# Boeing Alert Service Bulletin 777-28A0047: Revision 5 - Rights: © The Boeing Company. Filed by the FAA in regulations.gov docket FAA-2015-1273; AD 2016-11-03 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication. - Document: [Boeing Alert Service Bulletin 777-28A0047](https://openairdocs.org/service-documents/boeing/777-28a0047.md) - Title as filed: U.S. DOT/FAA - 777-28A0047 R5 - Pages: 124 - PDF: https://openairdocs.org/files/sha256/c9/ef/c9efd7bfea07bb5869f0dbac556cab304a905961d2339beb38f4f76354aecfcd - Page: https://openairdocs.org/service-documents/boeing/777-28a0047/file/c9efd7bfea07 ## Text Some pages are 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 Commercial Airplanes 777 Service Bulletin Number: 777-28A0047 Original Issue: April 13, 2007 Revision 5: September 20, 2010 ATA System: 2831 SUBJECT: FUEL - Fuel Jettison System - Center Override/Jettison Fuel Pumps and Main Jettison Fuel Pumps - Change to Give Redundant Control of the Pumps Export of this technology is controlled under the United States Export Administration Regulations (EAR) (15 CFR 730-774). An export license may be required before it is used for development, production or use by foreign persons from specific countries. The controller of this data has the individual responsibility to abide by all export laws. 9E991ECCN: BOEING PROPRIETARY, CONFIDENTIAL, AND/OR TRADE SECRET Copyright © 2007 The Boeing Company Unpublished Work - All Rights Reserved Boeing claims copyright in each page of this document only to the extent that the page contains copyrightable subject matter.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, the Boeing signature, the Boeing symbol, 707, 717, 727, 737, 747, 757, 767, 777, 787, Dreamliner, BBJ, DC-8, DC-9, DC-10, KC-10, KDC-10, MD-10, MD-11, MD-80, MD-88, MD-90, P-8A, Poseidon and the Boeing livery are all trademarks owned by The Boeing Company; and no trademark license is granted in connection with this document unless provided in writing by Boeing. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 13, 2007 777-28A0047Revision 5: September 20, 2010 1 of 124 2.0 ### Page 2 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 13, 2007 777-28A0047Revision 5: September 20, 2010 2 of 124 BOEING SERVICE BULLETIN 777-28A0047 BLANK PAGE ### Page 3 Table of Contents Revision Transmittal Sheet ............................................ 5 Summary ...................................................... 7 1. PLANNING INFORMATION ........................................ 1 1 A. Effectivity ............................................... 1 1 1. Airplanes ............................................ 1 1 2. Spares Affected ........................................ 1 2 B. Concurrent Requirements ...................................... 1 3 C. Reason ................................................ 1 3 D. Description .............................................. 1 4 E. Compliance .............................................. 1 5 F. Approval ............................................... 1 6 G. Manpower .............................................. 1 6 H. Weight and Balance Changes .................................... 1 8 I. Electrical Load Data ......................................... 1 8 J. References .............................................. 2 0 1. Existing Data: ......................................... 2 0 2. Data supplied with this Service Bulletin: ........................... 2 0 3. Installation Drawings Used in the Preparation of this Service Bulletin: ........... 2 0 K. Publications Affected ........................................ 2 1 L. Interchangeability and Intermixability of Parts ........................... 2 1 2. MATERIAL INFORMATION ........................................ 2 3 A. Material - Price and Availability ................................... 2 3 B. Industry Support Information .................................... 2 4 C. Parts Necessary For Each Airplane ................................. 2 4 1. Kits/Parts: ........................................... 2 4 2. Parts and Materials Supplied by the Operator: ........................ 3 1 3. Parts Modified and Reidentified: ............................... 3 1 4. Parts Removed and Not Replaced: .............................. 3 1 D. Parts Necessary to Change Spares ................................. 3 1 E. Special Tooling - Price and Availability ............................... 3 1 F. Special Tooling Necessary to do this Service Bulletin ....................... 3 1 3. ACCOMPLISHMENT INSTRUCTIONS .................................. 3 3 A. GENERAL INFORMATION ..................................... 3 3 B. WORK INSTRUCTIONS ....................................... 3 4 FIGURE 1: MAIN EQUIPMENT CENTER - INSTALLATION OF THE P301 PANEL [Group 1-2, Configuration 2 ] ................................................ 5 1 FIGURE 2: MAIN EQUIPMENT CENTER - INSTALLATION OF THE P302 PANEL [Group 1-2, Configuration 2 ] ................................................ 5 7 FIGURE 3: LEFT JETTISON FUEL PUMP - WIRING CHANGE [Group 1-2, Configuration 2] ..... 6 3 FIGURE 4: CENTER LEFT OVERRIDE FUEL PUMP - WIRING CHANGE [Group 1-2, Configuration 2] . 68 FIGURE 5: LEFT JETTISON NOZZLE VALVE - WIRING CHANGE [Group 1, Configuration 2] .... 7 1 FIGURE 6: LEFT JETTISON NOZZLE VALVE- WIRING CHANGE [Group 2, Configuration 2] .... 7 3 FIGURE 7: MAIN EQUIPMENT CENTER - AIRPLANE WIRE ROUTING [Group 1-2, Configuration 2] . 75 FIGURE 8: LEFT JETTISON NOZZLE VALVE - WIRING CHANGE [Group 1, Configuration 2] .... 9 9 FIGURE 9: LEFT JETTISON NOZZLE VALVE - WIRING CHANGE [Group 2, Configuration 2] . . . 101 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 13, 2007 777-28A0047Revision 5: September 20, 2010 3 of 124 BOEING SERVICE BULLETIN 777-28A0047 ### Page 4 FIGURE 10: MAIN EQUIPMENT CENTER - P301 PANEL - INSTALLATION OF RELAY SOCKETS AND RELAYS [Group 1-2, Configuration 2] ............................ 1 0 3 FIGURE 11: MAIN EQUIPMENT CENTER - P301 PANEL - INSTALLATION OF THE PANEL COVER [Group 1-2, Configuration 2] ..................................... 1 0 5 FIGURE 12: RIGHT FUEL JETTISON PUMP - WIRING CHANGE [Group 1-2, Configuration 2] .... 1 0 7 FIGURE 13: RIGHT JETTISON NOZZLE VALVE - WIRING CHANGE [Group 1-2, Configuration 2] . 110 FIGURE 14: CENTER RIGHT OVERRIDE FUEL PUMP - WIRING CHANGE [Group 1-2, Configuration 2] ................................................. 1 1 2 FIGURE 15: DEFUEL VALVE - WIRING CHANGE [Group 1-2, Configuration 2] ............ 1 1 5 FIGURE 16: RIGHT JETTISON NOZZLE VALVE - WIRING CHANGE [Group 1-2, Configuration 2] . 116 FIGURE 17: MAIN EQUIPMENT CENTER - P302 PANEL - INSTALLATION OF RELAY SOCKETS AND RELAYS [Group 1-2, Configuration 2] ............................ 1 1 7 FIGURE 18: MAIN EQUIPMENT CENTER - P302 PANEL - INSTALLATION OF THE PANEL COVER [Group 1-2, Configuration 2] ..................................... 1 1 9 FIGURE 19: MORE WORK - BOND MEASUREMENT - P301 PANEL [Group 1-2, Configuration 1] . . 121 FIGURE 20: MORE WORK - BOND MEASUREMENT - P302 PANEL [Group 1-2, Configuration 1] . . 123 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 13, 2007 777-28A0047Revision 5: September 20, 2010 4 of 124 BOEING SERVICE BULLETIN 777-28A0047 ### Page 5 Commercial Airplanes 777 Service Bulletin Revision Transmittal SheetNumber: 777-28A0047Original Issue: April 13, 2007 Revision 5: September 20, 2010 ATA System: 2831 SUBJECT: FUEL - Fuel Jettison System - Center Override/Jettison Fuel Pumps and Main Jettison Fuel Pumps - Change to Give Redundant Control of the Pumps This revision includes all pages of the service bulletin. COMPLIANCE INFORMATION RELATED TO THIS REVISION More work is necessary on airplanes changed as shown in the Original Issue, Revision 1, or Revision 2 of this service bulletin. The resistance of the bond between the terminal lugs on the ground stud GD41243 and the P301 panel structure must be measured to make sure the resistance is not more than 0.001 ohms. Also, the resistance of the bond between the terminal lugs on the ground stud GD41236 and the P302 panel structure must be measured to make sure the resistance is not more than 0.001 ohms No more work is necessary on airplanes changed in accordance with Revision 3, or Revision 4 of this service bulletin. REASON FOR REVISION This revision is sent to change the functional test for the center right override/jettison fuel pump. An operator reported a difference between the functional test for the center right override/jettison fuel pump and the functional test for the center left override/jettison fuel pump. The functional test for the center right override/jettison fuel pump did not have a step to make sure the power to the center right override/jettison pump goes off approximately 30 seconds after the pump switch is turned to the ON position with the plug DM28203 disconnected. This step in the test is not required to make sure the system is functional, but it is one way to check that the system performs its intended function. These sections were changed: 1. In Accomplishment Instructions, Paragraph 3.B., changed the functional test for the center right override/jettison fuel pump to make sure the power to the center right override/jettison pump shuts off. 2. In Figure 4, corrected the quantity of contacts for flag note 4 and 5. The data given in Information Notice 777-28A0047 IN 06 is included in this revision. 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. