# Boeing Alert Service Bulletin 777-28A0034: U.S. DOT/FAA - Service Information - Rights: © The Boeing Company. Filed by the FAA in regulations.gov docket FAA-2008-0847; AD 2013-05-03 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication. - Document: [Boeing Alert Service Bulletin 777-28A0034](https://openairdocs.org/service-documents/boeing/777-28a0034.md) - Title as filed: U.S. DOT/FAA - Service Information - Pages: 96 - PDF: https://openairdocs.org/files/sha256/60/b6/60b63d6e6c8bdd26475d52eda7d2ae1c65911bab970e21093eef881b70cdb516 - Page: https://openairdocs.org/service-documents/boeing/777-28a0034/file/60b63d6e6c8b ## 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: 777-28A0034 Original Issue: August 02, 2007 Revision 2: September 20, 2010 ATA System: 2822 2825 2826 2831 SUBJECT: FUEL - Main and Center Tank Valve Actuators - Inspection and Replacement Export of this technology is controlled under the United States Export Administration Regulations (EAR) (15 CFR 730-774). An export license may be required before it is used for development, production or use by foreign persons from specific countries. The controller of this data has the individual responsibility to abide by all export laws. 9E991ECCN: BOEING PROPRIETARY, CONFIDENTIAL, AND/OR TRADE SECRET Copyright © 2007 The Boeing Company Unpublished Work - All Rights Reserved Boeing claims copyright in each page of this document only to the extent that the page contains copyrightable subject matter. Boeing also claims copyright in this document as a compilation and/or collective work. This document includes proprietary information owned by The Boeing Company and/or one or more third parties. Treatment of the document and the information it contains is governed by contract with Boeing. For more information, contact The Boeing Company, P.O. Box 3707, Seattle, Washington 98124. Boeing, the Boeing signature, the Boeing symbol, 707, 717, 727, 737, 747, 757, 767, 777, 787, Dreamliner, BBJ, DC-8, DC-9, DC-10, KC-10, KDC-10, MD-10, MD-11, MD-80, MD-88, MD-90, P-8A, Poseidon and the Boeing livery are all trademarks owned by The Boeing Company; and no trademark license is granted in connection with this document unless provided in writing by Boeing. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 02, 2007 777-28A0034Revision 2: September 20, 2010 1 of 96 2.0 ### Page 2 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 02, 2007 777-28A0034Revision 2: September 20, 2010 2 of 96 BOEING SERVICE BULLETIN 777-28A0034 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 4 C. Reason ................................................ 1 4 D. Description .............................................. 1 4 E. Compliance .............................................. 1 5 F. Approval ............................................... 1 6 G. Manpower .............................................. 1 6 H. Weight and Balance Changes .................................... 2 8 I. Electrical Load Data ......................................... 2 8 J. References .............................................. 2 8 1. Existing Data: ......................................... 2 8 2. Data supplied with this Service Bulletin: ........................... 2 8 3. Installation Drawings Used in the Preparation of this Service Bulletin: ........... 2 9 K. Publications Affected ........................................ 2 9 L. Interchangeability and Intermixability of Parts ........................... 2 9 2. MATERIAL INFORMATION ........................................ 3 1 A. Material - Price and Availability ................................... 3 1 B. Industry Support Information .................................... 3 1 C. Parts Necessary For Each Airplane ................................. 3 1 1. Kits/Parts: ........................................... 3 1 2. Parts and Materials Supplied by the Operator: ........................ 3 1 3. Parts Modified and Reidentified: ............................... 3 2 4. Parts Removed and Not Replaced: .............................. 3 2 D. Parts Necessary to Change Spares ................................. 3 2 E. Special Tooling - Price and Availability ............................... 3 2 F. Special Tooling Necessary to do this Service Bulletin ....................... 3 3 3. ACCOMPLISHMENT INSTRUCTIONS .................................. 3 5 A. GENERAL INFORMATION ..................................... 3 5 B. WORK INSTRUCTIONS ....................................... 3 5 FIGURE 1: INSPECT AND RECORD THE ENGINE FUEL SPAR MOV ACTUATOR PART NUMBER (LEFT WING) .............................................. 5 4 FIGURE 2: REMOVE AND KEEP INDEX PLATE ............................. 5 6 FIGURE 3: REWORK INDEX PLATE ................................... 5 8 FIGURE 4: MEASURE AND RECORD ELECTRICAL RESISTANCE FROM THE ADAPTER PLATE TO THE AIRPLANE STRUCTURE ................................ 5 9 FIGURE 5: PREPARE ADAPTER PLATE SURFACE ........................... 6 0 FIGURE 6: PUT INDEX PLATE IN POSITION FOR INSTALLATION .................. 6 1 FIGURE 7: INSTALL THE MOV ACTUATOR (DIRECTLY TO THE INDEX PLATE) .......... 6 2 FIGURE 8: CLEAN ADAPTER PLATE AND AIRPLANE SURFACE ................... 6 6 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 02, 2007 777-28A0034Revision 2: September 20, 2010 3 of 96 BOEING SERVICE BULLETIN 777-28A0034 ### Page 4 FIGURE 9: INSPECT AND RECORD THE ENGINE FUEL SPAR MOV ACTUATOR PART NUMBER (RIGHT WING) .............................................. 6 7 FIGURE 10: INSPECT AND RECORD THE FORWARD/AFT CROSSFEED MOV ACTUATOR PART NUMBER (LEFT WING) .......................................... 6 9 FIGURE 11: INSPECT AND RECORD THE APU FUEL SHUTOFF MOV ACTUATOR PART NUMBER (LEFT WING). ............................................. 7 1 FIGURE 12: INSPECT AND RECORD THE APU ISOLATION MOV ACTUATOR PART NUMBER (LEFT WING). ............................................. 7 3 FIGURE 13: REWORK BRACKET AT APU ISOLATION MOV ACTUATOR AREA ONLY ........ 7 5 FIGURE 14: INSPECT AND RECORD THE DEFUEL MOV ACTUATOR PART NUMBER (RIGHT WING). .................................................. 7 9 FIGURE 15: INSPECT AND RECORD FUEL JETTISON NOZZLE MOV ACTUATOR PART NUMBER (INSIDE THE LEFT WING AREA) .................................... 8 1 FIGURE 16: INSPECT AND RECORD FUEL JETTISON NOZZLE MOV ACTUATOR PART NUMBER (INSIDE THE RIGHT WING AREA) ................................... 8 2 FIGURE 17: INSPECT AND RECORD FUEL JETTISON NOZZLE MOV ACTUATOR PART NUMBER (LEFT WING) .............................................. 8 3 FIGURE 18: INSPECT AND RECORD FUEL JETTISON NOZZLE MOV ACTUATOR PART NUMBER (RIGHT WING) .............................................. 8 4 FIGURE 19: INSPECT AND RECORD FUEL JETTISON ISOLATION MOV ACTUATOR PART NUMBER (LEFT WING) .......................................... 8 5 FIGURE 20: INSPECT AND RECORD FUEL JETTISON ISOLATION MOV ACTUATOR PART NUMBER (RIGHT WING) ......................................... 8 7 FIGURE 21: INSTALL THE MOV ACTUATOR ............................... 8 9 FIGURE 22: INSTALL THE FUEL JETTISON NOZZLE VALVE MOV ACTUATOR (INSIDE WING AREA) .................................................. 9 3 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 02, 2007 777-28A0034Revision 2: September 20, 2010 4 of 96 BOEING SERVICE BULLETIN 777-28A0034 ### Page 5 Commercial Airplanes 777 Service Bulletin Revision Transmittal SheetNumber: 777-28A0034Original Issue: August 02, 2007 Revision 2: September 20, 2010 ATA System: 2822 2825 2826 2831 SUBJECT: FUEL - Main and Center Tank Valve Actuators - Inspection and Replacement This revision includes all pages of the service bulletin. COMPLIANCE INFORMATION RELATED TO THIS REVISION Federal Aviation Administration (FAA) Notice of Proposed Rule Making NPRM 2008-NM-056-AD, is related to this service bulletin. No more work is necessary on the airplane(s) changed in accordance with the original issue or Revision 1 of this service bulletin. REASON FOR REVISION This revision is sent to inform operators of the following corrections to apply cap seal to the fasteners of the Motor Operated Valve (MOV) actuator bonding jumper fasteners: – In paragraph 2.C., Parts Necessary For Each Airplane, the QTY for BMS 5-95 was increased to reflect the approximate total amount to consume when applying cap seal to the bonding jumper fasteners. – In paragraph 2.C., Parts Necessary For Each Airplane, footnote (e) was added to clarify optional part numbers for BMS 5-95 when applying cap seal on the bonding jumper fasteners. – In Figure 7, Figure 21, and Figure 22, for the install of the MOV actuator, the step table was revised to add a step to apply cap seal on the bonding jumper fasteners after measuring the electrical bond resistance. – In Figure 7, Figure 21, and Figure 22, footnote (f) was added to clarify optional part numbers for BMS 5-95 when applying cap seal on the bonding jumper fasteners. The information given in Information Notice 777-28A0034 IN 3 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 August 02, 2007Original Issue: May 20, 2010Revision 1: September 20, 2010Revision 2: BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 02, 2007 777-28A0034Revision 2: September 20, 2010 5 of 96 ### Page 6 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 02, 2007 777-28A0034Revision 2: September 20, 2010 6 of 96 BOEING SERVICE BULLETIN 777-28A0034 BLANK PAGE ### Page 7 Commercial Airplanes 777 Service Bulletin SummaryNumber: 777-28A0034Original Issue: August 02, 2007 Revision 2: September 20, 2010 ATA System: 2822 2825 2826 2831 SUBJECT: FUEL - Main and Center Tank Valve Actuators - Inspection and Replacement CONCURRENT REQUIREMENTS None BACKGROUND This service bulletin gives instruction to inspect all the motor operated valve (MOV) actuators and to install new MOV actuators where necessary. The MOV