Original Issue: March 15, 2007 Revision 2: August 13, 2009 747-28A2262 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 1 of 91 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## BOEING PROPRIETARY, CONFIDENTIAL, AND/OR TRADE SECRET Copyright © 2007 The Boeing Company Unpublished Work - All Rights Reserved Boeing claims copyright in each page of this document only to the extent that the page contains copyrightable subject matter.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, MD-11, MD-80, MD-90, the Boeing logo and the Boeing livery are among the trademarks owned by Boeing or its subsidiaries. No intellectual property license (express or implied) is granted in connection with this document or otherwise.**BLANK PAGE** Original Issue: March 15, 2007 Revision 2: August 13, 2009 747-28A2262 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 2 of 91 

### BOEING SERVICE BULLETIN 747-28A2262

BLANK PAGE**Table of Contents** Original Issue: March 15, 2007 Revision 2: August 13, 2009 747-28A2262 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 3 of 91 

### 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**Table of Contents** Original Issue: March 15, 2007 Revision 2: August 13, 2009 747-28A2262 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 4 of 91 

### 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 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 91Original Issue: March 15, 2007 Revision 2: August 13, 2009 747-28A2262 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 5 of 91 

### 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".Original Issue: March 15, 2007 Revision 2: August 13, 2009 747-28A2262 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 6 of 91 

### 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, 2009Original Issue: March 15, 2007 Revision 2: August 13, 2009 747-28A2262 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 7 of 91 

### 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.Original Issue: March 15, 2007 Revision 2: August 13, 2009 747-28A2262 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 8 of 91 

### 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 30Original Issue: March 15, 2007 Revision 2: August 13, 2009 747-28A2262 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 9 of 91 

### 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 STA379746Original Issue: March 15, 2007 Revision 2: August 13, 2009 747-28A2262 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 10 of 91 

### BOEING SERVICE BULLETIN 747-28A2262

BLANK PAGEOriginal Issue: March 15, 2007 Revision 2: August 13, 2009 747-28A2262 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 11 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

**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.Original Issue: March 15, 2007 Revision 2: August 13, 2009 747-28A2262 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 12 of 91 

### 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**Original Issue: March 15, 2007 Revision 2: August 13, 2009 747-28A2262 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 13 of 91 

### 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–RT955Original Issue: March 15, 2007 Revision 2: August 13, 2009 747-28A2262 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 14 of 91 

### 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–RU017Original Issue: March 15, 2007 Revision 2: August 13, 2009 747-28A2262 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 15 of 91 

### 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–RT605Original Issue: March 15, 2007 Revision 2: August 13, 2009 747-28A2262 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 16 of 91 

### BOEING SERVICE BULLETIN 747-28A2262

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 6Original Issue: March 15, 2007 Revision 2: August 13, 2009 747-28A2262 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 17 of 91 

### BOEING SERVICE BULLETIN 747-28A2262

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**Original Issue: March 15, 2007 Revision 2: August 13, 2009 747-28A2262 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 18 of 91 

### BOEING SERVICE BULLETIN 747-28A2262

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**Original Issue: March 15, 2007 Revision 2: August 13, 2009 747-28A2262 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 19 of 91 

### BOEING SERVICE BULLETIN 747-28A2262

**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.Original Issue: March 15, 2007 Revision 2: August 13, 2009 747-28A2262 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 20 of 91 

### BOEING SERVICE BULLETIN 747-28A2262

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.Original Issue: March 15, 2007 Revision 2: August 13, 2009 747-28A2262 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 21 of 91 

### BOEING SERVICE BULLETIN 747-28A2262

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.Original Issue: March 15, 2007 Revision 2: August 13, 2009 747-28A2262 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 22 of 91 

### BOEING SERVICE BULLETIN 747-28A2262

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 30Original Issue: March 15, 2007 Revision 2: August 13, 2009 747-28A2262 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 23 of 91 

### BOEING SERVICE BULLETIN 747-28A2262

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 +2304.0Original Issue: March 15, 2007 Revision 2: August 13, 2009 747-28A2262 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 24 of 91 

