# Boeing Alert Service Bulletin 767-28A0090: Boeing Commercial Airplane Group – Service Bullentin - Rights: © The Boeing Company. Filed by the FAA in regulations.gov docket FAA-2009-0314; AD 2009-22-13 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication. - Document: [Boeing Alert Service Bulletin 767-28A0090](https://openairdocs.org/service-documents/boeing/767-28a0090.md) - Title as filed: Boeing Commercial Airplane Group – Service Bullentin - Pages: 118 - PDF: https://openairdocs.org/files/sha256/f7/1b/f71b80f356f5878810416a573adb54b50ebbfb30f00aaa4a2d79031418b8c31c - Page: https://openairdocs.org/service-documents/boeing/767-28a0090/file/f71b80f356f5 ## Text Each page's text from the PDF; open the PDF at a page with #page=N. ### Page 1 July 03, 2008 767-28A0090 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 1 of 118 ALERT ALERT Commercial Airplane Group 767 ALERTALERT Service Bulletin Number: 767-28A0090 Date: July 03, 2008 ATA System: 2822 2825 2826 2831 SUBJECT: FUEL - Main and Center Tanks - Valve Actuator Inspection and Replacement BOEING PROPRIETARY, CONFIDENTIAL, AND/OR TRADE SECRET Copyright © 2008 The Boeing Company Unpublished Work - All Rights Reserved Boeing claims copyright in each page of this document only to the extent that the page contains copyrightable subject matter.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, BBJ, DC-8, DC-9, DC-10, MD-10, MD-11, MD-80, MD-88, MD-90, and the red-white-and-blue 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. ### Page 2 BLANK PAGE July 03, 2008 767-28A0090 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 2 of 118 BOEING SERVICE BULLETIN 767-28A0090 ALERT ALERT BLANK PAGE ### Page 3 Table of Contents July 03, 2008 767-28A0090 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 3 of 118 BOEING SERVICE BULLETIN 767-28A0090 ALERT ALERT Table of Contents Summary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5 1. PLANNING INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9 A. Effectivity . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9 1. Airplanes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9 2. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25 B. Concurrent Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25 C. Reason . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25 D. Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 26 E. Compliance. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 26 F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27 G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 28 H. Weight and Balance Changes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 43 I. Electrical Load Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 43 J. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 43 1. Existing Data: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 43 2. Data supplied with this Service Bulletin: . . . . . . . . . . . . . . . . . . . . . . . . . 44 3. Installation Drawings Used in the Preparation of this Service Bulletin: . . . . . . . . . . 44 K. Publications Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 44 L. Interchangeability and Intermixability of Parts . . . . . . . . . . . . . . . . . . . . . . . . . 44 2. MATERIAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 45 A. Material - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 45 B. Industry Support Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 45 C. Parts Necessary For Each Airplane . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 46 1. Kits/Parts: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 46 2. Parts and Materials Supplied by the Operator: . . . . . . . . . . . . . . . . . . . . . . 47 3. Parts Modified and Reidentified: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 47 4. Parts Removed and Not Replaced: . . . . . . . . . . . . . . . . . . . . . . . . . . . . 47 D. Parts Necessary to Change Spares . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 47 E. Special Tooling - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . 47 F. Special Tooling Necessary to do this Service Bulletin . . . . . . . . . . . . . . . . . . . . . 47 3. ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 49 A. GENERAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 49 B. WORK INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 50 FIGURE 1: Inspect and Record Defueling MOV Actuator Part Number . . . . . . . . . . . . . . . . . 73 FIGURE 2: Remove and Keep Index Plate. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 74 FIGURE 3: Rework Index Plate . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 76 FIGURE 4: Measure and Record Electrical Resistance from Adapter Plate to the Airplane Surface . . 77 FIGURE 5: Prepare Adapter Plate . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 78 FIGURE 6: Put Index Plate in Position for Installation. . . . . . . . . . . . . . . . . . . . . . . . . . 80 FIGURE 7: Install the MOV actuator . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 82 FIGURE 8: Clean Adapter Plate and Airplane Surface . . . . . . . . . . . . . . . . . . . . . . . . . 86 FIGURE 9: Inspect and Record Fuel Jettison Transfer MOV Actuator Part Number (left wing) . . . . . 88 FIGURE 10: Inspect and Record Fuel Jettison Transfer MOV Actuator Part Number (right wing) . . . 89 FIGURE 11: Inspect and Record Fuel Jettison Nozzle MOV Actuator Part Number (left wing) . . . . . 90 FIGURE 12: Inspect and Record Fuel Jettison Nozzle MOV Actuator Part Number (right wing) . . . . 92 ### Page 4 Table of Contents July 03, 2008 767-28A0090 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 4 of 118 BOEING SERVICE BULLETIN 767-28A0090 ALERT ALERT FIGURE 13: Inspect and Record APU Shutoff MOV Actuator Part Number . . . . . . . . . . . . . . . 94 FIGURE 14: Inspect and Record APU Isolation MOV Actuator Part Number . . . . . . . . . . . . . . 95 FIGURE 15: Inspect and Record Engine Fuel Shutoff MOV Actuator Part Number (left wing) . . . . . 96 FIGURE 16: Inspect and Record Engine Fuel Shutoff MOV Actuator Part Number (right wing) . . . . . 97 FIGURE 17: Inspect and Record Dual Forward/Aft Engine Fuel Crossfeed MOV Actuator . . . . . . . 98 FIGURE 18: Inspect and Record Single Engine Fuel Crossfeed MOV Actuator Part Number (left wing) . 100 FIGURE 19: Install the MOV actuator (directly to the motor operated valve). . . . . . . . . . . . . . 101 FIGURE 20: Remove Bracket and Install new Bracket on Engine Fuel Shutoff MOV Actuator Deflector (left wing) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 105 FIGURE 21: Remove Bracket and Install new Bracket on Engine Fuel Shutoff MOV Actuator Deflector (right wing) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 108 FIGURE 22: Install the Shim and Forward Engine Fuel Crossfeed MOV Actuator. . . . . . . . . . . 111 FIGURE 23: Install the Shim and Aft Engine Fuel Crossfeed MOV Actuator. . . . . . . . . . . . . . 115 ### Page 5 July 03, 2008 767-28A0090 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 5 of 118 ALERT ALERT Commercial Airplane Group 767 ALERTALERT Service Bulletin Number: 767-28A0090 Summary Date: July 03, 2008 ATA System: 2822 2825 2826 2831 SUBJECT: FUEL - Main and Center Tanks - Valve Actuator Inspection and Replacement THIS BULLETIN IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN PARAGRAPH 1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS SERVICE BULLETIN TO THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS SERVICE BULLETIN TO THE NEW OWNER. CONCURRENT REQUIREMENTS None. BACKGROUND This service bulletin gives instructions 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 767 Maintenance Planning Data (MPD) Document was change. ### Page 6 July 03, 2008 767-28A0090 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 6 of 118 BOEING SERVICE BULLETIN 767-28A0090 ALERT ALERT ACTION (PRR B13421-6) — 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 MA20A1001-1 is the only installed MOV actuator part number that is affected by this service bulletin. — If you are required to install the MA30A1001, you must do an electrical resistance check at 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. — If you are required to install the MA30A1001 at the dual foward/aft engine fuel crossfeed valve actuator location, you must inspect for the "SWEENEY ENGR CORP" marking on the adapter