkit (W0184) -- (a)

289T1144-104 - . . 1 Subkit (W0188) -- (a)

289T1144-102W . . 1 . Wire

289T1144-10201 . . 1 . Lacing Tape -- --

289T1144-10202 . . 1 . Identification Tape -- --

289T1144-10203 . . 1 . Identification Tape -- --

289T1144-10204 . . 1 . Identification Tape -- --

289T1144-10205 . . 1 . Identification Tape -- --

289T1144-10206 . . 1 . Identification Tape -- --

289T1144-10207 . . 1 . Identification Tape -- --

289T1144-10208 . . 1 . Identification Tape -- --

289T1144-10209 . . 1 . Identification Tape -- --

289T1144-10210 . . 1 . Identification Tape -- --

289T1144-10211 . . 1 . Identification Tape -- --

289T1144-103W . 1 . . Wire -- --

289T1144-10301 . 1 . . Lacing Tape -- --
 

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BOEING SERVICE BULLETIN 767-28A0084

289T1144-10302 . 1 . . Identification Tape -- --

289T1144-10303 . 1 . . Identification Tape -- --

289T1144-10304 . 1 . . Identification Tape -- --

289T1144-10305 . 1 . . Identification Tape -- --

289T1144-10306 . 1 . . Identification Tape -- --

289T1144-10307 . 1 . . Identification Tape -- --

289T1144-104W 1 . . . Wire -- --

289T1144-10401 1 . . . Lacing Tape -- --

289T1144-10402 1 . . . Identification Tape -- --

289T1144-10403 1 . . . Identification Tape -- --

289T1144-10404 1 . . . Identification Tape -- --

289T1144-10405 1 . . . Identification Tape -- --

289T1144-10406 1 . . . Identification Tape -- --

289T1144-10407 1 . . . Identification Tape -- --

BACC47CN1S 2 1 . . Contact -- --

M39029/11-145 4 3 11 . Contact -- --

BACS16AG1 . . 1 . Relay Socket -- --

BACS16AH1 . . 1 . Relay Socket -- --

BACT12AR222 . . 1 . Terminal Lug -- --

BACC47FJ2A . . 1 . Contact -- --

BACC47FJ1A 1 . 1 . Contact -- --

BACC47FK1A . 1 2 . Contact -- --

BACC47DJ1 . . 2 . Contact -- --

BACC47ER1 . 1 8 . Contact -- --

BACC47CP1S 2 1 . . Contact -- --

BACC47CN2 . 2 . . Contact -- --

BACC47FJ2A . 1 1 . Contact

(a) There are more parts than necessary.

Kit 289T1144

New Part Number

QTY

Name

Existing Part 

-105 -1 Number Notes

289T1144-1 . - Wire Kit -- (a)

289T1144-105 - 1 Subkit (W0192) -- (a)

289T1144-105W 1 . Wire -- --

289T1144-10501 1 . Lacing tape -- --

289T1144-10502 1 . Identification Tape -- --

Kit 289T1144

New Part 

Number

QTY

Name

Existing Part 

-104 -103 -102 -1 Number Notes
 

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BOEING SERVICE BULLETIN 767-28A0084

289T1144-10503 1 . Identification Tape -- --

289T1144-10504 1 . Identification Tape -- --

289T1144-10505 1 . Identification Tape -- --

289T1144-10506 1 . Identification Tape -- --

289T1144-10507 1 . Identification Tape -- --

289T1144-10508 1 . Identification Tape -- --

M39029/11-145 10 . Contact -- --

BACS16AG1 1 . Relay Socket -- --

BACS16AH1 1 . Relay Socket -- --

BACT12AR222 2 . Terminal Lug -- --

BACC47FJ1A 2 . Contact -- --

BACC47FK1A 1 . Contact -- --

BACC47DJ1 2 . Contact -- --

BACC47ER1 8 . Contact -- --

BACC47CP1S 3 . Contact -- --

Kit 289T1144

New Part 

Number

QTY

Name

Existing Part 

-201 -110 -109 -1 Number Notes

289T1144-1 . . . 1 Wire Kit -- (a)

289T1144-109 . . - 1 Subkit (W0942) -- (a)

289T1144-110 . - . 1 Subkit (W1118) -- (a)

289T1144-201 - . . 1 Spares (a)