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 13, 2007 777-28A0047Revision 5: September 20, 2010 5 of 124 ### Page 6 REVISION HISTORY April 13, 2007Original Issue: April 03, 2008Revision 1: October 09, 2008Revision 2: June 11, 2009Revision 3: May 20, 2010Revision 4: September 20, 2010Revision 5: BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 13, 2007 777-28A0047Revision 5: September 20, 2010 6 of 124 BOEING SERVICE BULLETIN 777-28A0047 ### Page 7 Commercial Airplanes 777 Service Bulletin SummaryNumber: 777-28A0047Original Issue: April 13, 2007 Revision 5: September 20, 2010 ATA System: 2831 SUBJECT: FUEL - Fuel Jettison System - Center Override/Jettison Fuel Pumps and Main Jettison Fuel Pumps - Change to Give Redundant Control of the Pumps CONCURRENT REQUIREMENTS You cannot make the changes given in this service bulletin unless the changes given in these service bulletins are made: Service Bulletin 777-28A0040 Original Issue or Revision 1. Service Bulletin 777-28A0040 gives procedures to install Electrical Load Management System (ELMS) software changes for redundant control of the jettison fuel pumps. Boeing service bulletin 777-31-0097 Original Issue, Revision 1, Revision 2, or Revision 3. Service bulletin 777-31-0097 gives the procedures to install necessary software changes for the Airplane Information Management System (AIMS) to give status messages to Engine Indicating and Crew Alerting (EICAS) that relate to the fuel pumps. GE Aviation service bulletin 5000ELM-28-456 Revision 1. Service bulletin 5000ELM-28-456 gives the procedure to make wiring changes to the P110 panel for the redundant control of the left center override/jettison fuel pump by the jettison nozzle valve switch. GE Aviation service bulletin 6000ELM-28-457 Revision 1. Service bulletin 6000ELM-28-457 gives the procedure to make wiring changes to the P210 panel for the redundant control of the right center override/jettison fuel pump by the jettison nozzle valve switch. BACKGROUND Accomplishment of the changes in this service bulletin will help prevent an ignition source in a fuel tank as a result of a center override/jettison fuel pump or a main 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 center override/jettison fuel pump or a main 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. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 13, 2007 777-28A0047Revision 5: September 20, 2010 7 of 124 ### Page 8 This service bulletin gives the instructions to install new relays and contactors in the circuitry for the center override/jettison fuel pumps and the main jettison fuel pumps. The new relays and contactors for the center override/jettison fuel pumps allow ELMS to remove power from these pumps when the inputs to ELMS show that the pumps continue to run after the pumps have been commanded OFF. The new relays for the main jettison fuel pumps give redundant control of these pumps with the jettison nozzle valve switches. 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 SFAR 88, "Fuel Tank System Fault Tolerance Evaluation Requirements". ACTION (PRR 61998-7) Group 1-2, Configuration 2: Get access to the main equipment center. Install the new P301 panel on the left side of the airplane. Install the new P302 panel on the right side of the airplane. Change the airplane wiring. Change the wiring in the P110 and P210 panels as given in the Smiths service bulletins 5000ELM-28-456 and 6000ELM-28-457. Change the ELMS software as given in the Boeing service bulletin 777-28A0040. Make sure that Boeing service bulletin 777-31-0097 is accomplished. Do a functional test. Close access. Group 1-2, Configuration 1: More work is necessary. Get access to the main equipment center. Measure the resistance of the bond between the terminal lugs on the ground stud GD41243 and the P301 panel structure. Measure the resistance of the bond between the terminal lugs on the ground stud GD41236 and the P302 panel structure. Close access. For airplanes with ELMS-1, the hardware and wiring are installed by a different service bulletin. EFFECTIVITY 777-200/300/300ER 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 3 years after the original issue date on this service bulletin. INDUSTRY SUPPORT INFORMATION Boeing warranty remedies are not available for the configuration changes given in this service bulletin. MANPOWER Refer to Paragraph 1.G., Manpower. MATERIAL INFORMATION Boeing Supplied Kits/Parts. Refer to Paragraph 2.A., Material - Price and Availability. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 13, 2007 777-28A0047Revision 5: September 20, 2010 8 of 124 BOEING SERVICE BULLETIN 777-28A0047 ### Page 9 (OCR) BOEING SERVICE BULLETIN 777-28A0047 P200 INSTALL NEW P302 PANEL • - P210 AE0232 P110 ROUTE NEW WIRING ' P1 00 TO P200, P210, INSTALL P205, PANELS AND TO P100, P110, ROUTE NEW WIRING WIRING IN CHANGE AE0231 CHANGE THE NEW P301 PANEL AE0231 BRACKET P105, PANELS AND THE P205 WIRING IN AE0232 BRACKET PANEL THE P105 PANEL U46894 Original Issue: April 13, 2007 Revision 5: September 20, 2010 777-28A0047 Copyright © Unpublished Work - See page 1 for details. BOEING PROPRIETARY - 9 of 124 ### Page 10 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 13, 2007 777-28A0047Revision 5: September 20, 2010 10 of 124 BOEING SERVICE BULLETIN 777-28A0047 BLANK PAGE ### Page 11 Commercial Airplanes 777 Service Bulletin Number: 777-28A0047 Original Issue: April 13, 2007 Revision 5: September 20, 2010 ATA System: 2831 SUBJECT: FUEL - Fuel Jettison System - Center Override/Jettison Fuel Pumps and Main Jettison Fuel Pumps - Change to Give Redundant Control of the Pumps 1. PLANNING INFORMATION A. Effectivity 1. Airplanes This service bulletin is for the airplanes shown below. An equivalent change is on subsequent production airplanes. Refer to PRR 61998-7 for data about this change. Refer to Service Bulletin Index Document D624W001 Part 3 for Airplane Variable Number, Line Number, and Serial Number data. DESCRIPTIONCONFIGURATIONGROUP 777-300/300ER airplanes with ELMS-2-1 777-300/300ER airplanes with ELMS-2 that have accomplished the Original Issue, Revision 1 or Revision 2 of this bulletin 1 777-300/300ER airplanes with ELMS-2 that have not accomplished the Original Issue, Revision 1 or Revision 2 of this bulletin 2 777-200 airplanes with ELMS-2-2 777-200 airplanes with ELMS-2 that have accomplished the Original Issue, Revision 1 or Revision 2 of this bulletin 1 777-200 airplanes with ELMS-2 that have not accomplished the Original Issue, Revision 1 or Revision 2 of this bulletin 2 Airplane Models: 777-200, 777-300, 777-300ER GroupVariable Number 2WA282 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 13, 2007 777-28A0047Revision 5: September 20, 2010 11 of 124 ### Page 12 GroupVariable Number 2WA301 - WA304 2WB140 - WB141 2WB176 - WB177 2WB193 - WB194 2WB215 2WB368 2WB438 1WB508 - WB511 1WB596 - WB597 1WB619 - WB622 2WC115 - WC117 2WC287 - WC290 2WC303 - WC308 2WC363 - WC364 2WC373 - WC374 2WC381 - WC391 2WC441 2WC446 - WC448 2WC456 - WC458 2WC486 - WC489 2WC521 1WD501 - WD504 1WD521 - WD532 1WD561 - WD563 1WD581 - WD586 1WD606 1WD621 - WD625 1WD651 - WD652 1WD671 - WD675 2. Spares Affected None. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 13, 2007 777-28A0047Revision 5: September 20, 2010 12 of 124 BOEING SERVICE BULLETIN 777-28A0047 ### Page 13 B. Concurrent Requirements You cannot make the changes given in this service bulletin unless the changes given in these service bulletins are made: Service Bulletin 777-28A0040 Original Issue or Revision 1. Service Bulletin 777-28A0040 gives procedures to install Electrical Load Management System (ELMS) software changes for redundant control of the jettison fuel pumps. Boeing service bulletin 777-31-0097 Original Issue, Revision 1, Revision 2, or Revision 3. Service bulletin 777-31-0097 gives the procedures to install necessary software changes for the Airplane Information Management System (AIMS) to give status messages to Engine Indicating and Crew Alerting (EICAS) that relate to the fuel pumps. GE Aviation service bulletin 5000ELM-28-456 Revision 1. Service bulletin 5000ELM-28-456 gives the procedure to make wiring changes to the P110 panel for the redundant control of the left center override/jettison fuel pump by the jettison nozzle valve switch. GE Aviation service bulletin 6000ELM-28-457 Revision 1. Service bulletin 6000ELM-28-457 gives the procedure to make wiring changes to the P210 panel for the redundant control of the right center override/jettison fuel pump by the jettison nozzle valve switch. C. Reason Accomplishment of the changes in this service bulletin will help prevent an ignition source in a fuel tank as a result of a center override/jettison fuel pump or a main 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 center override/jettison fuel pump or a main 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 contactors in the circuitry for the center override/jettison fuel pumps and the main jettison fuel pumps. The new relays and contactors for the center override/jettison fuel pumps allow ELMS to remove power from these pumps when the inputs to ELMS show that the pumps continue to run after the pumps have been commanded OFF. The new relays for the main jettison fuel pumps give redundant control of these pumps with the jettison nozzle valve switches. 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 SFAR 88, "Fuel Tank System Fault Tolerance Evaluation Requirements". As a part of a service bulletin validation program, this change was completed on airplane WB193 by Service Bulletin 777-28A0047 Original Issue before the release of Revision 1 of this service bulletin. The change completed on airplane WB193 by Service Bulletin 777-28A0047 Original Issue is equivalent to the release of Revision 1 of this service bulletin. Airplane WB193 has the configuration of a Group 2 airplane. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 13, 2007 777-28A0047Revision 5: September 20, 2010 13 of 124 BOEING SERVICE BULLETIN 777-28A0047 ### Page 14 Revision 1 is sent to correct typos in the wire diagrams and wire installation figure, to include more information on access, and to update the material information section because more wiring parts are needed to complete the change. Revision 2 is sent to update the material information section. The 280W3256-110 wire subkit was replaced by the 280W3256-118 wire subkit. The 280W3256-110 wire subkit includes a wire that does not have sufficient length. The 280W3256-118 wire subkit includes the wire with the sufficient length. The 005W3301-2 replacement top kit was created that includes the replacement wire subkit. Revision 3 is sent to update the material information section and correct discrepancies. Several operators have incorporated this service bulletin and reported that some wires in some wire kits do not have sufficient length. New wire kits are available that have wires with sufficient length. The 280W3256-117 wire kit is replaced by the 280W3256-123 wire kit. The 280W3256-111 wire kit is replaced by the 280W3256-124 wire kit. The 280W3256-114 wire kit is replaced by the 280W3256-119 wire kit. The 280W3256-116 wire kit is replaced by the 280W3256-121 wire kit. The 005W3301-3 replacement top kit includes these replacement wire kits. Also, the steps for the connection of the ground wires to the ground studs GD41243 and GD41236 on the P301 and P302 panel did not include a reference to the Standard Wiring Practices Manual (SWPM) 20-20-00 and the maximum resistance. If the resistance is more than the maximum resistance permitted for these current return grounds, the fuel jettison pumps may not operate correctly. Revision 4 is sent to correct part number discrepancies in figures, add more electrical load data, and make the wire installation instructions more clear. The data given in Information Notice 777-28A0047 IN 05 is included in this revision. Revision 5 is sent to change the functional test for the center right override/jettison fuel pump. An operator reported a difference between the functional test for the center right override/jettison fuel pump and the functional test for the center left override/jettison fuel pump. The functional test for the center right override/jettison fuel pump did not have a step to make sure the power to the center right override/jettison pump goes off approximately 30 seconds after the pump switch is turned to the ON position with the plug DM28203 disconnected. This step in the test is not required to make sure the system is functional, but it is one way to check that the system performs its intended function. The data given in Information Notice 777-28A0047 IN 06 is included in this revision. D. Description Group 1-2, Configuration 2: Get access to the main equipment center. Install the new P301 panel on the left side of the airplane. Install the new P302 panel on the right side of the airplane. Change the airplane wiring. Change the wiring in the P110 and P210 panels as given in the Smiths service bulletins 5000ELM-28-456 and 6000ELM-28-457. Change the ELMS software as given in the Boeing service bulletin 777-28A0040. Make sure that Boeing service bulletin 777-31-0097 is accomplished. Do a functional test. Close access. Group 1-2, Configuration 1: More work is necessary. Get access to the main equipment center. Measure the resistance of the bond between the terminal lugs on the ground stud GD41243 and the P301 panel structure. Measure the resistance of the bond between the terminal lugs on the ground stud GD41236 and the P302 panel structure. Close access. For airplanes with ELMS-1, the hardware and wiring are installed by a different service bulletin. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 13, 2007 777-28A0047Revision 5: September 20, 2010 14 of 124 BOEING SERVICE BULLETIN 777-28A0047 ### Page 15 Revision 1 - No more work is necessary on airplanes changed as shown in the original issue of this service bulletin. Revision 2 - No more work is necessary on airplanes changed as shown in the original issue or Revision 1 of this service bulletin. Revision 3 - More work is necessary on airplanes changed as shown in the Original Issue, Revision 1, or Revision 2 of this service bulletin. The resistance of the bond between the terminal lugs on the ground stud GD41243 and the P301 panel structure must be measured to make sure the resistance is not more than 0.001 ohms. Also, the resistance of the bond between the terminal lugs on the ground stud GD41236 and the P302 panel structure must be measured to make sure the resistance is not more than 0.001 ohms. Revision 4 - More work is necessary on airplanes changed in accordance with the Original Issue, Revision 1, or Revision 2 of this service bulletin. Revision 4 - No more work is necessary on airplanes changed in accordance with Revision 3 of this service bulletin. Revision 5 - More work is necessary on airplanes changed as shown in the Original Issue, Revision 1, or Revision 2 of this service bulletin. The resistance of the bond between the terminal lugs on the ground stud GD41243 and the P301 panel structure must be measured to make sure the resistance is not more than 0.001 ohms. Also, the resistance of the bond between the terminal lugs on the ground stud GD41236 and the P302 panel structure must be measured to make sure the resistance is not more than 0.001 ohms. Revision 5 - No more work is necessary on airplanes changed in accordance with Revision 3, or Revision 4 of this service bulletin. The work in this service bulletin is done in the maintenance zone(s) given below. Group 1: Affected Maintenance Zones ZoneModel 117, 118777-300, 777-300ER Group 2: Affected Maintenance Zones ZoneModel 117, 118777-200 E. Compliance The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to this service bulletin. The Airworthiness Directive will make the compliance tasks and times given in this service bulletin mandatory. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 13, 2007 777-28A0047Revision 5: September 20, 2010 15 of 124 BOEING SERVICE BULLETIN 777-28A0047 ### Page 16 Boeing recommends that this service bulletin be incorporated within 3 years after the original issue date on this service bulletin. F. Approval This service bulletin was examined by the Federal Aviation Administration (FAA). The changes specified in this service bulletin comply with the applicable regulations and are FAA approved, as well as European Aviation Safety Agency (EASA)/Joint Aviation Authorities (JAA) approved for all EASA/JAA approved airplanes listed in the service bulletin effectivity. This service bulletin and its approval were based on the airplane in its original Boeing delivery configuration or as modified by other approved Boeing changes. If an airplane has a non-Boeing modification or repair that affects a component or system also affected by this service bulletin, the operator is responsible for obtaining appropriate regulatory agency approval before incorporating this service bulletin. G. Manpower The table below shows an estimate of the task-hours necessary to do this change for each airplane. This estimate is for direct labor only, done by an experienced crew. Adjust the estimate with operator task-hour data if necessary. The estimate does not include lost time. These are some examples of lost time: — Time to adjust to the workplace — Time to schedule the work — Time to examine the work — Time to cure the materials — Time to make the parts — Time to find the tools. Group 1, Configuration 2: Elapsed HoursTask-HoursNumber of Per- sons Task 0.250.502Open Access 1.251.251Figure 1 0.751.502Figure 2 27.0054.002Figure 3 and 7 6.0012.002Figure 4 and 7 4.759.502Figure 5 and 7 3.256.502Figure 8 0.750.751Figure 10 0.250.251Figure 11 15.2530.502Figure 12 and 7 6.2512.502Figure 13 and 7 3.256.502Figure 14 and 7 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 13, 2007 777-28A0047Revision 5: September 20, 2010 16 of 124 BOEING SERVICE BULLETIN 777-28A0047 ### Page 17 Group 1, Configuration 2: Elapsed HoursTask-HoursNumber of Per- sons Task 2.254.502Figure 15 and 7 1.753.502Figure 16 0.250.251Figure 17 0.250.251Figure 18 0.250.502Close Access 1.753.502Test 75.25148.25TOTAL FOR EACH AIRPLANE Group 2, Configuration 2: Elapsed HoursTask-HoursNumber of Per- sons Task 0.250.502Open Access 1.251.251Figure 1 0.751.502Figure 2 27.0054.002Figure 3 and 7 6.0012.002Figure 4 and 7 4.759.502Figure 6 and 7 3.256.502Figure 9 0.750.751Figure 10 0.250.251Figure 11 15.2530.502Figure 12 and 7 6.2512.502Figure 13 and 7 3.256.502Figure 14 and 7 2.254.502Figure 15 and 7 1.753.502Figure 16 0.250.251Figure 17 0.250.251Figure 18 0.250.502Close Access 1.753.502Test 75.25148.25TOTAL FOR EACH AIRPLANE BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 13, 2007 777-28A0047Revision 5: September 20, 2010 17 of 124 BOEING SERVICE BULLETIN 777-28A0047 ### Page 18 Group 1-2, Configuration 1: Elapsed HoursTask-HoursNumber of Per- sons Task 0.500.501Open Access 0.050.051Figure 19 0.050.051Figure 20 0.500.501Close Access 1.101.10TOTAL FOR EACH AIRPLANE H. Weight and Balance Changes Group 1: Change in Moment (Pound-Inches) Change in Weight (Pounds) Airplane +6582.4+48.4Group 1 Group 2: Change in Moment (Pound-Inches) Change in Weight (Pounds) Airplane +16794.8+48.4Group 2 I. Electrical Load Data 1. Direct Current (DC) Load Changes BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 13, 2007 777-28A0047Revision 5: September 20, 2010 18 of 124 BOEING SERVICE BULLETIN 777-28A0047 ### Page 19 AMPSDuty CycleLoad DataActionBusNomenclatureCircuit Breaker 0.50-Connected 100% ReviseRMDCR FUEL JETT NOZ VLVC28620 0.65-Connected 100% ReviseLMDCL FUEL JETT NOZ VLVC28621 0.54-Connected 100% ReviseHBBDFLNG VLVC28637 0.54MomentaryGround Op- eration 1.09-Connected 100% ReviseRMDCCTR R OVRD FUEL PUMP CTRLC28644 1.09ContinuousEngine Start 1.09ContinuousTaxi Out 1.09ContinuousTake Off and Climb 1.09ContinuousCruise 1.09ContinuousHold and Land 1.09-Connected 100% ReviseLMDCL FUEL JETT PUMP CTRLC28645 1.09IntermittentCruise 1.09IntermittentHold and Land 1.09-Connected 100% ReviseRMDCR FUEL JETT PUMP CTRLC28646 1.09IntermittentCruise 1.09IntermittentHold and Land 1.09-Connected 100% ReviseLMDCCTR L OVRD FUEL PUMP CTRLC28647 1.09ContinuousEngine Start 1.09ContinuousTaxi Out 1.09ContinuousTake Off and Climb 1.09ContinuousCruise 1.09ContinuousHold and Land BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 13, 2007 777-28A0047Revision 5: September 20, 2010 19 of 124 BOEING SERVICE BULLETIN 777-28A0047 ### Page 20 AMPSDuty CycleLoad DataActionBusNomenclatureCircuit Breaker Revise means to change the total load to the new load specified(a) 2. Alternating Current (AC) Load Changes None J. References 1. Existing Data: a. Engineering Change Memo PRR61998-7 b. 777-300 Structural Repair Manual (SRM) 51-20-09 c. 777 Aircraft Maintenance Manual (AMM) 24-22-00, 27-81-00, 28-31-01, 32-09-00 d. Boeing Drawing 012W6100 e. Boeing Service Bulletin 777-28A0040, 777-31-0097 f. GE Aviation Service Bulletin 5000ELM-28-456, 6000ELM-28-457 g. Standard Wiring Practices Manual (SWPM) 20-10-11, 20-10-12, 20-10-19, 20-20-00, 20-30-11, 20-30-12, 20-30-13, 20-60-06, 20-61-11, 20-61-19, 20-74-11, 20-81-12, 20-81-19, 20-81-22, 20-90-15 2. Data supplied with this Service Bulletin: None. 3. Installation Drawings Used in the Preparation of this Service Bulletin: TitleDrawing Number FRAME ASSY/INSTL - 309.5141W2120 P301/P302 PANEL INSTL LEFT/RIGHT OVERRIDE/JETTISON FUEL PUMP RELAYS284W2015 WIRE BUNDLE INSTL - BULKHEAD (STA 332.5)288W4106 WIRE BUNDLE INSTL - FWD W/W BLKHD (STA 180.5 - 332.5)288W4113 WIRE BUNDLE INSTL - L.S. CAB FLOOR & FWD PASS FLR (STA 209.5 - 379.0)288W4115 WIRE BUNDLE INSTL - R.S. CAB FLOOR & FWD PASS FLR (STA 209.5 - 379.0)288W4116 WIRE BUNDLE INSTL - L.S. LWR SDWL FWD W/W BLKHD (STA 180.5-414)288W4117 WIRE BUNDLE INSTL - R.S. LWR SDWL FWD W/W BLKHD (STA 180.5-414)288W4118 These drawings were used to prepare this service bulletin. These drawings are not necessary to make the specified changes, and are not supplied with this service bulletin. These drawings may not be applicable to all airplane configurations or operators. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 13, 2007 777-28A0047Revision 5: September 20, 2010 20 of 124 BOEING SERVICE BULLETIN 777-28A0047 ### Page 21 K. Publications Affected 1. Publications: Chapter-SectionPublication 28-31777 Maintenance Manual 28-22, 28-26, 28-31777 Wiring Diagram Manual 28-31, 25-71777 Illustrated Parts Catalog 28-31777 Schematic Diagram Manual 2. Damage Tolerance Based Structural Inspections: Boeing has evaluated this service bulletin for effects on Fatigue Critical Structure (FCS) and for changes to Damage Tolerance Inspections (DTI) required in the Maintenance Program. This service bulletin affects FCS but no new DTIs are necessary. L. Interchangeability and Intermixability of Parts Accomplishment of this service bulletin does not affect interchangeability or intermixability of parts. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 13, 2007 777-28A0047Revision 5: September 20, 2010 21 of 124 BOEING SERVICE BULLETIN 777-28A0047 ### Page 22 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 13, 2007 777-28A0047Revision 5: September 20, 2010 22 of 124 BOEING SERVICE BULLETIN 777-28A0047 BLANK PAGE ### Page 23 2. MATERIAL INFORMATION A. Material - Price and Availability Boeing can supply the kits shown in Paragraph 2.C., Parts Necessary For Each Airplane, and Paragraph 2.D. as shown below. If there is a limit to the quantity (QTY) of available kits, a supply sequence is given by Spares. More kits become available as shown in the Reorder Lead Time (ROLT). ROLT is calculated from the date Boeing gets the purchase order. Unit Price thru DEC 31/09 ROLT (Weeks) QTYDateNameKit Number $15, 71938184/29/2009Replacement Top Kit005W3301-3 No Longer AvailableReplacement Top Kit005W3301-2 No Longer AvailableTop Kit005W3301-1 For operators that have received a 005W3301-1 top kit, operators can order these wires to get wires with the correct length: 280W3256-118W wire to replace the 280W3256-110W wire, 280W3256-124W wire to replace the 280W3256-111W wire, 280W3256-121W wire kit to replace the 280W3256-106W wire, 280W3256-123W wire to replace the 280W3256-107W wire, 280W3256-119W wire to replace the 280W3256-103W wire kit. For operators that have received a 005W3301-2 top kit, operators can order these wires to get wires with the correct length: 280W3256-124W wire to replace the 280W3256-111W wire, a 280W3256-121W wire to replace the 280W3256-106W wire, 280W3256-123W wire to replace the 280W3256-107W wire, 280W3256-119W wire to replace the 280W3256-103W wire. Unit Price thruROLT (Weeks) QTYDateNameKit Number $163.00(a)(a)(a)Wire280W3256-118W $326.00(a)(a)(a)Wire280W3256-119W $163.00(a)(a)(a)Wire280W3256-121W $163.00(a)(a)(a)Wire280W3256-123W $124.00(a)(a)(a)Wire280W3256-124W (a) Contact Boeing Spares The kits are subject to the terms and conditions of the Boeing standard purchase order acknowledgment. After the Unit Price date, new price and ROLT data is applicable. Prices are in United States dollars. Terms: Net 30 days. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 13, 2007 777-28A0047Revision 5: September 20, 2010 23 of 124 BOEING SERVICE BULLETIN 777-28A0047 ### Page 24 Reference this service bulletin and submit your purchase order by one of the methods that follow: 1. Order on-line via ATA Spec 2000 or Boeing Part Page 2. Fax to (206) 662-7145 3. Spares Customer Support - MC 36-65 Boeing Spares Department P.O. Box 3707 Seattle, Washington 98124-2207 USA B. Industry Support Information Boeing warranty remedies are not available for the configuration changes given in this service bulletin. C. Parts Necessary For Each Airplane 1. Kits/Parts: To get the kits/parts shown below, refer to Paragraph 2.A., Material - Price and Availability. NOTE: One top kit and the items shown in Paragraph 2.C.2., Parts and Materials Supplied by the Operator, are necessary for each airplane. The Top Kit is divided into Figure kits for each installation figure shown in the table below. NOTE: The 005W3301-3 Replacement Top Kit is equivalent to a 005W3301-1 top kit plus these wires: 280W3256-118W, 280W3256-119W 280W3256-121W, 280W3256-123W and 280W3256-124W. The 005W3301-3 Replacement Top Kit is equivalent to a 005W3301-2 top kit plus these wires: 280W3256-119W, 280W3256-121W, 280W3256-123W, and 280W3256-124W. Figure Kit 1710721Top Kit 11111005W3301-3 Top Kit 005W3301-3Wire Kit 1280W3256- 101 1280W3256- 102 1280W3256- 105 1280W3256- 108 1280W3256- 109 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 13, 2007 777-28A0047Revision 5: September 20, 2010 24 of 124 BOEING SERVICE BULLETIN 777-28A0047 ### Page 25 Top Kit 005W3301-3Wire Kit 1280W3256- 112 1280W3256- 113 1280W3256- 115 1280W3256- 118 1280W3256- 119 1280W3256- 121 1280W3256- 123 1280W3256- 124 ALL KIT 005W3301-3 NOTES Existing Part NumberName Figure New Part Number 1710721 QTY RETAINER, PIERCER 442055306 (BACS31P1 option- al) PIERCING GROM- MET RETAINER 442055308 (BACS31P3 option- al) P301 PANEL AS- SEMBLY - LEFT OVERRIDE/JETTI- SON FUEL PUMP RELAYS 1284W2014-1 P302 PANEL AS- SEMBLY - RIGHT OVERRIDE/JETTI- SON FUEL PUMP RELAYS 1284W2014-9 CLAMP2287T0011-4 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 13, 2007 777-28A0047Revision 5: September 20, 2010 25 of 124 BOEING SERVICE BULLETIN 777-28A0047 ### Page 26 ALL KIT 005W3301-3 NOTES Existing Part NumberName Figure New Part Number 1710721 QTY CLAMP3287T0011-5 BRACKET ASSY- GROUND 11287T4137-148 RETAINER CLIP ASSY 3411A4902-7 FILLER ROD169B47961-3 NUT11BACN10YR3CD RELAY12BACR13CD2 RIVET, UNIVER- SAL HD 34BACR15BB5D6C SCREW, CAP1BACS12GU3K32 SCREW, CAP3BACS12GU3K50 SCREW, CAP1BACS12GU3K58 SCREW, CAP44BACS12GU3K6 RELAY SOCKET12BACS16AG1 RELAY SOCKET1BACS16W5A SPACER8BACS18AX1 RINGPOST, WIRE HARNESS MOUNTING SUP- PORT 8BACS31H1A RINGPOST, WIRE HARNESS MOUNTING SUP- PORT 11BACS31H1B STRAP66BACS38K1 STRAP10BACS38K3 STRAP54BACS38K4 STRAP20BACS38K7 STRAP22BACS38W3 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 13, 2007 777-28A0047Revision 5: September 20, 2010 26 of 124 BOEING SERVICE BULLETIN 777-28A0047 ### Page 27 ALL KIT 005W3301-3 NOTES Existing Part NumberName Figure New Part Number 1710721 QTY SUPPORT, WIRE HARNESS ASSEM- BLY, STRINGER CLIP 44BACS38Y3 CONNECTOR RING 10CR4H WASHER12NAS1149D0316H WASHER944NAS1149D0332J SPACERS FOR RIVETS 3NAS42DD6-128FC SPACERS FOR RIVETS 2NAS42DD6-32FC SPACERS FOR RIVETS 1NAS42DD6-96FC TIME DELAY RE- LAY 1TDH-7101-6002 KIT 280W3256-101 NotesNameQTYNew Part Number wire1280W3256-101W CONNECTOR, ELECTRICAL, RE- CEPTACLE, FLANGE MOUNT, BAYONET COU- PLING 1BACC45FN12- 12S6 CONTACT, SOCK- ET 7BACC47CP1S CONTACT, SOCK- ET, SIZE 20 3CTA-0165 CONTACT, PIN, SIZE 20 3CTA-0166 CONTACT, PIN, SIZE 20 7S280W555-920 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 13, 2007 777-28A0047Revision 5: September 20, 2010 27 of 124 BOEING SERVICE BULLETIN 777-28A0047 ### Page 28 KIT 280W3256-102 NotesNameQTYNew Part Number wire1280W3256-102W CONTACT, SOCK- ET, SIZE 20 3CTA-0165 CONTACT, PIN, SIZE 20 2CTA-0166 CONTACT, PIN, SIZE 20 4S280W555-920 KIT 280W3256-105 NotesNameQTYNew Part Number wire1280W3256-105W CONTACT, SOCK- ET 4BACC47CP1S TERMINAL4BACT12AR222 KIT 280W3256-108 NotesNameQTYNew Part Number wire1280W3256-108W CONTACT, SOCK- ET 4BACC47CP1S TERMINAL4BACT12AR222 KIT 280W3256-109 NotesNameQTYNew Part Number wire1280W3256-109W CONTACT, SOCK- ET, SIZE 20 2CTA-0165 WIRE SPLICE2D-436-39 SPLICE2NAS1387-5 KIT 280W3256-112 NotesNameQTYNew Part Number SPLICE7277156-1 Insullation Tape1280W3256-11201 wire1280W3256-112W TERMINAL14BACT12AR103 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 13, 2007 777-28A0047Revision 5: September 20, 2010 28 of 124 BOEING SERVICE BULLETIN 777-28A0047 ### Page 29 KIT 280W3256-113 NotesNameQTYNew Part Number GROUND ID TAPE1280W3256-11301 wire1280W3256-113W CONTACT, SOCK- ET 7BACC47ER1 TERMINAL, LUG4BACT12AC3 CONTACT, PIN, SIZE 20 2CTA-0166 KIT 280W3256-115 NotesNameQTYNew Part Number wire1280W3256-104W CONTACT, PIN4BACC47CN1S CONTACT, SOCK- ET 7BACC47DJ1 CONTACT, SOCK- ET 7BACC47ER1 TERMINAL, LUG1BACT12AC3 TERMINAL, LUG1BACT12AC8 TERMINAL5BACT12AR222 CONTACT, SOCK- ET, SIZE 20 2CTA-0165 WIRE SPLICE6D-436-39 SPLICE6NAS1387-5 KIT 280W3256-118 NotesNameQTYNew Part Number wire1280W3256-118W CONTACT448-100-5007P02 CONNECTOR, ELECTRICAL, PLUG, STRAIGHT, BAYONET COU- PLING 1BACC45FT12A12P6 CONTACT, PIN4BACC47CN1S CONTACT, SOCK- ET 7BACC47ER1 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 13, 2007 777-28A0047Revision 5: September 20, 2010 29 of 124 BOEING SERVICE BULLETIN 777-28A0047 ### Page 30 KIT 280W3256-118 NotesNameQTYNew Part Number TERMINAL, LUG1BACT12AC8 KIT 280W3256-119 NotesNameQTYNew Part Number wire1280W3256-119W CONTACT, SOCK- ET 1BACC47CP1S TERMINAL2BACT12AR222 WIRE SPLICE2D-436-39 SPLICE2NAS1387-5 KIT 280W3256-121 NotesNameQTYNew Part Number wire1280W3256-121W CONTACT, SOCK- ET 2BACC47CP1S TERMINAL2BACT12AR222 WIRE SPLICE2D-436-39 SPLICE2NAS1387-5 KIT 280W3256-123 NotesNameQTYNew Part Number wire1280W3256-123W CONTACT, PIN3BACC47CN1S TERMINAL5BACT12AR222 WIRE SPLICE3D-436-39 SPLICE3NAS1387-5 KIT 280W3256-124 NotesNameQTYNew Part Number FILLER SLEEVE7252-1231-000 SPLICE7277156-1 Insullation tape1280W3256-12401 wire1280W3256-124W BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 13, 2007 777-28A0047Revision 5: September 20, 2010 30 of 124 BOEING SERVICE BULLETIN 777-28A0047 ### Page 31 KIT 280W3256-124 NotesNameQTYNew Part Number CONTACT7BACC47DP3 TERMINAL14BACT12AR103 2. Parts and Materials Supplied by the Operator: NotesNameQTYPart Number / Specification (a)Nut2MS21042L-3 (a)Flat Washer2NAS1149D0316H Screw1BACS12GU3K48 (a) Refer to SWPM 20-20-00 for optional hardware. 