# Boeing Information Service Bulletin 747-28-2285: Revision 3 - Rights: © The Boeing Company. Filed by the FAA in regulations.gov docket FAA-2008-0090; AD 2011-06-03 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication. - Document: [Boeing Information Service Bulletin 747-28-2285](https://openairdocs.org/service-documents/boeing/sb-747-28-2285.md) - Title as filed: U.S. DOT/FAA - Service Bulletin - Pages: 90 - PDF: https://openairdocs.org/files/sha256/13/9b/139b034d8a3a3fe80cbd187e1afef5a3bdcdd3c61d5b54ba756750eeae09c7e9 - Page: https://openairdocs.org/service-documents/boeing/sb-747-28-2285/file/139b034d8a3a ## Text This text is OCR from a scan. OCR can misread letters and numbers. Each page's text from the PDF; open the PDF at a page with #page=N. ### Page 1 (OCR) (BOEING Commercial Group Airplane 747 Service Bulletin Number: 747-28-2285 Date: January 23, 2007 Revision 3: August 30, 2007 ATA System: 2811 SUBJECT: CONVERSION AIRPLANE - Boeing Converted Freighter Modification of a 747-400 Passenger (Combi) Airplane to a 747-400 BCF Airplane - Horizontal Stabilizer Tank Deactivation BOEING PROPRIETARY, CONFIDENTIAL, AND/OR TRADE SECRET Copyright © 2007 The Boeing Company Unpublished Work - All Rights Reserved Boeing claims copyright in each page of this document only to the extent that the page contains copyrightable subject matter.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. January 23, 2007 Revision 3: August 30, 2007 747-28-2285 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details 1 of 89 ### Page 2 (OCR) BOEING SERVICE BULLETIN 747-28-2285 BLANK PAGE BLANK PAGE January 23, 2007 Revision 3: August 30, 2007 747-28-2285 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 2 of 89 ### Page 3 (OCR) BOEING SERVICE BULLETIN 747-28-2285 Table of Contents Revision Transmittal Sheet. 5 Summary . 7 1. PLANNING INFORMATION. 11 A. Effectivity. 11 1. Airplanes 11 2. Spares Affected . 12 B. Concurrent Requirements 12 C. Reason 12 D. Description : 12 E. Compliance. 13 F. Approval. 14 G. Manpower 14 H. Weight and Balance Changes 14 Electrical Load Data 14 J. References. 15 1. Existing Data 15 2. Data supplied with this Service Bulletin: 16 3. Installation Drawings Used in the Preparation of this Service Bulletin: 17 4. Process Data: . 17 K Publications Affected. 17 Interchangeability and Intermixability of Parts 17 2. MATERIAL INFORMATION. 19 A. Material - Price and Availability. 19 B. Industry Support Information. 19 C. Parts Necessary For Each Airplane 19 1. Kits/Parts: . 19 2. Parts and Materials Supplied by the Operator: 21 3. Parts Modified and Reidentified: 21 4. Parts Removed and Not Replaced: 22 D. Parts Necessary to Change Spares 23 E. Special Tooling - Price and Availability. 23 Special Tooling Necessary to do this Service Bulletin 24 3. ACCOMPLISHMENT INSTRUCTIONS. 25 A. GENERAL INFORMATION 25 B. WORK INSTRUCTIONS.. 25 FIGURE 1: OVERHEAD CIRCUIT BREAKER PANEL P7-2 CHANGE 38 FIGURE 2: HORIZONTAL STABILIZER TANK AFT FUEL TRANSFER SYSTEM LOCATION 40 FIGURE 3: HORIZONTAL STABILIZER TANK FWD FUEL TRANSFER SYSTEM LOCATION 42 FIGURE 4: LEFT WING REFUELING PANEL P42 MODIFICATION 44 FIGURE 5: H.STAB FUEL PUMP LOW PRESSURE SWITCHES AND P85 PANEL CHANGE 46 FIGURE 6: HORIZONTALSTABILIZER TRANSFER PUMP MOTOR IMPELLER ASSY CHANGE 48 FIGURE 7: REMOTE ELECTRONIC UNIT CHANGES - E8 EQUIPMENT RACK 51 FIGURE 8: FUEL SYSTEM CARD FILE CHANGE 53 FIGURE 9: FUEL MANAGEMENT CONTROL PANEL CHANGE 54 FIGURE 10: DEACTIVATION OF TAIL TANK AT LEFT, CENTER, AND RIGHT EIU - E2-6 WIU WIRE Table of Contents January 23, 2007 Revision 3: August 30, 2007 747-28-2285 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 3 of 89 ### Page 4 (OCR) BOEING SERVICE BULLETIN 747-28-2285 CHANGE.. 55 FIGURE 11: REMOVAL OF HORIZONTAL STABILIZER TANK TRANSFER LINE. . 65 FIGURE 12: REWORK OF WIRE BUNDLES . . • . 73 FIGURE 13: FUEL MANAGEMENT CONTROL PANEL CHANGE . 76 FIGURE 14: DEACTIVATION OF TAIL TANK AT LEFT, CENTER, AND RIGHT EIU - E2-6 WIU WIRE CHANGE.... . 77 FIGURE 15: REWORK OF WIRE BUNDLES ... . 87 Table of Contents January 23, 2007 Revision 3: August 30, 2007 747-28-2285 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details 4 of 89 ### Page 5 (OCR) Commercial BOEING Group Airplane 747 Service Bulletin Number: 747-28-2285 Revision Transmittal Sheet Date: January 23, 2007 Revision 3: August 30, 2007 ATA System: 2811 SUBJECT: CONVERSION AIRPLANE - Boeing Converted Freighter Modification of a 747-400 Passenger (Combi) Airplane to a 747-400 BCF Airplane - Horizontal Stabilizer Tank Deactivation Revision 3, 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 revision 2 of this service bulletin. Revise approval statement from FAA approval to FAA/EASA approval. REASON FOR REVISION The changes in this service bulletin were requested by the operator. Revision 3, revises approval statement from FAA approval to FAA/EASA approval. Revision 2, deletes airplane RT075 (Group 3) configurations and figures to the service bulletin effectivity. Revision 1, adds airplane RT072 (Group 2) and RT075 (Group 3) to the service bulletin effectivity. 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: Jan. 23, 2007 | Revision 1: May 9, 2007 Revision 2: August 03, 2007 Revision 3: August 30, 2007 January 23, 2007 Revision 3: August 30, 2007 747-28-2285 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 5 of 89 ### Page 6 (OCR) BOEING SERVICE BULLETIN 747-28-2285 BLANK PAGE January 23, 2007 Revision 3: August 30, 2007 747-28-2285 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 6 of 89 ### Page 7 (OCR) @ BOEING Airplane Commercial Group 747 Service Bulletin Number: 747-28-2285 Summary Date: January 23, 2007 Revision 3: August 30, 2007 ATA System: 2811 SUBJECT: CONVERSION AIRPLANE - Boeing Converted Freighter Modification of a 747-400 Passenger (Combi) Airplane to a 747-400 BCF Airplane - Horizontal Stabilizer Tank Deactivation CONCURRENT REQUIREMENTS Refer to Paragraph 1.B., Concurrent Requirements. BACKGROUND As part of the special freighter conversion, the horizontal stabilizer fuel tank is to be deactivated and the fuel transfer line removed. This service bulletin provides instructions and a kit of parts to do that. ACTION (MC 0100MK4044, MC 0100MK4094) On P7-2 overhead circuit breaker panel, remove the Horizontal Stabilizer REFUEL & XFR circuit breakers C10125 and C10126. Rework the circuit breaker wiring. On the horizontal stabilizer refuel valve control unit, disconnect electrical connector, cap and stow wiring. At the FWD and AFT fuel isolation valves for the horizontal stabilizer transfer system, disconnect the electrical connector from each valve actuator, coil and stow wiring. Position manual override lever for affected valves, located on valve actuator, to closed position and lockwire to secure in place. On the P42 left wing refueling panel coil and stow wiring for indicator, switches and lights. Place "H.STAB TANK DEACTIVATED" placard above H.STAB indicator. On P85 panel, remove HOR STAB XFER/JETT PUMP circuit breakers C03141 and C03142. Remove HOR STAB XFER/JETT PUMP placard below the circuit breakers. Rework circuit breaker wire and pump wiring. Cap and stow plugs S1884 and S1885 for H.STAB fuel pump low pressure switches. On the horizontal stabilizer transfer / jettison pumps, remove two motor impeller assemblies located on the front spar of H. Stab tank. Install plugs and associated pins. On the E8 equipment rack, in the Remote Electronic Unit (REU), M7861, remove REU cover plate and H.STAB Individual Fuel Quantity Channel (IFQC) card. Re-install REU cover plate. Placard REU "INOP" and rework the wiring. On the Fuel System Card File, remove horizontal stabilizer transfer Single Point Sensor Control (SPSC) card and install cover assembly. Coil and stow SPSC card wiring. Insert jumper wire in Fuel System Card File. January 23, 2007 Revision 3: August 30, 2007 747-28-2285 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 7 of 89 ### Page 8 (OCR) BOEING SERVICE BULLETIN 747-28-2285 On P5 overhead panel, remove the Fuel Management Control Module (M00154) and rework the wiring. On the Fuel Quantity Indicating System (FQIS), reprogram FQIS card file for Horizontal Stabilizer absent. On the Wire Interface Unit (WIU), modify affected wire bundles at WU. On the fuel transfer line, remove and discard fuel transfer line from center