289T1144-109W . . 1 . Wire -- --

289T1144-10901 . . 1 . Lacing tape -- --

289T1144-10902 . . 1 . Identification Tape -- --

289T1144-10903 . . 1 . Identification Tape -- --

289T1144-10904 . . 1 . Identification Tape -- --

289T1144-10905 . . 1 . Identification Tape -- --

289T1144-10906 . . 1 . Identification Tape -- --

289T1144-110W . 1 . . Wire -- --

289T1144-11001 . 1 . . Lacing Tape -- --

289T1144-11002 . 1 . . Identification Tape -- --

289T1144-11003 . 1 . . Identification Tape -- --

BACC47CN1S 2 1 1 . Contact -- --

M39029/11-145 2 1 . . Contact -- --

BACT12AR222 2 . . . Terminal Lug -- --

Kit 289T1144

New Part Number

QTY

Name

Existing Part 

-105 -1 Number Notes
 

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2. Parts and Materials Supplied by the Operator:

None.

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.

BACC47FJ2A 2 . . . Contact -- --

BACC47FJ1A 2 1 1 . Contact -- --

BACC47FK1A 2 . 1 . Contact -- --

BACC47DJ1 2 . . . Contact -- --

BACC47ER1 2 . . Contact -- --

BACC47CP1S 2 . 2 . Contact -- --

BACC47CN2 2 . . . Contact -- --

Y-9015-C 1 . . . Eyelet -- --

BACM15C3C 2 . . . Burndy Block -- --

BACM15C3B 2 . . . Burndy Block -- --

(a) There are more parts than necessary.

Kit 289T1144

New Part 

Number

QTY

Name

Existing Part 

-201 -110 -109 -1 Number Notes
 

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BOEING SERVICE BULLETIN 767-28A0084

BLANK PAGE
 

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BOEING SERVICE BULLETIN 767-28A0084

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 cautions 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, and SWPM 20-10-19 for the wire 

separation requirements.

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.

B. WORK INSTRUCTIONS

1. Remove electrical power from the airplane as specified in 767 AMM 24-22-00.

2. Install a new relay bracket in P36 panel as specified in Figure 1.

3. Install a new relay bracket in P37 panel as specified in Figure 2.

4. Make wiring changes (W/B 0176) in P36 panel as specified in Figure 3.

5. Make wiring changes (W/B 0184) in P36 panel as specified in Figure 4.

6. Install two relays in P36 panel as specified in Figure 5.
 

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7. Make wiring changes (W/B 0188) in P37 panel as specified in Figure 6.

8. Make wiring changes (W/B 0192) in P37 panel as specified in Figure 7.

9. Install two relays in P37 Panel as specified in Figure 8.

10. Make wiring changes (W/B 0942) specified in Figure 9. Refer to Figure 10 for wire routing.

11. Make wiring changes (W/B 1118) in P37 panel as specified in Figure 11.

12. Do the following System Test: 

a. Do the "Override Pump Auto Shutoff Functional Test" as given in 767 AMM 28-22-00.

b. Do the "Test of the Left Override/Jettison Pump" as given in 767 AMM 28-31-00.

c. Do the "Test of the Right Override/Jettison Pump" as given in 767 AMM 28-31-00.

13. Install covers on P36 and P37 Panels if not aready installed.

14. Put the airplane back to a serviceable condition.
 FIGURE 1: Relay Bracket Installation P36 PANEL, Group 1 Airplanes

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BOEING SERVICE BULLETIN 767-28A0084

FIGURE 1: Relay Bracket Installation P36 PANEL, Group 1 Airplanes

P36 PANEL

MAIN EQUIPMENT CENTER

A

A

FWD

FWD

1 4

498799

(SHEET 1 OF 3)
 FIGURE 1: Relay Bracket Installation P36 PANEL, Group 1 Airplanes

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A-A

B-B

SUPPORT BRACKET

STANCHION

1.25 ± 0.14

1.70

0.30

STANCHION

SUPPORT BRACKET

B B

FWD

INBD

3

2

FWD

UP

498800

(SHEET 2 OF 3)
 FIGURE 1: Relay Bracket Installation P36 PANEL, Group 1 Airplanes

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BOEING SERVICE BULLETIN 767-28A0084

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 bracket installation on the P36 panel. Use parts 

in Top Kit 015T1775-1.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

1 Remove (Keep) Cover P36 Panel 1 --

2

Install (New) Bracket 284T0378-234 1 Position bracket with 

decal text K10691 and 

K10693 facing inboard.