3. Parts Modified and Reidentified: None. 4. Parts Removed and Not Replaced: None. D. Parts Necessary to Change Spares None. E. Special Tooling - Price and Availability None. F. Special Tooling Necessary to do this Service Bulletin No special tools or equipment are necessary to do the change in this service bulletin. But, maintenance and overhaul tools in the manuals given in Paragraph 1.J., References, can be necessary. Examine operator tool supply to make sure all necessary tools are available. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 13, 2007 777-28A0047Revision 5: September 20, 2010 31 of 124 BOEING SERVICE BULLETIN 777-28A0047 ### Page 32 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 13, 2007 777-28A0047Revision 5: September 20, 2010 32 of 124 BOEING SERVICE BULLETIN 777-28A0047 BLANK PAGE ### Page 33 3. ACCOMPLISHMENT INSTRUCTIONS A. GENERAL INFORMATION CAUTION: KEEP THE WORK AREA, WIRES AND ELECTRICAL BUNDLES CLEAN OF METAL PARTICLES OR CONTAMINATION WHEN YOU USE TOOLS. UNWANTED MATERIAL, METAL PARTICLES OR CONTAMINATION CAUGHT IN WIRE BUNDLES CAN CAUSE DAMAGE TO THE BUNDLES. DAMAGED WIRE BUNDLES CAN CAUSE SPARKS OR OTHER ELECTRICAL DAMAGE. NOTE: 1. Manual titles are referred to by acronyms. Refer to Paragraph 1.J., References, for definition of the acronyms. 2. Obey all of the warnings and cautions given in the specified manual sections. 3. Unless shown differently, these dimensions and tolerances are used: — Linear dimensions are in inches — Tolerance on linear dimensions, other than rivet and bolt edge margins, is plus or minus 0.03 inch. — Tolerance on rivet and bolt edge margin is plus or minus 0.05 inch — Angular tolerance is plus or minus 2 degrees — Hole dimensions for standard solid rivets are given in 777 Structural Repair Manual, Chapter 51 — Torque limits to tighten nuts and bolts are given in 777 Structural Repair Manual, Chapter 51. 4. For approved fastener and process material substitutions, refer to 777 Structural Repair Manual, Chapter 51, Alternate fasteners are given in 777 Structural Repair Manual Chapter 51 and Boeing Drawing 012W6100. 5. Refer to the Boeing Standard Wiring Practices Manuals SWPM 20-10-11 and SWPM 20-10-12 for the wire installation procedures. 6. If the length of fasteners specified in this service bulletin do not meet the installation standards, fasteners of the same specification, or an approved substitute, one grip length longer or shorter may be used. 7. These work instructions refer to procedures included on other Boeing documents. When the words "refer to" are used and the operator has an accepted alternative procedure, the accepted alternative procedure can be used. When the words "as given in" are included in the instruction, the procedure in the Boeing document must be used. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 13, 2007 777-28A0047Revision 5: September 20, 2010 33 of 124 BOEING SERVICE BULLETIN 777-28A0047 ### Page 34 B. WORK INSTRUCTIONS Group 1-2, Configuration 2: 1. Group 1-2, Configuration 2: Remove electrical power from the airplane. Refer to 777 AMM 24-22-00 as an accepted procedure. 2. Group 1-2, Configuration 2: Get access to the main equipment center. 3. Group 1-2, Configuration 2: Remove the cover from the P301 and P302 panels. 4. Group 1-2, Configuration 2: Install the P301 panel as given in Figure 1. 5. Group 1-2, Configuration 2: Install the P302 panel as given in Figure 2. 6. Group 1-2, Configuration 2: Do the wiring changes as given in Figure 3 and Figure 7. 7. Group 1-2, Configuration 2: Do the wiring changes as given in Figure 4 and Figure 7. 8. Group 1, Configuration 2: Do the wiring changes as given in Figure 5, Figure 7, and Figure 10. 9. Group 2, Configuration 2: Do the wiring changes as given in Figure 6, Figure 7, and Figure 10. 10. Group 1, Configuration 2: Do the wiring changes as given in Figure 8. 11. Group 2, Configuration 2: Do the wiring changes as given in Figure 9. 12. Group 1-2, Configuration 2: Install the cover on the P301 panel as given in Figure 11. 13. Group 1-2, Configuration 2: Do the wiring changes as given in Figure 12 and Figure 7. 14. Group 1-2, Configuration 2: Do the wiring changes as given in Figure 13, Figure 7, and Figure 17. 15. Group 1-2, Configuration 2: Do the wiring changes as given in Figure 14 and Figure 7. 16. Group 1-2, Configuration 2: Remove the walkways that are on top of the E-3 rack and the E-4 rack at Station 332 to get access to the wire bundles in front of the racks along the bulkhead. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 13, 2007 777-28A0047Revision 5: September 20, 2010 34 of 124 BOEING SERVICE BULLETIN 777-28A0047 ### Page 35 17. Group 1-2, Configuration 2: Do the wiring changes as given in Figure 15 and Figure 7. 18. Group 1-2, Configuration 2: Install the walkways on the E-3 rack and the E-4 rack. 19. Group 1-2, Configuration 2: Do the wiring changes as given in Figure 16. 20. Group 1-2, Configuration 2: Install the cover on the P302 panel as given in Figure 18. 21. Group 1-2, Configuration 2: Do the changes to the P110 and P210 Electrical Load Management System (ELMS) panels as given in the GE Aviation service bulletins specified in this table: PanelService Bulletin P110GE Aviation SB 5000ELM-28-456 P210GE Aviation SB 6000ELM-28-457 22. Group 1-2, Configuration 2: Do the ELMS software change as given in the Boeing service bulletin 777-28A0040. 23. Group 1-2, Configuration 2: Make sure that the AIMS software change is done as given in 777-31-0097. 24. Group 1-2, Configuration 2: Do a functional test. NOTE: It is recommended to use phase rotation indicators for this test. Two indicators will be needed. NOTE: As an alternative, two digital multimeters can be used for this test. a. Prepare for the test (1) Obey these precautions at all times during these tests: (a) To operate any of the fuel pumps, you must be in the flight compartment to continuously monitor the fuel quantity and low pressure indication in the applicable tank. WARNING: DO NOT OPERATE A FUEL PUMP IF THE LOW PRESSURE INDICATION COMES ON AND STAYS ON. FUEL VAPORS IN THE TANK MAY IGNITE AND CAUSE A FIRE OR EXPLOSION. (b) Immediately set the applicable fuel pump switch to the OFF position if the low pressure indication light comes on and stays on. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 13, 2007 777-28A0047Revision 5: September 20, 2010 35 of 124 BOEING SERVICE BULLETIN 777-28A0047 ### Page 36 NOTE: The FAULT light on the arm switch comes on to show low pressure for the jettison pumps. Set the arm switch to the OFF position if this occurs. (2) Supply primary and secondary external power to the airplane. Refer to 777 AMM 24-22-00 as an accepted procedure. WARNING: DO NOT OPERATE THE LEADING EDGE SLATS. IF THE LEADING EDGE SLATS MOVE, INJURY TO PERSONS AND DAMAGE TO EQUIPMENT CAN OCCUR. (3) In the flight compartment, put a DO-NOT-OPERATE tag on the flap control lever. Refer to 777 AMM 27-81-00 as an accepted procedure. (4) Open the refueling station door 521DB to get access to the P28 integrated refuel panel (IRP). WARNING: MAKE SURE NO PERSONS OR GROUND EQUIPMENT ARE BELOW OR NEAR THE WINGTIPS. FUEL CAN SPILL FROM THE JETTISON NOZZLE OUTLETS AND CAUSE INJURIES TO PERSONS AND DAMAGE TO EQUIPMENT. (5) Make sure that the fuel tanks have the fuel quantities as follows: (a) Do these steps to find the minimum fuel quantity for each main tank: 1) If you installed a dry jettison pump in a main fuel tank before this test or if a jettison pump is not primed, make sure the tank contains a minimum of 24,000 pounds (10,886 kilograms) of fuel. NOTE: When a main tank contains 24,000 pounds (10,886 kilograms) of fuel, the fuel level is above the centerline of the jettison pump. A dry jettison pump will not prime if the fuel level is below the pump centerline. 2) If the jettison pumps in a main fuel tank are wet and primed from operation, make sure there is a minimum of 15,000 pounds (6804 kilograms) of fuel in each main fuel tank. NOTE: This fuel will prevent dry operation of the fuel jettison pumps because the fuel level will be above the inlets of the jettison pumps. (b) Make sure there is 10,000 pounds (4,536 kilograms) of fuel or more in the center fuel tank. NOTE: This fuel will prevent dry operation of the center override jettison pumps. CAUTION: FUEL IN THE REFUEL/JETTISON MANIFOLD CAN BE PRESSURIZED 30 MINUTES AFTER REFUELING, DEFUELING, FUEL JETTISON OR FUEL TRANSFER OPERATIONS. IF THE JETTISON NOZZLE VALVES ARE OPENED, FUEL CAN SPILL FROM THE JETTISON NOZZLE OUTLETS. (6) If the refuel/jettison manifold has been pressurized in the last 60 minutes, do these steps before you continue: BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 13, 2007 777-28A0047Revision 5: September 20, 2010 36 of 124 BOEING SERVICE BULLETIN 777-28A0047 ### Page 37 (a) To remove pressure from the refuel/jettison manifold: 1) On the P28 IRP, set the refuel valve control switches for the left, right, and center fuel tanks to the OPEN position. NOTE: This step will remove pressure from the refuel/jettison manifold. 2) Wait 5 to 10 minutes to remove the pressure in the manifold. 