plate. If found, you must install the shim kit. — Some airplane models have a deflector installed at the left and right engine fuel shutoff MOV actuator location, where an installed wire support assembly can potentially interfere with the new MOV actuator. If you are required to install the MA30A1001 at these locations, you must also install the new wire support assembly on the deflector. The new wire support assembly will prevent part interference. — Close access to each MOV actuator. EFFECTIVITY 767 -200 /-300 /-300F /-400ER airplanes. Refer to this service bulletin Paragraph 1.A.1 for effectivity. COMPLIANCE The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to this service bulletin. The Airworthiness Directive will make the compliance tasks and times given in this service bulletin mandatory. Boeing recommends that this service bulletin be incorporated within 60 months after the date on this service bulletin. INDUSTRY SUPPORT INFORMATION Boeing warranty remedies are not available for the configuration changes given in this service bulletin. ### Page 7 July 03, 2008 767-28A0090 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 7 of 118 BOEING SERVICE BULLETIN 767-28A0090 ALERT ALERT MANPOWER MATERIAL INFORMATION Operator Supplied Parts. Refer to Paragraph 2.A., Material - Price and Availability. Airplanes Total Task Hours Elapsed Hours Group 1.0 401.00 (a) (b) 175.00 (a) (b) Group 2.0 401.00 (a) (b) 175.00 (a) (b) Group 3.0 237.15 (a) (b) 107.65 (a) (b) Group 4.0 237.15 (a) (b) 107.65 (a) (b) Group 5.1 405.60 (a) (b) 178.10 (a) (b) Group 5.2 394.85 (a) (b) 169.35 (a) (b) Group 6.1 241.75 (a) (b) 110.75 (a) (b) Group 6.2 231.00 (a) (b) 102.00 (a) (b) Group 7.1 405.60 (a) (b) 178.10 (a) (b) Group 7.2 405.60 (a) (b) 178.10 (a) (b) Group 7.3 394.85 (a) (b) 169.35 (a) (b) Group 7.4 394.85 (a) (b) 169.35 (a) (b) Group 8.1 241.75 (a) (b) 110.75 (a) (b) Group 8.2 231.00 (a) (b) 102.00 (a) (b) Group 9.0 447.45 (a) (b) 193.95 (a) (b) (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. ### Page 8 July 03, 2008 767-28A0090 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 8 of 118 BOEING SERVICE BULLETIN 767-28A0090 ALERT ALERT ENGINE FUEL CROSS FEED MOV ACTUATOR APU FUEL SHUTOFF MOV ACTUATOR APU FUEL ISOLATION MOV ACTUATOR FUEL JETTISON NOZZLE MOV ACTUATOR DEFUELING MOV ACTUATOR ENGINE FUEL SHUTOFF MOV ACTUATOR FUEL JETTISON TRANSFER MOV ACTUATOR FUEL JETTISON NOZZLE MOV ACTUATOR DEFUELING MOV ACTUATOR INSPECT THE MOV ACTUATORS AT THE ABOVE LOCATIONS. - IF THE MOV ACTUATOR HAS AN UNACCEPTABLE PART NUMBER, REPLACE THE MOV ACTUATOR. - PREPARE AN ELECTRICAL BOND. REAR SPAR INDEX PLATE TYPICAL MOV ACTURATOR INSTALLATION WITHOUT INDEX PLATE TYPICAL MOV ACTUATOR INSTALLATION WITH INDEX PLATE REAR SPAR FWD FWD ADAPTER PLATE FUEL JETTISON TRANSFER MOV ACTUATOR U31989 ### Page 9 July 03, 2008 767-28A0090 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 9 of 118 ALERT ALERT Commercial Airplane Group 767 ALERTALERT Service Bulletin Number: 767-28A0090 Date: July 03, 2008 ATA System: 2822 2825 2826 2831 SUBJECT: FUEL - Main and Center Tanks - Valve Actuator Inspection and Replacement THIS BULLETIN IS SENT TO THE OPERATORS OF RECORD OF THE AIRPLANES SHOWN IN PARAGRAPH 1.A., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS SERVICE BULLETIN TO THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS SERVICE BULLETIN TO THE NEW OWNER. 1. PLANNING INFORMATION A. Effectivity 1. Airplanes This service bulletin is for the airplanes shown below. An equivalent change is on subsequent production airplanes. Refer to PRR B13421-6 for data about this change. GROUP CONFIGURATION DESCRIPTION 1 - 767-200/300/300F airplanes with the production dual crossfeed installation and the production fuel jettison installation. 2 - 767-200/300/300F airplanes with the production dual crossfeed installation and the production fuel jettison installation. And requires an inspection to determine if the Sweeney adapter plates were installed in production. 3 - 767-200/300/300F airplanes with the production dual crossfeed installation, but without fuel jettison installation. 4 - 767-200/300/300F airplanes with the production dual crossfeed installation, but without fuel jettison installation. And requires an inspection to determine if the Sweeney adapter plates were installed in production. ### Page 10 July 03, 2008 767-28A0090 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 10 of 118 BOEING SERVICE BULLETIN 767-28A0090 ALERT ALERT Airplane models: 767-200 767-300 767-300F 767-400ER 5 - 767-200/300/300F airplanes effected by Boeing service bulletin 767-28-0034 to install the dual crossfeed, and with the production jettison installation. 1 Made changes as given in Boeing service bulletin 767-28-0034. 2 Did not make changes as given in Boeing service bulletin 767-28-0034. 6 - 767-200/300/300F airplanes effected by Boeing service bulletin 767-28-0034 to install the dual crossfeed, but without the production jettison installation. 1 Made changes as given in Boeing service bulletin 767-28-0034. 2 Did not make changes as given in Boeing service bulletin 767-28-0034. 7 - 767-200/300/300F airplanes effected by Boeing service bulletin 767-28-0034 to install the dual crossfeed, and effected by Boeing service bulletin 767-28-0027 to install the fuel jettison. 1 Made changes as given in Boeing service bulletin 767-28-0034, and made changes as given in Boeing service bulletin 767-28-0027. 2 Made changes as given in Boeing service bulletin 767-28-0034, but did not make changes as given in Boeing service bulletin 767-28-0027. 3 Did not make changes as given in Boeing service bulletin 767-28-0034, but made changes as given in Boeing service bulletin 767-28-0027. 4 Did not make changes as given in Boeing service bulletin 767-28-0034, and did not make changes as given in Boeing service bulletin 767- 28-0027. 8 - 767-200/300/300F airplanes effected only by Boeing service bulletin 767-28-0034 to install the dual crossfeed. No Jettison Installed. 1 Made changes as given in Boeing service bulletin 767-28-0034. 2 Did not make changes as given in Boeing service bulletin 767-28-0034. 9 - 767-400ER airplanes with an inspection to determine if the Sweeney adapter plates were installed in production. GROUP CONFIGURATION DESCRIPTION ### Page 11 July 03, 2008 767-28A0090 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 11 of 118 BOEING SERVICE BULLETIN 767-28A0090 ALERT ALERT IDENTIFICATION BY CUSTOMER, CUSTOMER CODE, GROUP AND VARIABLE NUMBER 767-200ER TANKER-JAPAN (YTD) 1 VR106 AA 767 LLC (SVX) 8V E 0 6 7 ABX AIR (ABX) 7V B 1 2 5 8 VA301 VA304–VA305 VA309–VA313 VA315 VA803 VA807–VA809 VB101–VB123 VB302 AEROFLOT (ARO) 1 VL896–VL897 2 VS216–VS217 VS321–VS324 VS392 5 VN471–VN472 AEROMEXICO (AMX) 1V F 1 6 2 2V S 2 1 1 5V F 0 7 1 V F 0 9 3 AEROSVIT (UKA) 5 VN157 7 VN155 AEROTURBINE (AUB) 8 VB051 VB054–VB055 VB321–VB322 AIR ALGERIE (ALG) 6 VK131–VK133 AIR ASTANA (AKZ) 1 VL899 AIR CANADA (ACN) 1 VN546–VN547 VN811–VN812 VS546–VS549 2 VS381–VS382 3 VN931–VN936 5 VN059–VN062 VN531 VN536 VN541–VN542 VN751–VN752 7 VA713–VA719 VN051–VN054 VN056–VN058 8 VA701–VA709 VA711–VA712 VB001–VB002 VB201–VB202 AIR CHINA (BEJ) 1 VN388 2 VS206 VS208 VS274 VS307 3 VK162–VK164 6V K 1 6 1 7 VE085–VE086 8 VE064 VE083–VE084 ### Page 12 July 03, 2008 767-28A0090 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 12 of 118 BOEING SERVICE BULLETIN 767-28A0090 ALERT ALERT AIR DO (HIA) 2 VS176–VS177 AIR EUROPA (ARE) 1 VN638 VS292–VS293 2 VS291 AIR ITALY (RIT) 1 VL913 AIR MADAGASCAR (MAD) 5V N 1 6 7 V N 7 3 1 AIR NEW ZEALAND (ANZ) 1 VN653 VN655–VN658 2 VS113 AIR NIUGINI (NIU) 5V N 6 5 1 AIR PACIFIC (APC) 1V N 6 7 6 AIR SAHARA (SAQ) 5V N 4 9 5 AIR SEYCHELLES (ASY) 1 VL941 VS526 AIR TRANSPORT INTERNATIONAL (TIN) 8 VA509–VA513 AIR ZIMBABWE (ZMB) 5V F 0 6 2 7V F 0 6 1 ALITALIA (ALI) 1 VL701–VL702 VN422–VN427 VN732 VN813 2 VS366–VS367 VS401 ALL NIPPON AIRWAYS (ANA) 1 VN194–VN198 VS721–VS732 VT501 VT521 3 VK100–VK113 4V R 4 0 1 5V N 1 9 3 6 VK094–VK099 7 VK081–VK093 VN191–VN192 ### Page 13 July 03, 2008 767-28A0090 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 13 of 118 BOEING SERVICE BULLETIN 767-28A0090 ALERT ALERT AMERICAN AIRLINES (AAL) 1 VN021–VN041 VS751–VS759 2 VS196–VS203 5 VN016–VN020 7 VA521–VA525 VA527–VA530 VN001–VN015 8 VA501–VA508 VA514–VA520 ARAMCO ASSOCIATED COMPANY (RAS) 1 VR084 ARKEFLY (HXL) 1 VN225 5 VN156 