3

Install (New) Screw BACS12GU3K7 2 Drill .218 - .2290 

diameter Holes.

Washer NAS1149D0332H 2 --

4

Install (Kept) Cover P36 Panel 1 Do not install Cover if 

wiring installation will be 

completed next.

(SHEET 3 OF 3)
 FIGURE 2: Relay Bracket Installation P37 Panel, Group 1 Airplanes

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FIGURE 2: Relay Bracket Installation P37 Panel, Group 1 Airplanes

MAIN EQUIPMENT CENTER

A

A

P37 PANEL

FWD

1

FWD

UP

4

498802

(SHEET 1 OF 3)
 FIGURE 2: Relay Bracket Installation P37 Panel, Group 1 Airplanes

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A-A

B-B

1.25 ± 0.14

0.30

1.70

SUPPORT

BRACKET

STANCHION

SUPPORT

BRACKET

STANCHION

B B

FWD

INBD

2 FWD

UP

3

498803

(SHEET 2 OF 3)
 FIGURE 2: Relay Bracket Installation P37 Panel, Group 1 Airplanes

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BOEING SERVICE BULLETIN 767-28A0084

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 bracket installation on the P37 Panel. Use parts 

in Top Kit 015T1775-1.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

1 Remove (Keep) Cover P37 Panel 1 --

2

Install (New) Bracket 284T0378-233 1 Position bracket with 

decal text K10690 and 

K10692 facing inboard.

3

Install (New) Screw BACS12GU3K7 2 Drill .218 - .2290 diameter 

Holes.

Washer NAS1149D0332H 2

4

Install (Kept) Cover P37 Panel 1 Do not install Cover if 

wiring installation will be 

completed next.

(SHEET 3 OF 3)
 FIGURE 3: Wire Bundle W0176 Changes P36 Panel, Group 1 Airplanes

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BOEING SERVICE BULLETIN 767-28A0084

FIGURE 3: Wire Bundle W0176 Changes P36 Panel, Group 1 Airplanes

REFERENCE: 767 WIRE DIAGRAM 28-42-12

P36 LEFT MISCELLANEOUS ELECTRICAL EQUIPMENT PANEL

K10693 L/H

TIME DELAY

W184

D11631

W176

83U-24

02F-24

AE0209A

C10

J

DA14154P

C5

J

DA14126P

W0942

TB216

YA10

YC10

TB216

4

3

8

5

16

4

K10691 L/H

HOLD RELAY

D11629 TB318

Z9

TB218

YC20

7

TB218

J DB14124P

11

YA20

85W-24 02H-22

K2089 LEFT

JETTISON RLY

K329

OVRD PUMP

CONT RLY

L FUEL

X1

D12156

C1 75W-22

53E-24

75W-22

02H-22

53E-24

YA20

TB218

J

2

DB14128P

02F-24

2

2

5

3

B1

7 83V-24

3 85U-24

83Y-24

85V-24

85J-24

53C-22 86V-22

53C-22

1

4

2

6

9

7

14

13

12

11

10

1

15

(4 LOCATIONS)

(4 LOCATIONS)

3

(10 LOCATIONS)

17 18

498812

(SHEET 1 OF 2)
 FIGURE 3: Wire Bundle W0176 Changes P36 Panel, Group 1 Airplanes

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BOEING SERVICE BULLETIN 767-28A0084

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

NOTE: Use the parts from wire kit 289T1144-102. Route new wiring in the P36 panel following the existing

wire bundle routing, refer to SWPM 20-10-11. Use lacing tape as necessary.

