# Boeing Alert Service Bulletin 777-28A0047: Revision 6 - 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 - SB-777-28A0047 Rev 6 - Pages: 124 - PDF: https://openairdocs.org/files/sha256/d8/0e/d80e76728d1da66e15aecda619d3156451668eaf0d3cc1f7af01dc63908c291f - Page: https://openairdocs.org/service-documents/boeing/777-28a0047/file/d80e76728d1d ## 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 6: July 11, 2013 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 300-774). 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 Boeing. Unpublished Work. All Rights Reserved. Treatment of this document and its content is governed by contract with Boeing. Rights to use this document are licensed on a per aircraft basis and such rights may not be transferable. For more information, contact The Boeing Company. 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, KC-46, KDC-10, MD-10, MD-11, MD-80, MD-88, MD-90, P-8, Poseidon and Boeing liveries 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. Original Issue: April 13, 2007 777-28A0047Revision 6: July 11, 2013 1 of 124 3.0 ### Page 2 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 13, 2007 777-28A0047Revision 6: July 11, 2013 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 3 B. Concurrent Requirements ...................................... 1 3 C. Reason ................................................ 1 4 D. Description .............................................. 1 5 E. Compliance .............................................. 1 6 F. Approval ............................................... 1 6 G. Manpower .............................................. 1 7 H. Weight and Balance Changes .................................... 1 9 I. Electrical Load Data ......................................... 2 0 J. References .............................................. 2 0 1. Existing Data: ......................................... 2 0 2. Data Supplied with this Service Bulletin: ........................... 2 1 3. Installation Drawings Used in the Preparation of this Service Bulletin: ........... 2 1 K. Publications Affected ........................................ 2 1 L. Interchangeability and Intermixability of Parts ........................... 2 2 M. Software Accomplishment Summary ................................ 2 2 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 0 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 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 13, 2007 777-28A0047Revision 6: July 11, 2013 3 of 124 BOEING SERVICE BULLETIN 777-28A0047 ### Page 4 FIGURE 9: LEFT JETTISON NOZZLE VALVE - WIRING CHANGE [Group 2, Configuration 2] . . . 101 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 RESISTANCE MEASUREMENT - P301 PANEL [Group 1-2, Configuration 1 ] ................................................ 1 2 1 FIGURE 20: MORE WORK - BOND RESISTANCE MEASUREMENT - P302 PANEL [Group 1-2, Configuration 1 ] ................................................ 1 2 3 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 13, 2007 777-28A0047Revision 6: July 11, 2013 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 6: July 11, 2013 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 Federal Aviation Administration (FAA) Airworthiness Directive (AD) 2011-09-05 is related to this service bulletin. No more work is necessary on the airplanes changed in accordance with Revision 3, Revision 4 or Revision 5 of this service bulletin. REASON FOR REVISION This revision is sent to tell operators that the related GE Aviation Service Bulletin (SB) 5000ELM-28-456 Revision 1 and SB 6000ELM-28-457 Revision 1 were issued to do more work because the contact crimp tool positioner and setting given in SB 5000ELM-28-456 original issue and SB 6000ELM-28-457 original issue were not correct for the size 22D contact. GE Aviation and Boeing have now confirmed that the size 22D contacts assembled in accordance with SB 5000ELM-28-456 original issue and SB 6000ELM-28-457 original issue is acceptable because a test has shown that the crimping procedure is satisfactory. It is also acceptable to do SB 5000ELM-28-456 Revision 1 and SB 6000ELM-28-457 Revision 1 that give the more work to remove the contact and assemble it with a different positioner and setting. These sections were changed: 1. In Summary, Background, added a Summary Evaluation Table. 2. In Summary Compliance and Paragraph 1.E., Compliance: a. Added an FAA AD reference. b. Changed the Boeing compliance data. 3. In Paragraph 1.B., Concurrent Requirements, changed the Boeing SB revision level. 4. In Paragraph 1.C., Reason, added an Alternative Method of Compliance (AMOC) notice. 5. In Paragraph 1.F., Approval, added the AMOC data. 6. In Paragraph 1.J.1., Existing Data, added an FAA AD reference. 7. In Paragraph 1.K., Publications Affected, changed the publications affected data. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 13, 2007 777-28A0047Revision 6: July 11, 2013 5 of 124 ### Page 6 8. In Figures 1 and 2: a. Sheet 3, View A-A, changed the illustration. b. Step table, added a note. The data given in Alternative Method of Compliance Notice 777-28A0047-AMOC-01 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. 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: July 11, 2013Revision 6: Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 13, 2007 777-28A0047Revision 6: July 11, 2013 6 of 124 BOEING SERVICE BULLETIN 777-28A0047 ### Page 7 Commercial Airplanes 777 Service Bulletin SummaryNumber: 777-28A0047Original Issue: April 13, 2007 Revision 6: July 11, 2013 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 Refer to Paragraph 1.B., Concurrent Requirements. BACKGROUND Accomplishment of the changes in this service bulletin will help prevent an ignition source in a fuel tank as a result of a 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". This table is provided to operators for planning purposes only. Refer to the applicable sections for more information. ReferenceAffectedPlanning Data Paragraph 1.A.2., Spares AffectedNoSpares Affected Paragraph 1.E., Compliance and Paragraph 1.F., Approval YesAD Related Paragraph 1.H., Weight and Balance ChangesYesWeight and Balance Change Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 13, 2007 777-28A0047Revision 6: July 11, 2013 7 of 124 ### Page 8 ReferenceAffectedPlanning Data Paragraph 1.I., Electrical Load DataYesElectrical Load Changed Paragraph 1.K., Publications AffectedYesPublications Affected Paragraph 1.K., Publications AffectedNoAirplane Flight Operations Affected (Flight Crew Operations Manual and/or FAA Approved Air- plane Flight Manual) Paragraph 2.C.1., Kits/PartsYesKits/Parts Required Paragraph 2.C.2., Parts and Materials Supplied by the Operator YesOperator Supplied Parts/Material Paragraph 2.F., Special Tooling Necessary to do this Service Bulletin NoSpecial Tooling Required 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 in accordance with the GE Aviation service bulletins 5000ELM-28-456 and 6000ELM-28-457. Change the ELMS software in accordance with 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. Group 1-2, Configuration 3: No more work is necessary. 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 Federal Aviation Administration (FAA) Airworthiness Directive (AD) 2011-09-05 is related to this service bulletin. Boeing recommends that the change given in this service bulletin be done within 36 months after the effective date of AD 2011-09-05. 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. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 13, 2007 777-28A0047Revision 6: July 11, 2013 8 of 124 BOEING SERVICE BULLETIN 777-28A0047 ### Page 9 (OCR) BOEING SERVICE BULLETIN 777-28A0047 MATERIAL INFORMATION Boeing Supplied Kits/Parts. Refer to Paragraph 2.A., Material - Price and Availability. P200 P302 PANEL INSTALL NEW P210 AE0232 P110 ROUTE NEW WIRING • P100 TO P200, P210, INSTALL P205, PANELS AND TO P100, P110, ROUTE NEW WIRING WIRING IN CHANGE THE AE0231 CHANGE THE NEW P301 PANEL AE0231 BRACKET P105, PANELS AND AE0232 BRACKET THE P205 PANEL WIRING IN THE P105 PANEL U46894 Original Issue: April 13, 2007 Revision 6: July 11, 2013 Export Controlled ECCN: 9E991 - BOEING 777-28A0047 PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 9 of 124 ### Page 10 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 13, 2007 777-28A0047Revision 6: July 11, 2013 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 6: July 11, 2013 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 Refer to Service Bulletin Index D624W001 Part 3 for Airplane Variable Number, Line Number, and Serial Number data. This service bulletin is for the airplanes shown below. An equivalent change is on subsequent production airplanes. Refer to PRR 61998-7 for data about this change. 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 service bulletin 1 777-300/300ER airplanes with ELMS-2 that have not accomplished the Original Issue, Revision 1, Revision 2, Revision 3, Revision 4 or Revision 5 of this service bulletin 2 777-300/300ER airplanes with ELMS-2 that have accomplished Revision 3, Revision 4 or Revision 5 of this service bulletin 3 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 13, 2007 777-28A0047Revision 6: July 11, 2013 11 of 124 ### Page 12 DESCRIPTIONCONFIGURATIONGROUP 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 service bulletin 1 777-200 airplanes with ELMS-2 that have not accomplished the Original Issue, Revision 1, Revision 2, Revision 3, Revision 4 or Revision 5 of this service bulletin 2 777-200 airplanes with ELMS-2 that have accomplished Revision 3, Revision 4 or Revision 5 of this service bulletin 3 Airplane Models: 777-200, 777-300, 777-300ER GroupVariable Number 2WA282 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 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 13, 2007 777-28A0047Revision 6: July 11, 2013 12 of 124 BOEING SERVICE BULLETIN 777-28A0047 ### Page 13 GroupVariable Number 2WC486 - WC489 2WC521 1WD501 - WD504 1WD521 - WD532 1WD561 - WD563 1WD581 - WD586 1WD606 1WD621 - WD625 1WD651 - WD652 1WD671 - WD675 2. Spares Affected None. B. Concurrent Requirements Group 1-2, Configuration 2: The service bulletins listed below must be done before or at the same time as this service bulletin: Group 1-2, Configuration 2: DescriptionService BulletinCompany Install Electrical Load Management System (ELMS) software changes for redundant control of the jettison fuel pumps. 