Original Issue: March 15, 2007

Revision 2: August 13, 2009 747-28A2262

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 1 of 91

Commercial

Airplanes 747

Service Bulletin

Number: 747-28A2262

Original Issue: March 15, 2007

Revision 2: August 13, 2009

ATA System: 2817

SUBJECT: FUEL - Horizontal Stabilizer Tank Fuel Transfer System - Automatic Pump Shutoff 

Change

BOEING PROPRIETARY, CONFIDENTIAL, AND/OR TRADE SECRET

Copyright © 2007 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Unpublished Work - All Rights Reserved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, 

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 Table of Contents

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BOEING SERVICE BULLETIN 747-28A2262

Table of Contents

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

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

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

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

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

2. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18

B. Concurrent Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18

C. Reason . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

D. Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21

E. Compliance. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21

F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22

G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22

H. Weight and Balance Changes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23

I. Electrical Load Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23

J. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23

1. Existing Data: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23

2. Data supplied with this Service Bulletin: . . . . . . . . . . . . . . . . . . . . . . . . . 23

3. Installation Drawings Used in the Preparation of this Service Bulletin: . . . . . . . . . . 24

K. Publications Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 24

L. Interchangeability and Intermixability of Parts . . . . . . . . . . . . . . . . . . . . . . . . . 25

2. MATERIAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27

A. Material - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27

B. Industry Support Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27

C. Parts Necessary For Each Airplane . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27

1. Kits/Parts: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27

2. Parts and Materials Supplied by the Operator: . . . . . . . . . . . . . . . . . . . . . . 29

3. Parts Modified and Reidentified: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29

4. Parts Removed and Not Replaced: . . . . . . . . . . . . . . . . . . . . . . . . . . . . 30

D. Parts Necessary to Change Spares . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 30

E. Special Tooling - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . 30

F. Special Tooling Necessary to do this Service Bulletin . . . . . . . . . . . . . . . . . . . . . 30

3. ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 31

A. GENERAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 31

B. WORK INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 31

FIGURE 1: Change the E-8 Aft Equipment Center . . . . . . . . . . . . . . . . . . . . . . . . . . . 38

FIGURE 2: E-8 Wiring Changes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 41

FIGURE 3: Relay Installation, E-8 Aft Equipment Center . . . . . . . . . . . . . . . . . . . . . . . . 45

FIGURE 4: Ship’s Wiring Installation. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 48

FIGURE 5: Ship’s Wiring Changes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 50

FIGURE 6: P414 Panel Wiring Changes. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 52

FIGURE 7: P415 Panel Wiring Changes. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 54

FIGURE 8: MAWEA Card File Wiring Changes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 56

FIGURE 9: E2-6 Shelf Wiring Changes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 57

FIGURE 10: E2-6 Shelf Wire Integration Unit Wiring Changes . . . . . . . . . . . . . . . . . . . . . 59

FIGURE 11: E2-6 Shelf Wiring Changes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 64
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BOEING SERVICE BULLETIN 747-28A2262

FIGURE 12: E2-6 Shelf Wire Integration Unit Wiring Changes. . . . . . . . . . . . . . . . . . . . . . 66

FIGURE 13: E2-6 Shelf Wiring Changes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 71

FIGURE 14: E2-6 Shelf Wiring Changes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 73

FIGURE 15: E2-6 Shelf Wire Integration Unit Wiring Changes. . . . . . . . . . . . . . . . . . . . . . 75

FIGURE 16: E2-6 Shelf Wire Integration Unit Wiring Changes. . . . . . . . . . . . . . . . . . . . . . 81

FIGURE 17: Relay Bracket Installation . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 86

FIGURE 18: Relay Installation, E-8 Aft Equipment Center . . . . . . . . . . . . . . . . . . . . . . . . 89

FIGURE 19: P414 Panel Wiring Changes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 91
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Commercial

Airplanes 747

Service Bulletin

Number: 747-28A2262 Revision Transmittal Sheet

Original Issue: March 15, 2007

Revision 2: August 13, 2009

ATA System: 2817

SUBJECT: FUEL - Horizontal Stabilizer Tank Fuel Transfer System - Automatic Pump Shutoff 

Change

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 original issue or Revision 1 of this service 

bulletin.

Federal Aviation Administration (FAA) Airworthiness Directive 2007-13-04 is related to this service bulletin.

REASON FOR REVISION

This revision is sent to address comments received from operators since the original issue and Revision 1 of 

the service bulletin.

Airplane RT671 was moved from Group 7 to new Group 8.

Airplane RT703 was moved from Group 1 to new Group 9.

Boeing found the Work Instructions B.4, B.5 and B.7 through B.16 in Revision 1, did not agree with the figure 

numbers given in the service bulletin. After investigating, Boeing found that during the preparation of Revision 

1, the Figure 2 was inadvertently moved to a different part of the service bulletin. This caused the figures to 

renumber according to their order of placement in the service bulletin. This revision restores the Figure 2 into 

its correct location in the document. This restores the correct figure number assigned to the Figure. The figure 

numbers 1 through 16 in Revision 2 agree with the figure numbers in the original issue of service bulletin 747-

28A2262.

The following sections of the service bulletin were changed:

1. Groups 8 and 9 were added to Group and Configuration tables in Section 1, Manpower table, Weight and 

Balance table and Material Information Section 2 where applicable.

2. Compliance and Approval section, removed reference to Airworthiness Directive 2002-24-51 and 

Airworthiness Directive 2002-24-52 which are superseded by Airworthiness Directive 2007-13-04.

3. Compliance statements in the Summary and Planning sections were revised with the wording "original 

issue date".
 

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BOEING SERVICE BULLETIN 747-28A2262

4. Material Information Section 2, Parts and Material Supplied by Operator, Added, contact BACC47CP3S as 

operator supplied for airplanes RT043-RT047 and RT433-RT477 only.

5. Accomplishment Instruction Section 3:

— added Step B.9, for new Groups 8 and 9.

— added Group 8 to Work Instruction Steps B.3-B.4, B.6-B.7, B.9-B.11, B.17-B.18.

— added Group 9 to Work Instruction Steps B.2, B.4-B.5, B.7, B.9-B.13.

6. Revised Figures numbers 2 through 14:

— Figure 2, restored to Figure 3.

— Figure 3, restored to Figure 4.

— Figure 4, restored to Figure 5.

— Figure 5, restored to Figure 6.

— Figure 6, restored to Figure 7.

— Figure 7, restored to Figure 8.

— Figure 8, restored to Figure 9.

— Figure 9, restored to Figure 10.

— Figure 10, restored to Figure 11.

— Figure 11, restored to Figure 12.

— Figure 12, restored to Figure 13.

— Figure 13, restored to Figure 14.

— Figure 14, restored to Figure 2.

7. Figures 2, 4-5, 7-8, 14-15, 17-19 added Group 8 applicability.

8. Figures 1-5, 7-10 and 19 added Group 9 applicability.

9. Figures 2, revised Flag Note 3, contact part number should be BACC47CP3S for connector D40106J.

10. Figures 6 and 7, added information note for ground block if existing ground block is full.

11. Added new Figure 19, to show wire W3846-595-20 connected to GDX2-DC. Added information note for 

ground block if existing ground block is full.

The data given in Information Notice 767-28-2262 IN 04 is included in this revision. The information Notice IN 

03 was corrected in IN 04

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: March 15, 2007

Revision 1: May 8, 2008

Revision 2: August 13, 2009
Original Issue: March 15, 2007

Revision 2: August 13, 2009 747-28A2262

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Commercial

Airplanes 747

Service Bulletin

Number: 747-28A2262 Summary

Original Issue: March 15, 2007

Revision 2: August 13, 2009

ATA System: 2817

SUBJECT: FUEL - Horizontal Stabilizer Tank Fuel Transfer System - Automatic Pump Shutoff 

Change

CONCURRENT REQUIREMENTS

Boeing service bulletin 747-31-2376 Original Issue for General Electric powered airplanes, 747-31-2377 

Original Issue for Pratt and Whitney powered airplanes or 747-31-2378 Original Issue for Rolls Royce powered 

airplanes, are necessary to be accomplished prior to or concurrent with this service bulletin. The service 

bulletins will install updated Integrated Display System (IDS) software on the affected airplanes.

BACKGROUND

This service bulletin installs an automatic shut off system for the Horizontal Stabilizer Tank (HST) fuel pumps. 

Installation of the automatic system will prevent a potential ignition source in the tank by making sure the pumps 

do not run dry for an extended period of time when the fuel level is below the pump inlet. The dry running of the 

pumps could result in fire/explosion of the fuel tank.

Currently the flight crew turns off the pumps when a low pressure indication is displayed on Engine Indication 

and Crew Alerting System (EICAS) and the "PRESS" lights for the pumps are ON. The automatic shut off 

system installed by this service bulletin will make sure the pumps will not run for more than 14 seconds with 

continuous low fuel pressure and if the flight crew does not respond to the indication sooner. The flight crew 

remains in primary control, with this automatic shut off system as a backup, to turn the pumps off after a low 

pressure indication.

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

Limitations (AWL) "28-AWL-24" will be added to section 9 of the MPD to include a functional check of the 

horizontal stabilizer fuel boost pump Automatic Shutoff System. This change also affects Section 1 of the FAA 

Approved Airplane Flight Manual.

This service bulletin is the result of the safety assessments conducted by Boeing under Special Federal Aviation 

Regulation (SFAR) 88, "Fuel Tank System Fault Tolerance Evaluation Requirements".

As a part of a service bulletin validation program, this change was completed on airplane RT672 by Service 

Bulletin 747-28A2262 and before the release of Revision 1 of this service bulletin. The change completed on 

airplane RT672 by Service Bulletin 747-28A2262 is equivalent to Revision 1 of this service bulletin. Airplane 

RT672 has the configuration of a Group 3 airplane.
 

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BOEING SERVICE BULLETIN 747-28A2262

ACTION (PRR 85539-4)

Group 1-9: In the E-8 rack, install two new relays and make wiring changes. Install new wiring between the E8 rack and the P414 and P415 panels. Make wiring changes in the P414 and P415 panels. Make wiring 

changes to the E2-6 shelf and E2-6 shelf wire integration unit. Make wiring changes at the Modularized Avionics 

and Warning Electronics Assembly (MAWEA) card file. Do a functional test. Change your scheduled 

maintenance program to include periodic functional checks of the Horizontal Stabilizer Fuel Boost Pump 

Automatic Shutoff System as given in 747-400 Maintenance Planning Data (MPD) document, Section 9, 

Airworthiness Limitation (AWL) Number 28-AWL-24.

EFFECTIVITY

747-400 airplanes. See Service Bulletin Paragraph 1.A.1 for effectivity.

COMPLIANCE

Federal Aviation Administration (FAA) Airworthiness Directive 2007-13-04 is related to this service bulletin.

Boeing recommends operator’s incorporate this change within 36 months after the original issue date of this 

service bulletin. In addition, operators should change their scheduled maintenance program to include periodic 

functional checks of the Horizontal Stabilizer Fuel Boost Pump Automatic Shutoff System as given in 747-400 

Maintenance Planning Data (MPD) document, Section 9, Airworthiness Limitation (AWL) Number 28-AWL-24.

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

Groups 1-9 117 30
 

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BOEING SERVICE BULLETIN 747-28A2262

WIRE INTEGRATION UNIT M4260

AT THE E2-6 SHELF AND

MAKE WIRING CHANGES

AT THE MAWEA CARDFILE

MAKE WIRING CHANGES

P415 PANEL

CHANGES AT THE

MAKE WIRING

P414 PANEL

CHANGES AT THE

MAKE WIRING

BUNDLE W4588

ADD NEW WIRE TO

EXISTING WIRE

ADD NEW WIRE TO

EXISTING WIRE

BUNDLE W4437

INSTALL TWO NEW RELAYS

AND CHANGE THE WIRING

AT THE E-8 AFT

EQUIPMENT CENTER

AC1402

AC1401

1000

STA

1480

STA

520

STA

379746
 

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BLANK PAGE
Original Issue: March 15, 2007

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Commercial

Airplanes 747

Service Bulletin

Number: 747-28A2262

Original Issue: March 15, 2007

Revision 2: August 13, 2009

ATA System: 2817

SUBJECT: FUEL - Horizontal Stabilizer Tank Fuel Transfer System - Automatic Pump Shutoff 

Change

1. PLANNING INFORMATION

A. Effectivity

1. Airplanes

Refer to Service Bulletin Index Document D6-30300 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 85539-4 for data about this change.

GROUP CONFIGURATION DESCRIPTION

1 - 747-400 Airplanes with Horizontal Stabilizer 

Fuel Tank Active. Grouping based on wiring 

configuration differences in E2-6 shelf.

