Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 1 of 182 

### Commercial **Airplanes** 

# 747 Service Bulletin

**Number: 747-28A2281** Original Issue: December 13, 2007 Revision 1: November 25, 2009 ATA System: 2817 2831 **SUBJECT:** FUEL - Fuel Jettison System - Horizontal Stabilizer Tank Override/Jettison Fuel Pumps - Change to Give Redundant Control of the Fuel Pumps 

## BOEING PROPRIETARY, CONFIDENTIAL, AND/OR TRADE SECRET Copyright © 2007 The Boeing Company Unpublished Work - All Rights Reserved Boeing claims copyright in each page of this document only to the extent that the page contains copyrightable subject matter.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PAGE** Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 2 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

BLANK PAGE**Table of Contents** Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 3 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

**Table of Contents** Revision Transmittal Sheet . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5 Summary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9 1. PLANNING INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13 A. Effectivity . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13 1. Airplanes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13 2. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25 B. Concurrent Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25 C. Reason . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25 D. Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 26 E. Compliance. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27 F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27 G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27 H. Weight and Balance Changes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 44 I. Electrical Load Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 44 J. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 45 1. Existing Data: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 45 2. Data supplied with this Service Bulletin: . . . . . . . . . . . . . . . . . . . . . . . . . 45 3. Installation Drawings Used in the Preparation of this Service Bulletin: . . . . . . . . . . 46 K. Publications Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 46 L. Interchangeability and Intermixability of Parts . . . . . . . . . . . . . . . . . . . . . . . . . 47 2. MATERIAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 49 A. Material - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 49 B. Industry Support Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 50 C. Parts Necessary For Each Airplane . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 50 1. Kits/Parts: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 50 2. Parts and Materials Supplied by the Operator: . . . . . . . . . . . . . . . . . . . . . . 56 3. Parts Modified and Reidentified: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 56 4. Parts Removed and Not Replaced: . . . . . . . . . . . . . . . . . . . . . . . . . . . . 56 D. Parts Necessary to Change Spares . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 56 E. Special Tooling - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . 56 F. Special Tooling Necessary to do this Service Bulletin . . . . . . . . . . . . . . . . . . . . . 56 3. ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 57 A. GENERAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 57 B. WORK INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 57 FIGURE 1: INSTALL RELAYS ON E-8 SHELF . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 8 2 FIGURE 2: WIRE BUNDLE ROUTING INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . 92 FIGURE 3: REWORK / INSTALL NEW WIRING (WIRE BUNDLE W4488) . . . . . . . . . . . . . . . 96 FIGURE 4: REWORK / INSTALL NEW WIRING (WIRE BUNDLE W4488) . . . . . . . . . . . . . . . 97 FIGURE 5: INSTALL NEW WIRING (WIRE BUNDLE W4488) . . . . . . . . . . . . . . . . . . . . . 98 FIGURE 6: REWORK / INSTALL NEW WIRING (WIRE BUNDLE W4488) . . . . . . . . . . . . . . . 99 FIGURE 7: REWORK / INSTALL NEW WIRING (WIRE BUNDLE W4488) . . . . . . . . . . . . . . . 101 FIGURE 8: INSTALL NEW WIRING (WIRE BUNDLE W4588) . . . . . . . . . . . . . . . . . . . . . 103 FIGURE 9: INSTALL NEW WIRING (WIRE BUNDLE W4588) . . . . . . . . . . . . . . . . . . . . . 104 FIGURE 10: REWORK / INSTALL NEW WIRING (WIRE BUNDLE W4588) . . . . . . . . . . . . . . 106 FIGURE 11: REWORK / INSTALL NEW WIRING (WIRE BUNDLE W4588) . . . . . . . . . . . . . . 108**Table of Contents** Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 4 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

FIGURE 12: REWORK / INSTALL NEW WIRING (WIRE BUNDLE W4588) . . . . . . . . . . . . . 110 FIGURE 13: REWORK / INSTALL NEW WIRING (WIRE BUNDLE W3845) . . . . . . . . . . . . . 112 FIGURE 14: REWORK / INSTALL NEW WIRING (WIRE BUNDLE W4758) . . . . . . . . . . . . . 113 FIGURE 15: REWORK / INSTALL NEW WIRING ON E8 SHELF (WIRE BUNDLE W3851) . . . . . 114 FIGURE 16: INSTALL NEW WIRING ON E8 SHELF (WIRE BUNDLE W3851) . . . . . . . . . . . . 116 FIGURE 17: REWORK / INSTALL NEW WIRING ON E8 SHELF (WIRE BUNDLE W3851) . . . . . 118 FIGURE 18: REWORK / INSTALL NEW WIRING ON E8 SHELF (WIRE BUNDLE W3851) . . . . . 120 FIGURE 19: INSTALL NEW WIRING ON E8 SHELF (WIRE BUNDLE W3851) . . . . . . . . . . . . 122 FIGURE 20: INSTALL NEW WIRING ON E8 SHELF (WIRE BUNDLE W3851) . . . . . . . . . . . . 123 FIGURE 21: REWORK / INSTALL NEW WIRING ON E8 SHELF (WIRE BUNDLE W3851) . . . . . 124 FIGURE 22: INSTALL RELAYS ON E-8 SHELF . . . . . . . . . . . . . . . . . . . . . . . . . . . . 126 FIGURE 23: WIRE BUNDLE ROUTING INFORMATION . . . . . . . . . . . . . . . . . . . . . . . 133 FIGURE 24: REWORK / INSTALL NEW WIRING (WIRE BUNDLE W4488) . . . . . . . . . . . . . 137 FIGURE 25: INSTALL NEW WIRING (WIRE BUNDLE W4588) . . . . . . . . . . . . . . . . . . . . 138 FIGURE 26: REWORK / INSTALL NEW WIRING (WIRE BUNDLE W3845) . . . . . . . . . . . . . 139 FIGURE 27: INSTALL NEW WIRING (WIRE BUNDLE W4758) . . . . . . . . . . . . . . . . . . . . 140 FIGURE 28: REWORK / INSTALL NEW WIRING ON E8 SHELF (WIRE BUNDLE W3851) . . . . . 141 FIGURE 29: INSTALL NEW WIRING ON E8 SHELF (WIRE BUNDLE W3851) . . . . . . . . . . . . 143 FIGURE 30: REWORK / INSTALL NEW WIRING ON E8 SHELF (WIRE BUNDLE W3851) . . . . . 144 FIGURE 31: REWORK / INSTALL NEW WIRING ON E8 SHELF (WIRE BUNDLE W3851) . . . . . 146 FIGURE 32: INSTALL NEW WIRING ON E8 SHELF (WIRE BUNDLE W3851) . . . . . . . . . . . . 148 FIGURE 33: REWORK / INSTALL NEW WIRING ON E8 SHELF (WIRE BUNDLE W3851) . . . . . 149 FIGURE 34: WIRE BUNDLE ROUTING E-8 SHELF . . . . . . . . . . . . . . . . . . . . . . . . . . 151 FIGURE 35: WIRE BUNDLE ROUTING P180 PANEL TO MAWEA CARD FILE . . . . . . . . . . . 154 FIGURE 36: WIRE BUNDLE ROUTING E-8 SHELF . . . . . . . . . . . . . . . . . . . . . . . . . . 162 FIGURE 37: REWORK / INSTALL NEW WIRING (WIRE BUNDLE W4488) . . . . . . . . . . . . . 165 FIGURE 38: REWORK / INSTALL NEW WIRING (WIRE BUNDLE W4488) . . . . . . . . . . . . . 166 FIGURE 39: REWORK / INSTALL NEW WIRING (WIRE BUNDLE W4488) . . . . . . . . . . . . . 167 FIGURE 40: REWORK / INSTALL NEW WIRING (WIRE BUNDLE W4488) . . . . . . . . . . . . . 169 FIGURE 41: REWORK / INSTALL NEW WIRING ON E8 SHELF (WIRE BUNDLE W3851) . . . . . 171 FIGURE 42: REWORK / INSTALL NEW WIRING ON E8 SHELF (WIRE BUNDLE W3851) . . . . . 173 FIGURE 43: INSTALL NEW WIRING ON E8 SHELF (WIRE BUNDLE 3851) . . . . . . . . . . . . . 175 FIGURE 44: INSTALL NEW WIRING (WIRE BUNDLE W4588) . . . . . . . . . . . . . . . . . . . . 176 FIGURE 45: REWORK/INSTALL NEW WIRING (WIRE BUNDLE W4588) . . . . . . . . . . . . . . 177 FIGURE 46: REWORK/INSTALL NEW WIRING (WIRE BUNDLE W4588) . . . . . . . . . . . . . . 179 FIGURE 47: REWORK/INSTALL NEW WIRING (WIRE BUNDLE W3845) . . . . . . . . . . . . . . 181Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 5 of 182 

### Commercial **Airplanes** 

# 747 Service Bulletin

**Number: 747-28A2281** 

### Revision Transmittal Sheet Original Issue: December 13, 2007 Revision 1: November 25, 2009 ATA System: 2817 2831 **SUBJECT:** FUEL - Fuel Jettison System - Horizontal Stabilizer Tank Override/Jettison Fuel Pumps - Change to Give Redundant Control of the Fuel Pumps
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 of this service bulletin. **REASON FOR REVISION** This revision is sent to address the comments received from operators since the original issue of the service bulletin and incorporate differences identified during the validation of the service bulletin. Airplanes RT966-RT967 were deleted from the effectivity. These airplanes are not equipped with horizontal stabilizer fuel tanks. As a part of a service bulletin validation program, this change was completed on Airplane RT409 by original issue of Service Bulletin 747-28A2281 and before the release of Revision 1 of this service bulletin. The change completed on airplane RT409 by Service Bulletin 747-28A2281 is equivalent to Revision 1 of this service bulletin. Airplane RT409 has the configuration of a Group 20 airplane. The following effectivity group assignments were changed to show the correct wiring configuration for the affected airplanes. New airplane Groups 20-37 were added to the service bulletin. The table below shows the new Groups assignments for the effective airplanes: **Airplanes Affected Old Airplane Group New Airplane Group**  RT061, RT407- RT410, RT480- RT487 2 20

RT431-RT435 2 21 RT436 2 22 RT573-RT574, RT576 17 23 RT501, RT506- RT507, RT509 4 24
RT455 2 25Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 6 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

The following sections of the service bulletin are changed: — ATA system - added ATA 2817 — Summary Section, Group and Configuration tables in Section 1, added new airplane Groups 20-37 where applicable. — Concurrent Requirements, updated revision level for service bulletin 747-28A2262. — Compliance statements in the Summary and Planning sections were revised with wording "original issue date". — Description Section 1.D added new airplane Group 20-22; Group 23, Configuration 2; Group 24-37. — Manpower tables revised to add new airplane Group 20-22; Group 23, Configuration 2; Group 24-37 and new figures 37-47 to man-hour tables. — Weight and Balance added new airplane Groups 20-37 to the table and new weight and balance information for airplane Groups 16; Group 18; Groups 32-37. — Electrical Load Data added new airplane Groups 20-37 to the applicability. — Material Information Section 2, Added new airplane Group 20-22; Group 23, Configuration 2; Group 24-37 to 015U1808-1 Top Kit. Created new supplemental kit 015U1808-3 with new connector for Group 16; Group 18, Configuration 2; Groups 32-37 airplanes. Figure kits were updated with new applicability and new airplane Group 20-22; Group 23, Configuration 2; Group 24-37. — Parts and Materials, Supplied by the operator, added washer and nut for alternate tray configuration. — Accomplishment Instructions Section 3, General Information, added Note 7 to clarify wire clamp size selection. RT503, RT505 2 26 RT451-RT454 2 27 RT021-RT022 2 28 RT001-RT005, RT401-RT406, RT471-RT479, RT571 2 29

RT502, RT504 2 30 RT551-RT556, RT591, RT641, RT643-RT645, RT671, RT691- RT692 2 31

RM081, RM083, RT411-RT412, RT609-RT630, RT753-RT755, RT945-RT949 1 32

RT605-RT608, RT752 2 33 RM146, RT783- RT784 8 34
RT777 11 35 RT751 2 36 RT601-RT604 2 37 **Airplanes Affected Old Airp lane Group New Airplane**  **Group**Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 7 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

— Accomplishment Instructions Section 3. revised figure reference, airplane applicability and added new airplane Group 20-22; Group 23, Configuration 2; Group 24-37 where applicable. — Figure 1 changes: — Added new airplane Group 20-22; Group 23, Configuration 2; Group 24-37. — Revised sheet 1 and 2, added sheets 5, 6 and 7 to show alternate tray configuration. — Revised Circle Note 2, More Data, added additional wording, If Static Inverter is installed. — Revised Circle Note 3, More Data, added information for bolt installation if equipment tray has stiffening joggle. — Revised Circle Note 6, More Data, added hole diameter to drilling procedure. — Revised Circle Note 18, More Data, added additional wording, If Static Inverter was removed. — Added Note (e), gives information for bracket and bolt installation if equipment tray has stiffening joggle. — Figure 2 added new airplane Group 20-22; Group 23, Configuration 2; Group 24-37. — Figure 3 Flag Note 2, corrected SWPM call out. Changed SWPM 20-10-11 to SWPM 20-61-11 and added new airplane Group 32, 34-35. — Figures 4 revised illustration to show wire W4488-071-22 as a cap and stowed wire. — Figures 5 revised airplane applicability. — Figures 6 revised airplane applicability and added new airplane Group 30-31, 33, 37. — Figures 8 revised airplane applicability and added new airplane Group 20-22; Group 23, Configuration 2; Group 24-31. — Figures 10 revised airplane applicability. — Figure 13 revised Flag Note 2 socket P/N to BACC47CP1S for connector D41807J. Revised airplane applicability and added new airplane Group 20-22; Group 23, Configuration 2; Group 24-31. — Figure 14 revised to show wire W4758-633-24 connected to pin C9 on connector DW3417C and wire W4758-634-24 connected to pin C8 on connector DW3417C. The nomenclature shown inside M7952 is also revised to show "FUEL CMD STAB R" for pin C9 and "FUEL CMD STAB L" for pin C8. Added new airplane Group 20-22; Group 23, Configuration 2, Group 24-37. — Figure 15 added new airplane Group 20, 22; Group 23, Configuration 2; Group 24-25, 28, 32-36. — Figure 16 and 17 added new airplane Group 20-22; Group 23, Configuration 2; Group 24-37. — Figure 18 revised Flag Note 2 socket P/N to BACC47CP3T for connector D40106J and added new airplane Group 20, 22; Group 23, Configuration 2; Group 24-25, 28, 32-36. — Figure 19 revised airplane applicability and added new airplane Group 20-22, 29. — Figure 20 revised airplane applicability and added new airplane Group 30-35, 37. — Figure 21 added new airplane Group 20-22; Group 23, Configuration 2; Group 24-37. — Figure 26 revised Flag Note 2 socket P/N to BACC47CP1S for connector D41807J. — Figure 27 revised to show wire W4758-633-24 connected to pin C9 on connector DW3417C and wire W4758-634-24 connected to pin C8 on connector DW3417C. The nomenclature shown inside M7952 is also revised to show "FUEL CMD STAB R" for pin C9 and "FUEL CMD STAB L" for pin C8. — Figure 31 revised Flag Note 2 socket P/N to BACC47CP3T for connector D40106J. — Figure 36 added new airplane Group 20-22; Group 23, Configuration 2; Group 24-37. — New Figure 37 added to use pin 30 on connector D40103P for Group 20, 29 airplanes. — New Figure 38 added to use pin 36 on connector D40103P for Group 6, Configuration 2; Group 23, Configuration 2; Group 24 airplanes. — New Figure 39 added to use pin 30 on connector D40103P for Group 3, Configuration 1; Group 21-22 airplanes. — New Figure 40 added to use pin 36 on connector D40103P for Group 5, Configuration 2, Group 13, 25-28, 36 airplanes. — New Figure 41 added to show wire W3851-320-12B deleted from pin B2 and wire W3851-321-12Y deleted from pin C2 on relay R7401 for Group 19, Configuration 1; Group 21, 26-27, 29-31, 37 airplanes. — New Figure 42 added to show wire W3851-323-12B deleted from pin B2 and wire W3851-324-12Y deleted from pin C2 on relay R7402 for Group 21, 26-27, 29-31, 37 airplanes. — New Figure 43 added to use pin 36 on connector D40103J for Group 5, Configuration 2; Group 6, Configuration 2; Group 13; Group 23, Configuration 2; Group 24-28, 36 airplanes.Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 8 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

— New Figure 44 added to install new connector D41785P for Group 18, Configuration 2; Group 32-33, 36- 37 airplanes. — New Figure 45 added to install new connector D41785P for Group 16, 35 airplanes. — New Figure 46 added to install new connector D41785P for Group 34 airplanes. — New Figure 47 added to install new connector D41785J for Group 16; Group 18, Configuration 2; Group 32-37 airplanes. The data given in Information Notice 747-28A2281 IN 01, IN 02 and IN 03 is included in this revision. 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: December 13, 2007 Revision 1: November 25, 2009Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 9 of 182 

### Commercial **Airplanes** 

# 747 Service Bulletin

**Number: 747-28A2281** 

### Summary Original Issue: December 13, 2007 Revision 1: November 25, 2009 ATA System: 2817 2831 **SUBJECT:** FUEL - Fuel Jettison System - Horizontal Stabilizer Tank Override/Jettison Fuel Pumps - Change to Give Redundant Control of the Fuel Pumps

**CONCURRENT REQUIREMENTS** Refer to Paragraph 1.B. for the list of concurrent requirements. **BACKGROUND** Accomplishment of the changes in this service bulletin will help prevent an ignition source in a fuel tank as a result of a horizontal stabilizer override/jettison fuel pump that continues to run after it has been commanded off. An ignition source in a fuel tank could result in a fire or an explosion. A safety assessment conducted by Boeing indicates that there is a small risk of an ignition source in a fuel tank if a horizontal stabilizer override/jettison fuel pump continues to run for an extended time after fuel level goes below the pump inlet. Normally the pump is commanded off when a low fuel pressure is indicated. If a single failure in the pump control circuitry occurs, a pump can continue to run after it is commanded off. When a pump runs after the fuel level goes below the pump inlet, there is a small risk that the pump can cause an ignition source in the fuel tank from an overheat condition, electrical arcs or frictional sparks. This service bulletin gives the instructions to install new relays and wiring in the circuitry for the horizontal stabilizer override/jettison fuel pumps. The new relays and wiring for the horizontal stabilizer override/jettison fuel pumps remove power from these pumps when the pumps continue to run after the pumps have been commanded off. Each set of relays have a new Engine Indication and Crew Alerting System (EICAS) status message to annunciate a fault in a pump control relay. For the horizontal stabilizer tank, the EICAS status messages are FUEL CMD STAB L and Fuel CMD STAB R. These changes help make sure that the risk of an ignition source in a fuel tank is kept to a minimum. The changes are identical to the changes to airplanes in production. 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". **ACTION** Group 1-8, 10-15, 17, 19-31: Get access to E8 shelf and install new relays. Rework/install new wiring on E8 shelf. Get access and rework/install new airplane wiring from E8 shelf to disconnect AC1401 and rework/install new airplane wiring from disconnect AC1401 to P180 panel. Rework/install new wiring on P180 panel. Rework wiring from P180 panel to Modularized Avionics and Warning Electronics Assembly (MAWEA) Card File (P54). Do a functional test. Close access.Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 10 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

Group 9: Get access to E8 shelf and install new relays. Rework/install new wiring on E8 shelf. Get access and rework/install new airplane wiring from E8 shelf to disconnect AC1401 and install new airplane wiring from disconnect AC1401 to P180 panel. Rework/install new wiring on P180 panel. Install new wiring from P180 panel to MAWEA Card File (P54). Do a functional test. Close access. Group 16, 18, 32-37: Get access to E8 shelf and install new relays. Rework/install new wiring on E8 shelf. Get access and rework/install new airplane wiring from E8 shelf to disconnect AC1401 and rework/install new airplane wiring from disconnect AC1401 to P180 panel and add new connector to P180 panel. Rework/install new wiring on P180 panel. Rework wiring from P180 panel to MAWEA Card File (P54). Do a functional test. Close access. Boeing Service Bulletin 747-28A2280 is related to this service bulletin and has some common access procedures. **EFFECTIVITY** 747-400 Airplanes. Refer to Paragraph 1.A.1., Airplanes for the list of affected airplanes. **COMPLIANCE** The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to this service bulletin. The Airworthiness Directive will make the compliance tasks and times given in this service bulletin mandatory. Boeing recommends that this service bulletin be incorporated within 5 years after the original issue of this service bulletin. **INDUSTRY SUPPORT INFORMATION** Boeing warranty remedies are not available for the configuration changes given in this service bulletin. **MANPOWER**

**MATERIAL INFORMATION** Boeing Supplied Kits/Parts. Refer to Paragraph 2.A., Material - Price and Availability. **Airplanes Total Task Hours Elapsed Hours** Groups 1, 7, 18, 19, 32 101.20 52.30 Groups 2, 3, 5, 10, 12, 14, 20-22, 25- 31, 33, 36-37 101.30 52.35

Groups 4, 6, 15, 17, 23-24 101.10 52.25 Group 8, 11, 34-35 101.40 52.40 Group 9 107.40 55.30 Group 13, 16 101.50 52.45Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 11 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

STA 1580 STA 2200 2100 STA
STA 1980 AC1401 ADD/REWORK 2 WIRES FROM E-8 SHELF TO P180 PANEL (W4588) ADD/REWORK 2 WIRES FROM E-8 SHELF TO P180 PANEL (W4488) INSTALL 2 NEW RELAYS ON E-8 SHELF. REWORK WIRING ON E-8 SHELF.

REVISE WIRING ON P180 PANEL AND MAWEA CARD FILE P54.1325681Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 12 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

BLANK PAGEOriginal Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 13 of 182 

### Commercial **Airplanes** 

# 747 Service Bulletin

**Number: 747-28A2281** Original Issue: December 13, 2007 Revision 1: November 25, 2009 ATA System: 2817 2831 **SUBJECT:** FUEL - Fuel Jettison System - Horizontal Stabilizer Tank Override/Jettison Fuel Pumps - Change to Give Redundant Control of the Fuel Pumps

**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 85539-8 for data about this change. **GROUP CONFIGURATION DESCRIPTION** 1 - 747-400 airplanes with horizontal stabilizer tank which require wiring changes to the E8 shelf, P180 panel and Modularized Avionics and Warning Electronics Assembly (MAWEA) card file, Top KIt 015U1808-1 kit for parts. 2 - 747-400 airplanes with horizontal stabilizer tank which require wiring changes to the E8 shelf, P180 panel and MAWEA card file, Top kit 015U1808-1 kit for parts. 3 - 747-400 airplanes with horizontal stabilizer tank affected by service bulletin 747-28-2197 or 747- 28-2183. 1 747-400 airplanes with horizontal stabilizer tank changed by service bulletin 747-28-2197 or 747-28-2183. 2 747-400 airplanes with horizontal stabilizer tank not changed by service bulletin 747-28-2197 or 747-28-2183.Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 14 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

4 - 747-400 airplanes with horizontal stabilizer tank which require wiring changes to the E8 shelf, P180 panel and MAWEA card file, Top Kit 015U1808-1 kit for parts. 5 - 747-400 airplanes with horizontal stabilizer tank affected by service bulletin 747-28-2265. 1 747-400 airplanes with horizontal stabilizer tank changed by service bulletin 747-28-2265. 2 747-400 airplanes with horizontal stabilizer tank not changed by service bulletin 747-28-2265. 6 - 747-400 airplanes with horizontal stabilizer tank affected by service bulletin 747-28-2272. 1 747-400 airplanes with horizontal stabilizer tank changed by service bulletin 747-28-2272. 2 747-400 airplanes with horizontal stabilizer tank not changed by service bulletin 747-28-2272. 7 - 747-400 airplanes with horizontal stabilizer tank which require wiring changes to the E8 shelf, P180 panel and MAWEA card file, Top kit 015U1808-1 kit for parts. 8 - 747-400 airplanes with horizontal stabilizer tank which require wiring changes to the E8 shelf, P180 panel and MAWEA card file, Top kit 015U1808-1 kit for parts. 9 - 747-400 airplanes with horizontal stabilizer tank which require wiring changes to the E8 shelf, P180 panel and MAWEA card file, Top kit 015U1808-2 kit for parts. 10 - 747-400 airplanes with horizontal stabilizer tank which require wiring changes to the E8 shelf, P180 panel and MAWEA card file, Top kit 015U1808-1 kit for parts. 11 - 747-400 airplanes with horizontal stabilizer tank which require wiring changes to the E8 shelf, P180 panel and MAWEA card file. Top Kit 015U1808-1 kit of parts. 12 - 747-400 airplanes with horizontal stabilizer tank which require wiring changes to the E8 shelf, P180 panel and MAWEA card file, Top Kit 015U1808-1 kit for parts. 13 - 747-400 airplanes with horizontal stabilizer tank which require wiring changes to the E8 shelf, P180 panel and MAWEA card file, Top Kit 015U1808-1 kit for parts. **GROUP CONFIGURATION DESCRIPTION**Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 15 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

14 - 747-400 airplanes with horizontal stabilizer tank which require wiring changes to the E8 shelf, P180 panel and MAWEA card file, Top Kit 015U1808-1 kit for parts. 15 - 747-400 airplanes with horizontal stabilizer tank affected by service bulletin 747-28-2275. 1 747-400 airplanes with horizontal stabilizer tank changed by service bulletin 747-28-2275. 2 747-400 airplanes with horizontal stabilizer tank not changed by service bulletin 747-28-2275, 16 - 747-400 airplanes with horizontal stabilizer tank which require wiring changes to the E8 shelf, P180 panel and MAWEA card file, Top Kit 015U1808-1 kit for parts. 17 - 747-400 airplanes with horizontal stabilizer tank affected by service bulletin 747-28-2274. 1 747-400 airplanes with horizontal stabilizer tank changed by service bulletin 747-28-2274. 2 747-400 airplanes with horizontal stabilizer tank not changed by service bulletin 747-28-2274. 18 - 747-400 airplanes with horizontal stabilizer tank affected by service bulletin 747-28-2247. 1 747-400 airplanes with horizontal stabilizer tank changed by service bulletin 747-28-2247. 2 747-400 airplanes with horizontal stabilizer tank not changed by service bulletin 747-28-2247. 19 - 747-400 airplanes with horizontal stabilizer tank affected by service bulletin 747-28-2197 or 747- 28-2183. 1 747-400 airplanes with horizontal stabilizer tank changed by service bulletin 747-28-2197 or 747-28-2183. 2 747-400 airplanes with horizontal stabilizer tank not changed by service bulletin 747-28-2197 or 747-28-2183. 20 - 747-400 airplanes with horizontal stabilizer tank which require wiring changes to the E8 shelf, P180 panel and MAWEA card file, Top Kit 015U1808-1 kit for parts. 21 - 747-400 airplanes with horizontal stabilizer tank which require wiring changes to the E8 shelf, P180 panel and MAWEA card file, Top Kit 015U1808-1 kit for parts. **GROUP CONFIGURATION DESCRIPTION**Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 16 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

22 - 747-400 airplanes with horizontal stabilizer tank which require wiring changes to the E8 shelf, P180 panel and MAWEA card file, Top Kit 015U1808-1 kit for parts. 23 - 747-400 airplanes with horizontal stabilizer tank affected by service bulletin 747-28-2274 1 747-400 airplanes with horizontal stabilizer tank changed by service bulletin 747-28-2274. 2 747-400 airplanes with horizontal stabilizer tank not changed by service bulletin 747-28-2274. 24 - 747-400 airplanes with horizontal stabilizer tank which require wiring changes to the E8 shelf, P180 panel and MAWEA card file, Top Kit 015U1808-1 kit for parts. 25 - 747-400 airplanes with horizontal stabilizer tank which require wiring changes to the E8 shelf, P180 panel and MAWEA card file, Top Kit 015U1808-1 kit for parts. 26 - 747-400 airplanes with horizontal stabilizer tank which require wiring changes to the E8 shelf, P180 panel and MAWEA card file, Top Kit 015U1808-1 kit for parts. 27 - 747-400 airplanes with horizontal stabilizer tank which require wiring changes to the E8 shelf, P180 panel and MAWEA card file, Top Kit 015U1808-1 kit for parts. 28 - 747-400 airplanes with horizontal stabilizer tank which require wiring changes to the E8 shelf, P180 panel and MAWEA card file, Top Kit 015U1808-1 kit for parts. 29 - 747-400 airplanes with horizontal stabilizer tank which require wiring changes to the E8 shelf, P180 panel and MAWEA card file, Top Kit 015U1808-1 kit for parts. 30 - 747-400 airplanes with horizontal stabilizer tank which require wiring changes to the E8 shelf, P180 panel and MAWEA card file, Top Kit 015U1808-1 kit for parts. 31 - 747-400 airplanes with horizontal stabilizer tank which require wiring changes to the E8 shelf, P180 panel and MAWEA card file, Top Kit 015U1808-1 kit for parts. 32 - 747-400 airplanes with horizontal stabilizer tank which require wiring changes to the E8 shelf, P180 panel and MAWEA card file, Top Kit 015U1808-1 kit for parts. **GROUP CONFIGURATION DESCRIPTION**Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 17 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