VN164–VN165 ASIANA AIRLINES (AAR) 1V W 8 5 1 3 VK143–VK148 4 VR426 AUSTRALIAN AIRLINES (AUF) 2V S 4 8 6 5 VN089–VN092 AUSTRIAN (AUL) 1 VN242–VN243 VS303 2 VS301–VS302 5 VN671 AVIANCA (AVI) 5 VF072 VF092 VF161 VN532 6 VE171–VE172 7 VN152 AWAS (AWW) 7V B 3 2 5 BELAIR AIRLINES (BLB) 1 VL932 BELLVIEW AIRLINES (BEB) 7 VE125–VE126 BLUE CITY HOLDING (BCY) 7V E 0 6 9 BLUE PANORAMA AIRLINES (BPA) 1 VL911 VN174 2V S 0 6 1 5 VN681 BRA TRANSPORTES AEREOS (BRW) 5 VN376 8V A 8 0 6 ### Page 14 July 03, 2008 767-28A0090 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 14 of 118 BOEING SERVICE BULLETIN 767-28A0090 ALERT ALERT BRAVO AIRLINES (BVA) 7 VE104 BRITISH AIRWAYS (BAB) 1 VN125–VN127 VN133–VN137 2 VS246–VS248 5 VN118–VN122 VN124 7 VN111–VN114 CAMEROON AIRLINES (CAM) 1 VS308 8 VA801 CHINA EASTERN YUNNAN AIRLINES (YUN) 1 VL871–VL873 CONDOR (CDF) 1 VN684–VN691 5V N 6 8 3 CONTINENTAL AIRLINES (CAL) 1 VR051–VR060 9 VQ071–VQ086 CROCUS CORPORATION (CCS) 1 VS825 DELTA AIR LINES (DAL) 1 VL753 VN261–VN276 VS471–VS472 2 VS066–VS070 VS073–VS078 VS266–VS273 VS466–VS470 3 VK055–VK056 4 VR471–VR472 5 VN251–VN260 VN301–VN306 6 VK046–VK054 7 VK036–VK045 8 VA302–VA303 VA306 VA314 VK035 9 VQ001–VQ021 EDREES AVIATION (SME) 8 VA804 EL AL ISRAEL AIRLINES (ELA) 3V N 9 7 2 5 VF101–VF102 VN537 VN682 8 VB281–VB284 ERITREAN AIR LINES (ERJ) 8 VE066 ETHIOPIAN AIRLINES (ETH) 1 VL898 VS881–VS883 2 VS306 VS506–VS507 8 VE002 ### Page 15 July 03, 2008 767-28A0090 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 15 of 118 BOEING SERVICE BULLETIN 767-28A0090 ALERT ALERT ETIHAD AIRWAYS (ETI) 2V S 3 9 1 EUROATLANTIC AIRWAYS (MAE) 1 VN561–VN562 5 VN551 7 VN151 EVERGREEN AIR CENTER (EAC) 8V E 0 6 1 EXCEL AIRWAYS (SBE) 1 VN557 7 VB326–VB327 VL011 VN153 FIRST CHOICE AIRWAYS (ATZ) 1 VL751–VL752 VL754 VN791–VN792 3 VN921 FLYGLOBESPAN.COM (FGS) 1 VN654 2V S 1 1 2 FLYJET LIMITED (FJE) 8V E 1 1 7 GABON AIRLINES (GBO) 8 VA017–VA018 GE CAPITAL CORPORATION (GEF) 7V E 1 2 3 GULF AIR (GUL) 1 VN307–VN310 VN313–VN314 7 VL004–VL006 HAINAN AIRLINES (HNA) 1 VS426–VS428 VS497 2V S 4 9 6 HAWAIIAN AIRLINES (HWI) 1 VS309–VS311 VS821–VS824 VS841–VS843 5 VN381 7 VN171–VN173 8 VK031–VK034 HEWA BORA AIRWAYS (EXD) 8V E 0 2 1 ICELANDAIR (ICE) 5 VN158 VN163 7 VN211 ### Page 16 July 03, 2008 767-28A0090 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 16 of 118 BOEING SERVICE BULLETIN 767-28A0090 ALERT ALERT ITALIAN AIR FORCE (ZSV) 1 VR086–VR087 ITOCHU CORPORATION (CIT) 3 VF181–VF184 JAL INTERNATIONAL (JAL) 1 VS701–VS714 3 VK012–VK016 VK181 VK186 4V R 4 4 1 V R 4 6 1 6 VK010–VK011 7 VK004–VK009 VK021–VK022 8 VB371–VB373 VK001–VK003 KALAIR (BERMUDA) (KLB) 1V N 3 1 1 KENYA AIRWAYS (KEN) 1 VN421 VS331–VS333 6 VK141 7 VL003 KLM - ROYAL DUTCH AIRLINES (KLM) 1 VL900 2 VS136 KRASAIR (ZXD) 7V F 0 5 1 8 VE001 VE022–VE023 LAN AIRLINES (LAN) 1 VL703 VR258–VR260 VT511–VT512 2 VR251 VR256–VR257 VS111 VS131–VS133 3 VN966–VN971 5 VN063–VN064 VN166 VN168 VN753 LOT POLISH AIRLINES (LOT) 1 VN292–VN293 5 VN233 VN291 VN652 7 VF041–VF042 MALEV HUNGARIAN AIRLINES (HGA) 1 VF171–VF172 MARTINAIR HOLLAND (MTH) 1V N 3 8 5 5 VN222–VN224 VN672 7V N 2 2 1 MAXJET AIRWAYS (SLQ) 7 VF001–VF002 8 VB301 VE041 VE063 ### Page 17 July 03, 2008 767-28A0090 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 17 of 118 BOEING SERVICE BULLETIN 767-28A0090 ALERT ALERT MEXICANA (CMA) 7 VL001–VL002 VN154 MID EAST JET (SKL) 1V F 2 5 1 MYTRAVEL AIRWAYS (GUE) 3 VN951–VN953 NATIONWIDE AIRLINES (NWR) 1 VN556 NEOS (NEO) 1 VL892 VL894 NORTH AMERICAN AIRLINES (NNA) 1 VL755 VL895 2V S 3 1 6 3 VN922 OCEANAIR AIRLINES (OAL) 1 VN500 PACE AIRLINES (PIE) 8V B 0 5 3 PHOENIX AIRCRAFT LEASING, INC. (PLB) 8V A 8 1 0 PLUNA (PLU) 1 VN436 PRIVATAIR (PTS) 2V S 1 3 7 QANTAS (QAN) 1 VN093–VN099 2 VS186–VS187 5 VN086–VN088 VN116–VN117 VN123 VN130–VN132 7 VN081–VN085 VN115 ROYAL AIR MAROC (RAM) 1 VN636 VS336–VS337 ROYAL BRUNEI AIRLINES (RBA) 1 VN382–VN384 VN386–VN387 5 VN372 SALAMIS AVIATION (LMV) 8V E 0 6 8 ### Page 18 July 03, 2008 767-28A0090 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 18 of 118 BOEING SERVICE BULLETIN 767-28A0090 ALERT ALERT SHANGHAI AIRLINES (SHA) 2 VS207 3 VK171 VR423 4 VR421–VR422 SKYMARK AIRLINES (SKM) 1 VN637 VS231 VS263 VS861 2 VS261–VS262 SKYSTAR (SYW) 8 VA011–VA012 STAR AIR (SBJ) 3 VB441–VB444 7 VB328 8 VA307–VA308 VB323 VE101–VE103 STATE AIR COMPANY "BERKUT" (ORE) 1V R 0 8 1 TAA (TNL) 8 VA002–VA003 VA006 VA009–VA010 VA014–VA015 VA019–VA020 TAMPA CARGO (TMP) 7 VE121–VE122 VE124 TEEBAH AIRLINES (EBH) 8 VA710 THE SULTAN'S FLIGHT (BWN) 1V F 1 8 0 THOMSONFLY (BRI) 1 VL912 VL914 2 VS051–VS056 6 VB329–VB332 TRANSAERO AIRLINES (TRX) 5 VN371 VN631–VN633 6 VE118 7 VE143 8 VE116 TRANSATLANTIC INTL AIRLINES (TIB) 8 VA016 TUI AIRLINES BELGIUM (TLB) 5V N 2 3 4 TURKMENISTAN AIRLINES (TUE) 1 VS891 ### Page 19 July 03, 2008 767-28A0090 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 19 of 118 BOEING SERVICE BULLETIN 767-28A0090 ALERT ALERT UK INTERNATIONAL AIRLINES (UKI) 8 VA004–VA005 UNITED AIRLINES (UAL) 1 VN498–VN499 VN501–VN513 VS103–VS104 2 VS091–VS102 5 VN491–VN494 VN496–VN497 8 VA007–VA008 UPS (UPS) 1 VR210–VR211 VW701–VW721 2 VR201–VR209 US AIRWAYS (USA) 3V E 1 5 2 6 VE147–VE149 VE151 7 VE141–VE142 VE144–VE146 UZBEKISTAN AIRWAYS (UZB) 1 VL806–VL807 VS844 VS896 VARIG AIRLINES (VAR) 5 VN231–VN232 7 VN055 VIVA MACAU (VMC) 5V F 0 9 1 6V K 1 4 2 VOLARE S.P.A (VLR) 1 VL931 YONA (IOP) 1 VN312 ZOOM AIRLINES (YFM) 1 VL891 VL893 VN634–VN635 IDENTIFICATION BY VARIABLE NUMBER Variable Group VA002–VA012 8 VA014–VA020 8 VA301–VA315 8 VA501–VA520 8 VA521–VA525 7 VA527–VA530 7 VA701–VA712 8 VA713–VA719 7 VA801 8 ### Page 20 July 03, 2008 767-28A0090 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 20 of 118 BOEING SERVICE BULLETIN 767-28A0090 ALERT ALERT VA803–VA804 8 VA806–VA810 8 VB001–VB002 8 VB051 8 VB053–VB055 8 VB101–VB123 8 VB125 7 VB201–VB202 8 VB281–VB284 8 VB301–VB302 8 VB321–VB323 8 VB325–VB328 7 VB329–VB332 6 VB371–VB373 8 VB441–VB444 3 VE001–VE002 8 VE021–VE023 8 VE041 8 VE061 8 VE063–VE064 8 VE066–VE068 8 VE069 7 VE083–VE084 8 VE085–VE086 7 VE101–VE103 8 VE104 7 VE116–VE117 8 VE118 6 VE121–VE126 7 VE141–VE146 7 VE147–VE149 6 VE151 6 VE152 3 VE171–VE172 6 VF001–VF002 7 VF041–VF042 7 VF051 7 VF061 7 VF062 5 Variable Group ### Page 21 July 03, 2008 767-28A0090 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 21 of 118 BOEING SERVICE BULLETIN 767-28A0090 ALERT ALERT VF071–VF072 5 VF091–VF093 5 VF101–VF102 5 VF161 5 VF162 1 VF171–VF172 1 VF180 1 VF181–VF184 3 VF251 1 VK001–VK003 8 VK004–VK009 7 VK010–VK011 6 VK012–VK016 3 VK021–VK022 7 VK031–VK035 8 VK036–VK045 7 VK046–VK054 6 VK055–VK056 3 VK081–VK093 7 VK094–VK099 6 VK100–VK113 3 VK131–VK133 6 VK141–VK142 6 VK143–VK148 3 VK161 6 VK162–VK164 3 VK171 3 VK181 3 VK186 3 VL001–VL006 7 VL011 7 VL701–VL703 1 VL751–VL755 1 VL806–VL807 1 VL871–VL873 1 VL891–VL900 1 VL911–VL914 1 VL931–VL932 1 VL941 1 Variable Group ### Page 22 July 03, 2008 767-28A0090 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 22 of 118 BOEING SERVICE BULLETIN 767-28A0090 ALERT ALERT VN001–VN015 7 VN016–VN020 5 VN021–VN041 1 VN051–VN058 7 VN059–VN064 5 VN081–VN085 7 VN086–VN092 5 VN093–VN099 1 VN111–VN115 7 VN116–VN124 5 VN125–VN127 1 VN130–VN132 5 VN133–VN137 1 VN151–VN155 7 VN156–VN158 5 VN163–VN168 5 VN171–VN173 7 VN174 1 VN191–VN192 7 VN193 5 VN194–VN198 1 VN211 7 VN221 7 VN222–VN224 5 VN225 1 VN231–VN234 5 VN242–VN243 1 VN251–VN260 5 VN261–VN276 1 VN291 5 VN292–VN293 1 VN301–VN306 5 VN307–VN314 1 VN371–VN372 5 VN376 5 VN381 5 VN382–VN388 1 VN421–VN427 1 VN436 1 Variable Group ### Page 23 July 03, 2008 767-28A0090 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 23 of 118 BOEING SERVICE BULLETIN 767-28A0090 ALERT ALERT VN471–VN472 5 VN491–VN497 5 VN498–VN513 1 VN531–VN532 5 VN536–VN537 5 VN541–VN542 5 VN546–VN547 1 VN551 5 VN556–VN557 1 VN561–VN562 1 VN631–VN633 5 VN634–VN638 1 VN651–VN652 5 VN653–VN658 1 VN671–VN672 5 VN676 1 VN681–VN683 5 VN684–VN691 1 VN731 5 VN732 1 VN751–VN753 5 VN791–VN792 1 VN811–VN813 1 VN921–VN922 3 VN931–VN936 3 VN951–VN953 3 VN966–VN972 3 VQ001–VQ021 9 VQ071–VQ086 9 VR051–VR060 1 VR081 1 VR084 1 VR086–VR087 1 VR106 1 VR201–VR209 2 VR210–VR211 1 VR251 2 VR256–VR257 2 VR258–VR260 1 Variable Group ### Page 24 July 03, 2008 767-28A0090 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 24 of 118 BOEING SERVICE BULLETIN 767-28A0090 ALERT ALERT VR401 4 VR421–VR422 4 VR423 3 VR426 4 