2 - 747-400 Airplanes with Horizontal Stabilizer 

Fuel Tank Active. Grouping based on wiring 

configuration differences in E2-6 shelf.

3 - 747-400 Airplanes with Horizontal Stabilizer 

Fuel Tank Active. Grouping based on wiring 

configuration differences in E2-6 shelf.

4 - 747-400 Airplanes with Horizontal Stabilizer 

Fuel Tank Active. Grouping based on wiring 

configuration differences in E2-6 shelf and have 

different AP2301 disconnect on E-8 rack.

5 - 747-400 Airplanes with Horizontal Stabilizer 

Fuel Tank Active. Grouping based on wiring 

configuration differences in E2-6 shelf and have 

different AP2301 disconnect on E-8 rack.

6 - 747-400 Airplanes with Horizontal Stabilizer 

Fuel Tank Active. Grouping based on wiring 

configuration differences in E2-6 shelf and have 

different AP2301 disconnect on E-8 rack.
 

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BOEING SERVICE BULLETIN 747-28A2262

Airplane models:

747-400

IDENTIFICATION BY CUSTOMER, CUSTOMER CODE, GROUP AND VARIABLE NUMBER

AEROLINEAS ARGENTINAS (ARG)

1 RT704

2 RT701–RT702

AIR ATLANTA ICELANDIC (AID)

1 RT515

6 RT751

AIR CARGO GERMANY (CGU)

1 RT633

AIR CHINA (BEJ)

1 RM341

AIR CHINA CARGO (CGC)

1 RT101 RT103

AIR FRANCE (AFA)

1 RM401–RM402 RT071–RT073 RT121

4 RT591

AIR NEW ZEALAND (ANZ)

1 RM082 RM191–RM192 RT673 RT932

3 RT672

8 RT671

9 RT703

AIR PACIFIC (APC)

7 RT502 RT504

7 - 747-400 Airplanes with Horizontal Stabilizer 

Fuel Tank Active. Grouping based on wiring 

configuration differences in E2-6 shelf and have 

different AP2301 disconnect on E-8 rack.

8 - 747-400 Airplanes with Horizontal Stabilizer 

Fuel Tank Active. Grouping based on wiring 

configuration differences in E2-6 shelf and have 

different AP2301 disconnect on E-8 rack and 

uses GDX2-DC for P414 panel.

9 - 747-400 Airplanes with Horizontal Stabilizer 

Fuel Tank Active. Grouping based on wiring 

configuration differences in E2-6 shelf and have 

different AP2301 disconnect on E-8 rack and 

uses GDX2-DC for P414 panel.

GROUP CONFIGURATION DESCRIPTION
 

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BOEING SERVICE BULLETIN 747-28A2262

AIR PULLMANTUR (PUL)

1 RT523 RT525 RT749

ALL NIPPON AIRWAYS (ANA)

1 RT753–RT755 RT777

2 RT776

ASIANA AIRLINES (AAR)

1 RM071 RT131–RT136 RU032

ATLAS AIR (TLS)

2 RT752

AVION AIRCRAFT TRADING H.F. (VNG)

1 RT634

BAHRAIN ROYAL FLIGHT (BHR)

1 RM426

BRITISH AIRWAYS (BAB)

1 RM096–RM097 RM136–RM145 RM261–RM264 RT488–RT499

RU121 RU126–RU132

3 RT485–RT487

7 RT471–RT484

CATHAY PACIFIC AIRWAYS (CAT)

1 RT457–RT469 RT511–RT512 RT514 RT517–RT518

RT522 RT528–RT529 RT782 RT837

2 RT781

3 RT455–RT456 RT508

7 RT451–RT454

CHINA AIRLINES (CHI)

1 RM021–RM024 RT636–RT640

CORSAIR (COR)

1 RT613–RT614 RT616 RT618–RT619 RT621

DRAGONAIR (DRG)

1 RT510 RT513 RT516 RT519

RT524

DUBAI AIR WING (DAW)

1 RM167–RM168 RT102

EL AL ISRAEL AIRLINES (ELA)

1 RM091 RT527 RU081–RU083

EVA AIR (EVA)

1 RM116–RM117 RT162–RT163 RT165–RT168 RT951–RT955
 

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BOEING SERVICE BULLETIN 747-28A2262

EVERGREEN INTERNATIONAL A/L (EVR)

1 RT743

7 RT631–RT632

EXPORT RESTRICTED AIRPLANES (YWV)

1 RT620

3 RT606

7 RT602

GARUDA INDONESIA (GIA)

1 RT931 RU061–RU062

GECAS (GEF)

1 RT412 RT615 RT622

GREAT WALL AIRLINES (GWL)

1 RT520

HIS MAJESTY THE SULTAN'S FLIGHT (BWN)

1 RT440

JAL INTERNATIONAL (JAL)

1 RT861–RT864

2 RT648–RT650

6 RT641–RT647

KALITTA AIR (KAC)

6 RT021–RT022

KLM - ROYAL DUTCH AIRLINES (KLM)

1 RM801–RM803 RT006–RT014

6 RT001–RT005

KOREAN AIR (KAL)

1 RM011–RM013 RT575–RT588 RT590 RT811–RT814

3 RT574

6 RT061

7 RT571–RT573

KUWAIT AIRWAYS (KUW)

1 RT151

LION AIR (MLI)

7 RT503 RT505

LUFTHANSA GERMAN AIRLINES (DLH)

1 RT045–RT047 RT437–RT439 RT441–RT447

4 RT431–RT436

6 RT043–RT044

MALAYSIA AIRLINES (MAS)

1 RM036–RM040 RM366–RM367 RT744 RT746

RT748 RT750 RU016–RU017
 

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BOEING SERVICE BULLETIN 747-28A2262

MARTINAIR HOLLAND (MTH)

3 RT509

7 RT501 RT506–RT507

NORTHWEST AIRLINES (NWA)

1 RM241–RM246

7 RT401–RT410

OMAN ROYAL FLIGHT (RFO)

1 RM010

PHILIPPINE AIRLINES (PAL)

1 RT152 RU051–RU052 RU059–RU060

PRESIDENTIAL FLIGHT (ABD)

1 RM084 RT137

QANTAS (QAN)

1 RF001–RF006 RM331–RM333 RT559–RT568 RT742

RU031

5 RT551–RT558

6 RT741

SAUDI ARABIAN AIRLINES (SVA)

1 RM156–RM157 RU101–RU102

SAUDI ROYAL FLIGHT (SRF)

1 RM158

SINGAPORE AIRLINES (SIA)

1 RM041–RM045 RT521 RT526 RT530

RT831–RT835

SONAIR (SON)

1 RM231–RM233

SOUTH AFRICAN AIRWAYS (SAA)

1 RM081 RM083 RM147

THAI AIRWAYS INTERNATIONAL (TII)

1 RM026–RM030 RM431 RT694–RT699 RT801–RT803

2 RT693

6 RT691–RT692

TRANSAERO AIRLINES (TRX)

1 RM146 RT783–RT784

UNITED AIR LINES (UAL)

1 RM166 RM169–RM177 RT411 RT609–RT612

RT617 RT623–RT630

3 RT607–RT608

7 RT601 RT603–RT605
 

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UPS (UPS)

1 RT161 RT164

VIRGIN ATLANTIC AIRWAYS (VAA)

1 RM051–RM053 RM351–RM355 RT945–RT949

WORLD AIRWAYS, INC. (WLD)

1 RT745 RT747

IDENTIFICATION BY VARIABLE NUMBER

Variable Group

RF001–RF006 1

RM010–RM013 1

RM021–RM024 1

RM026–RM030 1

RM036–RM045 1

RM051–RM053 1

RM071 1

RM081–RM084 1

RM091 1

RM096–RM097 1

RM116–RM117 1

RM136–RM147 1

RM156–RM158 1

RM166–RM177 1

RM191–RM192 1

RM231–RM233 1

RM241–RM246 1

RM261–RM264 1

RM331–RM333 1

RM341 1

RM351–RM355 1

RM366–RM367 1

RM401–RM402 1

RM426 1

RM431 1

RM801–RM803 1

RT001–RT005 6

RT006–RT014 1

RT021–RT022 6

RT043–RT044 6
 

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RT045–RT047 1

RT061 6

RT071–RT073 1

RT101–RT103 1

RT121 1

RT131–RT137 1

RT151–RT152 1

RT161–RT168 1

RT401–RT410 7

RT411–RT412 1

RT431–RT436 4

RT437–RT447 1

RT451–RT454 7

RT455–RT456 3

RT457–RT469 1

RT471–RT484 7

RT485–RT487 3

RT488–RT499 1

RT501–RT507 7

RT508–RT509 3

RT510–RT530 1

RT551–RT558 5

RT559–RT568 1

RT571–RT573 7

RT574 3

RT575–RT590 1

RT591 4

RT601–RT605 7

RT606–RT608 3

RT609–RT630 1

RT631–RT632 7

RT633–RT640 1

RT641–RT647 6

RT648–RT650 2

RT671 8

RT672 3

RT673 1

RT691–RT692 6

RT693 2

Variable Group
 

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2. Spares Affected

None.

B. Concurrent Requirements

Boeing service bulletin 747-31-2376 Original Issue for General Electric powered airplanes, 747-31-

2377 Original Issue for Pratt and Whitney powered airplanes or 747-31-2378 Original Issue for Rolls 

Royce powered airplanes, is necessary to be accomplished prior to or concurrent with this service 

bulletin. The service bulletins will install updated Integrated Display System (IDS) software on the 

affected airplanes.

RT694–RT699 1

RT701–RT702 2

RT703 9

RT704 1

RT741 6

RT742–RT750 1

RT751 6

RT752 2

RT753–RT755 1

RT776 2

RT777 1

RT781 2

RT782–RT784 1

RT801–RT803 1

RT811–RT814 1

RT831–RT837 1

RT861–RT864 1

RT931–RT932 1

RT945–RT949 1

RT951–RT955 1

RU016–RU017 1

RU031–RU032 1

RU051–RU052 1

RU059–RU062 1

RU081–RU083 1

RU101–RU102 1

RU121 1

RU126–RU132 1

Variable Group
 

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C. Reason

This service bulletin installs an automatic shut off system for the Horizontal Stabilizer Tank fuel 

pumps. Installation of the automatic system will prevent a potential ignition source in the tank by 

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

pump inlet. The dry running of the pumps could result in fire/explosion of the fuel tank.

Currently the flight crew turns off the pumps when a low pressure indication is displayed on Engine 

Indication and Crew Alerting System (EICAS) and the "PRESS" lights for the pumps are ON. The 

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

more than 14 seconds with continuous low fuel pressure and if the flight crew does not respond to the 

indication sooner. The flight crew remains in primary control, with this automatic shut off system as a 

backup, to turn the pumps off after a low pressure indication.

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

Airworthiness Limitations (AWL) "28-AWL-24" will be added to section 9 of the MPD to include a 

functional check of the horizontal stabilizer fuel boost pump Automatic Shutoff System. This change 

also affects Section 1 of the FAA Approved Airplane Flight Manual.

This service bulletin is the result of the safety assessments conducted by Boeing under Special 

Federal Aviation Regulation (SFAR) 88, "Fuel Tank System Fault Tolerance Evaluation 

Requirements".

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

bulletin. It was found that certain airplanes have a different configuration on the E-8 rack then what is 

shown in figures 1 and 3. This revision also includes changes identified during the validation of the 

service bulletin.

As a part of a service bulletin validation program, this change was completed on airplane RT672 by 

Service Bulletin 747-28A2262 before the release of Revision 1 of this service bulletin. The change 

was completed on airplane RT672 by Service Bulletin 747-28A2262 is equivalent to Revision 1 of this 

service bulletin. Airplane RT672 has the configuration of a Group 3 airplane.

The following sections of the service bulletin were changed:

1. Planning Information Section 1, Effectivity, airplane grouping was revised to add new airplane 

groups. The following airplanes have been removed from figures 1 and 3 and added to the new 

figures 17 and 18.

— Airplanes RT551-RT558 were deleted from Group 1 and moved to the new Group 5.

— Airplanes RT001-RT005, RT021-RT022, RT043-RT044, RT061, RT641-RT647, RT691-

RT692, RT741 and RT751 were deleted from Group 2 and moved to the new Group 6.

— Airplanes RT401-RT410, RT451-RT454, RT471-RT484, RT501-RT507, RT571-RT573, 

RT601-RT605, RT631-RT632 and RT671 were deleted from Group 3 and moved to the new 

Group 7.

2. Approval Section 1, Added new AD to Approval statement, AD 2007-13-04.

3. Accomplishment Instructions Section 3, Work Instruction B.15 and B.17 were revised to correct 

the Group applicability.

