# Boeing Alert Service Bulletin 747-28A2262: Boeing Service Bulletin (2) - Rights: © The Boeing Company. Filed by the FAA in regulations.gov docket FAA-2009-0454; AD 2010-14-08 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication. - Document: [Boeing Alert Service Bulletin 747-28A2262](https://openairdocs.org/service-documents/boeing/747-28a2262.md) - Title as filed: Boeing Service Bulletin (2) - Pages: 91 - PDF: https://openairdocs.org/files/sha256/55/7d/557d97b8ea8da34cf404a08206637e79061826dd6fea13a045528f5eb27c532d - Page: https://openairdocs.org/service-documents/boeing/747-28a2262/file/557d97b8ea8d ## Text Each page's text from the PDF; open the PDF at a page with #page=N. ### Page 1 Original Issue: March 15, 2007 Revision 2: August 13, 2009 747-28A2262 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 1 of 91 Commercial Airplanes 747 Service Bulletin Number: 747-28A2262 Original Issue: March 15, 2007 Revision 2: August 13, 2009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Automatic Pump Shutoff Change BOEING PROPRIETARY, CONFIDENTIAL, AND/OR TRADE SECRET Copyright © 2007 The Boeing Company Unpublished Work - All Rights Reserved Boeing claims copyright in each page of this document only to the extent that the page contains copyrightable subject matter.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. ### Page 2 BLANK PAGE Original Issue: March 15, 2007 Revision 2: August 13, 2009 747-28A2262 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 2 of 91 BOEING SERVICE BULLETIN 747-28A2262 BLANK PAGE ### Page 3 Table of Contents Original Issue: March 15, 2007 Revision 2: August 13, 2009 747-28A2262 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 3 of 91 BOEING SERVICE BULLETIN 747-28A2262 Table of Contents Revision Transmittal Sheet .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 ### Page 4 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 . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 91 ### Page 5 Original 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". ### Page 6 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, 2009 ### Page 7 Original 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. ### Page 8 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 E- 8 rack and the P414 and P415 panels. Make wiring changes in the P414 and P415 panels. Make wiring changes to the E2-6 shelf and E2-6 shelf wire integration unit. Make wiring changes at the Modularized Avionics and Warning Electronics Assembly (MAWEA) card file. Do a functional test. Change your scheduled maintenance program to include periodic functional checks of the Horizontal Stabilizer Fuel Boost Pump Automatic Shutoff System as given in 747-400 Maintenance Planning Data (MPD) document, Section 9, Airworthiness Limitation (AWL) Number 28-AWL-24. EFFECTIVITY 747-400 airplanes. See Service Bulletin Paragraph 1.A.1 for effectivity. COMPLIANCE Federal Aviation Administration (FAA) Airworthiness Directive 2007-13-04 is related to this service bulletin. Boeing recommends operator’s incorporate this change within 36 months after the original issue date of this service bulletin. In addition, operators should change their scheduled maintenance program to include periodic functional checks of the Horizontal Stabilizer Fuel Boost Pump Automatic Shutoff System as given in 747-400 Maintenance Planning Data (MPD) document, Section 9, Airworthiness Limitation (AWL) Number 28-AWL-24. INDUSTRY SUPPORT INFORMATION Boeing warranty remedies are not available for the configuration changes given in this service bulletin. MANPOWER MATERIAL INFORMATION Boeing Supplied Kits/Parts. Refer to Paragraph 2.A., Material - Price and Availability. Airplanes Total Task Hours Elapsed Hours Groups 1-9 117 30 ### Page 9 Original 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 STA 379746 ### Page 10 Original 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 PAGE ### Page 11 Original 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. ### Page 12 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) 