Airplane models:
747-400 IDENTIFICATION BY CUSTOMER, CUSTOMER CODE, GROUP AND VARIABLE NUMBER AEROLINEAS ARGENTINAS (ARG) 11 RT704 13 RT701–RT702 AIR ATLANTA ICELANDIC (AID) 1 RT515 36 RT751 AIR CARGO GERMANY (CGU) 1 RT633 AIR CHINA (BEJ) 1 RM341 AIR CHINA CARGO (CGC) 10 RT101 RT103 AIR FRANCE (AFA) 1 RM401–RM403 RT071–RT073 RT121 31 RT591 33 - 747-400 airplanes with horizontal stabilizer tank which require wiring changes to the E8 shelf, P180 panel and MAWEA card file, Top Kit 015U1808-1 kit for parts. 34 - 747-400 airplanes with horizontal stabilizer tank which require wiring changes to the E8 shelf, P180 panel and MAWEA card file, Top Kit 015U1808-1 kit for parts. 35 - 747-400 airplanes with horizontal stabilizer tank which require wiring changes to the E8 shelf, P180 panel and MAWEA card file, Top Kit 015U1808-1 kit for parts. 36 - 747-400 airplanes with horizontal stabilizer tank which require wiring changes to the E8 shelf, P180 panel and MAWEA card file, Top Kit 015U1808-1 kit for parts. 37 - 747-400 airplanes with horizontal stabilizer tank which require wiring changes to the E8 shelf, P180 panel and MAWEA card file, Top Kit 015U1808-1 kit for parts. **GROUP CONFIGURATION DESCRIPTION**Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 18 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

AIR NEW ZEALAND (ANZ) 1 RM082 RT673 11 RT703 12 RM191–RM192 19 RT932 2 RT672 31 RT671 AIR PACIFIC (APC) 30 RT502 RT504 AIR PULLMANTUR (PUL) 1 RT523 RT525 RT749 ALL NIPPON AIRWAYS (ANA) 16 RT776 32 RT753–RT755 35 RT777 ASIANA AIRLINES (AAR) 1 RM071 RT131–RT136 RU032 ATLAS AIR (TLS) 33 RT752 AVION AIRCRAFT TRADING H.F. (VNG) 1 RT634 18 RT756 BAHRAIN ROYAL FLIGHT (BHR) 7 RM426 BRITISH AIRWAYS (BAB) 1 RM096–RM097 RM136–RM145 RM261–RM264 RT488–RT499 RU121 RU126–RU132 20 RT480–RT487 29 RT471–RT479 CATHAY PACIFIC AIRWAYS (CAT) 1 RT457–RT469 RT511–RT512 RT514 RT517 RT522 RT529 RT837 14 RT781–RT782 25 RT455 27 RT451–RT454 4 RT518 RT528 5 RT456 6 RT508 CHINA AIRLINES (CHI) 1 RM021–RM024 RT636–RT640 9 RM441–RM443 RM445Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 19 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

CORSAIR (COR) 32 RT613–RT614 RT616 RT618–RT619 RT621 DRAGONAIR (DRG) 1 RT519 15 RT510 RT513 4 RT516 RT524 DUBAI AIR WING (DAW) 1 RM167–RM168 10 RT102 EL AL ISRAEL AIRLINES (ELA) 1 RM091 RT527 RU081–RU083 EVA AIR (EVA) 1 RM116–RM117 RT162–RT163 RT165–RT168 RT951–RT955 EVERGREEN INTERNATIONAL A/L (EVR) 1 RT743 EXPORT RESTRICTED AIRPLANES (YWV) 32 RT620 33 RT606 37 RT602 GARUDA INDONESIA (GIA) 1 RU061–RU062 19 RT931 GECAS (GEF) 32 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 RT642 RT646–RT650 31 RT641 RT643–RT645 KALITTA AIR (KAC) 28 RT021–RT022 KLM - ROYAL DUTCH AIRLINES (KLM) 1 RM801–RM803 RT006–RT014 29 RT001–RT005Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 20 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

KOREAN AIR (KAL) 1 RM011–RM013 RT577–RT588 RT590 RT811–RT814 17 RT572 RT575 20 RT061 23 RT573–RT574 RT576 29 RT571 KUWAIT AIRWAYS (KUW) 1 RT151 LION AIR (MLI) 26 RT503 RT505 LUFTHANSA GERMAN AIRLINES (DLH) 1 RT045–RT047 RT437–RT439 RT441–RT447 21 RT431–RT435 22 RT436 3 RT043–RT044 MALAYSIA AIRLINES (MAS) 1 RM036–RM040 RM366–RM367 RT744 RT746 RT748 RT750 RU016–RU017 MARTINAIR HOLLAND (MTH) 24 RT501 RT506–RT507 RT509 NORTHWEST AIRLINES (NWA) 1 RM241–RM246 20 RT407–RT410 29 RT401–RT406 OMAN ROYAL FLIGHT (RFO) 7 RM010 PHILIPPINE AIRLINES (PAL) 1 RT152 RU051–RU052 RU059–RU060 PRESIDENTIAL FLIGHT (ABD) 1 RM084 RT137 QANTAS (QAN) 1 RF001–RF006 RM331–RM333 RT561–RT568 RT742 RU031 2 RT557–RT560 RT741 31 RT551–RT556 SAUDI ARABIAN AIRLINES (SVA) 1 RU101–RU102 7 RM156–RM157 SAUDI ROYAL FLIGHT (SRF) 7 RM158Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 21 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

SINGAPORE AIRLINES (SIA) 1 RM041–RM045 RT521 RT831–RT835 4 RT526 RT530 SONAIR (SON) 1 RM231–RM233 SOUTH AFRICAN AIRWAYS (SAA) 32 RM081 RM083 8 RM147 THAI AIRWAYS INTERNATIONAL (TII) 1 RM026–RM030 RM431 RT694–RT699 RT801–RT803 2 RT693 31 RT691–RT692 TRANSAERO AIRLINES (TRX) 34 RM146 RT783–RT784 UNITED AIR LINES (UAL) 1 RM166 RM169–RM177 32 RT411 RT609–RT612 RT617 RT623–RT630 33 RT605 RT607–RT608 37 RT601 RT603–RT604 UPS (UPS) 1 RT161 RT164 VIRGIN ATLANTIC AIRWAYS (VAA) 1 RM051–RM053 RM351–RM355 32 RT945–RT949 WORLD AIRWAYS, INC. (WLD) 1 RT745 RT747 YANGTZE RIVER EXPRESS (YTH) 18 RT757 IDENTIFICATION BY VARIABLE NUMBER **Variable Group** RF001–RF006 1 RM010 7 RM011–RM013 1 RM021–RM024 1 RM026–RM030 1 RM036–RM045 1 RM051–RM053 1 RM071 1 RM081 32Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 22 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

RM082 1 RM083 32 RM084 1 RM091 1 RM096–RM097 1 RM116–RM117 1 RM136–RM145 1 RM146 34 RM147 8 RM156–RM158 7 RM166–RM177 1 RM191–RM192 12 RM231–RM233 1 RM241–RM246 1 RM261–RM264 1 RM331–RM333 1 RM341 1 RM351–RM355 1 RM366–RM367 1 RM401–RM403 1 RM426 7 RM431 1 RM441–RM443 9 RM445 9 RM801–RM803 1 RT001–RT005 29 RT006–RT014 1 RT021–RT022 28 RT043–RT044 3 RT045–RT047 1 RT061 20 RT071–RT073 1 RT101–RT103 10 RT121 1 RT131–RT137 1 RT151–RT152 1 RT161–RT168 1 RT401–RT406 29 RT407–RT410 20 **Variable Group**Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 23 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

RT411–RT412 32 RT431–RT435 21 RT436 22 RT437–RT447 1 RT451–RT454 27 RT455 25 RT456 5 RT457–RT469 1 RT471–RT479 29 RT480–RT487 20 RT488–RT499 1 RT501 24 RT502 30 RT503 26 RT504 30 RT505 26 RT506–RT507 24 RT508 6 RT509 24 RT510 15 RT511–RT512 1 RT513 15 RT514–RT515 1 RT516 4 RT517 1 RT518 4 RT519–RT523 1 RT524 4 RT525 1 RT526 4 RT527 1 RT528 4 RT529 1 RT530 4 RT551–RT556 31 RT557–RT560 2 RT561–RT568 1 RT571 29 RT572 17 **Variable Group**Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 24 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

RT573–RT574 23 RT575 17 RT576 23 RT577–RT588 1 RT590 1 RT591 31 RT601–RT604 37 RT605–RT608 33 RT609–RT630 32 RT633–RT634 1 RT636–RT640 1 RT641 31 RT642 2 RT643–RT645 31 RT646–RT650 2 RT671 31 RT672 2 RT673 1 RT691–RT692 31 RT693 2 RT694–RT699 1 RT701–RT702 13 RT703–RT704 11 RT741 2 RT742–RT750 1 RT751 36 RT752 33 RT753–RT755 32 RT756–RT757 18 RT776 16 RT777 35 RT781–RT782 14 RT783–RT784 34 RT801–RT803 1 RT811–RT814 1 RT831–RT835 1 RT837 1 RT861–RT864 1 RT931–RT932 19 **Variable Group**Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 25 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

2. Spares Affected None. **B. Concurrent Requirements** Changes given in this service bulletin can not be made unless the changes given in these service bulletins are made.

**C. Reason** Accomplishment of the changes in this service bulletin will help prevent an ignition source in a fuel tank as a result of a horizontal stabilizer override/jettison fuel pump that continues to run after it has been commanded off. An ignition source in a fuel tank could result in a fire or an explosion. A safety assessment conducted by Boeing indicates that there is a small risk of an ignition source in a fuel tank if a horizontal stabilizer override/jettison fuel pump continues to run for an extended time after fuel level goes below the pump inlet. Normally the pump is commanded off when a low fuel pressure is indicated. If a single failure in the pump control circuitry occurs, a pump can continue to run after it is commanded off. When a pump runs after the fuel level goes below the pump inlet, there is a small risk that the pump can cause an ignition source in the fuel tank from an overheat condition, electrical arcs or frictional sparks. RT945–RT949 32 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

**Company Service Bulletin Revision Level Description Notes** Boeing 747-28A2262 Original Issue, Revision 1, Revision 2. Install automatic shutoff system for the Horizontal Stabilizer Tank (HST) fuel pumps. (a)

(a) This service bulletin is not a concurrent or prior requirement for airplanes RM403, RM441-RM443, RM445. **Variable Group**Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 26 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

This service bulletin gives the instructions to install new relays and wiring in the circuitry for the horizontal stabilizer override/jettison fuel pumps. The new relays and wiring for the horizontal stabilizer override/jettison fuel pumps remove power from these pumps when the pumps continue to run after the pumps have been commanded off. Each set of relays have a new Engine Indication and Crew Alerting System (EICAS) status message to annunciate a fault in a pump control relay. For the horizontal stabilizer tank, the EICAS status messages are FUEL CMD STAB L and Fuel CMD STAB R. These changes help make sure that the risk of an ignition source in a fuel tank is kept to a minimum. The changes are identical to the changes to airplanes in production. 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 the comments received from operators since the original issue of the service bulletin and incorporate differences identified during the validation of the service bulletin. Airplanes RT966-RT967 were deleted from the effectivity. These airplanes are not equipped with stabilizer tanks. As a part of a service bulletin validation program, this change was completed on Airplane RT409 by original issue of Service Bulletin 747-28A2281 and before the release of Revision 1 of this service bulletin. The change completed on airplane RT409 by Service Bulletin 747-28A2281 is equivalent to Revision 1 of this service bulletin. Airplane RT409 has the configuration of a Group 20 airplane. The data given in Information Notice 747-28A2281 IN 01, IN 02 and IN 03 is included in this revision. **D. Description** Group 1-2; Group 3, Configuration 1; Group 4; Group 5, Configuration 2; Group 6, Configuration 2; Group 7-8, 10-14; Group 15, Configuration 2; Group 17, Configuration 2; Group 19, Configuration 1; Group 20-22; Group 23, Configuration 2; Group 24-31: Get access to E8 shelf and install new relays. Rework/install new wiring on E8 shelf. Get access and rework/install new airplane wiring from E8 shelf to disconnect AC1401 and rework/install new airplane wiring from disconnect AC1401 to P180 panel. Rework/install new wiring on P180 panel. Rework wiring from P180 panel to Modularized Avionics and Warning Electronics Assembly (MAWEA). Do a functional test. Close access. Group 9: Get access to E8 shelf and install new relays. Rework/install new wiring on E8 shelf. Get access and rework/install new airplane wiring from E8 shelf to disconnect AC1401 and install new airplane wiring from disconnect AC1401 to P180 panel. Rework/install new wiring on P180 panel. Install new wiring from P180 panel to MAWEA. Do a functional test. Close access. Group 16; Group 18, Configuration 2; Group 32-37: Get access to E8 shelf and install new relays. Rework/install new wiring on E8 shelf. Get access and rework/install new airplane wiring from E8 shelf to disconnect AC1401 and rework/install new airplane wiring from disconnect AC1401 to P180 panel and add new connector to P180 panel. Rework/install new wiring on P180 panel. Rework wiring from P180 panel to MAWEA Card File (P54). Do a functional test. Close access. Revision 1 - No more work is necessary on airplanes changed as shown in the original issue of this service bulletin. Boeing Service Bulletin 747-28A2280 is related to this service bulletin and has some common access procedures.Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 27 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

**E. Compliance** The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to this service bulletin. The Airworthiness Directive will make the compliance tasks and times given in this service bulletin mandatory. Boeing recommends that this service bulletin be incorporated within 5 years after the original issue date of this service bulletin. **F. Approval** This service bulletin was examined by the Federal Aviation Administration (FAA). The changes specified in this service bulletin comply with the applicable regulations and are FAA approved, as well as European Aviation Safety Agency (EASA)/Joint Aviation Authorities (JAA) approved for all EASA/ JAA approved airplanes listed in the service bulletin effectivity. This service bulletin and its approval were based on the airplane in its original Boeing delivery configuration or as modified by other approved Boeing changes. If an airplane has a non-Boeing modification or repair that affects a component or system also affected by this service bulletin, the operator is responsible for obtaining appropriate regulatory agency approval before incorporating this service bulletin. **G. Manpower** The table below shows an estimate of the task-hours necessary to do this service bulletin 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 3, Configuration 2; Group 5, Configuration 1; Group 6, Configuration 1; Group 15, Configuration 1; Group 17, Configuration 1; Group 18, Configuration 1; Group 19, Configuration 2; Group 23, Configuration 1: Airplanes, No work is necessary for airplanes in this configuration and no Task-Hours are required. Group 1:
**Task Number of**  **Persons Task-Hours Elapsed Hours** Open Access 4 13.00 3.25 Figure 1 1 2.75 2.75 Figure 2 n/a n/a n/a Figure 3 2 19.90 9.95 Figure 8 2 23.20 11.60 Figure 13 1 1.85 1.85 Figure 14 1 0.20 0.20Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 28 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

Figure 15 2 6.60 3.30 Figure 16 1 2.75 2.75 Figure 17 1 2.85 2.85 Figure 18 2 6.60 3.30 Figure 20 1 2.75 2.75 Figure 21 1 2.85 2.85 Figure 36 1 0.40 0.40 Close Access 4 13.00 3.25 Test 2 2.50 1.25 TOTAL FOR EACH AIRPLANE 101.20 52.30 Group 18, Configuration 2; Group 32:
**Task Number of**  **Persons Task-Hours Elapsed Hours** Open Access 4 13.00 3.25 Figure 1 1 2.75 2.75 Figure 2 n/a n/a n/a Figure 3 2 19.90 9.95 Figure 44 2 23.20 11.60 Figure 47 1 1.85 1.85 Figure 14 1 0.20 0.20 Figure 15 2 6.60 3.30 Figure 16 1 2.75 2.75 Figure 17 1 2.85 2.85 Figure 18 2 6.60 3.30 Figure 20 1 2.75 2.75 Figure 21 1 2.85 2.85 Figure 36 1 0.40 0.40 Close Access 4 13.00 3.25 Test 2 2.50 1.25 TOTAL FOR EACH AIRPLANE 101.20 52.30 Group 2:
**Task Number of**  **Persons Task-Hours Elapsed Hours** Open Access 4 13.00 3.25 Figure 1 1 2.75 2.75 Figure 2 n/a n/a n/a Group 1:
**Task Number of**  **Persons Task-Hours Elapsed Hours**Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 29 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

Figure 6 2 20.00 10.00 Figure 8 2 23.20 11.60 Figure 13 1 1.85 1.85 Figure 14 1 0.20 0.20 Figure 15 2 6.60 3.30 Figure 16 1 2.75 2.75 Figure 17 1 2.85 2.85 Figure 18 2 6.60 3.30 Figure 20 1 2.75 2.75 Figure 21 1 2.85 2.85 Figure 36 1 0.40 0.40 Close Access 4 13.00 3.25 Test 2 2.50 1.25 TOTAL FOR EACH AIRPLANE 101.30 52.35 Group 33:
**Task Number of**  **Persons Task-Hours Elapsed Hours** Open Access 4 13.00 3.25 Figure 1 1 2.75 2.75 Figure 2 n/a n/a n/a Figure 6 2 20.00 10.00 Figure 44 2 23.20 11.60 Figure 47 1 1.85 1.85 Figure 14 1 0.20 0.20 Figure 15 2 6.60 3.30 Figure 16 1 2.75 2.75 Figure 17 1 2.85 2.85 Figure 18 2 6.60 3.30 Figure 20 1 2.75 2.75 Figure 21 1 2.85 2.85 Figure 36 1 0.40 0.40 Close Access 4 13.00 3.25 Test 2 2.50 1.25 TOTAL FOR EACH AIRPLANE 101.30 52.35 Group 2:
**Task Number of**  **Persons Task-Hours Elapsed Hours**Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 30 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

Group 3, Configuration 1:
**Task Number of**  **Persons Task-Hours Elapsed Hours** Open Access 4 13.00 3.25 Figure 1 1 2.75 2.75 Figure 2 n/a n/a n/a Figure 39 2 20.00 10.00 Figure 8 2 23.20 11.60 Figure 13 1 1.85 1.85 Figure 14 1 0.20 0.20 Figure 15 2 6.60 3.30 Figure 16 1 2.75 2.75 Figure 17 1 2.85 2.85 Figure 18 2 6.60 3.30 Figure 19 1 2.75 2.75 Figure 21 1 2.85 2.85 Figure 36 1 0.40 0.40 Close Access 4 13.00 3.25 Test 2 2.50 1.25 TOTAL FOR EACH AIRPLANE 101.30 52.35 Group 4; Group 15, Configuration 2; Group 17, Configuration 2:
**Task Number of**  **Persons Task-Hours Elapsed Hours** Open Access 4 13.00 3.25 Figure 1 1 2.75 2.75 Figure 2 n/a n/a n/a Figure 5 2 19.80 9.90 Figure 8 2 23.20 11.60 Figure 13 1 1.85 1.85 Figure 14 1 0.20 0.20 Figure 15 2 6.60 3.30 Figure 16 1 2.75 2.75 Figure 17 1 2.85 2.85 Figure 18 2 6.60 3.30 Figure 20 1 2.75 2.75 Figure 21 1 2.85 2.85 Figure 36 1 0.40 0.40 Close Access 4 13.00 3.25 Test 2 2.50 1.25 TOTAL FOR EACH AIRPLANE 101.10 52.25Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 31 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

Group 5, Configuration 2; Group 25:
**Task Number of**  **Persons Task-Hours Elapsed Hours** Open Access 4 13.00 3.25 Figure 1 1 2.75 2.75 Figure 2 n/a n/a n/a Figure 40 2 20.00 10.00 Figure 8 2 23.20 11.60 Figure 13 1 1.85 1.85 Figure 14 1 0.20 0.20 Figure 15 2 6.60 3.30 Figure 16 1 2.75 2.75 Figure 17 1 2.85 2.85 Figure 18 2 6.60 3.30 Figure 43 1 2.75 2.75 Figure 21 1 2.85 2.85 Figure 36 1 0.40 0.40 Close Access 4 13.00 3.25 Test 2 2.50 1.25 TOTAL FOR EACH AIRPLANE 101.30 52.35 Group 6, Configuration 2; Group 24:
**Task Number of**  **Persons Task-Hours Elapsed Hours** Open Access 4 13.00 3.25 Figure 1 1 2.75 2.75 Figure 2 n/a n/a n/a Figure 38 2 19.80 9.90 Figure 8 2 23.20 11.60 Figure 13 1 1.85 1.85 Figure 14 1 0.20 0.20 Figure 15 2 6.60 3.30 Figure 16 1 2.75 2.75 Figure 17 1 2.85 2.85 Figure 18 2 6.60 3.30 Figure 43 1 2.75 2.75 Figure 21 1 2.85 2.85 Figure 36 1 0.40 0.40 Close Access 4 13.00 3.25 Test 2 2.50 1.25 TOTAL FOR EACH AIRPLANE 101.10 52.25Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 32 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

Group 7:
**Task Number of**  **Persons Task-Hours Elapsed Hours** Open Access 4 13.00 3.25 Figure 1 1 2.75 2.75 Figure 2 n/a n/a n/a Figure 4 2 19.90 9.95 Figure 8 2 23.20 11.60 Figure 13 1 1.85 1.85 Figure 14 1 0.20 0.20 Figure 15 2 6.60 3.30 Figure 16 1 2.75 2.75 Figure 17 1 2.85 2.85 Figure 18 2 6.60 3.30 Figure 19 1 2.75 2.75 Figure 21 1 2.85 2.85 Figure 36 1 0.40 0.40 Close Access 4 13.00 3.25 Test 2 2.50 1.25 TOTAL FOR EACH AIRPLANE 101.20 52.30 Group 8:
**Task Number of**  **Persons Task-Hours Elapsed Hours** Open Access 4 13.00 3.25 Figure 1 1 2.75 2.75 Figure 2 n/a n/a n/a Figure 3 2 19.90 9.95 Figure 11 2 23.40 11.70 Figure 13 1 1.85 1.85 Figure 14 1 0.20 0.20 Figure 15 2 6.60 3.30 Figure 16 1 2.75 2.75 Figure 17 1 2.85 2.85 Figure 18 2 6.60 3.30 Figure 20 1 2.75 2.75 Figure 21 1 2.85 2.85 Figure 36 1 0.40 0.40 Close Access 4 13.00 3.25 Test 2 2.50 1.25 TOTAL FOR EACH AIRPLANE 101.40 52.40Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 33 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

Group 34:
**Task Number of**  **Persons Task-Hours Elapsed Hours** Open Access 4 13.00 3.25 Figure 1 1 2.75 2.75 Figure 2 n/a n/a n/a Figure 3 2 19.90 9.95 Figure 46 2 23.40 11.70 Figure 47 1 1.85 1.85 Figure 14 1 0.20 0.20 Figure 15 2 6.60 3.30 Figure 16 1 2.75 2.75 Figure 17 1 2.85 2.85 Figure 18 2 6.60 3.30 Figure 20 1 2.75 2.75 Figure 21 1 2.85 2.85 Figure 36 1 0.40 0.40 Close Access 4 13.00 3.25 Test 2 2.50 1.25 TOTAL FOR EACH AIRPLANE 101.40 52.40 Group 9:
**Task Number of**  **Persons Task-Hours Elapsed Hours** Open Access 4 13.00 3.25 Figure 22 1 2.75 2.75 Figure 23 n/a n/a n/a Figure 24 2 19.90 9.95 Figure 25 2 23.20 11.60 Figure 26 1 1.85 1.85 Figure 27 2 6.40 3.20 Figure 28 2 6.60 3.30 Figure 29 1 2.75 2.75 Figure 30 1 2.85 2.85 Figure 31 2 6.60 3.30 Figure 32 1 2.75 2.75 Figure 33 1 2.85 2.85 Figure 34 1 0.40 0.40 Figure 35 n/a n/a n/aOriginal Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 34 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

Close Access 4 13.00 3.25 Test 2 2.50 1.25 TOTAL FOR EACH AIRPLANE 107.40 55.30 Group 10:
**Task Number of**  **Persons Task-Hours Elapsed Hours** Open Access 4 13.00 3.25 Figure 1 1 2.75 2.75 Figure 2 n/a n/a n/a Figure 3 2 19.90 9.95 Figure 12 2 23.30 11.65 Figure 13 1 1.85 1.85 Figure 14 1 0.20 0.20 Figure 15 2 6.60 3.30 Figure 16 1 2.75 2.75 Figure 17 1 2.85 2.85 Figure 18 2 6.60 3.30 Figure 20 1 2.75 2.75 Figure 21 1 2.85 2.85 Figure 36 1 0.40 0.40 Close Access 4 13.00 3.25 Test 2 2.50 1.25 TOTAL FOR EACH AIRPLANE 101.30 52.35 Group 11:
**Task Number of**  **Persons Task-Hours Elapsed Hours** Open Access 4 13.00 3.25 Figure 1 1 2.75 2.75 Figure 2 n/a n/a n/a Figure 3 2 19.90 9.95 Figure 10 2 23.40 11.70 Figure 13 1 1.85 1.85 Figure 14 1 0.20 0.20 Figure 15 2 6.60 3.30 Figure 16 1 2.75 2.75 Figure 17 1 2.85 2.85 Group 9:
**Task Number of**  **Persons Task-Hours Elapsed Hours**Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 35 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

Figure 18 2 6.60 3.30 Figure 20 1 2.75 2.75 Figure 21 1 2.85 2.85 Figure 36 1 0.40 0.40 Close Access 4 13.00 3.25 Test 2 2.50 1.25 TOTAL FOR EACH AIRPLANE 101.40 52.40 Group 35:
**Task Number of**  **Persons Task-Hours Elapsed Hours** Open Access 4 13.00 3.25 Figure 1 1 2.75 2.75 Figure 2 n/a n/a n/a Figure 3 2 19.90 9.95 Figure 45 2 23.40 11.70 Figure 47 1 1.85 1.85 Figure 14 1 0.20 0.20 Figure 15 2 6.60 3.30 Figure 16 1 2.75 2.75 Figure 17 1 2.85 2.85 Figure 18 2 6.60 3.30 Figure 20 1 2.75 2.75 Figure 21 1 2.85 2.85 Figure 36 1 0.40 0.40 Close Access 4 13.00 3.25 Test 2 2.50 1.25 TOTAL FOR EACH AIRPLANE 101.40 52.40 Group 12:
**Task Number of**  **Persons Task-Hours Elapsed Hours** Open Access 4 13.00 3.25 Figure 1 1 2.75 2.75 Figure 2 n/a n/a n/a Figure 3 2 19.90 9.95 Figure 9 2 23.30 11.65 Figure 13 1 1.85 1.85 Group 11:
**Task Number of**  **Persons Task-Hours Elapsed Hours**Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 36 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

Figure 14 1 0.20 0.20 Figure 15 2 6.60 3.30 Figure 16 1 2.75 2.75 Figure 17 1 2.85 2.85 Figure 18 2 6.60 3.30 Figure 20 1 2.75 2.75 Figure 21 1 2.85 2.85 Figure 36 1 0.40 0.40 Close Access 4 13.00 3.25 Test 2 2.50 1.25 TOTAL FOR EACH AIRPLANE 101.30 52.35 Group 13:
**Task Number of**  **Persons Task-Hours Elapsed Hours** Open Access 4 13.00 3.25 Figure 1 1 2.75 2.75 Figure 2 n/a n/a n/a Figure 40 2 20.00 10.00 Figure 10 2 23.40 11.70 Figure 13 1 1.85 1.85 Figure 14 1 0.20 0.20 Figure 15 2 6.60 3.30 Figure 16 1 2.75 2.75 Figure 17 1 2.85 2.85 Figure 18 2 6.60 3.30 Figure 43 1 2.75 2.75 Figure 21 1 2.85 2.85 Figure 36 1 0.40 0.40 Close Access 4 13.00 3.25 Test 2 2.50 1.25 TOTAL FOR EACH AIRPLANE 101.50 52.45 Group 12:
**Task Number of**  **Persons Task-Hours Elapsed Hours**Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 37 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

Group 14:
**Task Number of**  **Persons Task-Hours Elapsed Hours** Open Access 4 13.00 3.25 Figure 1 1 2.75 2.75 Figure 2 n/a n/ n/a Figure 5 2 19.80 9.90 Figure 11 2 23.40 11.70 Figure 13 1 1.85 1.85 Figure 14 1 0.20 0.20 Figure 15 2 6.60 3.30 Figure 16 1 2.75 2.75 Figure 17 1 2.85 2.85 Figure 18 2 6.60 3.30 Figure 20 1 2.75 2.75 Figure 21 1 2.85 2.85 Figure 36 1 0.40 0.40 Close Access 4 13.00 3.25 Test 2 2.50 1.25 TOTAL FOR EACH AIRPLANE 101.30 52.35 Group 16:
**Task Number of**  **Persons Task-Hours Elapsed Hours** Open Access 4 13.00 3.25 Figure 1 1 2.75 2.75 Figure 2 n/a n/a n/a Figure 7 2 20.00 10.00 Figure 45 2 23.40 11.70 Figure 47 1 1.85 1.85 Figure 14 1 0.20 0.20 Figure 15 2 6.60 3.30 Figure 16 1 2.75 2.75 Figure 17 1 2.85 2.85 Figure 18 2 6.60 3.30 Figure 20 1 2.75 2.75 Figure 21 1 2.85 2.85 Figure 36 1 0.40 0.40 Close Access 4 13.00 3.25 Test 2 2.50 1.25 TOTAL FOR EACH AIRPLANE 101.50 52.45Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 38 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