wing tank to the horizontal stabilizer fuel tank, and install plugs. On the E2 equipment rack, make changes to the left, center, and right Electronic Instrument Unit (EIU) configuration pins to disable the Horizontal Stab Tank display and associated messaging on the Integrated Display Unit (IDS). EFFECTIVITY Group Operator Airplanes AFA RT071 AFA RT072 COMPLIANCE No compliance time is given. INDUSTRY SUPPORT INFORMATION Boeing Industry Support information is provided in Master Change 0100MK4044, and 0100MK4094. MANPOWER Man Hours are not listed in this Service Bulletin. They are negotiated separately between Boeing and the contracted modification facility. MATERIAL INFORMATION Negotiated Kits. January 23, 2007 Revision 3: August 30, 2007 747-28-2285 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 8 of 89 ### Page 9 (OCR) BOEING SERVICE BULLETIN 747-28-2285 POSITION MANUAL OVERRIDE LEVER FOR AFT ISOLATION VALVES TO CLOSE POSITION AND DI SCONNECT POSITION MANUAL OVERRIDE LEVER ELECTRICAL CONNECTOR FOR FWD ISOLATION VALVES TO FROM VALVE ACTUATOR CLOSE POSITION AND DISCONNECT ELECTRICAL CONNECTOR FROM VALVE ACTUATOR REMOVE 2 MOTOR REMOVE SPS CARD FROM IMPELLER UNITS. FUEL SYSTEM CARD FILE INSTALL PLUGS AND INSTALL COVER ASSY IN AFT EQUIPMENT RACK E8 REMOVE IFQC CARD IN REU. PLACARD REU INOP. REMOVE REMOVE FUEL 2 CIRUIT BREAKERS ON P85 MGMT PANEL PANEL. IN THE P5 REMOVE HORI ZONTAL FWDC STABILIZER FUEL TRANSFER LINE AND REMOVE REFUEL AND PLACARD "H. STAB TANK INSTALL PLUGS XFR STAB L AND DEACTIVATED" ON LEFT STAB R CIRCUIT WING REFUELING P42 PANEL BREAKERS ON P7 PANEL REMOVE RELAYS AND CHANGE THE WIRING AT THE P7, P414 FUEL SYSTEM CARD FILE, E2-6 SHELF AND THE P54 PANEL. REVISE PIN 1302596 PROGRAMMING TO THE LEFT, CENTER AND RIGHT EIU ON SHELF 6 OF E2-6. January 23, 2007 Revision 3: August 30, 2007 747-28-2285 BOEING PROPRIETARY - Copyright © Upublished Work - See page 1 for details. 9 of 89 ### Page 10 (OCR) BOEING SERVICE BULLETIN 747-28-2285 BLANK PAGE January 23, 2007 Revision 3: August 30, 2007 747-28-2285 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 10 of 89 ### Page 11 (OCR) Commercial Q BOEING Airplane Group 747 Service Bulletin Number: 747-28-2285 Date: January 23, 2007 Revision 3: August 30, 2007 ATA System: 2811 SUBJECT: CONVERSION AIRPLANE - Boeing Converted Freighter Modification of a 747-400 Passenger (Combi) Airplane to a 747-400 BCF Airplane - Horizontal Stabilizer Tank Deactivation 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. Refer to Master Change 0100MK4044, and 0100MK4094 for data about this change. GROUP CONFIGURATION DESCRIPTION 747-400 airplane RT071 to be modified to a 747-400SF. 2 747-400 airplane RT072 to be modified to a 747-400SF. Airplane models: 747-400 IDENTIFICATION BY CUSTOMER, CUSTOMER CODE, GROUP AND VARIABLE NUMBER AIR FRANCE (AFA) 1 RT071 2 RT072 IDENTIFICATION BY VARIABLE NUMBER Variable Group RT071 1 RT072 2 January 23, 2007 Revision 3: August 30, 2007 747-28-2285 BOEING PROPRIETARY - Copyright & Unpublished Work - See page 1 for details. 11 of 89 ### Page 12 (OCR) BOEING SERVICE BULLETIN 747-28-2285 2. Spares Affected None. B. Concurrent Requirements The service bulletin(s) listed below must be done before or at the same time as this service bulletin: Company Service Bulletin Description Boeing 747-28-2182 "FUEL - INDICATING - FUEL QUANTITY PROCESSOR AND REMOTE ELECTRONICS UNIT CHANGE" Boeing 747-00-2008 (RT071) "ADMINISTRATIVE GENERAL - Aircraft - General - Conversion Airplane - Boeing Converted Freighter Modification of a 747-400 Passenger/Combi Airplane to a 747-400 BCF Airplane - Collector Service Bulletin." Boeing 747-00-2059 (RT072) "ADMINISTRATIVE GENERAL - Aircraft - General - Conversion Airplane - Boeing Converted Freighter Modification of a 747-400 Passenger/Combi Airplane to a 747-400 BCF Airplane - Collector Service Bulletin." C. Reason As part of the special freighter conversion, the horizontal stabilizer fuel tank is to be deactivated and the fuel transfer line removed. This service bulletin provides instructions and a kit of parts to do that. Revision 3, revises approval statement from FAA approval to FAA/EASA approval. Revision 2, deletes airplane RT075 (Group 3) configurations and figures to the service bulletin effectivity. Revision 1 is adding RT072 (Group 2) and RT075 (Group 3) airplanes to this service bulletin effectivity. D. Description On P7-2 overhead circuit breaker panel, remove the Horizontal Stabilizer REFUEL & XFR circuit breakers C10125 and C10126. Rework the circuit breaker wiring. On the horizontal stabilizer refuel valve control unit, disconnect electrical connector, cap and stow wiring. At the FWD and AFT fuel isolation valves for the horizontal stabilizer transfer system, disconnect the electrical connector from each valve actuator, coil and stow wiring. Position manual override lever for affected valves, located on valve actuator, to closed position and lockwire to secure in place. On the P42 left wing refueling panel coil and stow wiring for indicator, switches and lights. Place "H.STAB TANK DEACTIVATED" placard above H.STAB indicator. On P85 panel, remove HOR STAB XFER/JETT PUMP circuit breakers C03141 and C03142. Remove HOR STAB XFER/JETT PUMP placard below the circuit breakers. Rework circuit breaker wire and pump wiring. Cap and stow plugs S1884 and S1885 for H.STAB fuel pump low pressure switches. January 23, 2007 Revision 3: August 30, 2007 747-28-2285 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 12 of 89 ### Page 13 (OCR) BOEING SERVICE BULLETIN 747-28-2285 On the horizontal stabilizer transfer / jettison pumps, remove two motor impeller assemblies located on the front spar of H. Stab tank. Install plugs and associated pins. On the E8 equipment rack, in the Remote Electronic Unit (REU), M7861, remove REU cover plate and H.STAB Individual Fuel Quantity Channel (IFQC) card. Re-install REU cover plate. Placard REU "INOP" and rework the wiring. On the Fuel System Card File, remove horizontal stabilizer transfer Single Point Sensor Control (SPS) card and install cover assembly. Coil and stow SPSC card wiring. Insert jumper wire in Fuel System Card File. On P5 overhead panel, remove the Fuel Management Control Module (M00154) and rework the wiring. On the Fuel Quantity Indicating System (FQIS), reprogram FQIS card file for Horizontal Stabilizer absent. On the Wire Interface Unit (WIU), modify affected wire bundles at WIU. On the fuel transter line, remove and discard fuel transter line from center wing tank to the horizontal stabilizer fuel tank, and install plugs. On the E2 equipment rack, make changes to the left, center, and right Electronic Instrument Unit (EIU) configuration pins to disable the Horizontal Stab Tank display and associated messaging on the Integrated Display Unit (IDS). Revision 3 - revises approval statement from FAA approval to FAA/EASA approval. Revision 3 - No more work is necessary on airplanes changed as shown in the revision 2 of this service bulletin. Revision 2 - deletes airplane RT075 (Group 3) configurations and figures to the service bulletin effectivity. Revision 2 - No more work is necessary on airplanes changed as shown in the revision 1 of this service bulletin. Revision 1 - is adding RT072 (Group 2) and RT075 (Group 3) airplanes to this service bulletin effectivity. Revision 1 - No more work is necessary on airplanes changed as shown in the original release of this service bulletin. E. Compliance No compliance time is given. January 23, 2007 Revision 3: August 30, 2007 747-28-2285 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 13 of 89 ### Page 14 (OCR) BOEING SERVICE BULLETIN 747-28-2285 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 Man Hours are not listed in this Service Bulletin. They are negotiated separately between Boeing and the contracted modification facility. H. Weight and Balance Changes Boeing requires that, because of the magnitude and uniqueness of major modification programs, the total airplane weight and center of gravity will be determined by actual weighing after all modifications are complete and prior to delivery. The actual data will be recorded and placed in Chapter 2 of the Weight and Balance Manual. I. Electrical Load Data Refer to Document Number D828B006-1001 for Electrical Load Data. NOTE: The electrical loads of AFA Model 747-400B airplanes RT071, and RT072 as specified in document D281U002-422 have been reviewed and the following loads were deleted. 