VR441 4 VR461 4 VR471–VR472 4 VS051–VS056 2 VS061 2 VS066–VS070 2 VS073–VS078 2 VS091–VS102 2 VS103–VS104 1 VS111–VS113 2 VS131–VS133 2 VS136–VS137 2 VS176–VS177 2 VS186–VS187 2 VS196–VS203 2 VS206–VS208 2 VS211 2 VS216–VS217 2 VS231 1 VS246–VS248 2 VS261–VS262 2 VS263 1 VS266–VS274 2 VS291 2 VS292–VS293 1 VS301–VS302 2 VS303 1 VS306–VS307 2 VS308–VS311 1 VS316 2 VS321–VS324 2 VS331–VS333 1 VS336–VS337 1 VS366–VS367 2 VS381–VS382 2 Variable Group ### Page 25 July 03, 2008 767-28A0090 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 25 of 118 BOEING SERVICE BULLETIN 767-28A0090 ALERT ALERT 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. B. Concurrent Requirements None C. Reason This service bulletin gives instructions 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. VS391–VS392 2 VS401 2 VS426–VS428 1 VS466–VS470 2 VS471–VS472 1 VS486 2 VS496 2 VS497 1 VS506–VS507 2 VS526 1 VS546–VS549 1 VS701–VS714 1 VS721–VS732 1 VS751–VS759 1 VS821–VS825 1 VS841–VS844 1 VS861 1 VS881–VS883 1 VS891 1 VS896 1 VT501 1 VT511–VT512 1 VT521 1 VW701–VW721 1 VW851 1 Variable Group ### Page 26 July 03, 2008 767-28A0090 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 26 of 118 BOEING SERVICE BULLETIN 767-28A0090 ALERT ALERT 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 767 Maintenance Planning Data (MPD) Document was change. D. Description — 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 MA20A1001- 1 is the only installed MOV actuator part number that is affected by this service bulletin. — If you are required to install the MA30A1001, you must do an electrical resistance check at 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. — If you are required to install the MA30A1001 at the dual foward/aft engine fuel crossfeed valve actuator location, you must inspect for the "SWEENEY ENGR CORP" marking on the adapter plate. If found, you must install the shim kit. — Some airplane models have a deflector installed at the left and right engine fuel shutoff MOV actuator location, where an installed wire support assembly can potentially interfere with the new MOV actuator. If you are required to install the MA30A1001 at these locations, you must also install the new wire support assembly on the deflector. The new wire support assembly will prevent part interference. — Close access to each MOV actuator. E. Compliance The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to this service bulletin. The Airworthiness Directive will make the compliance tasks and times given in this service bulletin mandatory. Boeing recommends that this service bulletin be incorporated within 60 months on the release date of this service bulletin. ### Page 27 July 03, 2008 767-28A0090 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 27 of 118 BOEING SERVICE BULLETIN 767-28A0090 ALERT ALERT 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. ### Page 28 July 03, 2008 767-28A0090 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 28 of 118 BOEING SERVICE BULLETIN 767-28A0090 ALERT ALERT G. Manpower Work Package Tasks Number of Persons Task Hours Elapsed Hours Work Package 1 Prepare 2 1.00 0.50 Open MOV actuator access 1 0.10 0.10 Figure 1 1 0.25 0.25 Remove MOV actuator 1 0.25 0.25 Figure 2 1 1.00 1.00 Figure 3 1 1.00 1.00 Figure 4 1 0.50 0.50 MOV access/ fuel tank entry (a) 4 32.0 8.00 Remove adapter plate and adapter shaft (a) 2 2.00 1.00 Figure 8 (a) 1 1.00 1.00 Install adapter plate and adapter shaft (a) 2 2.00 1.00 Figure 4 (a) 1 0.50 0.50 Figure 5 1 1.50 1.50 Figure 6 1 0.50 0.50 Install index plate 1 0.50 0.50 Figure 7 1 0.25 0.25 Close MOV access in fuel tank 2 8.00 4.00 Close MOV actuator access 1 0.10 0.10 Test fuel system 2 2.00 1.00 Total for Work Package 54.45 22.95 ### Page 29 July 03, 2008 767-28A0090 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 29 of 118 BOEING SERVICE BULLETIN 767-28A0090 ALERT ALERT Work Package 2 Prepare 2 1.00 0.50 Open MOV actuator access 1 0.10 0.10 Figure 9 1 0.25 0.25 Remove MOV actuator 1 0.25 0.25 Figure 2 1 1.00 1.00 Figure 3 1 1.00 1.00 Figure 4 1 0.50 0.50 MOV access/ fuel tank entry (a) 4 32.0 8.00 Remove adapter plate and adapter shaft (a) 2 2.00 1.00 Figure 8 (a) 1 1.00 1.00 Install adapter plate and adapter shaft (a) 2 2.00 1.00 Figure 4 (a) 1 0.50 0.50 Figure 5 1 1.50 1.50 Figure 6 1 0.50 0.50 Install index plate 1 0.50 0.50 Figure 7 1 0.25 0.25 Close MOV access in fuel tank 2 8.00 4.00 Close MOV actuator access 1 0.10 0.10 Test fuel system 2 2.00 1.00 Total for Work Package 54.45 22.95 Work Package Tasks Number of Persons Task Hours Elapsed Hours ### Page 30 July 03, 2008 767-28A0090 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 30 of 118 BOEING SERVICE BULLETIN 767-28A0090 ALERT ALERT Work Package 3 Prepare 2 1.00 0.50 Open MOV actuator access 1 0.10 0.10 Figure 10 1 0.25 0.25 Remove MOV actuator 1 0.25 0.25 Figure 2 1 1.00 1.00 Figure 3 1 1.00 1.00 Figure 4 1 0.50 0.50 MOV access/ fuel tank entry (a) 4 32.0 8.00 Remove adapter plate and adapter shaft (a) 2 2.00 1.00 Figure 8 (a) 1 1.00 1.00 Install adapter plate and adapter shaft (a) 2 2.00 1.00 Figure 4 (a) 1 0.50 0.50 Figure 5 1 1.50 1.50 Figure 6 1 0.50 0.50 Install index plate 1 0.50 0.50 Figure 7 1 0.25 0.25 Close MOV access in fuel tank 2 8.00 4.00 Close MOV actuator access 1 0.10 0.10 Test fuel system 2 2.00 1.00 Total for Work Package 54.45 22.95 Work Package Tasks Number of Persons Task Hours Elapsed Hours ### Page 31 July 03, 2008 767-28A0090 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 31 of 118 BOEING SERVICE BULLETIN 767-28A0090 ALERT ALERT Work Package 4 Prepare 2 1.00 0.50 Open MOV actuator access 1 0.10 0.10 Figure 11 1 0.50 0.50 Remove MOV actuator 1 0.25 0.25 Figure 2 1 1.00 1.00 Figure 3 1 1.00 1.00 Figure 4 1 0.50 0.50 MOV access/ fuel tank entry (a) 4 32.0 8.00 Remove adapter plate and adapter shaft (a) 2 2.00 1.00 Figure 8 (a) 1 1.00 1.00 Install adapter plate and adapter shaft (a) 2 2.00 1.00 Figure 4 (a) 1 0.50 0.50 Figure 5 1 1.50 1.50 Figure 6 1 0.50 0.50 Install index plate 1 0.50 0.50 Figure 7 1 0.25 0.25 Close MOV access in fuel tank 2 8.00 4.00 Close MOV actuator access 1 0.10 0.10 Test fuel system 2 2.00 1.00 Total for Work Package 54.70 22.20 Work Package Tasks Number of Persons Task Hours Elapsed Hours ### Page 32 July 03, 2008 767-28A0090 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 32 of 118 BOEING SERVICE BULLETIN 767-28A0090 ALERT ALERT Work Package 5 Prepare 2 1.00 0.50 Open MOV actuator access 1 0.10 0.10 Figure 12 1 0.50 0.50 Remove MOV actuator 1 0.25 0.25 Figure 2 1 1.00 1.00 Figure 3 1 1.00 1.00 Figure 4 1 0.50 0.50 MOV access/ fuel tank entry (a) 4 32.0 8.00 Remove adapter plate and adapter shaft (a) 2 2.00 1.00 Figure 8 (a) 1 1.00 1.00 Install adapter plate and adapter shaft (a) 2 2.00 1.00 Figure 4 (a) 1 0.50 0.50 Figure 5 1 1.50 1.50 Figure 6 1 0.50 0.50 Install index plate 1 0.50 0.50 Figure 7 1 0.25 0.25 Close MOV access in fuel tank 2 8.00 4.00 Close MOV actuator access 1 0.10 0.10 Test fuel system 2 2.00 1.00 Total for Work Package 54.70 22.20 Work Package Tasks Number of Persons Task Hours Elapsed Hours ### Page 33 July 03, 2008 767-28A0090 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 33 of 118 BOEING SERVICE BULLETIN 767-28A0090 ALERT ALERT Work Package 6 Prepare 2 1.00 0.50 Open MOV actuator access 1 0.10 0.10 Figure 13 1 0.50 0.50 Remove MOV actuator 1 0.25 0.25 Figure 18 1 0.25 0.25 Close MOV actuator access 1 0.50 0.50 Test fuel system 2 2.00 1.00 Total for Work Package 4.60 3.10 Work Package 7 Prepare 2 1.00 0.50 Open MOV actuator access 1 0.10 0.10 Figure 14 1 0.50 0.50 Remove MOV actuator 1 0.25 0.25 Figure 18 1 0.25 0.25 Close MOV actuator access 1 0.50 0.50 Test fuel system 2 2.00 1.00 Total for Work Package 4.60 3.10 Work Package Tasks Number of Persons Task Hours Elapsed Hours ### Page 34 July 03, 2008 767-28A0090 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 34 of 118 BOEING SERVICE BULLETIN 767-28A0090 ALERT ALERT Work Package 8 Prepare 2 1.00 0.50 Open MOV actuator access 1 0.10 0.10 Figure 15 1 0.25 0.25 Remove MOV actuator 1 0.25 0.25 Figure 20 1 2.00 2.00 Figure 2 1 1.00 1.00 Figure 3 1 1.00 1.00 Figure 4 1 0.50 0.50 MOV access/ fuel tank entry (a) 4 32.0 8.00 Remove adapter plate and adapter shaft (a) 2 2.00 1.00 Figure 8 (a) 1 1.00 1.00 Install adapter plate and adapter shaft (a) 2 2.00 1.00 Figure 4 (a) 1 0.50 0.50 Figure 