### 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.9E991 ECCN: 

## BOEING PROPRIETARY, CONFIDENTIAL, AND/OR TRADE SECRET Copyright © 2007 The Boeing Company Unpublished Work - All Rights Reserved Boeing claims copyright in each page of this document only to the extent that the page contains copyrightable subject matter.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BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 02, 2007 777-28A0034 Revision 2: September 20, 2010 1 of 96 2.0BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 02, 2007 777-28A0034 Revision 2: September 20, 2010 2 of 96 **BOEING SERVICE BULLETIN 777-28A0034**

BLANK PAGE**Table of Contents** Revision Transmittal Sheet............................................ 5 Summary...................................................... 7 1. PLANNING INFORMATION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11 A. Effectivity. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11 1. Airplanes. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11 2. Spares Affected. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13 B. Concurrent Requirements. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14 C. Reason. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14 D. Description. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14 E. Compliance. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15 F. Approval. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16 G. Manpower. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16 H. Weight and Balance Changes. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 28 I. Electrical Load Data. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 28 J. References. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 28 1. Existing Data:. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 28 2. Data supplied with this Service Bulletin:. . . . . . . . . . . . . . . . . . . . . . . . . . . 28 3. Installation Drawings Used in the Preparation of this Service Bulletin:. . . . . . . . . . . 29 K. Publications Affected. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29 L. Interchangeability and Intermixability of Parts. . . . . . . . . . . . . . . . . . . . . . . . . . . 29 2. MATERIAL INFORMATION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 31 A. Material - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 31 B. Industry Support Information. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 31 C. Parts Necessary For Each Airplane. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 31 1. Kits/Parts:. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 31 2. Parts and Materials Supplied by the Operator:. . . . . . . . . . . . . . . . . . . . . . . . 31 3. Parts Modified and Reidentified:. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 32 4. Parts Removed and Not Replaced:. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 32 D. Parts Necessary to Change Spares. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 32 E. Special Tooling - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 32 F. Special Tooling Necessary to do this Service Bulletin. . . . . . . . . . . . . . . . . . . . . . . 33 3. ACCOMPLISHMENT INSTRUCTIONS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 35 A. GENERAL INFORMATION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 35 B. WORK INSTRUCTIONS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 35 FIGURE 1: INSPECT AND RECORD THE ENGINE FUEL SPAR MOV ACTUATOR PART NUMBER (LEFT WING). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 54 FIGURE 2: REMOVE AND KEEP INDEX PLATE. . . . . . . . . . . . . . . . . . . . . . . . . . . . . 56 FIGURE 3: REWORK INDEX PLATE. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 58 FIGURE 4: MEASURE AND RECORD ELECTRICAL RESISTANCE FROM THE ADAPTER PLATE TO THE AIRPLANE STRUCTURE. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 59 FIGURE 5: PREPARE ADAPTER PLATE SURFACE. . . . . . . . . . . . . . . . . . . . . . . . . . . 60 FIGURE 6: PUT INDEX PLATE IN POSITION FOR INSTALLATION. . . . . . . . . . . . . . . . . . 61 FIGURE 7: INSTALL THE MOV ACTUATOR (DIRECTLY TO THE INDEX PLATE). . . . . . . . . . 62 FIGURE 8: CLEAN ADAPTER PLATE AND AIRPLANE SURFACE. . . . . . . . . . . . . . . . . . . 66

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 02, 2007 777-28A0034 Revision 2: September 20, 2010 3 of 96 **BOEING SERVICE BULLETIN 777-28A0034**FIGURE 9: INSPECT AND RECORD THE ENGINE FUEL SPAR MOV ACTUATOR PART NUMBER (RIGHT WING). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 67 FIGURE 10: INSPECT AND RECORD THE FORWARD/AFT CROSSFEED MOV ACTUATOR PART NUMBER (LEFT WING). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 69 FIGURE 11: INSPECT ANDRECORD THE APU FUEL SHUTOFF MOV ACTUATOR PART NUMBER (LEFT WING).. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 71 FIGURE 12: INSPECT AND RECORD THE APU ISOLATION MOV ACTUATOR PART NUMBER (LEFT WING).. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 73 FIGURE 13: REWORK BRACKET AT APU ISOLATION MOV ACTUATOR AREA ONLY. . . . . . . . 75 FIGURE 14: INSPECT AND RECORD THE DEFUEL MOV ACTUATOR PART NUMBER (RIGHT WING). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 79 FIGURE 15: INSPECT AND RECORD FUEL JETTISON NOZZLE MOV ACTUATOR PART NUMBER (INSIDE THE LEFT WING AREA). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 81 FIGURE 16: INSPECT AND RECORD FUEL JETTISON NOZZLE MOV ACTUATOR PART NUMBER (INSIDE THE RIGHT WING AREA). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 82 FIGURE 17: INSPECT AND RECORD FUEL JETTISON NOZZLE MOV ACTUATOR PART NUMBER (LEFT WING). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 83 FIGURE 18: INSPECT AND RECORD FUEL JETTISON NOZZLE MOV ACTUATOR PART NUMBER (RIGHT WING). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 84 FIGURE 19: INSPECT AND RECORD FUEL JETTISON ISOLATION MOV ACTUATOR PART NUMBER (LEFT WING). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 85 FIGURE 20: INSPECT AND RECORD FUEL JETTISON ISOLATION MOV ACTUATOR PART NUMBER (RIGHT WING). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 87 FIGURE 21: INSTALL THE MOV ACTUATOR. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 89 FIGURE 22: INSTALL THE FUEL JETTISON NOZZLE VALVE MOV ACTUATOR (INSIDE WING AREA) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 93

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 02, 2007 777-28A0034 Revision 2: September 20, 2010 4 of 96 **BOEING SERVICE BULLETIN 777-28A0034**

### Commercial **Airplanes** 

# 777 Service Bulletin **Revision Transmittal Sheet 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 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, 2007 Original Issue: May 20, 2010 Revision 1: September 20, 2010 Revision 2:

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 02, 2007 777-28A0034 Revision 2: September 20, 2010 5 of 96BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 02, 2007 777-28A0034 Revision 2: September 20, 2010 6 of 96 **BOEING SERVICE BULLETIN 777-28A0034**

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### Commercial **Airplanes** 

# 777 Service Bulletin **Summary 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 **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 777-28A0034 Revision 2: September 20, 2010 7 of 96— 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 Hours**  **Total Task Hours Airplanes**  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 777-28A0034 Revision 2: September 20, 2010 8 of 96 **BOEING SERVICE BULLETIN 777-28A0034**BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 02, 2007 777-28A0034 Revision 2: September 20, 2010 9 of 96 **BOEING SERVICE BULLETIN 777-28A0034**BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 02, 2007 777-28A0034 Revision 2: September 20, 2010 10 of 96 **BOEING SERVICE BULLETIN 777-28A0034**

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### 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.
**DESCRIPTION CONFIGURATION**  **GROUP** 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**Group Variable Number**  1 WA001 - WA017 1 WA076 - WA080 1 WA086 - WA093 1 WA101 - WA104 1 WA116 - WA119 1 WA131 - WA137 1 WA171 - WA175 1 WA196 - WA198