1. Direct Current (DC) Loads Airplanes Nomenclature Connected Circuit Bus Load Breaker RT071, Refuel and Transfer 1.40 10125 DC1P7 RT072 Stabilizer - Left Refuel and Transfer 1.40 10126 DC2P7 Stabilizer - Right January 23, 2007 Revision 3: August 30, 2007 747-28-2285 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 14 of 89 ### Page 15 (OCR) BOEING SERVICE BULLETIN 747-28-2285 2. Alternating Current (AC) Loads Airplanes Nomenclature Connected Load Circuit Bus Breaker RT071, Horizontal Stabilizer 4.600KVA.76PF 3141 GSB-3 RT072 Boost Pump - Fwd Horizontal Stabilizer 4.600KVA. 76PF 3142 AC2P85P183 Boost Pump - Aft J. References 1. Existing Data: a. Engineering Change Memo MC 0100MK4044, and MC 0100MK4094. b. 747-400 Aircraft Maintenance Manual (AMM) 12-11-10, 20-11-06, 20-11-16, 24-22-00, 28-11-00, 28-17-01, 28-17-04, 28-17-06, 28-17-10, 28-21-12, 28-22-00, 28-26-00, 28-41-00, 28-41-17, 29-11-00, 32-00-30 c. 747-400 Wiring Diagram Manual (WDM) 24-51-26, 24-51-64, 24-54-23, 28-21-11, 28-21-12, 28-21-13, 28-21-21, 28-21-23, 28-21-24, 28-21-25, 28-21-26, 28-21-27, 28-21-28, 28-21-29, 28-21-30, 28-21-31, 28-42-15, 28-43-12, 28-54-13, 31-61-12, 31-61-22, 31-61-32 d. 747-400SF Structural Repair Manual (SRM) 51 e. Standard Wiring Practices Manual (SWPM) 20-10-11, 20-10-12, 20-20-00 f. Boeing Parts Standards Document, D-590. g. Electrical Load Data Document, D828B006-1001. h. Boeing Service Bulletins: Refer to Paragraph 1.B., Concurrent Requirements. January 23, 2007 Revision 3: August 30, 2007 747-28-2285 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 15 of 89 ### Page 16 (OCR) BOEING SERVICE BULLETIN 747-28-2285 2. Data supplied with this Service Bulletin: NOTE: 1. The Module Parts List (MPL) drawings listed below will not be shipped with this service bulletin. Drawing access will be given to the modification site through My Boeing Fleet (MBF). This was negotiated by the operator and modification facility under Master Change 0100MK4044, and 0100MK4094. 2. Within the MPL is a list of the retrofit and/or production drawing picture sheets required to facilitate installation of the identified part, assembly or installation as given in this service bulletin Group 1: RMC 800B0289-1 MPL Title Drawing Sheet Rev Number 834B0401-1001 FUEL TANK DEACTIVATION - 834B0401 IMPL E HORIZONTAL STABILIZER 148U0002 1 A 148U0002 DL 284U1255 1 C 284U1255 DL 284U4219 7 344U1011 4 344U1011 DL 344U1014 1 344U1014 DL B 344U1022 1 K 344U1022 2 G 344U1022 DL 344U1023 2 344U1023 DL Group 2: RMC 800B0299-1 MPL Title Drawing Sheet Rev Number 834B0401-1001 FUEL TANK DEACTIVATION - 834B0401 MPL HORIZONTAL STABILIZER 148U0002 1 148U0002 IDL 284U1255 1 C 284U1255 IDL 284U4219 7 344U1011 4 January 23, 2007 Revision 3: August 30, 2007 747-28-2285 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 16 of 89 ### Page 17 (OCR) BOEING SERVICE BULLETIN 747-28-2285 Group 2: RMC 800B0299-1 MPL Title Drawing Sheet Rev Number 344U1011 DL 344U1014 1 B 344U1014 DL B 344U1022 1 344U1022 2 G 344U1022 DL 344U1023 2 344U1023 DL 3. Installation Drawings Used in the Preparation of this Service Bulletin: None. 4. Process Data: Boeing Process specifications referred to on the drawings are not given in this service bulletin since these procedures are frequently used as standard shop practices. K. Publications Affected Publication Chapter-Section 747 FAA Approved Airplane Flight Manual 747 Operations Manual 6.20, L.10, 12.10, 12.20, 12.30, NNC.12, NP.21 747 Maintenance Manual 11-13, 28-10, 28-30, and 28-40 (Dual configuration already exists) 747 Wiring Diagram Manual 24-51, 24-54, 28-21, 28-22, 28-27, 28-41, 28-42, 28-43, 28-51, and 31-61 747 Fault Reporting Manual 28-10 747 Fault Isolation Manual 28 CMCS Index, 28 EICAS Index 747 Illustrated Parts Catalog 28-22, 28-26, and 28-41 Ramp Maintenance Manual 28-00 L. Interchangeability and Intermixability of Parts Refer to Paragraph 2.C., Parts Necessary For Each Airplane, for interchangeability and intermixability information. January 23, 2007 Revision 3: August 30, 2007 747-28-2285 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 17 of 89 ### Page 18 (OCR) BOEING SERVICE BULLETIN 747-28-2285 BLANK PAGE January 23, 2007 Revision 3: August 30, 2007 747-28-2285 BOEING PROPRIETARY - Copyright @ Unpublished Work - See page 1 for details. 18 of 89 ### Page 19 (OCR) BOEING SERVICE BULLETIN 747-28-2285 2. MATERIAL INFORMATION A. Material - Price and Availability Boeing supplies the kits shown in Paragraph 2. C., Parts Necessary For Each Airplane. This was negotiated with the operator under Master Change 0100MK4044, and 0100MK4094. B. Industry Support Information Boeing Industry Support Information is provided in Master Change 0100MK4044, and 0100MK4094. 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. January 23, 2007 Revision 3: August 30, 2007 747-28-2285 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 19 of 89 ### Page 20 (OCR) BOEING SERVICE BULLETIN 747-28-2285 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. Kit 834B0401 QTY New Part Existing Part Number 1001 Name Number Notes 834B0401-1001 FUEL TANK DEACTIVATION - (a) HORIZONTAL STABILIZER 285U0096-6 1 COVER ASSY 65B02637-22 1 BLANKING PLATE 65B02637-28 1 GASKET 835B0004-1 1 PLUG - CONNECTOR FITTING, HST FUEL TRANSFER LINE 835U0001-1 2 MACHINED PARTS DETAILS- PLUG 835U0002-1 2 MACHINED PARTS DETAILS-PIN AS5168W32 2 PLUG, FLARED TUBE (b) BAC27EFS595 1 MARKER BAC27TFDE0013 1 VINYL DECAL- (INOP) MS21913W32 1 PLUG, FLARELESS (D) (C) (a) Kit has more parts than necessary. Discard extra parts or keep them for other use. (b) Optional to AS5168W32 in the forward fitting 344U0014 only. (c) MS21913W32 is a substitute for AS5168W32 Kit 826B4260 QTY Existing Part New Part Number Name Number Notes 829B9006-14 1 Wire January 23, 2007 Revision 3: August 30, 2007 747-28-2285 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details 20 of 89 ### Page 21 (OCR) BOEING SERVICE BULLETIN 747-28-2285 2. Parts and Materials Supplied by the Operator: Part Number / Specification QTY Name Notes 2645 4 Plug Button (a) (a) PALL AEROPOWER CORP 5775 RIO VISTA CLEARWATER FL 33760 USA 727-539-8448 3. Parts Modified and Reidentified: None January 23, 2007 Revision 3: August 30, 2007 747-28-2285 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 21 of 89 ### Page 22 (OCR) BOEING SERVICE BULLETIN 747-28-2285 4. Parts Removed and Not Replaced: Existing Part Number Name QTY Notes 60-72101-1 or 60-72102-4 Motor-Impeller Assembly 2 Refer to 747-400 AMM 28-17-04 (Boeing Part Number (a) 60B92603-22 or 60B92603-26) S344T002-8 Horizontal Stabilizer 1 Refer to 747-400 AMM 28-17-10 Transfer Single Point (a) Sensor Control Card (SPSC) A3 60B92018-207 Individual Fuel Quantity 1 Refer to 747-400 AMM 28-41-17 Channel (IFQC) Card (a) Y5XA1 R7391 Relay 1 Located on P54 panel 10-60536-25 (opt 10-60536-22) Hose Assy 1 34400000-6 Fitting 1 344U1022-10 Tube Assy 1 344U1022-11 Tube Assy 344U1022-12 Tube Assy 344U1022-13 Tube Assy 1 344U1022-14 Tube Assy 1 344U1022-2 Tube Assy 1 344U1022-22 Sleeve 1 344U1022-23 Shroud 1 344U1022-25 Tube Assy 344U1022-26 Tube Assy 1 344U1022-5 Tube Assy 3 344U1022-8 Tube Assy 1 34401022-9 Tube Assy 1 6305B374S48-03 Nut Assy 2 6305B381S48-1 Shroud Connector 1 63211-48 Coupling Assy 1 69B92447-39 Spacer 1 (b) 69B92447-52 Spacer 1 (b) 69B92447-8 Spacer 1 | (b) AN735D48 Clamp, Loop 20 AS1712D48 Coupling 11 BACB30NM3HK7 Bolt 6 BACC10CC48 Clamp, U-style BACC10CC48S Clamp 1 (b) BACC10EW48A Clamp, U-style 60 January 23, 2007 Revision 3: August 30, 2007 747-28-2285 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 22 of 89 ### Page 23 (OCR) BOEING SERVICE BULLETIN 747-28-2285 Existing Part Number Name QTY Notes BACC10EW48B Clamp, U-style 60 BACJ40A20-3 Bonding Jumper 2 BACJ40A20-4 Bonding Jumper 4 BACJ40A20-5 Bonding Jumper 9 BACS40R008E048F Shim, Laminated 1 MS24665-144 Pin 4 MS29513-234 O-ring 2 MS29513-241 O-ring 1 MS29513-338 O-ring 26 NAS1523AA3R O-ring 6 344U0000-2 Fitting 1 MS29513-241 O-ring 1 AP7102D32-1 (opt Union 1 AFP720D3232 or AP7102D32 or MS21900D32) MS29512-32 O-ring 1 344U0018-8 (opt 344U0018-5) Tube Assy 1 10-60536-23 Hose Assy 1 BACC18AD7 Circuit Breaker 2 BAC27EFS595 Marker 1 Refer to 747-400 AMM 20-11-06 BACC18AE25 