FLAG 

NOTE NAME IDENTIFICATION QTY MORE DATA

1 Contact BACC47ER1 8 SWPM 20-81-19

2 Contact BACC47DJ1 2 SWPM 20-81-12

3 Contact M39029/11-145 11 SWPM 20-90-11

4 Contact BACC47FK1A 2 SWPM 20-74-12

5 Contact BACC47FJ1A 1 SWPM 20-74-12

6 Contact BACC47FJ2A 1 SWPM 20-74-12

7 Terminal Lug BACT12AR222 1 SWPM 20-30-11

8 Relay Socket BACS16AH1 1 SWPM 20-81-19

9 Relay Socket BACS16AG1 1 SWPM 20-81-19

10 Identification Tape 289T1144-10202 1 SWPM 20-10-11

11 Identification Tape 289T1144-10203 1 SWPM 20-10-11

12 Identification Tape 289T1144-10204 1 SWPM 20-10-11

13 Identification Tape 289T1144-10205 1 SWPM 20-10-11

14 Identification Tape 289T1144-10206 1 SWPM 20-10-11

15 Identification Tape 289T1144-10207 1 SWPM 20-10-11

16 Identification Tape 289T1144-10208 1 SWPM 20-10-11

17 Wire 289T1144-102W 1 SWPM 20-10-11

18 Lacing Tape 289T1144-10201 1 SWPM 20-10-11

989752

ADDED WIRE OR NEW ROUTING

EXISTING WIRE

DELETED WIRE OR FORMER ROUTING

(SHEET 2 OF 2)
 FIGURE 4: Wire Bundle W0184 Changes P36 Panel, Group 1 Airplanes

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BOEING SERVICE BULLETIN 767-28A0084

FIGURE 4: Wire Bundle W0184 Changes P36 Panel, Group 1 Airplanes

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

NOTE: Use the parts from wire kit 289T1144-103. Route new wiring in the P36 panel following the existing

wire bundle routing, refer to SWPM 20-10-11. Use lacing tape as necessary.

FLAG 

NOTE NAME IDENTIFICATION QTY MORE DATA

1 Contact BACC47ER1 1 SWPM 20-81-19

2 Contact M39029/11-145 1 SWPM 20-90-11

3 Contact BACC47FJ2A 1 SWPM 20-74-12

4 Contact BACC47FK1A 1 SWPM 20-74-12

5 Identification Tape 289T1144-10302 1 SWPM 20-10-11

6 Identification Tape 289T1144-10303 1 SWPM 20-10-11

7 Identification Tape 289T1144-10304 1 SWPM 20-10-11

8 Wire 289T1144-103W 1 SWPM 20-10-11

9 Lacing Tape 289T1144-10301 1 SWPM 20-10-11

P36 LEFT MISCELLANEOUS ELECTRICAL EQUIPMENT PANEL

K633 OVERRIDE

PUMP GROUND

ENABLE RELAY

D10068

5

AE0209A

J

22

DB14178P

W184

763-24 767-24

TB216

YA10

763-24

1

3

2

YA20

TB218

YC10

TB216

W176 768-24

768-24

J

C1

DA14180P 4

5 6

7

REFERENCE WIRE DIAGRAM 28-22-12

8 9

ADDED WIRE OR NEW ROUTING

EXISTING WIRE

DELETED WIRE OR FORMER ROUTING

498822

(SHEET 1 OF 1)
 FIGURE 5: Relay Installation P36 Panel, Groups 1 Airplanes

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BOEING SERVICE BULLETIN 767-28A0084

FIGURE 5: Relay Installation P36 Panel, Groups 1 Airplanes

P36 PANEL

MAIN EQUIPMENT CENTER

A

A

FWD

FWD

498823

(SHEET 1 OF 2)
 FIGURE 5: Relay Installation P36 Panel, Groups 1 Airplanes

May 03, 2006

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BOEING SERVICE BULLETIN 767-28A0084

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. Use parts from Top Kit 015T1775-1.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

1 Install Relay BACR13CD2 1 --

2 Install Relay TDH-1852-1402 1 --

K10693

K10691

A-A

1

2

FWD

UP

D30103

(SHEET 2 OF 2)
 FIGURE 6: Wire Bundle W0192 Changes P37 Panel, Group 1 Airplanes

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BOEING SERVICE BULLETIN 767-28A0084

FIGURE 6: Wire Bundle W0192 Changes P37 Panel, Group 1 Airplanes

REFERENCE: 767 WIRE DIAGRAM 28-22-12, 28-42-12

P37 RIGHT MISCELLANEOUS ELECTRICAL EQUIPMENT PANEL

K10692 R/H

TIME DELAY

W1118

D31186

78U-24

2

79H-24

5

D6

DA14202P

63E-24

12

YA12

TB212

4

3

14

6

8

K10690 R/H

HOLD RELAY

D31184 TB212

Z17

TB212

Z19

7

TB212

J DA14210P

7

YA14

79X-24 004-24

C1

K2090

W188

J

K330

OVRD PUMP

CONT RLY

R FUEL

X1

D12158

RIGHT

78U-24

004-24

YC14

YC12

TB212

W188

2

2

5

3

TB304

7 79J-24

3 79G-24

79Q-24

79B-24

JETTISON RLY

B1

79V-24

63E-24

63C-22 51B-24 D5

51B-24

1

J

7

4

9

51A-22

11

1

DA14248P

13

63C-22

AE0218A

5

51A-22

10

W192

(4 LOCATIONS)