actuators are installed at each fuel system. The new MOV actuator will prevent electrical current flow through the actuator into the fuel tank. If this service bulletin is not done it is possible that a flow of electricity into the fuel tank will supply an ignition source for the fuel fumes in the tank. The Boeing system safety assessment necessary for Special Federal Aviation Regulation (SFAR) 88, showed that under specific conditions it was possible for electrical current to flow through certain MOV actuators into the fuel tank. A new MOV actuator is available to replace the existing MOV actuator with this condition. The new MOV actuator includes an internal electrical isolator to give the MOV actuator protection against electrical energy from lightning, 115 VAC hot shorts, and 28 VDC internal shorts. The new MOV actuator will prevent the flow of an electrical current into the fuel tank and increase the reliability of the fuel system. This service bulletin replaces the MOV actuator part number MA20A1001-1 with the new MOV actuator part number MA30A1001. The MOV actuator part number MA20A1001-1 is the only installed MOV actuator part number that is affected by this service bulletin. This service bulletin gives instruction on how to measure the electrical resistance of bonds at the installed MOV actuator locations, how to prepare a Faying surface for the install of the new MOV actuator, how to prepare affected airplane parts, and how to install the new MOV actuator. This service bulletin is the result of a safety assessment conducted by Boeing under SFAR 88, "Fuel Tank System Fault Tolerance Evaluation Requirements". Section 9 of the Maintenance Planning Data (MPD) document was changed. ACTION (PRR 61777-187, PRR 61998-3) The following actions are necessary: BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 02, 2007 777-28A0034Revision 2: September 20, 2010 7 of 96 ### Page 8 — Gain access to each MOV actuator. — Inspect each MOV actuator part number. If the MOV actuator part number is MA20A1001-1, remove, discard, and replace with the MOV actuator part number MA30A1001. The MOV actuator part number MA20A1001-1 is the only installed MOV actuator part number that is affected by this service bulletin. — If you are required to install the MOV actuator part number MA30A1001, you must do an electrical resistance check of each location. If the measured resistance is not acceptable, you must rework the Faying bond and the airplane parts. This may require rework of the index plate and the adapter plate. This may require a tank entry to rework the interface between the adapter plate and the airplane structure. — Remove, rework, and reinstall the bracket at the APU Isolation MOV actuator location to prevent part interference with the new MOV actuator part number MA30A1001. — Close access to each MOV actuator. EFFECTIVITY 777 -200 /-200LR /-300 /-300ER airplanes. Refer to Paragraph 1.A., Effectivity for the list of affected airplanes. COMPLIANCE Federal Aviation Administration (FAA) Notice of Proposed Rule Making 2008-NM-056-AD, is related to this service bulletin. Boeing recommends that operators accomplish this service bulletin be incorporated within 60 months after the original issue date on this service bulletin. INDUSTRY SUPPORT INFORMATION Boeing warranty remedies are not available for the configuration changes given in this service bulletin. MANPOWER Elapsed HoursTotal Task HoursAirplanes 142.35 (a) (b)327.35 (a)(b)Group 1 182.05 (a) (b)427.05 (a)(b)Group 2 (a) Entry into the fuel tank should not be frequent. (b) If entry into the fuel tank is not necessary, the time needed to do the work is much less. MATERIAL INFORMATION Boeing Supplied Kits/Parts. Refer to Paragraph 2.A., Material - Price and Availability. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 02, 2007 777-28A0034Revision 2: September 20, 2010 8 of 96 BOEING SERVICE BULLETIN 777-28A0034 ### Page 9 (OCR) BOEING SERVICE BULLETIN 777-28A0034 FUEL JETTISON FORWARD/ AFT ISOLATION MOV ACTUATOR CROSS FEED MOV ACTUATOR FUEL JETTISON NOZZLE MOV APU FUEL SHUTOFF ACTUATOR MOV ACTUATOR APU FUEL ISOLATION MOV ACTUATOR FUEL JETTISON ISOLATION MOV DEFUELING MOV ACTUATOR ACTUATOR ENGINE FUEL SPAR MOV ACTUATOR FUEL JETTISON NOZZLE MOV ACTUATOR INSPECT THE MOV ACTUATORS AT THE ABOVE LOCATIONS. - IF THE MOV ACTUATOR HAS AN UNACCEPTABLE PART NUMBER, REPLACE THE MOV ACTUATOR. - AT LOCATIONS WITH AN INDEX PLATE, PREPARE AN ELECTRICAL BOND. REAR SPAR INDEX REAR SPAR PLATE FWD ADAPTER PLATE → FWD TYPICAL MOV ACTURATOR TYPICAL MOV ACTUATOR INSTALLATION WITHOUT INDEX INSTALLATION WITH INDEX PLATE PLATE U32450 Original Issue: August 02, 2007 Revision 2: September 20, 2010 777-28A0034 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 9 of 96 ### Page 10 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 02, 2007 777-28A0034Revision 2: September 20, 2010 10 of 96 BOEING SERVICE BULLETIN 777-28A0034 BLANK PAGE ### Page 11 Commercial Airplanes 777 Service Bulletin Number: 777-28A0034 Original Issue: August 02, 2007 Revision 2: September 20, 2010 ATA System: 2822 2825 2826 2831 SUBJECT: FUEL - Main and Center Tank Valve Actuators - Inspection and Replacement 1. PLANNING INFORMATION A. Effectivity 1. Airplanes Refer to Service Bulletin Index Document 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 61998-3 for data about this change. DESCRIPTIONCONFIGURATIONGROUP 777-200/-300 airplanes with jettison nozzle MOV actuator located inside the rear wing area. -1 777-200LR/-300ER airplanes with jettison nozzle MOV actuator located on the rear wing spar. -2 Airplane Models: 777-200, 777-200LR, 777-300, 777-300ER GroupVariable Number 1WA001 - WA017 1WA076 - WA080 1WA086 - WA093 1WA101 - WA104 1WA116 - WA119 1WA131 - WA137 1WA171 - WA175 1WA196 - WA198 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 02, 2007 777-28A0034Revision 2: September 20, 2010 11 of 96 ### Page 12 GroupVariable Number 1WA206 - WA212 1WA221 - WA223 1WA231 - WA232 1WA241 - WA250 1WA261 - WA266 1WA281 - WA282 1WA301 - WA304 1WB001 - WB021 1WB031 - WB046 1WB051 - WB088 1WB101 - WB106 1WB121 - WB125 1WB131 - WB141 1WB151 - WB155 1WB161 - WB177 1WB181 - WB194 1WB201 - WB215 1WB231 - WB247 1WB271 - WB273 1WB276 - WB286 1WB291 - WB302 1WB306 - WB307 1WB311 - WB337 1WB341 - WB342 1WB366 - WB368 1WB371 - WB388 1WB406 1WB411 - WB413 1WB416 - WB437 1WB446 - WB453 1WB476 1WB481 - WB484 1WB501 - WB511 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 02, 2007 777-28A0034Revision 2: September 20, 2010 12 of 96 BOEING SERVICE BULLETIN 777-28A0034 ### Page 13 GroupVariable Number 1WB531 - WB537 1WB551 - WB554 1WB591 - WB597 1WB601 - WB606 1WB611 - WB622 1WB631 - WB638 1WB646 - WB649 1WC051 - WC073 1WC101 - WC104 1WC111 - WC116 1WC241 - WC243 1WC281 - WC290 1WC301 - WC308 1WC361 - WC364 1WC371 - WC374 1WC381 - WC390 1WC441 1WC446 - WC448 1WC456 - WC458 1WC486 - WC489 2WD001 - WD002 2WD501 - WD504 2WD521 - WD532 2WD561 - WD563 2WD581 - WD586 2WD606 2WD621 - WD625 2WD651 - WD652 2WD671 - WD675 2. Spares Affected Examine your spares supply for the parts or components identified in Paragraph 2.C., Parts Necessary for Each Airplane. If any parts or components are found, refer to Paragraph 2.C. for the recommended use. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 02, 2007 777-28A0034Revision 2: September 20, 2010 13 of 96 BOEING SERVICE BULLETIN 777-28A0034 ### Page 14 B. Concurrent Requirements None. C. Reason This service bulletin gives instruction to inspect all the motor operated valve (MOV) actuators and to install new MOV actuators where necessary. The MOV actuators are installed at each fuel system. The new MOV actuator will prevent electrical current flow through the actuator into the fuel tank. If this service bulletin is not done it is possible that a flow of electricity into the fuel tank will supply an ignition source for the fuel fumes in the tank. The Boeing system safety assessment necessary for Special Federal Aviation Regulation (SFAR) 88, showed that under specific conditions it was possible for electrical current to flow through certain MOV actuators into the fuel tank. A new MOV actuator is available to replace the existing MOV actuator with this condition. The new MOV actuator includes an internal electrical isolator to give the MOV actuator protection against electrical energy from lightning, 115 VAC hot shorts, and 28 VDC internal shorts. The new MOV actuator will prevent the flow of an electrical current into the fuel tank and increase the reliability of the fuel system. This service bulletin replaces the MOV actuator part number MA20A1001-1 with the new MOV actuator part number MA30A1001. The MOV actuator part number MA20A1001-1 is the only installed MOV actuator part number that is affected by this service bulletin. This service bulletin gives instruction on how to measure the electrical resistance of bonds at the installed MOV actuator locations, how to prepare a Faying surface for the install of the new MOV actuator, how to prepare affected airplane parts, and how to install the new MOV actuator. This service bulletin is the result of a safety assessment conducted by Boeing under SFAR 88, "Fuel Tank System Fault Tolerance Evaluation Requirements". Section 9 of the Maintenance Planning Data (MPD) document was changed. Revision 1 is sent to correct the accomplishment instructions and to correct the MOV actuator part number. Revision 2 is sent to add a step to apply BMS 5-95 as cap seal on the bonding jumper fasteners, to clarify the quantity of BMS 5-95 consumed, and to clarify optional part numbers for BMS 5-95 when installing the MOV actuator. D. Description The following actions are necessary: BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 02, 2007 777-28A0034Revision 2: September 20, 2010 14 of 96 BOEING SERVICE BULLETIN 777-28A0034 ### Page 15 — Gain