5 1 1.50 1.50 Figure 6 1 0.50 0.50 Install index plate 1 0.50 0.50 Figure 7 1 0.25 0.25 Close MOV access in fuel tank 2 8.00 4.00 Close MOV actuator access 1 0.10 0.10 Test fuel system 2 2.00 1.00 Total for Work Package 56.45 24.95 Work Package Tasks Number of Persons Task Hours Elapsed Hours ### Page 35 July 03, 2008 767-28A0090 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 35 of 118 BOEING SERVICE BULLETIN 767-28A0090 ALERT ALERT Work Package 9 Prepare 2 1.00 0.50 Open MOV actuator access 1 0.10 0.10 Figure 16 1 0.25 0.25 Remove MOV actuator 1 0.25 0.25 Figure 21 1 2.00 2.00 Figure 2 1 1.00 1.00 Figure 3 1 1.00 1.00 Figure 4 1 0.50 0.50 MOV access/ fuel tank entry (a) 4 32.0 8.00 Remove adapter plate and adapter shaft (a) 2 2.00 1.00 Figure 8 (a) 1 1.00 1.00 Install adapter plate and adapter shaft (a) 2 2.00 1.00 Figure 4 (a) 1 0.50 0.50 Figure 5 1 1.50 1.50 Figure 6 1 0.50 0.50 Install index plate 1 0.50 0.50 Figure 7 1 0.25 0.25 Close MOV access in fuel tank 2 8.00 4.00 Close MOV actuator access 1 0.10 0.10 Test fuel system 2 2.00 1.00 Total for Work Package 56.45 24.95 Work Package Tasks Number of Persons Task Hours Elapsed Hours ### Page 36 July 03, 2008 767-28A0090 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 36 of 118 BOEING SERVICE BULLETIN 767-28A0090 ALERT ALERT Work Package 10 Prepare 2 1.00 0.50 Open MOV actuator access 1 0.10 0.10 Figure 15 1 0.25 0.25 Remove MOV actuator 1 0.25 0.25 Figure 2 1 1.00 1.00 Figure 3 1 1.00 1.00 Figure 4 1 0.50 0.50 MOV access/ fuel tank entry (a) 4 32.0 8.00 Remove adapter plate and adapter shaft (a) 2 2.00 1.00 Figure 8 (a) 1 1.00 1.00 Install adapter plate and adapter shaft (a) 2 2.00 1.00 Figure 4 (a) 1 0.50 0.50 Figure 5 1 1.50 1.50 Figure 6 1 0.50 0.50 Install index plate 1 0.50 0.50 Figure 7 1 0.25 0.25 Close MOV access in fuel tank 2 8.00 4.00 Close MOV actuator access 1 0.10 0.10 Test fuel system 2 2.00 1.00 Total for Work Package 54.45 22.95 Work Package Tasks Number of Persons Task Hours Elapsed Hours ### Page 37 July 03, 2008 767-28A0090 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 37 of 118 BOEING SERVICE BULLETIN 767-28A0090 ALERT ALERT Work Package 11 Prepare 2 1.00 0.50 Open MOV actuator access 1 0.10 0.10 Figure 16 1 0.25 0.25 Remove MOV actuator 1 0.25 0.25 Figure 2 1 1.00 1.00 Figure 3 1 1.00 1.00 Figure 4 1 0.50 0.50 MOV access/ fuel tank entry (a) 4 32.0 8.00 Remove adapter plate and adapter shaft (a) 2 2.00 1.00 Figure 8 (a) 1 1.00 1.00 Install adapter plate and adapter shaft (a) 2 2.00 1.00 Figure 4 (a) 1 0.50 0.50 Figure 5 1 1.50 1.50 Figure 6 1 0.50 0.50 Install index plate 1 0.50 0.50 Figure 7 1 0.25 0.25 Close MOV access in fuel tank 2 8.00 4.00 Close MOV actuator access 1 0.10 0.10 Test fuel system 2 2.00 1.00 Total for Work Package 54.45 22.95 Work Package Tasks Number of Persons Task Hours Elapsed Hours ### Page 38 July 03, 2008 767-28A0090 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 38 of 118 BOEING SERVICE BULLETIN 767-28A0090 ALERT ALERT Work Package 12 Prepare 2 1.00 0.50 Open MOV actuator access 1 0.10 0.10 Figure 17 1 0.25 0.25 Remove MOV actuator 1 0.25 0.25 Figure 2 (b) 1 2.00 2.00 Figure 3 (b) 1 2.00 2.00 Figure 4 (b) 1 1.00 1.00 MOV access/ fuel tank entry (a) 4 32.0 8.00 Remove adapter plate and adapter shaft (a)(b) 2 4.00 2.00 Figure 8. (a)(b) 1 2.00 2.00 Install adapter plate and adapter shaft (a)(b) 2 4.00 2.00 Figure 4 (a)(b) 1 1.00 1.00 Figure 5 (b) 1 3.00 3.00 Figure 6 (b) 1 1.00 1.00 Install index plate (b) 1 1.00 1.00 Figure 7(b)(c) 1 0.50 0.50 Close MOV access in fuel tank 2 8.00 4.00 Close MOV actuator access 1 0.10 0.10 Test fuel system 2 2.00 1.00 Total for Work Package 65.20 31.70 Work Package Tasks Number of Persons Task Hours Elapsed Hours ### Page 39 July 03, 2008 767-28A0090 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 39 of 118 BOEING SERVICE BULLETIN 767-28A0090 ALERT ALERT Work Package 13 Prepare 2 1.00 0.50 Open MOV actuator access 1 0.10 0.10 Figure 18 1 0.25 0.25 Remove MOV actuator 1 0.25 0.25 Figure 2 1 1.00 1.00 Figure 3 1 1.00 1.00 Figure 4 1 0.50 0.50 MOV access/ fuel tank entry (a) 4 32.0 8.00 Remove adapter plate and adapter shaft (a) 2 2.00 1.00 Figure 8. (a) 1 1.00 1.00 Install adapter plate and adapter shaft (a) 2 2.00 1.00 Figure 4 (a) 1 0.50 0.50 Figure 5 1 1.50 1.50 Figure 6 1 0.50 0.50 Install index plate 1 0.50 0.50 Figure 7 1 0.25 0.25 Close fuel tank access (a) 2 8.00 4.00 Close MOV actuator access 1 0.10 0.10 Test fuel system 2 2.00 1.00 Total for Work Package 54.45 22.95 Work Package Tasks Number of Persons Task Hours Elapsed Hours ### Page 40 July 03, 2008 767-28A0090 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 40 of 118 BOEING SERVICE BULLETIN 767-28A0090 ALERT ALERT (a) This 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 in not satisfactory. (b) This figure applies to the two MOV actuators for this Work Packages. (c) Figure 7 is a standard MOV actuator install, which does not require a shim plate install. If a visual inspection has determined that a Sweeney adapter assembly is installed, then the shim kit must be installed. Either Figure 22 or Figure 23 will be referred to in the Accomplishment Instructions to do the work. See the Accomplishment Instructions for Work Package 9 for more detail. Group 1-2: Only the Work Packages for these Groups Sum of Work Packages Total Task-Hours (a) Total Elapsed Hours Work Package 1 54.45 22.95 Work Package 2 54.45 22.95 Work Package 3 54.45 22.95 Work Package 4 54.70 22.20 Work Package 5 54.70 22.20 Work Package 6 4.60 3.10 Work Package 8 56.45 24.95 Work Package 9 56.45 24.95 Work Package 12 65.20 31.70 TOTAL FOR EACH AIRPLANE 455.45 197.95 (a) See the Work Package tables for details. Group 3-4: Only the Work Packages for these Groups Sum of Work Packages Total Task-Hours (a) Total Elapsed Hours Work Package 1 54.45 22.95 Work Package 6 4.60 3.10 Work Package 8 56.45 24.95 Work Package 9 56.45 24.95 Work Package 12 65.20 31.70 TOTAL FOR EACH AIRPLANE 237.15 107.65 (a) See the Work Package tables for details. Group 5, Configuration 1; Group 7, Configuration 1; Group 7, Configuration 2: Only the Work Packages for these Groups Sum of Work Packages Total Task-Hours (a) Total Elapsed Hours Work Package 1 54.45 22.95 Work Package 2 54.45 22.95 Work Package 3 54.45 22.95 Work Package 4 54.70 22.20 Work Package Tasks Number of Persons Task Hours Elapsed Hours ### Page 41 July 03, 2008 767-28A0090 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 41 of 118 BOEING SERVICE BULLETIN 767-28A0090 ALERT ALERT Work Package 5 54.70 22.20 Work Package 6 4.60 3.10 Work Package 7 4.60 3.10 Work Package 8 56.45 24.95 Work Package 9 56.45 24.95 Work Package 12 65.20 31.70 TOTAL FOR EACH AIRPLANE 460.05 201.05 (a) See the Work Package tables for details. Group 5, Configuration 2; Group 7, Configuration 3; Group 7, Configuration 4: Only the Work Packages for these Groups Sum of Work Packages Total Task-Hours (a) Total Elapsed Hours Work Package 1 54.45 22.95 Work Package 2 54.45 22.95 Work Package 3 54.45 22.95 Work Package 4 54.70 22.20 Work Package 5 54.70 22.20 Work Package 6 4.60 3.10 Work Package 7 4.60 3.10 Work Package 8 56.45 24.95 Work Package 9 56.45 24.95 Work Package 13 54.45 22.95 TOTAL FOR EACH AIRPLANE 449.30 192.30 (a) See the Work Package tables for details. Group 6, Configuration 1; Group 8, Configuration 1: Only the Work Packages for these Groups Sum of Work Packages Total Task-Hours (a) Total Elapsed Hours Work Package 1 54.45 22.95 Work Package 6 4.60 3.10 Work Package 7 4.60 3.10 Work Package 8 56.45 24.95 Work Package 9 56.45 24.95 Work Package 12 65.20 31.70 TOTAL FOR EACH AIRPLANE 241.75 110.75 (a) See the Work Package tables for details. Group 5, Configuration 1; Group 7, Configuration 1; Group 7, Configuration 2: Only the Work Packages for these Groups Sum of Work Packages Total Task-Hours (a) Total Elapsed Hours ### Page 42 July 03, 2008 767-28A0090 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 42 of 118 BOEING SERVICE BULLETIN 767-28A0090 ALERT ALERT Group 6, Configuration 2; Group 8, Configuration 2: Only the Work Packages for these Groups Sum of Work Packages Total Task-Hours (a) Total Elapsed Hours Work Package 1 54.45 22.95 Work Package 6 4.60 3.10 Work Package 7 4.60 3.10 Work Package 8 56.45 24.95 Work Package 9 56.45 24.95 Work Package 13 54.45 22.95 TOTAL FOR EACH AIRPLANE 231.00 102.00 (a) See