Circuit Breaker 2 BAC27EEL23764 Marker 1 Refer to 747-400 AMM 20-11-06 233U3100-247 Fuel Management Panel 1 Assy (a) Keep the part if there are other uses for it. (b) Quantity used varies. D. Parts Necessary to Change Spares None. E. Special Tooling - Price and Availability The operator can supply the tools shown in Paragraph 2.F., Special Tooling Necessary to do this Service Bulletin. Tool price and supply data are not given. January 23, 2007 Revision 3: August 30, 2007 747-28-2285 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details 23 of 89 ### Page 24 (OCR) BOEING SERVICE BULLETIN 747-28-2285 F. Special Tooling Necessary to do this Service Bulletin To get the tools shown below, refer to Paragraph 2.E., Special Tooling - Price and Availability. Maintenance and overhaul tools in the manuals shown in Paragraph 1.J., References, can also be necessary. Examine operator tool supply to make sure all necessary tools are available. Tool Kit Number Name Shop Supply ESDS Wrist Strap (1 required) Shop Supply Jumper Wire (4 required) January 23, 2007 Revision 3: August 30, 2007 747-28-2285 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 24 of 89 ### Page 25 (OCR) BOEING SERVICE BULLETIN 747-28-2285 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: Manual titles are referred to by acronyms. Refer to Paragraph 1.J., References, for definition of the acronyms. 2. Obey all of the warnings and cautions given in the specified manual sections. Unless shown differently, these dimensions and tolerances are used: - Tolerance on linear dimensions, other than rivet and bolt edge margins, is plus or Tolerance on rivet and bolt edge margin is plus or minus 0.05 inch Angular tolerance is plus or minus 2 degrees Hole dimensions for standard solid rivets are given in 747 Structural Repair Manual, Chapter 51(747-400SF SRM 51). Torque limits to tighten nuts and bolts are given in 747 Structural Repair Manual, Chapter 51 (747-400SF SRM 51). 4. For approved fastener and process material substitutions, refer to 747 Structural Repair Manual, Chapter 51(747-400SF SRM 51). 5. Refer to the Boeing Standard Wiring Practices Manuals 20-10-11 and 20-10-12 for the wire installation procedures (SWPM 20-10-11and SWPM 20-10-12). If the length of fasteners specified in this service bulletin do not meet the installation standards, fasteners of the same specification, or an approved substitute, one grip length longer or shorter may be used. 7. Refer to the BSWPM 20-20-00 (SWPM 20-20-00) the necessary grounding procedures. This is the same as BAC5117 which is used on the drawings. B. WORK INSTRUCTIONS Horizontal Stabilizer Tank Preparation 1. Defuel Horizontal Stabilizer Tank (HST) per 747-400 AMM 28-26-00. In addition, defuel Main Tanks 2 and 3 sufficiently to allow the Fill/Jettison Manifold to drain. 2. Sump HST per 747-400 AMM 12-11-10. Open the following circuit breakers and attach DO-NOT-CLOSE tag on the P7 Overhead Circuit Breaker Panel: January 23, 2007 Revision 3: August 30, 2007 747-28-2285 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 25 of 89 ### Page 26 (OCR) BOEING SERVICE BULLETIN 747-28-2285 a. 7H25 REFUEL & XFR STAB L. b. 7H26 REFUEL & XFR STAB R. Manually open one of the horizontal stabilizer isolation valves at the rear spar of the center wing tank. Refer to 747-400 AMM 28-17-01. NOTE: This will let fuel from the fuel transfer line drain into main tanks 2 and 3. 5. On the flight deck push FUEL synoptic EICAS display switch. 6. On the lower EICAS display, record the fuel quantity for all displayed tanks. 7. After the fuel has drained from the fuel transfer line, manually close the horizontal stabilizer isolation valve that was opened. 8. Close the circuit breakers opened in step 3 above. 9. Purge the fuel tanks as specified in 747-400 AMM 28-11-00. Prepare the horizontal stabilizer for entry. 10. Clean and corrosion protect HST as necessary to prepare for deactivation in accordance with 747-400 AMM 28-11-00. 11. Close HST (do not put fuel into the HST). 12. Put the stabilizer in the neutral trim position (3 units of trim) as follows: a. Supply electrical power. Refer to the 747-400 AMM 24-22-00. WARNING: MAKE SURE THAT PERSONS AND EQUIPMENT ARE CLEAR OF ALL CONTROL SURFACES BEFORE YOU SUPPLY HYDRAULIC POWER AILERONS, RUDDERS, ELEVATORS, FLAPS, SPOILERS, LANDING GEAR, AND THRUST REVERSERS CAN MOVE QUICKLY WHEN YOU SUPPLY HYDRAULIC POWER. THIS CAN CAUSE INJURY TO PERSONS AND DAMAGE TO EQUIPMENT. b. Supply hydraulic power. Refer to the 747-400 AMM 29-11-00. c. Use the STAB TRIM ALTN switches to set the horizontal stabilizer to the neutral rig position (3 units of trim). d. Set the STAB TRIM 2 and 3 switches on the control stand to CUTOUT. e. On the P7 panel, open the L STAB TRIM S/O VLV circuit breaker (position E7) and the R STAB TRIM S/O VLV circuit breaker (position E20) and attach DO-NOT-CLOSE tabs. Set all FLT CONTROL HYD POWER TAIL switches on the P461 pilots overhead maintenance panel to SHUTOFF. January 23, 2007 Revision 3: August 30, 2007 747-28-2285 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 26 of 89 ### Page 27 (OCR) BOEING SERVICE BULLETIN 747-28-2285 g. On the P180 panel, open these circuit breakers and attach DO-NOT-CLOSE tags: (1) ELEV/RUD VLV SYS 2, position E7 (2) ELEV/RUD VLV SYS 4, position E22 (3) ELEV/RUD VLV SYS 1, position H8 (4) ELEV/RUD VLV SYS 3, position H23 13. Install the gear door locks. Refer to the 747-400 AMM 32-00-30. 14. Remove hydraulic power. Refer to the 747-400 AMM 29-11-00. 15. Remove electrical power. Refer to the 747-400 AMM 24-22-00. Horizontal Stabilizer Tank Deactivation Procedure 1. The following circuit breakers are to be opened and remain open throughout the duration of this HST deactivation procedure. Location Name Circuit Breaker Panel Position P-6 D05 FUEL QTY 1 C10123 P-6 D06 FUEL QTY 2 C10124 P180 M08 FUELING VALVE 2 C00086 P180 M09 FUELING LTS-HOT or FUELING PWR-HOT BATH C01143 P180 C25 FUELING LIGHTS PANEL (if installed) C10746 P180 C26 FUELING LTS RECP (if installed) C10747 P414 F17 FUELING VALVE C00090 P414 F22 LIGHT FUELING or FUELING POWER C01142 P415 M14 FUEL OVERFILL CONT C00062 P6 F06 FUEL SYS MGMT CH 1 C10129 P6 F08 FUEL SYS MGMT CH 2 C10130 E2-6 F9 LEFT elO C10174 E2-6 F10 CENTER EU C10175 E2-6 F15 RIGHT EIU C10176 2. Remove and install plugs for REFUEL & XFR STAB L circuit breaker C10125 and REFUEL & XFR STAB R circuit breaker C10126. Refer to Figure 1. 3. Modify wire bundle W0007 on P7 Overhead Circuit Breaker Panel. a. Group 1: Figure 12 b. Group 2: Figure 15 January 23, 2007 Revision 3: August 30, 2007 747-28-2285 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 27 of 89 ### Page 28 (OCR) BOEING SERVICE BULLETIN 747-28-2285 4. Modify wire bundles W4092 and W4094 on Overhead Circuit Breaker Panel P7. a. Group 1: Figure 12 b. Group 2: Figure 15 5. Change AFT Horizontal Stabilizer Fuel Isolation Valves as follows: a. Locate two isolation valves on rear spar of H. Stab tank, L aft valve (V435), Raft valve (V436). Refer to Figure 5. b. Disconnect electrical connector from valve actuator. Rework wire bundle W4607 and W4618. (1) Group 1: Figure 12 (2) Group 2: Figure 15 c. Position manual override lever for affected valves, located on valve actuator, to closed position and LOCKWIRE. Refer to Figure 2 for location. 6. Change FWD Horizontal Stabilizer Fuel Isolation Valves as follows: a. Locate two isolation valves on rear spar of center tank, L fwd valve (V439), R fwd valve (V440). Refer to Figure 3 for location. b. Disconnect electrical connector from valve actuator. Rework wire bundle W4611 and W4641. (1) Group 1: Figure 12 (2) Group 2: Figure 15 c. Position manual override lever for affected valves, located on valve actuator, to closed position and LOCKWIRE. Refer to Figure 3 for location. 7. Modify wire bundle W0144 on Pressure Fueling Control Panel P42. a. Group 1: Figure 12 b. Group 2: Figure 15 Coil and stow wiring for indicator, switches, and lights. 8. Install the "H.STAB TANK DEACTIVATED" placard (marker) above H.STAB indicator, Part Number BAC27EFS595 as given in 747-400 AMM 20-11-06-404-012 ALUMINUM FOIL MARKER INSTALLATION. Refer to Figure 4. 