access to each MOV actuator. — Inspect each MOV actuator part number. If the MOV actuator part number is MA20A1001-1, remove, discard, and replace with the MOV actuator part number MA30A1001. The MOV actuator part number MA20A1001-1 is the only installed MOV actuator part number that is affected by this service bulletin. — If you are required to install the MOV actuator part number MA30A1001, you must do an electrical resistance check of each location. If the measured resistance is not acceptable, you must rework the Faying bond and the airplane parts. This may require rework of the index plate and the adapter plate. This may require a tank entry to rework the interface between the adapter plate and the airplane structure. — Remove, rework, and reinstall the bracket at the APU Isolation MOV actuator location to prevent part interference with the new MOV actuator part number MA30A1001. — Close access to each MOV actuator. Revision 1 - No more work is necessary on airplanes changed as shown in the original issue of this service bulletin. Revision 2 - No more work is necessary on airplanes changed in accordance with the original issue or Revision 1 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 531, 533, 543, 551, 631, 633, 643, 651777-200, 777-300 Group 2: Affected Maintenance Zones ZoneModel 531, 533, 543, 551, 631, 633, 643, 651777-200LR, 777-300ER E. Compliance Federal Aviation Administration (FAA) Notice of Proposed Rule Making 2008-NM-056-AD, is related to this service bulletin. Boeing recommends that operators accomplish this service bulletin be incorporated within 60 months after the original issue date on this service bulletin. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 02, 2007 777-28A0034Revision 2: September 20, 2010 15 of 96 BOEING SERVICE BULLETIN 777-28A0034 ### Page 16 F. Approval This service bulletin was examined by the Federal Aviation Administration (FAA). The changes specified in this service bulletin comply with the applicable regulations and are FAA approved, as well as European Aviation Safety Agency (EASA)/Joint Aviation Authorities (JAA) approved for all EASA/JAA approved airplanes listed in the service bulletin effectivity. This service bulletin and its approval were based on the airplane in its original Boeing delivery configuration or as modified by other approved Boeing changes. If an airplane has a non-Boeing modification or repair that affects a component or system also affected by this service bulletin, the operator is responsible for obtaining appropriate regulatory agency approval before incorporating this service bulletin. G. Manpower The tables below shows an estimate of the task hours necessary to do these work packages 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 inspect the work  Time to cure the materials  Time to make the parts  Time to find the tools. Work Package Versus MOV Actuator Equipment Numbers MOV Actuator Equipment No.Work Package No. V281641 V282642 V28163/V282633 V280234 V280315 V283106 V281667 V282668 V281669 V2826610 V2816511 V2826512 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 02, 2007 777-28A0034Revision 2: September 20, 2010 16 of 96 BOEING SERVICE BULLETIN 777-28A0034 ### Page 17 Work Packages for All Groups Elapsed Hours Task HoursNumber of Persons TasksWork Package 0.501.002PrepareWork Package 1 0.100.101Open MOV ac- tuator access 0.250.251Figure 1 0.250.251Remove MOV actuator 1.001.001Figure 2 1.001.001Figure 3 0.500.501Figure 4 8.0032.04MOV access/ fuel tank entry (a) 1.002.002Remove adapter plate and adapter shaft (a) 1.001.001Figure 8 (a) 1.002.002Install adapter plate and adapter shaft (a) 0.500.501Figure 4 (a) 1.501.501Figure 5 0.500.501Figure 6 0.500.501Install index plate 0.250.251Figure 7 4.008.002Close fuel tank access (a) 0.100.101Close MOV ac- tuator access 21.9552.45Total for Work Package BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 02, 2007 777-28A0034Revision 2: September 20, 2010 17 of 96 BOEING SERVICE BULLETIN 777-28A0034 ### Page 18 Work Packages for All Groups Elapsed Hours Task HoursNumber of Persons TasksWork Package 0.501.002PrepareWork Package 2 0.100.101Open MOV ac- tuator access 0.250.251Figure 9 0.250.251Remove MOV actuator 1.001.001Figure 2 1.001.001Figure 3 0.500.501Figure 4 8.0032.04MOV access/ fuel tank entry (a) 1.002.002Remove adapter plate and adapter shaft (a) 1.001.001Figure 8 (a) 1.002.002Install adapter plate and adapter shaft (a) 0.500.501Figure 4 (a) 1.501.501Figure 5 0.500.501Figure 6 0.500.501Install index plate 0.250.251Figure 7 4.008.002Close fuel tank access (a) 0.100.101Close MOV ac- tuator access 21.9552.45Total for Work Package BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 02, 2007 777-28A0034Revision 2: September 20, 2010 18 of 96 BOEING SERVICE BULLETIN 777-28A0034 ### Page 19 Work Packages for All Groups Elapsed Hours Task HoursNumber of Persons TasksWork Package 0.501.002PrepareWork Package 3 0.100.101Open MOV ac- tuator access 0.500.501Figure 10 0.250.251Remove MOV actuator 1.001.001Figure 2 1.001.001Figure 3 0.500.501Figure 4 8.0032.04MOV access/ fuel tank entry (a) 1.002.002Remove adapter plate and adapter shaft (a) 1.001.001Figure 8 (a) 1.002.002Install adapter plate and adapter shaft (a) 0.500.501Figure 4 (a) 1.501.501Figure 5 0.500.501Figure 6 0.500.501Install index plate 0.250.251Figure 7 4.008.002Close fuel tank access (a) 0.100.101Close MOV ac- tuator access 22.2052.70Total for Work Package BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 02, 2007 777-28A0034Revision 2: September 20, 2010 19 of 96 BOEING SERVICE BULLETIN 777-28A0034 ### Page 20 Work Packages for All Groups Elapsed Hours Task HoursNumber of Persons TasksWork Package 0.501.002PrepareWork Package 4 0.100.101Open MOV ac- tuator access 0.500.501Figure 11 0.250.251Remove MOV actuator 0.250.251Figure 21 0.500.501Close MOV ac- tuator access 2.12.6Total for Work Package 0.501.002PrepareWork Package 5 0.100.101Open MOV ac- tuator access 0.500.501Figure 12 0.250.251Remove MOV actuator 2.002.001Figure 13 0.250.251Figure 21 0.500.501Close MOV ac- tuator access 4.14.6Total for Work Package BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 02, 2007 777-28A0034Revision 2: September 20, 2010 20 of 96 BOEING SERVICE BULLETIN 777-28A0034 ### Page 21 Work Packages for All Groups Elapsed Hours Task HoursNumber of Persons TasksWork Package 0.501.002PrepareWork Package 6 0.100.101Open MOV ac- tuator access 0.250.251Figure 14 0.250.251Remove MOV actuator 1.001.001Figure 2 1.001.001Figure 3 0.500.501Figure 4 8.0032.04MOV access/ fuel tank entry (a) 1.002.002Remove adapter plate and adapter shaft (a) 1.001.001Figure 8 (a) 1.002.002Install adapter plate and adapter shaft (a) 0.500.501Figure 4 (a) 1.501.501Figure 5 0.500.501Figure 6 0.500.501Install index plate 0.250.251Figure 7 4.008.002Close fuel tank access (a) 0.100.101Close MOV ac- tuator access 21.9552.45Total for Work Package BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 02, 2007 777-28A0034Revision 2: September 20, 2010 21 of 96 BOEING SERVICE BULLETIN 777-28A0034 ### Page 22 Work Packages for All Groups Elapsed Hours Task HoursNumber of Persons TasksWork Package 0.501.002PrepareWork Package 7 0.100.101Open MOV ac- tuator access 0.500.501Figure 15 0.250.251Remove MOV actuator 0.250.251Figure 22 0.500.501Close MOV ac- tuator access 2.12.6Total for Work Package 0.501.002PrepareWork Package 8 0.100.101Open MOV ac- tuator access 0.500.501Figure 16 0.250.251Remove MOV actuator 0.250.251Figure 22 0.500.501Close MOV ac- tuator access 2.12.6Total for Work Package BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 02, 2007 777-28A0034Revision 2: September 20, 2010 22 of 96 BOEING SERVICE BULLETIN 777-28A0034 ### Page 23 Work Packages for All Groups Elapsed Hours Task HoursNumber of Persons TasksWork Package 0.501.002PrepareWork Package 9 0.100.101Open MOV ac- tuator access 0.250.251Figure 17 0.250.251Remove MOV actuator 1.001.001Figure 2 1.001.001Figure 3 0.500.501Figure 4 8.0032.04MOV access/ fuel tank entry (a) 1.002.002Remove adapter plate and adapter shaft (a) 1.001.001Figure 8 (a) 1.002.002Install adapter plate and adapter shaft (a) 0.500.501Figure 4 (a) 1.501.501Figure 5 0.500.501Figure 6 0.500.501Install index plate 0.250.251Figure 7 4.008.002Close fuel tank access (a) 0.100.101Close MOV ac- tuator access 21.9552.45Total for Work Package BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 02, 2007 777-28A0034Revision 2: September 20, 2010 23 of 96 BOEING SERVICE BULLETIN 777-28A0034 ### Page 24 Work Packages for All Groups Elapsed Hours Task HoursNumber of Persons TasksWork Package 0.501.002PrepareWork Package 10 0.100.101Open MOV ac- tuator access 0.250.251Figure 18 0.250.251Remove MOV actuator 1.001.001Figure 2 1.001.001Figure 3 0.500.501Figure 4 8.0032.04MOV access/ fuel tank entry (a) 1.002.002Remove adapter plate and adapter shaft (a) 1.001.001Figure 8 (a) 1.002.002Install adapter plate and adapter shaft (a) 0.500.501Figure 4 (a) 1.501.501Figure 5 0.500.501Figure 6 0.500.501Install index plate 0.250.251Figure 7 4.008.002Close fuel tank access (a) 0.100.101Close MOV ac- tuator access 21.9552.45Total for Work Package BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 02, 2007 777-28A0034Revision 2: September 20, 2010 24 of 96 BOEING SERVICE BULLETIN 777-28A0034 ### Page 25 Work Packages for All Groups Elapsed Hours Task HoursNumber of Persons TasksWork Package 0.501.002PrepareWork Package 11 0.100.101Open MOV ac- tuator access 0.250.251Figure 19 0.250.251Remove MOV actuator 1.001.001Figure 2 1.001.001Figure 3 0.500.501Figure 4 8.0032.04MOV access/ fuel tank entry (a) 1.002.002Remove adapter plate and adapter shaft (a) 1.001.001Figure 8 (a) 1.002.002Install adapter plate and adapter shaft (a) 0.500.501Figure 4 (a) 1.501.501Figure 5 0.500.501Figure 6 0.500.501Install index plate 0.250.251Figure 7 4.008.002Close fuel tank access (a) 0.100.101Close MOV ac- tuator access 21.9552.45Total for Work Package BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 02, 2007 777-28A0034Revision 2: September 20, 2010 25 of 96 BOEING SERVICE BULLETIN 777-28A0034 ### Page 26 Work Packages for All Groups Elapsed Hours Task HoursNumber of Persons TasksWork Package 0.501.002PrepareWork Package 12 0.100.101Open MOV ac- tuator access 0.250.251Figure 20 0.250.251Remove MOV actuator 1.001.001Figure 2 1.001.001Figure 3 0.500.501Figure 4 8.0032.04MOV access/ fuel tank entry (a) 1.002.002Remove adapter plate and adapter shaft (a) 1.001.001Figure 8 (a) 1.002.002Install adapter plate and adapter shaft (a) 0.500.501Figure 4 (a) 1.501.501Figure 5 0.500.501Figure 6 0.500.501Install index plate 0.250.251Figure 7 4.008.002Close fuel tank access (a) 0.100.101Close MOV ac- tuator access 21.9552.45Total for Work Package (a) Task is associated with a tank entry. A tank entry should not be likely. A tank entry is only required if the electrical bonding resistance measure is not satisfactory. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 02, 2007 777-28A0034Revision 2: September 20, 2010 26 of 96 BOEING SERVICE BULLETIN 777-28A0034 ### Page 27 Group 1: Only the Work Packages for this Group Total Elapsed Hours (a)Total Task-Hours (a)Sum of Work Packages 21.9552.45Work Package 1 21.9552.45Work Package 2 22.2052.70Work Package 3 2.102.60Work Package 4 4.104.60Work Package 5 21.9552.45Work Package 6 2.102.60Work Package 7 2.102.60Work Package 8 21.9552.45Work Package 11 21.9552.45Work Package 12 142.35327.35TOTAL FOR EACH AIRPLANE (a) See the Work Package tables for details. Group 2: Only the Work Packages for this Group Total Elapsed Hours (a)Total Task-Hours (a)Sum of Work Packages 21.9552.45Work Package 1 21.9552.45Work Package 2 22.2052.70Work Package 3 2.102.60Work Package 4 4.104.60Work Package 5 21.9552.45Work Package 6 21.9552.45Work Package 9 21.9552.45Work Package 10 21.9552.45Work Package 11 21.9552.45Work Package 12 182.05427.05TOTAL FOR EACH AIRPLANE (a) See the Work Package tables for details. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 02, 2007 777-28A0034Revision 2: September 20, 2010 27 of 96 BOEING SERVICE BULLETIN 777-28A0034 ### Page 28 H. Weight and Balance Changes Change in Moment (Pound-Inches) Change in Weight (Pounds) Airplane +5448.9+4.1777-200 +6199.2+4.1777-300 Change in Moment (Pound-Inch- es) Change in Weight (Pounds)Work Package +483.2+0.4Work Package 1 +483.2+0.4Work Package 2 +466.6+0.4Work Package 3 +474.0+0.4Work Package 4 +474.0+0.4Work Package 5 +465.1+0.4Work Package 6 +582.4+0.4Work Package 7 +582.4+0.4Work Package 8 +582.4+0.4Work Package 9 +582.4+0.4Work Package 10 +465.3+0.4Work Package 11 +465.3+0.4Work Package 12 I. Electrical Load Data Not changed. J. References 1. Existing Data: a. Engineering Change Memo PRR 61998-3 b. Standard Overhaul Practices Manual (SOPM) 20-30-03, 20-43-03, 20-50-10 c. Standard Wiring Practices Manual (SWPM) 20-20-00 d. 777 Aircraft Maintenance Manual (AMM) 28-22-01, 28-22-02, 28-22-02, 28-22-03, 28-22-04, 28-25-02, 28-25-05, 28-26-01, 28-26-02, 28-31-02, 28-31-03, 28-31-04, 28-31-05 e. FAA Notice of Proposed Rule Making 2008-NM-056-AD. 2. Data supplied with this Service Bulletin: None. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 02, 2007 777-28A0034Revision 2: September 20, 2010 28 of 96 BOEING SERVICE BULLETIN 777-28A0034 ### Page 29 3. Installation Drawings Used in the Preparation of this Service Bulletin: TitleDrawing Number Equipment Inst - Engine Fuel Feed System343W3001 Equipment Inst - Refueling and Jettison System (left wing)344W3001 Equipment Inst - Refueling and Jettison System (right wing)344W3001 Equipment Inst - APU Fuel Feed (wing)346W3001 Rear Spar Assy - Wing112W1003 K. Publications Affected Chapter-SectionPublication 28-22, 28-25, 28-26, 28-31777 Maintenance Manual 28-22, 28-25, 28-26, 28-31777 Illustrated Parts Catalog 9777 Maintenance Planning Data 1. Publications: None. 2. Damage Tolerance Based Structural Inspections: Boeing has evaluated the repairs and/or changes in this service bulletin for effects on Fatigue Critical Structure (FCS) and for changes to Damage Tolerance Inspections (DTI) required in the Maintenance Program. This service bulletin does not affect FCS, therefore DTIs are not necessary. L. Interchangeability and Intermixability of Parts Refer to Paragraph 2.C., Parts Necessary For Each Airplane, for interchangeability and intermixability information. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 02, 2007 777-28A0034Revision 2: September 20, 2010 29 of 96 BOEING SERVICE BULLETIN 777-28A0034 ### Page 30 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 02, 2007 777-28A0034Revision 2: September 20, 2010 30 of 96 BOEING SERVICE BULLETIN 777-28A0034 BLANK PAGE ### Page 31 2. MATERIAL INFORMATION A. Material - Price and Availability The operator can supply the parts and materials shown in Paragraph 2.C., Parts Necessary For Each Airplane. As an alternative, operators can purchase the parts from Boeing Spares. This service bulletin does not show the Boeing price and supply data. 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: None. 2. Parts and Materials Supplied by the Operator: Group 1: NotesNameQTYPart Number / Specification Replaces MA20A1001-1 (S343T003-39) Motor Operated Valve Actuator11MA30A1001 (S343T003-66) (a) (b) (c) (e)pressure and environmental sealant- chromate type, class B 66 ozBMS 5-95 (d)bonding jumper, 5 inch6BACJ40A20-5 (d)bonding jumper, 6 inch3BACJ40A20-6 (d)bonding jumper, 7 inch1BACJ40A20-7 (d)bonding jumper, 9 inch1BACJ40A20-9 colored chemical conversion coating for aluminum, type 2, class A or D 4 oz.BAC 5626 chemical and solvent resistant finish (primer) 4 oz.BMS 10-11 (a) Supplier: ITT Aerospace Controls 28150 Industry Drive, Valencia, CA, 91355 USA. (b) For use on surfaces outside of a fuel tank that may be exposed to fuel. (c) BMS 5-45 Fuel Tank Sealant is optional (BAC5117-6). (d) The new MOV actuator (MA30A1001) installation may require that a longer bonding jumper be installed to reach the bonding jumper mounting screw on either side of the MOV actuator. (e) BMS 5-45 or BMS 5-145 can be used as a substitute for BMS 5-95 for the application of cap seal on the MOV actuator bonding jumper fasteners as described in the work packages of this service bulletin. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 02, 2007 777-28A0034Revision 2: September 20, 2010 31 of 96 BOEING SERVICE BULLETIN 777-28A0034 ### Page 32 Group 2: NotesNameQTYPart Number / Specification Replaces MA20A1001-1 (S343T003-39) Motor Operated Valve Actuator11MA30A1001 (S343T003-66) (a) (b) (c) (e)Pressure and Environmental Sealant-Chromate Type 66 ozBMS 5-95 (d)bonding jumper, 5 inch6BACJ40A20-5 (d)bonding jumper, 6 inch1BACJ40A20-6 (d)bonding jumper, 7 inch3BACJ40A20-7 (d)bonding jumper, 9 inch1BACJ40A20-9 colored chemical conversion coating for aluminum, type 2, class A or D 4 oz.BAC 5626 chemical and solvent resistant finish (primer) 4 oz.BMS 10-11 (a) Supplier: ITT Aerospace Controls 28150 Industry Drive, Valencia, CA, 91355 USA (b) For use on surfaces outside of a fuel tank that may be exposed to fuel (c) BMS 5-45 Fuel Tank Sealant is optional (BAC5117-6). (d) The new MOV actuator (MA30A1001) installation may require that a longer bonding jumper be installed to reach the bonding jumper mounting screw on either side of the MOV actuator. (e) BMS 5-45 or BMS 5-145 can be used as a substitute for BMS 5-95 for the application of cap seal on the MOV actuator bonding jumper fasteners as described in the work packages of this service bulletin. 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. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 02, 2007 777-28A0034Revision 2: September 20, 2010 32 of 96 BOEING SERVICE BULLETIN 777-28A0034 ### Page 33 F. Special Tooling Necessary to do this Service Bulletin No special tools or equipment are necessary to do the change in this service bulletin. But, maintenance and overhaul tools in the manuals given in Paragraph 1.J., References, can be necessary. Examine operator tool supply to make sure all necessary tools are available. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 02, 2007 777-28A0034Revision 2: September 20, 2010 33 of 96 BOEING SERVICE BULLETIN 777-28A0034 ### Page 34 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 02, 2007 777-28A0034Revision 2: September 20, 2010 34 of 96 BOEING SERVICE BULLETIN 777-28A0034 BLANK PAGE ### Page 35 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. The work instructions are divided into work packages. Task-Hours and Elapsed-Hours for each package are given in Paragraph 1.G., Manpower. You can do each work package independently. 4. Unless shown differently, these dimensions and tolerances are used: — Torque limits to tighten nuts and bolts are given in Structural Repair Manual, Chapter 51. 5. For approved fastener and process material substitutions, refer to 777 Structural Repair Manual, Chapter 51, Alternate fasteners are given in 777 Structural Repair Manual Chapter 51 and Boeing Drawing 777 012W6100. 6. Refer to the Boeing Standard Wiring Practices Manuals 20-10-11 and 20-10-12 for the wire installation procedures. 7. These work instructions refer to procedures included on other Boeing documents. When the words "refer to" are used and the operator has an accepted alternative procedure, the accepted alternative procedure can be used. When the words "as given in" are included in the instruction, the procedure in the Boeing document must be used. 8. All AMM references refer to the post 777-28A0034 procedures in the AMM. B. WORK INSTRUCTIONS Group 1-2: Work Package 1 - ENGINE FUEL SPAR VALVE ACTUATOR - LEFT (V28164) 1. Get access to the MOV actuator. Refer to 777 AMM 28-22-02 as an accepted procedure. 