the Work Package tables for details. Group 9: Only the Work Packages for these Groups Sum of Work Packages Total Task-Hours (a) Total Elapsed Hours Work Package 1 54.45 22.95 Work Package 2 54.45 22.95 Work Package 3 54.45 22.95 Work Package 4 54.70 22.20 Work Package 5 54.70 22.20 Work Package 6 4.60 3.10 Work Package 10 52.45 22.95 Work Package 11 52.45 22.95 Work Package 12 65.20 31.70 Work Package 13 54.45 22.95 TOTAL FOR EACH AIRPLANE 501.90 216.90 (a) See the Work Package tables for details. ### Page 43 July 03, 2008 767-28A0090 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 43 of 118 BOEING SERVICE BULLETIN 767-28A0090 ALERT ALERT H. Weight and Balance Changes I. Electrical Load Data Not changed. J. References 1. Existing Data: a. Engineering Change Memo PRR B13421-6 b. 767 Aircraft Maintenance Manual (AMM) 767 AMM 20-10-22, 767 AMM 20-10-23, 767 AMM 28-22-01 767 AMM 28-22-02, 767 AMM 28-22-11, 767 AMM 28-22-12, 767 AMM 28-25-02, 767 AMM 28-25-04, 767 AMM 28-26-01, 767 AMM 28-26-11, 767 AMM 28-31-03, 767 AMM 28-31-04, 767 AMM 28-31-06, and 767 AMM 28-31-05. c. Boeing Standard Operating Practices Manual SOPM 20-30-03 and SOPM 20-50-19. d. Boeing Standard Wiring Practices Manual SWPM 20-20-00. e. Boeing Structural Repair Manual 767-200 SRM 51-40-02 and 767-200 SRM 51-40-08. f. Boeing Structural Repair Manual 767-300 SRM 51-40-02 and 767-300 SRM 51-40-08. g. Boeing Structural Repair Manual 767-300F SRM 51-40-02 and 767-300F SRM 51-40-08. Airplane Change in Weight (Pounds) Change in Moment (Pound-Inches) 767-200 +4.4 +6028.0 767-300 +4.4 +6608.9 Work Package Change in Weight (Pounds) Change in Moment (Pound-Inches) Work Package 1 (a) +0.4 +465.1 Work Package 2 +0.4 +465.3 Work Package 3 +0.4 +465.3 Work Package 4 +0.4 +582.4 Work Package 5 +0.4 +582.4 Work Package 6 +0.4 +474.0 Work Package 7 +0.4 +474.0 Work Package 8 +0.4 +483.2 Work Package 9 +0.4 +483.2 Work Package 10 +0.4 +483.2 Work Package 11 +0.4 +483.2 Work Package 12 (a) +0.4 +466.6 (a) Values are for one individual MOV actuator listed in the work package. ### Page 44 July 03, 2008 767-28A0090 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 44 of 118 BOEING SERVICE BULLETIN 767-28A0090 ALERT ALERT h. Boeing Structural Repair Manual 767-400 SRM 51-40-02 and 767-400 SRM 51-40-08. i. Boeing Service Bulletin 767-28-0027 FUEL - DUMP - FUEL JETTISON SYSTEM INSTALLATION. j. Boeing Service bulletin 767-28-0034 FUEL - DISTRIBUTION - DUAL CROSSFEED VALVE INSTALLATION. 2. Data supplied with this Service Bulletin: None. 3. Installation Drawings Used in the Preparation of this Service Bulletin: K. Publications Affected L. Interchangeability and Intermixability of Parts Refer to Paragraph 2.C., Parts Necessary For Each Airplane, for interchangeability and intermixability information. Drawing Number Title 343T0002 Equipment - Engine Fuel Feed System 346T0004 APU Fuel Feed Syst - Wing 344T0002 Equipment Instl - Refueling System 340T0007 Fuel System Diagram Publication Chapter-Section 767 Airplane Maintenance Manual (AMM) 28-22, 28-25, 28-26, 28-31 767 Illustrated parts Catalog (IPC) 28-22, 28-25, 28-26, 28-31 767 Maintenance Planning Data (MPD) document 9 ### Page 45 July 03, 2008 767-28A0090 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 45 of 118 BOEING SERVICE BULLETIN 767-28A0090 ALERT ALERT 2. MATERIAL INFORMATION A. Material - Price and Availability Boeing can supply the kits shown in Paragraph 2.C., Parts Necessary For Each Airplane as shown below. If there is a limit to the quantity (QTY) of available kits, a supply sequence is given by Spares. More kits become available as shown in the Reorder Lead Time (ROLT). ROLT is calculated from the date Boeing gets the purchase order. The kits are subject to the terms and conditions of the Boeing standard purchase order acknowledgment. After the Unit Price date, new price and ROLT data is applicable. Prices are in United States dollars. Terms: Net 30 days. Reference this service bulletin and submit your purchase order by one of the methods that follow: 1. Order on-line via ATA Spec 2000 or Boeing Part Page 2. Fax to (206) 662-7145 3. Spares Customer Support - MC 36-65 Boeing Spares Department P.O. Box 3707 Seattle, Washington 98124-2207 USA B. Industry Support Information Boeing warranty remedies are not available for the configuration changes are given in this service bulletin. Kit Number Name Date QTY ROLT (Weeks) Unit Price thru (DEC 31/08) 015T1805-1 Top Kit - Bracket Installation Available 60 23 280.00 015T1805-1 Top Kit - Bracket Installation JAN 30/08 30 23 015T1805-1 Top Kit - Bracket Installation FEB 29/08 30 23 015T1805-1 Top Kit - Bracket Installation MAR 31/08 30 23 015T1805-1 Top Kit - Bracket Installation APR 29/08 30 23 015T1805-1 Top Kit - Bracket Installation MAY 29/08 30 23 015T1805-1 Top Kit - Bracket Installation JUL 07/08 30 23 015T1805-1 Top Kit - Bracket Installation JUL 30/08 10 23 015T1805-2 Top Kit - Bracket Install and Shim Install Available 25 30 716.00 ### Page 46 July 03, 2008 767-28A0090 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 46 of 118 BOEING SERVICE BULLETIN 767-28A0090 ALERT ALERT C. Parts Necessary For Each Airplane 1. Kits/Parts: NOTE: One top kit and the items shown in Paragraph 2.C.2., Parts and Materials Supplied by the Operator, are necessary for each airplane. The Top Kit is divided into Figure kits for each installation figure shown in the table below. To get the kits/parts shown below, refer to Paragraph 2.A., Material - Price and Availability. Figure Kit T o p K i t 1 92 02 12 2 015T1805-1 1 1 - - 015T1805-2 1 1 1 1 Kit 015T1805-1 - Group 1-8: New Part Number Figure Name Existing Part Number Notes 19 20 Qty 287T0015-723 1 1 WIRE SUPPORT ASSY 287T0015-7 BACR15BA5AD7C 2 2 RIVET, 100 DEG BACR15FV6KE7 2 2 RIVET Kit 015T1805-2 - Group 9: New Part Number Figure Name Existing Part Number Notes 19 20 21 22 Qty 287T0015-723 1 1 - - WIRE SUPPORT ASSY 287T0015-7 343T0002-29 - - 1 1 SHIM - SWEENEY MOV ADAPTER BACR15BA5AD7C 2 2 - - RIVET, 100 DEG BACR15FV6KE7 2 2 - - RIVET BACS12HM08AH1 0- - 4 4 S C R E W ### Page 47 July 03, 2008 767-28A0090 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 47 of 118 BOEING SERVICE BULLETIN 767-28A0090 ALERT ALERT 2. Parts and Materials Supplied by the Operator: 3. Parts Modified and Reidentified: None. 4. Parts Removed and Not Replaced: D. Parts Necessary to Change Spares None. E. Special Tooling - Price and Availability None. F. Special Tooling Necessary to do this Service Bulletin No special tools or equipment are necessary to do the change in this service bulletin. But, maintenance and overhaul tools in the manuals given in Paragraph 1.J., References, can be necessary. Examine operator tool supply to make sure all necessary tools are available. Part Number / Specification QTY Name Notes MA30A1001 (S343T003-66) (a) 11 MOTOR OPERATED VALVE ACTUATOR Replaces MA20A1001-1 (S343T003-39) PR-1440 33 oz. SEALANT, CATEGORY 2 (b) (c) BACJ40A20-4 6 BONDING JUMPER, 4 INCH (d) BACJ40A20-5 1 BONDING JUMPER, 5 INCH (d) BACJ40A20-6 4 BONDING JUMPER, 6 INCH (d) ALODINE 1201 4 oz. ALODINE CHEMICAL COATING, TYPE 2, CLASS A BMS 10-11 4 oz. TYPE 1 PRIMER (a) Supplier: ITT Aerospace Controls 28150 Industry Drive, Valencia, CA, 91355 USA (b) For fuel tank or areas exposed to fuel vapor. (c) In accordance with AMS-S-8802 (d) The new MOV actuator (MA30A1001) installation may require that a longer or shorter bonding jumper be installed to reach the bonding jumper mounting screw on either side of the MOV actuator. Existing Part Number Name QTY Notes 287T0015-7 WIRE SUPPORT ASSY 2 Bracket removed from each deflector located at the engine fuel shutoff MOV actuator. (a) Keep the part if there are other uses for it. ### Page 48 July 03, 2008 767-28A0090 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 48 of 118 BOEING SERVICE BULLETIN 767-28A0090 ALERT ALERT BLANK PAGE ### Page 49 July 03, 2008 767-28A0090 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 49 of 118 BOEING SERVICE BULLETIN 767-28A0090 ALERT ALERT 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: — Linear dimensions are in inches — Tolerance on linear dimensions, other than rivet and bolt edge margins, is plus or minus 0.03 inch. — Tolerance on rivet and bolt edge margin is plus or minus 0.05 inch — Hole dimensions for standard solid rivets are given in the 767 Structural Repair Manual, Chapter 51 — Torque limits to tighten nuts and bolts are given in the 767 Structural Repair Manual, Chapter 51. 