777-28A0040 Original Issue thru Revision 2 Boeing Install software changes for the Airplane Informa- tion Management System (AIMS) to give status messages to Engine Indicating and Crew Alerting (EICAS) that relate to the fuel pumps. 777-31-0097 Original Issue thru Revision 3 Boeing Make wiring changes to the P110 panel for the redundant control of the left center override/jetti- son fuel pump by the jettison nozzle valve switch. 5000ELM-28-456 Original Issue, Revision 1 GE Aviation Make wiring changes to the P210 panel for the redundant control of the right center override/jet- tison fuel pump by the jettison nozzle valve switch. 6000ELM-28-457 Original Issue, Revision 1 GE Aviation Group 1, Configuration 1, 3; Group 2, Configuration 1, 3: None. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 13, 2007 777-28A0047Revision 6: July 11, 2013 13 of 124 BOEING SERVICE BULLETIN 777-28A0047 ### Page 14 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. Revision 1 was 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 was 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 was 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. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 13, 2007 777-28A0047Revision 6: July 11, 2013 14 of 124 BOEING SERVICE BULLETIN 777-28A0047 ### Page 15 Revision 4 was 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 IN05 is included in this revision. Revision 5 was 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 IN06 is included in this revision. Revision 6 is sent to tell operators that the related GE Aviation Service Bulletin (SB) 5000ELM-28-456 Revision 1 and SB 6000ELM-28-457 Revision 1 were issued to do more work because the contact crimp tool positioner and setting given in SB 5000ELM-28-456 original issue and SB 6000ELM-28-457 original issue were not correct for the size 22D contact. GE Aviation and Boeing have now confirmed that the size 22D contacts assembled in accordance with SB 5000ELM-28-456 original issue and SB 6000ELM-28-457 original issue is acceptable because a test has shown that the crimping procedure is satisfactory. It is also acceptable to do SB 5000ELM-28-456 Revision 1 and SB 6000ELM-28-457 Revision 1 that give the more work to remove the contact and assemble it with a different positioner and setting. The data given in Alternative Method of Compliance Notice 777-28A0047-AMOC-01 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 in accordance with the GE Aviation service bulletins 5000ELM-28-456 and 6000ELM-28-457. Change the ELMS software in accordance with 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. Group 1-2, Configuration 3: No more work is necessary. For airplanes with ELMS-1, the hardware and wiring are installed by a different service bulletin. Revision 1 - No more work is necessary on airplanes changed in accordance with the original issue of this service bulletin. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 13, 2007 777-28A0047Revision 6: July 11, 2013 15 of 124 BOEING SERVICE BULLETIN 777-28A0047 ### Page 16 Revision 2 - No more work is necessary on airplanes changed in accordance with the original issue or Revision 1 of this service bulletin. Revision 3 - More work is necessary on airplanes changed in accordance with the Original Issue or 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 - No more work is necessary on airplanes changed in accordance with Revision 3 of this service bulletin. Revision 5 - No more work is necessary on airplanes changed in accordance with Revision 3, or Revision 4 of this service bulletin. Revision 6 - No more work is necessary on airplanes changed in accordance with Revision 3, Revision 4 or Revision 5 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 Federal Aviation Administration (FAA) Airworthiness Directive (AD) 2011-09-05 is related to this service bulletin. Boeing recommends that the change given in this service bulletin be done within 36 months after the effective date of AD 2011-09-05. F. Approval This service bulletin was examined by the 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. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 13, 2007 777-28A0047Revision 6: July 11, 2013 16 of 124 BOEING SERVICE BULLETIN 777-28A0047 ### Page 17 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. In addition, the Manager of the FAA Seattle Aircraft Certification Office approves the action (i.e. inspection or modification) defined in this service bulletin as an alternative method of compliance to the requirements of paragraphs (g) and (h) of AD 2011-09-05. All provisions of AD 2011-09-05 that are not specifically referenced in the above statement remain fully applicable and must be complied with. 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 PersonsTask 0.250.502Open Access 1.251.251FIGURE 1 0.751.502FIGURE 2 27.0054.002FIGURE 3 and FIGURE 7 6.0012.002FIGURE 4 and FIGURE 7 4.759.502FIGURE 5 and FIGURE 7 3.256.502FIGURE 8 0.750.751FIGURE 10 0.250.251FIGURE 11 15.2530.502FIGURE 12 and FIGURE 7 6.2512.502FIGURE 13 and FIGURE 7 3.256.502FIGURE 14 and FIGURE 7 2.254.502FIGURE 15 and FIGURE 7 1.753.502FIGURE 16 0.250.251FIGURE 17 0.250.251FIGURE 18 0.250.502Close Access Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 13, 2007 777-28A0047Revision 6: July 11, 2013 17 of 124 BOEING SERVICE BULLETIN 777-28A0047 ### Page 18 Group 1, Configuration 2: Elapsed HoursTask-HoursNumber of PersonsTask 1.753.502Test 75.25148.25TOTAL FOR EACH AIRPLANE Group 2, Configuration 2: Elapsed HoursTask-HoursNumber of PersonsTask 0.250.502Open Access 1.251.251FIGURE 1 0.751.502FIGURE 2 27.0054.002FIGURE 3 and FIGURE 7 6.0012.002FIGURE 4 and FIGURE 7 4.759.502FIGURE 6 and FIGURE 7 3.256.502FIGURE 9 0.750.751FIGURE 10 0.250.251FIGURE 11 15.2530.502FIGURE 12 and FIGURE 7 6.2512.502FIGURE 13 and FIGURE 7 3.256.502FIGURE 14 and FIGURE 7 2.254.502FIGURE 15 and FIGURE 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 1-2, Configuration 1: Elapsed HoursTask-HoursNumber of PersonsTask 0.500.501Open Access 0.050.051FIGURE 19 0.050.051FIGURE 20 0.500.501Close Access 1.101.10TOTAL FOR EACH AIRPLANE Group 1-2, Configuration 3: None. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 13, 2007 777-28A0047Revision 6: July 11, 2013 18 of 124 BOEING SERVICE BULLETIN 777-28A0047 ### Page 19 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 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 13, 2007 777-28A0047Revision 6: July 11, 2013 19 of 124 BOEING SERVICE BULLETIN 777-28A0047 ### Page 20 I. Electrical Load Data 1. Direct Current (DC) Load Changes AMPSDuty CycleLoad DataAction (a)BusNomenclatureCircuit 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 Operation 1.09-Connected 100%ReviseRMDCCTR R OVRD FUEL PUMP CTRL C28644 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 CTRL C28645 1.09IntermittentCruise 1.09IntermittentHold and Land 1.09-Connected 100%ReviseRMDCR FUEL JETT PUMP CTRL C28646 1.09IntermittentCruise 1.09IntermittentHold and Land 1.09-Connected 100%ReviseLMDCCTR L OVRD FUEL PUMP CTRL C28647 1.09ContinuousEngine Start 1.09ContinuousTaxi Out 1.09ContinuousTake Off and Climb 1.09ContinuousCruise 1.09ContinuousHold and Land (a) "Revise" means to change the total load to the new load specified. 2. Alternating Current (AC) Load Changes None. J. References 1. Existing Data: a. Engineering Change Memo PRR 61998-7 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 13, 2007 777-28A0047Revision 6: July 11, 2013 20 of 124 BOEING SERVICE BULLETIN 777-28A0047 ### Page 21 b. Boeing Service Bulletin 777-28A0040, 777-31-0097 c. Federal Aviation Administration (FAA) Airworthiness Directive (AD) 2011-09-05 d. Service Bulletin Index D624W001 e. 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, 20-30-22, 20-60-06, 20-61-11, 20-61-19, 20-74-11, 20-81-12, 20-81-19, 20-81-22, 20-90-15 f. 777 Aircraft Maintenance Manual (AMM) 24-22-00, 27-81-00, 28-31-01, 32-09-00 g. 777-300 Structural Repair Manual (SRM) 51-20-09 h. GE Aviation Service Bulletin 5000ELM-28-456, 6000ELM-28-457 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. K. Publications Affected 1. Publications: Chapter-SectionPublication 28-31777 Maintenance Manual Equipment List, 28-22, 28-26, 28-31777 Wiring Diagram Manual 28-31, 25-71777 Illustrated Parts Catalog 28-22, 28-26, 28-31777 Schematic Diagram Manual Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 13, 2007 777-28A0047Revision 6: July 11, 2013 21 of 124 BOEING SERVICE BULLETIN 777-28A0047 ### Page 22 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. M. Software Accomplishment Summary Not affected. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 13, 2007 777-28A0047Revision 6: July 11, 2013 22 of 124 BOEING SERVICE BULLETIN 777-28A0047 ### 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. Operators are encouraged to share schedule requirements with Boeing for incorporation of the service bulletin. The kits are subject to the terms and conditions of the Boeing standard purchase order acknowledgment. Prices are in United States Dollars. Terms: Net 30 days. Reference this service bulletin and submit your purchase order by one of these methods: 1. Order on-line via ATA Spec 2000 or The Boeing PART Page 2. Fax to (206) 662-7145 Group 1-2, Configuration 2: REFER TO THE BOEING PART PAGE ON MYBOEINGFLEET.COM OR CONTACT FIRST RESPONDER AT FR@BOEING.COM FOR THE LATEST REORDER LEAD TIME (ROLT) AND PRICE INFORMATION 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 Group 1-2, Configuration 2: 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. Group 1-2, Configuration 2: 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. Group 1-2, Configuration 2: 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 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 13, 2007 777-28A0047Revision 6: July 11, 2013 23 of 124 BOEING SERVICE BULLETIN 777-28A0047 ### Page 24 Group 1-2, Configuration 2: Unit Price thruROLT (Weeks) QTYDateNameKit Number (a) Contact Boeing Spares Group 1, Configuration 1, 3; Group 2, Configuration 1, 3: None. B. Industry Support Information Boeing warranty remedies are not available for the configuration changes given in this service bulletin. C. Parts Necessary for Each Airplane 1. Kits/Parts: To get the kits/parts shown below, refer to Paragraph 2.A., Material - Price and Availability. Group 1-2, Configuration 2: 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. Group 1-2, Configuration 2: 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. Group 1-2, Configuration 2: Figure Kit 1710721Top Kit 11111005W3301-3 Group 1-2, Configuration 2: Top Kit 005W3301-3Wire Kit 1280W3256-101 1280W3256-102 1280W3256-105 1280W3256-108 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 13, 2007 777-28A0047Revision 6: July 11, 2013 24 of 124 BOEING SERVICE BULLETIN 777-28A0047 ### Page 25 Group 1-2, Configuration 2: Top Kit 005W3301-3Wire Kit 1280W3256-109 1280W3256-112 1280W3256-113 1280W3256-115 1280W3256-118 1280W3256-119 1280W3256-121 1280W3256-123 1280W3256-124 Group 1-2, Configuration 2: KIT 005W3301-3 NOTES Existing Part NumberName Figure New Part Number 1710721 QTY RETAINER, PIERCER442055306 (BACS31P1 optional) PIERCING GROMMET RETAINER 442055308 (BACS31P3 optional) P301 PANEL ASSEM- BLY - LEFT OVER- RIDE/JETTISON FUEL PUMP RELAYS 1284W2014-1 P302 PANEL ASSEM- BLY - RIGHT OVER- RIDE/JETTISON FUEL PUMP RELAYS 1284W2014-9 CLAMP2287T0011-4 CLAMP3287T0011-5 BRACKET ASSY- GROUND 11287T4137-148 RETAINER CLIP ASSY3411A4902-7 FILLER ROD169B47961-3 NUT11BACN10YR3CD Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 13, 2007 777-28A0047Revision 6: July 11, 2013 25 of 124 BOEING SERVICE BULLETIN 777-28A0047 ### Page 26 Group 1-2, Configuration 2: KIT 005W3301-3 NOTES Existing Part NumberName Figure New Part Number 1710721 QTY RELAY12BACR13CD2 RIVET, UNIVERSAL HD 34BACR15BB5D6C SCREW, CAP1BACS12GU3K32 SCREW, CAP3BACS12GU3K50 SCREW, CAP1BACS12GU3K58 SCREW, CAP44BACS12GU3K6 RELAY SOCKET12BACS16AG1 RELAY SOCKET1BACS16W5A SPACER8BACS18AX1 RINGPOST, WIRE HARNESS MOUNTING SUPPORT 8BACS31H1A RINGPOST, WIRE HARNESS MOUNTING SUPPORT 11BACS31H1B STRAP66BACS38K1 STRAP10BACS38K3 STRAP54BACS38K4 STRAP20BACS38K7 STRAP22BACS38W3 SUPPORT, WIRE HARNESS ASSEM- BLY, STRINGER CLIP 44BACS38Y3 CONNECTOR RING10CR4H WASHER12NAS1149D0316H WASHER944NAS1149D0332J SPACERS FOR RIV- ETS 3NAS42DD6-128FC SPACERS FOR RIV- ETS 2NAS42DD6-32FC Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 13, 2007 777-28A0047Revision 6: July 11, 2013 26 of 124 BOEING SERVICE BULLETIN 777-28A0047 ### Page 27 Group 1-2, Configuration 2: KIT 005W3301-3 NOTES Existing Part NumberName Figure New Part Number 1710721 QTY SPACERS FOR RIV- ETS 1NAS42DD6-96FC TIME DELAY RELAY1TDH-7101-6002 Group 1-2, Configuration 2: KIT 280W3256-101 NotesNameQTYNew Part Number wire1280W3256-101W CONNECTOR, ELECTRICAL, RECEPTACLE, FLANGE MOUNT, BAYONET COUPLING 1BACC45FN12-12S6 CONTACT, SOCKET7BACC47CP1S CONTACT, SOCKET, SIZE 203CTA-0165 CONTACT, PIN, SIZE 203CTA-0166 CONTACT, PIN, SIZE 207S280W555-920 Group 1-2, Configuration 2: KIT 280W3256-102 NotesNameQTYNew Part Number wire1280W3256-102W CONTACT, SOCKET, SIZE 203CTA-0165 CONTACT, PIN, SIZE 202CTA-0166 CONTACT, PIN, SIZE 204S280W555-920 Group 1-2, Configuration 2: KIT 280W3256-105 NotesNameQTYNew Part Number wire1280W3256-105W CONTACT, SOCKET4BACC47CP1S TERMINAL4BACT12AR222 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 13, 2007 777-28A0047Revision 6: July 11, 2013 27 of 124 BOEING SERVICE BULLETIN 777-28A0047 ### Page 28 Group 1-2, Configuration 2: KIT 280W3256-108 NotesNameQTYNew Part Number wire1280W3256-108W CONTACT, SOCKET4BACC47CP1S TERMINAL4BACT12AR222 Group 1-2, Configuration 2: KIT 280W3256-109 NotesNameQTYNew Part Number wire1280W3256-109W CONTACT, SOCKET, SIZE 202CTA-0165 WIRE SPLICE2D-436-39 SPLICE2NAS1387-5 Group 1-2, Configuration 2: KIT 280W3256-112 NotesNameQTYNew Part Number SPLICE7277156-1 Insullation Tape1280W3256-11201 wire1280W3256-112W TERMINAL14BACT12AR103 Group 1-2, Configuration 2: KIT 280W3256-113 NotesNameQTYNew Part Number GROUND ID TAPE1280W3256-11301 wire1280W3256-113W CONTACT, SOCKET7BACC47ER1 TERMINAL, LUG4BACT12AC3 CONTACT, PIN, SIZE 