2. Read and record the part number of the MOV actuator as given in Figure 1. a. If the MOV actuator is not part number MA20A1001-1, the part is acceptable. No more work is necessary at this location. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 02, 2007 777-28A0034Revision 2: September 20, 2010 35 of 96 BOEING SERVICE BULLETIN 777-28A0034 ### Page 36 (1) Close Access to each MOV actuator. Refer to 777 AMM 28-22-02 as an accepted procedure. (2) Put the airplane in a serviceable condition or do another work package. b. If the MOV actuator is part number MA20A1001-1, the part is not acceptable. Do the following steps to install the MOV actuator with part number MA30A1001: (1) Remove and discard the MOV actuator, and remove and keep the bonding jumper. Refer to 777 AMM 28-22-02 as an accepted procedure. (2) Remove and keep the index plate as given in Figure 2. NOTE: Make an ink mark with a pen across the index plate, the adapter plate, and the airplane structure as a reference for installation alignment. (3) Rework the index plate as given in Figure 3. (4) Prepare the adapter plate surface as given in Figure 5. (5) Measure and record the electrical resistance of the bond from the adapter plate to the airplane structure as given in Figure 4. (a) If the resistance is less than 1.5 milliohms, the bond is acceptable. Do the following steps: 1) Temporarily put the index plate in position for installation as given in Figure 6. 2) Install the index plate. Refer to 777 AMM 28-22-01 as an accepted procedure. 3) Install the MOV actuator as given in Figure 7. Refer to 777 AMM 28-22-02 as an accepted procedure for the install of the MOV actuator body. 4) Do an operational test of MOV actuator. Refer to 777 AMM 28-22-02 as an accepted procedure. (b) If the resistance is 1.5 milliohms or greater, the bond is not acceptable. A fuel tank entry is necessary to make an acceptable bond. Do the following steps: 1) Get access to the Motor Operated Valve (MOV). Refer to 777 AMM 28-22-01 as an accepted procedure. 2) Remove the adapter plate and adapter shaft. Refer to 777 AMM 28-22-01 as an accepted procedure. 3) Clean the adapter plate and the airplane structure as given in Figure 8. 4) Install the adapter plate and the adapter shaft. Refer to 777 AMM 28-22-01 as an accepted procedure. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 02, 2007 777-28A0034Revision 2: September 20, 2010 36 of 96 BOEING SERVICE BULLETIN 777-28A0034 ### Page 37 5) Prepare the adapter plate surface as given in Figure 5. 6) Measure and record the electrical resistance of the bond from the adapter plate to the airplane structure as given in Figure 4. a) If the resistance is less than 0.5 milliohms, the bond is acceptable. Do the following steps: {1} Temporarily put the index plate in position for installation as given in Figure 6. {2} Install the index plate. Refer to 777 AMM 28-22-01 as an accepted procedure. {3} Install the MOV actuator as given in Figure 7. Refer to 777 AMM 28-22-02 as an accepted procedure for the install of the MOV actuator body. {4} Do an operational test of MOV actuator. Refer to 777 AMM 28-22-02 as an accepted procedure. b) If the resistance is 0.5 milliohms or greater, the bond is not acceptable. Do the following steps: {1} Return to step 2.b.(5)(b)2) and rework the bond until it is acceptable. 7) Close access to the Motor Operated Valve. Refer to 777 AMM 28-22-01 as an accepted procedure. 3. Close access to the MOV actuator. Refer to 777 AMM 28-22-02 as an accepted procedure. 4. Put the airplane in a serviceable condition or do another work package. Group 1-2: Work Package 2 - ENGINE FUEL SPAR VALVE ACTUATOR - RIGHT (V28264) 1. Get access to the MOV actuator. Refer to 777 AMM 28-22-02 as an accepted procedure. 2. Read and record the part number of the MOV actuator as given in Figure 9. a. If the MOV actuator is not part number MA20A1001-1, the part is acceptable. No more work is necessary at this location. (1) Close Access to each MOV actuator. Refer to 777 AMM 28-22-02 as an accepted procedure. (2) Put the airplane in a serviceable condition or do another work package. b. If the MOV actuator is part number MA20A1001-1, the part is not acceptable. Do the following steps to install the MOV actuator with part number MA30A1001: BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 02, 2007 777-28A0034Revision 2: September 20, 2010 37 of 96 BOEING SERVICE BULLETIN 777-28A0034 ### Page 38 (1) Remove and discard the MOV actuator, and remove and keep the bonding jumper. Refer to 777 AMM 28-22-02 as an accepted procedure. (2) Remove and keep the index plate as given in Figure 2. NOTE: Make an ink mark with a pen across the index plate, the adapter plate, and the airplane structure as a reference for installation alignment. (3) Rework the index plate as given in Figure 3. (4) Prepare the adapter plate surface as given in Figure 5. (5) Measure and record the electrical resistance of the bond from the adapter plate to the airplane structure as given in Figure 4. (a) If the resistance is less than 1.5 milliohms, the bond is acceptable. Do the following steps: 1) Temporarily put the index plate in position for installation as given in Figure 6. 2) Install the index plate. Refer to 777 AMM 28-22-01 as an accepted procedure. 3) Install the MOV actuator as given in Figure 7. Refer to 777 AMM 28-22-02 as an accepted procedure for the install of the MOV actuator body. 4) Do an operational test of MOV actuator. Refer to 777 AMM 28-22-02 as an accepted procedure. (b) If the resistance is 1.5 milliohms or greater, the bond is not acceptable. A fuel tank entry is necessary to make an acceptable bond. Do the following steps: 1) Get access to the Motor Operated Valve (MOV). Refer to 777 AMM 28-22-01 as an accepted procedure. 2) Remove the adapter plate and adapter shaft. Refer to 777 AMM 28-22-01 as an accepted procedure. 3) Clean the adapter plate and the airplane structure as given in Figure 8. 4) Install the adapter plate and the adapter shaft. Refer to 777 AMM 28-22-01 as an accepted procedure. 5) Prepare the adapter plate surface as given in Figure 5. 6) Measure and record the electrical resistance of the bond from the adapter plate to the airplane structure as given in Figure 4. a) If the resistance is less than 0.5 milliohms, the bond is acceptable. Do the following steps: BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 02, 2007 777-28A0034Revision 2: September 20, 2010 38 of 96 BOEING SERVICE BULLETIN 777-28A0034 ### Page 39 {1} Temporarily put the index plate in position for installation as given in Figure 6. {2} Install the index plate. Refer to 777 AMM 28-22-01 as an accepted procedure. {3} Install the MOV actuator as given in Figure 7. Refer to 777 AMM 28-22-02 as an accepted procedure for the install of the MOV actuator body. {4} Do an operational test of MOV actuator. Refer to 777 AMM 28-22-02 as an accepted procedure. b) If the resistance is 0.5 milliohms or greater, the bond is not acceptable. Do the following steps: {1} Return to step 2.b.(5)(b)2) and rework the bond until it is acceptable. 7) Close access to the Motor Operated Valve. Refer to 777 AMM 28-22-01 as an accepted procedure. 3. Close access to the MOV actuator. Refer to 777 AMM 28-22-02 as an accepted procedure. 4. Put the airplane in a serviceable condition or do another work package. Group 1-2: Work Package 3 - FORWARD/AFT CROSSFEED VALVE ACTUATOR - LEFT (V28163/V28263) 1. Get access to each MOV actuator. Refer to 777 AMM 28-22-04 as an accepted procedure. 2. For each MOV actuator, read and record the part number of each MOV actuator as given in Figure 10. a. If the MOV actuator is not part number MA20A1001-1, the part is acceptable. No more work is necessary at this location. (1) Close Access to each MOV actuator. Refer to 777 AMM 28-22-04 as an accepted procedure. (2) Put the airplane in a serviceable condition or do another work package. b. If the MOV actuator is part number MA20A1001-1, the part is not acceptable. Do the following steps to install the MOV actuator with part number MA30A1001: (1) Remove and discard the MOV actuator, and remove and keep the bonding jumper. Refer to 777 AMM 28-22-04 as an accepted procedure. (2) Remove and keep the index plate as given in Figure 2. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 02, 2007 777-28A0034Revision 2: September 20, 2010 39 of 96 BOEING SERVICE BULLETIN 777-28A0034 ### Page 40 NOTE: Make an ink mark with a pen across the index plate, the adapter plate, and the airplane structure as a reference for installation alignment. (3) Rework the index plate as given in Figure 3. (4) Prepare the adapter plate surface as given in Figure 5. (5) Measure and record the electrical resistance of the bond from the adapter plate to the airplane structure as given in Figure 4. (a) If the resistance is less than 1.5 milliohms, the bond is acceptable. Do the following steps: 1) Temporarily put the index plate in position for installation as given in Figure 6. 2) Install the index plate. Refer to 777 AMM 28-22-03 as an accepted procedure. 3) Install the MOV actuator as given in Figure 7. Refer to 777 AMM 28-22-04 as an accepted procedure for the install of the MOV actuator body. 4) Do an operational test of MOV actuator. Refer to 777 AMM 28-22-04 as an accepted procedure. (b) If the resistance is 1.5 milliohms or greater, the bond is not acceptable. A fuel tank entry is necessary to make an acceptable bond. Do the following steps: 1) Get access to the Motor Operated Valve (MOV). Refer to 777 AMM 28-22-03 as an accepted procedure. 2) Remove the adapter plate and adapter shaft. Refer to 777 AMM 28-22-03 as an accepted procedure. 3) Clean the adapter plate and the airplane structure as given in Figure 8. 4) Install the adapter plate and the adapter shaft. Refer to 777 AMM 28-22-03 as an accepted procedure. 