### BOEING SERVICE BULLETIN 747-28A2262

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, 28-22Original Issue: March 15, 2007 Revision 2: August 13, 2009 747-28A2262 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 25 of 91 

### BOEING SERVICE BULLETIN 747-28A2262

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**Original Issue: March 15, 2007 Revision 2: August 13, 2009 747-28A2262 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 26 of 91 

### BOEING SERVICE BULLETIN 747-28A2262

BLANK PAGEOriginal Issue: March 15, 2007 Revision 2: August 13, 2009 747-28A2262 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 27 of 91 

### BOEING SERVICE BULLETIN 747-28A2262

**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 $4,112.00Original Issue: March 15, 2007 Revision 2: August 13, 2009 747-28A2262 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 28 of 91 

### BOEING SERVICE BULLETIN 747-28A2262

**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**  **Number Notes -105 -104 -103 -102 -101 -1**  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 -- --Original Issue: March 15, 2007 Revision 2: August 13, 2009 747-28A2262 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 29 of 91 

### BOEING SERVICE BULLETIN 747-28A2262

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**  **Number Notes -105 -104 -103 -102 -101 -1** Original Issue: March 15, 2007 Revision 2: August 13, 2009 747-28A2262 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 30 of 91 

### BOEING SERVICE BULLETIN 747-28A2262

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.Original Issue: March 15, 2007 Revision 2: August 13, 2009 747-28A2262 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 31 of 91 

### BOEING SERVICE BULLETIN 747-28A2262

**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.Original Issue: March 15, 2007 Revision 2: August 13, 2009 747-28A2262 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 32 of 91 

### BOEING SERVICE BULLETIN 747-28A2262

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 powerOriginal Issue: March 15, 2007 Revision 2: August 13, 2009 747-28A2262 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 33 of 91 

### BOEING SERVICE BULLETIN 747-28A2262

(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 powerOriginal Issue: March 15, 2007 Revision 2: August 13, 2009 747-28A2262 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 34 of 91 

### BOEING SERVICE BULLETIN 747-28A2262

(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 powerOriginal Issue: March 15, 2007 Revision 2: August 13, 2009 747-28A2262 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 35 of 91 

### BOEING SERVICE BULLETIN 747-28A2262

(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 powerOriginal Issue: March 15, 2007 Revision 2: August 13, 2009 747-28A2262 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 36 of 91 

### BOEING SERVICE BULLETIN 747-28A2262

(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 powerOriginal Issue: March 15, 2007 Revision 2: August 13, 2009 747-28A2262 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 37 of 91 

### BOEING SERVICE BULLETIN 747-28A2262

(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** Original Issue: March 15, 2007 Revision 2: August 13, 2009 747-28A2262 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 38 of 91 

### BOEING SERVICE BULLETIN 747-28A2262

**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 FWD INBD

FWD UP A SEE356692

**(SHEET 1 OF 3) FIGURE 1: Change the E-8 Aft Equipment Center**  Original Issue: March 15, 2007 Revision 2: August 13, 2009 747-28A2262 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 39 of 91 

### BOEING SERVICE BULLETIN 747-28A2262

This Figure applies to Group 1-3, 9: 

## A-A 5.10 

## A

A

UP
INBD 2

2 UP

FWD



### A 2 3 1357070

**(SHEET 2 OF 3) FIGURE 1: Change the E-8 Aft Equipment Center**  Original Issue: March 15, 2007 Revision 2: August 13, 2009 747-28A2262 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 40 of 91 

### 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 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**  Original Issue: March 15, 2007 Revision 2: August 13, 2009 747-28A2262 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 41 of 91 

### BOEING SERVICE BULLETIN 747-28A2262

**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-LEFTR10155 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
P D40107J W4478 POS 14 AP2301

176-20 185-20

059-20 058-20

GDX1-DC 058-20

POS 16 AP2301 DR10155 (5 LOCATIONS)

2360314

**(SHEET 1 OF 4) FIGURE 2: E-8 Wiring Changes**  Original Issue: March 15, 2007 Revision 2: August 13, 2009 747-28A2262 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 42 of 91 

