Boeing ASB 747-28A2281: Revision 1, text

Text

From the PDF’s text layer: layout, tables and figures are lost. The PDF is the document.

Query with SQL

duckdb -csv -c "SELECT p.page, p.text_source, p.text, f.rights_holder, f.license
  FROM 'https://openairdocs.org/data/latest/service_document_file_page.parquet' p JOIN 'https://openairdocs.org/data/latest/service_document_file.parquet' f USING (file_sha256)
  WHERE p.file_sha256 = 'f88302e414dcd1dee140d4a2c740d2fd12bcc52ba78e3240e97b434d2791c0ba'
  ORDER BY p.page"

Prints the whole list as CSV. It reads the release’s Parquet files over HTTPS, so there’s nothing to download first. Install DuckDB to run it.

SELECT p.page, p.text_source, p.text, f.rights_holder, f.license
FROM 'https://openairdocs.org/data/latest/service_document_file_page.parquet' p JOIN 'https://openairdocs.org/data/latest/service_document_file.parquet' f USING (file_sha256)
WHERE p.file_sha256 = 'f88302e414dcd1dee140d4a2c740d2fd12bcc52ba78e3240e97b434d2791c0ba'
ORDER BY p.page

Run it at the DuckDB prompt, or in any tool that reads Parquet over HTTPS. More ways to query the release are on Use the data.

Page 1Open in PDF

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BOEING PROPRIETARY, CONFIDENTIAL, AND/OR TRADE SECRET Copyright © 2007 The Boeing Company Unpublished Work - All Rights Reserved Boeing claims copyright in each page of this document only to the extent that the page contains copyrightable subject matter.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.

Page 2Open in PDF

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

Page 3Open in PDF

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

Page 4Open in PDF

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) . . . . . . . . . . . . . . 181

Page 5Open in PDF

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 22 0 RT431-RT435 2 21 RT436 2 22 RT573-RT574, RT576 17 23 RT501, RT506- RT507, RT509 42 4 RT455 2 25

Page 6Open in PDF

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 22 9 RT502, RT504 2 30 RT551-RT556, RT591, RT641, RT643-RT645, RT671, RT691- RT692 23 1 RM081, RM083, RT411-RT412, RT609-RT630, RT753-RT755, RT945-RT949 13 2 RT605-RT608, RT752 23 3 RM146, RT783- RT784 83 4 RT777 11 35 RT751 2 36 RT601-RT604 2 37 Airplanes Affected Old Airp lane Group New Airplane Group

Page 7Open in PDF

— 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.

Page 8Open in PDF

— 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, 2009

Page 9Open in PDF

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.

Page 10Open in PDF

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 52.45

Page 11Open in PDF

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.

1325681

Page 12Open in PDF

BLANK PAGE

Pages 13–24 of 182