4. Accomplishment Instructions Section 3, Work Instruction B.20, Functional Test, was revised to 

clarify the steps.
 

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5. Accomplishment Instructions Section 3, Work Instruction B.11 and B.12, Group applicability was 

revised to add Group 5.

6. Accomplishment Instructions Section 3, Work Instruction B.13 and B.14, Group applicability was 

revised to add Group 6.

7. Accomplishment Instructions Section 3, Work Instruction B.16 and B.17, Group applicability was 

revised to add Group 7.

8. Figures 12, 15 and 16 were updated to be in accordance with the wire wrap requirements shown 

in Chapter 20 of the Standard Wire Practices Manual (SWPM).

9. Figures 1 and 3 revised to remove Group 4 airplanes.

10. Figures 9-16 updated the Group applicability.

11. Figures 17 and 18 added new figures for Group 4, 5, 6 and 7 airplanes.

12. Figure 11 corrected typographical error for flag note 2.

The data given in Information Notice 767-28-2262 IN 01 and 767-28A2262 IN 02 is included in this 

revision

Revision 2 is sent to address comments received from operators since the original issue and Revision 

1 of the service bulletin.

Airplane RT671 was moved from Group 7 to new Group 8.

Airplane RT703 was moved from Group 1 to new Group 9.

Boeing found the Work Instructions B.4, B.5 and B.7 through B.16 in Revision 1, did not agree with 

the figure numbers given in the service bulletin. After investigating, Boeing found that during the 

preparation of Revision 1, the Figure 2 was inadvertently moved to a different part of the service 

bulletin. This caused the figures to renumber according to their order of placement in the service 

bulletin. This revision restores the Figure 2 into its correct location in the document. This restores the 

correct figure number assigned to the Figure. The figure numbers 1 through 16 in Revision 2 agree 

with the figure numbers in the original issue of service bulletin 747-28A2262.

The following sections of the service bulletin were changed:

1. Groups 8 and 9 were added to Group and Configuration tables in Section 1, Manpower table, 

Weight and Balance table and Material Information Section 2 where applicable.

2. Compliance and Approval section, removed reference to Airworthiness Directive 2002-24-51 and 

Airworthiness Directive 2002-24-52 which are superseded by Airworthiness Directive 2007-13-

04.

3. Compliance statements in the Summary and Planning sections were revised with the wording 

"original issue date".

4. Material Information Section 2, Parts and Material Supplied by Operator, Added, contact 

BACC47CP3S as operator supplied for airplanes RT043-RT047 and RT433-RT477 only.
 

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5. Accomplishment Instruction Section 3:

— added Step B.9, for new Groups 8 and 9.

— added Group 8 to Work Instruction Steps B.3-B.4, B.6-B.7, B.9-B.11, B.17-B.18.

— added Group 9 to Work Instruction Steps B.2, B.4-B.5, B.7, B.9-B.13.

6. Revised Figures numbers 2 through 14:

— Figure 2, restored to Figure 3.

— Figure 3, restored to Figure 4.

— Figure 4, restored to Figure 5.

— Figure 5, restored to Figure 6.

— Figure 6, restored to Figure 7.

— Figure 7, restored to Figure 8.

— Figure 8, restored to Figure 9.

— Figure 9, restored to Figure 10.

— Figure 10, restored to Figure 11.

— Figure 11, restored to Figure 12.

— Figure 12, restored to Figure 13.

— Figure 13, restored to Figure 14.

— Figure 14, restored to Figure 2.

7. Figures 2, 4-5, 7-8, 14-15, 17-19 added Group 8 applicability.

8. Figures 1-5, 7-10 and 19 added Group 9 applicability.

9. Figures 2, revised Flag Note 3, contact part number should be BACC47CP3S for connector 

D40106J.

10. Figures 6 and 7, added information note for ground block if existing ground block is full.

11. Added new Figure 19, to show wire W3846-595-20 connected to GDX2-DC. Added information 

note for ground block if existing ground block is full.

The data given in Information Notice 767-28-2262 IN 04 is included in this revision. The information 

Notice IN 03 was corrected in IN 04

D. Description

Group 1-9: In the E-8 rack, two new relays are installed and wiring changes are made. New wiring is 

installed between the E-8 rack and the P414 and P415 panels. Wiring changes are made in the P414 

and P415 panels. Wiring changes are made to the E2-6 shelf and E2-6 shelf wire integration unit. 

Wiring changes are made at the Modularized Avionics and Warning Electronics Assembly (MAWEA) 

card file. A functional test is done.

Revision 2 - No more work is necessary on airplanes changed as shown in the original issue or 

Revision 1 of this service bulletin.

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

service bulletin.

E. Compliance

Federal Aviation Administration (FAA) Airworthiness Directive 2007-13-04 is related to this service 

bulletin.
 

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

issue date of this service bulletin. In addition, operators should change their scheduled maintenance 

program to include periodic functional checks of the Horizontal Stabilizer Fuel Boost Pump Automatic 

Shutoff System as given in 747-400 Maintenance Planning Data (MPD) document, Section 9, 

Airworthiness Limitation (AWL) Number 28-AWL-24.

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.

This service bulletin has been approved by the FAA. In addition, the Manager of the FAA Seattle 

Aircraft Certification Office approves the installation of the horizonal stabilizer tank automatic shutoff 

system, as described in this service bulletin, as an alternative method of compliance to the 

requirements of paragraph (h), (l) and (m), fueling and use of the Horizontal Stabilizer Tank (HST) of 

AD 2007-13-04. All provisions of AD 2007-13-04 that are not specifically referenced in the above 

statement remain fully applicable and must be complied with. Compliance with the conditions of this 

AMOC approval requires concurrent incorporation of the associated revisions to the Airplane Flight 

Manual Section 1 and incorporation of the related Airworthiness Limitations (AWL) in Section 9 of the 

MPD into the operator’s maintenance documentation.

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 1-9: 

Task

Number of 

Persons Task-Hours Elapsed Hours

Open Access 4 30 7.5

Change 4 44 11

Close Access 4 40 10

Test 2 3 1.5

TOTAL FOR EACH AIRPLANE 117 30
 

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This estimate does not include the task-hour data given in the service bulletins in Paragraph 1.B., 

Concurrent Requirements.

H. Weight and Balance Changes

I. Electrical Load Data

Not changed.

J. References

1. Existing Data:

a. Engineering Change Memo PRR 85539-4

b. 747-400 Aircraft Maintenance Manual (AMM) 12-11-01, 20-41-02, 20-41-03, 24-22-00, 

45-10-00

c. 747-400 Structural Repair Manual (SRM) 51-40-02

d. 747-400 Maintenance Planning Data (MPD) Section 9

e. 747-400 Wiring Diagrams 28-21-26, 28-21-27, 28-21-28, 28-21-29, 28-21-30, 28-21-31, 

28-42-15, 30-41-21, 30-41-31 

f. Boeing Service Bulletin 747-31-2376

g. Boeing Service Bulletin 747-31-2377

h. Boeing Service Bulletin 747-31-2378

i. Federal Aviation Administration (FAA) Airworthiness Directive 2007-13-04

j. Standard Overhaul Practices Manual (SOPM) 20-50-05

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

20-20-11, 20-30-11, 20-30-12, 20-30-16, 20-60-00, 20-61-11, 20-71-14, 20-72-17, 

20-72-18, 20-81-12, 20-81-19

2. Data supplied with this Service Bulletin:

None.

Group 1-9: 

Airplane

Change in Weight 

(Pounds)

Change in Moment 

(Pound-Inches)

Groups 1-9 +2.4 +2304.0
 

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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.

K. Publications Affected

1. Publications

Drawing Number Title

288U4147 Wire Bundle Installation, Lower Sidewall LH, STA 403 Thru STA 

523

288U4148 Wire Bundle Installation, Lower Sidewall RH, STA 403 Thru STA 

523

288U4150 Wire Bundle Installation, Main Deck Floor Beams RH, STA 403 

Thru 523 and Aft 400 Bulkhead RH

288U4151 Wire Bundle Installation, Main Deck Floor Beams LH, STA 403 

Thru 523 and Aft 400 Bulkhead LH

288U4156 Wire Bundle Installation, Main Deck Floor Beams, STA 403 Thru 

523, LBL 50 to RBL 50

288U4210 Wire Bundle Installation, Main Deck Floor Beams RH, STA 523 

Thru 723

288U4211 Wire Bundle Installation, Main Deck Floor Beams LH, STA 523 

Thru 723

288U4230 Wire Bundle Installation, Main Deck Floor Beams RH, STA 723 

Thru 997

288U4231 Wire Bundle Installation, Main Deck Floor Beams LH, STA 723 

Thru 997

288U4410 Wire Bundle Installation, Pressure Deck and Main Deck FLR 

Beams RH, STA 997 Thru 1243

288U4411 Wire Bundle Installation, Pressure Deck and Main Deck FLR 

Beams LH, STA 997 Thru 1243

288U4430 Wire Bundle Installation, Pressure Deck and Main Deck FLR 

Beams RH, STA 1243 Thru 1483

288U4431 Wire Bundle Installation, Pressure Deck and Main Deck FLR 

Beams LH, STA 1243 Thru 1483

288U4610 Wire Bundle Installation, Passenger Floor Beams, 46 SEC (FWD) 

R.H. STA 1500 - 1720

288U4611 Wire Bundle Installation, Main Deck Floor Beams LH, STA 1483 

Thru 1723

Publication Chapter-Section

747 FAA Approved Airplane Flight Manual Section 1

747-400 Operations Manual 12.20, 12.30, NNC.12, NP.20

747-400 Maintenance Manual 28-17, 28-22
 

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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.

747-400 Wiring Diagram Manual 28-21, 28-42, 30-41

747-400 Weight and Balance Manual 1-22

747-400 Illustrated Parts Catalog 11-11, 28-21

747-400 System Schematic Manual 28-21, 28-42, 30-41

747-400 Maintenance Planning Data 

(MPD) Document

Section 9

Publication Chapter-Section
 

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BLANK PAGE
 

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2. MATERIAL INFORMATION

A. Material - Price and Availability

Boeing can supply the kit 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.

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.

Group 1-9: 

Kit Number Name Date QTY

ROLT 

(Weeks)

Unit Price thru

Dec 31, 2007

015U1765-1 Top KIt, Automatic HST 

Pump Shutoff Addition

Available 45 22 $4,112.00
 

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NOTE: One top kit is necessary for each airplane.

Group 1-9: 

Kit 015U1765

New Part Number QTY Name

Existing Part 

Number Notes

015U1765-1 -- Top Kit, Automatic 

HST Pump Shutoff 

Addition

-- --

289U1214-1 1 Wire Kit -- --

65B48634-39 1 Relay Bracket -- --

BAC27EEL28836 1 Marker -- (a)

BAC27EEL28837 1 Marker -- (a)

BACR15DR4PAC2 3 Rivet -- (b)

BACS38K10 50 Strap -- (a)

BACS38K7C 150 Strap -- (a)

TDH-1852-1402 2 Relay -- (a) (c)

(a) This part is used in production.

(b) 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.

(c) Leach Corp (58657), 6900 Orangethorpe Avenue, P.O. Box 5032, Buena 

Park, California 90622-5032

Group 1-9: 

Kit 289U1214

New Part 

Number

QTY

Name

Existing Part 

-105 -104 -103 -102 -101 -1 Number Notes

289U1214-1 . . . . . -- Wire Kit -- (b)

289U1214-101 . . . . -- 1 Subkit, W3851 -- (b)

289U1214-102 . . . -- . 1 Subkit, W3842, 

W3846, W4437, 

W4478

-- (b)

289U1214-103 . . -- . . 1 Subkit, W3942, 

W3944, W4488, 

W4588

-- (b)

289U1214-104 . -- . . . 1 Subkit, W4260, 

W4261, W4262, 

W4263

-- (b)

289U1214-105 -- . . . . 1 Subkit, W4758 -- (b)

289U1214-10101 . . . . 1 . I.D. Tape -- --
 

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2. Parts and Materials Supplied by the Operator:

3. Parts Modified and Reidentified:

None.