5) Prepare the adapter plate surface as given in Figure 5. 6) Measure and record the electrical resistance of the bond from the adapter plate to the airplane structure as given in Figure 4. a) If the resistance is less than 0.5 milliohms, the bond is acceptable. Do the following steps: BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 02, 2007 777-28A0034Revision 2: September 20, 2010 40 of 96 BOEING SERVICE BULLETIN 777-28A0034 ### Page 41 {1} Temporarily put the index plate in position for installation as given in Figure 6. {2} Install the index plate. Refer to 777 AMM 28-22-03 as an accepted procedure. {3} Install the MOV actuator as given in Figure 7. Refer to 777 AMM 28-22-04 as an accepted procedure for the install of the MOV actuator body. {4} Do an operational test of MOV actuator. Refer to 777 AMM 28-22-04 as an accepted procedure. b) If the resistance is 0.5 milliohms or greater, the bond is not acceptable. Do the following steps: {1} Return to step 2.b.(5)(b)2) and rework the bond until it is acceptable. 7) Close access to the Motor Operated Valve. Refer to 777 AMM 28-22-03 as an accepted procedure. 3. For each MOV actuator, close access to the MOV actuator. Refer to 777 AMM 28-22-04 as an accepted procedure. 4. Put the airplane in a serviceable condition or do another work package. Group 1-2: Work Package 4 - APU FUEL SHUTOFF VALVE ACTUATOR - LEFT (V28023) 1. Get access to the MOV actuator. Refer to 777 AMM 28-25-02 as an accepted procedure. 2. Read and record the part number of the MOV actuator as given in Figure 11. a. If the MOV actuator is not part number MA20A1001-1, the part is acceptable. No more work is necessary at this location. (1) Close Access to each MOV actuator. Refer to 777 AMM 28-25-02 as an accepted procedure. (2) Put the airplane in a serviceable condition or do another work package. b. If the MOV actuator is part number MA20A1001-1, the part is not acceptable. Do the following steps to install the MOV actuator with part number MA30A1001: BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 02, 2007 777-28A0034Revision 2: September 20, 2010 41 of 96 BOEING SERVICE BULLETIN 777-28A0034 ### Page 42 (1) Remove and discard the MOV actuator, and remove and keep the bonding jumper. Refer to 777 AMM 28-25-02 as an accepted procedure. (2) Install the MOV actuator as given in Figure 21. Refer to 777 AMM 28-25-02 as an accepted procedure for the install of the MOV actuator body. (3) Do an operational test of MOV actuator. Refer to 777 AMM 28-25-02 as an accepted procedure. 3. When you are done with the work, close access to the MOV actuator. Refer to 777 AMM 28-25-02 as an accepted procedure. 4. Put the airplane in a serviceable condition or do another work package. Group 1-2: Work Package 5 - APU FUEL ISOLATION VALVE ACTUATOR - LEFT (V28031) 1. Get access to the MOV actuator. Refer to 777 AMM 28-25-05 as an accepted procedure. 2. Read and record the part number of the MOV actuator as given in Figure 12. a. If the MOV actuator is not part number MA20A1001-1, the part is acceptable. No more work is necessary at this location. (1) Close Access to each MOV actuator. Refer to 777 AMM 28-25-05 as an accepted procedure. (2) Put the airplane in a serviceable condition or do another work package. b. If the MOV actuator is part number MA20A1001-1, the part is not acceptable. Do the following steps to install the MOV actuator with part number MA30A1001: (1) Remove and discard the MOV actuator, and remove and keep the bonding jumper. Refer to 777 AMM 28-25-05 as an accepted procedure. (2) Remove, Rework, and Install the bracket at APU Isolation MOV actuator to provided space for the new actuator. Do work as given in Figure 13. (3) Install the MOV actuator as given in Figure 21. Refer to 777 AMM 28-25-05 as an accepted procedure for the install of the MOV actuator body. (4) Do an operational test of MOV actuator. Refer to 777 AMM 28-25-05 as an accepted procedure. 3. Close access to the MOV actuator. Refer to 777 AMM 28-25-05 as an acceptable procedure. 4. Put the airplane in a serviceable condition or do another work package. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 02, 2007 777-28A0034Revision 2: September 20, 2010 42 of 96 BOEING SERVICE BULLETIN 777-28A0034 ### Page 43 Group 1-2: Work Package 6 - DEFUEL VALVE ACTUATOR - RIGHT (V28310) 1. Get access to the MOV actuator. Refer to 777 AMM 28-26-02 as an accepted procedure. 2. Read and record the part number of the MOV actuator as given in Figure 14. a. If the MOV actuator is not part number MA20A1001-1, the part is acceptable. No more work is necessary at this location. (1) Close Access to each MOV actuator. Refer to 777 AMM 28-26-02 as an accepted procedure. (2) Put the airplane in a serviceable condition or do another work package. b. If the MOV actuator is part number MA20A1001-1, the part is not acceptable. Do the following steps to install the MOV actuator with part number MA30A1001: (1) Remove and discard the MOV actuator, and remove and keep the bonding jumper. Refer to 777 AMM 28-26-02 as an accepted procedure. (2) Remove and keep the index plate as given in Figure 2. NOTE: Make an ink mark with a pen across the index plate, the adapter plate, and the airplane structure as a reference for installation alignment. (3) Rework the index plate as given in Figure 3. (4) Prepare the adapter plate surface as given in Figure 5. (5) Measure and record the electrical resistance of the bond from the adapter plate to the airplane structure as given in Figure 4. (a) If the resistance is less than 1.5 milliohms, the bond is acceptable. Do the following steps: 1) Temporarily put the index plate in position for installation as given in Figure 6. 2) Install the index plate. Refer to 777 AMM 28-26-01 as an accepted procedure. 3) Install the MOV actuator as given in Figure 7. Refer to 777 AMM 28-26-02 as an accepted procedure for the install of the MOV actuator body. 4) Do an operational test of MOV actuator. Refer to 777 AMM 28-26-02 as an accepted procedure. (b) If the resistance is 1.5 milliohms or greater, the bond is not acceptable. A fuel tank entry is necessary to make an acceptable bond. Do the following steps: BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 02, 2007 777-28A0034Revision 2: September 20, 2010 43 of 96 BOEING SERVICE BULLETIN 777-28A0034 ### Page 44 1) Get access to the Motor Operated Valve (MOV). Refer to 777 AMM 28-26-01 as an accepted procedure. 2) Remove the adapter plate and adapter shaft. Refer to 777 AMM 28-26-01 as an accepted procedure. 3) Clean the adapter plate and the airplane structure as given in Figure 8. 4) Install the adapter plate and the adapter shaft. Refer to 777 AMM 28-26-01 as an accepted procedure. 5) Prepare the adapter plate surface as given in Figure 5. 6) Measure and record the electrical resistance of the bond from the adapter plate to the airplane structure as given in Figure 4. a) If the resistance is less than 0.5 milliohms, the bond is acceptable. Do the following steps: {1} Temporarily put the index plate in position for installation as given in Figure 6. {2} Install the index plate. Refer to 777 AMM 28-26-01 as an accepted procedure. {3} Install the MOV actuator as given in Figure 7. Refer to 777 AMM 28-26-02 as an accepted procedure for the install of the MOV actuator body. {4} Do an operational test of MOV actuator. Refer to 777 AMM 28-26-02 as an accepted procedure.. b) If the resistance is 0.5 milliohms or greater, the bond is not acceptable. Do the following steps: {1} Return to step 2.b.(5)(b)2) and rework the bond until it is acceptable. 7) Close access to the Motor Operated Valve. Refer to 777 AMM 28-26-01 as an accepted procedure. 3. Close access to the MOV actuator. Refer to both 777 AMM 28-26-02 as an accepted procedure. 4. Put the airplane in a serviceable condition or do another work package. Group 1: Work Package 7 - FUEL JETTISON NOZZLE VALVE ACTUATOR - LEFT (V28166) 1. Get access to the MOV actuator. Refer to 777 AMM 28-31-03 as an accepted procedure. 2. Read and record the part number of the MOV actuator as given in Figure 15. a. If the MOV actuator is not part number MA20A1001-1, the part is acceptable. No more work is necessary at this location. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 02, 2007 777-28A0034Revision 2: September 20, 2010 44 of 96 BOEING SERVICE BULLETIN 777-28A0034 ### Page 45 (1) Close Access to each MOV actuator. Refer to 777 AMM 28-31-03 as an accepted procedure. (2) Put the airplane in a serviceable condition or do another work package. b. If the MOV actuator is part number MA20A1001-1, the part is not acceptable. Do the following steps to install the MOV actuator with part number MA30A1001: (1) Remove and discard the MOV actuator, and remove and keep the bonding jumper. Refer to 777 AMM 28-31-03 as an accepted procedure. (2) Install the MOV actuator as given in Figure 22. Refer to 777 AMM 28-31-03 as an accepted procedure as an accepted procedure for the install of the MOV actuator body. (3) Do an operational test of MOV actuator. Refer to 777 AMM 28-31-03 as an accepted procedure. 3. Close access to the MOV actuator. Refer to 777 AMM 28-31-03 as an accepted procedure. 4. Put the airplane in a serviceable condition or do another work package. Group 1: Work Package 8 - FUEL JETTISON NOZZLE VALVE ACTUATOR - RIGHT (V28266) 1. Get access to the MOV actuator. Refer to 777 AMM 28-31-03 as an accepted procedure. 