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 02, 2007 777-28A0034 Revision 2: September 20, 2010 11 of 96**Group Variable Number**  1 WA206 - WA212 1 WA221 - WA223 1 WA231 - WA232 1 WA241 - WA250 1 WA261 - WA266 1 WA281 - WA282 1 WA301 - WA304 1 WB001 - WB021 1 WB031 - WB046 1 WB051 - WB088 1 WB101 - WB106 1 WB121 - WB125 1 WB131 - WB141 1 WB151 - WB155 1 WB161 - WB177 1 WB181 - WB194 1 WB201 - WB215 1 WB231 - WB247 1 WB271 - WB273 1 WB276 - WB286 1 WB291 - WB302 1 WB306 - WB307 1 WB311 - WB337 1 WB341 - WB342 1 WB366 - WB368 1 WB371 - WB388 1 WB406 1 WB411 - WB413 1 WB416 - WB437 1 WB446 - WB453 1 WB476 1 WB481 - WB484 1 WB501 - WB511

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 02, 2007 777-28A0034 Revision 2: September 20, 2010 12 of 96 **BOEING SERVICE BULLETIN 777-28A0034 Group**  **Variable Number** 1 WB531 - WB537 1 WB551 - WB554 1 WB591 - WB597 1 WB601 - WB606 1 WB611 - WB622 1 WB631 - WB638 1 WB646 - WB649 1 WC051 - WC073 1 WC101 - WC104 1 WC111 - WC116 1 WC241 - WC243 1 WC281 - WC290 1 WC301 - WC308 1 WC361 - WC364 1 WC371 - WC374 1 WC381 - WC390 1 WC441 1 WC446 - WC448 1 WC456 - WC458 1 WC486 - WC489 2 WD001 - WD002 2 WD501 - WD504 2 WD521 - WD532 2 WD561 - WD563 2 WD581 - WD586 2 WD606 2 WD621 - WD625 2 WD651 - WD652 2 WD671 - 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 777-28A0034 Revision 2: September 20, 2010 13 of 96 **BOEING SERVICE BULLETIN 777-28A0034 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 777-28A0034 Revision 2: September 20, 2010 14 of 96 **BOEING SERVICE BULLETIN 777-28A0034**— 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 Zone**  **Model** 531, 533, 543, 551, 631, 633, 643, 651 777-200, 777-300 **Group 2:**
**Affected Maintenance Zones Zone**  **Model** 531, 533, 543, 551, 631, 633, 643, 651 777-200LR, 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 777-28A0034 Revision 2: September 20, 2010 15 of 96 **BOEING SERVICE BULLETIN 777-28A0034 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.** V28164 1 V28264 2 V28163/V28263 3 V28023 4 V28031 5 V28310 6 V28166 7 V28266 8 V28166 9 V28266 10 V28165 11 V28265 12

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 02, 2007 777-28A0034 Revision 2: September 20, 2010 16 of 96 **BOEING SERVICE BULLETIN 777-28A0034 Work Packages for All Groups**  **Elapsed Hours**  **Task Hours Number of**  **Persons Tasks**  **Work Package**

0.50 1.00 2 Prepare Work Package 1 0.10 0.10 1 Open MOV ac- tuator access 0.25 0.25 1 Figure 1 0.25 0.25 1 Remove MOV actuator 1.00 1.00 1 Figure 2 1.00 1.00 1 Figure 3 0.50 0.50 1 Figure 4 8.00 32.0 4 MOV access/ fuel tank entry (a) 1.00 2.00 2 Remove adapter plate and adapter shaft (a) 1.00 1.00 1 Figure 8 (a) 1.00 2.00 2 Install adapter plate and adapter shaft (a) 0.50 0.50 1 Figure 4 (a) 1.50 1.50 1 Figure 5 0.50 0.50 1 Figure 6 0.50 0.50 1 Install index plate 0.25 0.25 1 Figure 7 4.00 8.00 2 Close fuel tank access (a) 0.10 0.10 1 Close MOV ac- tuator access 21.95 52.45 Total for Work Package

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 02, 2007 777-28A0034 Revision 2: September 20, 2010 17 of 96 **BOEING SERVICE BULLETIN 777-28A0034 Work Packages for All Groups**  **Elapsed Hours**  **Task Hours Number of**  **Persons Tasks**  **Work Package**

0.50 1.00 2 Prepare Work Package 2 0.10 0.10 1 Open MOV ac- tuator access 0.25 0.25 1 Figure 9 0.25 0.25 1 Remove MOV actuator 1.00 1.00 1 Figure 2 1.00 1.00 1 Figure 3 0.50 0.50 1 Figure 4 8.00 32.0 4 MOV access/ fuel tank entry (a) 1.00 2.00 2 Remove adapter plate and adapter shaft (a) 1.00 1.00 1 Figure 8 (a) 1.00 2.00 2 Install adapter plate and adapter shaft (a) 0.50 0.50 1 Figure 4 (a) 1.50 1.50 1 Figure 5 0.50 0.50 1 Figure 6 0.50 0.50 1 Install index plate 0.25 0.25 1 Figure 7 4.00 8.00 2 Close fuel tank access (a) 0.10 0.10 1 Close MOV ac- tuator access 21.95 52.45 Total for Work Package

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 02, 2007 777-28A0034 Revision 2: September 20, 2010 18 of 96 **BOEING SERVICE BULLETIN 777-28A0034 Work Packages for All Groups**  **Elapsed Hours**  **Task Hours Number of**  **Persons Tasks**  **Work Package**

0.50 1.00 2 Prepare Work Package 3 0.10 0.10 1 Open MOV ac- tuator access 0.50 0.50 1 Figure 10 0.25 0.25 1 Remove MOV actuator 1.00 1.00 1 Figure 2 1.00 1.00 1 Figure 3 0.50 0.50 1 Figure 4 8.00 32.0 4 MOV access/ fuel tank entry (a) 1.00 2.00 2 Remove adapter plate and adapter shaft (a) 1.00 1.00 1 Figure 8 (a) 1.00 2.00 2 Install adapter plate and adapter shaft (a) 0.50 0.50 1 Figure 4 (a) 1.50 1.50 1 Figure 5 0.50 0.50 1 Figure 6 0.50 0.50 1 Install index plate 0.25 0.25 1 Figure 7 4.00 8.00 2 Close fuel tank access (a) 0.10 0.10 1 Close MOV ac- tuator access 22.20 52.70 Total for Work Package

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 02, 2007 777-28A0034 Revision 2: September 20, 2010 19 of 96 **BOEING SERVICE BULLETIN 777-28A0034 Work Packages for All Groups**  **Elapsed Hours**  **Task Hours Number of**  **Persons Tasks**  **Work Package**

0.50 1.00 2 Prepare Work Package 4 0.10 0.10 1 Open MOV ac- tuator access 0.50 0.50 1 Figure 11 0.25 0.25 1 Remove MOV actuator 0.25 0.25 1 Figure 21 0.50 0.50 1 Close MOV ac- tuator access 2.1 2.6 Total for Work Package 0.50 1.00 2 Prepare Work Package 5 0.10 0.10 1 Open MOV ac- tuator access 0.50 0.50 1 Figure 12 0.25 0.25 1 Remove MOV actuator 2.00 2.00 1 Figure 13 0.25 0.25 1 Figure 21 0.50 0.50 1 Close MOV ac- tuator access 4.1 4.6 Total for Work Package

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 02, 2007 777-28A0034 Revision 2: September 20, 2010 20 of 96 **BOEING SERVICE BULLETIN 777-28A0034 Work Packages for All Groups**  **Elapsed Hours**  **Task Hours Number of**  **Persons Tasks**  **Work Package**