289U1214-10102 . . . . 1 . I.D. Tape -- --

289U1214-10103 . . . . 1 . I.D. Tape -- --

289U1214-10104 . . . . 1 . I.D. Tape -- --

289U1214-101W . . . . 1 . Wire -- --

289U1214-102W . . . 1 . . Wire -- --

289U1214-103W . . 1 . . . Wire -- --

289U1214-104W . 1 . . . . Wire -- --

BACC47CN1S . . 2 3 5 . Contact -- --

BACC47CN3S . . 1 . . . Contact -- --

BACC47CP1S . . 3 2 3 . Contact -- --

BACC47CP3S . . 1 . . . Contact -- --

BACC47DE1A . . 2 2 3 . Contact -- --

BACC47DJ1 . . 3 3 . . Contact -- --

BACC47EF1 . 4 . . . . Contact -- --

BACC47EG2 . 4 . . . . Contact -- --

BACC47ER1 . . . . 12 . Contact -- --

BACS16AH1 . . . . 2 . Relay Socket -- --

BACT12AR202 . . . . 10 . Terminal Lug -- --

BMS13-

46T03C01G024

. 1 . . . Wire -- (a)

D436-37 . . . . 3 . Splice -- --

324484 5 . 2 . . Terminal, End Cap -- --

(a) Length is 36 inches

(b) There are more parts than are necessary.

Part Number / 

Specification QTY Name Notes

BACC47CP3S 1 Contact Required for airplanes 

RT043-RT047 and RT433-

RT447 only.

Group 1-9: 

Kit 289U1214

New Part 

Number

QTY

Name

Existing Part 

-105 -104 -103 -102 -101 -1 Number Notes
 

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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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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

— Hole dimensions for standard solid rivets are given in 747-400 Structural Repair 

Manual, Chapter 51

4. For approved fastener and process material substitutions, refer to 747-400 Structural 

Repair Manual, Chapter 51, Alternate fasteners are given in 747-400 Structural Repair 

Manual Chapter 51 and Boeing Drawing 012W6100.

5. Refer to the Boeing Standard Wiring Practices Manuals 20-10-11 and 20-10-12 for the 

wire installation procedures and 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.

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

B. WORK INSTRUCTIONS

1. Remove electrical power from the airplane as given in 747-400 AMM 24-22-00.

2. Group 1-3, 9: Install a new relay bracket as necessary in the E-8 Aft Equipment Center as given 

in Figure 1.

3. Group 4-8: Install a new relay bracket as necessary in the E-8 Aft Equipment Center as given in 

Figure 17.

4. Group 1-9: Change the wiring in the E-8 Aft Equipment Center as given in Figure 2.
 

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5. Group 1-3, 9: Install new relays in the E-8 Aft Equipment Center as given in Figure 3.

6. Group 4-8: Install new relays in the E-8 Aft Equipment Center as given in Figure 18.

7. Group 1-9: Install new wiring to existing ship’s wiring as given in Figure 4 and Figure 5.

8. Group 1-7: Change the wiring in the P414 panel as given in Figure 6.

9. Group 8-9: Change the wiring in the P414 panel as given in Figure 19.

10. Group 1-9: Change the wiring in the P415 panel as given in Figure 7.

11. Group 1-9: Change the wiring in the MAWEA card file as given in Figure 8.

12. Group 1, 5, 9: Change the wiring on the E2-6 shelf as given in Figure 9.

13. Group 1, 5, 9: Change the wiring in the E2-6 shelf wire integration unit as given in Figure 10.

14. Group 2, 6: Change the wiring on the E2-6 shelf as given in Figure 11.

15. Group 2, 6: Change the wiring in the E2-6 shelf wire integration unit as given in Figure 12.

16. Group 4: Change the wiring on the E2-6 shelf as given in Figure 13.

17. Group 3, 7-8: Change the wiring in the E2-6 shelf wire integration unit as given in Figure 14.

18. Group 3, 7-8: Change the wiring on the E2-6 shelf as given in Figure 15.

19. Group 4: Change the wiring in the E2-6 shelf wire integration unit as given in Figure 16.

20. Restore electrical power to the airplane as given in 747-400 AMM 24-22-00.

21. Do the following functional test:

a. Open the fueling station door to get access to the P42 panel.

b. Load a minimum 2000 pounds of fuel in the Horizontal Stabilizer Tank as given in 747-400 

AMM 12-11-01.

c. Set the Stabilizer Trim to approximately 3 trim units.

d. For the Left Horizontal Stabilizer Fuel Pump

(1) Make sure circuit breaker C3141 (Horiz STAB Xfer/Jett Pump Left) on the P85 panel is 

closed.

(2) Make sure the following circuit breakers on the P414 panel are closed:

C/B Number Grid Location Name

C90 F17 Fueling Valve

C1142 F22 Fueling power
 

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(3) On the P42 panel, open switch S1879 (Horiz-Stab ISLN Con VLV).

(4) On the M154 panel, set the L STAB Pump switch to "ON".

(5) Make sure the left Horizontal Stabilizer Fuel Pump is running.

(6) Open circuit breaker C3141 (Horiz STAB Xfer/Jett Pump Left) on the P85 panel.

(7) In the E-8 Equipment Center, make sure relay R7401 (HSTAB Pump Cont Left) is 

energized for more than 20 seconds. Use Ohm meter to make sure there is continuity 

between pins A1 and A2.

(8) On the M154 panel, set the L STAB Pump switch to "OFF".

(9) On the P42 panel, close switch S1879 (Horiz-Stab ISLN Con VLV).

(10) Open the following circuit breakers on the P414 panel:

(11) On the E-8 Equipment Center at connector D40108P, disconnect wire W4478-002-20 

at pin 2 (de-pin). Protect removed pin from coming in contact with other surfaces and 

from contamination by installing a protective cover such as a plastic bag.

(12) Close circuit breaker C3141 (Horiz STAB Xfer/Jett Pump Left) on the P85 panel.

(13) Close the following circuit breakers on the P414 panel:

(14) On the P42 panel, open switch S1879 (Horiz-Stab ISLN Con VLV).

(15) On the M154 panel, set the L STAB Pump switch to "ON".

(16) Make sure the left Horizontal Stabilizer Fuel Pump is running.

(17) Open circuit breaker C3141 (Horiz STAB Xfer/Jett Pump Left) on the P85 panel. At the 

same time, start timing using a stopwatch.

(18) After 14 seconds, make sure relay R7401 (HSTAB Pump Cont Left) is not energized. 

Use Ohm meter to make sure there is no continuity between pins A1 and A2.

(19) Make sure that the Left Pump Low Pressure light is illuminated.

(20) On the M154 panel, set the L STAB Pump switch to "OFF".

(21) Make sure that the Left Pump Low Pressure light is not illuminated.

C/B Number Grid Location Name

C90 F17 Fueling Valve

C1142 F22 Fueling power

C/B Number Grid Location Name

C90 F17 Fueling Valve

C1142 F22 Fueling power
 

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(22) On the M154 panel, set the L STAB Pump switch to "ON".

(23) Make sure relay R7401 (HSTAB Pump Cont Left) is energized. Use Ohm meter to 

make sure there is continuity between pins A1 and A2.

(24) After 14 seconds, make sure relay R7401 (HSTAB Pump Cont Left) is not energized. 

Use Ohm meter to make sure there is no continuity between pins A1 and A2.

(25) On the M154 panel, set the L STAB Pump switch to "OFF".

(26) Open the following circuit breakers on the P414 panel:

(27) On the P42 panel, close switch S1879 (Horiz-Stab ISLN Con VLV).

(28) On the E-8 Equipment Center at connector D40108P, remove protective cover and 

connect wire W4478-002-20 at pin 2 (reinstall pin).

(29) Close circuit breaker C3141 (Horiz STAB Xfer/Jett Pump Left) on the P85 panel.

(30) Close the following circuit breakers on the P414 panel:

(31) On the P42 panel, open switch S1879 (Horiz-Stab ISLN Con VLV).

(32) On the M154 panel, set the L STAB Pump switch to "ON".

(33) Make sure relay R7401 (HSTAB Pump Cont Left) is energized for more than 20 

seconds. Use Ohm meter to make sure there is continuity between pins A1 and A2.

(34) On the M154 panel, set the L STAB Pump switch to "OFF".

(35) On the P42 panel, close switch S1879 (Horiz-Stab ISLN Con VLV).

e. For the Right Horizontal Stabilizer Fuel Pump

(1) Make sure circuit breaker C3142 (Horiz STAB Xfer/Jett Pump Right) on the P85 panel 

is closed.

(2) Make sure the following circuit breakers on the P414 panel are closed:

C/B Number Grid Location Name

C90 F17 Fueling Valve

C1142 F22 Fueling power

C/B Number Grid Location Name

C90 F17 Fueling Valve

C1142 F22 Fueling power

C/B Number Grid Location Name

C90 F17 Fueling Valve

C1142 F22 Fueling power
 

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(3) On the P42 panel, open switch S1879 (Horiz-Stab ISLN Con VLV).

(4) On the M154 panel, set the R STAB Pump switch to "ON".

(5) Make sure the right Horizontal Stabilizer Fuel Pump is running.

(6) Open circuit breaker C3142 (Horiz STAB Xfer/Jett Pump Right) on the P85 panel.

(7) Make sure relay R7402 (HSTAB Pump Cont Right) is energized for more than 20 

seconds. Use Ohm meter to make sure there is continuity between pins A1 and A2.

(8) On the M154 panel, set the R STAB Pump switch to "OFF".

(9) On the P42 panel, close switch S1879 (Horiz-Stab ISLN Con VLV).

(10) Open the following circuit breakers on the P414 panel:

(11) On the E-8 Equipment Center at connector D40103P, disconnect wire W4488-070-22 

at pin 36 (de-pin). Protect removed pin from coming in contact with other surfaces and 

from contamination by installing a protective cover such as a plastic bag.

(12) Close circuit breaker C3142 (Horiz STAB Xfer/Jett Pump Right) on the P85 panel.

(13) Close the following circuit breakers on the P414 panel:

(14) On the P42 panel, open switch S1879 (Horiz-Stab ISLN Con VLV).

(15) On the M154 panel, set the R STAB Pump switch to "ON".

(16) Make sure the right Horizontal Stabilizer Fuel Pump is running.

(17) Open circuit breaker C3142 (Horiz STAB Xfer/Jett Pump Right) on the P85 panel. At 

the same time, start timing using a stopwatch. 

(18) After 14 seconds, make sure relay R7402 (HSTAB Pump Cont Right) is not energized. 

Use Ohm meter to make sure there is no continuity between pins A1 and A2.

(19) Make sure that the Right Pump Low Pressure light is illuminated.

(20) On the M154 panel, set the R STAB Pump switch to "OFF".

(21) Make sure that the Right Pump Low Pressure light is not illuminated.

C/B Number Grid Location Name

C90 F17 Fueling Valve

C1142 F22 Fueling power

C/B Number Grid Location Name

C90 F17 Fueling Valve

C1142 F22 Fueling power
 

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(22) On the M154 panel, set the R STAB Pump switch to "ON".

(23) Make sure relay R7402 (HSTAB Pump Cont Right) is energized. Use Ohm meter to 

make sure there is continuity between pins A1 and A2. 

(24) After 14 seconds, make sure relay R7402 (HSTAB Pump Cont Right) is not energized. 

Use Ohm meter to make sure there is no continuity between pins A1 and A2.

(25) On the M154 panel, set the R STAB Pump switch to "OFF".

(26) Open the following circuit breakers on the P414 panel:

(27) On the P42 panel, close switch S1879 (Horiz-Stab ISLN Con VLV).

(28) On the E-8 Equipment Center at connector D40103P, remove protective cover and 

connect wire W4488-070-22 at pin 36 (reinstall pin).

(29) Close circuit breaker C3142 (Horiz STAB Xfer/Jett Pump Right) on the P85 panel.

(30) Close the following circuit breakers on the P414 panel:

(31) On the P42 panel, open switch S1879 (Horiz-Stab ISLN Con VLV).

(32) On the M154 panel, set the R STAB Pump switch to "ON".

(33) Make sure relay R7402 (HSTAB Pump Cont Right) is energized for more than 20 

seconds. Use Ohm meter to make sure there is continuity between pins A1 and A2.

(34) On the M154 panel, set the R STAB Pump switch to "OFF".

(35) On the P42 panel, close switch S1879 (Horiz-Stab ISLN Con VLV).

f. Close the fueling station door.

g. Do the following check using Central Maintenance Computer (CMC) input monitoring as 

given in 747-400 AMM 45-10-00:

(1) Select the "<CMC" Main Menu on the Multipurpose Control Display Unit (MCDU).

(2) Go to Page 2 by selecting the "NEXT PAGE" button.

(3) Select "<INPUT MONITORING" to show an empty Input Monitoring page on the 

MCDU.

C/B Number Grid Location Name

C90 F17 Fueling Valve

C1142 F22 Fueling power

C/B Number Grid Location Name

C90 F17 Fueling Valve

C1142 F22 Fueling power
 

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(4) Use the MCDU keyboard and type the following into the MCDU scratchpad: C/26/3/00.

(5) Select the top left key (LSK1L) of the MCDU.

(6) Make sure that Bit 19 is "1" (Indicates that the IDS Auto Shutoff program pin is SET).