1R M 3 4 1 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 ### Page 13 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) 1R M 4 2 6 BRITISH AIRWAYS (BAB) 1 RM096–RM097 RM136–RM145 RM261–RM264 RT488–RT499 RU121 RU126–RU132 3 RT485–RT487 7 RT471–RT484 CATHAY PACIFIC AIRWAYS (CAT) 1 RT457–RT469 RT511–RT512 RT514 RT517–RT518 RT522 RT528–RT529 RT782 RT837 2 RT781 3 RT455–RT456 RT508 7 RT451–RT454 CHINA AIRLINES (CHI) 1 RM021–RM024 RT636–RT640 CORSAIR (COR) 1 RT613–RT614 RT616 RT618–RT619 RT621 DRAGONAIR (DRG) 1 RT510 RT513 RT516 RT519 RT524 DUBAI AIR WING (DAW) 1 RM167–RM168 RT102 EL AL ISRAEL AIRLINES (ELA) 1 RM091 RT527 RU081–RU083 EVA AIR (EVA) 1 RM116–RM117 RT162–RT163 RT165–RT168 RT951–RT955 ### Page 14 Original 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–RU017 ### Page 15 Original 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) 1R M 0 1 0 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) 1R M 1 5 8 SINGAPORE AIRLINES (SIA) 1 RM041–RM045 RT521 RT526 RT530 RT831–RT835 SONAIR (SON) 1 RM231–RM233 SOUTH AFRICAN AIRWAYS (SAA) 1 RM081 RM083 RM147 THAI AIRWAYS INTERNATIONAL (TII) 1 RM026–RM030 RM431 RT694–RT699 RT801–RT803 2 RT693 6 RT691–RT692 TRANSAERO AIRLINES (TRX) 1 RM146 RT783–RT784 UNITED AIR LINES (UAL) 1 RM166 RM169–RM177 RT411 RT609–RT612 RT617 RT623–RT630 3 RT607–RT608 7 RT601 RT603–RT605 ### Page 16 Original 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 6 ### Page 17 Original 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 ### Page 18 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 ### Page 19 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. ### Page 20 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. ### Page 21 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. ### Page 22 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 30 ### Page 23 Original 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 +2304.0 ### Page 24 Original 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, 28-22 ### Page 25 Original 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 ### Page 26 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 PAGE ### Page 27 Original 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 $4,112.00 ### Page 28 Original 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 2 8 9 U 1 2 1 4 - 1 ..... - - W i r e K i t - - ( b ) 2 8 9 U 1 2 1 4 - 1 0 1 .... - - 1 S u b k i t , W 3 8 5 1 - - ( 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) 2 8 9 U 1 2 1 4 - 1 0 5 - - .... 1 S u b k i t , W 4 7 5 8 - - ( b ) 2 8 9 U 1 2 1 4 - 1 0 1 0 1 .... 1 . I . D . T a p e - - - - ### Page 29 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. 2 8 9 U 1 2 1 4 - 1 0 1 0 2 .... 1 . I . D . T a p e - - - - 2 8 9 U 1 2 1 4 - 1 0 1 0 3 .... 1 . I . D . T a p e - - - - 2 8 9 U 1 2 1 4 - 1 0 1 0 4 .... 1 . I . D . T a p e - - - - 2 8 9 U 1 2 1 4 - 1 0 1 W .... 1 . W i r e - - - - 289U1214-102W . . . 1 . . Wire -- -- 289U1214-103W . . 1 . . . Wire -- -- 2 8 9 U 1 2 1 4 - 1 0 4 W . 1 .... W i r e - - - - 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 -- -- B A C C 4 7 E F 1 . 4 .... C o n t a c t - - - - B A C C 4 7 E G 2 . 4 .... C o n t a c t - - - - B A C C 4 7 E R 1 .... 1 2 . C o n t a c t - - - - B A C S 1 6 A H 1 .... 2 . R e l a y S o c k e t - - - - B A C T 1 2 A R 2 0 2 .... 1 0 . T e r m i n a l L u g - - - - BMS13- 46T03C01G024 .1. . . W i r e - - ( a ) D 4 3 6 - 3 7 .... 3 . S p l i c e - - - - 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 ### Page 30 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. ### Page 31 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. ### Page 32 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 power ### Page 33 Original 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 power ### Page 34 Original 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 power ### Page 35 Original 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 power ### Page 36 Original 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 "