202CTA-0166 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 13, 2007 777-28A0047Revision 6: July 11, 2013 28 of 124 BOEING SERVICE BULLETIN 777-28A0047 ### Page 29 Group 1-2, Configuration 2: KIT 280W3256-115 NotesNameQTYNew Part Number wire1280W3256-104W CONTACT, PIN4BACC47CN1S CONTACT, SOCKET7BACC47DJ1 CONTACT, SOCKET7BACC47ER1 TERMINAL, LUG1BACT12AC3 TERMINAL, LUG1BACT12AC8 TERMINAL5BACT12AR222 CONTACT, SOCKET, SIZE 202CTA-0165 WIRE SPLICE6D-436-39 SPLICE6NAS1387-5 Group 1-2, Configuration 2: KIT 280W3256-118 NotesNameQTYNew Part Number wire1280W3256-118W CONTACT448-100-5007P02 CONNECTOR, ELECTRICAL, PLUG, STRAIGHT, BAYONET COUPLING 1BACC45FT12A12P6 CONTACT, PIN4BACC47CN1S CONTACT, SOCKET7BACC47ER1 TERMINAL, LUG1BACT12AC8 Group 1-2, Configuration 2: KIT 280W3256-119 NotesNameQTYNew Part Number wire1280W3256-119W CONTACT, SOCKET1BACC47CP1S TERMINAL2BACT12AR222 WIRE SPLICE2D-436-39 SPLICE2NAS1387-5 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 13, 2007 777-28A0047Revision 6: July 11, 2013 29 of 124 BOEING SERVICE BULLETIN 777-28A0047 ### Page 30 Group 1-2, Configuration 2: KIT 280W3256-121 NotesNameQTYNew Part Number wire1280W3256-121W CONTACT, SOCKET2BACC47CP1S TERMINAL2BACT12AR222 WIRE SPLICE2D-436-39 SPLICE2NAS1387-5 Group 1-2, Configuration 2: KIT 280W3256-123 NotesNameQTYNew Part Number wire1280W3256-123W CONTACT, PIN3BACC47CN1S TERMINAL5BACT12AR222 WIRE SPLICE3D-436-39 SPLICE3NAS1387-5 Group 1-2, Configuration 2: KIT 280W3256-124 NotesNameQTYNew Part Number FILLER SLEEVE7252-1231-000 SPLICE7277156-1 Insullation tape1280W3256-12401 wire1280W3256-124W CONTACT7BACC47DP3 TERMINAL14BACT12AR103 2. Parts and Materials Supplied by the Operator: Group 1-2, Configuration 2: NotesNameQtyPart Number/ Specification SCREW, CAP1BACS12GU3K48 (a)NUT2MS21042L-3 (a)WASHER1NAS1149D0316H Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 13, 2007 777-28A0047Revision 6: July 11, 2013 30 of 124 BOEING SERVICE BULLETIN 777-28A0047 ### Page 31 Group 1-2, Configuration 2: NotesNameQtyPart Number/ Specification (a) Refer to SWPM 20-20-00 for optional hardware. Group 1, Configuration 1, 3; Group 2, Configuration 1, 3: None. 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. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 13, 2007 777-28A0047Revision 6: July 11, 2013 31 of 124 BOEING SERVICE BULLETIN 777-28A0047 ### Page 32 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 13, 2007 777-28A0047Revision 6: July 11, 2013 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 and fasteners are in Structural Repair Manual (SRM) Chapter 51 – Torque limits to tighten nuts and bolts are in SRM Chapter 51 4. Use the approved fastener and process material substitutions in accordance with SRM Chapter 51. 5. Refer to the SWPM 20-10-11 and SWPM 20-10-12 for the wire installation procedures, and SWPM 20-10-19 for the wire separation requirements, as accepted procedures. 6. The necessary conditions for selection of clamp type and size are included in SWPM 20-10-12. If any wire bundle support clamp specified in this service bulletin does not make a correct fit on the wire bundle, refer to SWPM 20-10-12 as an accepted procedure to select a clamp that fits correctly. 7. If the length of any fastener specified in this service bulletin does not meet installation standards given in SRM Chapter 51, then a fastener of the same specification, or an approved substitute, with a length which meets the installation standards given in SRM Chapter 51 may be used. In addition, washers may be installed for fastener grip length in accordance with SRM Chapter 51. 8. These work instructions refer to procedures included in 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 "in accordance with" are included in the instruction, the procedure in the Boeing document must be used. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 13, 2007 777-28A0047Revision 6: July 11, 2013 33 of 124 BOEING SERVICE BULLETIN 777-28A0047 ### Page 34 9. The instructions in Paragraph 3.B., Work Instructions and the figures can include operation of tools or test equipment. Boeing Engineering Tool Drawings, the Illustrated Tool and Equipment Manual, and the Special Tool and Ground Handling Drawing Index contain data on versions of the tools or test equipment that you can use. It is permitted to use replaced tools. It is not permitted to use superseded tools. 10. If it is necessary to remove more parts for access, you can remove those parts. If you can get access without removing identified parts, it is not necessary to remove all of the identified parts. Jacking and shoring limitations must be observed. 11. Where the work instructions include installation of a kept part, a new or serviceable part with the same part number can be installed as an alternative to the kept part. 12. This service bulletin includes functional test procedures for the systems changed by this service bulletin. More functional tests can possibly be necessary in accordance with standard maintenance practices because of interruption to other airplane systems. 