### 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

P D40106J 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

10 7 11 GDX1-DC361668

**(SHEET 2 OF 4) FIGURE 2: E-8 Wiring Changes**  Original Issue: March 15, 2007 Revision 2: August 13, 2009 747-28A2262 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 43 of 91 

### BOEING SERVICE BULLETIN 747-28A2262

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**  Original Issue: March 15, 2007 Revision 2: August 13, 2009 747-28A2262 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 44 of 91 

### 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**  Original Issue: March 15, 2007 Revision 2: August 13, 2009 747-28A2262 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 45 of 91 

### 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 FWD INBD

FWD UP A SEE364268

**(SHEET 1 OF 3) FIGURE 3: Relay Installation, E-8 Aft Equipment Center**  Original Issue: March 15, 2007 Revision 2: August 13, 2009 747-28A2262 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 46 of 91 

### BOEING SERVICE BULLETIN 747-28A2262

This Figure applies to Group 1-3, 9: OPTIONAL INSTALLATION



### A UP

FWD 3 3

2 2

1 1364449

**(SHEET 2 OF 3) FIGURE 3: Relay Installation, E-8 Aft Equipment Center**  Original Issue: March 15, 2007 Revision 2: August 13, 2009 747-28A2262 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 47 of 91 

### 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**  Original Issue: March 15, 2007 Revision 2: August 13, 2009 747-28A2262 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 48 of 91 

### BOEING SERVICE BULLETIN 747-28A2262

**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 1364691

**(SHEET 1 OF 2) FIGURE 4: Ship’s Wiring Installation**  Original Issue: March 15, 2007 Revision 2: August 13, 2009 747-28A2262 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 49 of 91 

### BOEING SERVICE BULLETIN 747-28A2262

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**  Original Issue: March 15, 2007 Revision 2: August 13, 2009 747-28A2262 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 50 of 91 

### BOEING SERVICE BULLETIN 747-28A2262

**FIGURE 5: Ship’s Wiring Changes**

This Figure applies to Group 1-9: 

### W3942 OR OR W3842
W3846 2 W4478-002-20

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 W3851 36

W3944 21 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 ROUTING364786

**(SHEET 1 OF 2) FIGURE 5: Ship’s Wiring Changes**  Original Issue: March 15, 2007 Revision 2: August 13, 2009 747-28A2262 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 51 of 91 

### BOEING SERVICE BULLETIN 747-28A2262

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**  Original Issue: March 15, 2007 Revision 2: August 13, 2009 747-28A2262 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 52 of 91 

### BOEING SERVICE BULLETIN 747-28A2262

**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

D40345J P 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

3365120

EXISTING WIRE ADDED WIRE OR NEW ROUTING

**(SHEET 1 OF 2) FIGURE 6: P414 Panel Wiring Changes**  Original Issue: March 15, 2007 Revision 2: August 13, 2009 747-28A2262 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 53 of 91 

### BOEING SERVICE BULLETIN 747-28A2262

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**  Original Issue: March 15, 2007 Revision 2: August 13, 2009 747-28A2262 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 54 of 91 

### BOEING SERVICE BULLETIN 747-28A2262

**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

21 W4588
D40406J POS 14 AE0418

28-21-29 (2 LOCATIONS)

P 5

4 3 2

1365101
ADDED WIRE OR NEW ROUTING EXISTING WIRE

**(SHEET 1 OF 2) FIGURE 7: P415 Panel Wiring Changes**  Original Issue: March 15, 2007 Revision 2: August 13, 2009 747-28A2262 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 55 of 91 

### BOEING SERVICE BULLETIN 747-28A2262

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**  Original Issue: March 15, 2007 Revision 2: August 13, 2009 747-28A2262 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 56 of 91 

### BOEING SERVICE BULLETIN 747-28A2262

**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 W4758- 634-24 C9 W4758- 632-24 C7 W4758- 631-24 C6

REFERENCE: WIRE DIAGRAM 30-41-21, 30-41-31 1365108 ADDED WIRE OR NEW ROUTING

EXISTING WIRE DELETED WIRE OR FORMER ROUTING

**(SHEET 1 OF 1) FIGURE 9: E2-6 Shelf Wiring Changes**  Original Issue: March 15, 2007 Revision 2: August 13, 2009 747-28A2262 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 57 of 91 