Group 19, Configuration 1:
**Task Number of**  **Persons Task-Hours Elapsed Hours** Open Access 4 13.00 3.25 Figure 1 1 2.75 2.75 Figure 2 n/a n/a n/a Figure 3 2 19.90 9.95 Figure 8 2 23.20 11.60 Figure 13 1 1.85 1.85 Figure 14 1 0.20 0.20 Figure 41 2 6.60 3.30 Figure 16 1 2.75 2.75 Figure 17 1 2.85 2.85 Figure 18 2 6.60 3.30 Figure 20 1 2.75 2.75 Figure 21 1 2.85 2.85 Figure 36 1 0.40 0.40 Close Access 4 13.00 3.25 Test 2 2.50 1.25 TOTAL FOR EACH AIRPLANE 101.20 52.30 Group 20:
**Task Number of**  **Persons Task-Hours Elapsed Hours** Open Access 4 13.00 3.25 Figure 1 1 2.75 2.75 Figure 2 n/a n/a n/a Figure 37 2 20.00 10.00 Figure 8 2 23.20 11.60 Figure 13 1 1.85 1.85 Figure 14 1 0.20 0.20 Figure 15 2 6.60 3.30 Figure 16 1 2.75 2.75 Figure 17 1 2.85 2.85 Figure 18 2 6.60 3.30 Figure 19 1 2.75 2.75 Figure 21 1 2.85 2.85 Figure 36 1 0.40 0.40 Close Access 4 13.00 3.25 Test 2 2.50 1.25 TOTAL FOR EACH AIRPLANE 101.30 52.35Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 39 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

Group 21:
**Task Number of**  **Persons Task-Hours Elapsed Hours** Open Access 4 13.00 3.25 Figure 1 1 2.75 2.75 Figure 2 n/a n/a n/a Figure 39 2 20.00 10.00 Figure 8 2 23.20 11.60 Figure 13 1 1.85 1.85 Figure 14 1 0.20 0.20 Figure 41 2 6.60 3.30 Figure 16 1 2.75 2.75 Figure 17 1 2.85 2.85 Figure 42 2 6.60 3.30 Figure 19 1 2.75 2.75 Figure 21 1 2.85 2.85 Figure 36 1 0.40 0.40 Close Access 4 13.00 3.25 Test 2 2.50 1.25 TOTAL FOR EACH AIRPLANE 101.30 52.35 Group 22:
**Task Number of**  **Persons Task-Hours Elapsed Hours** Open Access 4 13.00 3.25 Figure 1 1 2.75 2.75 Figure 2 n/a n/a n/a Figure 39 2 20.00 10.00 Figure 8 2 23.20 11.60 Figure 13 1 1.85 1.85 Figure 14 1 0.20 0.20 Figure 15 2 6.60 3.30 Figure 16 1 2.75 2.75 Figure 17 1 2.85 2.85 Figure 18 2 6.60 3.30 Figure 19 1 2.75 2.75 Figure 21 1 2.85 2.85 Figure 36 1 0.40 0.40 Close Access 4 13.00 3.25 Test 2 2.50 1.25 TOTAL FOR EACH AIRPLANE 101.30 52.35Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 40 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

Group 23, Configuration 2:
**Task Number of**  **Persons Task-Hours Elapsed Hours** Open Access 4 13.00 3.25 Figure 1 1 2.75 2.75 Figure 2 n/a n/a n/a Figure 38 2 19.80 9.90 Figure 8 2 23.20 11.60 Figure 13 1 1.85 1.85 Figure 14 1 0.20 0.20 Figure 15 2 6.60 3.30 Figure 16 1 2.75 2.75 Figure 17 1 2.85 2.85 Figure 18 2 6.60 3.30 Figure 43 1 2.75 2.75 Figure 21 1 2.85 2.85 Figure 36 1 0.40 0.40 Close Access 4 13.00 3.25 Test 2 2.50 1.25 TOTAL FOR EACH AIRPLANE 101.10 52.25 Group 26:
**Task Number of**  **Persons Task-Hours Elapsed Hours** Open Access 4 13.00 3.25 Figure 1 1 2.75 2.75 Figure 2 n/a n/a n/a Figure 40 2 20.00 10.00 Figure 8 2 23.20 11.60 Figure 13 1 1.85 1.85 Figure 14 1 0.20 0.20 Figure 41 2 6.60 3.30 Figure 16 1 2.75 2.75 Figure 17 1 2.85 2.85 Figure 42 2 6.60 3.30 Figure 43 1 2.75 2.75 Figure 21 1 2.85 2.85 Figure 36 1 0.40 0.40 Close Access 4 13.00 3.25 Test 2 2.50 1.25 TOTAL FOR EACH AIRPLANE 101.30 52.35Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 41 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

Group 27:
**Task Number of**  **Persons Task-Hours Elapsed Hours** Open Access 4 13.00 3.25 Figure 1 1 2.75 2.75 Figure 2 n/a n/a n/a Figure 40 2 20.00 10.00 Figure 8 2 23.20 11.60 Figure 13 1 1.85 1.85 Figure 14 1 0.20 0.20 Figure 41 2 6.60 3.30 Figure 16 1 2.75 2.75 Figure 17 1 2.85 2.85 Figure 42 2 6.60 3.30 Figure 43 1 2.75 2.75 Figure 21 1 2.85 2.85 Figure 36 1 0.40 0.40 Close Access 4 13.00 3.25 Test 2 2.50 1.25 TOTAL FOR EACH AIRPLANE 101.30 52.35 Group 28:
**Task Number of**  **Persons Task-Hours Elapsed Hours** Open Access 4 13.00 3.25 Figure 1 1 2.75 2.75 Figure 2 n/a n/a n/a Figure 40 2 20.00 10.00 Figure 8 2 23.20 11.60 Figure 13 1 1.85 1.85 Figure 14 1 0.20 0.20 Figure 15 2 6.60 3.30 Figure 16 1 2.75 2.75 Figure 17 1 2.85 2.85 Figure 18 2 6.60 3.30 Figure 43 1 2.75 2.75 Figure 21 1 2.85 2.85 Figure 36 1 0.40 0.40 Close Access 4 13.00 3.25 Test 2 2.50 1.25 TOTAL FOR EACH AIRPLANE 101.30 52.35Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 42 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

Group 36:
**Task Number of**  **Persons Task-Hours Elapsed Hours** Open Access 4 13.00 3.25 Figure 1 1 2.75 2.75 Figure 2 n/a n/a n/a Figure 40 2 20.00 10.00 Figure 44 2 23.20 11.60 Figure 47 1 1.85 1.85 Figure 14 1 0.20 0.20 Figure 15 2 6.60 3.30 Figure 16 1 2.75 2.75 Figure 17 1 2.85 2.85 Figure 18 2 6.60 3.30 Figure 43 1 2.75 2.75 Figure 21 1 2.85 2.85 Figure 36 1 0.40 0.40 Close Access 4 13.00 3.25 Test 2 2.50 1.25 TOTAL FOR EACH AIRPLANE 101.30 52.35 Group 29:
**Task Number of**  **Persons Task-Hours Elapsed Hours** Open Access 4 13.00 3.25 Figure 1 1 2.75 2.75 Figure 2 n/a n/a n/a Figure 37 2 20.00 10.00 Figure 8 2 23.20 11.60 Figure 13 1 1.85 1.85 Figure 14 1 0.20 0.20 Figure 41 2 6.60 3.30 Figure 16 1 2.75 2.75 Figure 17 1 2.85 2.85 Figure 42 2 6.60 3.30 Figure 19 1 2.75 2.75 Figure 21 1 2.85 2.85 Figure 36 1 0.40 0.40 Close Access 4 13.00 3.25 Test 2 2.50 1.25 TOTAL FOR EACH AIRPLANE 101.30 52.35Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 43 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

Group 30:
**Task Number of**  **Persons Task-Hours Elapsed Hours** Open Access 4 13.00 3.25 Figure 1 1 2.75 2.75 Figure 2 n/a n/a n/a Figure 6 2 20.00 10.00 Figure 8 2 23.20 11.60 Figure 13 1 1.85 1.85 Figure 14 1 0.20 0.20 Figure 41 2 6.60 3.30 Figure 16 1 2.75 2.75 Figure 17 1 2.85 2.85 Figure 42 2 6.60 3.30 Figure 20 1 2.75 2.75 Figure 21 1 2.85 2.85 Figure 36 1 0.40 0.40 Close Access 4 13.00 3.25 Test 2 2.50 1.25 TOTAL FOR EACH AIRPLANE 101.30 52.35 Group 31:
**Task Number of**  **Persons Task-Hours Elapsed Hours** Open Access 4 13.00 3.25 Figure 1 1 2.75 2.75 Figure 2 n/a n/a n/a Figure 6 2 20.00 10.00 Figure 8 2 23.20 11.60 Figure 13 1 1.85 1.85 Figure 14 1 0.20 0.20 Figure 41 2 6.60 3.30 Figure 16 1 2.75 2.75 Figure 17 1 2.85 2.85 Figure 42 2 6.60 3.30 Figure 20 1 2.75 2.75 Figure 21 1 2.85 2.85 Figure 36 1 0.40 0.40 Close Access 4 13.00 3.25 Test 2 2.50 1.25 TOTAL FOR EACH AIRPLANE 101.30 52.35Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 44 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

**H. Weight and Balance Changes**

**I. Electrical Load Data** 1. Direct Current (DC) Loads

2. Alternating Current (AC) Loads None 3. Type Group 37:
**Task Number of**  **Persons Task-Hours Elapsed Hours** Open Access 4 13.00 3.25 Figure 1 1 2.75 2.75 Figure 2 n/a n/a n/a Figure 6 2 20.00 10.00 Figure 44 2 23.20 11.60 Figure 47 1 1.85 1.85 Figure 14 1 0.20 0.20 Figure 41 2 6.60 3.30 Figure 16 1 2.75 2.75 Figure 17 1 2.85 2.85 Figure 42 2 6.60 3.30 Figure 20 1 2.75 2.75 Figure 21 1 2.85 2.85 Figure 36 1 0.40 0.40 Close Access 4 13.00 3.25 Test 2 2.50 1.25 TOTAL FOR EACH AIRPLANE 101.30 52.35

**Airplane Change in Weight**  **(Pounds) Change in Moment**  **(Pound-Inches)** Groups 1-8 and Groups 10-15, 17, 19-31 +4.8 lbs +7516.8 lb-in

Group 9 +4.9 lbs +7673.4 lb-in Groups 16, 18, 32- 37 +4.9 lbs +7673.4 lb-in

**Airplanes Amperes Bus** Groups 1-37 0.60 D1P7 0.60 D2P7Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 45 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

Continuous Intermittent **J. References** 1. Existing Data: a. Engineering Change Memo PRR 85539-8 b. 747-400 Aircraft Maintenance Manual (AMM) 12-11-01, 20-11-16, 24-22-00, 24-29-04; 25-21-01, 25-22-01, 25-52-01, 25-76-02, 31-61-00, 32-09-02, 34-61-02, 45-10-00, 53-21-02 c. 747 Wiring Diagram 28-21-28, 28-21-31, 28-42-15, 30-41-31 d. Boeing Drawing 012W6100 e. 747 Structural Repair Manual (SRM) Subject 51-40-05 f. Boeing Parts Standards Document D-590 g. Boeing Service Bulletin 747-28-2183 h. Boeing Service Bulletin 747-28-2197 i. Boeing Service Bulletin 747-28-2247 j. Boeing Service Bulletin 747-28-2265 k. Boeing Service Bulletin 747-28-2272 l. Boeing Service Bulletin 747-28-2274 m. Boeing Service Bulletin 747-28-2275 n. Boeing Service Bulletin 747-28A2262 o. Boeing Service Bulletin 747-28A2280 p. Standard Wiring Practices Manual (SWPM) 20-10-11, 20-10-12, 20-10-19, 20-20-00, 20-30-11, 20-30-12, 20-61-11 2. Data supplied with this Service Bulletin: None.Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 46 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

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

2. Damage Tolerance Based Structural Inspections: **Drawing Number Title** 284U4218 Aft Equip Center Assy - E8 288U3080 Modular Wire Bundle Instl, E8, Left Aft Equipment Panel 288U4661 Wire Bundle Installation, Upper Sidewall LH, Sta 2163 thru 2360 288U4641 Wire bundle Installation, Upper Sidewall LH, Sta 1983 thru 2163 288U4645 Wire Bundle Installation, Main deck sidewall LH, Sta 1983 thru 2163 288U4651 Wire Bundle Installation, Main deck floor beams LH, Sta 1983 thru 2163 288U4631 Wire Bundle Installation, Main deck floor beams LH, Sta 1723 thru 1983 288U4611 Wire Bundle Installation, Main deck floor beams LH, Sta 1483 thru 1723 288U4431 Wire Bundle Installation, Pressure deck and main deck FLR BMS LH, Sta 1243 thru 1483 288U4411 Wire Bundle Installation, Pressure deck and main deck FLR BMS LH, Sta 997 thru 1243 288U4231 Wire Bundle Installation, Main deck floor beams LH, Sta 723 thru 997 288U4211 Wire Bundle Installation, Main deck floor beams LH, Sta 523 thru 723 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 60 288U4150 Wire Bundle Installation, Main deck floor beams RH, Sta 403 thru 523 AFT Sta 400 bulkhead RH 288U4152 Wire Bundle Installation, Main Electronics Equipment Center RH, Sta 440 thru 460 288U4148 Wire Bundle Installation, Lower Sidewall RH, Sta 403 thru 523

**Publication Chapter-Section** 747 Maintenance Manual 28-17 747 Fault Isolation Manual 28-31 747 Wiring Diagram Manual 28-21, 28-42, 30-41 747 System Schematic Manual 28-21, 28-42, 30-41 747 Fault Reporting Manual EICAS Status Messages 747 Illustrated Parts Catalog 28-21Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 47 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

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.Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 48 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

BLANK PAGEOriginal Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 49 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

**2. MATERIAL INFORMATION A. Material - Price and Availability**  Boeing can supply the kits/parts shown in Paragraph 2.C., Parts Necessary For Each Airplane, and Paragraph 2.D., as shown below. If there is a limit to the quantity (QTY) of available kits/parts, a supply sequence is given by Spares. More kits/parts become available as shown in the Reorder Lead Time (ROLT). ROLT is calculated from the date Boeing gets the purchase order.

The kits are subject to the terms and conditions of the Boeing standard purchase order acknowledgment. After the Unit Price date, new price and ROLT data is applicable. Prices are in United States dollars. Terms: Net 30 days. Reference this service bulletin and submit your purchase order by one of the methods that follow: 1. Order on-line via ATA Spec 2000 or Boeing Part Page 2. Fax to (206) 662-7145 Group 1-2; Group 3, Configuration 1; Group 4; Group 5, Configuration 2; Group 6, Configuration 2; Group 7-8, 10-14; Group 15, Configuration 2; Group 16; Group 17, Configuration 2; Group 18, Configuration 2; Group 19, Configuration 1; Group 20-22; Group 23, Configuration 2; Group 24-37: **Top Kit Number Name Date QTY ROLT**  **(Weeks) Unit Price thru** 015U1808-1 Horizontal Stabilizer Tank Jettison Pump Uncommanded On. (a) 50 (a) (a)

(a) For Top Kit availability and pricing contact Boeing Spares. Group 9: **Top Kit Number Name Date QTY ROLT**  **(Weeks) Unit Price thru** 015U1808-2 Horizontal Stabilizer Tank Jettison Pump Uncommanded On. (a) 1 (a) (a)

(a) For Top Kit availability and pricing contact Boeing Spares. Group 16; Group 18, Configuration 2; Group 32-37: **Top Kit Number Name Date QTY ROLT**  **(Weeks) Unit Price thru** 015U1808-3 Supplemental kit to supply connector and ID tape. (b) (a) - (a) (a)

(a) For Top Kit availability and pricing contact Boeing Spares. (b) Operators who have ordered a 015U1808-1 kit can order the 015U1808-3 kit to complete the airplane installation. If an operator has not ordered the 015U1808-1 kit, the operator will need to order the 015U1808-1 and 015U1808-3 kits to complete the airplane installation.Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 50 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

3. Spares Customer Support - MC 36-65 Boeing Spares Department P.O. Box 3707 Seattle, Washington 98124-2207 USA **B. Industry Support Information** Boeing warranty remedies are not available for the configuration changes given in this service bulletin. **C. Parts Necessary For Each Airplane** 1. Kits/Parts: To get the kits/parts shown below, refer to Paragraph 2.A., Material - Price and Availability.Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 51 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

**NOTE:** One top kit and the items shown in Paragraph 2.C.2., Parts and Materials Supplied by the Operator, are necessary for each airplane. The Top Kit is divided into Figure kits for each installation figure shown in the table below. **Figure Kit Top Kit 1 3 13 14 22 24 26 27 34 36**  015U1808-1 1 1 1 1 - - - - - 1 015U1808-2 - - - - 1 1 1 1 1 -
**Wire Kit Top Kit 289U1225-**  **101 289U1225-**  **102 289U1225-**  **103 289U1225-**  **104** 015U1808-1 1 1 1 1 015U1808-2 1 1 1 -
**Wire Kit Top Kit 289U1225-**  **105 289U1225-**  **106** 015U1808-1 - 1 015U1808-2 1 1 **Kit 015U1808-1 - Group 1-2; Group 3, Configurat ion 1; Group 4-5; Group 5, Configuration 2;**  **Group 6, Configuration 2; Group 7-8, 10-14; Group 15, Configuration 2; Group 16; Group 17, Configuration 2; Group 18, Configuration 2;**  **Group 19, Configuration 1; Group 20-22; Group 23, Configuration 2; Group 24-37:** 

**New Part Number**  **Figure**

**Name Existing Part**  **Number Notes 1 3 13 14 36**  **Qty** 001-1908-000 4 - - - - TERMINAL BARR
284U4011-45 1 - - - - RELAY BRACKET ASSY

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

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

289T9001-91 - - 1 - - LACING TAPE - WHITE (135C) 100 FT BAC27EEL19431 1 - - - - MARKER BAC27EEL29698 1 - - - - VINYL MARKER BAC27EEL29699 1 - - - - VINYL MARKER BACC10GE10 - - - - 1 CLAMP, LOOPOriginal Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 52 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

BACC10GE5 2 - - - 1 CLAMP, LOOP
BACJ40A20-2 1 - - - - BONDING JUMPER BACN10YR3CD 8 - - - - NUT BACS12GU3K10 4 - - - - SCREW BACS12GU3K8 4 - - - - SCREW BACS12GU3K9 1 - - - - SCREW, CAP BACS12HN06-7 1 - - - - BOLT BACS12HN3-20 - - - - 1 BOLT BACS12HN3-36 1 - - - - SCREW BACS12HN3-8 - - - - 1 BOLT
BH315 2 - - - - RELAY,25A,W/ AUX NAS1149D0316H 10 - - - - WASHER NAS1149D0332J 10 - - - 2 WASHER
NAS42DD6-64FC 2 - - - 1 SPACERS FOR RIVETS **Kit 015U1808-2 - Group 9:**

**New Part Number**  **Figure**

**Name Existing Part**  **Number Notes 22 24 26 27 34**  **Qty** 001-1908-000 4 - - - - TERMINAL BARR
284U4011-45 1 - - - - RELAY BRACKET ASSY

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

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

289T9001-91 - - 1 - - LACING TAPE - WHITE (135C) 100 FT BAC27EEL19431 1 - - - - MARKER BAC27EEL29698 1 - - - - VINYL MARKER **Kit 015U1808-1 - Group 1-2; Group 3, Configuration 1; Group 4-5; Group 5, Configuration 2; Group 6, Configuration 2; Group 7-8, 10-14; Group 15, Configuration 2; Group 16; Group 17,**  **Configuration 2; Group 18, Configuration 2; Group 19, Configuration 1; Group 20-22; Group 23, Configuration 2; Group 24-37:** 

**New Part Number**  **Figure**

**Name Existing Part**  **Number Notes 1 3 13 14 36**  **Qty**Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 53 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

BAC27EEL29699 1 - - - - VINYL MARKER BACC10GE10 - - - - 1 CLAMP, LOOP BACC10GE5 2 - - - 1 CLAMP, LOOP
BACJ40A20-2 1 - - - - BONDING JUMPER BACN10YR3CD 8 - - - - NUT BACS12GU3K10 4 - - - - SCREW BACS12GU3K8 4 - - - - SCREW BACS12GU3K9 1 - - - - SCREW, CAP BACS12HN06-7 1 - - - - BOLT BACS12HN3-20 - - - - 1 BOLT BACS12HN3-36 1 - - - - SCREW BACS12HN3-8 - - - - 1 BOLT
BH315 2 - - - - RELAY,25A,W/ AUX NAS1149D0316H 10 - - - - WASHER NAS1149D0332J 10 - - - 2 WASHER
NAS42DD6-64FC 2 - - - 1 SPACERS FOR RIVETS **Kit 289U1225-101 - Group 1-2; Group 3, Configuration 1; Group 4-5; Group 5, Configuration 2; Group 6, Configuration 2; Group 7-14; Group**  **15, Configuration 2; Group 16; Group 17, Configuration 2; Group 18, Configuration 2; Group 19, Configuration 1; Group 20-22; Group 23,**  **Configuration 2; Group 24-37:**

**New Part Number -101**  **Name Notes Qty**  289U1225-101W 1 WIRE - RAW MATERIAL BACC47CN1S 3 CONTACT, PIN BACC47CP1S 3 CONTACT

M23053/5-107-4 3 INSULATION SLEEVING, HEAT SHRINKABLE, POLYOLEFIN, FLEXIBLE, X-LINKED **Kit 015U1808-2 - Group 9:**

**New Part Number**  **Figure**

**Name Existing Part**  **Number Notes 22 24 26 27 34**  **Qty**Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 54 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

**Kit 289U1225-102 - Group 1-2; Group 3, Configuration 1; Group 4; Group 5, Configuration 2; Group 6, C**  **onfiguration 2; Group 7-14; Group 15, Configuration 2; Group 16; Group 17, Configuration 2; Group 18,**  **Configuration 2; Group 19, Configuration 1; Group 20-22; Group 23, Configuration 2; Group 24-37:** 

**New Part Number -102**  **Name Notes Qty**  289U1225-102W 1 WIRE - RAW MATERIAL BACC47CN1S 3 CONTACT, PIN BACC47CP1S 3 CONTACT

M23053/5-107-4 3 INSULATION SLEEVING, HEAT SHRINKABLE, POLYOLEFIN, FLEXIBLE, X-LINKED **Kit 289U1225-103 - Group 1-2; Group 3, Configuration 1; Group 4-5; Group 5, Configuration 2; Group 6, C**  **onfiguration 2; Group 7-14; Group 15, Configuration 2; Group 16; Group 17, Configuration 2; Group 18,**  **Configuration 2; Group 19, Configuration 1; Group 20-22; Group 23, Configuration 2; Group 24-37:** 

**New Part Number -103**  **Name Notes Qty**  289U1225-103W 1 WIRE - RAW MATERIAL BACC47CN1S 3 CONTACT, PIN BACC47CP1S 3 CONTACT **Kit 289U1225-104 - Group 1-2; Group 3, Configuration 1; Group 4; Group 5, Configuration 2; Group 6, Configuration 2; Group 7-8, 10-14;**  **Group 15, Configuration 2; Group 16; Group 17, Configuration 2; Group 18, Configuration 2; Group 19, Configuration 1; Group 20-22;**  **Group 23, Configuration 2; Group 24-37:**

**New Part Number -104**  **Name Notes Qty**  BACC47EG2 3 CONTACT, SOCKET **Kit 289U1225-105 - Group 9:**

**New Part Number -105**  **Name Notes Qty**  289U1225-105W 1 WIRE - RAW MATERIAL BACC47EG2 3 CONTACT, SOCKETOriginal Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 55 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

**Kit 289U1225-106 - Group 1-2; Group 3, Configuration 1; Group 4; Group 5, Configuration 2; Group 6, Configuration 2; Group 7-14; Group**  **15, Configuration 2; Group 16; Group 17, Configuration 2; Group 18, Configuration 2; Group 19, Configuration 1; Group 20-22; Group 23,**  **Configuration 2; Group 24-37:**

**New Part Number -106**  **Name Notes Qty**  289U1225-106W 1 WIRE - RAW MATERIAL BACC47CN1S 3 CONTACT, PIN BACC47CP1S 3 CONTACT BACC47CP3T 7 CONTACT BACT12AC12 7 TERMINAL, LUG BACT12AC2 21 TERMINAL, LUG BACT12E10 13 TERMINAL, LUG D436-38 3 SPLICE **Kit 015U1808-3 - Group 16; Group 18, Configuration 2; Group 32-37: New Part**  **Number -3**  **Name Existing Part**  **Number Notes Qty** 
289U1225-10701 1 ID TAPE - CONNECTOR
289U1225-10801 1 ID TAPE - CONNECTOR

BACC45FN16- 24S6 1 CONNECTOR, ELECTRICAL, RECEPTACLE, FLANGE MOUNT, BAYONET COUPLING

BACC45FT16- 24P6 1 CONNECTOR, ELECTRICAL, PLUG, STRAIGHT, BAYONET COUPLING BACC47CN1S 2 CONTACT, PIN
BACC47CP1S 2 CONTACT, SOCKET BACN10JC04CM 3 NUT BACS12HN04U6 3 SCREW NAS1149DN332J 3 WASHER, PLAINOriginal Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 56 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

2. Parts and Materials Supplied by the Operator:

3. Parts Modified and Reidentified: None. 4. Parts Removed and Not Replaced: None. **D. Parts Necessary to Change Spares** None. **E. Special Tooling - Price and Availability** None. **F. Special Tooling Necessary to do this Service Bulletin** No special tools or equipment are necessary to do the change in this service bulletin. But, maintenance and overhaul tools in the manuals given in Paragraph 1.J., References, can be necessary. Examine operator tool supply to make sure all necessary tools are available. **Part Number / Specification QTY Name Notes**  BMS 10-11, TYPE 1 1 pt PRIMER (a) BMS 5-95 1 pt SEALANT (a) NAS1149D616H or equivalent 1 Washer (b)
BACN10YR06CD or equivalent 1 Nut (b) (a) See the Qualified Products List at the end of the Boeing Material Specification (BMS) for supplier data. (b) If relay mounting bracket hole requires relocation (see Figure 1, Circle Note 3) these parts or equivalent may be required.Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 57 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

**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. The instructions identified in Paragraph 3.B. Work Instructions and the Figures(s) give the recommended sequence of steps. The sequence of steps to do this service bulletin can be changed. 2. Manual titles are referred to by acronyms. Refer to Paragraph 1.J., References, for definition of the acronyms. 3. Obey all of the warnings and cautions given in the specified manual sections. 4. 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 in 747 SRM, Chapter 51. — Torque limits to tighten nuts and bolts are in 747 SRM, Chapter 51. 5. Use the approved fastener and process material substitutions in accordance with 747 SRM, Chapter 51. 6. Refer to the SWPM 20-10-11 and SWPM 20-10-12 for the wire installation procedures, and SWPM 20-10-19 for wire separation requirements, as accepted procedures. 7. The necessary conditions for selection of a clamp and clamp size are included in SWPM 20-10-12. If the clamp size for the wire harness supports specified in this service bulletin does not make a correct fit on the wire bundle, refer to SWPM 20-10-12 as an accepted procedure to select the correct clamp. 8. If the length of any fastener specified in this service bulletin does not meet the installation standards in 747 SRM, Chapter 51, then a fastener of the same specification, or an approved substitute, with a length which meets the installation standards in 747 SRM, Chapter 51 may be used. 9. 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 Group 3, Configuration 2; Group 5, Configuration 1; Group 6, Configuration 1; Group 15,** Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 58 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

**Configuration 1; Group 17, Configuration 1; Group 18, Configuration 1; Group 19,**  **Configuration 2; Group 23, Configuration 1: Airplanes** 1. Airplanes - No work is necessary for airplanes in this configuration. The airplanes in this configuration do not have active Horizontal Stabilizer Tanks. **Group 1-2; Group 3, Configuration 1; Group 4; Group 5, Configuration 2; Group 6, Configuration 2; Group 7-8, 10-14; Group 15, Configuration 2; Group 16; Group 17,**  **Configuration 2; Group 18, Configuration 2; Gr oup 19, Configuration 1; Group 20-22; Group**  **23, Configuration 2; Group 24-37: Airplanes** 1. Gain access to the rework area as follows: a. If the airplane has a crew rest located over door 5 remove the sidewall partitions as necessary for access to the E-8 shelf and wire bundle routing, refer to 747-400 AMM 25-76-02. b. If the airplane has no crew rest located over door 5 remove the ceiling and lower side wall linings (station 2320 to 2300) as necessary for access to E-8 shelf and wire bundle routing, refer to 747-400 AMM 25-21-01 and 747-400 AMM 25-22-01 as accepted procedures. c. Remove the ceiling panels in the passenger compartment (station 2310 to station 2100 and some airplanes to station 1980) as necessary for access to the outer portion of the sidewall where required for routing of ships wire bundles, refer to 747-400 AMM 25-22-01 as an accepted procedure. d. Remove the ceiling panels in the rear cargo compartment (station 2100 or station 1980 to station 1480 as necessary for access to the cargo compartment ceiling where required for routing of ships wire bundles, refer to 747-400 AMM 25-52-01 as an accepted procedure. e. Remove the floor panels on the main deck (station 1480 to station 980) as necessary for access to the wire bundles that route between the forward cargo compartment and the aft cargo compartment, refer to 747-400 AMM 53-21-02 as an accepted procedure. Some airplanes may have the wire bundle routed in a conduit and removal of the floor panels may not be required. f. Remove cargo ceiling linings in the forward cargo compartment (station 980 to station 400) as necessary to access the wire bundles that route in the forward cargo compartment ceiling and to the main equipment bay, refer to 747-400 AMM 25-52-01 as an accepted procedure. **NOTE:** Operators should check their applicable wiring configurations to determine how much access will be required. 2. Remove electrical power from the airplane, refer to 747-400 AMM 24-22-00 as an accepted procedure. 3. Group 1-2; Group 3, Configuration 1; Group 4; Group 5, Configuration 2; Group 6, Configuration 2; Group 7-8, 10-14; Group 15, Configuration 2; Group 16; Group 17, Configuration 2; Group 18, Configuration 2; Group 19, Configuration 1; Group 20-22; Group 23, Configuration 2; Group 24-37: Install new relays on the E-8 shelf as given in Figure 1.Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 59 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