(7) Select "<INPUT MONITORING" to show an empty Input Monitoring page on the 

MCDU.

(8) Use the MCDU keyboard and type the following into the MCDU scratchpad: C/26/4/00.

(9) Select the top left key (LSK1L) of the MCDU.

(10) Make sure that Bit 27 is "0" (Indicates that the IDS 502 Fuel Message Reversion 

program pin is NOT SET).

(11) Make sure the following circuit breakers are closed in the P6 panel.

(12) Select "<INPUT MONITORING" to show an empty Input Monitoring page on the 

MCDU.

(13) On the MCDU keyboard, type the following into the MCDU scratchpad: E/034/272/00.

(14) Select the top left key (LSK1L) of the MCDU.

(15) Make sure that Bits 14, 15, 16, and 17 are "0".

22. Put the airplane back to a serviceable condition.

23. Change your scheduled maintenance program to include periodic functional checks of the 

Horizontal Stabilizer Fuel Boost Pump Automatic Shutoff System as given in 747-400 

Maintenance Planning Data (MPD) document, Section 9, Airworthiness Limitation (AWL) 

Number 28-AWL-24.

C/B Number Grid Location Name

C68 E28 Window Heat 2L & 

3R PWR

C69 E30 Window Heat 2R 

& 3L PWR

C10104 E31 Window Heat 2R 

& 3L IND

C10105 E29 Window Heat 2L & 

3R IND
 FIGURE 1: Change the E-8 Aft Equipment Center

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FIGURE 1: Change the E-8 Aft Equipment Center

AFT E/E EQUIPMENT CENTER

ENTRY DOOR

NO. 5L

MAIN

E8 RACK

AFT EQUIPMENT CENTER - E8

INBD FWD

FWD

UP SEE A

356692

(SHEET 1 OF 3)
 FIGURE 1: Change the E-8 Aft Equipment Center

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This Figure applies to Group 1-3, 9: 

A-A

5.10

A

A

UP

INBD

2

2

UP

FWD

A

2 3

1

357070

(SHEET 2 OF 3)
 FIGURE 1: Change the E-8 Aft Equipment Center

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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.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

1

Inspect Disconnect 

Bracket

-- -- Inspect for open relay 

positions 69 and 71.

NOTE: Steps 2 and 3 are only necessary for airplanes that have existing relays at positions 69 

and 71. For airplanes that have open spaces at positions 69 and 71, Steps 2 and 3 are 

optional.

2

Install Relay Bracket 65B48634-39 1 Prepare surface for fay 

surface bond as given in 

SWPM 20-20-00. Refer 

to SWPM 20-20-00 and 

747-400 SRM 51-40-02 

as an accepted 

procedure for Rivet 

installation. Rivet hole 

diameter is 0.129 - 0.132 

inch.

Rivet BACR15DR4PAC2 3

NOTE: The relay bracket may be installed at any location in the area indicated to avoid 

interference with the identification markers of existing relays.

3

Repair or Replace Marker -- -- Repair or replace any 

relay identification 

markers covered by the 

installation of the new 

relay bracket. Refer to 

SOPM 20-50-05 as an 

accepted procedure.

(SHEET 3 OF 3)
 FIGURE 2: E-8 Wiring Changes

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FIGURE 2: E-8 Wiring Changes

28-21-28

28-42-15

28-42-15

28-42-15

R7401 RLYHIGH STAGE

PUMP CONT-LEFT

14

NC

13

NC

X2

11

X1

12

T

D

3

TIME DELAY-LEFT

R10155 RLYAUTO SHUTOFF

4

5

2

7

8

5

1

7

2 3

4

9

6

SM11

(4 LOCATIONS)

188-20

182-20

GDX1-DC

184-20

DR10155

2

9

D40108J

E8-EQUIPMENT CENTER - AFT LEFT

(2 LOCATIONS)

W3851

059-20

183-20

P

D40107J P

W4478

POS 14

AP2301

176-20

185-20

059-20

058-20

GDX1-DC

058-20

POS 16

AP2301

DR10155

(5 LOCATIONS)

2

360314

(SHEET 1 OF 4)
 FIGURE 2: E-8 Wiring Changes

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BOEING SERVICE BULLETIN 747-28A2262

28-21-31

28-42-15

28-42-15

28-42-15

14

NC

13

NC

X2

11

X1

12

T

D

3

4

5

2

7

R7402 RLYHIGH STAGE

PUMP CONT-RIGHT

R10156 RLYAUTO SHUTOFF

TIME DELAY-RIGHT

AP2301

33

056-20

P D40103J

POS 15

36

056-20

057-20

057-20

189-20

187-20

186-20

D40106J P

6

POS 11

AP2301

177-20

DR10156

DR10156

SM12

(4 LOCATIONS)

180-20

E8-EQUIPMENT CENTER - AFT LEFT

(2 LOCATIONS)

W3851

181-20

GDX1-DC

(5 LOCATIONS)

W4488

5

1

2 3

4

6

7 10

11

GDX1-DC

361668

(SHEET 2 OF 4)
 FIGURE 2: E-8 Wiring Changes

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This Figure applies to Group 1-9: 

REFERENCE: 747-400 WIRING DIAGRAM 28-21-28, 28-21-31, 28-42-15

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

NOTE: Use the wire and parts from wire kit 289U1214-101 and contact BACC47CP3S is supplied in wire kit

289U1214-103 for all airplanes except RT043-RT047 and RT433-RT447 which is operator supplied.

Route new wires with the same existing bundle (Separation Code N2, tie color White), use straps

supplied in Top Kit 015U1765-1. 

FLAG 

NOTE NAME IDENTIFICATION QTY MORE DATA

1 Contact BACC47DE1A 2 Refer to SWPM 20-20-11 as an 

accepted procedure.

2 Contact BACC47CN1S 4 Refer to SWPM 20-61-11 as an 

accepted procedure.

3 Contact BACC47CP1S 1 For connector D40107J. Refer 

to SWPM 20-61-11 as an 

accepted procedure.

Contact BACC47CP3S 1 For connector D40106J. Refer 

to SWPM 20-61-11.

Refer to SWPM 20-60-00 as 

an accepted procedure, (fold 

back method) for instructions 

to use AWG 20 wire in this 

contact.

4 Splice D-436-37 2 Refer to SWPM 20-30-12 as 

an accepted procedure.

5 Terminal Lug BACT12AR202 8 Refer to SWPM 20-30-11 as an 

accepted procedure.

6 Contact BACC47ER1 10 Refer to SWPM 20-81-19 as 

an accepted procedure.

7 Relay Socket BACS16AH1 2 Refer to SWPM 20-81-19 as 

an accepted procedure.

8 Identification Tape 289U1214-10101 1 Tape ID DR10155. Refer to 

SWPM 20-10-11 as an 

accepted procedure.

989752

ADDED WIRE OR NEW ROUTING

EXISTING WIRE

DELETED WIRE OR FORMER ROUTING

(SHEET 3 OF 4)
 FIGURE 2: E-8 Wiring Changes

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BOEING SERVICE BULLETIN 747-28A2262

9 Identification Tape 289U1214-10102 1 Tape ID R7401. Refer to 

SWPM 20-10-11 as an 

accepted procedure.

10 Identification Tape 289U1214-10103 1 Tape ID DR10156. Refer to 

SWPM 20-10-11 as an 

accepted procedure.

11 Identification Tape 289U1214-10104 1 Tape ID R7402. Refer to 

SWPM 20-10-11 as an 

accepted procedure.

FLAG 

NOTE NAME IDENTIFICATION QTY MORE DATA

(SHEET 4 OF 4)
 FIGURE 3: Relay Installation, E-8 Aft Equipment Center

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BOEING SERVICE BULLETIN 747-28A2262

FIGURE 3: Relay Installation, E-8 Aft Equipment Center

AFT E/E EQUIPMENT CENTER

ENTRY DOOR

NO. 5L

MAIN

E8 RACK

AFT EQUIPMENT CENTER - E8

INBD FWD

FWD

UP SEE A

364268

(SHEET 1 OF 3)
 FIGURE 3: Relay Installation, E-8 Aft Equipment Center

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BOEING SERVICE BULLETIN 747-28A2262

This Figure applies to Group 1-3, 9: 

OPTIONAL

INSTALLATION

A

UP

FWD

3

3

2

2

1

1

364449

(SHEET 2 OF 3)
 FIGURE 3: Relay Installation, E-8 Aft Equipment Center

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BOEING SERVICE BULLETIN 747-28A2262

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.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

1 Install Relay TDH-1852-1402 2 --

2 Install Marker BAC27EEL28836 1 Refer to SOPM 20-50-05 

as an accepted procedure.

3 Install Marker BAC27EEL28837 1 Refer to SOPM 20-50-05 

as an accepted procedure.

(SHEET 3 OF 3)
 FIGURE 4: Ship’s Wiring Installation

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FIGURE 4: Ship’s Wiring Installation

This Figure applies to Group 1-9: 

The step numbers shown below agree with the numbers shown in the circle symbols in the figure.

NOTE: The wires added in this Figure connect to existing spare wires that run from disconnect panels AC1401

and AC1402 to the E-8 Aft Equipment Center.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

1

Install Wire W4588-520-20 --

Strap BACS38K7C --

Add new wire to existing wire bundle W4588. Follow existing routing from AC1401 to P415 

panel. Refer to drawings 288U4611, 288U4431, 288U4411, 288U4231, 288U4211, 

288U4151, 288U4156, 288U4150, and 288U4148. Refer to SWPM 20-10-11 and SWPM 

20-10-12 as an accepted procedure for the wire installation. Refer to SWPM 20-10-19 as an 

accepted procedure for the wire bundle separation requirements. Wire bundle W4588 is 

Separation Code 32 and tie color red. 

AC1402

AC1401

P414

PANEL

PANEL

P415

520

STA

1000

STA

1480

STA

2

1

2

1

364691

(SHEET 1 OF 2)
 FIGURE 4: Ship’s Wiring Installation

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2

Install Wire W4437-543-20 --

Strap BACS38K7C --

Add new wire to existing wire bundle W4437. Follow existing routing from AC1402 to P414 

panel. Refer to Wire Bundle Installation drawings 288U4610, 288U4430, 288U4410, 

288U4230, 288U4210, 288U4150, 288U4156, 288U4151, and 288U4147. Refer to SWPM 

20-10-11 and SWPM 20-10-12 as an accepted procedure for the wire installation. Refer to 

SWPM 20-10-19 as an accepted procedure for the wire bundle separation requirements. Wire 

Bundle W4437 is Separation Code 32 and tie color red.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

(SHEET 2 OF 2)
 FIGURE 5: Ship’s Wiring Changes

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FIGURE 5: Ship’s Wiring Changes

This Figure applies to Group 1-9: 

W3942

OR

OR

W3842

W3846

W4478-002-20 2

13

REFERENCE: 747-400 WIRE DIAGRAM 28-21-27, 28-21-28, 28-21-30, 28-21-31

AC1401

30

J D43827P

POS 10

D40406P

CENTER-RIGHT

P415 PNL-PWR

W4488-070-22

D40103P

36 W3851

21 W3944

AE0418

POS 14

W4588-070-20

AE0410

W4588-520-20

J

DISTRIBUTION

POS 15

AP2301

J

E8 EQPT- CTR

AFT- LEFT

D43634J P

AC1402

J

POS 5

D43705P

W4437-543-20

AE0417

POS 10

D40345P J

P414 PNL-PWR

DISTRIBUTION

CENTER-LEFT

23

AP2301

POS 14

W3851

D40108P J

E8 EQPT- CTR

AFT- LEFT

29

9

5

8

7

3

4

2 6

1

ADDED WIRE OR NEW ROUTING

EXISTING WIRE

DELETED WIRE OR FORMER ROUTING

364786

(SHEET 1 OF 2)
 FIGURE 5: Ship’s Wiring Changes

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

NOTE: Use the wire and parts from wire kit 289U1214-102 and 289U1214-103.

FLAG 

NOTE NAME IDENTIFICATION QTY MORE DATA

1 Spare Wire -- -- W4478-002-20 is an existing spare wire.

2 Contact BACC47CN1S 1 Refer to SWPM 20-61-11 as an accepted 

procedure.

3 Contact BACC47CP1S 1 Refer to SWPM 20-61-11 as an accepted 

procedure.

4 Spare Wire -- -- W4488-070-22 is an existing spare wire.

5 End Cap 324484 1 Refer to SWPM 20-30-16 as an accepted 

procedure.

6 Contact BACC47CN1S or 

BACC47CP1S

1 Refer to SWPM 20-61-11 as an accepted 

procedure. BACC47CP1S for airplanes 

RF001-RF006, RM096-RM097, RM136-

RM145, RM261-RM264, RM331-RM333, 

RT471-RT499, RU121, and RU126-

RU132 only.