5. For approved fastener and process material substitutions, refer to the 767 Structural Repair Manual, Chapter 51, Alternate fasteners are given in the 767 Structural Repair Manual Chapter 51 and Boeing Drawing 767 012W6100. 6. Refer to the Boeing Standard Wiring Practices Manuals 20-10-11 and 20-10-12 for the wire installation procedures. 7. If the length of fasteners specified in this service bulletin do not meet the installation standards, fasteners of the same specification, or an approved substitute, one grip length longer or shorter may be used. 8. A General Visual Inspection is defined as: A visual examination of an interior or exterior area, installation or assembly to detect obvious damage, failure or irregularity. This level of inspection is made from within touching distance unless otherwise specified. A mirror may be necessary to ensure visual access to all surfaces in the inspection area. This level of inspection is made under normal available lighting conditions such as daylight, hangar lighting, flashlight or drop-light and may require removal or opening of access panels or doors. Stands, ladders or platforms may be required to gain proximity to the area being checked. 9. 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 ### Page 50 July 03, 2008 767-28A0090 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 50 of 118 BOEING SERVICE BULLETIN 767-28A0090 ALERT ALERT 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. B. WORK INSTRUCTIONS Group 1-9: Work Package 1 - DEFUELING VALVE ACTUATOR (three units). 1. Get access to each MOV actuator. Refer to 767 AMM 28-26-11 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. However, if you decide to install the MOV actuator with part number MA30A1001 for reasons not related to this service bulletin, you must do the steps below so that the electrical bond for part number MA30A1001 is acceptable. 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. Refer to 767 AMM 28-26-11 as an accepted procedure. (2) Remove and keep the index plate as given in Figure 2. NOTE: Make an ink mark across the index plate, the adapter plate, and the airplane structure with a pen as a reference for installation alignment. (3) Rework the index plate as given in Figure 3. (4) 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) Prepare the adapter plate as given in Figure 5. 2) Temporarily put the index plate in position for installation as given in Figure 6. 3) Install the index plate. Refer to 767 AMM 28-26-01-824-142 as an accepted procedure. Refer to the adapter shaft alignment task, if the index plate cannot be visually aligned using the reference mark. NOTE: Do not install the MOV actuator according to the AMM task. The MOV actuator must be installed by Figure 7 to do steps that are not included in the AMM task. 4) Install the MOV actuator as given in Figure 7. Refer to 767 AMM 28-26-11 as an accepted procedure. 5) Test the operation of the MOV actuator. Refer to 767 AMM 28-26-11 as an accepted procedure. ### Page 51 July 03, 2008 767-28A0090 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 51 of 118 BOEING SERVICE BULLETIN 767-28A0090 ALERT ALERT (b) If the resistance is 1.5 milliohms or greater, the bond is not acceptable. 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 767 AMM 28-26-01 as an accepted procedure. 2) Remove the adapter plate and the adapter shaft. Refer to 767 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 767 AMM 28-26-01 as an accepted procedure. 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 0.5 milliohms, the bond is acceptable. Do the following steps: 1} Prepare the adapter plate as given in Figure 5. 2} Temporarily put the index plate in position for installation as given in Figure 6. 3} Install the index plate. Refer to 767 AMM 28-26-01-824-142 as an accepted procedure. Refer to the adapter shaft alignment task, if the index plate cannot be visually aligned using the reference mark. NOTE: Do not install the MOV actuator according to the AMM task. The MOV actuator must be installed by Figure 7 to do steps that are not included in the AMM task. 4} Install the MOV actuator as given in Figure 7. Refer to 767 AMM 28-26-11 as an accepted procedure. 5} Test the operation of the MOV actuator. Refer to 767 AMM 28-26-11 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.(4)(b)2) and rework the bond until it is acceptable. 6) Close access to the Motor Operated Valve. Refer to 767 AMM 28-26-01 as an accepted procedure. 3. Close access to the MOV actuator and do a function test of the MOV actuator. Refer to 767 AMM 28-26-11 as an accepted procedure. 4. Put the airplane in a serviceable condition. ### Page 52 July 03, 2008 767-28A0090 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 52 of 118 BOEING SERVICE BULLETIN 767-28A0090 ALERT ALERT Group 1-2, 5; Group 7, Configuration 1; Group 7, Configuration 3; Group 9: Work Package 2 - FUEL JETTISON TRANSFER VALVE ACTUATOR (left wing). 1. Get access to the MOV actuator. Refer to 767 AMM 28-31-04 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. However, if you decide to install the MOV actuator with part number MA30A1001 for reasons not related to this service bulletin, you must do the steps below so that the electrical bond for part number MA30A1001 is acceptable. 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. Refer to 767 AMM 28-31-04 as an accepted procedure. (2) Remove and keep the index plate as given in Figure 2. NOTE: Make an ink mark across the index plate, the adapter plate, and the airplane structure with a pen as a reference for installation alignment. (3) Rework the index plate as given in Figure 3. (4) 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) Prepare the adapter plate as given in Figure 5. 2) Temporarily put the index plate in position for installation as given in Figure 6. 3) Install the index plate. Refer to 767 AMM 28-31-06-824-083 as an accepted procedure. Refer to the adapter shaft alignment task, if the index plate cannot be visually aligned using the reference mark. NOTE: Do not install the MOV actuator according to the AMM task. The MOV actuator must be installed by Figure 7 to do steps that are not included in the AMM task. 4) Install the MOV actuator as given in Figure 7. Refer to 767 AMM 28-31-04 as an accepted procedure. 5) Test the operation of the MOV actuator. Refer to 767 AMM 28-31-04 as an accepted procedure. (b) If the resistance is 1.5 milliohms or greater, the bond is not acceptable. Fuel tank entry is necessary to make an acceptable bond. Do the following steps: ### Page 53 July 03, 2008 767-28A0090 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 53 of 118 BOEING SERVICE BULLETIN 767-28A0090 ALERT ALERT 1) Get access to the Motor Operated Valve (MOV). Refer to 767 AMM 28-31-06 as an accepted procedure. 2) Remove the adapter plate and the adapter shaft. Refer to 767 AMM 28-31-06 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 767 AMM 28-31-06 as an accepted procedure. 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 0.5 milliohms, the bond is acceptable. Do the following steps: 1} Prepare the adapter plate as given in Figure 5. 2} Temporarily put the index plate in position for installation as given in Figure 6. 3} Install the index plate. Refer to 767 AMM 28-31-06-824-083 as an accepted procedure. Refer to the adapter shaft alignment task, if the index plate cannot be visually aligned using the reference mark. NOTE: Do not install the MOV actuator according to the AMM task. The MOV actuator must be installed by Figure 7 to do steps that are not included in the AMM task. 4} Install the MOV actuator as given in Figure 7. Refer to 767 AMM 28-31-04 as an accepted procedure. 5} Test the operation of the MOV actuator. Refer to 767 AMM 28-31-04 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.(4)(b)2) and rework the bond until it is acceptable. 6) Close access to the Motor Operated Valve. Refer to 767 AMM 28-31-06 as an accepted procedure. 3. Close access to the MOV actuator and do a function test of the MOV actuator. Refer to 767 AMM 28-31-04 as an accepted procedure. 