### BOEING SERVICE BULLETIN 747-28A2262

**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 2379748 ADDED WIRE OR NEW ROUTING

**(SHEET 1 OF 2) FIGURE 9: E2-6 Shelf Wiring Changes**  Original Issue: March 15, 2007 Revision 2: August 13, 2009 747-28A2262 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 58 of 91 

### BOEING SERVICE BULLETIN 747-28A2262

**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 Revision 2: August 13, 2009 747-28A2262 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 59 of 91 

### BOEING SERVICE BULLETIN 747-28A2262

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



### MAIN EQUIPMENT CENTER M4260 WIU E2-6 SHELF 1 THROUGH 3 SEE DETAILS FWD380296

**(SHEET 1 OF 5) FIGURE 10: E2-6 Shelf Wire Integration Unit Wiring Changes**  Original Issue: March 15, 2007 Revision 2: August 13, 2009 747-28A2262 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 60 of 91 

### BOEING SERVICE BULLETIN 747-28A2262

This Figure applies to Group 1, 5, 9: E2-6 EQPT CENTER- MAIN RIGHT-SHELF 6 M4260 WIU

DQ2611 GDY1-17 D2
DW2611A D2
DW2631A DQ2631 DQ2651 D2
DW2651A AR0426 W4260
GDY5-17

GDY3-17

REFERENCE: 747-400 WIRE DIAGRAM 28-42-15380339 ADDED WIRE OR NEW ROUTING EXISTING WIRE

**(SHEET 2 OF 5) FIGURE 10: E2-6 Shelf Wire Integration Unit Wiring Changes**  Original Issue: March 15, 2007 Revision 2: August 13, 2009 747-28A2262 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 61 of 91 

### BOEING SERVICE BULLETIN 747-28A2262

**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**  **(f) EQUIP. NO. PIN EQUIP. NO. PIN**  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**  Original Issue: March 15, 2007 Revision 2: August 13, 2009 747-28A2262 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 62 of 91 

### BOEING SERVICE BULLETIN 747-28A2262

DETAIL 1

**ACTION (a)**  **WIRE NO. (b)**  **TYPE (c)**  **FROM TO LENGTH**  **(d) NOTES**  **(e) SL**  **(f) EQUIP. NO. PIN EQUIP. NO. PIN**  ADD QF1062-24 RD DQ2651 D2 GDY0005 17 6.0 -- -- 2 3 4 5 6 7 8 9 1112131415 10 1

A B C D EDQ2651

M4260 WIUGDY5



### DETAIL 1 16 1 15 30380342

A B C D E 2 3 4 5 6 7 8 9 1112131415 10 1DQ2631GDY3

M4260 WIU 

### DETAIL 2 15 30 1 16380343

**(SHEET 4 OF 5) FIGURE 10: E2-6 Shelf Wire Integration Unit Wiring Changes**  Original Issue: March 15, 2007 Revision 2: August 13, 2009 747-28A2262 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 63 of 91 

### BOEING SERVICE BULLETIN 747-28A2262

DETAIL 2

**ACTION (a)**  **WIRE NO. (b)**  **TYPE (c)**  **FROM TO LENGTH**  **(d) NOTES**  **(e) SL**  **(f) EQUIP. NO. PIN EQUIP. NO. PIN**  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**  **(f) EQUIP. NO. PIN EQUIP. NO. PIN**  ADD QF1066-24 RD DQ2611 D2 GDY0001 17 6.0 -- -- A B C D E 2 3 4 5 6 7 8 9 1112131415 10 1DQ2611GDY1

M4260 WIU 

### DETAIL 3 16 15 30 1380344

**(SHEET 5 OF 5) FIGURE 11: E2-6 Shelf Wiring Changes**  Original Issue: March 15, 2007 Revision 2: August 13, 2009 747-28A2262 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 64 of 91 

### BOEING SERVICE BULLETIN 747-28A2262

**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 ROUTING380347

**(SHEET 1 OF 2) FIGURE 11: E2-6 Shelf Wiring Changes**  Original Issue: March 15, 2007 Revision 2: August 13, 2009 747-28A2262 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 65 of 91 