4. Group 1-2; Group 3, Configuration 1; Group 4; Group 5, Configuration 2; Group 6, Configuration 2; Group 7-8, 10-14; Group 15, Configuration 2; Group 16; Group 17, Configuration 2; Group 18, Configuration 2; Group 19, Configuration 1; Group 20-22; Group 23, Configuration 2; Group 24-37: Make wiring changes using the routing shown, for wire bundles W4488 and W4588, as given in Figure 2 and for wire bundle routing for wire bundle W3851, as given in Figure 36. 5. Group 1, 8, 10-12; Group 18, Configuration 2; Group 19, Configuration 1; Group 32, 34-35: Make wiring changes to wire bundle W4488 as given in Figure 3 and Figure 2 6. Group 7: Make wiring changes to wire bundle W4488 as given in Figure 4 and Figure 2. 7. Group 4, 14; Group 15, Configuration 2; Group 17, Configuration 2: Make wiring changes to wire bundle W4488 as given in Figure 5 and Figure 2. 8. Group 2, 30-31, 33, 37: Make wiring changes to wire bundle W4488 as given in Figure 6 and Figure 2. 9. Group 16: Make wiring changes to wire bundle W4488 as given in Figure 7 and Figure 2. 10. Group 20, 29: Make wiring changes to wire bundle W4488 as given in Figure 37 and Figure 2 11. Group 6, Configuration 2; Group 23, Configuration 2; Group 24: Make wiring changes to wire bundle W4488 as given in Figure 38 and Figure 2. 12. Group 3, Configuration 1; Group 21-22: Make wiring changes to wire bundle W4488 as given in Figure 39 and Figure 2. 13. Group 5, Configuration 2; Group 13, 25-28, 36: Make wiring changes to wire bundle W4488 as given in Figure 40 and Figure 2. 14. Group 1-2; Group 3, Configuration 1; Group 4; Group 5, Configuration 2; Group 6, Configuration 2; Group 7; Group 15, Configuration 2; Group 17, Configuration 2; Group 19, Configuration 1; Group 20-22; Group 23, Configuration 2; Group 24-31: Make wiring changes to wire bundle W4588 as given in Figure 8 and Figure 2. 15. Group 18, Configuration 2; Group 32-33, 36-37: Make wiring changes to wire bundle W4588 as given in Figure 44 and Figure 2.Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 60 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

16. Group 12: Make wiring changes to wire bundle W4588 as given in Figure 9 and Figure 2. 17. Group 11, 13: Make wiring changes to wire bundle W4588 as given in Figure 10 and Figure 2. 18. Group 16, 35: Make wiring changes to wire bundle W4588 as given in Figure 45 and Figure 2. 19. Group 8, 14: Make wiring changes to wire bundle W4588 as given in Figure 11 and Figure 2. 20. Group 34: Make wiring changes to wire bundle W4588 as given in Figure 46 and Figure 2. 21. Group 10: Make wiring changes to wire bundle W4588 as given in Figure 12 and Figure 2. 22. Group 1-2; Group 3, Configuration 1; Group 4; Group 5, Configuration 2; Group 6, Configuration 2; Group 7-8, 10-14; Group 15, Configuration 2; Group 17, Configuration 2; Group 19, Configuration 1; Group 20-22; Group 23, Configuration 2; Group 24-31: Make wiring changes to wire bundle W3845 as given in Figure 13. 23. Group 16; Group 18, Configuration 2; Group 32-37: Make wiring changes to wire bundle W3845 as given in Figure 47. 24. Group 1-2; Group 3, Configuration 1; Group 4; Group 5, Configuration 2; Group 6, Configuration 2; Group 7-8, 10-14; Group 15, Configuration 2; Group 16; Group 17, Configuration 2; Group 18, Configuration 2; Group 19, Configuration 1; Group 20-22; Group 23, Configuration 2; Group 24-37: Make wiring changes to wire bundle W4758 as given in Figure 14. See Figure 2 and 35 for MAWEA card file location and wire routing information. 25. Group 1-2; Group 3, Configuration 1; Group 4; Group 5, Configuration 2; Group 6, Configuration 2; Group 7-8, 10-14; Group 15, Configuration 2; Group 16; Group 17, Configuration 2; Group 18, Configuration 2; Group 20, 22; Group 23, Configuration 2; Group 24-25, 28, 32-36: Make wiring changes to wire bundle W3851 and route wiring as given in Figure 15 and Figure 36. 26. Group 19, Configuration 1; Group 21, 26-27, 29-31, 37: Make wiring changes to wire bundle W3851 and route wiring as given in Figure 41 and Figure 36.Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 61 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

27. Group 1-2; Group 3, Configuration 1; Group 4; Group 5, Configuration 2; Group 6, Configuration 2; Group 7-8, 10-14; Group 15, Configuration 2; Group 16; Group 17, Configuration 2; Group 18, Configuration 2; Group 19, Configuration 1; Group 20-22; Group 23, Configuration 2; Group 24-37: Make wiring changes to wire bundle W3851 and route wiring as given in Figure 16 and Figure 36. 28. Group 1-2; Group 3, Configuration 1; Group 4; Group 5, Configuration 2; Group 6, Configuration 2; Group 7-8, 10-14; Group 15, Configuration 2; Group 16; Group 17, Configuration 2; Group 18, Configuration 2; Group 19, Configuration 1; Group 20-22; Group 23, Configuration 2; Group 24-37: Make wiring changes to wire bundle W3851 and route wiring as given in Figure 17 and Figure 36. 29. Group 1-2; Group 3, Configuration 1; Group 4; Group 5, Configuration 2; Group 6, Configuration 2; Group 7-8, 10-14; Group 15, Configuration 2; Group 16; Group 17, Configuration 2; Group 18, Configuration 2; Group 19, Configuration 1; Group 20, 22; Group 23, Configuration 2; Group 24-25, 28, 32-36: Make wiring changes to wire bundle W3851 and route wiring as given in Figure 18 and Figure 36. 30. Group 21, 26-27, 29-31, 37: Make wiring changes to wire bundle W3851 and route wiring as given in Figure 42 and Figure 36. 31. Group 3, Configuration 1; Group 7, 20-22, 29: Make wiring changes to wire bundle W3851 and route wiring as given in Figure 19 and Figure 36. 32. Group 5, Configuration 2; Group 6, Configuration 2; Group 13; Group 23, Configuration 2; Group 24-28, 36: Make wiring changes to wire bundle W3851 and route wiring as given in Figure 43 and Figure 36. 33. Group 1-2, 4, 8, 10-12, 14; Group 15, Configuration 2; Group 16; Group 17, Configuration 2; Group 18, Configuration 2; Group 19, Configuration 1; Group 30-35, 37: Make wiring changes to wire bundle W3851 and route wiring as given in Figure 20 and Figure 36. 34. Group 1-2; Group 3, Configuration 1; Group 4; Group 5, Configuration 2; Group 6, Configuration 2; Group 7-8, 10-14; Group 15, Configuration 2; Group 16; Group 17, Configuration 2; Group 18, Configuration 2; Group 19, Configuration 1; Group 20-22; Group 23, Configuration 2; Group 24-37: Make wiring changes to wire bundle W3851 and route wiring as given in Figure 21 and Figure 36. 35. Group 1-2; Group 3, Configuration 1; Group 4; Group 5, Configuration 2; Group 6, Configuration 2; Group 7-8, 10-14; Group 15, Configuration 2; Group 16; Group 17, Configuration 2; Group 18, Configuration 2; Group 19, Configuration 1; Group 20-22; Group 23, Configuration 2; Group 24-37: Do the functional test.Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 62 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

a. Prepare for the test. (1) Obey these precautions at all times during these tests: (a) To operate any of the fuel pumps, you must be in the flight compartment to continuously monitor the fuel quantity and low pressure indication in the applicable tank. **WARNING:** DO NOT OPERATE A FUEL PUMP IF THE LOW PRESSURE INDICATION COMES ON AND STAYS ON. FUEL VAPORS IN THE TANK MAY IGNITE AND CAUSE A FIRE OR EXPLOSION. (b) Immediately set the applicable fuel pump switch to the OFF position if the low pressure indication light comes on and stays on. (2) Make sure that power is supplied to the airplane. Refer to 747-400 AMM 24-22-00 as an accepted procedure. (3) Make sure the airplane is in ground mode. Refer to 747-400 AMM 32-09-02 as an accepted procedure. (4) Make sure that the Computer Display Unit (CDU) is installed. Refer to 747-400 AMM 34-61-02 as an accepted procedure. (5) Make sure that the fuel jettison system is serviceable. (6) Make sure that the Integrated Display System (IDS) is serviceable. Refer to 747-400 AMM 31-61-00 as an accepted procedure. (7) Make sure that the Central Maintenance Computer (CMC) is serviceable. Refer to 747-400 AMM 45-10-00 as an accepted procedure. (8) Make sure that the Horizontal Stabilizer Tanks (HST) have the fuel quantities as follows: (a) Make sure there is 2,000 pounds (907 kilograms) or more of fuel in the HST. **NOTE:** This fuel will prevent dry operation of the jettison pumps. (b) If the quantity of fuel is not sufficient, refer to 747-400 AMM 12-11-01 as an accepted procedure. (9) Open the refueling station door. b. Do this test of the automatic pump shutoff for the Left HST Fuel Pump: (1) Make sure the following circuit breaker on the P85 panel is closed: **C/B Number Location Name** C03141 Horiz Stab Xfer/Jett Pump LeftOriginal Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 63 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

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

(3) Make sure the following circuit breaker on the P7 panel is closed:

(4) Open S1879 Switch "Horiz-Stab ISLN Con VLV" on P42. (5) Set the S14 L HSTAB Pump switch on the M154 panel to ON. (6) Verify L HSTAB fuel pump is running. (7) Open the following circuit breaker on the P85 panel:

(8) At the same time as you OPEN the circuit breaker C03141, start timing with a stopwatch. (9) Use an ohmmeter to verify, the relays R7401 and R1365 RLY-HSTAB Pump Cont Left (located on E8 shelf) are energized for more than 20 seconds. (10) Set the S14 L STAB pump switch on the M154 panel to OFF. (11) Close S1879 Switch "Horiz-Stab ISLN Con VLV" on P42. (12) Open the following circuit breakers on the P414 panel:

(13) Open the following circuit breaker on the P7 panel:

(14) Disconnect pin B1 from relay R7393 Rly-Jtsn Ovrd-Left on the P414. **C/B Number Location Name** C00090 F17 Fueling Valve C01142 F22 Fueling Pwr

**C/B Number Location Name** C10125 H25 HSTAB-L Refuel &Xfer Cont

**C/B Number Location Name** C03141 Horiz Stab Xfer/Jett Pump Left

**C/B Number Location Name** C00090 F17 Fueling Valve C01142 F22 Fueling Pwr

**C/B Number Location Name** C10125 H25 HSTAB-L Refuel &Xfer ContOriginal Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 64 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

(15) Close the following circuit breaker on the P85 panel:

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

(17) Close the following circuit breaker on the P7 panel:

(18) Open S1879 Switch "Horiz-Stab ISLN Con VLV" on the P42 panel. (19) Set the S14 L HSTAB Pump switch on the M154 panel to ON. (20) Verify L HSTAB fuel pump is running. (21) Open the following circuit breaker on the P85 panel:

(22) At the same time as you OPEN the circuit breaker C03141, start timing with a stopwatch. (23) Use an ohmmeter to verify, that after approximately 14 seconds, the relays R7401 and R1365 RLY-HSTAB Pump Cont Left Relay (located on E8 shelf) are de-energized. (24) Verify Left Pump Low Pressure light ILLUMINATED. (25) Set the S14 L STAB Pump switch on the M154 panel to OFF. (26) Verify Left Low Pressure light EXTINGUISHES. (27) Set the S14 L HSTAB Pump switch on the M154 panel to ON. (28) Use an ohmmeter to verify, the relays R7401 and R1365 RLY-HSTAB Pump Cont Left Relay (located on E8 shelf) are energized. (29) Use an ohmmeter to verify, that after approximately 14 seconds, the relays R7401 and R1365 RLY-HSTAB Pump Cont Left Relay (located on E8 shelf) are de-energized. **C/B Number Location Name** C03141 Horiz Stab Xfer/Jett Pump Left

**C/B Number Location Name** C00090 F17 Fueling Valve C01142 F22 Fueling Pwr

**C/B Number Location Name** C10125 H25 HSTAB-L Refuel &Xfer Cont

**C/B Number Location Name** C03141 Horiz Stab Xfer/Jett Pump LeftOriginal Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 65 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

(30) Set the S14 L STAB Pump switch on the M154 panel to OFF. (31) Open the following circuit breakers on the P414 panel:

(32) Open the following circuit breaker on the P7 panel:

(33) CLOSE S1879 Switch "Horiz-Stab ISLN Con VLV" on the P42 panel. (34) Reconnect pin B1 to relay R7393 Rly-Jtsn Ovrd-Left on the P414 panel. (35) CLOSE the following circuit breaker on the P85 panel:

(36) CLOSE the following circuit breakers on the P414 panel:

(37) CLOSE the following circuit breaker on the P7 panel:

(38) OPEN S1879 Switch "Horiz-Stab ISLN Con VLV" on the P42 panel. (39) Set the S14 L STAB Pump switch on the M154 panel to ON. (40) At the same time the S14 L STAB Pump switch on the M154 panel is CLOSED, start timing with a stopwatch. (41) Verify L HSTAB fuel pump is running more than 20 seconds. (42) Set the S14 L STAB Pump switch on the M154 panel to OFF. **C/B Number Location Name** C00090 F17 Fueling Valve C01142 F22 Fueling Pwr

**C/B Number Location Name** C10125 H25 HSTAB-L Refuel &Xfer Cont

**C/B Number Location Name** C03141 Horiz Stab Xfer/Jett Pump Left

**C/B Number Location Name** C00090 F17 Fueling Valve C01142 F22 Fueling Pwr

**C/B Number Location Name** C10125 H25 HSTAB-L Refuel &Xfer ContOriginal Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 66 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

(43) OPEN the following circuit breaker on the P7 panel:

(44) OPEN the following circuit breakers on the P414 panel:

(45) OPEN the following circuit breaker on the P85 panel:

(46) CLOSE S1879 Switch "Horiz-Stab ISLN Con VLV" on the P42 panel. c. Do this test of the Uncommanded On for the LEFT HST FUEL PUMP: **WARNING:** VERIFY S14 L STAB PUMP SWITCH ON THE P154 PANEL IS IN THE OFF POSITION BEFORE DOING THE UNCOMMANDED ON TEST. (1) Ground Pin 11 on relay R7401 RLY-HSTAB Pump Cont - Left relay. (2) Wait for a minimum of 60 seconds and check the Engine Indication and Crew Alerting System (EICAS) Status Message, the following message should be displayed on the EICAS Status "FUEL CMD STAB L". (3) Use an ohmmeter to measure the resistance between the pins A1 and A2, pins B1 and B2, pins C1 and C2 and pins to ground of relay R7401 and relay R1365 on the E8 shelf. Verify that the resistance value shows an OPEN circuit. (4) Remove the ground jumper at pin 11 on relay R7401 RLY-HSTAB Pump Cont - Left relay. d. Do this test of the automatic pump shutoff for the Right STAB Fuel Pump: (1) Make sure the following circuit breaker on the P85 panel is closed: **C/B Number Location Name** C10125 H25 HSTAB-L Refuel &Xfer Cont

**C/B Number Location Name** C00090 F17 Fueling Valve C01142 F22 Fueling Pwr

**C/B Number Location Name** C03141 Horiz Stab Xfer/Jett Pump Left

**C/B Number Location Name** C03142 Horiz Stab Xfer/Jett Pump RightOriginal Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 67 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

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

(3) Make sure the following circuit breaker on the P7 panel is closed:

(4) Open S1879 Switch "Horiz-Stab ISLN Con VLV" on the P42 panel. (5) Set the S15 R STAB Pump switch on the M154 panel to ON. (6) Verify R HSTAB fuel pump is running. (7) Open the following circuit breaker on the P85 panel:

(8) At the same time as you OPEN the circuit breaker C03142, start timing with a stopwatch. (9) Use an ohmmeter to verify, the relays R7402 and R1366 RLY-HSTAB Pump Cont Right (located on E8 shelf) are energized for more than 20 seconds. (10) Set the S15 R STAB pump switch on the M154 panel to OFF. (11) Close S1879 Switch "Horiz-Stab ISLN Con VLV" on the P42 panel. (12) Open the following circuit breakers on the P414 panel:

(13) Open the following circuit breaker on the P7 panel:

(14) Disconnect pin B1 from relay R7394 Rly-Jtsn Ovrd-Right on the P415. **C/B Number Location Name** C00090 F17 Fueling Valve C01142 F22 Fueling Pwr

**C/B Number Location Name** C10126 H26 HSTAB-R Refuel & Xfer Cont

**C/B Number Location Name** C03142 Horiz Stab Xfer/Jett Pump Right

**C/B Number Location Name** C00090 F17 Fueling Valve C01142 F22 Fueling Pwr

**C/B Number Location Name** C10126 H26 HSTAB-R Refuel & Xfer ContOriginal Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 68 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

(15) Close the following circuit breaker on the P85 panel:

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

(17) Close the following circuit breaker on the P7 panel:

(18) Open S1879 Switch "Horiz-Stab ISLN Con VLV" on the P42 panel. (19) Set the S15 R STAB Pump switch on the M154 panel to ON. (20) Verify R HSTAB fuel pump is running. (21) Open the following circuit breaker on the P85 panel:

(22) At the same time as you OPEN the circuit breaker C03142, start timing with a stopwatch. (23) Use an ohmmeter to verify, that after approximately 14 seconds, the relays R7402 and R1366 RLY-HSTAB Pump Cont Right Relay (located on E8 shelf) are de-energized. (24) Verify Right Pump Low Pressure light ILLUMINATED. (25) Set the S15 R STAB Pump switch on the M154 panel to OFF. (26) Verify Right Low Pressure light EXTINGUISHES. (27) Set the S15 R STAB Pump switch on the M154 panel to ON. (28) Use an ohmmeter to verify, the relays R7402 and R1366 RLY-HSTAB Pump Cont Right Relay (located on E8 shelf) are energized. (29) Use an ohmmeter to verify, that after approximately 14 seconds, the relays R7402 and R1366 RLY-HSTAB Pump Cont Right Relay (located on E8 shelf) are de-energized. **C/B Number Location Name** C03142 Horiz Stab Xfer/Jett Pump Right

**C/B Number Location Name** C00090 F17 Fueling Valve C01142 F22 Fueling Pwr

**C/B Number Location Name** C10126 H26 HSTAB-R Refuel & Xfer Cont

**C/B Number Location Name** C03142 Horiz Stab Xfer/Jett Pump RightOriginal Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 69 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

(30) Set the S15 R STAB Pump switch on the M154 panel to OFF. (31) Open the following circuit breakers on the P414 panel:

(32) Open the following circuit breaker on the P7 panel:

(33) CLOSE S1879 Switch "Horiz-Stab ISLN Con VLV" on the P42 panel. (34) Reconnect pin B1 to relay R7394 Rly-Jtsn Ovrd-Right on the P415 panel. (35) CLOSE the following circuit breaker on the P85 panel:

(36) CLOSE the following circuit breakers on the P414 panel:

(37) CLOSE the following circuit breaker on the P7 panel:

(38) OPEN S1879 Switch "Horiz-Stab ISLN Con VLV" on the P42 panel. (39) Set the S15 R STAB Pump switch on the M154 panel to ON. (40) At the same time the S15 R STAB Pump switch on the M154 Panel is CLOSED, start timing with a stopwatch. (41) Verify R HSTAB fuel pump is running more than 20 seconds. (42) Set the S15 R STAB Pump switch on the M154 panel to OFF. **C/B Number Location Name** C00090 F17 Fueling Valve C01142 F22 Fueling Pwr

**C/B Number Location Name** C10126 H26 HSTAB-R Refuel & Xfer Cont

**C/B Number Location Name** C03142 Horiz Stab Xfer/Jett Pump Right

**C/B Number Location Name** C00090 F17 Fueling Valve C01142 F22 Fueling Pwr

**C/B Number Location Name** C10126 H26 HSTAB-R Refuel & Xfer ContOriginal Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 70 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

(43) OPEN the following circuit breaker on the P7 panel:

(44) OPEN the following circuit breakers on the P414 panel:

(45) OPEN the following circuit breaker on the P85 panel:

(46) CLOSE S1879 Switch "Horiz-Stab ISLN Con VLV" on the P42 panel. e. Do this test of the Uncommanded On for the RIGHT HST FUEL PUMP: **WARNING:** VERIFY S15 R STAB PUMP SWITCH ON THE P154 PANEL IS IN THE OFF POSITION BEFORE DOING THE UNCOMMANDED ON TEST. (1) Ground Pin 11 on relay R7402 RLY-HSTAB Pump Cont - Right relay. (2) Wait for a minimum of 60 seconds and check the EICAS Status Message, the following message should be displayed on the EICAS Status "FUEL CMD STAB R". (3) Use an ohmmeter to measure the resistance between the pins A1 and A2, pins B1 and B2, pins C1 and C2 and pins to ground of relay R7402 and relay R1366 on the E8 shelf. Verify that the resistance value shows an OPEN circuit. (4) Remove the ground jumper at pin 11 on relay R7402 RLY-HSTAB Pump Cont - Right relay. (5) Clear the following EICAS Status Messages using the CMC: — "FUEL CMD STAB L" — "FUEL CMD STAB R" (6) After 60 seconds, verfiy the following messages are NOT displayed on the EICAS Status: — "FUEL CMD STAB L" — "FUEL CMD STAB R" 36. CLOSE Fueling Station Door. 37. Close access to the main equipment center. 38. Put the airplane back to a serviceable condition. **C/B Number Location Name** C10126 H26 HSTAB-R Refuel & Xfer Cont

**C/B Number Location Name** C00090 F17 Fueling Valve C01142 F22 Fueling Pwr

**C/B Number Location Name** C03142 Horiz Stab Xfer/Jett Pump RightOriginal Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 71 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

**Group 9: Airplanes** 1. Gain access to the rework area as follows: **NOTE:** Operators should check their applicable wiring configurations to determine how much access will be required. a. If the airplane has a crew rest located over door 5 remove the sidewall partitions as necessary for access to the E-8 shelf and wire bundle routing, refer to 747-400 AMM 25-76-02 as an accepted procedure. b. If the airplane has no crew rest located over door 5 remove the ceiling and lower side wall linings (station 2320 to 2300) as necessary for access to E-8 shelf and wire bundle routing, refer to 747-400 AMM 25-21-01 and 747-400 AMM 25-22-01 as accepted procedures. c. Remove the ceiling panels in the passenger compartment (station 2310 to station 2100 and some airplanes to station 1980) as necessary for access to the outer portion of the sidewall where required for routing of ships wire bundles, refer to 747-400 AMM 25-22-01 as an accepted procedure. d. Remove the ceiling panels in the rear cargo compartment (station 2100 or station 1980 to station 1480 as necessary for access to the cargo compartment ceiling where required for routing of ships wire bundles, refer to 747-400 AMM 25-52-01 as an accepted procedure. e. Remove the floor panels on the main deck (station 1480 to station 980) as necessary for access to the wire bundles that route between the forward cargo compartment and the aft cargo compartment, refer to 747-400 AMM 53-21-02 as an accepted procedure. Some airplanes may have the wire bundle routed in a conduit and removal of the floor panels may not be required. f. Remove cargo ceiling linings in the forward cargo compartment (station 980 to station 400) as necessary to access the wire bundles that route in the forward cargo compartment ceiling and to the main equipment bay, refer to 747-400 AMM 25-52-01 as an accepted procedure. 2. Remove electrical power from the airplane, refer to 747-400 AMM 24-22-00 as an accepted procedure. 3. Install new relays on the E-8 shelf as given in Figure 22. 4. Make wiring changes using the routing shown, refer to Figure 23 for wire bundles W4488 and W4588 and for wire bundle W3851, refer to Figure 34. 5. Make wiring changes to wire bundle W4488 as given in Figure 24 and Figure 23. 6. Make wiring changes to wire bundle W4588 as given in Figure 25 and Figure 23. 7. Make wiring changes to wire bundle W3845 as given in Figure 26. 8. Make wiring changes to wire bundle W4758 and route wiring as given in Figure 27 and Figure 35. 9. Make wiring changes to wire bundle W3851 and route wiring as given in Figure 28 and Figure 34. 10. Make wiring changes to wire bundle W3851 and route wiring as given in Figure 29 and Figure 34.Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 72 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

11. Make wiring changes to wire bundle W3851 and route wiring as given in Figure 30 and Figure 34. 12. Make wiring changes to wire bundle W3851 and route wiring as given in Figure 31 and Figure 34. 13. Make wiring changes to wire bundle W3851 and route wiring as given in Figure 32 and Figure 34. 14. Make wiring changes to wire bundle W3851 and route wiring as given in Figure 33 and Figure 34. 15. Group 9: Do the functional test. a. Prepare for the test. (1) Obey these precautions at all times during these tests: (a) To operate any of the fuel pumps, you must be in the flight compartment to continuously monitor the fuel quantity and low pressure indication in the applicable tank. **WARNING:** DO NOT OPERATE A FUEL PUMP IF THE LOW PRESSURE INDICATION COMES ON AND STAYS ON. FUEL VAPORS IN THE TANK MAY IGNITE AND CAUSE A FIRE OR EXPLOSION. (b) Immediately set the applicable fuel pump switch to the OFF position if the low pressure indication light comes on and stays on. (2) Make sure that power is supplied to the airplane. Refer to 747-400 AMM 24-22-00 as an accepted procedure. (3) Make sure the airplane is in ground mode. Refer to 747-400 AMM 32-09-02 as an accepted procedure. (4) Make sure that the CDU is installed. Refer to 747-400 AMM 34-61-02 as an accepted procedure. (5) Make sure that the fuel jettison system is serviceable. (6) Make sure that the Integrated Display System (IDS) is serviceable. Refer to 747-400 AMM 31-61-00 as an accepted procedure. (7) Make sure that the Central Maintenance Computer (CMC) is serviceable. Refer to 747-400 AMM 45-10-00 as an accepted procedure. (8) Make sure that the Horizontal Stabilizer Tanks (HST) have the fuel quantities as follows: (a) Make sure there is 2,000 pounds (907 kilograms) or more of fuel in the HST. **NOTE:** This fuel will prevent dry operation of the jettison pumps. (b) If the quantity of fuel is not sufficient, refer to 747-400 AMM 12-11-01 as an accepted procedure. (9) Open the refueling station door.Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 73 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

b. Do this test of the automatic pump shutoff for the Left HST Fuel Pump: (1) Make sure the following circuit breaker on the P85 panel is closed:

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

(3) Make sure the following circuit breaker on the P7 panel is closed:

(4) Open S1879 Switch "Horiz-Stab ISLN Con VLV" P42. (5) Set the S14 L STAB Pump switch on the M154 panel to ON. (6) Verify L HSTAB fuel pump is running. (7) Open the following circuit breaker on the P85 panel:

(8) At the same time as you OPEN the circuit breaker C03141, start timing with a stopwatch. (9) Use an ohmmeter to verify, the relays R7401 and R1365 RLY-HSTAB Pump Cont Left (located on E8 shelf) are energized for more than 20 seconds. (10) Set the S14 L STAB pump switch on the M154 panel to OFF. (11) Close S1879 Switch Horiz-Stab ISLN Con VLV P42. (12) Open the following circuit breakers on the P414 panel: **C/B Number Location Name** C03141 Horiz Stab Xfer/Jett Pump Left

**C/B Number Location Name** C00090 F17 Fueling Valve C01142 F22 Fueling Pwr

**C/B Number Location Name** C10125 H25 HSTAB-L Refuel & Xfer Cont

**C/B Number Location Name** C03141 Horiz Stab Xfer/Jett Pump Left

**C/B Number Location Name** C00090 F17 Fueling Valve C01142 F22 Fueling PwrOriginal Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 74 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

(13) Open the following circuit breaker on the P7 panel:

(14) Disconnect pin B1 from relay R7393 Rly-Jtsn Ovrd-Left on the P414. (15) Close the following circuit breaker on the P85 panel:

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

(17) Close the following circuit breaker on the P7 panel:

(18) Open S1879 Switch "Horiz-Stab ISLN Con VLV" on the P42 panel. (19) Set the S14 L STAB Pump switch on the M154 panel to ON. (20) Verify L HSTAB fuel pump is running. (21) Open the following circuit breaker on the P85 panel:

(22) At the same time as you OPEN the circuit breaker C03141, start timing with a stopwatch. (23) Use an ohmmeter to verify, that after approximately 14 seconds, the relays R7401 and R1365 RLY-HSTAB Pump Cont Left Relay (located on E8 shelf) are de-energized. (24) Verify Left Pump Low Pressure light ILLUMINATED. (25) Set the S14 L STAB Pump switch on the M154 panel to OFF. (26) Verify Left Low Pressure light EXTINGUISHES. **C/B Number Location Name** C10125 H25 HSTAB-L Refuel & Xfer Cont

**C/B Number Location Name** C03141 Horiz Stab Xfer/Jett Pump Left

**C/B Number Location Name** C00090 F17 Fueling Valve C01142 F22 Fueling Pwr

**C/B Number Location Name** C10125 H25 HSTAB-L Refuel & Xfer Cont

**C/B Number Location Name** C03141 Horiz Stab Xfer/Jett Pump LeftOriginal Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 75 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

(27) Set the S14 L STAB Pump switch on the M154 panel to ON. (28) Use an ohmmeter to verify, the relays R7401 and R1365 RLY-HSTAB Pump Cont Left Relay (located on E8 shelf) are energized. (29) Use an ohmmeter to verify, that after approximately 14 seconds, the relays R7401 and R1365 RLY-HSTAB Pump Cont Left Relay (located on E8 shelf) are de-energized. (30) Set the S14 L STAB Pump switch on the M154 panel to OFF. (31) Open the following circuit breakers on the P414 panel:

(32) Open the following circuit breaker on the P7 panel:

(33) CLOSE S1879 Switch "Horiz-Stab ISLN Con VLV" on the P42 panel. (34) Reconnect pin B1 to relay R7393 Rly-Jtsn Ovrd-Left on the P414 panel. (35) CLOSE the following circuit breaker on the P85 panel:

(36) CLOSE the following circuit breakers on the P414 panel:

(37) CLOSE the following circuit breaker on the P7 panel:

(38) OPEN S1879 Switch "Horiz-Stab ISLN Con VLV" on the P42 panel. (39) Set the S14 L STAB Pump switch on the M154 panel to ON. **C/B Number Location Name** C00090 F17 Fueling Valve C01142 F22 Fueling Pwr

**C/B Number Location Name** C10125 H25 HSTAB-L Refuel & Xfer Cont

**C/B Number Location Name** C03141 Horiz Stab Xfer/Jett Pump Left

**C/B Number Location Name** C00090 F17 Fueling Valve C01142 F22 Fueling Pwr

**C/B Number Location Name** C10125 H25 HSTAB-L Refuel & Xfer ContOriginal Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 76 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

(40) At the same time the S14 L STAB Pump switch on the M154 panel is CLOSED, start timing with a stopwatch. (41) Verify L HSTAB fuel pump is running more than 20 seconds. (42) Set the S14 L STAB Pump switch on the M154 panel to OFF. (43) OPEN the following circuit breaker on the P7 panel:

(44) OPEN the following circuit breakers on the P414 panel:

(45) OPEN the following circuit breaker on the P85 panel:

(46) CLOSE S1879 Switch Horiz-Stab ISLN Con VLV on the P42 panel. c. Do this test of the Uncommanded On for the LEFT HST FUEL PUMP: **WARNING:** VERIFY S14 L STAB PUMP SWITCH ON THE P154 PANEL IS IN THE OFF POSITION BEFORE DOING THE UNCOMMANDED ON TEST. (1) Ground Pin 11 on relay R7401 RLY-HSTAB Pump Cont - Left relay. (2) Wait for a minimum of 60 seconds and check the EICAS Status Message, the following message should be displayed on the EICAS Status "FUEL CMD STAB L". (3) Use an ohmmeter to measure the resistance between the pins A1 and A2, pins B1 and B2, pins C1 and C2 and pins to ground of relay R7401 and relay R1365 on the E8 shelf. Verify that the resistance value shows an OPEN circuit. (4) Remove the ground jumper at pin 11 on relay R7401 RLY-HSTAB Pump Cont - Left relay. d. Do this test of the automatic pump shutoff for the Right STAB Fuel Pump: **C/B Number Location Name** C10125 H25 HSTAB-L Refuel & Xfer Cont

**C/B Number Location Name** C00090 F17 Fueling Valve C01142 F22 Fueling Pwr

**C/B Number Location Name** C03141 Horiz Stab Xfer/Jett Pump LeftOriginal Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 77 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

(1) Make sure the following circuit breaker on the P85 panel is closed:

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

(3) Make sure the following circuit breaker on the P7 panel is closed:

(4) Open S1879 Switch "Horiz-Stab ISLN Con VLV" on the P42 panel. (5) Set the S15 R STAB Pump switch on the M154 panel to ON. (6) Verify R HSTAB fuel pump is running. (7) Open the following circuit breaker on the P85 panel:

(8) At the same time as you OPEN the circuit breaker C03142, start timing with a stopwatch. (9) Use an ohmmeter to verify, the relays R7402 and R1366 RLY-HSTAB Pump Cont Right (located on E8 shelf) are energized for more than 20 seconds. (10) Set the S15 R STAB pump switch on the M154 panel to OFF. (11) Close S1879 Switch "Horiz-Stab ISLN Con VLV" on the P42 panel. (12) Open the following circuit breakers on the P414 panel: **C/B Number Location Name** C03142 Horiz Stab Xfer/Jett Pump Right

**C/B Number Location Name** C00090 F17 Fueling Valve C01142 F22 Fueling Pwr

**C/B Number Location Name** C10126 H26 HSTAB-R Refuel & Xfer Cont

**C/B Number Location Name** C03142 Horiz Stab Xfer/Jett Pump Right

**C/B Number Location Name** C00090 F17 Fueling Valve C01142 F22 Fueling PwrOriginal Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 78 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

(13) Open the following circuit breaker on the P7 panel:

(14) Disconnect pin B1 from relay R7394 Rly-Jtsn Ovrd-Right on the P415. (15) Close the following circuit breaker on the P85 panel:

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

(17) Close the following circuit breaker on the P7 panel:

(18) Open S1879 Switch "Horiz-Stab ISLN Con VLV" on the P42 panel. (19) Set the S15 R STAB Pump switch on the M154 panel to ON. (20) Verify R HSTAB fuel pump is running. (21) Open the following circuit breaker on the P85 panel:

(22) At the same time as you OPEN the circuit breaker C03142, start timing with a stopwatch. (23) Use an ohmmeter to verify, that after approximately 14 seconds, the relays R7402 and R1366 RLY-HSTAB Pump Cont Right Relay (located on E8 shelf) are de-energized. (24) Verify Right Pump Low Pressure light ILLUMINATED. (25) Set the S15 R STAB Pump switch on the M154 panel to OFF. (26) Verify Right Low Pressure light EXTINGUISHES. **C/B Number Location Name** C10126 H26 HSTAB-R Refuel & Xfer Cont

**C/B Number Location Name** C03142 Horiz Stab Xfer/Jett Pump Right

**C/B Number Location Name** C00090 F17 Fueling Valve C01142 F22 Fueling Pwr

**C/B Number Location Name** C10126 H26 HSTAB-R Refuel & Xfer Cont

**C/B Number Location Name** C03142 Horiz Stab Xfer/Jett Pump RightOriginal Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 79 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

(27) Set the S15 R STAB Pump switch on the M154 panel to ON. (28) Use an ohmmeter to verify, the relays R7402 and R1366 RLY-HSTAB Pump Cont Right Relay (located on E8 shelf) are energized. (29) Use an ohmmeter to verify, that after approximately 14 seconds, the relays R7402 and R1366 RLY-HSTAB Pump Cont Right Relay (located on E8 shelf) are de-energized. (30) Set the S15 R STAB Pump switch on the M154 panel to OFF. (31) Open the following circuit breakers on the P414 panel:

(32) Open the following circuit breaker on the P7 panel:

(33) CLOSE S1879 Switch "Horiz-Stab ISLN Con VLV" on the P42 panel. (34) Reconnect pin B1 to relay R7394 Rly-Jtsn Ovrd-Right on the P415 panel. (35) CLOSE the following circuit breaker on the P85 panel:

(36) CLOSE the following circuit breakers on the P414 panel:

(37) CLOSE the following circuit breaker on the P7 panel:

(38) OPEN S1879 Switch "Horiz-Stab ISLN Con VLV" on the P42 panel. (39) Set the S15 R STAB Pump switch on the M154 panel to ON. **C/B Number Location Name** C00090 F17 Fueling Valve C01142 F22 Fueling Pwr

**C/B Number Location Name** C10126 H26 HSTAB-R Refuel & Xfer Cont

**C/B Number Location Name** C03142 Horiz Stab Xfer/Jett Pump Right

**C/B Number Location Name** C00090 F17 Fueling Valve C01142 F22 Fueling Pwr

**C/B Number Location Name** C10126 H26 HSTAB-R Refuel & Xfer ContOriginal Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 80 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

(40) At the same time the S15 R STAB Pump switch on the M154 panel is CLOSED, start timing with a stopwatch. (41) Verify R HSTAB fuel pump is running more than 20 seconds. (42) Set the S15 R STAB Pump switch on the M154 panel to OFF. (43) OPEN the following circuit breaker on the P7 panel:

(44) OPEN the following circuit breakers on the P414 panel:

(45) OPEN the following circuit breaker on the P85 panel:

(46) CLOSE S1879 Switch "Horiz-Stab ISLN Con VLV" on the P42 panel. e. Do this test of the Uncommanded On for the RIGHT HST FUEL PUMP: **WARNING:** VERIFY S15 R STAB PUMP SWITCH ON THE P154 PANEL IS IN THE OFF POSITION BEFORE DOING THE UNCOMMANDED ON TEST. (1) Ground Pin 11 on relay R7402 RLY-HSTAB Pump Cont - Right relay. (2) Wait for a minimum of 60 seconds and check the EICAS Status Message, the following message should be displayed on the EICAS Status "FUEL CMD STAB R". (3) Use an ohmmeter to measure the resistance between the pins A1 and A2, pins B1 and B2, pins C1 and C2 and pins to ground of relay R7402 and relay R1366 on the E8 shelf. Verify that the resistance value shows an OPEN circuit. (4) Remove the ground jumper at pin 11 on relay R7402 RLY-HSTAB Pump Cont - Right relay. (5) Clear the following EICAS Status Messages using the CMC: — "FUEL CMD STAB L" — "FUEL CMD STAB R" (6) After 60 seconds, verfiy the following messages are NOT displayed on the EICAS Status: — "FUEL CMD STAB L" **C/B Number Location Name** C10126 H26 HSTAB-R Refuel & Xfer Cont

**C/B Number Location Name** C00090 F17 Fueling Valve C01142 F22 Fueling Pwr

**C/B Number Location Name** C03142 Horiz Stab Xfer/Jett Pump RightOriginal Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 81 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

— "FUEL CMD STAB R" 16. CLOSE Fueling Station Door. 17. CLOSE access to the main equipment center. 18. Put the airplane back to a serviceable condition.**FIGURE 1: INSTALL RELAYS ON E-8 SHELF** Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 82 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

**FIGURE 1: INSTALL RELAYS ON E-8 SHELF**

UP FWD
INBD AFT E/E EQUIPMENT CENTER ENTRY DOOR NO. 5L MAIN E8 RACK

AFT EQUIPMENT

CENTER - E8 STA 2302.94

STA 2302.94 FOR ALTERNATE CONFIGURATION FWD INBD

1 2

19 18 SEE A SEE F1324636

**(SHEET 1 OF 10) FIGURE 1: INSTALL RELAYS ON E-8 SHELF**  Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 83 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

UP FWD
INBD

AFT EQUIPMENT

CENTER - E8 STA 2302.94 RELAYS SHOWN INSTALLED



### A B SEE E THROUGH1325448

**(SHEET 2 OF 10) FIGURE 1: INSTALL RELAYS ON E-8 SHELF**  Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 84 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

RELAY INSTALLATION

FWD 

### B UP FWD
INBD



### C 7

5

4 3

5 7

3 6 13 12

111325453

**(SHEET 3 OF 10) FIGURE 1: INSTALL RELAYS ON E-8 SHELF**  Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 85 of 182 

### BOEING SERVICE BULLETIN 747-28A2281R1365

4 LOCATIONSR1366 FWD

FWD INBD OUTBD



### D

E 16 14

9

8 8

15 13 12

13 12 14

10 10 171345377

**(SHEET 4 OF 10) FIGURE 1: INSTALL RELAYS ON E-8 SHELF**  Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 86 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

UP FWD
INBD

AFT EQUIPMENT

CENTER - E8 (ALTERNATE CONFIGURATION) STA 2302.94 RELAYS SHOWN INSTALLED



### F G SEE J THROUGH1702058

**(SHEET 5 OF 10) FIGURE 1: INSTALL RELAYS ON E-8 SHELF**  Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 87 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

RELAY INSTALLATION

FWD 

### G UP FWD
INBD



### H 7

5

4 3

5 7

3 6 13 12

111702060

**(SHEET 6 OF 10) FIGURE 1: INSTALL RELAYS ON E-8 SHELF**  Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 88 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

This Figure applies to Group 1-2; Group 3, Configuration 1; Group 4; Group 5, Configuration 2; Group 6, Configuration 2; Group 7-8, 10-14; Group 15, Configuration 2; Group 16; Group 17, Configuration 2; Group 18, Configuration 2; Group 19, Configuration 1; Group 20-22; Group 23, Configuration 2; Group 24-37:R1365

4 LOCATIONSR1366 FWD

FWD INBD OUTBD



### I

J 16 14

9

8 8

15 13 12

13 12 14

10 10 171702063

**(SHEET 7 OF 10) FIGURE 1: INSTALL RELAYS ON E-8 SHELF**  Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 89 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

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 relay installation on the E-8 shelf. Use the parts in Top Kit 015U1808-1.

**STEP TASK NAME IDENTIFICATION QTY MORE DATA** 1 Open E-8 SHELF - - Gain access to the E-8 shelf. 2 Remove/Keep Static Inverter - - Refer to 747-400 AMM 24-29-04 as an accepted procedure, if Static Inverter is installed. 3 Install (New) RELAY BRACKET DETAIL 284U4011-45 1 Prepare and apply faying surface bond between the bottom surface of the bracket and the tray, refer to SWPM 20-20-00 as an accepted procedure. Install (New) BOLT BACS12HN06-7 1 If the bolt can not be installed because of a stiffening joggle in the equipment tray see Note (e). 4 Install (New) BONDING JUMPER BACJ40A20-2 1 Prepare surfaces for bonding jumper. Refer to SWPM 20-20-00 as an accepted procedure. Install (New) SCREW, CAP BACS12GU3K9 1 Install (New) WASHER NAS1149D0316H 4 Install washers in build up as shown. Install (New) NUT BACN10YR3CD 1 5 Install (New) SCREW BACS12HN3-36 1 Install clamps in location, do no tighten until after wiring is installed. Install (New) WASHER NAS1149D0332J 2 Install (New) CLAMP, LOOP BACC10GE5 2 Refer to SWPM 20-10-12 as an accepted procedure for clamp installation. Install (New) SPACERS FOR RIVETS NAS42DD6-64FC 2 Install (New) NUT BACN10YR3CD 1 6 Install (New) SCREW BACS12GU3K10 1 Back drill hole. Hole diameter 0.187 - 0.191 inch, refer to 747-400 SRM 51-40-05 as an accepted procedure. Install (New) WASHER NAS1149D0316H 1 Install (New) NUT BACN10YR3CD 1

**(SHEET 8 OF 10) FIGURE 1: INSTALL RELAYS ON E-8 SHELF**  Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 90 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

7 Prepare FAY SURFACE BOND - - Prepare surfaces on both sides of bracket. Use Cleaning Method Type I. Refer to SWPM 20-20-00 as an accepted procedure. 8 Install (New) RELAY,25A,W/ AUX BH315 2 9 Install (New) SCREW BACS12GU3K8 4 Install at four locations Install (New) WASHER NAS1149D0332J 4 Install on near side. Install (New) WASHER NAS1149D0316H 4 Install on far side. Install (New) NUT BACN10YR3CD 4 10 Measure RESISTANCE - - (a), (b) 11 Measure RESISTANCE - - (c), (d) 12 Apply SEALANT BMS 5-95 1 Fillet seal all sides of relays and between bracket and tray, refer to 747-400 AMM 51-31-01 as an accepted procedure. 13 Apply PRIMER BMS 10-11, TYPE 1 - Touch-up all bare metal surfaces and top coat to match area color. 14 Install (New) TERMINAL BARR 001-1908-000 4 Install terminal barrier be wire installation. 15 Install (New) VINYL MARKER BAC27EEL29698 1 For Vinyl Marker installation, Refer to 747-400 AMM 20-11-16 as an accepted procedure. 16 Install (New) VINYL MARKER BAC27EEL29699 1 For Vinyl Marker installation, Refer to 747-400 AMM 20-11-16 as an accepted procedure. 17 Install (New) MARKER BAC27EEL19431 1 For Vinyl Marker installation, Refer to 747-400 AMM 20-11-16 as an accepted procedure. 18 Install (Kept) Static Inverter 1 Do not install static inverter until wiring is completed. Install Static Inverter, (if static inverter was removed) refer to 747-400 AMM 24-29-04 as an accepted procedure. 19 Close E-8 SHELF - Do not close shelf doors until wiring is complete. (a) Use Bonding Meter. Refer to SWPM 20-20-00 Procedure “Bonding Test for Faying Surfaces” as an accepted procedure. Maximum resistance between relay mount and structure, 0.0025 Ohms. **STEP TASK NAME IDENTIFICATION QTY MORE DATA**

**(SHEET 9 OF 10) FIGURE 1: INSTALL RELAYS ON E-8 SHELF**  Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 91 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

The parts shown in the table below are provided as extra parts for this figure.

(b) If maximum resistance is exceeded, disassemble relay assembly and reassemble making sure both relay mounting surface and structure assembly are clean. Refer to SWPM 20-20-00. (c) Use Bonding Meter. Refer to SWPM 20-20-00 Procedure “Bonding Test for Faying Surfaces” as an accepted procedure. Maximum resistance between mounting bracket and structure, 0.003 Ohms. (d) If maximum resistance is exceeded, disassemble bonding jumper assembly and reassemble bonding jumper making sure mounting surfaces are clean. Refer to SWPM 20-20-00 as an accepted procedure. (e) The existing hole location in the bracket for the bolt may interfere with a stiffening joggle in the equipment tray. If this condition exists move the mounting hole in the bracket 1 inch outboard from the center of the existing hole and plug existing hole in the bracket. Drill new hole 0.138 - 0.142 inch diameter to install the bolt shown Circle Note 3 using additional hardware, washer NAS1149DN616H or equivalent and nut BACN10YR06CD or equivalent.

**NAME IDENTIFICATION QTY MORE DATA** Nut BACN10YR3CD 1 Bolt BACS12GU3K10 3 Washer NAS1149D0316H 1 Washer NAS1149D0332J 4 **STEP TASK NAME IDENTIFICATION QTY MORE DATA**

**(SHEET 10 OF 10) FIGURE 2: WIRE BUNDLE ROUTING INFORMATION**  Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 92 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

**FIGURE 2: WIRE BUNDLE ROUTING INFORMATION**

STA 1580 STA 2200 2100 STA
STA 1980 AC1401

W4588 W4488

B SEE 2 A SEE

11325695

**(SHEET 1 OF 4) FIGURE 2: WIRE B**  **UNDLE ROUTING INFORMATION** Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 93 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

ENTRY DOOR NO. 5L MAIN

E8 RACK STA 2340 STA 2320 STA 2300 S-10L S-11L
S-12L
S-13L

W4488

P180 PANEL STA 380 FLOOR BEAM MAWEA CARDFILE

W4588 W4758

FWD FWD INBD 

### A 1

2



### B SEE C

31325765

**(SHEET 2 OF 4) FIGURE 2: WIRE BUNDLE ROUTING INFORMATION**  Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 94 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

This Figure applies to Group 1-2; Group 3, Configuration 1; Group 4; Group 5, Configuration 2; Group 6, Configuration 2; Group 7-8, 10-14; Group 15, Configuration 2; Group 16; Group 17, Configuration 2; Group 18, 

### AP2301

D40103P (POSITION 15) STA 2300 STA 2320

W4488

FWD UP



### C 11325848

**(SHEET 3 OF 4) FIGURE 2: WIRE B**  **UNDLE ROUTING INFORMATION** Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 95 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

Configuration 2; Group 19, Configuration 1; Group 20-22; Group 23, Configuration 2; Group 24-37: The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The information shown is wire bundle routing for wire bundles W4488, W4455 and used existing wires for wire bundle W4758. Install wires. Refer to SWPM 20-10-11 and SWPM 20-10-19 as accepted procedures. For wiring changes see applicable figures. **STEP TASK NAME IDENTIFICATION QTY MORE DATA** 1 INSTALL WIRE BUNDLE W4488 - - Follow existing wire bundle W4488 routing from E-8 shelf, disconnect location AP2301 to disconnect location AC1401. 2 INSTALL WIRE BUNDLE W4588 - - Follow existing wire bundle W4588 routing from disconnect location AC1401 to P180 Panel disconnect location AE0304. 3 INSTALL WIRE BUNDLE W4758 - - Use existing wire bundle wiring for W4758 routed from P180 Panel to MAWEA card file.

**(SHEET 4 OF 4) FIGURE 3: REWORK / INSTALL NEW WIRING (WIRE BUNDLE W4488)**  Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 96 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

**FIGURE 3: REWORK / INSTALL NEW WIRING (WIRE BUNDLE W4488)**

This Figure applies to Group 1, 8, 10-12; Group 18, Configuration 2; Group 19, Configuration 1; Group 32, 34- 35: 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 289U1225-101. Route new wiring following the existing wire bundle routing, refer to SWPM 20-10-11 and SWPM 20-10-19. Use lacing tape as necessary.

**FLAG NOTE NAME IDENTIFICATION QTY MORE DATA**  1 ASSY -101 (W4488) 289U1225-101W 1 Refer to SWPM 20-10-11 as an accepted procedure. 2 CONTACT, PIN BACC47CN1S 2 Refer to SWPM 20-61-11 an accepted procedure. 3 CONTACT, SOCKET BACC47CP1S 2 Refer to SWPM 20-61-11 as an accepted procedure. 4 INSULATION SLEEVING, HEAT SHRINKABLE, POLYOLEFIN, FLEXIBLE, X-LI M23053/5-107-4 1 Refer to SWPM 20-10-11 as an accepted procedure.

5 LACING TAPE 289T9001-21 1 Refer to SWPM 20-10-11 as an accepted procedure. 

### 071-22 W3851

-106

CENTER - AFT LEFT 47 D43827P (POS 10) W4488- 35

AP2301

D40103P (POS 15) 37 J EQUIPMENT E8 W4588 -102

085-20 W4488- W4588 -102 084-20 46
W4588 (REF) 31 (2 LOCATIONS)
(2 LOCATIONS)

J AC1401 2

3

4 1 5

REFERENCE: 747 WIRING DIAGRAM 28-42-15
ADDED WIRE OR NEW ROUTING

EXISTING WIRE DELETED WIRE OR FORMER ROUTING1326169

**(SHEET 1 OF 1) FIGURE 4: REWORK / INSTALL NEW WIRING (WIRE BUNDLE W4488)**  Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 97 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

**FIGURE 4: REWORK / INSTALL NEW WIRING (WIRE BUNDLE W4488)**

This Figure applies to Group 7: 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 289U1225-101. Route new wiring following the existing wire bundle routing, refer to SWPM 20-10-11 and SWPM 20-10-19 as an accepted procedure. Use lacing tape as necessary, see kit of parts for Figure 3 for lacing tape.

**FLAG NOTE NAME IDENTIFICATION QTY MORE DATA**  1 ASSY -101 (W4488) 289U1225-101W 1 Refer to SWPM 20-10-11 as an accepted procedure. 2 CONTACT, PIN BACC47CN1S 2 Refer to SWPM 20-61-11 as an accepted procedure. 3 CONTACT, SOCKET BACC47CP1S 2 Refer to SWPM 20-61-11 as an accepted procedure. 4 INSULATION SLEEVING, HEAT SHRINKABLE, POLYOLEFIN, FLEXIBLE, X-LI M23053/5-107-4 2 Refer to SWPM 20-10-11 as an accepted procedure.

5 LACING TAPE 289T9001-21 1 Refer to SWPM 20-10-11 as an accepted procedure. 1 5

004-20 W3851

-106

CENTER - AFT LEFT 47 D43827P (POS 10) W4488- 30

AP2301

D40103P (POS 15) 37 J EQUIPMENT E8 W4588 -102

085-20 W4488- W4588 -102 084-20 46

W4588 (REF) 33 (2 LOCATIONS)
(2 LOCATIONS)

J AC1401 2

3

4 071-22 31

REFERENCE: 747 WIRING DIAGRAM 28-42-15
ADDED WIRE OR NEW ROUTING

EXISTING WIRE DELETED WIRE OR FORMER ROUTING1326172

**(SHEET 1 OF 1) FIGURE 5: INSTALL NEW WIRING (WIRE BUNDLE W4488)**  Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 98 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

**FIGURE 5: INSTALL NEW WIRING (WIRE BUNDLE W4488)**

This Figure applies to Group 4, 14; Group 15, Configuration 2; Group 17, Configuration 2: 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 289U1225-101. Route new wiring following the existing wire bundle routing, refer to SWPM 20-10-11 and SWPM 20-10-19 as an accepted procedure. Use lacing tape as necessary, see kit of parts for Figure 3 for lacing tape.

**FLAG NOTE NAME IDENTIFICATION QTY MORE DATA**  1 ASSY -101 (W4488) 289U1225-101W 1 Refer to SWPM 20-10-11 as an accepted procedure. 2 CONTACT, PIN BACC47CN1S 2 Refer to SWPM 20-61-11 as an accepted procedure. 3 CONTACT, SOCKET BACC47CP1S 2 Refer to SWPM 20-61-11 as an accepted procedure. 4 LACING TAPE 289T9001-21 1 Refer to SWPM 20-10-11 as an accepted procedure. 

### 1 4

CENTER - AFT LEFT W4588 -102 47 D43827P (POS 10) W3851

-106 35 AP2301

D40103P (POS 15) 37 J W4488-

085-20 W4488- 084-20

EQUIPMENT E8 46 (2 LOCATIONS)
(2 LOCATIONS)

J AC1401 2

3

REFERENCE: 747 WIRING DIAGRAM 28-42-15
ADDED WIRE OR NEW ROUTING1326174

**(SHEET 1 OF 1) FIGURE 6: REWORK / INSTALL NEW WIRING (WIRE BUNDLE W4488)**  Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 99 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

**FIGURE 6: REWORK / INSTALL NEW WIRING (WIRE BUNDLE W4488)**

This Figure applies to Group 2, 30-31, 33, 37: 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 289U1225-101. Route new wiring following the existing wire bundle routing, refer to SWPM 20-10-11 and SWPM 20-10-19. Use lacing tape as necessary, see kit of parts for Figure 3 for lacing tape.

**FLAG NOTE NAME IDENTIFICATION QTY MORE DATA**  1 ASSY -101 (W4488) 289U1225-101W 1 Refer to SWPM 20-10-11 as an accepted procedure. 2 CONTACT, PIN BACC47CN1S 2 Refer to SWPM 20-61-11 as an accepted procedure. 

### 1 5

033-18

CENTER - AFT LEFT (2 LOCATIONS)

47 D43827P (POS 10) W4488- 35

AP2301

D40103P (POS 15) W3851

-106

37 W4588 -102 085-20 071-22 W4588 -102

J EQUIPMENT E8 W4488- 25 084-20

W4588 (REF) 46

31 (2 LOCATIONS)
(2 LOCATIONS)

J AC1401 2

3

4

REFERENCE: 747 WIRING DIAGRAM 28-42-15
ADDED WIRE OR NEW ROUTING

EXISTING WIRE DELETED WIRE OR FORMER ROUTING1326179

**(SHEET 1 OF 2) FIGURE 6: REWORK / INSTALL NEW WIRING (WIRE BUNDLE W4488)**  Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 100 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

3 CONTACT, SOCKET BACC47CP1S 2 Refer to SWPM 20-61-11 as an accepted procedure. 4 INSULATION SLEEVING, HEAT SHRINKABLE, POLYOLEFIN, FLEXIBLE, X-LI M23053/5-107-4 2 Refer to SWPM 20-10-11 as an accepted procedure.

5 LACING TAPE 289T9001-21 1 Refer to SWPM 20-10-11 as an accepted procedure. **FLAG NOTE NAME IDENTIFICATION QTY MORE DATA** 

**(SHEET 2 OF 2) FIGURE 7: REWORK / INSTALL NEW WIRING (WIRE BUNDLE W4488)**  Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 101 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

**FIGURE 7: REWORK / INSTALL NEW WIRING (WIRE BUNDLE W4488)**

This Figure applies to Group 16: 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 289U1225-101. Route new wiring following the existing wire bundle routing, refer to SWPM 20-10-11 and SWPM 20-10-19 as an accepted procedure. Use lacing tape as necessary, see kit of parts for Figure 3 for lacing tape.