13. Shaded areas in Figures are to separate the non-critical and non-authoritative information from the critical and authoritative information. B. WORK INSTRUCTIONS Group 1-2, Configuration 2: 1. 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 in accordance with FIGURE 1. 5. Group 1-2, Configuration 2: Install the P302 panel in accordance with FIGURE 2. 6. Group 1-2, Configuration 2: Do the wiring changes in accordance with FIGURE 3 and FIGURE 7. 7. Group 1-2, Configuration 2: Do the wiring changes in accordance with FIGURE 4 and FIGURE 7. 8. Group 1-2, Configuration 2: Do the wiring changes in accordance with FIGURE 5, FIGURE 7, and FIGURE 10. 9. Group 1-2, Configuration 2: Do the wiring changes in accordance with FIGURE 6, FIGURE 7, and FIGURE 10. 10. Group 1-2, Configuration 2: Do the wiring changes in accordance with FIGURE 8. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 13, 2007 777-28A0047Revision 6: July 11, 2013 34 of 124 BOEING SERVICE BULLETIN 777-28A0047 ### Page 35 11. Group 1-2, Configuration 2: Do the wiring changes in accordance with FIGURE 9. 12. Group 1-2, Configuration 2: Install the cover on the P301 panel in accordance with FIGURE 11. 13. Group 1-2, Configuration 2: Do the wiring changes in accordance with FIGURE 12 and FIGURE 7. 14. Group 1-2, Configuration 2: Do the wiring changes in accordance with FIGURE 13, FIGURE 7, and FIGURE 17. 15. Group 1-2, Configuration 2: Do the wiring changes in accordance with 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. 17. Group 1-2, Configuration 2: Do the wiring changes in accordance with 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 in accordance with FIGURE 16. 20. Group 1-2, Configuration 2: Install the cover on the P302 panel in accordance with FIGURE 18. 21. Group 1-2, Configuration 2: Do the changes to the P110 and P210 Electrical Load Management System (ELMS) panels in accordance with 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 in accordance with the Boeing service bulletin 777-28A0040. 23. Group 1-2, Configuration 2: Make sure that the AIMS software change is done in accordance with the Boeing service bulletin 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. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 13, 2007 777-28A0047Revision 6: July 11, 2013 35 of 124 BOEING SERVICE BULLETIN 777-28A0047 ### Page 36 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. 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. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 13, 2007 777-28A0047Revision 6: July 11, 2013 36 of 124 BOEING SERVICE BULLETIN 777-28A0047 ### Page 37 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: (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 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 13, 2007 777-28A0047Revision 6: July 11, 2013 37 of 124 BOEING SERVICE BULLETIN 777-28A0047 ### Page 38 LocationPositionSwitch/Control 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 (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 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 13, 2007 777-28A0047Revision 6: July 11, 2013 38 of 124 BOEING SERVICE BULLETIN 777-28A0047 ### Page 39 Number, Location, Name 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 (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: Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 13, 2007 777-28A0047Revision 6: July 11, 2013 39 of 124 BOEING SERVICE BULLETIN 777-28A0047 ### Page 40 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. (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. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 13, 2007 777-28A0047Revision 6: July 11, 2013 40 of 124 BOEING SERVICE BULLETIN 777-28A0047 ### Page 41 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. (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 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 13, 2007 777-28A0047Revision 6: July 11, 2013 41 of 124 BOEING SERVICE BULLETIN 777-28A0047 ### Page 42 — 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. (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. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 13, 2007 777-28A0047Revision 6: July 11, 2013 42 of 124 BOEING SERVICE BULLETIN 777-28A0047 ### Page 43 (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 (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: Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 13, 2007 777-28A0047Revision 6: July 11, 2013 43 of 124 BOEING SERVICE BULLETIN 777-28A0047 ### Page 44 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. 