### BOEING SERVICE BULLETIN 747-28A2262

**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 Revision 2: August 13, 2009 747-28A2262 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 66 of 91 

### BOEING SERVICE BULLETIN 747-28A2262

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



### MAIN EQUIPMENT CENTER M4260 WIU E2-6 SHELF 1 THROUGH 3 SEE DETAILS FWD

FWD380351

**(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 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 67 of 91 

### BOEING SERVICE BULLETIN 747-28A2262

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 28-42-15384942

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 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 68 of 91 

### 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**  **(f) EQUIP. NO. PIN EQUIP. NO. PIN**  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 2 3 4 5 6 7 8 9 11 12 13 14 15 10 1

M4260 WIUDQ2651GDY5



### DETAIL 1 15 30 1 16380352

**(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 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 69 of 91 

### BOEING SERVICE BULLETIN 747-28A2262

DETAIL 1

**ACTION (a)**  **WIRE NO. (b)**  **TYPE (c)**  **FROM TO LENGTH**  **(d) NOTES**  **(e) SL**  **(f) EQUIP. NO. PIN EQUIP. NO. PIN**  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**  **(f) EQUIP. NO. PIN EQUIP. NO. PIN**  ADD QF1064-24 RD DQ2631 A12 GDY0003 12 6.0 -- -- A B C D E 2 3 4 5 6 7 8 9 11 12 13 14 15 10 1



### M4260 WIUDQ2631GDY3



### DETAIL 2 15 30 1 16380353

**(SHEET 4 OF 5) FIGURE 12: E2-6 Shelf Wire Integration Unit Wiring Changes**  Original Issue: March 15, 2007 Revision 2: August 13, 2009 747-28A2262 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 70 of 91 

### BOEING SERVICE BULLETIN 747-28A2262

DETAIL 3

**ACTION (a)**  **WIRE NO. (b)**  **TYPE (c)**  **FROM TO LENGTH**  **(d) NOTES**  **(e) SL**  **(f) EQUIP. NO. PIN EQUIP. NO. PIN**  ADD QF1066-24 RD DQ2625 D7 GDY0002 22 6.0 -- -- A B C D E 2 3 4 5 6 7 8 9 11 12 13 14 15 10 1

A B C D E 2 3 4 5 6 7 8 9 11 12 13 14 15 10 1

A B C D E 2 3 4 5 6 7 8 9 11 12 13 14 15 10 1



### M4260 WIUDQ2625DQ2623DQ2621GDY2



### DETAIL 3 15 30 1 16380354

**(SHEET 5 OF 5) FIGURE 13: E2-6 Shelf Wiring Changes**  Original Issue: March 15, 2007 Revision 2: August 13, 2009 747-28A2262 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 71 of 91 

### BOEING SERVICE BULLETIN 747-28A2262

**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 28-42-15384969 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 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 72 of 91 

### BOEING SERVICE BULLETIN 747-28A2262

**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**  Original Issue: March 15, 2007 Revision 2: August 13, 2009 747-28A2262 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 73 of 91 

### BOEING SERVICE BULLETIN 747-28A2262

**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) 

## W4260 AR0426

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

2380356

ADDED WIRE OR NEW ROUTING

**(SHEET 1 OF 2) FIGURE 14: E2-6 Shelf Wiring Changes**  Original Issue: March 15, 2007 Revision 2: August 13, 2009 747-28A2262 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 74 of 91 

### BOEING SERVICE BULLETIN 747-28A2262

**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**  Original Issue: March 15, 2007 Revision 2: August 13, 2009 747-28A2262 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 75 of 91 

### BOEING SERVICE BULLETIN 747-28A2262

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

1 THROUGH 3 SEE DETAILS

M4260 WIU E2-6 SHELF


### MAIN EQUIPMENT CENTER FWD

FWD380357

**(SHEET 1 OF 6) FIGURE 15: E2-6 Shelf Wire Integration Unit Wiring Changes**  Original Issue: March 15, 2007 Revision 2: August 13, 2009 747-28A2262 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 76 of 91 

### BOEING SERVICE BULLETIN 747-28A2262

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 28-42-15384962 ADDED WIRE OR NEW ROUTING