9. Remove relay R7391 and rework wire bundle W0076 on Center Equipment Panel P54. a. Group 1: Figure 12 b. Group 2: Figure 15 January 23, 2007 Revision 3: August 30, 2007 747-28-2285 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 28 of 89 ### Page 29 (OCR) BOEING SERVICE BULLETIN 747-28-2285 10. Modify wire bundle W4606 on the Horizontal Stabilizer Refuel Valve Control Unit. Refer to Figure 2 for component location. a. Group 1: Figure 12 b. Group 2: Figure 15 11. Remove "HOR STAB XFER/JETT PUMP L" circuit breaker C03141 and "HOR STAB XFER/ JETT R" circuit breaker C03142. Remove HOR STAB XFER/JETT PUMP LEFT and RIGHT placard as shown in Figure 5. 12. Modify wire bundle W2018 on AFT MISC Circuit Breaker Panel P85. a. Group 1: Figure 12 b. Group 2: Figure 15 13. Modify wire bundles W4601 and W4602 on Left AFT Equipment Center E8. Cap and stow pump wiring and plugs S1884 and S1885 as indicated a. Group 1: Figure 12 b. Group 2: Figure 15 14. Remove fuel transfer line and install plugs as shown in Figure 11. 15. Change Horizontal Stabilizer Motor Impeller Assemblies as shown in Figure 6 and as follows: a. Remove two motor impeller assemblies located on the front spar of HST. Refer to 747-400 AMM 28-17-04. b. Install two plugs and two associated pins and do the following: (1) Install new packing MS29513-007, lubricated with petrolatum, into groove on pin, part number 835U0002-1. (2) Put end of pin with packing into housing on top of unit. (3) Install new packing M25988-1-238, lubricated with petrolatum into groove on plug, part number 835U0001-1. (4) Carefully push the plug into housing. Make sure that smallest hole is in line with pin on housing. (5) Put the bonding clips) with the bonding jumper(s) attached into position on the plug. CAUTION: ENSURE SOCKET HEAD MOUNTING SCREWS ARE P/N MS24674-9 OR EQUIVALENT ALTERNATIVE (THREAD LENGTH 15MM). QUANTITY (1) WASHER P/N NAS1149DN832J MUST BE USED AT EACH SCREW LOCATION. (Б) Install socket head screws and washers at five locations to fasten the bonding clips and plug, part number 835U0001-1, to the pump housing. January 23, 2007 Revision 3: August 30, 2007 747-28-2285 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 29 of 89 ### Page 30 (OCR) BOEING SERVICE BULLETIN 747-28-2285 Install nut, part number BACN10JC06C, and washer, part number NAS620C6 to the threaded end on pin to secure pin in housing. 16. Modify the Remote Electronic Unit (REU) at M7861 in Equipment Center E8 as shown in Figure 7 and as follows: a. Remove the "H.STAB INDIVIDUAL FUEL QUANTITY CHANNEL (IFQC) CARD", part number 60B92018-207 in accordance with 747-400 AMM 28-41-17. b. Install the cover plate on the REU, M7861 and tighten the four captive screws. c. Placard REU "INOP". d. Modify wire bundle W3851 on AFT Left Equipment Center E8. (1) Group 1: Figure 12 (2) Group 2: Figure 15 17. Modify wire bundle W3890 and "reprogram FQIS card file for Horizontal Stabilizer absent", as referenced in Figure 11. a. Group 1: Figure 12 b. Group 2: Figure 15 NOTE: Reprogram FQIS card file for Horizontal Stabilizer absent 18. Change Fuel System Card File as follows: a. Remove horizontal stabilizer Single Point Sensor Control Card (SPS) A3, in accordance with 747-400 AMM 28-17-10 and Figure 8. b. Install cover assembly, part number 285U0096-6, at SPSC installation location. Refer to Figure 8. Modify wire bundle W4764 by inserting jumper wire in Fuel System Card File. (1) Group 1: Figure 12 (2) Group 2: Figure 15 d. Modify wire bundle W4974 on shelf 6 of Main Right Equipment Center E2-6. (1) Group 1: Figure 12 (2) Group 2: Figure 15 19. Change P5 Fuel Management Control Panel as follows: a. Remove the Fuel Management Control module (M00154) from the P5. (1) Group 1: Figure 9 January 23, 2007 Revision 3: August 30, 2007 747-28-2285 BOEING PROPRIETARY - Copyright @ Unpublished Work - See page 1 for details. 30 of 89 ### Page 31 (OCR) BOEING SERVICE BULLETIN 747-28-2285 (2) Group 2: Figure 13 b. Modify wire bundles W4751 and W4753 on Pilots Overhead Panel P5. (1) Group 1: Figure 12 (2) Group 2: Figure 15 20. Deactivate tail tank at WIU for the left, center, and right Electronic Instrument Units (EIU) E2-6 WIU modifications. Group 1: Deactivate tail tank at WIU for the left, center, and right Electronic Instrument Units (EIU) E2-6 WIU modifications. referred in Figure 10. (1) Modify wire bundle W4970, W4980, W4990 on shelf 6 of the Main Right Equipment Center E2-6 for the left, center, and right ElUs as shown in Figure 12. Group 2: Deactivate tail tank at WIU for the left, center, and right Electronic Instrument Units (EIU) E2-6 WIU modifications. referred in Figure 14 Modify wire bundle W4970, W4980, W4990 on shelf 6 of the Main Right Equipment Center E2-6 for the left, center, and right ElUs as shown in Figure 15. 21. Close all circuit breakers that were opened in step 1 above. WARNING: MAKE SURE THAT PERSONS AND EQUIPMENT ARE CLEAR OF ALL CONTROL SURFACES BEFORE YOU SUPPLY HYDRAULIC POWER. ALERONS, RUDDERS, ELEVATORS, FLAPS, SPOILERS, LANDING GEAR, AND THRUST REVERSERS CAN MOVE QUICKLY WHEN YOU SUPPLY HYDRAULIC POWER. THIS CAN CAUSE INJURY TO PERSONS AND DAMAGE EQUIPMENT. 22. Supply electrical power to airplane. Refer to the 747-400 AMM 28-22-00. Horizontal Stabilizer Tank Functional Check 1. Do the following steps to check the IDS program pin configuration: NOTE: Only check the NON-X values shown in steps c, e, and g below. The "X" values in the program pin codes shown below are not pertinent to this change and may be any value. a. Display the configuration maintenance page on the CMC display unit. b. Put the Captain's and First Officer's source select switches in the L position. c. Make sure that the following is displayed: IDS PROGRAM PINS: 1/XXXX X0XX/32 33/XXXX XX/56 1/P d. Put the Captain's and First Officer's source select switches in the C position. January 23, 2007 Revision 3: August 30, 2007 747-28-2285 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 31 of 89 ### Page 32 (OCR) BOEING SERVICE BULLETIN 747-28-2285 e. Make sure that the following is displayed: IDS PROGRAM PINS: 1/XXXX XOXX/32 33/XXXX XX/56 1/P f. Put the Captain's and First Officer's source select switches in the R position. Make sure that the following is displayed: IDS PROGRAM PIN: 1/XXXX XOXX/32 33/XXXX XX/56 1/P 2. Do an electrical test of the P42 panel as follows. The airplane must be in the ground mode for this test: a. Open these circuit breakers on the P6 panel: CB NO. LOC Nomenclature C10123 D05 FUEL QTY 1 C10124 D06 FUEL QTY 2 b. Open these circuit breakers on the P414 panel: CB NO. LOC Nomenclature C00090 F17 FUELING VALVE C01142 F22 FUELING PWR C10131 M33 HOR STAB SUMP DRAIN VLV c. Open these circuit breakers on the P180-1 panel: CB NO. LOC Nomenclature C00086 M08 FUELING VALVE 2 C01143 M09 FUELING LTS - HOT d. Open the P42 fueling panel door. e. On the P42 panel, put the battery switch in the NORM position. 1. On the P414 panel, position F22, close the circuit breaker C01142, FUELING PWR. g- On the P42 panel, push and hold the GAUGES TEST switch. See that all the fuel quantity indicator displays read 888.8. The horizontal stabilizer indicator will remain blank. h. Release the GAUGES TEST switch. i. Set the SELECT QTY value to 222.2. J- Press the PRESELECT SET QTY switch to the TOTAL position and hold for more than 2 seconds. January 23, 2007 Revision 3: August 30, 2007 747-28-2285 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 32 of 89 ### Page 33 (OCR) BOEING SERVICE BULLETIN 747-28-2285 k. Release the PRESELECT SET QTY switch. See that the quantity 222.2 can be seen in the bottom display of the TOTAL FUEL indicator. m. On the flight deck, push the FUEL synoptic EICAS display switch. n. On the lower EICAS display, see that the fuel quantities are within +/- 200 Ibs (+/- 100 kgs) of the quantities recorded in Step 6 of the Horizontal Stabilizer Tank Preparation Procedure. NOTE: Horizontal Stabilizer tank fuel quantity will not be displayed. o. On the P414 panel, position F22, open the circuit breaker C01142, FUELING PWR. p. On the P42 panel, see that the refuel indicator displays go blank. q. On the P42 panel, put the battery switch in the BATT position. r. On the P180-1 panel, position M09, close the circuit breaker C01143, FUELING PWR-HOT BAT. S. On the P42 panel, see that the refuel indicator quantities are within +/- 200 Ibs (+/- 100 kgs) of the quantities recorded in Step 6 of the Horizontal Stabilizer Tank Preparation Procedure. NOTE: Horizontal Stabilizer tank fuel quantity will not be displayed. t. On the P180-1 panel, position M09, open the circuit breaker C01143, FUELING PWR-HOT BAT. u. On the P42 panel, see that the refuel indicator displays go blank. v. On the P42 panel, put the battery switch in the NORM position. 