3) Set the refuel valve control switches to the CLOSED position. (7) If the refuel/jettison manifold has not been pressurized in the last 60 minutes, then continue to the next step. WARNING: MAKE SURE THE AIRPLANE IS IN THE CONFIGURATION SHOWN IN THIS TABLE. IF THE AIRPLANE IS NOT IN THE CONFIGURATION SHOWN, WHEN THE AIRPLANE IS PUT IN THE AIR MODE, A FUEL SPILL AT THE JETTISON NOZZLES CAN OCCUR AND CAUSE INJURY TO PERSONS AND DAMAGE TO EQUIPMENT. (8) Make sure that the switches and controls are in the positions shown in this table: LocationPositionSwitch/Control P5 OVERHEAD PANELOFFAPU START SWITCH P5 OVERHEAD PANELNORMALAPU FIRE SWITCH P5 OVERHEAD PANELCLOSEDAFT FUEL CROSSFEED VALVE P5 OVERHEAD PANELCLOSEDFWD FUEL CROSSFEED VALVE P5 OVERHEAD PANELOFFL AFT FUEL PUMP P5 OVERHEAD PANELOFFL FWD FUEL PUMP P5 OVERHEAD PANELOFFL CENTER FUEL PUMP P5 OVERHEAD PANELCLOSEDL JETTISON NOZZLE VALVE P5 OVERHEAD PANELOFFR AFTFUEL PUMP P5 OVERHEAD PANELOFFR FWD FUEL PUMP P5 OVERHEAD PANELOFFR CENTER FUEL PUMP P5 OVERHEAD PANELCLOSEDR JETTISON NOZZLE VALVE P5 OVERHEAD PANELOFFFUEL TO REMAIN SWITCH P5 OVERHEAD PANELOFFJETTISON ARM SWITCH P8 AISLE STANDNORMALL ENGINE FIRE SWITCH P8 AISLE STANDNORMALR ENGINE FIRE SWITCH P10 AISLE STANDCUTOFFL FUEL CONTROL SWITCH P10 AISLE STANDCUTOFFR FUEL CONTROL SWITCH P28 REFUEL PANELCLOSEDDEFUEL VALVE BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 13, 2007 777-28A0047Revision 5: September 20, 2010 37 of 124 BOEING SERVICE BULLETIN 777-28A0047 ### Page 38 (9) Make sure that these circuit breakers on the P110 panel are open: Number, Location, Name C28645, L022, L FUEL JETT PUMP CTRL C28647, L021, CTR L OVRD FUEL PUMP CTRL C28621, L025, L FUEL JETT NOZ VLV (10) Make sure that these circuit breakers on the P210 panel are open: Number, Location, Name C28644, L002, CTR R OVRD FUEL PUMP CTRL C28620, K012, R FUEL JETT NOZ VALVE C28646, K014, R FUEL JETT PUMP CTRL (11) Make sure that these circuit breakers on the P310 panel are open: Number, Location, Name C49601, B006, APUC 1 C49600, B007, APU INLET DR ACTR C28614, B001, DC FUEL PUMP C28638, F005, APU FUEL ISLN VLV C28612, G009, FUEL XFEED VALVE-AFT C26636, L005, FIRE EXT APU C28650, L011, APU INLET DOOR/FUEL SOV CTRL C28623, J011, RFLNG QTY (12) Make sure that this circuit breaker on the P320 panel is open: Number, Location, Name C28301, G009, L FWD FUEL BOOST PUMP GND SVC (13) Make sure that this circuit breaker on the P320 panel is closed: Number, Location, Name C28603, D007, RFLNG CTRL GND (14) Make sure that this circuit breaker on the P11 panel is open. Number, Location, Name C28003, A017, APU FUEL S/O VALVE BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 13, 2007 777-28A0047Revision 5: September 20, 2010 38 of 124 BOEING SERVICE BULLETIN 777-28A0047 ### Page 39 (15) Make sure that this circuit breaker on the P49 panel is open. Number, Location, Name C49602, A017, APUC 2 (16) Do these steps to set a zero fuel weight (ZFW) that will let the fuel jettison system operate: (a) On the Flight Management Computer (FMC) display, do the steps as necessary to get access to the PERF INIT page: 1) When the airplane is on the ground with the Air Data Inertial Reference Unit (ADIRU) position initialized, push the INIT/REF mode key. 2) Push PERF from the INIT/REF INDEX page. 3) Push PERF INIT from the ACT RTE page or the TAKEOFF REF page. (b) On line 3L, under ZFW, enter a zero fuel weight that is 30,000 pounds (13,608 kilograms) less than the rated maximum landing weight (MLW) for the airplane. NOTE: This shows the FMC that the airplane gross weight is more than the MLW and permits the jettison system to operate. (17) Get access to the left and right main jettison pumps on the main wing. Refer to 777 AMM 28-31-01 as an accepted procedure. b. Do this test for the operation and indication of the left and right main jettison pump: WARNING: OBEY THE PROCEDURE THAT PUTS THE AIRPLANE IN THE AIR MODE. IF YOU DO NOT DO THE PROCEDURE CORRECTLY, INJURIES TO PERSONS AND DAMAGE TO EQUIPMENT CAN OCCUR. (1) Set the air/ground system to air mode simulation. Refer to 777 AMM 32-09-00 as an accepted procedure to control the air/ground mode simulation on the Maintenance Access Terminal (MAT). NOTE: The following twenty-two steps make sure that the left and right main jettison pump enable relays, K28249 and K28252, and left and right main jettison pump control relays, K28247 and K28248, are installed correctly and the voltage and phase rotation to the main jettison pumps is correct. (2) Disconnect the DM28104 plug from the left main jettison pump. NOTE: The left main jettison pump is located on the rear spar of the left wing at approximately Inboard Rear Spar Station (IRSS) 538. (3) Disconnect the DM28204 plug from the right main jettison pump. NOTE: The right main jettison pump is located on the rear spar of the right wing at approximately Inboard Rear Spar Station 538. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 13, 2007 777-28A0047Revision 5: September 20, 2010 39 of 124 BOEING SERVICE BULLETIN 777-28A0047 ### Page 40 (4) Disconnect the DS28111 plug from the pressure switch on the left main jettison pump. (5) Disconnect the DS28211 plug from the pressure switch on the right main jettison pump. (6) Make sure that continuity exists between pin G of the DM28104 plug and airplane ground. (7) Prepare to do a check of the power to plug DM28104. Do Step (a) or Step (b): (a) Connect a phase rotation indicator to the wiring connector of plug DM28104. Phase A goes to pin B, Phase B goes to pin D, and Phase C goes to pin F. (b) Get a multimeter ready to do a check of the voltage between pins. (8) Make sure that continuity exists between pin G of the DM28204 plug and airplane ground. (9) Prepare to do a check of the power to plug DM28204. Do Step (a) or Step (b): (a) If a second phase rotation indicator is available, connect it to the wiring connector of plug DM28204. Phase A goes to pin B, Phase B goes to pin D, and Phase C goes to pin F. (b) Get a multimeter ready to do a check of the voltage between pins. (10) On EICAS, the fuel management maintenance page, make sure that the command and status indication for the left and right main jettison pumps are displayed as OFF and PRESS. WARNING: MAKE SURE THAT THE CONNECTOR TO THE FUEL PUMP IS DISCONNECTED BEFORE THE JETTISON ARM SWITCH IS SET TO THE ARMED POSITION. IF POWER IS SUPPLIED TO THE PUMP IN THE AIR MODE, THE FUEL WILL COME OUT OF THE JETTISON NOZZLES. INJURY TO PERSONS OR DAMAGE TO EQUIPMENT CAN OCCUR. (11) Close the refueling station door 521DB. (12) Close the following circuit breakers on the P110 panel: Number, Location, Name C28621, L25, LEFT JETT NOZ VLV C28645, L22, L FUEL JETT PUMP CTRL (13) Close this circuit breaker on the P210 panel: Number, Location, Name C28620, K012, RIGHT JETT NOZ VLV C28646, K014, R FUEL JETT PUMP CTRL (14) On the P5 overhead panel, set the jettison arm switch to the ARMED position. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 13, 2007 777-28A0047Revision 5: September 20, 2010 40 of 124 BOEING SERVICE BULLETIN 777-28A0047 ### Page 41 (15) On the P5 overhead panel, set the left nozzle valve switch to the ON position. (16) Do a check of the power to plug DM28104 and plug DM28204. Do the applicable step: (a) If a phase rotation indicator is used, make sure that the 3-phase rotator light is on for a minimum of 70 seconds and displays the proper phase sequence of A-B-C. (b) If a multimeter is used, make sure that the voltage is approximately 200 volts between one of these sets of pins for a minimum of 70 seconds: — pin B and pin D — pin D and pin F — pin B and pin F. (17) On the P5 overhead panel, set the left nozzle valve switch to the OFF position. (18) On the P5 overhead panel, set the right nozzle valve switch to the ON position. (19) Do a check of the power to plug DM28104 and DM28204. Do the applicable step: (a) If a phase rotation indicator is used, make sure that the 3-phase rotator light is on for a minimum of 70 seconds and displays the proper phase sequence of A-B-C. (b) If a multimeter is used, make sure that the voltage is approximately 200 volts between one of these sets of pins for a minimum of 70 seconds: — pin B and pin D — pin D and pin F — pin B and pin F. (20) On the P5 overhead panel, set the right nozzle valve switch to the OFF position. (21) On the P5 overhead panel, set the jettison arm switch to the DISARMED position. (22) Open this circuit breaker on the P210 panel: Number, Location, Name C28646, K014, R FUEL JETT PUMP CTRL (23) Open this circuit breaker on the P110 panel: Number, Location, Name C28645, L22, L FUEL JETT PUMP CTRL (24) Set the air/ground system to ground mode simulation. Refer to 777 AMM 32-09-00 as an accepted procedure to control the air/ground mode simulation on the MAT. NOTE: The following seven steps make sure that the jettison BITE time delay relay K28250 is installed correctly. With no other enable relays being used, the jettison BITE time delay relay will only allow the pumps to be powered for 60 seconds. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 13, 2007 777-28A0047Revision 5: September 20, 2010 41 of 124 BOEING SERVICE BULLETIN 777-28A0047 ### Page 42 (25) On EICAS, the fuel management maintenance page, make sure that the command and status indication for the left main jettison pump are displayed as OFF and PRESS. (26) Close this circuit breaker on the P110 panel: Number, Location, Name C28645, L22, L FUEL JETT PUMP CTRL (27) Close this circuit breaker on the P210 panel: Number, Location, Name C28646, K014, R FUEL JETT PUMP CTRL (28) On the P5 overhead panel, set the jettison arm switch to the ARMED position and start a timer. NOTE: The main jettison pump connectors should only remain powered for 60 seconds. (29) Do a check of the power to plug DM28104 and plug DM28204. Do the applicable step: (a) If a phase rotation indicator is used, make sure that the 3-phase rotator light is on for approximately 60 seconds and displays the proper phase sequence of A-B-C, and then the power shuts off. (b) If a multimeter is used, make sure that the voltage is approximately 200 volts between one of these sets of pins for approximately 60 seconds and then the power shuts off: — pin B and pin D — pin D and pin F — pin B and pin F. (30) The EICAS FUEL JETTISON PUMP (L and R) status messages will be set after 30 seconds. Manually clear these in the EICAS display unit if the messages are not cleared automatically approximately 10 seconds after they are set. (31) On the P5 overhead panel, set the jettison arm switch to the DISARMED position. (32) Open this circuit breaker on the P210 panel: Number, Location, Name C28646, K014, R FUEL JETT PUMP CTRL (33) Open this circuit breaker on the P110 panel: Number, Location, Name C28645, L22, L FUEL JETT PUMP CTRL BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 13, 2007 777-28A0047Revision 5: September 20, 2010 42 of 124 BOEING SERVICE BULLETIN 777-28A0047 ### Page 43 (34) Connect the DS28111 plug to the pressure switch on the left main jettison pump. (35) Connect the DS28211 plug to the pressure switch on the right main jettison pump. (36) Remove the phase rotation indicator from the DM28104 plug if an indicator was installed to do a check of the power. NOTE: The following nineteen steps make sure that the jettison defuel enable relay K28251 is installed correctly. The jettison pumps are run briefly as a final check of the correct operation. (37) Remove the phase rotation indicator from the DM28104 plug if an indicator was installed to do a check of the power. (38) Connect the DM28104 plug to the left main jettison pump. (39) Remove the phase rotation indicator from the DM28204 plug if an indicator was installed to do a check of the power. (40) Connect the DM28204 plug to the right main jettison pump. (41) On EICAS, the fuel management maintenance page, make sure that the command and status indication for the left main jettison pump are displayed as OFF and NO PRESS. (42) Close this circuit breaker on the P110 panel: Number, Location, Name C28645, L22, L FUEL JETT PUMP CTRL (43) Close this circuit breaker on the P210 panel: Number, Location, Name C28646, K014, R FUEL JETT PUMP CTRL (44) Make sure this circuit breaker on the P310 panel is closed: Number, Location, Name C28637, J10, DEFUEL VLV (45) Open the refueling station door 521DB. (46) On the P28 IRP, set the defuel valve switch to OPEN. WARNING: DO NOT OPERATE ANY FUEL PUMP IF THE AMBER PRESS LIGHT COMES ON AND STAYS ON. FUEL VAPORS IN THE TANK MAY IGNITE AND CAUSE A FIRE OR AN EXPLOSION. (47) On the P5 overhead panel, set the jettison arm switch to the ARMED position. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 13, 2007 777-28A0047Revision 5: September 20, 2010 43 of 124 BOEING SERVICE BULLETIN 777-28A0047 ### Page 44 NOTE: To operate any of the fuel pumps you must stay in the flight compartment to continuously monitor the fuel quantity and the low pressure indication for the applicable tank. (48) Make sure that the left and right main jettison pumps run for 70 seconds. The noise of the pumps can be heard as they run. (49) On EICAS, the fuel management maintenance page, watch the display for 70 seconds and make sure that the command and status indication for the left main jettison pump are displayed as ON and PRESS to make sure that the fuel pressure stays high. (50) If the amber PRESS light comes on and stays on, immediately set the applicable fuel pump switch to the OFF position. (51) On the P5 overhead panel, set the jettison arm switch to the OFF position. (52) Open this circuit breaker on the P110 panel: Number, Location, Name C28645, L22, L FUEL JETT PUMP CTRL (53) Open this circuit breaker on the P210 panel: Number, Location, Name C28646, K014, R FUEL JETT PUMP CTRL (54) Open this circuit breaker on the P310 panel: Number, Location, Name C28637, J10, DEFUEL VLV (55) On the P28 IRP, set the defuel valve switch to CLOSE. (56) Close the refueling station door 521DB. c. Do this test for the operation and indication of the center left override/jettison pump: NOTE: This test is a check of the new auto-shutoff hardware functionality for the center left override/jettison pump. (1) Make sure that primary and secondary external power is supplied to the airplane. Refer to 777 AMM 24-22-00 as an accepted procedure. (2) Make sure that the air/ground system is set ground mode simulation. Refer to 777 AMM 32-09-00 as an accepted procedure to control the air/ground mode simulation on the MAT. (3) On the P5 overhead panel, make sure that the center left override/jettison pump switch is set to the OFF position. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 13, 2007 777-28A0047Revision 5: September 20, 2010 44 of 124 BOEING SERVICE BULLETIN 777-28A0047 ### Page 45 (4) On the P5 overhead panel, make sure that the amber PRESS light for the center left override/jettison fuel pump switch is off. (5) On EICAS, the fuel management maintenance page, make sure that the command and status indication for the center left override/jettison pump is displayed as OFF and NO PRESS. (6) Disconnect the DM28103 plug from the center left override/jettison pump. NOTE: The center left override/jettison fuel pump is located on the rear spar of the center wing box at approximately Left Body Buttock Line (LBBL) 69. (7) Make sure that continuity exists between pin G of the DS28103 plug and airplane ground. (8) Prepare to do a check of the power to plug DM28103. Do Step (a) or Step (b): (a) Connect a phase rotation indicator to the wiring connector of plug DM28103. Phase A goes to pin B, Phase B goes to pin D, and Phase C goes to pin F. (b) Get a multimeter ready to do a check of the voltage between pins. (9) Close this circuit breaker on the P110 panel: Number, Location, Name C28647, L21, CTR L OVRD FUEL PUMP CTRL (10) On the P5 overhead panel, set the center left override/jettison pump switch to the ON position. NOTE: The pump will shut off in 30 seconds after the pump is turned ON because of the new low pressure auto-shutoff functionality. Make sure that you do the next four steps in the 30 seconds time period. (11) Do a check of the power to plug DM28103. Do the applicable step: (a) If a phase rotation indicator is used, make sure that the phase sequence on the DM28103 plug is A-B-C. (b) If a multimeter is used, do a check that the voltage is approximately 200 volts between these pins: — pin B and pin D — pin D and pin F — pin B and pin F. (12) On the P5 overhead panel, make sure that the amber PRESS light for the center left override/jettison pump switch is on. (13) On EICAS, the fuel management maintenance page, make sure that the command and status indication for the center left override/jettison pump is displayed as ON and NO PRESS. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 13, 2007 777-28A0047Revision 5: September 20, 2010 45 of 124 BOEING SERVICE BULLETIN 777-28A0047 ### Page 46 (14) Make sure that the power to the center left override/jettison fuel pump shuts off in approximately 30 seconds. (15) On the P5 overhead panel, set the center left override/jettison fuel pump switch to the OFF position. (16) On the P5 overhead panel, make sure that the amber PRESS light for the center left override/jettison pump switch goes off. (17) Open this circuit breaker on the P110 panel: Number, Location, Name C28647, L21, CTR L OVRD FUEL PUMP CTRL (18) Remove the phase rotation indicator from the DM28103 plug if one was used to do a check of the power. (19) Connect the DM28103 connector to the center left override/jettison pump. (20) Close this circuit breaker on the P110 panel: Number, Location, Name C28647, L21, CTR L OVRD FUEL PUMP CTRL NOTE: The following eight steps do a check of the normal center left override/jettison fuel pump functionality. WARNING: DO NOT OPERATE ANY FUEL PUMP IF THE AMBER PRESS LIGHT COMES ON AND STAYS ON. FUEL VAPORS IN THE TANK MAY IGNITE AND CAUSE A FIRE OR AN EXPLOSION. (21) On the P5 overhead panel, set the center left override/jettison pump switch to the ON position. NOTE: To operate any of the fuel pumps you must stay in the flight compartment to continuously monitor the fuel quantity and the low pressure indication for the applicable tank. (22) On the P5 overhead panel, make sure that the amber PRESS light for the center left override/jettison pump switch is off. (23) On EICAS, the fuel management maintenance page, make sure that the command and status indication for the center left override/jettison pump is displayed as ON and PRESS. (24) If the amber PRESS light comes on and stays on, immediately set the applicable fuel pump switch to the OFF position. (25) Make sure that the center left override/jettison fuel pump runs more than 30 seconds. The noise of the pump can be heard as it runs. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 13, 2007 777-28A0047Revision 5: September 20, 2010 46 of 124 BOEING SERVICE BULLETIN 777-28A0047 ### Page 47 (26) On the P5 overhead panel, set the center left override/jettison pump switch to the OFF position. (27) On the P5 overhead panel, make sure that the amber PRESS light for the center left override/jettison pump switch is off. (28) On EICAS, the fuel management maintenance page, make sure that the command and status indication for the center left override/jettison pump is displayed as OFF and NO PRESS. d. Do this test for the operation and indication of the center right override/jettison pump: NOTE: This test is a check of the new auto-shutoff hardware functionality for the center right override/jettison pump. (1) Make sure that primary and secondary external power is supplied to the airplane. Refer to 777 AMM 24-22-00 as an accepted procedure. (2) Make sure that the air/ground system is set ground mode simulation. Refer to 777 AMM 32-09-00 as an accepted procedure to control the air/ground mode simulation on the MAT. (3) On the P5 overhead panel, make sure the center right override/jettison pump switch is set to the OFF position. (4) On the P5 overhead panel, make sure that the amber PRESS light for the center right override/jettison pump switch is off. (5) On EICAS, the fuel management maintenance page, make sure that the command and status indication for the center right override/jettison pump is displayed as OFF and NO PRESS. (6) Disconnect the DM28203 plug from the center right override/jettison pump. NOTE: The center right override fuel pump is located on the rear spar of the center wing box at approximately Right Body Buttock Line (RBBL) 69. (7) Make sure that continuity exists between pin G of the DS28203 plug and airplane ground. (8) Prepare to do a check of the power to plug DM28203. Do Step (a) or Step (b): (a) Connect a phase rotation indicator to the wiring connector of plug DM28203. Phase A goes to pin B, Phase B goes to pin D, and Phase C goes to pin F. (b) Get a multimeter ready to do a check of the voltage between pins. (9) Close this circuit breaker on the P210 panel: Number, Location, Name C28644, L02, CTR R OVRD FUEL PUMP CTRL BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 13, 2007 777-28A0047Revision 5: September 20, 2010 47 of 124 BOEING SERVICE BULLETIN 777-28A0047 ### Page 48 (10) On the P5 overhead panel, set the center right override/jettison fuel pump switch to the ON position. NOTE: The pump will shut off in 30 seconds after the pump is turned ON because of the new low pressure auto-shutoff functionality. Make sure that you do the next four steps in the 30 seconds time period. (11) Do a check of the power to plug DM28203. Do the applicable step: (a) If a phase rotation indicator is used, make sure that the phase sequence on the DM28203 plug is A, B, C. (b) If a multimeter is used, make sure