**FLAG NOTE NAME IDENTIFICATION QTY MORE DATA**  1 ASSY -101 (W4488) 289U1225-101W 1 Refer to SWPM 20-10-11 as an accepted procedure. 2 CONTACT, PIN BACC47CN1S 2 Refer to SWPM 20-61-11 as an accepted procedure. 

### 1 5

033-18

CENTER - AFT LEFT (2 LOCATIONS)

47 D43827P (POS 10) W4488- 35

AP2301

D40103P (POS 15) W3851

-106

37 W4588 -102 085-20 071-22 W4588 -102 W4588 -102

J EQUIPMENT E8 W4488- 084-20 46

31 (2 LOCATIONS)
(2 LOCATIONS)

J AC1401 2

3

4

REFERENCE: 747 WIRING DIAGRAM 28-42-15
ADDED WIRE OR NEW ROUTING

EXISTING WIRE DELETED WIRE OR FORMER ROUTING1326183

**(SHEET 1 OF 2) FIGURE 7: REWORK / INSTALL NEW WIRING (WIRE BUNDLE W4488)**  Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 102 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

3 CONTACT, SOCKET BACC47CP1S 2 Refer to SWPM 20-61-11 as an accepted procedure. 4 INSULATION SLEEVING, HEAT SHRINKABLE, POLYOLEFIN, FLEXIBLE, X-LI M23053/5-107-4 2 Refer to SWPM 20-10-11 as an accepted procedure.

5 LACING TAPE 289T9001-21 1 Refer to SWPM 20-10-11 as an accepted procedure. **FLAG NOTE NAME IDENTIFICATION QTY MORE DATA** 

**(SHEET 2 OF 2) FIGURE 8: INSTALL NEW WIRING (WIRE BUNDLE W4588)**  Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 103 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

**FIGURE 8: INSTALL NEW WIRING (WIRE BUNDLE W4588)**

This Figure applies to Group 1-2; Group 3, Configuration 1; Group 4; Group 5, Configuration 2; Group 6, Configuration 2; Group 7; Group 15, Configuration 2; Group 17, Configuration 2; Group 19, Configuration 1; Group 20-22; Group 23, Configuration 2; Group 24-31: 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 289U1225-102. Route new wiring following the existing wire bundle routing, refer to SWPM 20-10-11 and SWPM 20-10-19. Use lacing tape as necessary, see kit of parts for Figure 3 for lacing tape.

**FLAG NOTE NAME IDENTIFICATION QTY MORE DATA**  1 ASSY -102 (W4588) 289U1225-102W 1 Refer to SWPM 20-10-11 as an accepted procedure. 2 CONTACT, PIN BACC47CN1S 2 Refer to SWPM 20-61-11 as an accepted procedure. 3 CONTACT, SOCKET BACC47CP1S 2 Refer to SWPM 20-61-11 as an accepted procedure. 4 LACING TAPE 289T9001-21 1 Refer to SWPM 20-10-11 as an accepted procedure. 

### 1 4

DC POWER DISTRIBUTION W4488 -101 47 D43827P (POS 10) W3845

-103 12 AE0304

D41785P (POS 9) 13 J W4588-

149-20 W4588- 148-20

PANELP180 46 (2 LOCATIONS)

(2 LOCATIONS)

J AC1401 3

2

REFERENCE: 747 WIRING DIAGRAM 28-42-15
ADDED WIRE OR NEW ROUTING1326188

**(SHEET 1 OF 1) FIGURE 9: INSTALL NEW WIRING (WIRE BUNDLE W4588)**  Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 104 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

**FIGURE 9: INSTALL NEW WIRING (WIRE BUNDLE W4588)**

This Figure applies to Group 12: 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 289U1225-102. Route new wiring following the existing wire bundle routing, refer to SWPM 20-10-11 and SWPM 20-10-19. Use lacing tape as necessary, see kit of parts for Figure 3 for lacing tape.

**FLAG NOTE NAME IDENTIFICATION QTY MORE DATA**  1 ASSY -102 (W4588) 289U1225-102W 1 Refer to SWPM 20-10-11 as an accepted procedure. 2 CONTACT, PIN BACC47CN1S 2 Refer to SWPM 20-61-11 as an accepted procedure. 

### 1 5

DC POWER DISTRIBUTION W4488 -101 47 D43827P (POS 10) W3845

-103 12 AE0304

D41785P (POS 9) 13 AEO418

J D40406P (POS 14) 15

J W4588-

149-20 W4588- 148-20

PANELP180 46 113-20 SPARE W4588-

(2 LOCATIONS) (2 LOCATIONS)

J AC1401 3 2 4

REFERENCE: 747 WIRING DIAGRAM 28-42-15
ADDED WIRE OR NEW ROUTING

EXISTING WIRE DELETED WIRE OR FORMER ROUTING1326195

**(SHEET 1 OF 2) FIGURE 9: INSTALL NEW WIRING (WIRE BUNDLE W4588)**  Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 105 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

3 CONTACT, SOCKET BACC47CP1S 2 Refer to SWPM 20-61-11 as an accepted procedure. 4 INSULATION SLEEVING, HEAT SHRINKABLE, POLYOLEFIN, FLEXIBLE, X-LI M23053/5-107-4 1 Refer to SWPM 20-10-11 as an accepted procedure.

5 LACING TAPE 289T9001-21 1 Refer to SWPM 20-10-11 as an accepted procedure. **FLAG NOTE NAME IDENTIFICATION QTY MORE DATA** 

**(SHEET 2 OF 2) FIGURE 10: REWORK / INSTALL NEW WIRING (WIRE BUNDLE W4588)**  Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 106 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

**FIGURE 10: REWORK / INSTALL NEW WIRING (WIRE BUNDLE W4588)**

This Figure applies to Group 11, 13: 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 289U1225-102. Route new wiring following the existing wire bundle routing, refer to SWPM 20-10-11 and SWPM 20-10-19. Use lacing tape as necessary, see kit of parts for Figure 3 for lacing tape.

**FLAG NOTE NAME IDENTIFICATION QTY MORE DATA**  1 ASSY -102 (W4588) 289U1225-102W 1 Refer to SWPM 20-10-11 as an accepted procedure. 2 CONTACT, PIN BACC47CN1S 2 Refer to SWPM 20-61-11 as an accepted procedure. 

### 1 5 W4588-

DC POWER DISTRIBUTION W4488 -101 47 D43827P (POS 10) W3845

-103 12 AE0304

D41785P (POS 9) 13 AEO418

J D40406P (POS 14) 15 114-20

J W4588-

149-20 W4588- 148-20

PANEL- P180 (2 LOCATIONS)

46 18 113-20 SPARE W4588-

(2 LOCATIONS) (2 LOCATIONS)

J AC1401 3 2 4

SPARE

REFERENCE: 747 WIRING DIAGRAM 28-42-15
ADDED WIRE OR NEW ROUTING

EXISTING WIRE DELETED WIRE OR FORMER ROUTING1326249

**(SHEET 1 OF 2) FIGURE 10: REWORK / INSTALL NEW WIRING (WIRE BUNDLE W4588)**  Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 107 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

3 CONTACT, SOCKET BACC47CP1S 2 Refer to SWPM 20-61-11 as an accepted procedure. 4 INSULATION SLEEVING, HEAT SHRINKABLE, POLYOLEFIN, FLEXIBLE, X-LI M23053/5-107-4 2 Refer to SWPM 20-10-11 as an accepted procedure.

5 LACING TAPE 289T9001-21 1 Refer to SWPM 20-10-11 as an accepted procedure. **FLAG NOTE NAME IDENTIFICATION QTY MORE DATA** 

**(SHEET 2 OF 2) FIGURE 11: REWORK / INSTALL NEW WIRING (WIRE BUNDLE W4588)**  Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 108 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

**FIGURE 11: REWORK / INSTALL NEW WIRING (WIRE BUNDLE W4588)**

This Figure applies to Group 8, 14: 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 289U1225-102. Route new wiring following the existing wire bundle routing, refer to SWPM 20-10-11 and SWPM 20-10-19. Use lacing tape as necessary, see kit of parts for Figure 3 for lacing tape.

**FLAG NOTE NAME IDENTIFICATION QTY MORE DATA**  1 ASSY -102 (W4588) 289U1225-102W 1 Refer to SWPM 20-10-11 as an accepted procedure. 2 CONTACT, PIN BACC47CN1S 2 Refer to SWPM 20-61-11 as an accepted procedure. 

### 1 5

DC POWER DISTRIBUTION W4488 -101 47 D43827P (POS 10) W3845

-103 12 AE0304

D41785P (POS 9) 13 J D41805P (POS 19) 1 119-20 W4588-

J W4588-

149-20 W4588- 148-20

PANELP180 46 (2 LOCATIONS)

117-20 2 SPARE W4588-

(2 LOCATIONS) (2 LOCATIONS)

J AC1401 3 2 4

SPARE

REFERENCE: 747 WIRING DIAGRAM 28-42-15
ADDED WIRE OR NEW ROUTING

EXISTING WIRE DELETED WIRE OR FORMER ROUTING1326260

**(SHEET 1 OF 2) FIGURE 11: REWORK / INSTALL NEW WIRING (WIRE BUNDLE W4588)**  Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 109 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

3 CONTACT, SOCKET BACC47CP1S 2 Refer to SWPM 20-61-11 as an accepted procedure. 4 INSULATION SLEEVING, HEAT SHRINKABLE, POLYOLEFIN, FLEXIBLE, X-LI M23053/5-107-4 2 Refer to SWPM 20-10-11 as an accepted procedure.

5 LACING TAPE 289T9001-21 1 Refer to SWPM 20-10-11 as an accepted procedure. **FLAG NOTE NAME IDENTIFICATION QTY MORE DATA** 

**(SHEET 2 OF 2) FIGURE 12: REWORK / INSTALL NEW WIRING (WIRE BUNDLE W4588)**  Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 110 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

**FIGURE 12: REWORK / INSTALL NEW WIRING (WIRE BUNDLE W4588)**

This Figure applies to Group 10: 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 289U1225-102. Route new wiring following the existing wire bundle routing, refer to SWPM 20-10-11 and SWPM 20-10-19. Use lacing tape as necessary, see kit of parts for Figure 3 for lacing tape.

**FLAG NOTE NAME IDENTIFICATION QTY MORE DATA**  1 ASSY -102 (W4588) 289U1225-102W 1 Refer to SWPM 20-10-11 as an accepted procedure. 2 CONTACT, PIN BACC47CN1S 2 Refer to SWPM 20-61-11 as an accepted procedure. 

### 1 5

DC POWER DISTRIBUTION W4488 -101 47 D43827P (POS 10) W3845

-103 12 AE0304

D41785P (POS 9) 13 J D41805P (POS 19) 1

J W4588-

149-20 W4588- 148-20

PANELP180 46 117-20 SPARE W4588-

(2 LOCATIONS) (2 LOCATIONS)

J AC1401 3 2 4

REFERENCE: 747 WIRING DIAGRAM 28-42-15
ADDED WIRE OR NEW ROUTING

EXISTING WIRE DELETED WIRE OR FORMER ROUTING1326280

**(SHEET 1 OF 2) FIGURE 12: REWORK / INSTALL NEW WIRING (WIRE BUNDLE W4588)**  Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 111 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

3 CONTACT, SOCKET BACC47CP1S 2 Refer to SWPM 20-61-11 as an accepted procedure. 4 INSULATION SLEEVING, HEAT SHRINKABLE, POLYOLEFIN, FLEXIBLE, X-LI M23053/5-107-4 1 Refer to SWPM 20-10-11 as an accepted procedure.

5 LACING TAPE 289T9001-21 1 Refer to SWPM 20-10-11 as an accepted procedure. **FLAG NOTE NAME IDENTIFICATION QTY MORE DATA** 

**(SHEET 2 OF 2) FIGURE 13: REWORK / INSTALL NEW WIRING (WIRE BUNDLE W3845)**  Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 112 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

**FIGURE 13: REWORK / INSTALL NEW WIRING (WIRE BUNDLE W3845)**

This Figure applies to Group 1-2; Group 3, Configuration 1; Group 4; Group 5, Configuration 2; Group 6, Configuration 2; Group 7-8, 10-14; Group 15, Configuration 2; Group 17, Configuration 2; Group 19, Configuration 1; Group 20-22; Group 23, Configuration 2; Group 24-31: 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 289U1225-103, if additional BACC47CP1S socket is required use extra from -101 or -102 wire kit. Route new wiring following the existing wire bundle routing, refer to SWPM 20-10-11 and SWPM 20-10-19 as an accepted procedure. Use lacing tape as necessary.

**FLAG NOTE NAME IDENTIFICATION QTY MORE DATA**  1 ASSY -103 (W3845) 289U1225-103W 1 Refer to SWPM 20-10-11 as an accepted procedure. 2 CONTACT, SOCKET BACC47CP1S 2 Refer to SWPM 20-61-11 as an accepted procedure. 3 CONTACT, SOCKET BACC47CP1S 2 Refer to SWPM 20-61-11 as an accepted procedure. 4 LACING TAPE 289T9001-91 1 Refer to SWPM 20-10-11 as an accepted procedure. 1 4

19 J J 18 12

D41785P D41807P AE0304 AE0304

(2 LOCATIONS)

P180 PANEL-DC POWER DISTRIBUTION J D41786P 2AB-24 29 13 2AE-24 2AD-24 

# W3845

28 NC 2AC-24 W4815 (REF) W4588

-102 (2 LOCATIONS)

(POS 10) (POS 13) W4758 -104
3 2

NC (POS 9)

REFERENCE: 747 WIRING DIAGRAM 28-42-15, 30-41-31
ADDED WIRE OR NEW ROUTING

EXISTING WIRE DELETED WIRE OR FORMER ROUTING1326291

**(SHEET 1 OF 1) FIGURE 14: REWORK / INSTALL NEW WIRING (WIRE BUNDLE W4758)**  Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 113 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

**FIGURE 14: REWORK / INSTALL NEW WIRING (WIRE BUNDLE W4758)**

This Figure applies to Group 1-2; Group 3, Configuration 1; Group 4; Group 5, Configuration 2; Group 6, Configuration 2; Group 7-8, 10-14; Group 15, Configuration 2; Group 16; Group 17, Configuration 2; Group 18, Configuration 2; Group 19, Configuration 1; Group 20-22; Group 23, Configuration 2; Group 24-37: 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 289U1225-104. Use existing wiring and follow existing wire bundle routing, refer to SWPM 20-10-11 and SWPM 20-10-19 as an accepted procedure. Use lacing tape as necessary.

**FLAG NOTE NAME IDENTIFICATION QTY MORE DATA**  1 CONTACT, SOCKET BACC47EG2 2 Refer to SWPM 20-61-11 as an accepted procedure. 2 LACING TAPE 289T9001-51 1 Refer to SWPM 20-10-11 as an accepted procedure. 1

DW3417C W4758- 634-24 W4758- 633-24

M7952 19

MAWEA CARD FILE (P54) 18

D41807P J

PANEL-DC POWER DISTRIBUTION AE0304

FUEL CMD

P180 (POS 13) (2 LOCATIONS)

W3845

-103 2

FUEL CMD

STAB L STAB R C9

C8

REFERENCE: 747 WIRING DIAGRAM 30-41-31
ADDED WIRE OR NEW ROUTING

EXISTING WIRE DELETED WIRE OR FORMER ROUTING1326308

**(SHEET 1 OF 1) FIGURE 15: REWORK / INSTALL NEW WIRING ON E8 SHELF (WIRE BUNDLE W3851)**  Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 114 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

**FIGURE 15: REWORK / INSTALL NEW WIRING ON E8 SHELF (WIRE BUNDLE W3851)**

This Figure applies to Group 1-2; Group 3, Configuration 1; Group 4; Group 5, Configuration 2; Group 6, Configuration 2; Group 7-8, 10-14; Group 15, Configuration 2; Group 16; Group 17, Configuration 2; Group 18, Configuration 2; Group 20, 22; Group 23, Configuration 2; Group 24-25, 28, 32-36: 1 7

23

196-20 332-12B 

# W3851

C1 C2

A1 J D40107P 1

194-20 336-12Y W4601 (REF)

C1

W2018 (REF)

X2

H.S. PUMP CONT-LEFT C2

R7401 RLY

EQUIPMENT CENTER - LEFT AFT E8 15

19 054-20

B1 B2

A2 AP2301

334-12R B1

A1

X2

H.S. PUMP CONT-LEFT R1365 RLY B2

A2 335-12B (3 LOCATIONS)

X1

5 3 2

(5 LOCATIONS) 195-20

333-12Y 331-12R 319-12R

320-12B 321-12Y

4 (6 LOCATIONS) X1 (3 LOCATIONS)

6

REFERENCE: 747 WIRING DIAGRAM 28-21-28 ADDED WIRE OR NEW ROUTING

EXISTING WIRE DELETED WIRE OR FORMER ROUTING1326327

**(SHEET 1 OF 2) FIGURE 15: REWORK / INSTALL NEW WIRING ON E8 SHELF (WIRE BUNDLE W3851)**  Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 115 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

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 289U1225-106. Route new wiring following the existing wire bundle routing, refer to SWPM 20-10-11 and SWPM 20-10-19. Use lacing tape as necessary, see kit of parts for Figure 13 for lacing tape.

**FLAG NOTE NAME IDENTIFICATION QTY MORE DATA**  1 ASSY -106 (W3851) 289U1225-106W 1 Refer to SWPM 20-10-11 as an accepted procedure. 2 CONTACT, SOCKET BACC47CP1S 1 Refer to SWPM 20-61-11 as an accepted procedure. 3 CONTACT BACC47CP3T 3 Refer to SWPM 20-61-11 as an accepted procedure. 4 TERMINAL LUG BACT12E10 6 Refer to SWPM 20-30-11 as an accepted procedure. 5 TERMINAL LUG BACT12AC2 5 Refer to SWPM 20-30-11 as an accepted procedure. 6 TERMINAL LUG BACT12AC12 3 Refer to SWPM 20-30-11 as an accepted procedure. 7 LACING TAPE 289T9001-91 1 Refer to SWPM 20-10-11 as an accepted procedure.

**(SHEET 2 OF 2) FIGURE 16: INSTALL NEW WIRING ON E8 SHELF (WIRE BUNDLE W3851)**  Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 116 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

**FIGURE 16: INSTALL NEW WIRING ON E8 SHELF (WIRE BUNDLE W3851)**

This Figure applies to Group 1-2; Group 3, Configuration 1; Group 4; Group 5, Configuration 2; Group 6, Configuration 2; Group 7-8, 10-14; Group 15, Configuration 2; Group 16; Group 17, Configuration 2; Group 18, Configuration 2; Group 19, Configuration 1; Group 20-22; Group 23, Configuration 2; Group 24-37: 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 289U1225-106. Route new wiring following the existing wire bundle routing, refer to SWPM 20-10-11 and SWPM 20-10-19 as an accepted procedure. Use lacing tape as necessary, see kit of parts for Figure 13 for lacing tape.

**FLAG NOTE NAME IDENTIFICATION QTY MORE DATA**  1 ASSY -106 (W3851) 289U1225-106W 1 Refer to SWPM 20-10-11 as an accepted procedure. 1 4

W4488

-101 

# W3851

11
H.S. PUMP CONT-LEFT R7401 RELAY

EQUIPMENT CENTER - LEFT AFT E8 197-20

604-20 (3 LOCATIONS)

H.S. PUMP CONT-LEFT R1365 RELAY 12 NC 13 14 NC

D40103P AP2301

11 NC 13 12 37 14 NC

J 2 3

REFERENCE: 747 WIRING DIAGRAM 28-42-15
ADDED WIRE OR NEW ROUTING

EXISTING WIRE DELETED WIRE OR FORMER ROUTING1326337

**(SHEET 1 OF 2) FIGURE 16: INSTALL NEW WIRING ON E8 SHELF (WIRE BUNDLE W3851)**  Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 117 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

2 CONTACT, PIN BACC47CN1S 1 Refer to SWPM 20-61-11 as an accepted procedure. 3 TERMINAL LUG BACT12AC2 3 Refer to SWPM 20-30-11 as an accepted procedure. 4 LACING TAPE 289T9001-91 1 Refer to SWPM 20-10-11 as an accepted procedure. **FLAG NOTE NAME IDENTIFICATION QTY MORE DATA** 

**(SHEET 2 OF 2) FIGURE 17: REWORK / INSTALL NEW WIRING ON E8 SHELF (WIRE BUNDLE W3851)**  Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 118 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

**FIGURE 17: REWORK / INSTALL NEW WIRING ON E8 SHELF (WIRE BUNDLE W3851)**

This Figure applies to Group 1-2; Group 3, Configuration 1; Group 4; Group 5, Configuration 2; Group 6, Configuration 2; Group 7-8, 10-14; Group 15, Configuration 2; Group 16; Group 17, Configuration 2; Group 18, Configuration 2; Group 19, Configuration 1; Group 20-22; Group 23, Configuration 2; Group 24-37: The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure. 1 4

198-20 11

600-20 H.S. PUMP CONT-LEFT R7401 RELAY

EQUIPMENT CENTER - LEFT AFT E8 J W4601 (REF) D40107P H.S. PUMP CONT-LEFT R1365 RELAY 12 NC 13 14 NC

11 NC 13 12 14 NC

064-20 AP2301

SM14 

# W3851

4 X1 X2

(2 LOCATIONS) 2

3

REFERENCE: 747 WIRING DIAGRAM 28-42-15
ADDED WIRE OR NEW ROUTING

EXISTING WIRE DELETED WIRE OR FORMER ROUTING1326351

**(SHEET 1 OF 2) FIGURE 17: REWORK / INSTALL NEW WIRING ON E8 SHELF (WIRE BUNDLE W3851)**  Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 119 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

**NOTE:** Use the parts from wire kit 289U1225-106. Route new wiring following the existing wire bundle routing, refer to SWPM 20-10-11 and SWPM 20-10-19. Use lacing tape as necessary, see kit of parts for Figure 13 for lacing tape.

**FLAG NOTE NAME IDENTIFICATION QTY MORE DATA**  1 ASSY -106 (W3851) 289U1225-106W 1 Refer to SWPM 20-10-11 as an accepted procedure. 2 TERMINAL LUG BACT12AC2 2 Refer to SWPM 20-30-11 as an accepted procedure. 3 SPLICE D436-38 1 Refer to SWPM 20-30-11 as an accepted procedure. 4 LACING TAPE 289T9001-91 1 Refer to SWPM 20-10-11 as an accepted procedure.

**(SHEET 2 OF 2) FIGURE 18: REWORK / INSTALL NEW WIRING ON E8 SHELF (WIRE BUNDLE W3851)**  Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 120 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

**FIGURE 18: REWORK / INSTALL NEW WIRING ON E8 SHELF (WIRE BUNDLE W3851)**

This Figure applies to Group 1-2; Group 3, Configuration 1; Group 4; Group 5, Configuration 2; Group 6, Configuration 2; Group 7-8, 10-14; Group 15, Configuration 2; Group 16; Group 17, Configuration 2; Group 18, Configuration 2; Group 19, Configuration 1; Group 20, 22; Group 23, Configuration 2; Group 24-25, 28, 32-36: 1 7 3

1

602-20 341-12B 2 

# W3851

C1 C2

A1 J D40106P 5

603-20 339-12Y W4602 (REF)

C1

W2018 (REF)

X2

H.S. PUMP CONT-RIGHT C2

R7402 RLY

EQUIPMENT CENTER - LEFT AFT E8 3

2 037-20

B1 B2

A2

X1 AP2301

337-12R B1

A1

X2

H.S. PUMP CONT-RIGHT R1366 RLY B2

A2 338-12B (3 LOCATIONS)

X1

5 (5 LOCATIONS) 199-20

342-12Y 340-12R 322-12R

323-12B 324-12Y

4 (6 LOCATIONS) (3 LOCATIONS) 6

REFERENCE: 747 WIRING DIAGRAM 28-21-31 ADDED WIRE OR NEW ROUTING

EXISTING WIRE DELETED WIRE OR FORMER ROUTING1327151

**(SHEET 1 OF 2) FIGURE 18: REWORK / INSTALL NEW WIRING ON E8 SHELF (WIRE BUNDLE W3851)**  Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 121 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

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 289U1225-106. Route new wiring following the existing wire bundle routing, refer to SWPM 20-10-11 and SWPM 20-10-19. Use lacing tape as necessary, see kit of parts for Figure 13 for lacing tape.

**FLAG NOTE NAME IDENTIFICATION QTY MORE DATA**  1 ASSY -106 (W3851) 289U1225-106W 1 Refer to SWPM 20-10-11 as an accepted procedure. 2 CONTACT BACC47CP3T 1 Refer to SWPM 20-61-11 as an accepted procedure. 3 CONTACT BACC47CP3T 3 Refer to SWPM 20-61-11 as an accepted procedure. 4 TERMINAL LUG BACT12E10 6 Refer to SWPM 20-30-11 as an accepted procedure. 5 TERMINAL LUG BACT12AC2 5 Refer to SWPM 20-30-11 as an accepted procedure. 6 TERMINAL LUG BACT12AC12 3 Refer to SWPM 20-30-11 as an accepted procedure. 7 LACING TAPE 289T9001-91 1 Refer to SWPM 20-10-11 as an accepted procedure.

**(SHEET 2 OF 2) FIGURE 19: INSTALL NEW WIRING ON E8 SHELF (WIRE BUNDLE W3851)**  Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 122 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

**FIGURE 19: INSTALL NEW WIRING ON E8 SHELF (WIRE BUNDLE W3851)**

This Figure applies to Group 3, Configuration 1; Group 7, 20-22, 29: 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 289U1225-106. Route new wiring following the existing wire bundle routing, refer to SWPM 20-10-11 and SWPM 20-10-19. Use lacing tape as necessary, see kit of parts for Figure 13 for lacing tape.

**FLAG NOTE NAME IDENTIFICATION QTY MORE DATA**  1 ASSY -106 (W3851) 289U1225-106W 1 Refer to SWPM 20-10-11 as an accepted procedure. 2 CONTACT, PIN BACC47CN1S 1 Refer to SWPM 20-61-11 as an accepted procedure. 3 TERMINAL LUG BACT12AC2 3 Refer to SWPM 20-30-11 as an accepted procedure. 4 LACING TAPE 289T9001-91 1 Refer to SWPM 20-10-11 as an accepted procedure. 1 4

W4488

-101 

# W3851

11
H.S. PUMP CONT-RIGHT R7402 RELAY

EQUIPMENT CENTER - LEFT AFT E8 192-20

193-20 (3 LOCATIONS)

H.S. PUMP CONT-RIGHT R1366 RELAY 12 NC 13 14 NC

D40103P AP2301

11 NC 13 12 30 14 NC

J 2 3

REFERENCE: 747 WIRING DIAGRAM 28-42-15
ADDED WIRE OR NEW ROUTING

EXISTING WIRE DELETED WIRE OR FORMER ROUTING1326367

**(SHEET 1 OF 1) FIGURE 20: INSTALL NEW WIRING ON E8 SHELF (WIRE BUNDLE W3851)**  Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 123 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

**FIGURE 20: INSTALL NEW WIRING ON E8 SHELF (WIRE BUNDLE W3851)**

This Figure applies to Group 1-2, 4, 8, 10-12, 14; Group 15, Configuration 2; Group 16; Group 17, Configuration 2; Group 18, Configuration 2; Group 19, Configuration 1; Group 30-35, 37: 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 289U1225-106. Route new wiring following the existing wire bundle routing, refer to SWPM 20-10-11 and SWPM 20-10-19. Use lacing tape as necessary, see kit of parts for Figure 13 for lacing tape.

**FLAG NOTE NAME IDENTIFICATION QTY MORE DATA**  1 ASSY -106 (W3851) 289U1225-106W 1 Refer to SWPM 20-10-11 as an accepted procedure. 2 CONTACT, PIN BACC47CN1S 1 Refer to SWPM 20-61-11 as an accepted procedure. 3 TERMINAL LUG BACT12AC2 3 Refer to SWPM 20-30-11 as an accepted procedure. 4 LACING TAPE 289T9001-91 1 Refer to SWPM 20-10-11 as an accepted procedure. 1 4

W4488

-101 

# W3851

11
H.S. PUMP CONT-RIGHT R7402 RELAY

EQUIPMENT CENTER - LEFT AFT E8 192-20

193-20 (3 LOCATIONS)

H.S. PUMP CONT-RIGHT R1366 RELAY 12 NC 13 14 NC

D40103P AP2301

11 NC 13 12 35 14 NC

J 2 3

REFERENCE: 747 WIRING DIAGRAM 28-42-15
ADDED WIRE OR NEW ROUTING

EXISTING WIRE DELETED WIRE OR FORMER ROUTING1326379

**(SHEET 1 OF 1) FIGURE 21: REWORK / INSTALL NEW WIRING ON E8 SHELF (WIRE BUNDLE W3851)**  Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 124 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

**FIGURE 21: REWORK / INSTALL NEW WIRING ON E8 SHELF (WIRE BUNDLE W3851)**

This Figure applies to Group 1-2; Group 3, Configuration 1; Group 4; Group 5, Configuration 2; Group 6, Configuration 2; Group 7-8, 10-14; Group 15, Configuration 2; Group 16; Group 17, Configuration 2; Group 18, Configuration 2; Group 19, Configuration 1; Group 20-22; Group 23, Configuration 2; Group 24-37: The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure. 1 4

191-20 11

601-20 H.S. PUMP CONT-RIGHT R7402 RELAY

EQUIPMENT CENTER - LEFT AFT E8 J W4602 (REF) D40106P H.S. PUMP CONT-RIGHT R1366 RELAY 12 NC 13 14 NC

11 NC 13 12 14 NC

063-20 AP2301

SM13 

# W3851

4 X1 X2

(2 LOCATIONS) 2

3

REFERENCE: 747 WIRING DIAGRAM 28-42-15
ADDED WIRE OR NEW ROUTING

EXISTING WIRE DELETED WIRE OR FORMER ROUTING1326390

**(SHEET 1 OF 2) FIGURE 21: REWORK / INSTALL NEW WIRING ON E8 SHELF (WIRE BUNDLE W3851)**  Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 125 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

**NOTE:** Use the parts from wire kit 289U1225-106. Route new wiring following the existing wire bundle routing, refer to SWPM 20-10-11 and SWPM 20-10-19. Use lacing tape as necessary, see kit of parts for Figure 13 for lacing tape.