3. Do an electrical test of the FQIS display, center tank fuel control card, and secondary valves and horizontal stabilizer sump drain valves as follows: a. On the rear spar of the center tank, disconnect connector DV437 from the left secondary refuel valve. b. On the P42 panel, put the CENTER tank valve position control switch in the OPEN position. c. On the P414 panel, position F22, close the circuit breaker C01142, FUELING PWR. d. On the rear spar of the center tank, make sure there is 23-30 VDC on DV437, between pins A and B. e. On the P42 panel, push and hold the C. TANK SEC. VAL. switch to the CLOSED position. See that the L and R valve position lights come on. On the rear spar of the center tank, make sure there is 0-3 VDC on DV437, between pins A and B. January 23, 2007 Revision 3: August 30, 2007 747-28-2285 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 33 of 89 ### Page 34 (OCR) BOEING SERVICE BULLETIN 747-28-2285 On the rear spar of the center tank, disconnect the left secondary refuel valve pressure switch connector DS1877. On the P42 panel, see that the secondary refuel valve L valve position lights goes off. h. On the P42 panel, release the C. TANK SEC. VAL. switch. On the P42 panel, put the CENTER tank valve position control switch in the CLOSED position. J. On the P42 panel, put the ALL VALVES switch in the OPEN position. k. On the rear spar of the center tank, make sure there is 23-30 VDC on DV437, between pins A and B. . On the P42 panel, put the ALL VALVES switch in the CLOSED position. m. On the rear spar of the center tank, make sure there is 0-3 VDC on DV437, between pins A and B. n. On the P414 panel, position F22, open the circuit breaker C01142, FUELING PWR. o. On the rear spar of the center tank, connect connectors DV437 and DS1877. p. On the rear spar of the center tank, disconnect connector DV438 from the right secondary refuel valve. q. On the P42 panel, put the CENTER tank valve position control switch in the OPEN position. On the P414 panel, position F22, close the circuit breaker C01142, FUELING PWR S. On the rear spar of the center tank, make sure there is 23-30 VDC on DV438, between pins A and B. t. On the P42 panel, push and hold the C. TANK SEC. VAL. switch to the CLOSED position. See that the Land R valve position lights come on. u. On the rear spar of the center tank, make sure there is 0-3 VDC on DV436, between pins A and B. v. On the rear spar of the center tank, disconnect the right secondary refuel valve pressure switch connector DS1876. On the P42 panel, see that the secondary refuel valve R valve position lights goes off. W. On the P42 panel, release the C. TANK SEC. VAL. switch. x. On the P42 panel, put the CENTER tank valve position control switch in the CLOSED position. y. On the P42 panel, put the ALL VALVES switch in the OPEN position. Z. On the rear spar of the center tank, make sure there is 23-30 VDC on DV438, between pins A and B. January 23, 2007 Revision 3: August 30, 2007 747-28-2285 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 34 of 89 ### Page 35 (OCR) BOEING SERVICE BULLETIN 747-28-2285 aa. On the P42 panel, put the ALL VALVES switch in the CLOSED position. ab. On the rear spar of the center tank, make sure there is 0-3 VDC on DV438, between pins A and B. ac. On the P414 panel, position F22, open the circuit breaker C01142, FUELING PWR. ad. On the rear spar of the center tank, connect connectors DV438 and DS1876. ae. On the P414 panel, close the circuit breakers C090, FUELING VALVE, position F17 and C10131, H/S SUMP DRAIN VALVE, position M33. af. On the P211 panel, push the L VALVE (L3666) and R VALVE (L3667) valve power lights. See that the lights come on when they are pushed. B0 HE VALVE DO ag. On the P211 panel, push the SUMP DRAIN MAINT switch to the open position. On the horizontal stabilizer, hear that each solenoid valve operates. On the P211 panel, see that the L VALVE and R VALVE valve power lights come on. ah. On the P211 panel, push the SUMP DRAIN MAINT switch to CLOSED position. al. On the P211 panel, push the SUMP DRAIN CONT switch to the L OPEN position. On the horizontal stabilizer, hear that the left solenoid valve operates. On the P211 panel, see that L VALVE valve power light comes on. Put the switch back to the normal position. On the P211 panel, push the SUMP DRAIN CONT switch to the R OPEN position. On the horizontal stabilizer, hear that the right solenoid valve operates. On the P211 panel, see that the R VALVE valve power light comes on. Put the switch back to the normal position. 4. Do an electrical test of the fuel system management cards as follows: a. On the CMC MCDU, go to the INPUT MONITORING screen. b. On the P6 panel, close the circuit breaker C10128, FUEL SYS MGMT CARD A, position F5, and open the circuit breaker C10127, FUEL SYS MGMT CARD B, position F7. c. On the P414 panel, position F22, open the circuit breaker C01142, FUELING PWR. d. On the P6 panel, close the circuit breaker C10129, FUEL SYS MGMT CH 1, position F6, and open the circuit breaker C10130, FUEL SYS MGMT CH 2, position F8. e. In the fuel system card file (M7852), on the A2 card, see that the CH 1 green LED is on and the CH 2 green LED is not on. f. On the CMC MCDU, put this data in for input monitoring: port "E69," label "270" and sdi "00." In the fuel system card file (M7852), on the A2 card, push and hold the BIT switch to the CH 1 position. See that the CH 1 green LED goes off. On the CMC MCDU see that bit 27 goes from "1" to "0" (main tank number 2 single point sensor). This can take up to 1 minute to happen. h. In the fuel system card file (M7853), on the A2 card, release the BIT switch. January 23, 2007 Revision 3: August 30, 2007 747-28-2285 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 35 of 89 ### Page 36 (OCR) BOEING SERVICE BULLETIN 747-28-2285 On the P6 panel, open the circuit breaker C10128, FUEL SYS MGMT CARD A, position F5, open the circuit breaker C10130, FUEL SYS MGMT CH 2, position F8, open the circuit breaker C10129, FUEL SYS MGMT CH 1, position F6, and open the circuit breaker C10127, FUEL SYS MGMT CARD B, position F7. On the P180 panel, close the circuit breaker C10136, FUEL SYS EICAS INTFC CONT, position H17. k. On the CMC MCDU, put this data in for input monitoring: port "E 10", label "274" and sdi "00." See that this data can be seen. This can take up to 1 minute to happen. Position 29 28 27 26 25 24 23 22 20 Status 1 1 1 1 Position 19 18 17 16 15 14 13 | 12 11 Status 1 On the CMC MCDU, put this data in for input monitoring: "E 10", label "270" and sdi "00." m. On the P5 panel, push the MAIN 1 AFT fuel pump switch to ON. See that bit 11 goes from "O" to "1." This can take up to 1 minute. n. On the P5 panel, push the MAIN 1 FWD fuel pump switch to ON. See that bit 12 goes from "O" to "1." This can take up to 1 minute to happen. o. On the P5 panel, push the MAIN 2 AFT fuel pump switch to ON. See that bit 13 goes from "O" to "1". This can take up to 1 minute to happen. p. On the P5 panel, push the MAIN 2 FWD fuel pump switch to ON. See that bit 14 goes from "0" to "1." This can take up to 1 minute. q. On the P5 panel, push the MAIN 3 AFT fuel pump switch to ON. See that bit 15 goes from "0" to "1." This can take up to 1 minute. On the P5 panel, push the MAIN 3 FWD fuel pump switch to ON. See that bit 16 goes from "0" to "1." This can take up to 1 minute. s. On the P5 panel, push the MAIN 4 AFT fuel pump switch to ON. See that bit 17 goes from "0" to "1." This can take up to 1 minute. t. On the P5 panel, push the MAIN 4 FWD fuel pump switch to ON. See that bit 18 goes from "0" to "1." This can take up to 1 minute. u. On the P5 panel, push the CTR L fuel pump switch to ON. See that bit 19 goes from "O" to "1." This can take up to 1 minute. V. On the P5 panel, push the CTR R fuel pump switch to ON. See that bit 20 goes from "0" to "1." This can take up to 1 minute. W. On the P5 panel, push the OVRD 2 MAIN AFT fuel pump switch to ON. See that bit 23 goes from "0" to "1." This can take up to 1 minute. January 23, 2007 Revision 3: August 30, 2007 747-28-2285 