7 Contact BACC47CP1S or 

BACC47CP3S

1 Refer to SWPM 20-61-11 as an accepted 

procedure. BACC47CP3S for airplanes 

RT043-RT047 and RT433-RT447 only. 

Refer to SWPM 20-60-00 as an accepted 

procedure, (fold back method) for 

instructions to use AWG 20 wire in this 

contact.

8 Pin Number -- -- Pin 21 is pin 4 for airplanes RM136-

RM137, RM156-RM158, RT043-RT047, 

RT431-RT447, RT471-RT499, RT641-

RT645, RU101-RU102, RU121, and 

RU126-RU132 only.

Pin 21 is pin 10 for airplanes RM191-

RM192 and RT551-RT555 only.

Pin 21 is pin 17 for airplanes RM096-

RM097 only.

Pin 21 is pin 20 for airplanes RM801-

RM803, RT001-RT014, RT021-RT022, 

RT061, RT071-RT073, RT101-RT103, 

RT121, RT131-RT137, RT701-RT704, 

RT776-RT777, and RT953-RT954 only.

Pin 21 is pin 28 for airplanes RT781-

RT784 only.

Pin 21 is pin 29 for airplanes RM010, 

RM146-RM147 and RM426 only.

9 Spare Wire -- -- W4588-070-20 is an existing spare wire.

(SHEET 2 OF 2)
 FIGURE 6: P414 Panel Wiring Changes

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FIGURE 6: P414 Panel Wiring Changes

This Figure applies to Group 1-7: 

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

NOTE: Use the wire and parts from wire kit 289U1214-102. Straps are part of Top Kit 015U1765-1. For the

wire installed in ground block GDX3-DC; if the ground block is full, use an adjacent or nearby ground

block with open contact cavities that the wire will reach.

FLAG 

NOTE NAME IDENTIFICATION QTY MORE DATA

1 Contact BACC47DE1A 1 Refer to SWPM 20-20-11 as an 

accepted procedure.

2 Contact BACC47DJ1 2 Refer to SWPM 20-81-12 as 

an accepted procedure.

REFERENCE: 747-400 WIRE DIAGRAM

NORM

JTSN

NC

NC

W3846

W3842

OR

595-20

594-20

W4437

GDX3-DC

23

P D40345J

POS 10

AE0417

(2 LOCATIONS)

DR7393

OVERRIDE - LEFT

R7393 RLY- JTSN

B3

B1

B2

A3

A1

P414 PNL- PWR DISTRIBUTION CENTER - LEFT

28-21-26

A2

X2

X1

4

1

2

3

365120

EXISTING WIRE

ADDED WIRE OR NEW ROUTING

(SHEET 1 OF 2)
 FIGURE 6: P414 Panel Wiring Changes

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3 Contact BACC47CP1S or 

BACC47CN1S

1 Refer to SWPM 20-61-11 as an 

accepted procedure. 

BACC47CN1S for airplanes 

RF001-RF006, RM096-

RM097, RM136-RM145, 

RM261-RM264, RM331-

RM333, RT471-RT499, 

RU121, and RU126-RU132 

only.

4 Bundle Number -- -- W3842 for airplanes RT402-

RT403 and RT501 only. All 

other airplanes are W3846. 

Make sure correct coded wires 

from kit are used. Route new 

wires with existing bundles. 

Separation code is N2, tie color 

is white. 

Strap BACS38K10 --

FLAG 

NOTE NAME IDENTIFICATION QTY MORE DATA

(SHEET 2 OF 2)
 FIGURE 7: P415 Panel Wiring Changes

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FIGURE 7: P415 Panel Wiring Changes

This Figure applies to Group 1-9: 

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

NOTE: Use the wire and parts from wire kit 289U1214-103, straps are part of Top Kit 015U1765-1. For the

wire installed in ground block GDX1-DC; if the ground block is full, use an adjacent or nearby ground

block with open contact cavities that the wire will reach.

FLAG 

NOTE NAME IDENTIFICATION QTY MORE DATA

1 Contact BACC47DE1A 1 Refer to SWPM 20-20-11 as an 

accepted procedure.

2 Contact BACC47DJ1 2 Refer to SWPM 20-81-12 as 

an accepted procedure.

3 Contact BACC47CN1S or 

BACC47CN3S

1 Refer to SWPM 20-61-11 

BACC47CN3S for airplanes 

RT043-RT047 and RT433-

RT447 only. Refer to SWPM 

20-60-00 as an accepted 

procedure for (fold back 

method) instructions to use 

AWG 20 wire in this contact.

REFERENCE: 747-400 WIRE DIAGRAM

NORM

JTSN

NC

NC

B3

B1

B2

A3

A1

A2

X2

X1

W3944

OR

W3942

P415 PNL- PWR DISTRIBUTION CENTER - RIGHT

OVERRIDE - RIGHT

R7394 RLY- JTSN

DR7394

1AB-20

1AC-20

GDX1-DC

W4588 21

D40406J

POS 14

AE0418

28-21-29

(2 LOCATIONS)

P

5

4

3

2

1

365101

ADDED WIRE OR NEW ROUTING

EXISTING WIRE

(SHEET 1 OF 2)
 FIGURE 7: P415 Panel Wiring Changes

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4 Pin Number -- -- Pin 21 is pin 4 for airplanes 

RM136-RM137, RM156-

RM158, RT043-RT047, 

RT431-RT447, RT471-RT499, 

RT641-RT645, RU101-RU102, 

RU121, and RU126-RU132 

only.

Pin 21 is pin 10 for airplanes 

RM191-RM192 and RT551-

RT555 only.

Pin 21 is pin 17 for airplanes 

RM096-RM097 only.

Pin 21 is pin 20 for airplanes 

RM801-RM803, RT001-

RT014, RT021-RT022, RT061, 

RT071-RT073, RT101-RT103, 

RT121, RT131-RT137, RT701-

RT704, RT776-RT777, and 

RT953-RT954 only.

Pin 21 is pin 28 for airplanes 

RT781-RT784 only.

Pin 21 is pin 29 for airplanes 

RM010, RM146-RM147 and 

RM426 only.

5 Bundle Number -- -- W3942 for airplanes RT402-

RT403 and RT501 only. All 

other airplanes are W3944. 

Make sure correct coded wires 

from kit are used. Route new 

wires with existing bundles. 

Separation code is N2, tie color 

is white.

Strap BACS38K10 --

FLAG 

NOTE NAME IDENTIFICATION QTY MORE DATA

(SHEET 2 OF 2)
 FIGURE 8: MAWEA Card File Wiring Changes

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FIGURE 8: MAWEA Card File Wiring Changes

This Figure applies to Group 1-9: 

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 289U1214-105.

FLAG 

NOTE NAME IDENTIFICATION QTY MORE DATA

1 End Cap 324484 4 Refer to SWPM 20-30-16 as 

an accepted procedure.

(4 LOCATIONS)

DW3417C

C8 W4758- 633-24

M7952 MAWEA CARD FILE

STA 328

WL 153

RBL 25

C9 W4758- 634-24

C7 W4758- 632-24

C6 W4758- 631-24

REFERENCE: WIRE DIAGRAM 30-41-21, 30-41-31

1

365108

ADDED WIRE OR NEW ROUTING

EXISTING WIRE

DELETED WIRE OR FORMER ROUTING

(SHEET 1 OF 1)
 FIGURE 9: E2-6 Shelf Wiring Changes

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FIGURE 9: E2-6 Shelf Wiring Changes

This Figure applies to Group 1, 5, 9: 

CAUTION: USE THE PRECAUTIONS FOR ELECTROSTATIC DISCHARGE AS SPECIFIED IN 747-400

AMM 20-41-02 AND 747-400 AMM 20-41-03. ELECTROSTATIC DISCHARGE CAN DAMAGE

COMPONENTS.

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

(3 LOCATIONS)

(3 LOCATIONS)

E2-6 EQPT CENTER- MAIN RIGHT-SHELF 6

AR0426

M7353 EIU-L

M7352 EIU-C

M7351 EIU-R

DM7353BA

DM7352BA

DM7351BA

G6

G6

G6

M4260 WIU

D2

D2

D2

DW2611A

DW2631A

DW2651A

W4261-01K-24

W4262-01K-24

W4263-01K-24

REFERENCE: 747-400 WIRING DIAGRAM 28-42-15

1

2

ADDED WIRE OR NEW ROUTING

379748

(SHEET 1 OF 2)
 FIGURE 9: E2-6 Shelf Wiring Changes

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NOTE: Use the wire and parts from wire kit 289U1214-104. Use straps from top kit 015U1765-1 and route new

wire with existing bundle. Wire bundle is Separation Code N2, Color White.

FLAG 

NOTE NAME IDENTIFICATION QTY MORE DATA

1 Contact BACC47EF1 3 Refer to SWPM 20-71-14 as 

an accepted procedure.

2 Contact BACC47EG2 3 Refer to SWPM 20-72-17 as 

an accepted procedure.

(SHEET 2 OF 2)
 FIGURE 10: E2-6 Shelf Wire Integration Unit Wiring Changes

Original Issue: March 15, 2007

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FIGURE 10: E2-6 Shelf Wire Integration Unit Wiring Changes

MAIN EQUIPMENT CENTER

M4260 WIU

E2-6 SHELF

1 THROUGH 3

SEE DETAILS

FWD

380296

(SHEET 1 OF 5)
 FIGURE 10: E2-6 Shelf Wire Integration Unit Wiring Changes

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This Figure applies to Group 1, 5, 9: 

E2-6 EQPT CENTER- MAIN RIGHT-SHELF 6

M4260 WIU

DQ2611

D2 GDY1-17

DW2611A

D2

DW2631A DQ2631

DQ2651

D2

DW2651A

AR0426 W4260

GDY5-17

GDY3-17

REFERENCE: 747-400 WIRE DIAGRAM 28-42-15

ADDED WIRE OR NEW ROUTING

380339

EXISTING WIRE

(SHEET 2 OF 5)
 FIGURE 10: E2-6 Shelf Wire Integration Unit Wiring Changes

Original Issue: March 15, 2007

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CAUTION: USE THE PRECAUTIONS FOR ELECTROSTATIC DISCHARGE AS SPECIFIED IN 747-400

AMM 20-41-02 AND 747-400 AMM 20-41-03. ELECTROSTATIC DISCHARGE CAN DAMAGE

COMPONENTS.

Change the wire wrap wires in the sequence shown in this table. Install the wire along the routing shown on the 

subsequent pages. Refer to SWPM 20-72-18 as an accepted procedure.

ACTION 

(a)

WIRE NO. 

(b)

TYPE 

(c)

FROM TO LENGTH 

(d)

NOTES 

(e)

SL 

EQUIP. NO. PIN EQUIP. NO. PIN (f)

ADD QF1062-24 RD DQ2651 D2 GDY0005 17 6.0 -- --

ADD QF1064-24 RD DQ2631 D2 GDY0003 17 6.0 -- --

ADD QF1066-24 RD DQ2611 D2 GDY0001 17 6.0 -- --

LEGEND FOR DETAILS 1-3

(a) DELETE Delete this wire from the wire integration unit (WIU).

IMPACT Possible impacted wire. A possible impacted wire is one that is installed on the same 

pin as a wire that is removed. Remove this wire if it is installed above a wire that must 

be removed. If removal is necessary, replace it with a new wire. The replacement 

wire part number or material is shown in the TYPE column. If you remove an 

impacted wire that has a sleeve, install the replacement wire in the same sleeve.

ADD Add this wire to the wire integration unit (WIU).

(b) Wire number is shown for reference only; the number is not printed on wire wrap wires.

(c) RD Cut from wire BMS13-46T03C01G024. This wire is BMS 13-46, Type 3, Class 1, 

AWG 24.

(d) The length of wire is in inches. Use these lengths as aids only. Cut the wire to the correct length 

during the installation.

(e) --

(f) --

(SHEET 3 OF 5)
 FIGURE 10: E2-6 Shelf Wire Integration Unit Wiring Changes

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DETAIL 1

ACTION 

(a)

WIRE NO. 

(b)

TYPE 

(c)

FROM TO LENGTH 

(d)

NOTES 

(e)

SL 

EQUIP. NO. PIN EQUIP. NO. PIN (f)

ADD QF1062-24 RD DQ2651 D2 GDY0005 17 6.0 -- --

1 2 3 4 5 6 7 8 9 1112131415 10

A

B

C

D

E

DQ2651

M4260 WIU

GDY5

DETAIL 1

16

1 15

30

380342

A

B

C

D

E

1 2 3 4 5 6 7 8 9 1112131415 10

DQ2631 GDY3

M4260 WIU

DETAIL 2

15

30

1

16

380343

(SHEET 4 OF 5)
 FIGURE 10: E2-6 Shelf Wire Integration Unit Wiring Changes

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DETAIL 2

ACTION 

(a)

WIRE NO. 