(4 LOCATIONS)

15 16

3

(11 LOCATIONS)

498833

(SHEET 1 OF 2)
 FIGURE 6: Wire Bundle W0192 Changes P37 Panel, Group 1 Airplanes

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BOEING SERVICE BULLETIN 767-28A0084

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

NOTE: Use the parts from wire kit 289T1144-105 and spares kit 289T1144-201. Route new wiring in the P37

panel following the existing wire bundle routing, refer to SWPM 20-10-11. Use lacing tape as

necessary.

FLAG 

NOTE NAME IDENTIFICATION QTY MORE DATA

1 Contact BACC47ER1 8 SWPM 20-81-19

2 Contact BACC47DJ1 2 SWPM 20-81-12

3 Contact M39029/11-145 12 SWPM 20-90-11

4 Terminal Lug BACT12AR222 1 SWPM 20-30-11

5 Contact BACC47FJ1A 2 SWPM 20-74-12

6 Contact BACC47FK1A 1 SWPM 20-74-12

7 Relay Socket BACS16AH1 1 SWPM 20-81-19

8 Relay Socket BACS16AG1 1 SWPM 20-81-19

9 Identification Tape 289T1144-10502 1 SWPM 20-10-11

10 Identification Tape 289T1144-10503 1 SWPM 20-10-11

11 Identification Tape 289T1144-10504 1 SWPM 20-10-11

12 Identification Tape 289T1144-10506 1 SWPM 20-10-11

13 Identification Tape 289T1144-10507 1 SWPM 20-10-11

14 Identification Tape 289T1144-10508 1 SWPM 20-10-11

15 Wire 289T1144-105W 1 SWPM 20-10-11

16 Lacing Tape 289T1144-10501 1 SWPM 20-10-11

989752

ADDED WIRE OR NEW ROUTING

EXISTING WIRE

DELETED WIRE OR FORMER ROUTING

(SHEET 2 OF 2)
 FIGURE 7: Wire Bundle W0188 Changes P37 Panel, Group 1 Airplanes

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BOEING SERVICE BULLETIN 767-28A0084

FIGURE 7: Wire Bundle W0188 Changes P37 Panel, Group 1 Airplanes

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

NOTE: Use the parts from wire kit 289T1144-104. Route new wiring in the P37 panel following the existing

wire bundle routing, refer to SWPM 20-10-11. Use lacing tape as necessary.

FLAG 

NOTE NAME IDENTIFICATION QTY MORE DATA

1 Contact M39029/11-145 1 SWPM 20-90-11

2 Contact BACC47FJ1A 1 SWPM 20-74-12

3 Identification Tape 289T1144-10407 1 SWPM 20-10-11

4 Wire 289T1144-104W 1 SWPM 20-10-11

5 Lacing Tape 289T1144-10401 1 SWPM 20-10-11

REFERENCE WIRE DIAGRAM 28-42-12

P37 RIGHT MISCELLANEOUS ELECTRICAL EQUIPMENT PANEL

074-22

074-22

AE0218

W192 Z19

TB212

W192 YC14

TB304

J

13

DA14194J

1

2

3

W188 4 5

498825

ADDED WIRE OR NEW ROUTING

EXISTING WIRE

DELETED WIRE OR FORMER ROUTING

(SHEET 1 OF 1)
 FIGURE 8: Relay Installation P37 Panel, Groups 1 Airplanes

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FIGURE 8: Relay Installation P37 Panel, Groups 1 Airplanes

MAIN EQUIPMENT CENTER

A

A

P37 PANEL

FWD

FWD

UP

498836

(SHEET 1 OF 2)
 FIGURE 8: Relay Installation P37 Panel, Groups 1 Airplanes

May 03, 2006

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BOEING SERVICE BULLETIN 767-28A0084