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 36 of 89 ### Page 37 (OCR) BOEING SERVICE BULLETIN 747-28-2285 x. On the P5 panel, push the OVRD 2 MAIN FWD fuel pump switch to ON. See that bit 24 goes from "0" to "1." This can take up to 1 minute. y. On the P5 panel, push the OVRD 3 MAIN AFT fuel pump switch to ON. See that bit 25 goes from "0" to "1." This can take up to 1 minute. z. On the P5 panel, push the OVRD 3 MAIN FWD fuel pump switch to ON. See that bit 26 goes from "0" to "1." This can take up to 1 minute. aa. On the P5 panel, push the number 1 tank FUEL X FEED switch to on (flow bar can be seen). See that bit 27 goes from "0" to "1." This can take up to 1 minute to happen. ab. On the P5 panel, push the number 2 tank FUEL X FEED switch to on (flow bar can be seen). See that bit 28 goes from "0" to "1." This can take up to 1 minute to happen. ac. On the P5 panel, push the number 3 tank FUEL X FEED switch to on (flow bar can be seen). See that bit 29 goes from "0" to "1." This can take up to 1 minute to happen. ad. On the CMC MCDU, put this data in for input monitoring: port "E 10", label "270" and sdi "10." ae. On the P5 panel, push the number 4 tank FUEL X FEED switch to on (flow ban can be seen). See that bit 11 goes from "0" to "1." This can take up to 1 minute. af. On the P5 panel, push all the switches on the M154 module to off. ag. On the P6 panel, close the circuit breakers C10128, FUEL SYS MGMT CARD A, position F5, C10127, FUEL SYS MGMT CARD B, position F7, C10129, FUEL SYS MGMT CH 1, position F6, and C10130, FUEL SYS MGMT CH 2, position F8. 5. Do the Fuel Quantity indication System Ground test as specified in the 747-400 AMM 28-41-00. NOTE: Horizontal Stabilizer is now deactivated and NOT to be fueled. 6. Do the Wing Surge Tank Float Switch Operational Test as specified in the 747-400 AMM 28-21-12. 7. Restore hydraulic power. Refer to the 747-400 AMM 29-11-00. 8. Remove the gear door locks. Refer to the 747-400 AMM 32-00-30. 9. Put the airplane back into serviceable condition. January 23, 2007 Revision 3: August 30, 2007 747-28-2285 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 37 of 89 ### Page 38 (OCR) BOEING SERVICE BULLETIN 747-28-2285 FIGURE 1: OVERHEAD CIRCUIT BREAKER PANEL P7-2 CHANGE P7-2 PANEL P7 OVERHEAD CIRCUIT BREAKER PANEL FWD FUEL XFR REFUEL & XFR STAB STAR 2.5 1X2 1302597 FIGURE 1: OVERHEAD CIRCUIT BREAKER PANEL P7-2 CHANGE January 23, 2007 (SHEET 1 OF 2) 747-28-2285 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 38 of 89 ### Page 39 (OCR) BOEING SERVICE BULLETIN 747-28-2285 The step numbers shown below agree with the numbers 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 one airplane. Each reference drawing listed is a Module Parts List (MPL). The MPL lists all the retrofit drawing and/or production drawings picture sheets to facilitate installation of the identified part, assembly or installation. STEP TASK NAME PART NUMBER QTY NOTES Remove Circuit Breaker BACC18AD7 2 - 2 Install Plug Button 2645 2 FIGURE 1: OVERHEAD CIRCUIT BREAKER PANEL P7-2 CHANGE January 23, 2007 (SHEET 2 OF 2) Revision 3: August 30, 2007 747-28-2285 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 39 of 89 ### Page 40 (OCR) BOEING SERVICE BULLETIN 747-28-2285 FIGURE 2: HORIZONTAL STABILIZER TANK AFT FUEL TRANSFER SYSTEM LOCATION REFUEL VALVE CONTROL UNIT FUEL TRANSFER PUMPS STABILIZER (DRY SIDE) STABILIZER FRONT SPAR FRONT SPAR REFUEL VALVE FUEL AFT ISOLATION VALVE •PUMP TRANSFER (IN HORIZONTAL STABILIZER TANK) SEE → FWD (WET SIDE) 1302598 STABILIZER REAR SPAR FIGURE 2: HORIZONTAL STABILIZER TANK AFT FUEL TRANSFER SYSTEM LOCATION January 23, 2007 (SHEET 1 OF 2) Revision 3: August 30, 2007 747-28-2285 BOING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 40 of 89 ### Page 41 (OCR) BOEING SERVICE BULLETIN 747-28-2285 ACTUATOR FOR THE AFT ISOLATION VALVE (LEFT-UPPER) VALVE - ADAPTER - MANUAL OVERRIDE LEVER (REF) ACTUATOR FOR THE REAR SPAR AFT ISOLATION VALVE (REF) (RIGHT-LOWER) VALVE ADAPTER → FWD LEVER (REF) MANUAL OVERRIDE 1302600 FIGURE 2: HORIZONTAL STABILIZER TANK AFT FUEL TRANSFER SYSTEM LOCATION January 23, 2007 (SHEET 2 OF 2) Revision 3: August 30, 2007 747-28-2285 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 41 of 89 ### Page 42 (OCR) BOEING SERVICE BULLETIN 747-28-2285 FIGURE 3: HORIZONTAL STABILIZER TANK FWD FUEL TRANSFER SYSTEM LOCATION CENTER WING TANK COMPONENTS SEE A HORIZONTAL STABILIZER FWD ISOLATION VALVES - SEE B CENTER WING TANK 1302601 FIGURE 3: HORIZONTAL STABILIZER TANK FWD FUEL TRANSFER SYSTEM LOCATION January 23, 2007 (SHEET 1 OF 2) Revision 3: August 30, 2007 747-28-2285 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 42 of 89 ### Page 43 (OCR) BOEING SERVICE BULLETIN 747-28-2285 VALVE BODY REAR SPAR VALVE VALVE ADAPTER ACTUATOR FWD < MANUAL OVERRIDE LEVER HORIZONTAL STABILIZER ISOLATION VALVE 1302602 FIGURE 3: HORIZONTAL STABILIZER TANK FWD FUEL TRANSFER SYSTEM LOCATION January 23, 2007 (SHEET 2 OF 2) Revision 3: August 30, 2007 747-28-2285 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 43 of 89 ### Page 44 (OCR) BOEING SERVICE BULLETIN 747-28-2285 FIGURE 4: LEFT WING REFUELING PANEL P42 MODIFICATION FWD C FWD H. STAB TANK DEACTIVATED 4.0 4.0 3.5 RESERVE 3 H. STAB OPEN CLOSED 1302603 FIGURE 4: LEFT WING REFUELING PANEL P42 MODIFICATION January 23, 2007 (SHEET 1 OF 2) Revision 3: August 30, 2007 747-28-2285 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 44 of 89 ### Page 45 (OCR) BOEING SERVICE BULLETIN 747-28-2285 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 one airplane. Each reference drawing listed is a Module Parts List (MPL). The MPL lists all the retrofit drawing and/or production drawings picture sheets to facilitate installation of the identified part, assembly or installation. STEP TASK NAME PART NUMBER QTY NOTES 1 Install Marker BAC27EFS595 Refer to 747-400 AMM 20-11-06 FIGURE 4: LEFT WING REFUELING PANEL P42 MODIFICATION January 23, 2007 (SHEET 2 OF 2) Revision 3: August 30, 2007 747-28-2285 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 45 of 89 ### Page 46 (OCR) BOEING SERVICE BULLETIN 747-28-2285 FIGURE 5: H.STAB FUEL PUMP LOW PRESSURE SWITCHES AND P85 PANEL CHANGE SEE A P85 PANEL FWD C E8 EQUIPMENT RACK → FWD DOOR NO. 5 20 SVCE OUT LAV WATER HTR CARGO HDLG AFT R FC1-FC2 FC3-FC4 | FC5-FC6 13 - HOR STAB XFER/JETT PUMP LEFT RIGHT THE BOEING CO PART NUMBER SERIAL NUMBER 1302605 FIGURE 5: H.STAB FUEL PUMP LOW PRESSURE SWITCHES AND P85 PANEL CHANGE January 23, 2007 (SHEET 1 OF 2) Revision 3: August 30, 2007 747-28-2285 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 46 of 89 ### Page 47 (OCR) BOEING SERVICE BULLETIN 747-28-2285 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 one airplane. Each reference drawing listed is a Module Parts List (MPL). The MPL lists all the retrofit drawing and/or production drawings picture sheets to facilitate installation of the identified part, assembly or installation. STEP TASK NAME PART NUMBER QTY NOTES 1 Remove Circuit Breakers BACC18AE25 2 2 Remove Marker BAC27EEL23764 1 Refer to 747-400 AMM 20-11-06. Install Plug Button 2645 2 FIGURE 5: H.STAB FUEL PUMP LOW PRESSURE SWITCHES AND P85 PANEL CHANGE January 23, 2007 (SHEET 2 OF 2) Revision 3: August 30, 2007 747-28-2285 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 47 of 89 ### Page 48 (OCR) BOEING SERVICE BULLETIN 747-28-2285 FIGURE 6: HORIZONTALSTABILIZER TRANSFER PUMP MOTOR IMPELLER ASSY CHANGE TRANSFER/ JETTI SON PUMP SEE (A FWD C STABILIZER FRONT SPAR PUMP HOUSING MOTOR IMPELLER ASSEMBLY • FWD TRANSFER/JETTISON PUMP 1302607 FIGURE 6: HORIZONTALSTABILIZER TRANSFER PUMP MOTOR IMPELLER ASSY CHANGE January 23, 2007 (SHEET 1 OF 3) Revision 3: August 30, 2007 747-28-2285 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 48 of 89 ### Page 49 (OCR) BOEING SERVICE BULLETIN 747-28-2285 HST FRONT SPAR ELECTRICAL BOND SURFACE F PACKING TRANSFER/ JETTISON PUMP HOUSING ELECTRICAL PLUG BOND SURFACE PIN PACKING (4 3 (2) PLUG PUMP HOUSING 1 NUT WASHER ELECTRICAL BOND SURFACE BOND ING CLIP MOUNTING BOLT (AMM 28-17-05) SOCKET HEAD SCREW AND (DO NOT REMOVE) WASHER (5 LOCATIONS) HST FRONT - BONDING JUMPER BUILD-UP SPAR (DO NOT DISASSEMBLE FROM BONDING CLIP) > PREPARE THE FAYING SURFACE OF THE TRANSFER/JETTISON PUMP HOUSING AND THE 1302608 MATING SURFACE OF THE PLUG FOR AN ELECTRICAL SURFACE BOND (SWPM 20-20-00). FIGURE 6: HORIZONTALSTABILIZER TRANSFER PUMP MOTOR IMPELLER ASSY CHANGE January 23, 2007 (SHEET 2 OF 3) Revision 3: August 30, 2007 747-28-2285 BOEING PROPRIETARY - Copyright ® Unpublished Work - See page 1 for details. 