(b)

TYPE 

(c)

FROM TO LENGTH 

(d)

NOTES 

(e)

SL 

EQUIP. NO. PIN EQUIP. NO. PIN (f)

ADD QF1064-24 RD DQ2631 D2 GDY0003 17 6.0 -- --

DETAIL 3

ACTION 

(a)

WIRE NO. 

(b)

TYPE 

(c)

FROM TO LENGTH 

(d)

NOTES 

(e)

SL 

EQUIP. NO. PIN EQUIP. NO. PIN (f)

ADD QF1066-24 RD DQ2611 D2 GDY0001 17 6.0 -- --

A

B

C

D

E

1 2 3 4 5 6 7 8 9 1112131415 10

DQ2611 GDY1

M4260 WIU

DETAIL 3

16

15

30

1

380344

(SHEET 5 OF 5)
 FIGURE 11: E2-6 Shelf Wiring Changes

Original Issue: March 15, 2007

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FIGURE 11: E2-6 Shelf Wiring Changes

This Figure applies to Group 2, 6: 

CAUTION: USE THE PRECAUTIONS FOR ELECTROSTATIC DISCHARGE AS SPECIFIED IN 747-400

AMM 20-41-02 AND 747-400 AMM 20-41-03. ELECTROSTATIC DISCHARGE CAN DAMAGE

COMPONENTS.

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

(3 LOCATIONS)

(3 LOCATIONS) AR0426

E2-6 EQPT CENTER- MAIN RIGHT-SHELF 6

M7353 EIU-L

M7352 EIU-C

M7351 EIU-R

DM7353BA

DM7352BA

DM7351BA

G6

G6

G6

M4260 WIU

A12

A12

D7

DW2625A

DW2631A

DW2651A

W4261-01K-24

W4262-01K-24

W4263-01K-24

1

2

REFERENCE: 747-400 WIRE DIAGRAM 28-42-15

ADDED WIRE OR NEW ROUTING

380347

(SHEET 1 OF 2)
 FIGURE 11: E2-6 Shelf Wiring Changes

Original Issue: March 15, 2007

Revision 2: August 13, 2009 747-28A2262

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NOTE: Use the wire and parts from wire kit 289U1214-104. Use straps from top kit 015U1765-1 and route new

wire with existing bundle. Wire bundle is Separation Code N2, Color White.

FLAG 

NOTE NAME IDENTIFICATION QTY MORE DATA

1 Contact BACC47EF1 3 Refer to SWPM 20-71-14 as 

an accepted procedure.

2 Contact BACC47EG2 3 Refer to SWPM 20-72-17 as 

an accepted procedure.

(SHEET 2 OF 2)
 FIGURE 12: E2-6 Shelf Wire Integration Unit Wiring Changes

Original Issue: March 15, 2007

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FIGURE 12: E2-6 Shelf Wire Integration Unit Wiring Changes

MAIN EQUIPMENT CENTER

M4260 WIU

E2-6 SHELF

1 THROUGH 3

SEE DETAILS

FWD

FWD

380351

(SHEET 1 OF 5)
 FIGURE 12: E2-6 Shelf Wire Integration Unit Wiring Changes

Original Issue: March 15, 2007

Revision 2: August 13, 2009 747-28A2262

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This Figure applies to Group 2, 6: 

E2-6 EQPT CENTER- MAIN RIGHT-SHELF 6

M4260 WIU

GDY2-22

GDY3-12

GDY5-12

DQ2651

DQ2631

DQ2625

A12

A12

D7

W4260

REFERENCE: 747-400 WIRE DIAGRAM 28-42-15

384942

ADDED WIRE OR NEW ROUTING

(SHEET 2 OF 5)
 FIGURE 12: E2-6 Shelf Wire Integration Unit Wiring Changes

Original Issue: March 15, 2007

Revision 2: August 13, 2009 747-28A2262

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CAUTION: USE THE PRECAUTIONS FOR ELECTROSTATIC DISCHARGE AS GIVEN IN 747-400 AMM

20-41-02 AND 747-400 AMM 20-41-03. ELECTROSTATIC DISCHARGE CAN DAMAGE

COMPONENTS.

Change the wire wrap wires in the sequence shown in this table. Install the wire along the routing shown on the 

subsequent pages. Refer to SWPM 20-72-18.

ACTION 

(a)

WIRE NO. 

(b)

TYPE 

(c)

FROM TO LENGTH 

(d)

NOTES 

(e)

SL 

EQUIP. NO. PIN EQUIP. NO. PIN (f)

ADD QF1062-24 RD DQ2651 A12 GDY0005 12 6.0 -- --

ADD QF1064-24 RD DQ2631 A12 GDY0003 12 6.0 -- --

ADD QF1066-24 RD DQ2625 D7 GDY0002 22 6.0 -- --

LEGEND FOR DETAILS 1-3

(a) DELETE Delete this wire from the wire integration unit (WIU).

IMPACT Possible impacted wire. A possible impacted wire is one that is installed on the same 

pin as a wire that is removed. Remove this wire if it is installed above a wire that must 

be removed. If removal is necessary, replace it with a new wire. The replacement 

wire part number or material is shown in the TYPE column. If you remove an 

impacted wire that has a sleeve, install the replacement wire in the same sleeve.

ADD Add this wire to the wire integration unit (WIU).

(b) Wire number is shown for reference only; the number is not printed on wire wrap wires.

(c) RD Cut from wire BMS13-46T03C01G024. This wire is BMS 13-46, Type 3, Class 1, 

AWG 24.

(d) The length of wire is in inches. Use these lengths as aids only. Cut the wire to the correct length 

during the installation.

(e) --

(f) --

A

B

C

D

E

1 2 3 4 5 6 7 8 9 11 12 13 14 15 10

M4260 WIU

DQ2651 GDY5

DETAIL 1

15

30

1

16

380352

(SHEET 3 OF 5)
 FIGURE 12: E2-6 Shelf Wire Integration Unit Wiring Changes

Original Issue: March 15, 2007

Revision 2: August 13, 2009 747-28A2262

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DETAIL 1

ACTION 

(a)

WIRE NO. 

(b)

TYPE 

(c)

FROM TO LENGTH 

(d)

NOTES 

(e)

SL 

EQUIP. NO. PIN EQUIP. NO. PIN (f)

ADD QF1062-24 RD DQ2651 A12 GDY0005 12 6.0 -- --

DETAIL 2

ACTION 

(a)

WIRE NO. 

(b)

TYPE 

(c)

FROM TO LENGTH 

(d)

NOTES 

(e)

SL 

EQUIP. NO. PIN EQUIP. NO. PIN (f)

ADD QF1064-24 RD DQ2631 A12 GDY0003 12 6.0 -- --

A

B

C

D

E

1 2 3 4 5 6 7 8 9 11 12 13 14 15 10

M4260 WIU

DQ2631 GDY3

DETAIL 2

15

30

1

16

380353

(SHEET 4 OF 5)
 FIGURE 12: E2-6 Shelf Wire Integration Unit Wiring Changes

Original Issue: March 15, 2007

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DETAIL 3

ACTION 

(a)

WIRE NO. 

(b)

TYPE 

(c)

FROM TO LENGTH 

(d)

NOTES 

(e)

SL 

EQUIP. NO. PIN EQUIP. NO. PIN (f)

ADD QF1066-24 RD DQ2625 D7 GDY0002 22 6.0 -- --

A

B

C

D

E

1 2 3 4 5 6 7 8 9 11 12 13 14 15 10

A

B

C

D

E

1 2 3 4 5 6 7 8 9 11 12 13 14 15 10

A

B

C

D

E

1 2 3 4 5 6 7 8 9 11 12 13 14 15 10

M4260 WIU

DQ2625 DQ2623 DQ2621 GDY2

DETAIL 3

15

30

1

16

380354

(SHEET 5 OF 5)
 FIGURE 13: E2-6 Shelf Wiring Changes

Original Issue: March 15, 2007

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FIGURE 13: E2-6 Shelf Wiring Changes

This Figure applies to Group 4: 

CAUTION: USE THE PRECAUTIONS FOR ELECTROSTATIC DISCHARGE AS GIVEN IN 747-400 AMM

20-41-02 AND 747-400 AMM 20-41-03. ELECTROSTATIC DISCHARGE CAN DAMAGE

COMPONENTS.

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

(3 LOCATIONS)

(3 LOCATIONS) W4260

AR0426

DM7353BA

DM7352BA

DM7351BA

G6

G6

G6

M4260 WIU

A4

E10

A4

DW2613A

DW2631A

DW2653A

W4261-01K-24

W4262-01K-24

W4263-01K-24

E2-6 EQPT CENTER- MAIN RIGHT-SHELF 6

M7353 EIU-L

M7352 EIU-C

M7351 EIU-R

1

2

REFERENCE: 747-400 WIRE DIAGRAM 28-42-15

384969

ADDED WIRE OR NEW ROUTING

(SHEET 1 OF 2)
 FIGURE 13: E2-6 Shelf Wiring Changes

Original Issue: March 15, 2007

Revision 2: August 13, 2009 747-28A2262

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NOTE: Use the wire and parts from wire kit 289U1214-104. Use straps from top kit 015U1765-1 and route new

wire with existing bundle. Wire bundle is Separation Code N2, Color White.

FLAG 

NOTE NAME IDENTIFICATION QTY MORE DATA

1 Contact BACC47EF1 3 Refer to SWPM 20-71-14 as 

an accepted procedure.

2 Contact BACC47EG2 3 Refer to SWPM 20-72-17 as 

an accepted procedure.

(SHEET 2 OF 2)
 FIGURE 14: E2-6 Shelf Wiring Changes

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FIGURE 14: E2-6 Shelf Wiring Changes

This Figure applies to Group 3, 7-8: 

CAUTION: USE THE PRECAUTIONS FOR ELECTROSTATIC DISCHARGE AS GIVEN IN 747-400 AMM

20-41-02 AND 747-400 AMM 20-41-03. ELECTROSTATIC DISCHARGE CAN DAMAGE

COMPONENTS.

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

REFERENCE: 747-400 WIRE DIAGRAM

E2-6 EQPT CENTER- MAIN RIGHT-SHELF 6

M4260 WIU

(3 LOCATIONS)

(3 LOCATIONS) AR0426 W4260

M7353 EIU-L

M7352 EIU-C

M7351 EIU-R

DM7353BA

DM7352BA

DM7351BA

G6

G6

G6 D1

E10

DW2625A

DW2631A

DW2665A

W4261-01K-24

W4262-01K-24

W4263-01K-24

28-42-15

D1

1

2

380356

ADDED WIRE OR NEW ROUTING

(SHEET 1 OF 2)
 FIGURE 14: E2-6 Shelf Wiring Changes

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NOTE: Use the wire and parts from wire kit 289U1214-104. Use straps from top kit 015U1765-1 and route new

wire with existing bundle. Wire bundle is Separation Code N2, Color White.

FLAG 

NOTE NAME IDENTIFICATION QTY MORE DATA

1 Contact BACC47EF1 3 Refer to SWPM 20-71-14 as 

an accepted procedure.

2 Contact BACC47EG2 3 Refer to SWPM 20-72-17 as 

an accepted procedure.

(SHEET 2 OF 2)
 FIGURE 15: E2-6 Shelf Wire Integration Unit Wiring Changes

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FIGURE 15: E2-6 Shelf Wire Integration Unit Wiring Changes

1 THROUGH 3

SEE DETAILS

M4260 WIU

E2-6 SHELF

MAIN EQUIPMENT CENTER

FWD

FWD

380357

(SHEET 1 OF 6)
 FIGURE 15: E2-6 Shelf Wire Integration Unit Wiring Changes

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This Figure applies to Group 3, 7-8: 

W4260

M4260 WIU

GDY2-17

GDY3-10

GDY6-16

DQ2665

DQ2631

DQ2625

D1

E10

D1

E2-6 EQPT CENTER- MAIN RIGHT-SHELF 6

REFERENCE: 747-400 WIRE DIAGRAM 28-42-15

384962

ADDED WIRE OR NEW ROUTING

(SHEET 2 OF 6)
 FIGURE 15: E2-6 Shelf Wire Integration Unit Wiring Changes

Original Issue: March 15, 2007

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CAUTION: USE THE PRECAUTIONS FOR ELECTROSTATIC DISCHARGE AS GIVEN IN 747-400 AMM

20-41-02 AND 747-400 AMM 20-41-03. ELECTROSTATIC DISCHARGE CAN DAMAGE

COMPONENTS.