0.50 1.00 2 Prepare Work Package 6 0.10 0.10 1 Open MOV ac- tuator access 0.25 0.25 1 Figure 14 0.25 0.25 1 Remove MOV actuator 1.00 1.00 1 Figure 2 1.00 1.00 1 Figure 3 0.50 0.50 1 Figure 4 8.00 32.0 4 MOV access/ fuel tank entry (a) 1.00 2.00 2 Remove adapter plate and adapter shaft (a) 1.00 1.00 1 Figure 8 (a) 1.00 2.00 2 Install adapter plate and adapter shaft (a) 0.50 0.50 1 Figure 4 (a) 1.50 1.50 1 Figure 5 0.50 0.50 1 Figure 6 0.50 0.50 1 Install index plate 0.25 0.25 1 Figure 7 4.00 8.00 2 Close fuel tank access (a) 0.10 0.10 1 Close MOV ac- tuator access 21.95 52.45 Total for Work Package

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 02, 2007 777-28A0034 Revision 2: September 20, 2010 21 of 96 **BOEING SERVICE BULLETIN 777-28A0034 Work Packages for All Groups**  **Elapsed Hours**  **Task Hours Number of**  **Persons Tasks**  **Work Package**

0.50 1.00 2 Prepare Work Package 7 0.10 0.10 1 Open MOV ac- tuator access 0.50 0.50 1 Figure 15 0.25 0.25 1 Remove MOV actuator 0.25 0.25 1 Figure 22 0.50 0.50 1 Close MOV ac- tuator access 2.1 2.6 Total for Work Package 0.50 1.00 2 Prepare Work Package 8 0.10 0.10 1 Open MOV ac- tuator access 0.50 0.50 1 Figure 16 0.25 0.25 1 Remove MOV actuator 0.25 0.25 1 Figure 22 0.50 0.50 1 Close MOV ac- tuator access 2.1 2.6 Total for Work Package

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 02, 2007 777-28A0034 Revision 2: September 20, 2010 22 of 96 **BOEING SERVICE BULLETIN 777-28A0034 Work Packages for All Groups**  **Elapsed Hours**  **Task Hours Number of**  **Persons Tasks**  **Work Package**

0.50 1.00 2 Prepare Work Package 9 0.10 0.10 1 Open MOV ac- tuator access 0.25 0.25 1 Figure 17 0.25 0.25 1 Remove MOV actuator 1.00 1.00 1 Figure 2 1.00 1.00 1 Figure 3 0.50 0.50 1 Figure 4 8.00 32.0 4 MOV access/ fuel tank entry (a) 1.00 2.00 2 Remove adapter plate and adapter shaft (a) 1.00 1.00 1 Figure 8 (a) 1.00 2.00 2 Install adapter plate and adapter shaft (a) 0.50 0.50 1 Figure 4 (a) 1.50 1.50 1 Figure 5 0.50 0.50 1 Figure 6 0.50 0.50 1 Install index plate 0.25 0.25 1 Figure 7 4.00 8.00 2 Close fuel tank access (a) 0.10 0.10 1 Close MOV ac- tuator access 21.95 52.45 Total for Work Package

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 02, 2007 777-28A0034 Revision 2: September 20, 2010 23 of 96 **BOEING SERVICE BULLETIN 777-28A0034 Work Packages for All Groups**  **Elapsed Hours**  **Task Hours Number of**  **Persons Tasks**  **Work Package**

0.50 1.00 2 Prepare Work Package 10 0.10 0.10 1 Open MOV ac- tuator access 0.25 0.25 1 Figure 18 0.25 0.25 1 Remove MOV actuator 1.00 1.00 1 Figure 2 1.00 1.00 1 Figure 3 0.50 0.50 1 Figure 4 8.00 32.0 4 MOV access/ fuel tank entry (a) 1.00 2.00 2 Remove adapter plate and adapter shaft (a) 1.00 1.00 1 Figure 8 (a) 1.00 2.00 2 Install adapter plate and adapter shaft (a) 0.50 0.50 1 Figure 4 (a) 1.50 1.50 1 Figure 5 0.50 0.50 1 Figure 6 0.50 0.50 1 Install index plate 0.25 0.25 1 Figure 7 4.00 8.00 2 Close fuel tank access (a) 0.10 0.10 1 Close MOV ac- tuator access 21.95 52.45 Total for Work Package

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 02, 2007 777-28A0034 Revision 2: September 20, 2010 24 of 96 **BOEING SERVICE BULLETIN 777-28A0034 Work Packages for All Groups**  **Elapsed Hours**  **Task Hours Number of**  **Persons Tasks**  **Work Package**

0.50 1.00 2 Prepare Work Package 11 0.10 0.10 1 Open MOV ac- tuator access 0.25 0.25 1 Figure 19 0.25 0.25 1 Remove MOV actuator 1.00 1.00 1 Figure 2 1.00 1.00 1 Figure 3 0.50 0.50 1 Figure 4 8.00 32.0 4 MOV access/ fuel tank entry (a) 1.00 2.00 2 Remove adapter plate and adapter shaft (a) 1.00 1.00 1 Figure 8 (a) 1.00 2.00 2 Install adapter plate and adapter shaft (a) 0.50 0.50 1 Figure 4 (a) 1.50 1.50 1 Figure 5 0.50 0.50 1 Figure 6 0.50 0.50 1 Install index plate 0.25 0.25 1 Figure 7 4.00 8.00 2 Close fuel tank access (a) 0.10 0.10 1 Close MOV ac- tuator access 21.95 52.45 Total for Work Package

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 02, 2007 777-28A0034 Revision 2: September 20, 2010 25 of 96 **BOEING SERVICE BULLETIN 777-28A0034 Work Packages for All Groups**  **Elapsed Hours**  **Task Hours Number of**  **Persons Tasks**  **Work Package**

0.50 1.00 2 Prepare Work Package 12 0.10 0.10 1 Open MOV ac- tuator access 0.25 0.25 1 Figure 20 0.25 0.25 1 Remove MOV actuator 1.00 1.00 1 Figure 2 1.00 1.00 1 Figure 3 0.50 0.50 1 Figure 4 8.00 32.0 4 MOV access/ fuel tank entry (a) 1.00 2.00 2 Remove adapter plate and adapter shaft (a) 1.00 1.00 1 Figure 8 (a) 1.00 2.00 2 Install adapter plate and adapter shaft (a) 0.50 0.50 1 Figure 4 (a) 1.50 1.50 1 Figure 5 0.50 0.50 1 Figure 6 0.50 0.50 1 Install index plate 0.25 0.25 1 Figure 7 4.00 8.00 2 Close fuel tank access (a) 0.10 0.10 1 Close MOV ac- tuator access 21.95 52.45 Total 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 777-28A0034 Revision 2: September 20, 2010 26 of 96 **BOEING SERVICE BULLETIN 777-28A0034 Group 1:**  **Only the Work Packages for this Group Total Elapsed Hours (a)**  **Total Task-Hours (a) Sum of Work Packages**  21.95 52.45 Work Package 1 21.95 52.45 Work Package 2 22.20 52.70 Work Package 3 2.10 2.60 Work Package 4 4.10 4.60 Work Package 5 21.95 52.45 Work Package 6 2.10 2.60 Work Package 7 2.10 2.60 Work Package 8 21.95 52.45 Work Package 11 21.95 52.45 Work Package 12 142.35 327.35 TOTAL 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** 21.95 52.45 Work Package 1 21.95 52.45 Work Package 2 22.20 52.70 Work Package 3 2.10 2.60 Work Package 4 4.10 4.60 Work Package 5 21.95 52.45 Work Package 6 21.95 52.45 Work Package 9 21.95 52.45 Work Package 10 21.95 52.45 Work Package 11 21.95 52.45 Work Package 12 182.05 427.05 TOTAL 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 777-28A0034 Revision 2: September 20, 2010 27 of 96 **BOEING SERVICE BULLETIN 777-28A0034 H. Weight and Balance Changes**  **Change in Moment (Pound-Inches)**  **Change in Weight (Pounds)**  **Airplane**