that the voltage is approximately 200 volts between these pins: — pin B and pin D — pin D and pin F — pin B and pin F. (12) On the P5 overhead panel, make sure that the amber PRESS light for the center right override/jettison pump switch is on. (13) On EICAS, the fuel management maintenance page, make sure that the command and status indication for the center right override/jettison pump is displayed as ON and NO PRESS. (14) Make sure that the power to the center right override/jettison fuel pump shuts off in approximately 30 seconds. (15) On the P5 overhead panel, set the center right override/jettison pump switch to the OFF position. (16) On the P5 overhead panel, make sure that the amber PRESS light for the center right override/jettison pump switch goes off. (17) Open this circuit breaker on the P210 panel: Number, Location, Name C28644, L02, CTR R OVRD FUEL PUMP CTRL (18) Remove the phase rotation indicator from the DM28203 plug if one was used to do a check of the power. (19) Connect the DM28203 plug to the center right override/jettison fuel pump. (20) Close this circuit breaker on the P210 panel: Number, Location, Name C28644, L02, CTR R OVRD FUEL PUMP CTRL BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 13, 2007 777-28A0047Revision 5: September 20, 2010 48 of 124 BOEING SERVICE BULLETIN 777-28A0047 ### Page 49 NOTE: The following eight steps do a check of the normal center right override/jettison fuel pump functionality. WARNING: DO NOT OPERATE ANY FUEL PUMP IF THE AMBER PRESS LIGHT COMES ON AND STAYS ON. FUEL VAPORS IN THE TANK MAY IGNITE AND CAUSE A FIRE OR AN EXPLOSION. (21) On the P5 overhead panel, set the center right override/jettison pump switch to the ON position. NOTE: To operate any of the fuel pumps you must stay in the flight compartment to continuously monitor the fuel quantity and the low pressure indication for the applicable tank. (22) On the P5 overhead panel, make sure that the amber PRESS light for the center right override/jettison pump switch is off. (23) On EICAS, the fuel management maintenance page, make sure that the command and status indication for the center right override/jettison pump is displayed as ON and PRESS. (24) If the amber PRESS light comes on and stays on, immediately set the applicable fuel pump switch to the OFF position. (25) Make sure that the center right override/jettison fuel pump runs more than 30 seconds. The noise of the pump can be heard as it runs. (26) On the P5 overhead panel, set the center right override/jettison pump switch to the OFF position. (27) On the P5 overhead panel, make sure that the amber PRESS light for the center right override/jettison pump switch is off. (28) On EICAS, the fuel management maintenance page, make sure that the command and status indication for the center right override/jettison pump is displayed as OFF and NO PRESS. 25. Group 1-2, Configuration 2: Close access to the left and right main jettison pumps on the main wing. Refer to 777 AMM 28-31-01 as an accepted procedure. 26. Group 1-2, Configuration 2: Put the airplane back to a serviceable condition. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 13, 2007 777-28A0047Revision 5: September 20, 2010 49 of 124 BOEING SERVICE BULLETIN 777-28A0047 ### Page 50 Group 1-2, Configuration 1: CONDITION: MORE WORK IS NECESSARY - BOND MEASUREMENT 1. Group 1-2, Configuration 1: Get access to the P301 panel in the main equipment center. 2. Group 1-2, Configuration 1: Measure the resistance between the terminal lugs on the ground stud GD41243 to the P301 panel structure as given in FIGURE 19. 3. Group 1-2, Configuration 1: Get access to the P302 panel in the main equipment center. 4. Group 1-2, Configuration 1: Measure the resistance between the terminal lugs on the ground stud GD41236 to the P302 panel structure as given in FIGURE 20. 5. Group 1-2, Configuration 1: Put the airplane back to a serviceable condition. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 13, 2007 777-28A0047Revision 5: September 20, 2010 50 of 124 BOEING SERVICE BULLETIN 777-28A0047 ### Page 51 (OCR) BOEING SERVICE BULLETIN 777-28A0047 This Figure applies only to: Group 1-2, Configuration 2. SEE DO / P100 STA STA 298.5 P301 309.5 • P100 / S-35L / S-36L — S-37L SEE BO > FWD U47255 FIGURE 1: MAIN EQUIPMENT CENTER - INSTALLATION OF THE P301 PANEL (SHEET 1 OF 6) Original Issue: April 13, 2007 Revision 5 September 20, 2010 BOEING PROPRIETARY - 777-28A0047 Copyright © Unpublished Work - See page 1 for details. 51 of 124 ### Page 52 (OCR) BOEING SERVICE BULLETIN 777-28A0047 STA 298.5 STA 309.5 • S-35L — 8-37L STA 309.5 > TWD S-35L → FWD U47282 FIGURE 1: MAIN EQUIPMENT CENTER - INSTALLATION OF THE P301 PANEL (SHEET 2 OF 6) Original Issue: April 13, 2007 Revision 5 September 20, 2010 777-28A0047 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 52 of 124 ### Page 53 (OCR) BOEING SERVICE BULLETIN 777-28A0047 2.04 0.62- |1.17 0.30 STA 309.5 1.70. S-35L 0.17 UP INBD C U47553 A-A FIGURE 1: MAIN EQUIPMENT CENTER - INSTALLATION OF THE P301 PANEL (SHEET 3 OF 6) Original Issue: April 13, 2007 Revision 5 September 20, 2010 BOEING PROPRIETARY - 777-28A0047 Copyright © Unpublished Work - See page 1 for details. 53 of 124 ### Page 54 (OCR) BOEING SERVICE BULLETIN 777-28A0047 GROUND STA 309.5 BRACKET SEE P301 GROUND WIRE FWD STA 298.5 SCREW (4 LOCATIONS) →FWD 309.5 STA / S-35L 2.00 INSULATION BLANKET ) 4 LOCATIONS 5 4 LOCATIONS > FWD 4 4 LOCATIONS The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary for this figure. FIGURE 1: MAIN EQUIPMENT CENTER - INSTALLATION OF THE P301 PANEL (SHEET 4 OF 6) Original Issue: April 13, 2007 Revision 5 September 20, 2010 BOEING PROPRIETARY - 777-28A0047 Copyright © Unpublished Work - See page 1 for details. 54 of 124 ### Page 55 MORE DATAQTYIDENTIFICATIONNAMETASKSTEP 4-SPRING CLIPRemove / Keep1 --INSULATION BLAN- KET Move2 Prepare holes for a driven rivet bond as given in the 777-300 SRM 51-20-09. 1287T4137-148BRACKET ASSY- GROUND Install (New)3 (a)--ResistanceMeasure 4BACS38Y3SUPPORT, WIRE HARNESS ASSEM- BLY, STRINGER CLIP Install (New)4 42055308 (BACS31P3 optional) PIERCING GROMMET RETAINER Install (New)5 42055306 (BACS31P1 optional) RETAINER, PIERCERInstall (New)6 Put the insulation blanket back in its initial position. --INSULATION BLAN- KET Move7 4-SPRING CLIPInstall (Kept)8 1284W2014-1P301 PANEL ASSEM- BLY - LEFT OVER- RIDE/JETTISON FUEL PUMP RELAYS Install (New)9 4NAS1149D0332JWASHERInstall (New) 4BACS12GU3K6SCREW, CAPInstall (New) 1-GROUND WIREInstall (New)10 1NAS1149D0316HWASHERInstall (New) 1BACN10YR3CDNUTInstall (New) (b)--ResistanceMeasure (a) Measure the resistance of the electrical bond between the bracket and the frame. Refer to SWPM 20-20- 00 as an accepted procedure. If the resistance is greater than 0.0005 ohms, do step 3 again with care to make sure that the parts are clean. (b) Measure the resistance of the electrical bond between the terminal lug on the ground wire and the bracket, Refer to SWPM 20-20-00 as an accepted procedure. If the resistance is greater than 0.001 ohms, do step 10 again with care to make sure that the parts are clean. The codes shown below agree with the letter shown in the upper left corner of the fastener symbols in the figure. A number in the lower right corner gives the grip length of the fastener. The QTY numbers shown below are the number of fasteners necessary for this figure. FIGURE 1: MAIN EQUIPMENT CENTER - INSTALLATION OF THE P301 PANEL (SHEET 5 OF 6) BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 13, 2007 777-28A0047Revision 5 September 20, 2010 55 of 124 BOEING SERVICE BULLETIN 777-28A0047 ### Page 56 If the grip length shown is not available at Boeing, fasteners supplied in kits may be one grip length longer than indicated. Also, if any of the fastener part numbers are not available or have been superseded, substitute fasteners may be supplied in Boeing kits, Boeing Document D-590 and Boeing drawing 012W6100 are used to determine the part numbers used as substitutes. MORE DATAHOLE DIAQTYIDENTIFICATIONNAMECODE --3BACR15BB5D6CRIVET, UNIVERSAL HD A The parts shown in the table below are provided as extra parts for this figure. MORE DATAQTYIDENTIFICATIONNAME -1BACR15BB5D6CRIVET, UNIVERSAL HD -1NAS1149D0316HWASHER FIGURE 1: MAIN EQUIPMENT CENTER - INSTALLATION OF THE P301 PANEL (SHEET 6 OF 6) BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 13, 2007 777-28A0047Revision 5 September 20, 2010 56 of 124 BOEING SERVICE BULLETIN 777-28A0047 ### Page 57 (OCR) BOEING SERVICE BULLETIN 777-28A0047 This Figure applies only to: Group 1-2, Configuration 2. P200 SEE DO STA 298.5 STA 309.5 P302 P200 S-35R S-36R S-37R SEE O0 FWD • U47951 FIGURE 2: MAIN EQUIPMENT CENTER - INSTALLATION OF THE P302 PANEL (SHEET 1 OF 6) Original Issue: April 13, 2007 Revision 5 September 20, 2010 BOEING PROPRIETARY - 777-28A0047 Copyright © Unpublished Work - See page 1 for details. 57 of 124 ### Page 58 (OCR) BOEING SERVICE BULLETIN 777-28A0047 STA 298.5 STA S-35R. 309.5 5-37R _ STA 309.5 S-36R FWD< U48173 FIGURE 2: MAIN EQUIPMENT CENTER - INSTALLATION OF THE P302 PANEL (SHEET 2 OF 6) Original Issue: April 13, 2007 Revision 5 September 20, 2010 777-28A0047 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 58 of 124 ### Page 59 (OCR) BOEING SERVICE BULLETIN 777-28A0047 STA 309.5 .1.20 - S-36R 0.12 0.30 0.62 1.17 A-A → INBD .04 U48138 FIGURE 2: MAIN EQUIPMENT CENTER - INSTALLATION OF THE P302 PANEL (SHEET 3 OF 6) Original Issue: April 13, 2007 Revision 5 September 20, 2010 BOEING PROPRIETARY - 777-28A0047 Copyright © Unpublished Work - See page 1 for details. 59 of 124 ### Page 60 (OCR) BOEING SERVICE BULLETIN 777-28A0047 GROUND BRACKET STA 309.5 10 SEE P302 P302 GROUND WIRE (4 LOCATIONS. • SCREW STA FWD 298.5 STA FWD. 309.5 S-36R 2.50 € 4 LOCATIONS FWD • INSULATION 44 LOCATIONS BLANKET 5 4 LOCATIONS The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary for this figure. FIGURE 2: MAIN EQUIPMENT CENTER - INSTALLATION OF THE P302 PANEL (SHEET 4 OF 6) Original Issue: April 13, 2007 Revision 5 September 20, 2010 BOEING PROPRIETARY - 777-28A0047 Copyright © Unpublished Work - See page 1 for details. 60 of 124 The text continues at https://openairdocs.org/service-documents/boeing/777-28a0047/file/c9efd7bfea07.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.