Change the wire wrap wires in the sequence shown in this table. Install the wire along the routing shown on the 

subsequent pages. Refer to SWPM 20-72-18.

ACTION 

(a)

WIRE NO. 

(b)

TYPE 

(c)

FROM TO LENGTH 

(d)

NOTES 

(e)

SL 

EQUIP. NO. PIN EQUIP. NO. PIN (f)

ADD QF1062-24 RD DQ2665 D1 GDY0006 16 6.0 -- --

ADD QF1064-24 RD DQ2631 E10 GDY0003 10 6.0 -- --

ADD QF1066-24 RD DQ2625 D1 GDY0002 17 6.0 -- --

LEGEND FOR DETAILS 1-3

(a) DELETE Delete this wire from the wire integration unit (WIU).

IMPACT Possible impacted wire. A possible impacted wire is one that is installed on the same 

pin as a wire that is removed. Remove this wire if it is installed above a wire that must 

be removed. If removal is necessary, replace it with a new wire. The replacement 

wire part number or material is shown in the TYPE column. If you remove an 

impacted wire that has a sleeve, install the replacement wire in the same sleeve.

ADD Add this wire to the wire integration unit (WIU).

(b) Wire number is shown for reference only; the number is not printed on wire wrap wires.

(c) RD Cut from wire BMS13-46T03C01G024. This wire is BMS 13-46, Type 3, Class 1, 

AWG 24.

(d) The length of wire is in inches. Use these lengths as aids only. Cut the wire to the correct length 

during the installation.

(e) --

(f) --

(SHEET 3 OF 6)
 FIGURE 15: E2-6 Shelf Wire Integration Unit Wiring Changes

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BOEING SERVICE BULLETIN 747-28A2262

DETAIL 1

ACTION 

(a)

WIRE NO. 

(b)

TYPE 

(c)

FROM TO LENGTH 

(d)

NOTES 

(e)

SL 

EQUIP. NO. PIN EQUIP. NO. PIN (f)

ADD QF1062-24 RD DQ2665 D1 GDY0006 16 6.0 -- --

A

B

C

D

E

1 2 3 4 5 6 7 8 9 11 12 13 14 15 10

A

B

C

D

E

1 2 3 4 5 6 7 8 9 11 12 13 14 15 10

A

B

C

D

E

1 2 3 4 5 6 7 8 9 11 12 13 14 15 10

M4260 WIU

DQ2665 DQ2663 DQ2661 GDY6

DETAIL 1

15

30

1

16

380360

(SHEET 4 OF 6)
 FIGURE 15: E2-6 Shelf Wire Integration Unit Wiring Changes

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BOEING SERVICE BULLETIN 747-28A2262

DETAIL 2

ACTION 

(a)

WIRE NO. 

(b)

TYPE 

(c)

FROM TO LENGTH 

(d)

NOTES 

(e)

SL 

EQUIP. NO. PIN EQUIP. NO. PIN (f)

ADD QF1064-24 RD DQ2631 E10 GDY0003 10 6.0 -- --

A

B

C

D

E

1 2 3 4 5 6 7 8 9 11 12 13 14 15 10

M4260 WIU

DQ2631 GDY3

DETAIL 2

15

30

1

16

380361

(SHEET 5 OF 6)
 FIGURE 15: E2-6 Shelf Wire Integration Unit Wiring Changes

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DETAIL 3

ACTION 

(a)

WIRE NO. 

(b)

TYPE 

(c)

FROM TO LENGTH 

(d)

NOTES 

(e)

SL 

EQUIP. NO. PIN EQUIP. NO. PIN (f)

ADD QF1066-24 RD DQ2625 D1 GDY0002 17 6.0 -- --

A

B

C

D

E

1 2 3 4 5 6 7 8 9 11 12 13 14 15 10

A

B

C

D

E

1 2 3 4 5 6 7 8 9 11 12 13 14 15 10

A

B

C

D

E

1 2 3 4 5 6 7 8 9 11 12 13 14 15 10

M4260 WIU

DQ2625 DQ2623 DQ2621 GDY2

DETAIL 3

15

30

1

16

380362

(SHEET 6 OF 6)
 FIGURE 16: E2-6 Shelf Wire Integration Unit Wiring Changes

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FIGURE 16: E2-6 Shelf Wire Integration Unit Wiring Changes

M4260 WIU

E2-6 SHELF

1 THROUGH 3

SEE DETAILS

MAIN EQUIPMENT CENTER

FWD

384970

(SHEET 1 OF 5)
 FIGURE 16: E2-6 Shelf Wire Integration Unit Wiring Changes

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Revision 2: August 13, 2009 747-28A2262

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This Figure applies to Group 4: 

E2-6 EQPT CENTER- MAIN RIGHT-SHELF 6

W4260

M4260 WIU

GDY1-4

GDY3-10

GDY5-4

DQ2653

DQ2631

DQ2613

A4

E10

A4

REFERENCE: 747-400 WIRE DIAGRAM 28-42-15

ADDED WIRE OR NEW ROUTING

384980

(SHEET 2 OF 5)
 FIGURE 16: E2-6 Shelf Wire Integration Unit Wiring Changes

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Revision 2: August 13, 2009 747-28A2262

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BOEING SERVICE BULLETIN 747-28A2262

CAUTION: USE THE PRECAUTIONS FOR ELECTROSTATIC DISCHARGE AS GIVEN IN 747-400 AMM

20-41-02 AND 747-400 AMM 20-41-03. ELECTROSTATIC DISCHARGE CAN DAMAGE

COMPONENTS.

Change the wire wrap wires in the sequence shown in this table. Install the wire along the routing shown on the 

subsequent pages. Refer to SWPM 20-72-18.

ACTION 

(a)

WIRE NO. 

(b)

TYPE 

(c)

FROM TO LENGTH 

(d)

NOTES 

(e)

SL 

EQUIP. NO. PIN EQUIP. NO. PIN (f)

ADD QF1062-24 RD DQ2653 A4 GDY0005 4 6.0 -- --

ADD QF1064-24 RD DQ2631 E10 GDY0003 10 6.0 -- --

ADD QF1066-24 RD DQ2613 A4 GDY0001 4 6.0 -- --

LEGEND FOR DETAILS 1-3

(a) DELETE Delete this wire from the wire integration unit (WIU).

IMPACT Possible impacted wire. A possible impacted wire is one that is installed on the same 

pin as a wire that is removed. Remove this wire if it is installed above a wire that must 

be removed. If removal is necessary, replace it with a new wire. The replacement 

wire part number or material is shown in the TYPE column. If you remove an 

impacted wire that has a sleeve, install the replacement wire in the same sleeve.

ADD Add this wire to the wire integration unit (WIU).

(b) Wire number is shown for reference only; the number is not printed on wire wrap wires.

(c) RD Cut from wire BMS13-46T03C01G024. This wire is BMS 13-46, Type 3, Class 1, 

AWG 24.

(d) The length of wire is in inches. Use these lengths as aids only. Cut the wire to the correct length 

during the installation.

(e) --

(f) --

(SHEET 3 OF 5)
 FIGURE 16: E2-6 Shelf Wire Integration Unit Wiring Changes

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DETAIL 1

ACTION 

(a)

WIRE NO. 

(b)

TYPE 

(c)

FROM TO LENGTH 

(d)

NOTES 

(e)

SL 

EQUIP. NO. PIN EQUIP. NO. PIN (f)

ADD QF1062-24 RD DQ2653 A4 GDY0005 4 6.0 -- --

A

B

C

D

E

1 2 3 4 5 6 7 8 9 11 12 13 14 15 10

A

B

C

D

E

1 2 3 4 5 6 7 8 9 11 12 13 14 15 10

M4260 WIU

DQ2653 DQ2651 GDY5

DETAIL 1

15

30

1

16

384994

A

B

C

D

E

1 2 3 4 5 6 7 8 9 11 12 13 14 15 10

M4260 WIU

DQ2631 GDY3

DETAIL 2

15

30

1

16

384993

(SHEET 4 OF 5)
 FIGURE 16: E2-6 Shelf Wire Integration Unit Wiring Changes

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DETAIL 2

ACTION 

(a)

WIRE NO. 

(b)

TYPE 

(c)

FROM TO LENGTH 

(d)

NOTES 

(e)

SL 

EQUIP. NO. PIN EQUIP. NO. PIN (f)

ADD QF1064-24 RD DQ2631 E10 GDY0003 10 6.0 -- --

DETAIL 3

ACTION 

(a)

WIRE NO. 

(b)

TYPE 

(c)

FROM TO LENGTH 

(d)

NOTES 

(e)

SL 

EQUIP. NO. PIN EQUIP. NO. PIN (f)

ADD QF1066-24 RD DQ2613 A4 GDY0001 4 6.0 -- --

A

B

C

D

E

1 2 3 4 5 6 7 8 9 11 12 13 14 15 10

A

B

C

D

E

1 2 3 4 5 6 7 8 9 11 12 13 14 15 10

M4260 WIU

DQ2613 DQ2611 GDY1

DETAIL 3

15

30

1

16

384995

(SHEET 5 OF 5)
 FIGURE 17: Relay Bracket Installation

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FIGURE 17: Relay Bracket Installation

AFT E/E EQUIPMENT CENTER

ENTRY DOOR

NO. 5L

MAIN

E8 RACK

AFT EQUIPMENT CENTER - E8

INBD FWD

FWD

UP

SEE A

1485044

(SHEET 1 OF 3)
 FIGURE 17: Relay Bracket Installation

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This Figure applies to Group 4-8: 

FWD

UP

2

A

3.00

0.5

1

1485076

(SHEET 2 OF 3)
 FIGURE 17: Relay Bracket Installation

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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.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

1 Install Relay Bracket 65B48634-39 1 Prepare surface for fay surface 

bond as given in SWPM 

20-20-00. Refer to SWPM 

20-20-00 and 747-400 SRM 

51-40-02 as an accepted 

procedure for Rivet installation. 

Rivet hole diameter is 0.129 - 

0.132 inch.

Rivet BACR15DR4PAC2 3

2 Repair or 

Replace

Marker -- Repair or replace any relay 

identification markers covered 

by the installation of the new 

relay bracket. Refer to SOPM 

20-50-05 as an accepted 

procedure.

(SHEET 3 OF 3)
 FIGURE 18: Relay Installation, E-8 Aft Equipment Center

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FIGURE 18: Relay Installation, E-8 Aft Equipment Center

AFT E/E EQUIPMENT CENTER

ENTRY DOOR

NO. 5L

MAIN

E8 RACK

AFT EQUIPMENT CENTER - E8

INBD FWD

FWD

UP

SEE A

1485191

(SHEET 1 OF 2)
 FIGURE 18: Relay Installation, E-8 Aft Equipment Center

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This Figure applies to Group 4-8: 

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.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

1 Install Relay TDH-1852-1402 2 --

2 Install Marker BAC27EEL28836 1 Refer to SOPM 20-50-05 

as an accepted procedure.

3 Install Marker BAC27EEL28837 1 Refer to SOPM 20-50-05 

as an accepted procedure.

A

3

2

1

FWD

1485189

(SHEET 2 OF 2)
 FIGURE 19: P414 Panel Wiring Changes

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FIGURE 19: P414 Panel Wiring Changes

This Figure applies to Group 8-9: 

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

NOTE: Use the wire and parts from wire kit 289U1214-102. Straps are part of Top Kit 015U1765-1. For the

wire installed in ground block GDX2-DC; if the ground block is full, use an adjacent or nearby ground

block with open contact cavities that the wire will reach.

FLAG 

NOTE NAME IDENTIFICATION QTY MORE DATA

1 Contact BACC47DE1A 1 Refer to SWPM 20-20-11 as an 

accepted procedure.

2 Contact BACC47DJ1 2 Refer to SWPM 20-81-12 as 

an accepted procedure.

3 Contact BACC47CP1S 1 Refer to SWPM 20-61-11 as an 

accepted procedure.

4 Bundle Number W3846 -- Make sure correct coded wires 

from kit are used. Route new 

wires with existing bundles. 

Separation code is N2, tie color 

is white. 

Strap BACS38K10 --

NORM

JTSN

NC

NC

W3846

595-20

594-20

W4437

GDX2-DC

23

P D40345J

POS 10

AE0417

(2 LOCATIONS)

DR7393

OVERRIDE - LEFT

R7393 RLY- JTSN

B2

B1

B3

A1

A3

P414 PNL- PWR DISTRIBUTION CENTER - LEFT

REFERENCE: 747-400 WIRE DIAGRAM 28-21-26

A2

X2

X1

4

1

2

3

EXISTING WIRE

ADDED WIRE OR NEW ROUTING

1576713

(SHEET 1 OF 1)