+5448.9 +4.1 777-200 +6199.2 +4.1 777-300 **Change in Moment (Pound-Inch es)**  **Change in Weight (Pounds) Work Package** 

+483.2 +0.4 Work Package 1 +483.2 +0.4 Work Package 2 +466.6 +0.4 Work Package 3 +474.0 +0.4 Work Package 4 +474.0 +0.4 Work Package 5 +465.1 +0.4 Work Package 6 +582.4 +0.4 Work Package 7 +582.4 +0.4 Work Package 8 +582.4 +0.4 Work Package 9 +582.4 +0.4 Work Package 10 +465.3 +0.4 Work Package 11 +465.3 +0.4 Work 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 777-28A0034 Revision 2: September 20, 2010 28 of 96 **BOEING SERVICE BULLETIN 777-28A0034**3. Installation Drawings Used in the Preparation of this Service Bulletin:
**Title Drawing Number**  Equipment Inst - Engine Fuel Feed System 343W3001 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 - Wing 112W1003

**K. Publications Affected Chapter-Section** 

**Publication** 28-22, 28-25, 28-26, 28-31 777 Maintenance Manual 28-22, 28-25, 28-26, 28-31 777 Illustrated Parts Catalog 9 777 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 777-28A0034 Revision 2: September 20, 2010 29 of 96 **BOEING SERVICE BULLETIN 777-28A0034**BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 02, 2007 777-28A0034 Revision 2: September 20, 2010 30 of 96 **BOEING SERVICE BULLETIN 777-28A0034**

BLANK PAGE**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: Notes**  **Name QTY**  **Part Number / Specification**  Replaces MA20A1001-1 (S343T003-39) Motor Operated Valve Actuator 11 MA30A1001 (S343T003-66) (a) (b) (c) (e) pressure and environmental sealant- chromate type, class B 66 oz BMS 5-95 (d) bonding jumper, 5 inch 6 BACJ40A20-5 (d) bonding jumper, 6 inch 3 BACJ40A20-6 (d) bonding jumper, 7 inch 1 BACJ40A20-7 (d) bonding jumper, 9 inch 1 BACJ40A20-9 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 777-28A0034 Revision 2: September 20, 2010 31 of 96 **BOEING SERVICE BULLETIN 777-28A0034 Group 2:**  **Notes Name**  **QTY Part Number /**  **Specification** Replaces MA20A1001-1 (S343T003-39) Motor Operated Valve Actuator 11 MA30A1001 (S343T003-66) (a) (b) (c) (e) Pressure and Environmental Sealant-Chromate Type 66 oz BMS 5-95 (d) bonding jumper, 5 inch 6 BACJ40A20-5 (d) bonding jumper, 6 inch 1 BACJ40A20-6 (d) bonding jumper, 7 inch 3 BACJ40A20-7 (d) bonding jumper, 9 inch 1 BACJ40A20-9 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 777-28A0034 Revision 2: September 20, 2010 32 of 96 **BOEING SERVICE BULLETIN 777-28A0034 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 777-28A0034 Revision 2: September 20, 2010 33 of 96 **BOEING SERVICE BULLETIN 777-28A0034**BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 02, 2007 777-28A0034 Revision 2: September 20, 2010 34 of 96 **BOEING SERVICE BULLETIN 777-28A0034**

BLANK PAGE**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 777-28A0034 Revision 2: September 20, 2010 35 of 96 **BOEING SERVICE BULLETIN 777-28A0034**(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 777-28A0034 Revision 2: September 20, 2010 36 of 96 **BOEING SERVICE BULLETIN 777-28A0034**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 777-28A0034 Revision 2: September 20, 2010 37 of 96 **BOEING SERVICE BULLETIN 777-28A0034**(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 777-28A0034 Revision 2: September 20, 2010 38 of 96 **BOEING SERVICE BULLETIN 777-28A0034**{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 777-28A0034 Revision 2: September 20, 2010 39 of 96 **BOEING SERVICE BULLETIN 777-28A0034 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 777-28A0034 Revision 2: September 20, 2010 40 of 96 **BOEING SERVICE BULLETIN 777-28A0034**{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 777-28A0034 Revision 2: September 20, 2010 41 of 96 **BOEING SERVICE BULLETIN 777-28A0034**(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 777-28A0034 Revision 2: September 20, 2010 42 of 96 **BOEING SERVICE BULLETIN 777-28A0034 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 777-28A0034 Revision 2: September 20, 2010 43 of 96 **BOEING SERVICE BULLETIN 777-28A0034**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 777-28A0034 Revision 2: September 20, 2010 44 of 96 **BOEING SERVICE BULLETIN 777-28A0034**(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 777-28A0034 Revision 2: September 20, 2010 45 of 96 **BOEING SERVICE BULLETIN 777-28A0034 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 777-28A0034 Revision 2: September 20, 2010 46 of 96 **BOEING SERVICE BULLETIN 777-28A0034**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 777-28A0034 Revision 2: September 20, 2010 47 of 96 **BOEING SERVICE BULLETIN 777-28A0034**(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 777-28A0034 Revision 2: September 20, 2010 48 of 96 **BOEING SERVICE BULLETIN 777-28A0034**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 777-28A0034 Revision 2: September 20, 2010 49 of 96 **BOEING SERVICE BULLETIN 777-28A0034**(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 777-28A0034 Revision 2: September 20, 2010 50 of 96 **BOEING SERVICE BULLETIN 777-28A0034**{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 777-28A0034 Revision 2: September 20, 2010 51 of 96 **BOEING SERVICE BULLETIN 777-28A0034 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 777-28A0034 Revision 2: September 20, 2010 52 of 96 **BOEING SERVICE BULLETIN 777-28A0034**{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 777-28A0034 Revision 2: September 20, 2010 53 of 96 **BOEING SERVICE BULLETIN 777-28A0034**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)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 02, 2007 777-28A0034 Revision 2 September 20, 2010 54 of 96 **BOEING SERVICE BULLETIN 777-28A0034 MORE DATA**  **QTY IDENTIFICATION**  **NAME TASK**  **STEP** Get access to thepart number markings on the MOV ac- tuator. 1

- Motor Operated Valve Actuator Get 1 Record the part number. 1

- Motor Operated Valve Actuator Record 2

**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 777-28A0034 Revision 2 September 20, 2010 55 of 96 **BOEING SERVICE BULLETIN 777-28A0034**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 777-28A0034 Revision 2 September 20, 2010 56 of 96 **BOEING SERVICE BULLETIN 777-28A0034 MORE DATA**  **QTY IDENTIFICATION**  **NAME TASK**  **STEP** Make an ink mark with a pen across both the index plate and the adapter plate as a referencefor installation alignment.
- - Reference Mark Make 1 Remove from the index plate mounting screws. - - Lockwire Remove 2

3

- Index Plate Mounting Screw Remove / Keep 3 Keep for rework. 1

- Index Plate Remove / Keep 4

**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 777-28A0034 Revision 2 September 20, 2010 57 of 96 **BOEING SERVICE BULLETIN 777-28A0034**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 DATA QTY**  **IDENTIFICATION NAME**  **TASK STEP**  (a) Remove anodized material fromthe index plate contact surface locations using an abrasive pad. Refer to SOPM 20-30-03 asan accepted procedure.

- - Anodized Material Remove 1 Clean contact surfaces. Refer to SOPM 20-30-03 asan accepted procedure.