2. Read and record the part number of the MOV actuator as given in Figure 16. a. If the MOV actuator is not part number MA20A1001-1, the part is acceptable. No more work is necessary at this location. (1) Close Access to each MOV actuator. Refer to 777 AMM 28-31-03 as an accepted procedure. (2) Put the airplane in a serviceable condition or do another work package. b. If the MOV actuator is part number MA20A1001-1, the part is not acceptable. Do the following steps to install the MOV actuator with part number MA30A1001: (1) Remove and discard the MOV actuator and remove and keep the bonding jumper. Refer to 777 AMM 28-31-03 as an accepted procedure. (2) Install the MOV actuator as given in Figure 22. Refer to 777 AMM 28-31-03 as an accepted procedure for the install of the MOV actuator body. (3) Do an operational test of MOV actuator. Refer to 777 AMM 28-31-03 as an accepted procedure. 3. Close access to the MOV actuator. Refer to 777 AMM 28-31-03 as an accepted procedure. 4. Put the airplane in a serviceable condition or do another work package. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 02, 2007 777-28A0034Revision 2: September 20, 2010 45 of 96 BOEING SERVICE BULLETIN 777-28A0034 ### Page 46 Group 2: Work Package 9 - FUEL JETTISON NOZZLE VALVE ACTUATOR - LEFT (V8166) 1. Get access to the MOV actuator. Refer to 777 AMM 28-31-03 as an accepted procedure. 2. Read and record the part number of the MOV actuator as given in Figure 17. a. If the MOV actuator is not part number MA20A1001-1, the part is acceptable. No more work is necessary at this location. (1) Close Access to each MOV actuator. Refer to 777 AMM 28-31-03 as an accepted procedure. (2) Put the airplane in a serviceable condition or do another work package. b. If the MOV actuator is part number MA20A1001-1, the part is not acceptable. Do the following steps to install the MOV actuator with part number MA30A1001: (1) Remove and discard the MOV actuator, and remove and keep the bonding jumper. Refer to 777 AMM 28-31-03 as an accepted procedure. (2) Remove and keep the index plate as given in Figure 2. NOTE: Make an ink mark with a pen across the index plate, the adapter plate, and the airplane structure as a reference for installation alignment. (3) Rework the index plate as given in Figure 3. (4) Prepare the adapter plate surface as given in Figure 5. (5) Measure and record the electrical resistance of the bond from the adapter plate to the airplane structure as given in Figure 4. (a) If the resistance is less than 1.5 milliohms, the bond is acceptable. Do the following steps: 1) Temporarily put the index plate in position for installation as given in Figure 6. 2) Install the index plate. Refer to 777 AMM 28-31-02 as an accepted procedure. 3) Install the MOV actuator as given in Figure 7. Refer to 777 AMM 28-31-03 as an accepted procedure for the install of the MOV actuator body. 4) Do an operational test of MOV actuator. Refer to 777 AMM 28-31-03 as an accepted procedure. (b) If the resistance is 1.5 milliohms or greater, the bond is not acceptable. A fuel tank entry is necessary to make an acceptable bond. Do the following steps: BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 02, 2007 777-28A0034Revision 2: September 20, 2010 46 of 96 BOEING SERVICE BULLETIN 777-28A0034 ### Page 47 1) Get access to the Motor Operated Valve (MOV). Refer to 777 AMM 28-31-02 as an accepted procedure. 2) Remove the adapter plate and adapter shaft. Refer to 777 AMM 28-31-02 as an accepted procedure. 3) Clean the adapter plate and the airplane structure as given in Figure 8. 4) Install the adapter plate and the adapter shaft. Refer to 777 AMM 28-31-02 as an accepted procedure. 5) Prepare the adapter plate surface as given in Figure 5. 6) Measure and record the electrical resistance of the bond from the adapter plate to the airplane structure as given in Figure 4. a) If the resistance is less than 0.5 milliohms, the bond is acceptable. Do the following steps: {1} Temporarily put the index plate in position for installation as given in Figure 6. {2} Install the index plate. Refer to 777 AMM 28-31-02 as an accepted procedure. {3} Install the MOV actuator as given in Figure 7. Refer to 777 AMM 28-31-03 as an accepted procedure for the install of the MOV actuator body. {4} Do an operational test of MOV actuator. Refer to 777 AMM 28-31-03 as an accepted procedure. b) If the resistance is 0.5 milliohms or greater, the bond is not acceptable. Do the following steps: {1} Return to step 2.b.(5)(b)2) and rework the bond until it is acceptable. 7) Close access to the Motor Operated Valve. Refer to 777 AMM 28-31-02 as an accepted procedure. 3. Close access to the MOV actuator. Refer to 777 AMM 28-31-03 as an accepted procedure. 4. Put the airplane in a serviceable condition or do another work package. Group 2: Work Package 10 - FUEL JETTISON NOZZLE VALVE ACTUATOR - RIGHT (V28266) 1. Get access to the MOV actuator. Refer to 777 AMM 28-31-03 as an accepted procedure. 2. Read and record the part number of the MOV actuator as given in Figure 18. a. If the MOV actuator is not part number MA20A1001-1, the part is acceptable. No more work is necessary at this location. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 02, 2007 777-28A0034Revision 2: September 20, 2010 47 of 96 BOEING SERVICE BULLETIN 777-28A0034 ### Page 48 (1) Close Access to each MOV actuator. Refer to 777 AMM 28-31-03 as an accepted procedure. (2) Put the airplane in a serviceable condition or do another work package. b. If the MOV actuator is part number MA20A1001-1, the part is not acceptable. Do the following steps to install the MOV actuator with part number MA30A1001: (1) Remove and discard the MOV actuator, and remove and keep the bonding jumper. Refer to 777 AMM 28-31-03 as an accepted procedure. (2) Remove and keep the index plate as given in Figure 2. NOTE: Make an ink mark with a pen across the index plate, the adapter plate, and the airplane structure as a reference for installation alignment. (3) Rework the index plate as given in Figure 3. (4) Prepare the adapter plate surface as given in Figure 5. (5) Measure and record the electrical resistance of the bond from the adapter plate to the airplane structure as given in Figure 4. (a) If the resistance is less than 1.5 milliohms, the bond is acceptable. Do the following steps: 1) Temporarily put the index plate in position for installation as given in Figure 6. 2) Install the index plate. Refer to 777 AMM 28-31-02 as an accepted procedure. 3) Install the MOV actuator as given in Figure 7. Refer to 777 AMM 28-31-03 as an accepted procedure for the install of the MOV actuator body. 4) Do an operational test of MOV actuator. Refer to 777 AMM 28-31-03 as an accepted procedure. (b) If the resistance is 1.5 milliohms or greater, the bond is not acceptable. A fuel tank entry is necessary to make an acceptable bond. Do the following steps: 1) Get access to the Motor Operated Valve (MOV). Refer to 777 AMM 28-31-02 as an accepted procedure. 2) Remove the adapter plate and adapter shaft. Refer to 777 AMM 28-31-02 as an accepted procedure. 3) Clean the adapter plate and the airplane structure as given in Figure 8. 4) Install the adapter plate and the adapter shaft. Refer to 777 AMM 28-31-02 as an accepted procedure. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 02, 2007 777-28A0034Revision 2: September 20, 2010 48 of 96 BOEING SERVICE BULLETIN 777-28A0034 ### Page 49 5) Prepare the adapter plate surface as given in Figure 5. 6) Measure and record the electrical resistance of the bond from the adapter plate to the airplane structure as given in Figure 4. a) If the resistance is less than 0.5 milliohms, the bond is acceptable. Do the following steps: {1} Temporarily put the index plate in position for installation as given in Figure 6. {2} Install the index plate. Refer to 777 AMM 28-31-02 as an accepted procedure. {3} Install the MOV actuator as given in Figure 7. Refer to 777 AMM 28-31-03 as an accepted procedure for the install of the MOV actuator body. {4} Do an operational test of MOV actuator. Refer to 777 AMM 28-31-03 as an accepted procedure. b) If the resistance is 0.5 milliohms or greater, the bond is not acceptable. Do the following steps: {1} Return to step 2.b.(5)(b)2) and rework the bond until it is acceptable. 7) Close access to the Motor Operated Valve. Refer to 777 AMM 28-31-02 as an accepted procedure. 3. Close access to the MOV actuator. Refer to 777 AMM 28-31-03 as an accepted procedure. 4. Put the airplane in a serviceable condition or do another work package. Group 1-2: Work Package 11 - FUEL JETTISON ISOLATION VALVE ACTUATOR - LEFT (V28165) 1. Get access to the MOV actuator. Refer to 777 AMM 28-31-05 as an accepted procedure. 2. Read and record the part number of the MOV actuator as given in Figure 19. a. If the MOV actuator is not part number MA20A1001-1, the part is acceptable. No more work is necessary at this location. (1) Close Access to each MOV actuator. Refer to 777 AMM 28-31-05 as an accepted procedure. (2) Put the airplane in a serviceable condition or do another work package. b. If the MOV actuator is part number MA20A1001-1, the part is not acceptable. Do the following steps to install the MOV actuator with part number MA30A1001: BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 02, 2007 777-28A0034Revision 2: September 20, 2010 49 of 96 BOEING SERVICE BULLETIN 777-28A0034 ### Page 50 (1) Remove and discard the MOV actuator, and remove and keep the bonding jumper. Refer to 777 AMM 28-31-05 as an accepted procedure. (2) Remove and keep the index plate as given in Figure 2. NOTE: Make an ink mark with a pen across the index plate, the adapter plate, and the airplane structure as a reference for installation alignment. (3) Rework the index plate as given in Figure 3. (4) Prepare the adapter plate surface as given in Figure 5. (5) Measure and record the electrical resistance of the bond from the adapter plate to the airplane structure as given in Figure 4. (a) If the resistance is less than 1.5 milliohms, the bond is acceptable. Do the following steps: 1) Temporarily put the index plate in position for installation as given in Figure 6. 2) Install the index plate. Refer to 777 AMM 28-31-04 as an accepted procedure. 