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: Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 13, 2007 777-28A0047Revision 6: July 11, 2013 44 of 124 BOEING SERVICE BULLETIN 777-28A0047 ### Page 45 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. (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: Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 13, 2007 777-28A0047Revision 6: July 11, 2013 45 of 124 BOEING SERVICE BULLETIN 777-28A0047 ### Page 46 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. (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: Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 13, 2007 777-28A0047Revision 6: July 11, 2013 46 of 124 BOEING SERVICE BULLETIN 777-28A0047 ### Page 47 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. (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. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 13, 2007 777-28A0047Revision 6: July 11, 2013 47 of 124 BOEING SERVICE BULLETIN 777-28A0047 ### Page 48 (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 (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. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 13, 2007 777-28A0047Revision 6: July 11, 2013 48 of 124 BOEING SERVICE BULLETIN 777-28A0047 ### Page 49 (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 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. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 13, 2007 777-28A0047Revision 6: July 11, 2013 49 of 124 BOEING SERVICE BULLETIN 777-28A0047 ### Page 50 (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. Group 1-2, Configuration 1: CONDITION: MORE WORK IS NECESSARY - BOND RESISTANCE MEASUREMENT 1. Get access to the P301 panel in the main equipment center. 2. Measure the resistance between the terminal lugs on the ground stud GD41243 to the P301 panel structure in accordance with FIGURE 19. 3. Get access to the P302 panel in the main equipment center. 4. Measure the resistance between the terminal lugs on the ground stud GD41236 to the P302 panel structure in accordance with FIGURE 20. 5. Put the airplane back to a serviceable condition. Group 1-2, Configuration 3: 1. No more work is necessary. Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 13, 2007 777-28A0047Revision 6: July 11, 2013 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 6 July 11, 2013 PROPRIETARY - Copyright © Unpublished Export Controlled ECCN: 9E991 - BOEING 777-28A0047 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 8-371 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 6 July 11, 2013 Export Controlled ECCN: 9E991 - BOEING 777-28A0047 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 1.60 MIN 1.70 MAX S-35L 0.17 MIN 1.00 MAX 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 6 July 11, 2013 Export Controlled ECCN: 9E991 - BOEING 777-28A0047 PROPRIETARY - 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 6 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 6 July 11, 2013 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished 777-28A0047 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. (c) 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. (c) All fasteners common to the bracket must be a minimum of 0.61 inch away from any existing fasteners. FIGURE 1: MAIN EQUIPMENT CENTER - INSTALLATION OF THE P301 PANEL (SHEET 5 OF 6) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 13, 2007 777-28A0047Revision 6 July 11, 2013 55 of 124 BOEING SERVICE BULLETIN 777-28A0047 ### Page 56 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. 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 HDA The parts shown in the table below are provided as extra parts for this figure. More DataQtyIdentificationName -1BACR15BB5D6CRIVET, UNIVERSAL HD FIGURE 1: MAIN EQUIPMENT CENTER - INSTALLATION OF THE P301 PANEL (SHEET 6 OF 6) Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: April 13, 2007 777-28A0047Revision 6 July 11, 2013 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 DO FWD • U47951 FIGURE 2: MAIN EQUIPMENT CENTER - INSTALLATION OF THE P302 PANEL (SHEET 1 OF 6) Original Issue: April 13, 2007 Revision 6 July 11, 2013 PROPRIETARY - Copyright © Unpublished Export Controlled ECCN: 9E991 - BOEING 777-28A0047 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 S-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 6 July 11, 2013 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Z110 89 ### Page 59 (OCR) BOEING SERVICE BULLETIN 777-28A0047 STA 309.5 1.20 MIN 2.00 MAX - S-36R 0.12 0.30 0.62- 1.17 A-A → INBD .04 FIGURE 2: MAIN EQUIPMENT CENTER - INSTALLATION OF THE P302 PANEL (SHEET 3 OF 6) Original Issue: April 13, 2007 Revision 6 July 11, 2013 Export Controlled ECCN: 9E991 - BOEING 777-28A0047 PROPRIETARY - 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 6 July 11, 2013 Export Controlled ECCN: 9E991 - BOEING PROPRIETARY - Copyright © Unpublished 777-28A0047 Work - See page 1 for details. 60 of 124 The text continues at https://openairdocs.org/service-documents/boeing/777-28a0047/file/d80e76728d1d.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.