- - Index Plate Clean 2 (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 777-28A0034 Revision 2 September 20, 2010 58 of 96 **BOEING SERVICE BULLETIN 777-28A0034**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 DATA QTY**  **IDENTIFICATION NAME**  **TASK STEP**  Measure electrical resistance from the adapter plate to therear wing spar. Refer to SWPM 20-20- 00 as an accepted procedure. 1

- Electrical Bond Measure 1

Record the electricalresistance in milliohms. 1

- Electrical Bond Record 2

**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 777-28A0034 Revision 2 September 20, 2010 59 of 96 **BOEING SERVICE BULLETIN 777-28A0034**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 DATA QTY**  **IDENTIFICATION NAME**  **TASK STEP**  Remove surface material fromadapter plate contact surface locations using an abrasive pad. Refer to SOPM 20-30-03 asan accepted procedure. - - Adapter Plate Clean 1

Clean contact surface locations. Refer to SOPM 20-30-03as an accepted procedure. - - Adapter Plate Clean 2

Use a minimum amount of sealant to reduce squeeze out. - BMS 5-95 (BMS 5-45 optional)Pressure and Environmental Sealant-Chromate Type Apply 3

**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 777-28A0034 Revision 2 September 20, 2010 60 of 96 **BOEING SERVICE BULLETIN 777-28A0034**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 DATA QTY**  **IDENTIFICATION NAME**  **TASK STEP**  Align referencemarkings made during index plate removal. 1

- Index Plate Put / Hold 1

Insert the kept bottom screw only. 1

- Index Plate Mounting Screw Insert 2 Tighten only to hold index plate in place for install. 1

- Index Plate Mounting Screw Tighten 3

**FIGURE 6: PUT INDEX PLATE IN POSITION FOR INSTALLATION (SHEET 1 OF 1)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 02, 2007 777-28A0034 Revision 2 September 20, 2010 61 of 96 **BOEING SERVICE BULLETIN 777-28A0034**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 DATA QTY**  **IDENTIFICATION NAME**  **TASK STEP**  Apply a Faying bond to the index plate. (a) - BMS 5-95 (BMS 5-45 optional)Pressure and Environmental Sealant-Chromate Type Apply 1

Do not connect the bonding jumper to the MOV actuator. 1 MA30A1001 Motor Operated Valve Actuator Install (New) 2

**FIGURE 7: INSTALL THE MOV ACTUATOR (DIRECTLY TO THE INDEX PLATE) (SHEET 1 OF 4)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 02, 2007 777-28A0034 Revision 2 September 20, 2010 62 of 96 **BOEING SERVICE BULLETIN 777-28A0034 MORE DATA**  **QTY IDENTIFICATION**  **NAME TASK**  **STEP** Measure the electrical resistance of the Faying bond from the foot of the MOVactuator to the airplane structure. (a) (b) - - Electrical Bond Measure 3

Measure the length of the bondingjumper from the attach point on the MOV actuator to the attach point on the airplane structure. Use the shortest bonding jumper that allows no tension. You can select a length from 5-to-9 inches. (a) 1 BACJ40A20-5 Bonding Jumper, 5 IN (optional) Measure 4

If you determined that the bonding jumper is too short, remove the bonding jumper and do the following sub-tasks. 1 BACJ40A20-5 Bonding Jumper, 5 IN (optional) Remove

You can select a length from 5-to-9 inches.(a) 1 BACJ40A20-5 Bonding Jumper, 5 IN (optional) Get

1 BACJ40A20-6 Bonding Jumper, 6 IN (optional) 1 BACJ40A20-7 Bonding Jumper, 7 IN (optional) 1 BACJ40A20-9 Bonding Jumper, 9 IN (optional)

**FIGURE 7: INSTALL THE MOV ACTUATOR (DIRECTLY TO THE INDEX PLATE) (SHEET 2 OF 4)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 02, 2007 777-28A0034 Revision 2 September 20, 2010 63 of 96 **BOEING SERVICE BULLETIN 777-28A0034 MORE DATA**  **QTY IDENTIFICATION**  **NAME TASK**  **STEP** Clean the surface of the bonding jumper lug and fasteners, and the airplane structure. (a) 1

- Bonding Jumper Clean 5

Attach the bondingjumpers to the airplane structure. Use the shortest bonding jumper that allows no tension. You can select a length from 5-to-9 inches. (a) 1

- Bonding Jumper Attach

Apply a Faying bondat the airplane structure for the bonding jumper of the correct length. (a) - BMS 5-95 (BMS 5-45 optional)Pressure and Environmental Sealant-Chromate Type Apply

Torque fasteners. (a) 1

- Bonding Jumper Torque
Clean the surface of the bonding jumper lug and fasteners,and the MOV actuator. (a) 1

- Bonding Jumper Clean 6

Measure the electrical resistance of the Faying bond from the lug on the end of the bonding jumperto a point on the airplane structure. (a) (c) - - Electrical Bond Measure

**FIGURE 7: INSTALL THE MOV ACTUATOR (DIRECTLY TO THE INDEX PLATE) (SHEET 3 OF 4)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 02, 2007 777-28A0034 Revision 2 September 20, 2010 64 of 96 **BOEING SERVICE BULLETIN 777-28A0034 MORE DATA**  **QTY IDENTIFICATION**  **NAME TASK**  **STEP** Attach the bonding jumper to the MOV actuator. - - Bonding Jumper Attach 7

Apply a Faying bond at the MOV actuator for the bonding jumper. (a) 1 BMS 5-95 (BMS 5-45 optional)Pressure and Environmental Sealant-Chromate Type Apply

Torque fasteners. (a) 1

- Bonding Jumper Torque

Measure the electrical resistance of the Faying bond from the lug on the end of the bonding jumper that is installed at the MOV actuator to the foot of the MOV actuator. (a) (d) (e) - - Electrical Bond Measure

Apply cap seal to thebonding jumper fasteners.(a) (f) - BMS 5-95 (BMS 5-45 optional)Pressure and Environmental Sealant-Chromate Type Apply 8

(a) Refer to SWPM 20-20-00 as an accepted procedure. (b) If the measured electrical resistance of the Faying bond from the foot of the MOV actuator to the airplane structure is less than 2.5 milliohms, the Faying bond is acceptable. If the measured electrical resistance of the Faying bond is not acceptable, rework the Faying Bond as necessary. (c) If the measured resistance of the Faying bond from the lug on the end of the bonding jumper to a pointon the airplane structure is less than 1.5 milliohms, the Faying bond is acceptable. If the measured electrical resistance of the Faying bond is not acceptable, rework the Faying Bond as necessary. (d) If the measured resistance of the Faying bond from the lug on the end of the bonding jumper that is installedat the MOV actuator to the foot of the MOV actuator is less than 1.5 milliohms, the Faying bond is acceptable. If the measured electrical resistance of the Faying bond is not acceptable, rework the Faying bond as necessary. (e) The purpose of this step is to measure the electrical continuity across the manufactured joint of the MOV actuator body. (f) 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.

**FIGURE 7: INSTALL THE MOV ACTUATOR (DIRECTLY TO THE INDEX PLATE) (SHEET 4 OF 4)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 02, 2007 777-28A0034 Revision 2 September 20, 2010 65 of 96 **BOEING SERVICE BULLETIN 777-28A0034**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 DATA QTY**  **IDENTIFICATION NAME**  **TASK STEP**  Clean contact surfaces. Refer to SOPM 20-30-03 asan accepted procedure. 1

- Adapter Plate Clean 1 Clean contact surfaces. Refer to SOPM 20-30-03 asan accepted procedure.