3) Install the MOV actuator as given in Figure 7. Refer to 777 AMM 28-31-05 as an accepted procedure for the install of the MOV actuator body. 4) Do an operational test of MOV actuator. Refer to 777 AMM 28-31-05 as an accepted procedure. (b) If the resistance is 1.5 milliohms or greater, the bond is not acceptable. A fuel tank entry is necessary to make an acceptable bond. Do the following steps: 1) Get access to the Motor Operated Valve (MOV). Refer to 777 AMM 28-31-04 as an accepted procedure. 2) Remove the adapter plate and adapter shaft. Refer to 777 AMM 28-31-04 as an accepted procedure. 3) Clean the adapter plate and the airplane structure as given in Figure 8. 4) Install the adapter plate and the adapter shaft. Refer to 777 AMM 28-31-04 as an accepted procedure. 5) Prepare the adapter plate surface as given in Figure 5. 6) Measure and record the electrical resistance of the bond from the adapter plate to the airplane structure as given in Figure 4. a) If the resistance is less than 0.5 milliohms, the bond is acceptable. Do the following steps: BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 02, 2007 777-28A0034Revision 2: September 20, 2010 50 of 96 BOEING SERVICE BULLETIN 777-28A0034 ### Page 51 {1} Temporarily put the index plate in position for installation as given in Figure 6. {2} Install the index plate. Refer to 777 AMM 28-31-04 as an accepted procedure. {3} Install the MOV actuator as given in Figure 7. Refer to 777 AMM 28-31-05 as an accepted procedure for the install of the MOV actuator body. {4} Do an operational test of MOV actuator. Refer to 777 AMM 28-31-05 as an accepted procedure. b) If the resistance is 0.5 milliohms or greater, the bond is not acceptable. Do the following steps: {1} Return to step 2.b.(5)(b)2) and rework the bond until it is acceptable. 7) Close access to the Motor Operated Valve. Refer to 777 AMM 28-31-04 as an accepted procedure. 3. Close access to the MOV actuator. Refer to 777 AMM 28-31-05 as an accepted procedure. 4. Put the airplane in a serviceable condition or do another work package. Group 1-2: Work Package 12 - FUEL JETTISON ISOLATION VALVE ACTUATOR - RIGHT (V28265) 1. Get access to the MOV actuator. Refer to 777 AMM 28-31-05 as an accepted procedure. 2. Read and record the part number of the MOV actuator as given in Figure 20. a. If the MOV actuator is not part number MA20A1001-1, the part is acceptable. No more work is necessary at this location. (1) Close Access to each MOV actuator. Refer to 777 AMM 28-31-05 as an accepted procedure. (2) Put the airplane in a serviceable condition or do another work package. b. If the MOV actuator is part number MA20A1001-1, the part is not acceptable. Do the following steps to install the MOV actuator with part number MA30A1001: (1) Remove and discard the MOV actuator, and remove and keep the bonding jumper. Refer to 777 AMM 28-31-05 as an accepted procedure. (2) Remove and keep the index plate as given in Figure 2. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 02, 2007 777-28A0034Revision 2: September 20, 2010 51 of 96 BOEING SERVICE BULLETIN 777-28A0034 ### Page 52 NOTE: Make an ink mark with a pen across the index plate, the adapter plate, and the airplane structure as a reference for installation alignment. (3) Rework the index plate as given in Figure 3. (4) Prepare the adapter plate surface as given in Figure 5. (5) Measure and record the electrical resistance of the bond from the adapter plate to the airplane structure as given in Figure 4. (a) If the resistance is less than 1.5 milliohms, the bond is acceptable. Do the following steps: 1) Temporarily put the index plate in position for installation as given in Figure 6. 2) Install the index plate. Refer to 777 AMM 28-31-04 as an accepted procedure. 3) Install the MOV actuator as given in Figure 7. Refer to 777 AMM 28-31-05 as an accepted procedure for the install of the MOV actuator body. 4) Do an operational test of MOV actuator. Refer to 777 AMM 28-31-05 as an accepted procedure. (b) If the resistance is 1.5 milliohms or greater, the bond is not acceptable. A fuel tank entry is necessary to make an acceptable bond. Do the following steps: 1) Get access to the Motor Operated Valve (MOV). Refer to 777 AMM 28-31-04 as an accepted procedure. 2) Remove the adapter plate and adapter shaft. Refer to 777 AMM 28-31-04 as an accepted procedure. 3) Clean the adapter plate and the airplane structure as given in Figure 8. 4) Install the adapter plate and the adapter shaft. Refer to 777 AMM 28-31-04 as an accepted procedure. 5) Prepare the adapter plate surface as given in Figure 5. 6) Measure and record the electrical resistance of the bond from the adapter plate to the airplane structure as given in Figure 4. a) If the resistance is less than 0.5 milliohms, the bond is acceptable. Do the following steps: BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 02, 2007 777-28A0034Revision 2: September 20, 2010 52 of 96 BOEING SERVICE BULLETIN 777-28A0034 ### Page 53 {1} Temporarily put the index plate in position for installation as given in Figure 6. {2} Install the index plate. Refer to 777 AMM 28-31-04 as an accepted procedure. {3} Install the MOV actuator as given in Figure 7. Refer to 777 AMM 28-31-05 as an accepted procedure for the install of the MOV actuator body. {4} Do an operational test of MOV actuator. Refer to 777 AMM 28-31-05 as an accepted procedure. b) If the resistance is 0.5 milliohms or greater, the bond is not acceptable. Do the following steps: {1} Return to step 2.b.(5)(b)2) and rework the bond until it is acceptable. 7) Close access to the Motor Operated Valve. Refer to 777 AMM 28-31-04 as an accepted procedure. 3. Close access to the MOV actuator. Refer to 777 AMM 28-31-05 as an accepted procedure. 4. Put the airplane in a serviceable condition or do another work package. BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 02, 2007 777-28A0034Revision 2: September 20, 2010 53 of 96 BOEING SERVICE BULLETIN 777-28A0034 ### Page 54 (OCR) BOEING SERVICE BULLETIN 777-28A0034 SEE A FWD 09 INBD FWD 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 the figure. FIGURE 1: INSPECT AND RECORD THE ENGINE FUEL SPAR MOV ACTUATOR PART NUMBER (LEFT WING) (SHEET 1 OF 2) Original Issue: August 02, 2007 Revision 2 September 20, 2010 BOEING PROPRIETARY - 777-28A0034 Copyright © Unpublished Work - See page 1 for details. 54 of 96 ### Page 55 MORE DATAQTYIDENTIFICATIONNAMETASKSTEP Get access to the part number mark- ings on the MOV ac- tuator.1- Motor Operated Valve ActuatorGet1 Record the part number.1- Motor Operated Valve ActuatorRecord2 FIGURE 1: INSPECT AND RECORD THE ENGINE FUEL SPAR MOV ACTUATOR PART NUMBER (LEFT WING) (SHEET 2 OF 2) BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 02, 2007 777-28A0034Revision 2 September 20, 2010 55 of 96 BOEING SERVICE BULLETIN 777-28A0034 ### Page 56 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 the figure. FIGURE 2: REMOVE AND KEEP INDEX PLATE (SHEET 1 OF 2) BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 02, 2007 777-28A0034Revision 2 September 20, 2010 56 of 96 BOEING SERVICE BULLETIN 777-28A0034 ### Page 57 MORE DATAQTYIDENTIFICATIONNAMETASKSTEP Make an ink mark with a pen across both the index plate and the adapter plate as a reference for installation align- ment.--Reference MarkMake1 Remove from the in- dex plate mounting screws.--LockwireRemove2 3- Index Plate Mounting ScrewRemove / Keep3 Keep for rework.1-Index PlateRemove / Keep4 FIGURE 2: REMOVE AND KEEP INDEX PLATE (SHEET 2 OF 2) BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 02, 2007 777-28A0034Revision 2 September 20, 2010 57 of 96 BOEING SERVICE BULLETIN 777-28A0034 ### Page 58 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 the figure. MORE DATAQTYIDENTIFICATIONNAMETASKSTEP (a) Remove an- odized material from the index plate con- tact surface loca- tions using an abra- sive pad. Refer to SOPM 20-30-03 as an accepted proce- dure.--Anodized MaterialRemove1 Clean contact sur- faces. Refer to SOPM 20-30-03 as an accepted proce- dure.--Index PlateClean2 (a) Make sure not to remove the reference mark needed for alignment. FIGURE 3: REWORK INDEX PLATE (SHEET 1 OF 1) BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 02, 2007 777-28A0034Revision 2 September 20, 2010 58 of 96 BOEING SERVICE BULLETIN 777-28A0034 ### Page 59 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 the figure. MORE DATAQTYIDENTIFICATIONNAMETASKSTEP Measure electrical resistance from the adapter plate to the rear wing spar. Re- fer to SWPM 20-20- 00 as an accepted procedure. 1-Electrical BondMeasure1 Record the electrical resistance in mil- liohms. 1-Electrical BondRecord2 FIGURE 4: MEASURE AND RECORD ELECTRICAL RESISTANCE FROM THE ADAPTER PLATE TO THE AIRPLANE STRUCTURE (SHEET 1 OF 1) BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 02, 2007 777-28A0034Revision 2 September 20, 2010 59 of 96 BOEING SERVICE BULLETIN 777-28A0034 ### Page 60 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 the figure. MORE DATAQTYIDENTIFICATIONNAMETASKSTEP Remove surface material from adapter plate con- tact surface loca- tions using an abra- sive pad. Refer to SOPM 20-30-03 as an accepted proce- dure. --Adapter PlateClean1 Clean contact sur- face locations. Refer to SOPM 20-30-03 as an accepted pro- cedure. --Adapter PlateClean2 Use a minimum amount of sealant to reduce squeeze out. -BMS 5-95 (BMS 5-45 optional) Pressure and Environ- mental Sealant-Chro- mate Type Apply3 FIGURE 5: PREPARE ADAPTER PLATE SURFACE (SHEET 1 OF 1) BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 02, 2007 777-28A0034Revision 2 September 20, 2010 60 of 96 BOEING SERVICE BULLETIN 777-28A0034 The text continues at https://openairdocs.org/service-documents/boeing/777-28a0034/file/60b63d6e6c8b.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.