**(SHEET 2 OF 6) FIGURE 15: E2-6 Shelf Wire Integration Unit Wiring Changes**  Original Issue: March 15, 2007 Revision 2: August 13, 2009 747-28A2262 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 77 of 91 

### 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**  **(f) EQUIP. NO. PIN EQUIP. NO. PIN**  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**  Original Issue: March 15, 2007 Revision 2: August 13, 2009 747-28A2262 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 78 of 91 

### BOEING SERVICE BULLETIN 747-28A2262

DETAIL 1

**ACTION (a)**  **WIRE NO. (b)**  **TYPE (c)**  **FROM TO LENGTH**  **(d) NOTES**  **(e) SL**  **(f) EQUIP. NO. PIN EQUIP. NO. PIN**  ADD QF1062-24 RD DQ2665 D1 GDY0006 16 6.0 -- -- A B C D E 2 3 4 5 6 7 8 9 11 12 13 14 15 10 1

A B C D E 2 3 4 5 6 7 8 9 11 12 13 14 15 10 1

A B C D E 2 3 4 5 6 7 8 9 11 12 13 14 15 10 1



### M4260 WIUDQ2665DQ2663DQ2661GDY6



### DETAIL 1 15 30 1 16380360

**(SHEET 4 OF 6) FIGURE 15: E2-6 Shelf Wire Integration Unit Wiring Changes**  Original Issue: March 15, 2007 Revision 2: August 13, 2009 747-28A2262 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 79 of 91 

### BOEING SERVICE BULLETIN 747-28A2262

DETAIL 2

**ACTION (a)**  **WIRE NO. (b)**  **TYPE (c)**  **FROM TO LENGTH**  **(d) NOTES**  **(e) SL**  **(f) EQUIP. NO. PIN EQUIP. NO. PIN**  ADD QF1064-24 RD DQ2631 E10 GDY0003 10 6.0 -- -- A B C D E 2 3 4 5 6 7 8 9 11 12 13 14 15 10 1

M4260 WIUDQ2631GDY3



### DETAIL 2 15 30 1 16380361

**(SHEET 5 OF 6) FIGURE 15: E2-6 Shelf Wire Integration Unit Wiring Changes**  Original Issue: March 15, 2007 Revision 2: August 13, 2009 747-28A2262 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 80 of 91 

### BOEING SERVICE BULLETIN 747-28A2262

DETAIL 3

**ACTION (a)**  **WIRE NO. (b)**  **TYPE (c)**  **FROM TO LENGTH**  **(d) NOTES**  **(e) SL**  **(f) EQUIP. NO. PIN EQUIP. NO. PIN**  ADD QF1066-24 RD DQ2625 D1 GDY0002 17 6.0 -- -- A B C D E 2 3 4 5 6 7 8 9 11 12 13 14 15 10 1

A B C D E 2 3 4 5 6 7 8 9 11 12 13 14 15 10 1

A B C D E 2 3 4 5 6 7 8 9 11 12 13 14 15 10 1

M4260 WIUDQ2625DQ2623DQ2621GDY2



### DETAIL 3 15 30 1 16380362

**(SHEET 6 OF 6) FIGURE 16: E2-6 Shelf Wire Integration Unit Wiring Changes**  Original Issue: March 15, 2007 Revision 2: August 13, 2009 747-28A2262 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 81 of 91 

### BOEING SERVICE BULLETIN 747-28A2262

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

M4260 WIU E2-6 SHELF 1 THROUGH 3 SEE DETAILS



### MAIN EQUIPMENT CENTER FWD384970

**(SHEET 1 OF 5) FIGURE 16: E2-6 Shelf Wire Integration Unit Wiring Changes**  Original Issue: March 15, 2007 Revision 2: August 13, 2009 747-28A2262 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 82 of 91 

### BOEING SERVICE BULLETIN 747-28A2262

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 28-42-15384980 ADDED WIRE OR NEW ROUTING

**(SHEET 2 OF 5) FIGURE 16: E2-6 Shelf Wire Integration Unit Wiring Changes**  Original Issue: March 15, 2007 Revision 2: August 13, 2009 747-28A2262 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 83 of 91 