- - Airplane Surface Clean 2

**FIGURE 8: CLEAN ADAPTER PLATE AND AIRPLANE SURFACE (SHEET 1 OF 1)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 02, 2007 777-28A0034 Revision 2 September 20, 2010 66 of 96 **BOEING SERVICE BULLETIN 777-28A0034**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 9: INSPECT AND RECORD THE ENGINE FUEL SPAR MOV ACTUATOR PART NUMBER (RIGHT WING)**  **(SHEET 1 OF 2)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 02, 2007 777-28A0034 Revision 2 September 20, 2010 67 of 96 **BOEING SERVICE BULLETIN 777-28A0034 MORE DATA**  **QTY IDENTIFICATION**  **NAME TASK**  **STEP** Get access to thepart number markings on the MOV ac- tuator. 1

- Motor Operated Valve Actuator Get 1 Record the part number. 1

- Motor Operated Valve Actuator Record 2

**FIGURE 9: INSPECT AND RECORD THE ENGINE FUEL SPAR MOV ACTUATOR PART NUMBER (RIGHT WING)**  **(SHEET 2 OF 2)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 02, 2007 777-28A0034 Revision 2 September 20, 2010 68 of 96 **BOEING SERVICE BULLETIN 777-28A0034 FIGURE 10: INSPECT AND RECORD THE FORWARD/AFT CROSSFEED MOV ACTUATOR PART NUMBER**  **(LEFT WING) (SHEET 1 OF 2)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 02, 2007 777-28A0034 Revision 2 September 20, 2010 69 of 96 **BOEING SERVICE BULLETIN 777-28A0034 MORE DATA**  **QTY IDENTIFICATION**  **NAME TASK**  **STEP** Get access to thepart number markings on the MOV actuator. 1

- Motor Operated Valve Actuator Get 1

Record the part number of forwardcrossfeed MOV Actuator. 1

- Motor Operated Valve Actuator Record 2

Get access to thepart number markings on the MOV actuator. 1

- Motor Operated Valve Actuator Get 3

Record the part number of forwardcrossfeed MOV Actuator. 1

- Motor Operated Valve Actuator Record 4

**FIGURE 10: INSPECT AND RECORD THE FORWARD/AFT CROSSFEED 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 777-28A0034 Revision 2 September 20, 2010 70 of 96 **BOEING SERVICE BULLETIN 777-28A0034**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 11: INSPECT AND RECORD THE APU FUEL SHUTOFF MOV ACTUATOR PART NUMBER (LEFT WING).**  **(SHEET 1 OF 2)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 02, 2007 777-28A0034 Revision 2 September 20, 2010 71 of 96 **BOEING SERVICE BULLETIN 777-28A0034 MORE DATA**  **QTY IDENTIFICATION**  **NAME TASK**  **STEP** Get access to thepart number markings on the MOV ac- tuator. 1

- Motor Operated Valve Actuator Get 1 Record the part number. 1

- Motor Operated Valve Actuator Record 2

**FIGURE 11: INSPECT AND RECORD THE APU FUEL SHUTOFF 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 777-28A0034 Revision 2 September 20, 2010 72 of 96 **BOEING SERVICE BULLETIN 777-28A0034**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 12: INSPECT AND RECORD THE APU ISOLATION MOV ACTUATOR PART NUMBER (LEFT WING).**  **(SHEET 1 OF 2)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 02, 2007 777-28A0034 Revision 2 September 20, 2010 73 of 96 **BOEING SERVICE BULLETIN 777-28A0034 MORE DATA**  **QTY IDENTIFICATION**  **NAME TASK**  **STEP** Get access to thepart number markings on the MOV ac- tuator. 1

- Motor Operated Valve Actuator Get 1 Record the part number. 1

- Motor Operated Valve Actuator Record 2

**FIGURE 12: INSPECT AND RECORD THE APU ISOLATION 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 777-28A0034 Revision 2 September 20, 2010 74 of 96 **BOEING SERVICE BULLETIN 777-28A0034 FIGURE 13: REWORK BRACKET AT APU ISOLATION MOV ACTUATOR AREA ONLY**  **(SHEET 1 OF 4)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 02, 2007 777-28A0034 Revision 2 September 20, 2010 75 of 96 **BOEING SERVICE BULLETIN 777-28A0034**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 DATA QTY**  **IDENTIFICATION NAME**  **TASK STEP**  Locate the bracket on the left wing rear spar, attached to rib number six, near the APU isolation valve actuator area. 1 287W1224-387 Bracket Locate 1

**FIGURE 13: REWORK BRACKET AT APU ISOLATION MOV ACTUATOR AREA ONLY (SHEET 2 OF 4)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 02, 2007 777-28A0034 Revision 2 September 20, 2010 76 of 96 **BOEING SERVICE BULLETIN 777-28A0034 MORE DATA**  **QTY IDENTIFICATION**  **NAME TASK**  **STEP** Remove all wire harnesses, P-clamps and jumper cablesneeded to get access to the Bracket. (a) (b) - - Wire Harness Generic Remove / Keep 2

Clean and prepare area as given in this figure. Refer to SOPM 20-30-03 asan acceptable procedure. 1 287W1224-387 Bracket Clean 3

Cut out a 1.0 X 0.35 inch area from the bracket as given in this figure. (c) (d) 1 287W1224-387 Bracket Cut 4

Chamfer all corners to a 0.25 inch radius. 1 287W1224-387 Bracket Chamfer 5 Mark this part withthe new part number. Refer to SOPM20-50-10 as an accepted procedure. 1 287W1224-435 Bracket Identify 6

Apply chemical coating to the area of bracket where the finish was removed. - BAC 5626 Colored Chemical Con-version Coating for Aluminum, Type 2, Class A or D Apply 7

Apply primer to the area of bracket where the finish was removed. Refer to SOPM 20-43-03 asan accepted procedure. - BMS 10-11 Chemical and Solvent Resistant Finish (primer) Apply

Install all kept wireharnesses, Pclamps and jumper cables. (a) (b) - - Wire Harness Generic Install (Kept) 8

(a) If you need to remove and install the bracket to make the modification, refer to SWPM 20-20-00 as an accepted procedure for the install of driven rivet electrical bonds (Category 7). (b) If you need to remove and install the bracket to make the modification, refer to SWPM 20-20-00 as an accepted procedure for fastener selection.

**FIGURE 13: REWORK BRACKET AT APU ISOLATION MOV ACTUATOR AREA ONLY (SHEET 3 OF 4)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 02, 2007 777-28A0034 Revision 2 September 20, 2010 77 of 96 **BOEING SERVICE BULLETIN 777-28A0034 MORE DATA**  **QTY IDENTIFICATION**  **NAME TASK**  **STEP** (c) You may want to drill a 0.25 inch radius at the inner corner before you cut. Refer to the figure. (d) Keep a .33 inch minimum edge margin from the P-clamp attach hole. Refer to the figure.