**FLAG NOTE NAME IDENTIFICATION QTY MORE DATA**  1 ASSY -106 (W3851) 289U1225-106W 1 Refer to SWPM 20-10-11 as an accepted procedure. 2 TERMINAL LUG BACT12AC2 2 Refer to SWPM 20-30-11 as an accepted procedure. 3 SPLICE D436-38 1 Refer to SWPM 20-30-12 as an accepted procedure. 4 LACING TAPE 289T9001-91 1 Refer to SWPM 20-10-11 as an accepted procedure.

**(SHEET 2 OF 2) FIGURE 22: INSTALL RELAYS ON E-8 SHELF**  Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 126 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

**FIGURE 22: INSTALL RELAYS ON E-8 SHELF**

UP FWD
INBD AFT E/E EQUIPMENT CENTER ENTRY DOOR NO. 5L MAIN E8 RACK

AFT EQUIPMENT

CENTER - E8 STA 2302.94

STA 2302.94 FWD INBD

SEE A

1 2

19 181345395

**(SHEET 1 OF 7) FIGURE 22: INSTALL RELAYS ON E-8 SHELF**  Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 127 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

UP FWD
INBD

AFT EQUIPMENT

CENTER - E8 STA 2302.94 RELAYS SHOWN INSTALLED B SEE D C



### A E1345396

**(SHEET 2 OF 7) FIGURE 22: INSTALL RELAYS ON E-8 SHELF**  Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 128 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

RELAY INSTALLATION

FWD 

### B UP FWD
INBD



### C 7

5

4 3

5 7

3 6 13 12

111345397

**(SHEET 3 OF 7) FIGURE 22: INSTALL RELAYS ON E-8 SHELF**  Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 129 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

This Figure applies to Group 9:R1365

4 LOCATIONSR1366 FWD

FWD INBD OUTBD



### D

E 9

8

8

10 10

16 14

15 13 12

13 12 14 171345398

**(SHEET 4 OF 7) FIGURE 22: INSTALL RELAYS ON E-8 SHELF**  Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 130 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

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 this figure. For relay installation on E-8 shelf use parts in Top Kit 015U1808-2.

**STEP TASK NAME IDENTIFICATION QTY MORE DATA** 1 Open E-8 SHELF - - Gain access to the E-8 shelf. 2 Remove/Keep Static Inverter - - Refer to 747-400 AMM 24-29-04 as an accepted procedure. 3 Install (New) RELAY BRACKET DETAIL 284U4011-45 1 Prepare and apply faying surface bond between the bottom surface of the bracket and the tray, refer to SWPM 20-20-00 as an accepted procedure. Install (New) BOLT BACS12HN06-7 1 4 Install (New) BONDING JUMPER BACJ40A20-2 1 Prepare surfaces for bonding jumper. Refer to SWPM 20-20-00 as an accepted procedure. Install (New) SCREW, CAP BACS12GU3K9 1 Install (New) WASHER NAS1149D0316H 4 Install washers in build up as shown. Install (New) NUT BACN10YR3CD 1 5 Install (New) SCREW BACS12HN3-36 1 Install clamps in location, do no tighten until after wiring is installed. Install (New) WASHER NAS1149D0332J 2 Install (New) CLAMP, LOOP BACC10GE5 2 Install (New) SPACERS FOR RIVETS NAS42DD6-64FC 2 Install (New) NUT BACN10YR3CD 1 6 Install (New) SCREW BACS12GU3K10 1 Back drill hole, for hole diameter, refer to 747-400 SRM 51-40-05 as an accepted procedure. Install (New) WASHER NAS1149D0316H 1 Install (New) NUT BACN10YR3CD 1 7 Prepare FAY SURFACE BOND - - Prepare surfaces on both sides of bracket. Use Cleaning Method Type I. Refer to SWPM 20-20-00. 8 Install (New) RELAY,25A,W/ AUX BH315 2

**(SHEET 5 OF 7) FIGURE 22: INSTALL RELAYS ON E-8 SHELF**  Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 131 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

9 Install (New) SCREW BACS12GU3K8 4 Install four locations Install (New) WASHER NAS1149D0332J 4 Install on near side. Install (New) WASHER NAS1149D0316H 4 Install on far side. Install (New) NUT BACN10YR3CD 4 10 Measure RESISTANCE - - (a), (b) 11 Measure RESISTANCE - - (c), (d) 12 Apply SEALANT BMS 5-95 1 Fillet seal all sides of relays and between bracket and tray, refer to 747-400 AMM 51-31-01 as an accepted procedure. 13 Apply PRIMER BMS 10-11, TYPE 1 - Touch-up all bare metal surfaces and top coat to match area color. 14 Install (New) TERMINAL BARR 001-1908-000 4 Install terminal barrier be wire installation. 15 Install (New) VINYL MARKER BAC27EEL29698 1 For Vinyl Marker installation, Refer to 747-400 AMM 20-11-16 as an accepted procedure. 16 Install (New) VINYL MARKER BAC27EEL29699 1 For Vinyl Marker installation, Refer to 747-400 AMM 20-11-16 as an accepted procedure. 17 Install (New) MARKER BAC27EEL19431 1 For Vinyl Marker installation, Refer to 747-400 AMM 20-11-16 as an accepted procedure. 18 Install (Kept) Static Inverter - 1 Do not install Static Inverter until wiring is completed. Install Static Inverter, refer to 747-400 AMM 24-29-04 as an accepted procedure. 19 Close E-8 SHELF - - Do not close shelf doors until wiring is complete. (a) Use Bonding Meter. Refer to SWPM 20-20-00 Procedure "Bonding Test for Faying Surfaces" as an accepted procedure. Maximum resistance between relay mount and structure, 0.0025 Ohms. (b) If maximum resistance is exceeded, disassemble relay assembly and reassemble making sure both relay mounting surface and structure assembly are clean. Refer to SWPM 20-20-00. (c) Use Bonding Meter. Refer to SWPM 20-20-00 Procedure "Bonding Test for Faying Surfaces" as an accepted procedure. Maximum resistance between mounting bracket and structure, 0.003 Ohms. (d) If maximum resistance is exceeded, disassemble bonding jumper assembly and reassemble bonding jumper making sure mounting surfaces are clean. Refer to SWPM 20-20-00 **STEP TASK NAME IDENTIFICATION QTY MORE DATA**

**(SHEET 6 OF 7) FIGURE 22: INSTALL RELAYS ON E-8 SHELF**  Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 132 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

The parts shown in the table below are provided as extra parts for this figure. **NAME IDENTIFICATION QTY MORE DATA** Bolt BACN10YR3CD 1 Bolt BACS12GU3K10 3 Washer NAS1149D0316H 1 Washer NAS1149D0332J 4

**(SHEET 7 OF 7) FIGURE 23: WIRE BUNDLE ROUTING INFORMATION**  Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 133 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

**FIGURE 23: WIRE BUNDL E ROUTING INFORMATION** 

STA 1580 STA 2200 2100 STA
STA 1980 AC1401

W4588 W4488

B SEE 2 A SEE

11326410

**(SHEET 1 OF 4) FIGURE 23: WIRE BUNDLE ROUTING INFORMATION**  Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 134 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

E8 RACK STA 2340 STA 2320 STA 2300 S-10L S-11L
S-12L
S-13L

W4488

ENTRY DOOR NO. 5L MAIN

P180 PANEL STA 380 FLOOR BEAM MAWEA CARDFILE

W4588 W4758

FWD FWD INBD 

### A 1 SEE C

2



### B 31326411

**(SHEET 2 OF 4) FIGURE 23: WIRE BUNDLE ROUTING INFORMATION**  Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 135 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

This Figure applies to Group 9: 

### AP2301

D40103P (POSITION 15) STA 2300 STA 2320

W4488

FWD UP



### C 11327097

**(SHEET 3 OF 4) FIGURE 23: WIRE BUNDLE ROUTING INFORMATION**  Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 136 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The information shown is wire bundle routing for wire bundles W4488, W4455, refer to SWPM 20-10-11. For wiring changes see applicable figures. **STEP TASK NAME IDENTIFICATION QTY MORE DATA** 1 INSTALL WIRE BUNDLE W4488 - - Follow existing wire bundle W4488 routing from E-8 shelf, disconnect location AP2301 to disconnect location AC1401. 2 INSTALL WIRE BUNDLE W4588 - - Follow existing wire bundle W4588 routing from disconnect location AC1401 to P180 Panel disconnect location AE0304. 3 INSTALL WIRE BUNDLE W4758 - - Follow existing wire bundle W4758 routing from P180 Panel disconnect location AE0304 to MAWEA card file.

**(SHEET 4 OF 4) FIGURE 24: REWORK / INSTALL NEW WIRING (WIRE BUNDLE W4488)**  Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 137 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

**FIGURE 24: REWORK / INSTALL NEW WIRING (WIRE BUNDLE W4488)**

This Figure applies to Group 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 289U1225-101. Route new wiring following the existing wire bundle routing, refer to SWPM 20-10-11 and SWPM 20-10-19. Use lacing tape as necessary.

**FLAG NOTE NAME IDENTIFICATION QTY MORE DATA**  1 ASSY -101 (W4488) 289U1225-101W 1 Refer to SWPM 20-10-11 as an accepted procedure. 2 CONTACT, PIN BACC47CN1S 2 Refer to SWPM 20-61-11 as an accepted procedure. 3 CONTACT, SOCKET BACC47CP1S 2 Refer to SWPM 20-61-11 as an accepted procedure. 4 INSULATION SLEEVING, HEAT SHRINKABLE, POLYOLEFIN, FLEXIBLE, X-LI M23053/5-107-4 1 Refer to SWPM 20-10-11 as an accepted procedure.

5 LACING TAPE 289T9001-21 1 Refer to SWPM 20-10-11 as an accepted procedure. 

### 071-22 W3851

-106

CENTER - AFT LEFT 47 D43827P (POS 10) W4488- 35

AP2301

D40103P (POS 15) 37 J EQUIPMENT E8 W4588 -102

085-20 W4488- W4588 -102 084-20 46
W4588 (REF) 31 (2 LOCATIONS)
(2 LOCATIONS)

J AC1401 2

3

4 1 5

REFERENCE: 747 WIRING DIAGRAM 28-42-15
ADDED WIRE OR NEW ROUTING

EXISTING WIRE DELETED WIRE OR FORMER ROUTING1327108

**(SHEET 1 OF 1) FIGURE 25: INSTALL NEW WIRING (WIRE BUNDLE W4588)**  Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 138 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

**FIGURE 25: INSTALL NEW WIRING (WIRE BUNDLE W4588)**

This Figure applies to Group 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 289U1225-102. Route new wiring following the existing wire bundle routing, refer to SWPM 20-10-11 and SWPM 20-10-19. Use lacing tape as necessary, see kit of parts for Figure 24 for lacing tape.

**FLAG NOTE NAME IDENTIFICATION QTY MORE DATA**  1 ASSY -102 (W4588) 289U1225-102W 1 Refer to SWPM 20-10-11 as an accepted procedure. 2 CONTACT, PIN BACC47CN1S 2 Refer to SWPM 20-61-11 as an accepted procedure. 3 CONTACT, SOCKET BACC47CP1S 2 Refer to SWPM 20-61-11 as an accepted procedure. 4 LACING TAPE 289T9001-21 1 Refer to SWPM 20-10-11 as an accepted procedure. 

### 1 4

DC POWER DISTRIBUTION W4488 -101 47 D43827P (POS 10) W3845

-103 12 AE0304

D41785P (POS 9) 13 J W4588-

149-20 W4588- 148-20

PANELP180 46 (2 LOCATIONS)

(2 LOCATIONS)

J AC1401 3

2

REFERENCE: 747 WIRING DIAGRAM 28-42-15
ADDED WIRE OR NEW ROUTING1327109

**(SHEET 1 OF 1) FIGURE 26: REWORK / INSTALL NEW WIRING (WIRE BUNDLE W3845)**  Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 139 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

**FIGURE 26: REWORK / INSTALL NEW WIRING (WIRE BUNDLE W3845)**

This Figure applies to Group 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 289U1225-103, if additional BACC47CP1S socket is required use extra from -101 or -102 wire kit. Route new wiring following the existing wire bundle routing, refer to SWPM 20-10-11 and SWPM 20-10-19. Use lacing tape as necessary.

**FLAG NOTE NAME IDENTIFICATION QTY MORE DATA**  1 ASSY -103 (W3845) 289U1225-103W 1 Refer to SWPM 20-10-11 as an accepted procedure. 2 CONTACT, SOCKET BACC47CP1S 2 Refer to SWPM 20-61-11 as an accepted procedure. 3 CONTACT, SOCKET BACC47CP1S 2 Refer to SWPM 20-61-11 as an accepted procedure. 4 LACING TAPE 289T9001-91 1 Refer to SWPM 20-10-11 as an accepted procedure. 1 4

19

J J 18 12

D41785P D41807P AE0304 AE0304

(2 LOCATIONS)

P180 PANEL-DC POWER DISTRIBUTION J D41786P 2AB-24 29 13 2AE-24 2AD-24 W3845

28 NC 2AC-24 W4815 (REF) W4588

-102 (2 LOCATIONS)

(POS 10) (POS 13) W4758 -105
3 2

NC (POS 9)

REFERENCE: 747 WIRING DIAGRAM 28-42-15, 30-41-31
ADDED WIRE OR NEW ROUTING

EXISTING WIRE DELETED WIRE OR FORMER ROUTING1327113

**(SHEET 1 OF 1) FIGURE 27: INSTALL NEW WIRING (WIRE BUNDLE W4758)**  Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 140 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

**FIGURE 27: INSTALL NEW WIRING (WIRE BUNDLE W4758)**

This Figure applies to Group 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 289U1225-105. Route new wiring following the existing wire bundle routing, refer to SWPM 20-10-11 and SWPM 20-10-19 as an accepted procedure. Use lacing tape as necessary.

**FLAG NOTE NAME IDENTIFICATION QTY MORE DATA**  1 ASSY -105 (W4758) 289U1225-105W 1 Refer to SWPM 20-10-11 as an accepted procedure. 2 CONTACT, PIN BACC47EG2 4 Refer to SWPM 20-61-11 as an accepted procedure. 3 LACING TAPE 289T9001-51 1 Refer to SWPM 20-10-11 as an accepted procedure. 1 3

DW3417C C9

W4758- W4758-

M7952 C8 19

MAWEA CARD FILE (P54) 18

D41807P J

PANEL-DC POWER DISTRIBUTION AE0304

FUEL CMD STAB L
P180 (POS 13) (4 LOCATIONS)

W3845

-103

634-24 633-24 2

FUEL CMD STAB R

REFERENCE: 747 WIRING DIAGRAM 30-41-31
ADDED WIRE OR NEW ROUTING

EXISTING WIRE DELETED WIRE OR FORMER ROUTING1327119

**(SHEET 1 OF 1) FIGURE 28: REWORK / INSTALL NEW WIRING ON E8 SHELF (WIRE BUNDLE W3851)**  Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 141 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

**FIGURE 28: REWORK / INSTALL NEW WIRING ON E8 SHELF (WIRE BUNDLE W3851)**

This Figure applies to Group 9: 1 7

23

196-20 332-12B W3851

C1 C2

A1 J D40107P 1

194-20 336-12Y W4601 (REF)

C1

W2018 (REF)

X2

H.S. PUMP CONT-LEFT C2

R7401 RLY

EQUIPMENT CENTER - LEFT AFT E8 15

19 054-20

B1 B2

A2 AP2301

334-12R B1

A1

X2

H.S. PUMP CONT-LEFT R1365 RLY B2

A2 335-12B (3 LOCATIONS)

X1

5 3 2

(5 LOCATIONS) 195-20

333-12Y 331-12R 319-12R

320-12B 321-12Y

4 (6 LOCATIONS) X1 (3 LOCATIONS)

6

REFERENCE: 747 WIRING DIAGRAM 28-21-28 ADDED WIRE OR NEW ROUTING

EXISTING WIRE DELETED WIRE OR FORMER ROUTING1327125

**(SHEET 1 OF 2) FIGURE 28: REWORK / INSTALL NEW WIRING ON E8 SHELF (WIRE BUNDLE W3851)**  Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 142 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

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 289U1225-106. Route new wiring following the existing wire bundle routing, refer to SWPM 20-10-11 and SWPM 20-10-19 as an accepted procedure. Use lacing tape as necessary, see kit of parts for Figure 26 for lacing tape.

**FLAG NOTE NAME IDENTIFICATION QTY MORE DATA**  1 ASSY -106 (W3851) 289U1225-106W 1 Refer to SWPM 20-10-11 as an accepted procedure. 2 CONTACT, SOCKET BACC47CP1S 1 Refer to SWPM 20-61-11 as an accepted procedure. 3 CONTACT BACC47CP3T 3 Refer to SWPM 20-61-11 as an accepted procedure. 4 TERMINAL LUG BACT12E10 6 Refer to SWPM 20-30-11 as an accepted procedure. 5 TERMINAL LUG BACT12AC2 5 Refer to SWPM 20-30-11 as an accepted procedure. 6 TERMINAL LUG BACT12AC12 3 Refer to SWPM 20-30-11 as an accepted procedure. 7 LACING TAPE 289T9001-91 1 Refer to SWPM 20-10-11 as an accepted procedure.

**(SHEET 2 OF 2) FIGURE 29: INSTALL NEW WIRING ON E8 SHELF (WIRE BUNDLE W3851)**  Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 143 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

**FIGURE 29: INSTALL NEW WIRING ON E8 SHELF (WIRE BUNDLE W3851)**

This Figure applies to Group 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 289U1225-106. Route new wiring following the existing wire bundle routing, refer to SWPM 20-10-11 and SWPM 20-10-19. Use lacing tape as necessary, see kit of parts for Figure 26 for lacing tape.

**FLAG NOTE NAME IDENTIFICATION QTY MORE DATA**  1 ASSY -106 (W3851) 289U1225-106W 1 Refer to SWPM 20-10-11 as an accepted procedure. 2 CONTACT, PIN BACC47CN1S 1 Refer to SWPM 20-61-11 as an accepted procedure. 3 TERMINAL LUG BACT12AC2 3 Refer to SWPM 20-30-11 as an accepted procedure. 4 LACING TAPE 289T9001-91 1 Refer to SWPM 20-10-11 as an accepted procedure. 1 4

W4488

-101 

# W3851

11
H.S. PUMP CONT-LEFT R7401 RELAY

EQUIPMENT CENTER - LEFT AFT E8 197-20

604-20 (3 LOCATIONS)

H.S. PUMP CONT-LEFT R1365 RELAY 12 NC 13 14 NC

D40103P AP2301

11 NC 13 12 37 14 NC

J 2 3

REFERENCE: 747 WIRING DIAGRAM 28-42-15
ADDED WIRE OR NEW ROUTING

EXISTING WIRE DELETED WIRE OR FORMER ROUTING1327130

**(SHEET 1 OF 1) FIGURE 30: REWORK / INSTALL NEW WIRING ON E8 SHELF (WIRE BUNDLE W3851)**  Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 144 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

**FIGURE 30: REWORK / INSTALL NEW WIRING ON E8 SHELF (WIRE BUNDLE W3851)**

This Figure applies to Group 9: The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure. 1 4

198-20 11

600-20 H.S. PUMP CONT-LEFT R7401 RELAY

EQUIPMENT CENTER - LEFT AFT E8 J W4601 (REF) D40107P H.S. PUMP CONT-LEFT R1365 RELAY 12 NC 13 14 NC

11 NC 13 12 14 NC

064-20 AP2301

SM14 

# W3851

4 X1 X2

(2 LOCATIONS) 2

3

REFERENCE: 747 WIRING DIAGRAM 28-42-15
ADDED WIRE OR NEW ROUTING

EXISTING WIRE DELETED WIRE OR FORMER ROUTING1327132

**(SHEET 1 OF 2) FIGURE 30: REWORK / INSTALL NEW WIRING ON E8 SHELF (WIRE BUNDLE W3851)**  Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 145 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

**NOTE:** Use the parts from wire kit 289U1225-106. Route new wiring following the existing wire bundle routing, refer SWPM 20-10-11 and SWPM 20-10-19. Use lacing tape as necessary, see kit of parts for Figure 26 for lacing tape.

**FLAG NOTE NAME IDENTIFICATION QTY MORE DATA**  1 ASSY -106 (W3851) 289U1225-106W 1 Refer to SWPM 20-10-11 as an accepted procedure. 2 TERMINAL LUG BACT12AC2 2 Refer to SWPM 20-30-11 as an accepted procedure. 3 SPLICE D436-38 1 Refer to SWPM 20-30-12 as an accepted procedure. 4 LACING TAPE 289T9001-91 1 Refer to SWPM 20-10-11 as an accepted procedure.

**(SHEET 2 OF 2) FIGURE 31: REWORK / INSTALL NEW WIRING ON E8 SHELF (WIRE BUNDLE W3851)**  Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 146 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

**FIGURE 31: REWORK / INSTALL NEW WIRING ON E8 SHELF (WIRE BUNDLE W3851)**

This Figure applies to Group 9: The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure. 1 7 3

1

602-20 341-12B 2 

# W3851

C1 C2

A1 J D40106P 5

603-20 339-12Y W4602 (REF)

C1

W2018 (REF)

X2

H.S. PUMP CONT-RIGHT C2

R7402 RLY

EQUIPMENT CENTER - LEFT AFT E8 3

2 037-20

B1 B2

A2

X1 AP2301

337-12R B1

A1

X2

H.S. PUMP CONT-RIGHT R1366 RLY B2

A2 338-12B (3 LOCATIONS)

X1

5 (5 LOCATIONS) 199-20

342-12Y 340-12R 322-12R

323-12B 324-12Y

4 (6 LOCATIONS) (3 LOCATIONS) 6

REFERENCE: 747 WIRING DIAGRAM 28-21-31 ADDED WIRE OR NEW ROUTING

EXISTING WIRE DELETED WIRE OR FORMER ROUTING1327154

**(SHEET 1 OF 2) FIGURE 31: REWORK / INSTALL NEW WIRING ON E8 SHELF (WIRE BUNDLE W3851)**  Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 147 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

**NOTE:** Use the parts from wire kit 289U1225-106. Route new wiring following the existing wire bundle routing, refer to SWPM 20-10-11 and SWPM 20-10-19. Use lacing tape as necessary, see kit of parts for Figure 26 for lacing tape.

**FLAG NOTE NAME IDENTIFICATION QTY MORE DATA**  1 ASSY -106 (W3851) 289U1225-106W 1 Refer to SWPM 20-10-11 as an accepted procedure. 2 CONTACT BACC47CP3T 1 Refer to SWPM 20-61-11 as an accepted procedure. 3 CONTACT BACC47CP3T 3 Refer to SWPM 20-61-11 as an accepted procedure. 4 TERMINAL LUG BACT12E10 6 Refer to SWPM 20-30-11 as an accepted procedure. 5 TERMINAL LUG BACT12AC2 5 Refer to SWPM 20-30-11 as an accepted procedure. 6 TERMINAL LUG BACT12AC12 3 Refer to SWPM 20-30-11 as an accepted procedure. 7 LACING TAPE 289T9001-91 1 Refer to SWPM 20-10-11 as an accepted procedure.

**(SHEET 2 OF 2) FIGURE 32: INSTALL NEW WIRING ON E8 SHELF (WIRE BUNDLE W3851)**  Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 148 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

**FIGURE 32: INSTALL NEW WIRING ON E8 SHELF (WIRE BUNDLE W3851)**

This Figure applies to Group 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 289U1225-106. Route new wiring following the existing wire bundle routing, refer to SWPM 20-10-11 and SWPM 20-10-19. Use lacing tape as necessary, see kit of parts for Figure 26 for lacing tape.

**FLAG NOTE NAME IDENTIFICATION QTY MORE DATA**  1 ASSY -106 (W3851) 289U1225-106W 1 Refer to SWPM 20-10-11 as an accepted procedure. 2 CONTACT, PIN BACC47CN1S 1 Refer to SWPM 20-61-11 as an accepted procedure. 3 TERMINAL LUG BACT12AC2 3 Refer to SWPM 20-30-11 as an accepted procedure. 4 LACING TAPE 289T9001-91 1 Refer to SWPM 20-10-11 as an accepted procedure. 1 4

W4488

-101 

# W3851

11
H.S. PUMP CONT-RIGHT R7402 RELAY

EQUIPMENT CENTER - LEFT AFT E8 192-20

193-20 (3 LOCATIONS)

H.S. PUMP CONT-RIGHT R1366 RELAY 12 NC 13 14 NC

D40103P AP2301

11 NC 13 12 35 14 NC

J 2 3

REFERENCE: 747 WIRING DIAGRAM 28-42-15
ADDED WIRE OR NEW ROUTING

EXISTING WIRE DELETED WIRE OR FORMER ROUTING1327159

**(SHEET 1 OF 1) FIGURE 33: REWORK / INSTALL NEW WIRING ON E8 SHELF (WIRE BUNDLE W3851)**  Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 149 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

**FIGURE 33: REWORK / INSTALL NEW WIRING ON E8 SHELF (WIRE BUNDLE W3851)**

This Figure applies to Group 9: The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure. 1 4

191-20 11

601-20 H.S. PUMP CONT-RIGHT R7402 RELAY

EQUIPMENT CENTER - LEFT AFT E8 J W4602 (REF) D40106P H.S. PUMP CONT-RIGHT R1366 RELAY 12 NC 13 14 NC

11 NC 13 12 14 NC

063-20 AP2301

SM13 

# W3851

4 X1 X2

(2 LOCATIONS) 2

3

REFERENCE: 747 WIRING DIAGRAM 28-42-15
ADDED WIRE OR NEW ROUTING

EXISTING WIRE DELETED WIRE OR FORMER ROUTING1327163

**(SHEET 1 OF 2) FIGURE 33: REWORK / INSTALL NEW WIRING ON E8 SHELF (WIRE BUNDLE W3851)**  Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 150 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

**NOTE:** Use the parts from wire kit 289U1225-106. Route new wiring following the existing wire bundle routing, refer to SWPM 20-10-11 and SWPM 20-10-19. Use lacing tape as necessary, see kit of parts for Figure 26 for lacing tape.

**FLAG NOTE NAME IDENTIFICATION QTY MORE DATA**  1 ASSY -106 (W3851) 289U1225-106W 1 Refer to SWPM 20-10-11 as an accepted procedure. 2 TERMINAL LUG BACT12AC2 2 Refer to SWPM 20-30-11 as an accepted procedure. 3 SPLICE D436-38 1 Refer to SWPM 20-30-12 as an accepted procedure. 4 LACING TAPE 289T9001-91 1 Refer to SWPM 20-10-11 as an accepted procedure.

**(SHEET 2 OF 2) FIGURE 34: WIRE BUNDLE ROUTING E-8 SHELF**  Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 151 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

**FIGURE 34: WIRE BUNDLE ROUTING E-8 SHELF**

UP FWD
INBD ENTRY DOOR NO. 5L MAIN E8 RACK

AFT EQUIPMENT

CENTER - E8 STA 2302.94

AFT E/E EQUIPMENT CENTER

STA 2302.94 FWD INBD

SEE A1343104

**(SHEET 1 OF 3) FIGURE 34: WIRE BUNDLE ROUTING E-8 SHELF**  Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 152 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

This Figure applies to Group 9: AP2301

W3851 R1365 R1366 R7402
R7401

4 LOCATIONS EXISTING CLAMP

UP FWD
INBD 

### A 6 5 4

3 2

1

21343075

**(SHEET 2 OF 3) FIGURE 34: WIRE BUNDLE ROUTING E-8 SHELF**  Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 153 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The information shown is wire bundle routing for W3851. Install new wires. Refer to SWPM 20-10-11 and SWPM 20-10-19 as accepted procedures. For wiring changes see applicable figures.

**STEP TASK NAME IDENTIFICATION QTY MORE DATA** 1 Remove CLAMPS - Remove clamps as necessary for routing new wires and removal of old wires. 2 Install (New) ASSY -106 (W3851) 1 Follow existing wire bundle W3851 routing on E-8 shelf. 3 Install (New) BOLT BACS12HN3-8 1 Install (New) WASHER NAS1149D0332J 1 Install (New) CLAMP, LOOP BACC10GE5 1 4 Tighten Clamps - 1 Tighten bolt after wiring is installed in clamp. 5 Install (New) BOLT BACS12HN3-20 1 Install (New) WASHER NAS1149D0332J 1 Install (New) CLAMP, LOOP BACC10GE10 1 Install (New) SPACERS FOR RIVETS NAS42DD6-64FC 1 6 INSTALL Clamps - Install existing clamps.