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. Use parts from Top Kit 015T1775-1.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

1 Install Relay BACR13CD2 1 --

2 Install Relay TDH-1852-1402 1 --

A-A

K10692

K10690

FWD

UP

1

2

498838

(SHEET 2 OF 2)
 FIGURE 9: Wire Bundle W0942 Changes P36 Panel to P37 Panel, Group 1 Airplanes

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Revision 1: April 26, 2007 767-28A0084

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BOEING SERVICE BULLETIN 767-28A0084

FIGURE 9: Wire Bundle W0942 Changes P36 Panel to P37 Panel, Group 1 Airplanes

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

NOTE: Use the parts from wire kit 289T1144-109. Reference Figure 10 for wire bundle routing information,

refer toSWPM 20-10-11. Use lacing tape as necessary.

FLAG 

NOTE NAME IDENTIFICATION QTY MORE DATA

1 Contact BACC47FJ1A 1 SWPM 20-74-12

2 Contact BACC47FK1A 1 SWPM 20-74-12

3 Identification Tape 289T1144-10902 1 SWPM 20-10-11

4 Identification Tape 289T1144-10903 1 SWPM 20-10-11

5 Wire 289T1144-109W 1 SWPM 20-10-11

6 Lacing Tape 289T1144-10901 1 SWPM 20-10-11

REFERENCE WIRE DIAGRAM 28-22-12

W176

J DA14154P

C10

AE0209A

W942- 011-24

AE0224A

DA14278

B1

J

W1118

P36 LEFT MISC ELEC P37 RIGHT MISC ELEC

EQUIPMENT PANEL EQUIPMENT PANEL

1 2

3 4 5 6

498845

ADDED WIRE OR NEW ROUTING

EXISTING WIRE

DELETED WIRE OR FORMER ROUTING

(SHEET 1 OF 1)
 FIGURE 10: Wire Bundle W0942 routing, P36 panel to P37 panel

May 03, 2006

Revision 1: April 26, 2007 767-28A0084

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BOEING SERVICE BULLETIN 767-28A0084

FIGURE 10: Wire Bundle W0942 routing, P36 panel to P37 panel 

MAIN EQUIPMENT CENTER

P36 PANEL

P37 PANEL

FWD

1 2

D37092

(SHEET 1 OF 2)
 FIGURE 10: Wire Bundle W0942 routing, P36 panel to P37 panel

May 03, 2006

Revision 1: April 26, 2007 767-28A0084

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BOEING SERVICE BULLETIN 767-28A0084

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. Use lacing tape supplied in kit 

289T1144-109 for wire bundle installation.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

1

Install Wire Bundle 

W0942

-- -- Gain access to the P36 

and P37 panel and 

follow existing routing. 

Refer to SWPM 

20-10-11 and SWPM 

20-10-12 for wire 

installation procedures.

2 Install Lacing Tape 289T1144-10901 -- --

(SHEET 2 OF 2)
 FIGURE 11: Wire Bundle W1118 Changes P37 Panel, Group 1 Airplanes

May 03, 2006

Revision 1: April 26, 2007 767-28A0084

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 44 of 44

BOEING SERVICE BULLETIN 767-28A0084

FIGURE 11: Wire Bundle W1118 Changes P37 Panel, Group 1 Airplanes

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

NOTE: Use the parts from wire kit 289T1144-110. Route new wiring in the P37 panel following the existing

wire bundle routing, refer to SWPM 20-10-11. Use lacing tape as necessary.

FLAG 

NOTE NAME IDENTIFICATION QTY MORE DATA

1 Contact BACC47FJ1A 1 SWPM 20-74-12

2 Contact M39029/11-145 1 SWPM 20-90-11

3 Identification Tape 289T1144-11002 1 SWPM 20-10-11

4 Wire 289T1144-110W 1 SWPM 20-10-11

5 Lacing Tape 289T1144-11001 1 SWPM 20-10-11

REFERENCE WIRE DIAGRAM 28-22-12

3

1

W942

2

AE0224A

DA14278P

B1

J

W192

P37 RIGHT MISCELLANEOUS ELECTRICAL PANEL

TB212

W1118- 14A-24 YC12

4 5

498849

ADDED WIRE OR NEW ROUTING

EXISTING WIRE

DELETED WIRE OR FORMER ROUTING

(SHEET 1 OF 1)