**FIGURE 13: REWORK BRACKET AT APU ISOLATION MOV ACTUATOR AREA ONLY (SHEET 4 OF 4)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 02, 2007 777-28A0034 Revision 2 September 20, 2010 78 of 96 **BOEING SERVICE BULLETIN 777-28A0034**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 14: INSPECT AND RECORD THE DEFUEL MOV ACTUATOR PART NUMBER (RIGHT WING). (SHEET 1 OF 2)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 02, 2007 777-28A0034 Revision 2 September 20, 2010 79 of 96 **BOEING SERVICE BULLETIN 777-28A0034 MORE DATA**  **QTY IDENTIFICATION**  **NAME TASK**  **STEP** Get access to thepart number markings on the MOV ac- tuator. 1

- Motor Operated Valve Actuator Get 1 Record the part number. 1

- Motor Operated Valve Actuator Record 2

**FIGURE 14: INSPECT AND RECORD THE DEFUEL MOV ACTUATOR PART NUMBER (RIGHT WING). (SHEET 2 OF 2)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 02, 2007 777-28A0034 Revision 2 September 20, 2010 80 of 96 **BOEING SERVICE BULLETIN 777-28A0034**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 DATA QTY**  **IDENTIFICATION NAME**  **TASK STEP**  Get access to thepart number markings on the MOV ac- tuator. 1

- Motor Operated Valve Actuator Get 1 Record the part number. 1

- Motor Operated Valve Actuator Record 2

**FIGURE 15: INSPECT AND RECORD FUEL JETTISON NOZZLE MOV ACTUATOR PART NUMBER (INSIDE THE LEFT WING AREA)**  **(SHEET 1 OF 1)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 02, 2007 777-28A0034 Revision 2 September 20, 2010 81 of 96 **BOEING SERVICE BULLETIN 777-28A0034**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 DATA QTY**  **IDENTIFICATION NAME**  **TASK STEP**  Get access to thepart number markings on the MOV ac- tuator. 1

- Motor Operated Valve Actuator Get 1 Record the part number. 1

- Motor Operated Valve Actuator Record 2

**FIGURE 16: INSPECT AND RECORD FUEL JETTISON NOZZLE MOV ACTUATOR PART NUMBER (INSIDE THE RIGHT WING AREA)**  **(SHEET 1 OF 1)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 02, 2007 777-28A0034 Revision 2 September 20, 2010 82 of 96 **BOEING SERVICE BULLETIN 777-28A0034**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 DATA QTY**  **IDENTIFICATION NAME**  **TASK STEP**  Get access to thepart number markings on the MOV ac- tuator. 1

- Motor Operated Valve Actuator Get 1 Record the part number. 1

- Motor Operated Valve Actuator Record 2

**FIGURE 17: INSPECT AND RECORD FUEL JETTISON NOZZLE MOV ACTUATOR PART NUMBER (LEFT WING)**  **(SHEET 1 OF 1)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 02, 2007 777-28A0034 Revision 2 September 20, 2010 83 of 96 **BOEING SERVICE BULLETIN 777-28A0034**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 DATA QTY**  **IDENTIFICATION NAME**  **TASK STEP**  Get access to thepart number markings on the MOV ac- tuator. 1

- Motor Operated Valve Actuator Get 1 Record the part number. 1

- Motor Operated Valve Actuator Record 2

**FIGURE 18: INSPECT AND RECORD FUEL JETTISON NOZZLE MOV ACTUATOR PART NUMBER (RIGHT WING)**  **(SHEET 1 OF 1)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 02, 2007 777-28A0034 Revision 2 September 20, 2010 84 of 96 **BOEING SERVICE BULLETIN 777-28A0034**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 19: INSPECT AND RECORD FUEL JETTISON ISOLATION MOV ACTUATOR PART NUMBER (LEFT WING)**  **(SHEET 1 OF 2)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 02, 2007 777-28A0034 Revision 2 September 20, 2010 85 of 96 **BOEING SERVICE BULLETIN 777-28A0034 MORE DATA**  **QTY IDENTIFICATION**  **NAME TASK**  **STEP** Get access to thepart number markings on the MOV ac- tuator. 1

- Motor Operated Valve Actuator Get 1 Record the part number. 1

- Motor Operated Valve Actuator Record 2

**FIGURE 19: INSPECT AND RECORD FUEL JETTISON ISOLATION 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 777-28A0034 Revision 2 September 20, 2010 86 of 96 **BOEING SERVICE BULLETIN 777-28A0034**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 20: INSPECT AND RECORD FUEL JETTISON ISOLATION MOV ACTUATOR PART NUMBER (RIGHT WING)**  **(SHEET 1 OF 2)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 02, 2007 777-28A0034 Revision 2 September 20, 2010 87 of 96 **BOEING SERVICE BULLETIN 777-28A0034 MORE DATA**  **QTY IDENTIFICATION**  **NAME TASK**  **STEP** Get access to thepart number markings on the MOV ac- tuator. 1

- Motor Operated Valve Actuator Get 1 Record the part number. 1

- Motor Operated Valve Actuator Record 2

**FIGURE 20: INSPECT AND RECORD FUEL JETTISON ISOLATION MOV ACTUATOR PART NUMBER (RIGHT WING)**  **(SHEET 2 OF 2)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 02, 2007 777-28A0034 Revision 2 September 20, 2010 88 of 96 **BOEING SERVICE BULLETIN 777-28A0034**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 DATA QTY**  **IDENTIFICATION NAME**  **TASK STEP**  Apply a Faying bond to the index plate. (a) - BMS 5-95 (BMS 5-45 optional)Pressure and Environmental Sealant-Chromate Type Apply 1

Do not connect the bonding jumper to the MOV actuator. 1 MA30A1001 Motor Operated Valve Actuator Install (New) 2

**FIGURE 21: INSTALL THE MOV ACTUATOR (SHEET 1 OF 4)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 02, 2007 777-28A0034 Revision 2 September 20, 2010 89 of 96 **BOEING SERVICE BULLETIN 777-28A0034 MORE DATA**  **QTY IDENTIFICATION**  **NAME TASK**  **STEP** Measure the electrical resistance of the Faying bond from the foot of the MOVactuator to the airplane structure. (a) (b) - - Electrical Bond Measure 3

Measure the length of the bondingjumper from the attach point on the MOV actuator to the attach point on the airplane structure. Use the shortest bonding jumper that allows no tension. You can select a length from 5-to-9 inches. (a) 1 BACJ40A20-5 Bonding Jumper, 5 IN (optional) Measure 4

If you determined that the bonding jumper is too short, remove the bonding jumper and do the following sub-tasks. 1 BACJ40A20-5 Bonding Jumper, 5 IN (optional) Remove

You can select a length from 5-to-9 inches.(a) 1 BACJ40A20-5 Bonding Jumper, 5 IN (optional) Get

1 BACJ40A20-6 Bonding Jumper, 6 IN (optional) 1 BACJ40A20-7 Bonding Jumper, 7 IN (optional) 1 BACJ40A20-9 Bonding Jumper, 9 IN (optional)

**FIGURE 21: INSTALL THE MOV ACTUATOR (SHEET 2 OF 4)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 02, 2007 777-28A0034 Revision 2 September 20, 2010 90 of 96 **BOEING SERVICE BULLETIN 777-28A0034 MORE DATA**  **QTY IDENTIFICATION**  **NAME TASK**  **STEP** Clean the surface of the bonding jumper lug and fasteners, and the airplane structure. (a) 1

- Bonding Jumper Clean 5

Attach the bondingjumpers to the airplane structure. Use the shortest bonding jumper that allows no tension. You can select a length from 5-to-9 inches. (a) 1

- Bonding Jumper Attach

Apply a Faying bondat the airplane structure for the bonding jumper of the correct length. (a) - BMS 5-95 (BMS 5-45 optional)Pressure and Environmental Sealant-Chromate Type Apply

Torque fasteners. (a) 1

- Bonding Jumper Torque
Clean the surface of the bonding jumper lug and fasteners,and the MOV actuator. (a) 1

- Bonding Jumper Clean 6

Measure the electrical resistance of the Faying bond from the lug on the end of the bonding jumperto a point on the airplane structure. (a) (c) - - Electrical Bond Measure