**(SHEET 3 OF 3) FIGURE 35: WIRE BUNDLE ROUTING P180 PANEL TO MAWEA CARD FILE**  Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 154 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

**FIGURE 35: WIRE BUNDLE ROUTING P180 PANEL TO MAWEA CARD FILE**



### A

P180 PANEL FOR WIRE BUNDLE ROUTING INFORMATION STA 380 FLOOR BEAM MAWEA CARDFILE W4588 W4758

FWD

F THROUGH SEE A 2



### B 11343077

**(SHEET 1 OF 8) FIGURE 35: WIRE BUNDLE ROUTING P180 PANEL TO MAWEA CARD FILE**  Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 155 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

A STA 380

W4758 W4588

S-39 FWD 

### A B SEE 1 2

P1801343126

**(SHEET 2 OF 8) FIGURE 35: WIRE BUNDLE ROUTING P180 PANEL TO MAWEA CARD FILE**  Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 156 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

A B STA 400

RBL 100 RBL 50

W4758

FWD BULKHEAD 

### B1343138

**(SHEET 3 OF 8) FIGURE 35: WIRE BUNDLE ROUTING P180 PANEL TO MAWEA CARD FILE**  Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 157 of 182 

### BOEING SERVICE BULLETIN 747-28A2281BSTA400W4758DFWDC1343186

**(SHEET 4 OF 8) FIGURE 35: WIRE BUNDLE ROUTING P180 PANEL TO MAWEA CARD FILE**  Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 158 of 182 

### BOEING SERVICE BULLETIN 747-28A2281DEW4758W4758STA420STA460FWDD1343192

**(SHEET 5 OF 8) FIGURE 35: WIRE BUNDLE ROUTING P180 PANEL TO MAWEA CARD FILE**  Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 159 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

E

F STA 380

W4758

FWD



### E 11343194

**(SHEET 6 OF 8) FIGURE 35: WIRE BUNDLE ROUTING P180 PANEL TO MAWEA CARD FILE**  Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 160 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

This Figure applies to Group 9: 

### F STA 380

W4758 STA 360 RBL 20

FWD



### F MAWAE CARD FILE 11343195

**(SHEET 7 OF 8) FIGURE 35: WIRE BUNDLE ROUTING P180 PANEL TO MAWEA CARD FILE**  Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 161 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The information shown is wire bundle routing for W4758. Install new wires. Refer to SWPM 20-10-11 and SWPM 20-10-19 as accepted procedures. For wiring changes see applicable figure.

**STEP TASK NAME IDENTIFICATION QTY MORE DATA** 1 ROUTING WIRE BUNDLE 289U1225-105W 1 Follow existing wire bundle W4758 routing from P180 panel to MAWEA card file. 2 ROUTING WIRE BUNDLE - 1 Follow existing wire bundle W4588 routing from Disconnect location AC1401 to P180 panel, disconnect location AE0304.

**(SHEET 8 OF 8) FIGURE 36: WIRE BUNDLE ROUTING E-8 SHELF**  Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 162 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

**FIGURE 36: WIRE BUNDLE ROUTING E-8 SHELF**

UP FWD
INBD ENTRY DOOR NO. 5L MAIN E8 RACK

AFT EQUIPMENT

CENTER - E8 STA 2302.94

AFT E/E EQUIPMENT CENTER

STA 2302.94 FWD INBD

SEE A1345408

**(SHEET 1 OF 3) FIGURE 36: WIRE BUNDLE ROUTING E-8 SHELF**  Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 163 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

This Figure applies to Group 1-2; Group 3, Configuration 1; Group 4; Group 5, Configuration 2; Group 6, Configuration 2; Group 7-8, 10-14; Group 15, Configuration 2; Group 16; Group 17, Configuration 2; Group 18, Configuration 2; Group 19, Configuration 1; Group 20-22; Group 23, Configuration 2; Group 24-37: AP2301

W3851 R1365 R1366 R7402
R7401

4 LOCATIONS EXISTING CLAMP

UP FWD
INBD 

### A 6 5 4

3 2

1

21345409

**(SHEET 2 OF 3) FIGURE 36: WIRE BUNDLE ROUTING E-8 SHELF**  Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 164 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The information shown is wire bundle routing for W3851. Install new wires. Refer to SWPM 20-10-11 and SWPM 20-10-19 as accepted procedures. For wiring changes see applicable figures.

**STEP TASK NAME IDENTIFICATION QTY MORE DATA** 1 Remove CLAMPS - Remove clamps as necessary for routing new wires and removal of old wires. 2 Install (New) ASSY -106 (W3851) 1 Follow existing wire bundle W3851 routing on E-8 shelf. 3 Install (New) BOLT BACS12HN3-8 1 For some installation a Install (New) WASHER NAS1149D0332J 1 Install (New) CLAMP, LOOP BACC10GE5 1 4 Tighten Clamps - 1 Tighten bolt after wiring is installed in clamp. 5 Install (New) BOLT BACS12HN3-20 1 Install (New) WASHER NAS1149D0332J 1 Install (New) CLAMP, LOOP BACC10GE10 1 Install (New) SPACERS FOR RIVETS NAS42DD6-64FC 1 6 INSTALL Clamps - Install existing clamps.

**(SHEET 3 OF 3) FIGURE 37: REWORK / INSTALL NEW WIRING (WIRE BUNDLE W4488)**  Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 165 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

**FIGURE 37: REWORK / INSTALL NEW WIRING (WIRE BUNDLE W4488)**

This Figure applies to Group 20, 29: 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 289U1225-101. Route new wiring following the existing wire bundle routing, refer to SWPM 20-10-11 and SWPM 20-10-19. Use lacing tape as necessary.

**FLAG NOTE NAME IDENTIFICATION QTY MORE DATA**  1 ASSY -101 (W4488) 289U1225-101W 1 Refer to SWPM 20-10-11 as an accepted procedure. 2 CONTACT, PIN BACC47CN1S 2 Refer toSWPM 20-61-11 an accepted procedure. 3 CONTACT, SOCKET BACC47CP1S 2 Refer to SWPM 20-61-11 as an accepted procedure. 4 INSULATION SLEEVING, HEAT SHRINKABLE, POLYOLEFIN, FLEXIBLE, X-LI M23053/5-107-4 1 Refer to SWPM 20-10-11 as an accepted procedure.

5 LACING TAPE 289T9001-21 1 Refer to SWPM 20-10-11 as an accepted procedure. 071-22 W3851

-106

CENTER - AFT LEFT 47 D43827P (POS 10) W4488- 30

AP2301

D40103P (POS 15) 37 J EQUIPMENT E8 W4588 -102

085-20 W4488- W4588 -102 084-20 46
W4588 (REF) 31 (2 LOCATIONS)

(2 LOCATIONS)

J AC1401 2

3

4 1 5

REFERENCE: 747 WIRING DIAGRAM 28-42-15
ADDED WIRE OR NEW ROUTING

EXISTING WIRE DELETED WIRE OR FORMER ROUTING1566752

**(SHEET 1 OF 1) FIGURE 38: REWORK / INSTALL NEW WIRING (WIRE BUNDLE W4488)**  Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 166 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

**FIGURE 38: REWORK / INSTALL NEW WIRING (WIRE BUNDLE W4488)**

This Figure applies to Group 6, Configuration 2; Group 23, Configuration 2; Group 24: 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 289U1225-101. Route new wiring following the existing wire bundle routing, refer to SWPM 20-10-11 and SWPM 20-10-19 as an accepted procedure. Use lacing tape as necessary.

**FLAG NOTE NAME IDENTIFICATION QTY MORE DATA**  1 ASSY -101 (W4488) 289U1225-101W 1 Refer to SWPM 20-10-11 as an accepted procedure. 2 CONTACT, PIN BACC47CN1S 2 Refer to SWPM 20-61-11 as an accepted procedure. 3 CONTACT, SOCKET BACC47CP1S 2 Refer to SWPM 20-61-11 as an accepted procedure. 4 INSULATION SLEEVING, HEAT SHRINKABLE, POLYOLEFIN, FLEXIBLE, X-LI M23053/5-107-4 1 Refer to SWPM 20-10-11 as an accepted procedure.

5 LACING TAPE 289T9001-21 1 Refer to SWPM 20-10-11 as an accepted procedure. 36

30 070-22 1 5

W3851

-106

CENTER - AFT LEFT 47 D43827P (POS 10) W4488- AP2301

D40103P (POS 15) 37 J EQUIPMENT E8 W4588 -102

085-20 W4488- W4588 -102 084-20 46
W4588 (REF) (2 LOCATIONS)
(2 LOCATIONS)

J AC1401 2

3

4

REFERENCE: 747 WIRING DIAGRAM 28-42-15
ADDED WIRE OR NEW ROUTING

EXISTING WIRE DELETED WIRE OR FORMER ROUTING1566763

**(SHEET 1 OF 1) FIGURE 39: REWORK / INSTALL NEW WIRING (WIRE BUNDLE W4488)**  Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 167 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

**FIGURE 39: REWORK / INSTALL NEW WIRING (WIRE BUNDLE W4488)**

This Figure applies to Group 3, Configuration 1; Group 21-22: 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 289U1225-101. Route new wiring following the existing wire bundle routing, refer to SWPM 20-10-11 and SWPM 20-10-19. Use lacing tape as necessary, see kit of parts for Figure 3 for lacing tape.

**FLAG NOTE NAME IDENTIFICATION QTY MORE DATA**  1 ASSY -101 (W4488) 289U1225-101W 1 Refer to SWPM 20-10-11 as an accepted procedure. 2 CONTACT, PIN BACC47CN1S 2 Refer to SWPM 20-61-11 as an accepted procedure. 30

33 004-20 1 5

CENTER - AFT LEFT (2 LOCATIONS)

47 D43827P (POS 10) W4488- AP2301

D40103P (POS 15) W3851

-106

37 W4588 -102 085-20 071-22 W4588 -102

J EQUIPMENT E8 W4488- 084-20

W4588 (REF) 46

31 (2 LOCATIONS)
(2 LOCATIONS)

J AC1401 2

3

4

REFERENCE: 747 WIRING DIAGRAM 28-42-15
ADDED WIRE OR NEW ROUTING

EXISTING WIRE DELETED WIRE OR FORMER ROUTING1566776

**(SHEET 1 OF 2) FIGURE 39: REWORK / INSTALL NEW WIRING (WIRE BUNDLE W4488)**  Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 168 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

3 CONTACT, SOCKET BACC47CP1S 2 Refer to SWPM 20-61-11 as an accepted procedure. 4 INSULATION SLEEVING, HEAT SHRINKABLE, POLYOLEFIN, FLEXIBLE, X-LI M23053/5-107-4 2 Refer to SWPM 20-10-11 as an accepted procedure.

5 LACING TAPE 289T9001-21 1 Refer to SWPM 20-10-11 as an accepted procedure. **FLAG NOTE NAME IDENTIFICATION QTY MORE DATA** 

**(SHEET 2 OF 2) FIGURE 40: REWORK / INSTALL NEW WIRING (WIRE BUNDLE W4488)**  Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 169 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

**FIGURE 40: REWORK / INSTALL NEW WIRING (WIRE BUNDLE W4488)**

This Figure applies to Group 5, Configuration 2; Group 13, 25-28, 36: 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 289U1225-101. Route new wiring following the existing wire bundle routing, refer to SWPM 20-10-11 and SWPM 20-10-19. Use lacing tape as necessary, see kit of parts for Figure 3 for lacing tape.

**FLAG NOTE NAME IDENTIFICATION QTY MORE DATA**  1 ASSY -101 (W4488) 289U1225-101W 1 Refer to SWPM 20-10-11 as an accepted procedure. 2 CONTACT, PIN BACC47CN1S 2 Refer to SWPM 20-61-11 as an accepted procedure. 36

070-22 30 1 5

CENTER - AFT LEFT (2 LOCATIONS)

47 D43827P (POS 10) W4488- AP2301

D40103P (POS 15) W3851

-106

37 W4588 -102 085-20 071-22 W4588 -102

J EQUIPMENT E8 W4488- 084-20

W4588 (REF) 46

31 (2 LOCATIONS)
(2 LOCATIONS)

J AC1401 2

3

4

REFERENCE: 747 WIRING DIAGRAM 28-42-15
ADDED WIRE OR NEW ROUTING

EXISTING WIRE DELETED WIRE OR FORMER ROUTING1566796

**(SHEET 1 OF 2) FIGURE 40: REWORK / INSTALL NEW WIRING (WIRE BUNDLE W4488)**  Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 170 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

3 CONTACT, SOCKET BACC47CP1S 2 Refer to SWPM 20-61-11 as an accepted procedure. 4 INSULATION SLEEVING, HEAT SHRINKABLE, POLYOLEFIN, FLEXIBLE, X-LI M23053/5-107-4 2 Refer to SWPM 20-10-11 as an accepted procedure.

5 LACING TAPE 289T9001-21 1 Refer to SWPM 20-10-11 as an accepted procedure. **FLAG NOTE NAME IDENTIFICATION QTY MORE DATA** 

**(SHEET 2 OF 2) FIGURE 41: REWORK / INSTALL NEW WIRING ON E8 SHELF (WIRE BUNDLE W3851)**  Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 171 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

**FIGURE 41: REWORK / INSTALL NEW WIRING ON E8 SHELF (WIRE BUNDLE W3851)**

This Figure applies to Group 19, Configuration 1; Group 21, 26-27, 29-31, 37: The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure. 320-12B 1 7

23

196-20 332-12B 

# W3851

C1 C2

A1 J D40107P 1

194-20 336-12Y W4601 (REF)

C1

W2018 (REF)

X2

H.S. PUMP CONT-LEFT C2

R7401 RLY

EQUIPMENT CENTER - LEFT AFT E8 15

19 054-20

B1 B2

A2 AP2301

334-12R B1

A1

X2

H.S. PUMP CONT-LEFT R1365 RLY B2

A2 335-12B (3 LOCATIONS)

X1

5 3 2

(5 LOCATIONS) 195-20

333-12Y 331-12R 319-12R

321-12Y

4 (6 LOCATIONS) X1 (3 LOCATIONS)

6

REFERENCE: 747 WIRING DIAGRAM 28-21-28 ADDED WIRE OR NEW ROUTING

EXISTING WIRE DELETED WIRE OR FORMER ROUTING1566856

**(SHEET 1 OF 2) FIGURE 41: REWORK / INSTALL NEW WIRING ON E8 SHELF (WIRE BUNDLE W3851)**  Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 172 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

**NOTE:** Use the parts from wire kit 289U1225-106. Route new wiring following the existing wire bundle routing, refer to SWPM 20-10-11 and SWPM 20-10-19. Use lacing tape as necessary, see kit of parts for Figure 13 for lacing tape.

**FLAG NOTE NAME IDENTIFICATION QTY MORE DATA**  1 ASSY -106 (W3851) 289U1225-106W 1 Refer to SWPM 20-10-11 as an accepted procedure. 2 CONTACT, SOCKET BACC47CP1S 1 Refer to SWPM 20-61-11 as an accepted procedure. 3 CONTACT BACC47CP3T 3 Refer to SWPM 20-61-11 as an accepted procedure. 4 TERMINAL LUG BACT12E10 6 Refer to SWPM 20-30-11 as an accepted procedure. 5 TERMINAL LUG BACT12AC2 5 Refer to SWPM 20-30-11 as an accepted procedure. 6 TERMINAL LUG BACT12AC12 3 Refer to SWPM 20-30-11 as an accepted procedure. 7 LACING TAPE 289T9001-91 1 Refer to SWPM 20-10-11 as an accepted procedure.

**(SHEET 2 OF 2) FIGURE 42: REWORK / INSTALL NEW WIRING ON E8 SHELF (WIRE BUNDLE W3851)**  Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 173 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

**FIGURE 42: REWORK / INSTALL NEW WIRING ON E8 SHELF (WIRE BUNDLE W3851)**

This Figure applies to Group 21, 26-27, 29-31, 37: The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure. 323-12B 1 7 3

1

602-20 341-12B 2 

# W3851

C1 C2

A1 J D40106P 5

603-20 339-12Y W4602 (REF)

C1

W2018 (REF)

X2

H.S. PUMP CONT-RIGHT C2

R7402 RLY

EQUIPMENT CENTER - LEFT AFT E8 3

2 037-20

B1 B2

A2

X1 AP2301

337-12R B1

A1

X2

H.S. PUMP CONT-RIGHT R1366 RLY B2

A2 338-12B (3 LOCATIONS)

X1

5 (5 LOCATIONS) 199-20

342-12Y 340-12R 322-12R

324-12Y

4 (6 LOCATIONS) (3 LOCATIONS) 6

REFERENCE: 747 WIRING DIAGRAM 28-21-31 ADDED WIRE OR NEW ROUTING

EXISTING WIRE DELETED WIRE OR FORMER ROUTING1566867

**(SHEET 1 OF 2) FIGURE 42: REWORK / INSTALL NEW WIRING ON E8 SHELF (WIRE BUNDLE W3851)**  Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 174 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

**NOTE:** Use the parts from wire kit 289U1225-106. Route new wiring following the existing wire bundle routing, refer to SWPM 20-10-11 and SWPM 20-10-19. Use lacing tape as necessary, see kit of parts for Figure 13 for lacing tape.

**FLAG NOTE NAME IDENTIFICATION QTY MORE DATA**  1 ASSY -106 (W3851) 289U1225-106W 1 Refer to SWPM 20-10-11 as an accepted procedure. 2 CONTACT BACC47CP3T 1 Refer to SWPM 20-61-11 as an accepted procedure. 3 CONTACT BACC47CP3T 3 Refer to SWPM 20-61-11 as an accepted procedure. 4 TERMINAL LUG BACT12E10 6 Refer to SWPM 20-30-11 as an accepted procedure. 5 TERMINAL LUG BACT12AC2 5 Refer to SWPM 20-30-11 as an accepted procedure. 6 TERMINAL LUG BACT12AC12 3 Refer to SWPM 20-30-11 as an accepted procedure. 7 LACING TAPE 289T9001-91 1 Refer to SWPM 20-10-11 as an accepted procedure.

**(SHEET 2 OF 2) FIGURE 43: INSTALL NEW WIRING ON E8 SHELF (WIRE BUNDLE 3851)**  Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 175 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

**FIGURE 43: INSTALL NEW WIRING ON E8 SHELF (WIRE BUNDLE 3851)**

This Figure applies to Group 5, Configuration 2; Group 6, Configuration 2; Group 13; Group 23, Configuration 2; Group 24-28, 36: 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 289U1225-106. Route new wiring following the existing wire bundle routing, refer to SWPM 20-10-11 and SWPM 20-10-19. Use lacing tape as necessary, see kit of parts for Figure 13 for lacing tape.

**FLAG NOTE NAME IDENTIFICATION QTY MORE DATA**  1 ASSY -106 (W3851) 289U1225-106W 1 Refer to SWPM 20-10-11 as an accepted procedure. 2 CONTACT, PIN BACC47CN1S 1 Refer to SWPM 20-61-11 as an accepted procedure. 3 TERMINAL LUG BACT12AC2 3 Refer to SWPM 20-30-11 as an accepted procedure. 4 LACING TAPE 289T9001-91 1 Refer to SWPM 20-10-11 as an accepted procedure. 36 1 4

W4488

-101 

# W3851

11
H.S. PUMP CONT-RIGHT R7402 RELAY

EQUIPMENT CENTER - LEFT AFT E8 192-20

193-20 (3 LOCATIONS)

H.S. PUMP CONT-RIGHT R1366 RELAY 12 NC 13 14 NC

D40103P AP2301

11 NC 13 12 14 NC

J 2 3

REFERENCE: 747 WIRING DIAGRAM 28-42-15
ADDED WIRE OR NEW ROUTING

EXISTING WIRE DELETED WIRE OR FORMER ROUTING1566869

**(SHEET 1 OF 1) FIGURE 44: INSTALL NEW WIRING (WIRE BUNDLE W4588)**  Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 176 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

**FIGURE 44: INSTALL NEW WIRING (WIRE BUNDLE W4588)**

This Figure applies to Group 18, Configuration 2; Group 32-33, 36-37: 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 289U1225-102 and supplemental kit 015U1808-3. Route new wiring following the existing wire bundle routing, refer to SWPM 20-10-11 and SWPM 20-10-19. Use lacing tape as necessary, see kit of parts for Figure 3 for lacing tape.

**FLAG NOTE NAME IDENTIFICATION QTY MORE DATA**  1 ASSY -102 (W4588) 289U1225-102W 1 Refer to SWPM 20-10-11 as an accepted procedure. 2 CONNECTOR, PLUG BACC45FT16- 24P6 1 New connector supplied in 015U1808-3 supplemental kit. Refer to SWPM 20-60-06 as an accepted procedure. 3 CONTACT, PIN BACC47CN1S 2 Refer to SWPM 20-61-11 as an accepted procedure. 4 CONTACT, SOCKET BACC47CP1S 2 Refer to SWPM 20-61-11 as an accepted procedure. 5 LACING TAPE 289T9001-21 1 Refer to SWPM 20-10-11 as an accepted procedure. 6 ID. Tape 289U1225-10801 1 Refer to SWPM 20-10-11 as an accepted procedure. 1 5

DC POWER DISTRIBUTION W4488 -101 47 D43827P (POS 10) W3845

-103 12 AE0304

D41785P (POS 9) 13 J W4588-

149-20 W4588- 148-20

PANELP180 46 (2 LOCATIONS)

(2 LOCATIONS)

J AC1401 4

3 2 6

REFERENCE: 747 WIRING DIAGRAM 28-42-15
ADDED WIRE OR NEW ROUTING1743637

**(SHEET 1 OF 1) FIGURE 45: REWORK/INSTALL NEW WIRING (WIRE BUNDLE W4588)**  Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 177 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

**FIGURE 45: REWORK/INSTALL NEW WIRING (WIRE BUNDLE W4588)**

This Figure applies to Group 16, 35: 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 289U1225-102 and supplemental kit 015U1808-3. Route new wiring following the existing wire bundle routing, refer to SWPM 20-10-11 and SWPM 20-10-19. Use lacing tape as necessary, see kit of parts for Figure 3 for lacing tape.
**FLAG NOTE NAME IDENTIFICATION QTY MORE DATA**  1 ASSY -102 (W4588) 289U1225-102W 1 Refer to SWPM 20-10-11 as an accepted procedure. 2 CONNECTOR, PLUG BACC45FT16- 24P6 1 New connector supplied in supplemental kit 015U1808-3. Refer to SWPM 20-60-06 as an accepted procedure. 3 CONTACT, PIN BACC47CN1S 2 Refer to SWPM 20-61-11 as an accepted procedure. 1 6 W4588-

DC POWER DISTRIBUTION W4488 -101 47 D43827P (POS 10) W3845

-103 12 AE0304

D41785P (POS 9) 13 AEO418

J D40406P (POS 14) 15 114-20

J W4588-

149-20 W4588- 148-20

PANEL- P180 (2 LOCATIONS)

46 18 113-20 SPARE W4588-

(2 LOCATIONS) (2 LOCATIONS)

J AC1401 4 3 5

SPARE

2 7

REFERENCE: 747 WIRING DIAGRAM 28-42-15
ADDED WIRE OR NEW ROUTING

EXISTING WIRE DELETED WIRE OR FORMER ROUTING1743638

**(SHEET 1 OF 2) FIGURE 45: REWORK/INSTALL NEW WIRING (WIRE BUNDLE W4588)**  Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 178 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

4 CONTACT, SOCKET BACC47CP1S 2 Refer to SWPM 20-61-11 as an accepted procedure. 5 INSULATION SLEEVING, HEAT SHRINKABLE, POLYOLEFIN, FLEXIBLE, X-LI M23053/5-107-4 2 Refer to SWPM 20-10-11 as an accepted procedure.

6 LACING TAPE 289T9001-21 1 Refer to SWPM 20-10-11 as an accepted procedure. 7 ID.TAPE 289U1225-10801 1 Refer to SWPM 20-10-11 as an accepted procedure. **FLAG NOTE NAME IDENTIFICATION QTY MORE DATA** 

**(SHEET 2 OF 2) FIGURE 46: REWORK/INSTALL NEW WIRING (WIRE BUNDLE W4588)**  Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 179 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

**FIGURE 46: REWORK/INSTALL NEW WIRING (WIRE BUNDLE W4588)**

This Figure applies to Group 34: 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 289U1225-102 and supplemental kit 015U1808-3. Route new wiring following the existing wire bundle routing, refer to SWPM 20-10-11 and SWPM 20-10-19. Use lacing tape as necessary, see kit of parts for Figure 3 for lacing tape.
**FLAG NOTE NAME IDENTIFICATION QTY MORE DATA**  1 ASSY -102 (W4588) 289U1225-102W 1 Refer to SWPM 20-10-11 as an accepted procedure. 2 CONNECTOR, PLUG BACC45FT16- 24P6 1 New connector supplied in supplemental kit 015U1808-3. Refer to SWPM 20-60-06 as an accepted procedure. 3 CONTACT, PIN BACC47CN1S 2 Refer to SWPM 20-61-11 as an accepted procedure. 1 6

DC POWER DISTRIBUTION W4488 -101 47 D43827P (POS 10) W3845

-103 12 AE0304

D41785P (POS 9) 13 J D41805P (POS 19) 1 119-20 W4588-

J W4588-

149-20 W4588- 148-20

PANELP180 46 (2 LOCATIONS)

117-20 2 SPARE W4588-

(2 LOCATIONS) (2 LOCATIONS)

J AC1401 4 3 5

SPARE

2 7

REFERENCE: 747 WIRING DIAGRAM 28-42-15
ADDED WIRE OR NEW ROUTING

EXISTING WIRE DELETED WIRE OR FORMER ROUTING1743639

**(SHEET 1 OF 2) FIGURE 46: REWORK/INSTALL NEW WIRING (WIRE BUNDLE W4588)**  Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 180 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

4 CONTACT, SOCKET BACC47CP1S 2 Refer to SWPM 20-61-11 as an accepted procedure. 5 INSULATION SLEEVING, HEAT SHRINKABLE, POLYOLEFIN, FLEXIBLE, X-LI M23053/5-107-4 2 Refer to SWPM 20-10-11 as an accepted procedure.

6 LACING TAPE 289T9001-21 1 Refer to SWPM 20-10-11 as an accepted procedure. 7 ID. TAPE 289U1225-10801 1 Refer to SWPM 20-10-11 as an accepted procedure. **FLAG NOTE NAME IDENTIFICATION QTY MORE DATA** 

**(SHEET 2 OF 2) FIGURE 47: REWORK/INSTALL NEW WIRING (WIRE BUNDLE W3845)**  Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 181 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

**FIGURE 47: REWORK/INSTALL NEW WIRING (WIRE BUNDLE W3845)**

This Figure applies to Group 16; Group 18, Configuration 2; Group 32-37: 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 289U1225-103 and supplemental kit 015U1808-3. Route new wiring following the existing wire bundle routing, refer to SWPM 20-10-11 and SWPM 20-10-19 as an accepted procedure. Use lacing tape as necessary.

**FLAG NOTE NAME IDENTIFICATION QTY MORE DATA**  1 ASSY -103 (W3845) 289U1225-103W 1 Refer to SWPM 20-10-11 as an accepted procedure. 1 5

19 J J 18 12

D41785P D41807P AE0304 AE0304

(2 LOCATIONS)

P180 PANEL-DC POWER DISTRIBUTION J D41786P 2AB-24 29 13 2AE-24 2AD-24 

# W3845

28 NC 2AC-24 W4815 (REF) W4588

-102 (2 LOCATIONS)

(POS 10) (POS 13) W4758 -104
4 3

NC (POS 9) 2 6

REFERENCE: 747 WIRING DIAGRAM 28-42-15, 30-41-31
ADDED WIRE OR NEW ROUTING

EXISTING WIRE DELETED WIRE OR FORMER ROUTING1743636

**(SHEET 1 OF 2) FIGURE 47: REWORK/INSTALL NEW WIRING (WIRE BUNDLE W3845)**  Original Issue: December 13, 2007 Revision 1: November 25, 2009 747-28A2281 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 182 of 182 

### BOEING SERVICE BULLETIN 747-28A2281

2 CONNECTOR, RECEPTACLE BACC45FN16- 24S6 1 New connector supplied in supplemental kit 015U1808-3. Refer to SWPM 20-60-06 as an accepted procedure. SCREW BACS12HN04U6 2 Hardware to install connector. WASHER NAS1149DN332J 2 NUT BACN10JC04CM 2 3 CONTACT, SOCKET BACC47CP1S 2 Refer to SWPM 20-61-11 as an accepted procedure. 4 CONTACT, SOCKET BACC47CP1S 2 Refer to SWPM 20-61-11 as an accepted procedure. 5 LACING TAPE 289T9001-91 1 Refer to SWPM 20-10-11 as an accepted procedure. 6 ID. TAPE 289U1225-10701 1 Refer to SWPM 20-10-11 as an accepted procedure. **FLAG NOTE NAME IDENTIFICATION QTY MORE DATA** 

**(SHEET 2 OF 2)**