### 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**  **(f) EQUIP. NO. PIN EQUIP. NO. PIN**  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**  Original Issue: March 15, 2007 Revision 2: August 13, 2009 747-28A2262 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 84 of 91 

### BOEING SERVICE BULLETIN 747-28A2262

DETAIL 1

**ACTION (a)**  **WIRE NO. (b)**  **TYPE (c)**  **FROM TO LENGTH**  **(d) NOTES**  **(e) SL**  **(f) EQUIP. NO. PIN EQUIP. NO. PIN**  ADD QF1062-24 RD DQ2653 A4 GDY0005 4 6.0 -- -- A B C D E 2 3 4 5 6 7 8 9 11 12 13 14 15 10 1

A B C D E 2 3 4 5 6 7 8 9 11 12 13 14 15 10 1



### M4260 WIUDQ2653DQ2651GDY5



### DETAIL 1 15 30 1 16384994

A B C D E 2 3 4 5 6 7 8 9 11 12 13 14 15 10 1

M4260 WIUDQ2631GDY3



### DETAIL 2 15 30 1 16384993

**(SHEET 4 OF 5) FIGURE 16: E2-6 Shelf Wire Integration Unit Wiring Changes**  Original Issue: March 15, 2007 Revision 2: August 13, 2009 747-28A2262 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 85 of 91 

### BOEING SERVICE BULLETIN 747-28A2262

DETAIL 2

**ACTION (a)**  **WIRE NO. (b)**  **TYPE (c)**  **FROM TO LENGTH**  **(d) NOTES**  **(e) SL**  **(f) EQUIP. NO. PIN EQUIP. NO. PIN**  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**  **(f) EQUIP. NO. PIN EQUIP. NO. PIN**  ADD QF1066-24 RD DQ2613 A4 GDY0001 4 6.0 -- -- A B C D E 2 3 4 5 6 7 8 9 11 12 13 14 15 10 1

A B C D E 2 3 4 5 6 7 8 9 11 12 13 14 15 10 1



### M4260 WIUDQ2613DQ2611GDY1



### DETAIL 3 15 30 1 16384995

**(SHEET 5 OF 5) FIGURE 17: Relay Bracket Installation**  Original Issue: March 15, 2007 Revision 2: August 13, 2009 747-28A2262 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 86 of 91 

### BOEING SERVICE BULLETIN 747-28A2262

**FIGURE 17: Relay Bracket Installation**



### AFT E/E EQUIPMENT CENTER ENTRY DOOR NO. 5L MAIN E8 RACK

AFT EQUIPMENT CENTER - E8 FWD INBD

FWD UP A SEE1485044

**(SHEET 1 OF 3) FIGURE 17: Relay Bracket Installation**  Original Issue: March 15, 2007 Revision 2: August 13, 2009 747-28A2262 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 87 of 91 

### BOEING SERVICE BULLETIN 747-28A2262

This Figure applies to Group 4-8: 

### FWD UP 2



### A 3.00

0.5

11485076

**(SHEET 2 OF 3) FIGURE 17: Relay Bracket Installation**  Original Issue: March 15, 2007 Revision 2: August 13, 2009 747-28A2262 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 88 of 91 

### 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 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**  Original Issue: March 15, 2007 Revision 2: August 13, 2009 747-28A2262 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 89 of 91 

### BOEING SERVICE BULLETIN 747-28A2262

**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 FWD INBD

FWD UP

A SEE1485191

**(SHEET 1 OF 2) FIGURE 18: Relay Installation, E-8 Aft Equipment Center**  Original Issue: March 15, 2007 Revision 2: August 13, 2009 747-28A2262 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 90 of 91 

### BOEING SERVICE BULLETIN 747-28A2262

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

FWD1485189

**(SHEET 2 OF 2) FIGURE 19: P414 Panel Wiring Changes**  Original Issue: March 15, 2007 Revision 2: August 13, 2009 747-28A2262 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 91 of 91 

### BOEING SERVICE BULLETIN 747-28A2262

**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

D40345J P 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 ROUTING1576713

**(SHEET 1 OF 1)**