**FIGURE 21: INSTALL THE MOV ACTUATOR (SHEET 3 OF 4)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 02, 2007 777-28A0034 Revision 2 September 20, 2010 91 of 96 **BOEING SERVICE BULLETIN 777-28A0034 MORE DATA**  **QTY IDENTIFICATION**  **NAME TASK**  **STEP** Attach the bonding jumper to the MOV actuator. - - Bonding Jumper Attach 7

Apply a Faying bond at the MOV actuator for the bonding jumper. (a) 1 BMS 5-95 (BMS 5-45 optional)Pressure and Environmental Sealant-Chromate Type Apply

Torque fasteners. (a) 1

- Bonding Jumper Torque

Measure the electrical resistance of the Faying bond from the lug on the end of the bonding jumper that is installed at the MOV actuator to the foot of the MOV actuator. (a) (d) (e) - - Electrical Bond Measure

Apply cap seal to thebonding jumper fasteners. (a) (f) - BMS 5-95 (BMS 5-45 optional)Pressure and Environmental Sealant-Chromate Type Apply 8

(a) Refer to SWPM 20-20-00 as an accepted procedure. (b) If the measured electrical resistance of the Faying bond from the foot of the MOV actuator to the airplane structure is less than 2.5 milliohms, the Faying bond is acceptable. If the measured electrical resistance of the Faying bond is not acceptable, rework the Faying Bond as necessary. (c) If the measured resistance of the Faying bond from the lug on the end of the bonding jumper to a pointon the airplane structure is less than 1.5 milliohms, the Faying bond is acceptable. If the measured electrical resistance of the Faying bond is not acceptable, rework the Faying Bond as necessary. (d) If the measured resistance of the Faying bond from the lug on the end of the bonding jumper that is installedat the MOV actuator to the foot of the MOV actuator is less than 1.5 milliohms, the Faying bond is acceptable. If the measured electrical resistance of the Faying bond is not acceptable, rework the Faying bond as necessary. (e) The purpose of this step is to measure the electrical continuity across the manufactured joint of the MOV actuator body. (f) 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.

**FIGURE 21: INSTALL THE MOV ACTUATOR (SHEET 4 OF 4)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 02, 2007 777-28A0034 Revision 2 September 20, 2010 92 of 96 **BOEING SERVICE BULLETIN 777-28A0034**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 DATA QTY**  **IDENTIFICATION NAME**  **TASK STEP**  Apply a Faying bond to the index plate. (a) - BMS 5-95 (BMS 5-45 optional)Pressure and Environmental Sealant-Chromate Type Apply 1

Do not connect the bonding jumper to the MOV actuator. 1 MA30A1001 Motor Operated Valve Actuator Install (New) 2

Measure the electrical resistance of the Faying bond from the foot of the MOVactuator to the airplane structure. (a) (b) - - Electrical Bond Measure 3

**FIGURE 22: INSTALL THE FUEL JETTISON NOZZLE VALVE MOV ACTUATOR (INSIDE WING AREA) (SHEET 1 OF 4)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 02, 2007 777-28A0034 Revision 2 September 20, 2010 93 of 96 **BOEING SERVICE BULLETIN 777-28A0034 MORE DATA**  **QTY IDENTIFICATION**  **NAME TASK**  **STEP** Measure the length of the bondingjumper from the attach point on the MOV actuator to the attach point on the airplane structure. Use the shortest bonding jumper that allows no tension. You can select a length from 5-to-9 inches. (a) 1 BACJ40A20-5 Bonding Jumper, 5 IN (optional) Measure 4

If you determined that the bonding jumper is too short, remove the bonding jumper and do the following sub-tasks. 1 BACJ40A20-5 Bonding Jumper, 5 IN (optional) Remove

You can select a length from 5-to-9 inches.(a) 1 BACJ40A20-5 Bonding Jumper, 5 IN (optional) Get

1 BACJ40A20-6 Bonding Jumper, 6 IN (optional) 1 BACJ40A20-7 Bonding Jumper, 7 IN (optional) 1 BACJ40A20-9 Bonding Jumper, 9 IN (optional)

**FIGURE 22: INSTALL THE FUEL JETTISON NOZZLE VALVE MOV ACTUATOR (INSIDE WING AREA) (SHEET 2 OF 4)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 02, 2007 777-28A0034 Revision 2 September 20, 2010 94 of 96 **BOEING SERVICE BULLETIN 777-28A0034 MORE DATA**  **QTY IDENTIFICATION**  **NAME TASK**  **STEP** Clean the surface of the bonding jumper lug and fasteners, and the airplane structure. (a) 1

- Bonding Jumper Clean 5

Attach the bondingjumpers to the airplane structure. Use the shortest bonding jumper that allows no tension. You can select a length from 5-to-9 inches. (a) 1

- Bonding Jumper Attach

Apply a Faying bondat the airplane structure for the bonding jumper of the correct length. (a) - BMS 5-95 (BMS 5-45 optional)Pressure and Environmental Sealant-Chromate Type Apply

Torque fasteners. (a) 1

- Bonding Jumper Torque
Clean the surface of the bonding jumper lug and fasteners,and the MOV actuator. (a) 1

- Bonding Jumper Clean 6

Measure the electrical resistance of the Faying bond from the lug on the end of the bonding jumperto a point on the airplane structure. (a) (c) - - Electrical Bond Measure

**FIGURE 22: INSTALL THE FUEL JETTISON NOZZLE VALVE MOV ACTUATOR (INSIDE WING AREA) (SHEET 3 OF 4)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 02, 2007 777-28A0034 Revision 2 September 20, 2010 95 of 96 **BOEING SERVICE BULLETIN 777-28A0034 MORE DATA**  **QTY IDENTIFICATION**  **NAME TASK**  **STEP** Attach the bonding jumper to the MOV actuator. - - Bonding Jumper Attach 7

Apply a Faying bond at the MOV actuator for the bonding jumper. (a) 1 BMS 5-95 (BMS 5-45 optional)Pressure and Environmental Sealant-Chromate Type Apply

Torque fasteners. (a) 1

- Bonding Jumper Torque

Measure the electrical resistance of the Faying bond from the lug on the end of the bonding jumper that is installed at the MOV actuator to the foot of the MOV actuator. (a) (d) (e) - - Electrical Bond Measure

Apply cap seal to thebonding jumper fasteners.(a) (f) - BMS 5-95 (BMS 5-45 optional)Pressure and Environmental Sealant-Chromate Type Apply 8

(a) Refer to SWPM 20-20-00 as an accepted procedure. (b) If the measured electrical resistance of the Faying bond from the foot of the MOV actuator to the airplane structure is less than 2.5 milliohms, the Faying bond is acceptable. If the measured electrical resistance of the Faying bond is not acceptable, rework the Faying Bond as necessary. (c) If the measured resistance of the Faying bond from the lug on the end of the bonding jumper to a pointon the airplane structure is less than 1.5 milliohms, the Faying bond is acceptable. If the measured electrical resistance of the Faying bond is not acceptable, rework the Faying Bond as necessary. (d) If the measured resistance of the Faying bond from the lug on the end of the bonding jumper that is installedat the MOV actuator to the foot of the MOV actuator is less than 1.5 milliohms, the Faying bond is acceptable. If the measured electrical resistance of the Faying bond is not acceptable, rework the Faying bond as necessary. (e) The purpose of this step is to measure the electrical continuity across the manufactured joint of the MOV actuator body. (f) 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.

**FIGURE 22: INSTALL THE FUEL JETTISON NOZZLE VALVE MOV ACTUATOR (INSIDE WING AREA) (SHEET 4 OF 4)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: August 02, 2007 777-28A0034 Revision 2 September 20, 2010 96 of 96 **BOEING SERVICE BULLETIN 777-28A0034**