49 of 89 ### Page 50 (OCR) BOEING SERVICE BULLETIN 747-28-2285 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 one airplane. Each reference drawing listed is a Module Parts List (MPL). The MPL lists all the retrofit drawing and/or production drawings picture sheets to facilitate installation of the identified part, assembly or installation. STEP TASK NAME PART NUMBER QTY NOTES Remove Motor Impeller 60-72101-1 or 60-72102-4 (Boeing 2 Refer 747-400 AMM 1 Assembly Part Number 60B92603-22 or 28-17-04. Keep 60892603-26) fasteners to install plug. 2 Install Plug 835U0001-1 2 Use kept fasteners, if usable (10 locations). Install Pin 83500002-1 2 4 Install Packing MS29513-007 2 5 Install Packing M25988-1-238 2 Install Nut BACN10JC06C 2 Use with pin 7 Install Washer NAS620C6 2 Use with pin FIGURE 6: HORIZONTALSTABILIZER TRANSFER PUMP MOTOR IMPELLER ASSY CHANGE January 23, 2007 (SHEET 3 OF 3) Revision 3: August 30, 2007 747-28-2285 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 50 of 89 ### Page 51 (OCR) BOEING SERVICE BULLETIN 747-28-2285 FIGURE 7: REMOTE ELECTRONIC UNIT CHANGES - E8 EQUIPMENT RACK AFT EQUIPMENT CENTER SEE A AFT EQUIPMENT RACK, E8 REMOTE ELECTRONICS UNIT (REU), M7861 FIDO SEE (B INOP ATTENTION ELECTROSTATIC W7861 GROUND L QUANTITY REMOTE ELEX UNIT JACK HOUSING FOR THE REMOTE ELECTRONICS UNIT AFT EQUIPMENT CENTER CAPTIVE SCREWS (4 LOCATIONS) INDIVIDUAL FUEL QUANTITY CHANNEL CARD, Y5CA1 2 COVER PLATE REMOTE ELECTRONICS 1302609 UNIT (REU), M7861 FIGURE 7: REMOTE ELECTRONIC UNIT CHANGES - E8 EQUIPMENT RACK January 23, 2007 (SHEET 1 OF 2) Revision 3: August 30, 2007 747-28-2285 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 51 of 89 ### Page 52 (OCR) BOEING SERVICE BULLETIN 747-28-2285 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 one airplane. Each reference drawing listed is a Module Parts List (MPL). The MPL lists all the retrofit drawing and/or production drawings picture sheets to facilitate installation of the identified part, assembly or installation. STEP TASK NAME PART NUMBER QTY NOTES Remove Individual Fuel Quantity 60B92018-207 1 Refer to 747-400 AMM 28-17-10 1 Channel (IFQC) Card Y5XA 1 2 Reinstall Cover Plate Install INOP Decal BAC27TFDE0013 1 Refer to 747-400 AMM 20-11-16 FIGURE 7: REMOTE ELECTRONIC UNIT CHANGES - E8 EQUIPMENT RACK January 23, 2007 (SHEET 2 OF 2) Revision 3: August 30, 2007 747-28-2285 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 52 of 89 ### Page 53 (OCR) BOEING SERVICE BULLETIN 747-28-2285 FIGURE 8: FUEL SYSTEM CARD FILE CHANGE FUEL SYSTEM CARD FILE FWDS ...0 UP ...... FWD 2 A3 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 one airplane. Each reference drawing listed is a Module Parts List (MPL). The MPL lists all the retrofit drawing and/or production drawings picture sheets to facilitate installation of the identified part, assembly or installation. STEP TASK NAME PART NUMBER QTY NOTES 1 Remove Single Point Sensor Card S344 T002-8 1 Remove Per 747-400 AMM (SPSC) 28-17-10 2 Install Cover Assembly 285U0096-6 1 FIGURE 8: FUEL SYSTEM CARD FILE CHANGE January 23, 2007 (SHEET 1 OF 1) Revision 3: August 30, 2007 747-28-2285 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 53 of 89 ### Page 54 (OCR) BOEING SERVICE BULLETIN 747-28-2285 FIGURE 9: FUEL MANAGEMENT CONTROL PANEL CHANGE FUEL MANAGEMENT - CONTROL PANEL FWD This Figure applies to Group 1: 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 one airplane. Each reference drawing listed is a Module Parts List (MPL). The MPL lists all the retrofit drawing and/or production drawings picture sheets to facilitate installation of the identified part, assembly or installation. STEP TASK NAME PART NUMBER QTY NOTES Remove Fuel Management 233U3100-247 1 (a) Panel Assy (M001540) NOTE: (a) Refer to the Electrical, Avionics, and Communication - Installation, 747-24 -2269, Service Bulletin. FIGURE 9: FUEL MANAGEMENT CONTROL PANEL CHANGE January 23, 2007 (SHEET 1 OF 1) Revision 3: August 30, 2007 747-28-2285 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 54 of 89 ### Page 55 (OCR) BOEING SERVICE BULLETIN 747-28-2285 FIGURE 10: DEACTIVATION OF TAIL TANK AT LEFT, CENTER, AND RIGHT EIU - E2-6 WIU WIRE CHANGE E2-6 SHELF M4970 WIU M4980 WIU M4990 WIU SEE DETAILS 1 THROUGH 6 FWD< MAIN EQUIPMENT CENTER FIGURE 10: DEACTIVATION OF TAIL TANK AT LEFT, CENTER, AND RIGHT EIU - E2-6 WIU WIRE CHANGE January 23, 2007 (SHEET 1 OF 10) Revision 3: August 30, 2007 747-28-2285 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 55 of 89 ### Page 56 (OCR) BOEING SERVICE BULLETIN 747-28-2285 This Figure applies to Group 1: WIRE NO. TYPE FROM TO LENGTH NOTES SL ACTION (a) (b) (c) EQUIP. NO. PIN EQUIP. NO. PIN (d) (e) (f) DELETE QL0021-26 RD DQ9711 B06 GDY1 21 - DELETE QC0021-26 RD DQ9811 B06 GDY1 21 DELETE QR0021-26 RD DQ9911 B06 GDY1 21 ADD QL0008-26 RD DQ9711 A08 GDY1 8 4.4 ADD QC0008-26 RD DQ9811 A08 GDY1 4.3 - ADD QR0024-26 RD DQ9911 A08 GDY1 8 4.3 Change the wire wrap wires in the sequence shown in this table. Install the wire along the routing shown on the subsequent pages. Refer to Boeing Standard Wiring Practices Manual 20-72-18. LEGEND FOR DETAILS 1-6 (a) DELETE Delete this wire from the wire integration unit (WIU). ADD Add this wire to the wire integration unit (WIU) (b) Wire number is shown for reference only; the number is not printed on wire wrap wires. (c) RD Cut from wire 829B9006-14. This wire is BMS 13-46, Type 3, Class 1, AWG 26 (a) The length of wire is in inches. Use these lengths as aids only. Cut the wire to the correct length during the installation. (e) None Sleeve Code: None FIGURE 10: DEACTIVATION OF TAIL TANK AT LEFT, CENTER, AND RIGHT EIU - E2-6 WIU WIRE CHANGE January 23, 2007 (SHEET 2 OF 10) Revision 3: August 30, 2007 747-28-2285 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 56 of 89 ### Page 57 (OCR) BOEING SERVICE BULLETIN 747-28-2285 NOTE: Reference: Wire Kit 826B4970 17 18 28 29 30 45 6 7 8 8107112137415 M4970 ROW A (1) ACTION WIRE NO.-GAGE TYP LENGTH NOTES CONNECTOR PIN CONNECTOR PIN (INCHES) DELETE QL0021-26 RD DQ9711 B06 GDY1 21 1301668 DETAIL 1 FIGURE 10: DEACTIVATION OF TAIL TANK AT LEFT, CENTER, AND RIGHT EIU - E2-6 WIU WIRE CHANGE January 23, 2007 (SHEET 3 OF 10) Revision 3: August 30, 2007 747-28-2285 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 57 of 89 ### Page 58 (OCR) BOEING SERVICE BULLETIN 747-28-2285 NOTE: Reference: Wire Kit 826B4980 4 25 26 27 28 29 30 3 4 5 6 7 8 9 10 11 12 13 14 15 7 8 9 10 11 12 19 14 15 M4980 ROW A (1) ACTION WIRE NO.-GAGE TYP LENGTH NOTES CONNECTOR PIN CONNECTOR PIN (INCHES) DELETE QC0021-26 RD DQ9811 B06 GDY1 21 1301672 DETAIL 2 FIGURE 10: DEACTIVATION OF TAIL TANK AT LEFT, CENTER, AND RIGHT EIU - E2-6 WIU WIRE CHANGE January 23, 2007 (SHEET 4 OF 10) Revision 3: August 30, 2007 747-28-2285 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 58 of 89 ### Page 59 (OCR) BOEING SERVICE BULLETIN 747-28-2285 NOTE: Reference: Wire Kit 826B4990 28 29.30 2 3 4 5 0 / 8 8 107112131475 8 9 10 11 M4990 ROW A (1) ACTION WIRE NO.-GAGE TYP LENGTH NOTES CONNECTOR PIN CONNECTOR PIN (INCHES) DELETE QR0021-26 RD DQ9911 B06 GDY1 21 1301674 DETAIL 3 FIGURE 10: DEACTIVATION OF TAIL TANK AT LEFT, CENTER, AND RIGHT EIU - E2-6 WIU WIRE CHANGE January 23, 2007 (SHEET 5 OF 10) Revision 3: August 30, 2007 747-28-2285 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 59 of 89 ### Page 60 (OCR) BOEING SERVICE BULLETIN 747-28-2285 NOTE: Reference: Wire Kit 826B4970 8 9 10 11 12 13 1415 8 9 10 11 12 13 M4970 ROW A (1) ACTION WIRE NO.-GAGE TYP LENGTH NOTES CONNECTOR PIN CONNECTOR PIN (INCHES) ADD QL0008-26 RD DQ9711 A08 GDY1 8 4.4 1301677 DETAIL 4 FIGURE 10: DEACTIVATION OF TAIL TANK AT LEFT, CENTER, AND RIGHT EIU - E2-6 WIU WIRE CHANGE January 23, 2007 (SHEET 6 OF 10) Revision 3: August 30, 2007 747-28-2285 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 60 of 89 The text continues at https://openairdocs.org/service-documents/boeing/sb-747-28-2285/file/139b034d8a3a.md?from=61 --- OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain, except the copies of manufacturers’ service documents, which belong to their rights holders.