4. Put the airplane in a serviceable condition. Group 1-2, 5; Group 7, Configuration 1; Group 7, Configuration 3; Group 9: Work Package 3 - ### Page 54 July 03, 2008 767-28A0090 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 54 of 118 BOEING SERVICE BULLETIN 767-28A0090 ALERT ALERT FUEL JETTISON TRANSFER VALVE ACTUATOR (right wing). 1. Get access to the MOV actuator. Refer to 767 AMM 28-31-04 as an accepted procedure. 2. Read and record the part number of the 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. However, if you decide to install the MOV actuator with part number MA30A1001 for reasons not related to this service bulletin, you must do the steps below so that the electrical bond for part number MA30A1001 is acceptable. 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. Refer to 767 AMM 28-31-04 as an accepted procedure. (2) Remove and keep the index plate as given in Figure 2. NOTE: Make an ink mark across the index plate, the adapter plate, and the airplane structure with a pen as a reference for installation alignment. (3) Rework the index plate as given in Figure 3. (4) 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) Prepare the adapter plate as given in Figure 5. 2) Temporarily put the index plate in position for installation as given in Figure 6. 3) Install the index plate. Refer to 767 AMM 28-31-06-824-083 as an accepted procedure. Refer to the adapter shaft alignment task, if the index plate cannot be visually aligned using the reference mark. NOTE: Do not install the MOV actuator according to the AMM task. The MOV actuator must be installed by Figure 7 to do steps that are not included in the AMM task. 4) Install the MOV actuator as given in Figure 7. Refer to 767 AMM 28-31-04 as an accepted procedure. 5) Test the operation of the MOV actuator. Refer to 767 AMM 28-31-04 as an accepted procedure. (b) If the resistance is 1.5 milliohms or greater, the bond is not acceptable. 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 767 AMM 28-31-06 as an accepted procedure. ### Page 55 July 03, 2008 767-28A0090 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 55 of 118 BOEING SERVICE BULLETIN 767-28A0090 ALERT ALERT 2) Remove the adapter plate and the adapter shaft. Refer to 767 AMM 28-31-06 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 767 AMM 28-31-06 as an accepted procedure. 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 0.5 milliohms, the bond is acceptable. Do the following steps: 1} Prepare the adapter plate as given in Figure 5. 2} Temporarily put the index plate in position for installation as given in Figure 6. 3} Install the index plate. Refer to 767 AMM 28-31-06-824-083 as an accepted procedure. Refer to the adapter shaft alignment task, if the index plate cannot be visually aligned using the reference mark. NOTE: Do not install the MOV actuator according to the AMM task. The MOV actuator must be installed by Figure 7 to do steps that are not included in the AMM task. 4} Install the MOV actuator as given in Figure 7. Refer to 767 AMM 28-31-04 as an accepted procedure. 5} Test the operation of the MOV actuator. Refer to 767 AMM 28-31-04 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.(4)(b)2) and rework the bond until it is acceptable. 6) Close access to the Motor Operated Valve. Refer to 767 AMM 28-31-06 as an accepted procedure. 3. Close access to the MOV actuator and do a function test of the MOV actuator. Refer to 767 AMM 28-31-04 as an accepted procedure. 4. Put the airplane in a serviceable condition. Group 1-2, 5; Group 7, Configuration 1; Group 7, Configuration 3; Group 9: Work Package 4 - FUEL JETTISON NOZZLE VALVE ACTUATOR (left wing). 1. Get access to the MOV actuator. Refer to 767 AMM 28-31-05 as an accepted procedure. 2. Read and record the part number of the MOV actuator as given in Figure 11. ### Page 56 July 03, 2008 767-28A0090 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 56 of 118 BOEING SERVICE BULLETIN 767-28A0090 ALERT ALERT a. If the MOV actuator is not part number MA20A1001-1, the part is acceptable. No more work is necessary at this location. However, if you decide to install the MOV actuator with part number MA30A1001 for reasons not related to this service bulletin, you must do the steps below so that the electrical bond for part number MA30A1001 is acceptable. 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. Refer to 767 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 across the index plate, the adapter plate, and the airplane structure with a pen as a reference for installation alignment. (3) Rework the index plate as given in Figure 3. (4) 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) Prepare the adapter plate as given in Figure 5. 2) Temporarily put the index plate in position for installation as given in Figure 6. 3) Install the index plate. Refer to 767 AMM 28-31-03-824-060 as an accepted procedure. Refer to the adapter shaft alignment task, if the index plate cannot be visually aligned using the reference mark. NOTE: Do not install the MOV actuator according to the AMM task. The MOV actuator must be installed by Figure 7 to do steps that are not included in the AMM task. 4) Install the MOV actuator as given in Figure 7. Refer to 767 AMM 28-31-05 as an accepted procedure. 5) Test the operation of the MOV actuator. Refer to 767 AMM 28-31-05 as an accepted procedure. (b) If the resistance is 1.5 milliohms or greater, the bond is not acceptable. 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 767 AMM 28-31-03 as an accepted procedure. 2) Remove the adapter plate and the adapter shaft. Refer to 767 AMM 28-31-03 as an accepted procedure. 3) Clean the adapter plate and the airplane structure as given in Figure 8. ### Page 57 July 03, 2008 767-28A0090 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 57 of 118 BOEING SERVICE BULLETIN 767-28A0090 ALERT ALERT 4) Install the adapter plate and the adapter shaft. Refer to 767 AMM 28-31-03 as an accepted procedure. 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 0.5 milliohms, the bond is acceptable. Do the following steps: 1} Prepare the adapter plate as given in Figure 5. 2} Temporarily put the index plate in position for installation as given in Figure 6. 3} Install the index plate. Refer to 767 AMM 28-31-03-824-060 as an accepted procedure. Refer to the adapter shaft alignment task, if the index plate cannot be visually aligned using the reference mark. NOTE: Do not install the MOV actuator according to the AMM task. The MOV actuator must be installed by Figure 7 to do steps that are not included in the AMM task. 4} Install the MOV actuator as given in Figure 7. Refer to 767 AMM 28-31-05 as an accepted procedure. 5} Test the operation of the MOV actuator. Refer to 767 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.(4)(b)2) and rework the bond until it is acceptable. 6) Close access to the Motor Operated Valve. Refer to 767 AMM 28-31-03 as an accepted procedure. 3. Close access to the MOV actuator and do a function test of the MOV actuator. Refer to 767 AMM 28-31-05 as an accepted procedure. 4. Put the airplane in a serviceable condition. Group 1-2, 5; Group 7, Configuration 1; Group 7, Configuration 3; Group 9: Work Package 5 - FUEL JETTISON NOZZLE VALVE ACTUATOR (right wing). 1. Get access to the MOV actuator. Refer to 767 AMM 28-31-05 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. However, if you decide to install the MOV actuator with part number MA30A1001 for reasons not related to this service bulletin, you must do the steps below so that the electrical bond for part number MA30A1001 is acceptable. ### Page 58 July 03, 2008 767-28A0090 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 58 of 118 BOEING SERVICE BULLETIN 767-28A0090 ALERT ALERT 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. Refer to 767 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 across the index plate, the adapter plate, and the airplane structure with a pen as a reference for installation alignment. (3) Rework the index plate as given in Figure 3. (4) 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) Prepare the adapter plate as given in Figure 5. 2) Temporarily put the index plate in position for installation as given in Figure 6. 3) Install the index plate. Refer to 767 AMM 28-31-06-824-060 as an accepted procedure. Refer to the adapter shaft alignment task, if the index plate cannot be visually aligned using the reference mark. NOTE: Do not install the MOV actuator according to the AMM task. The MOV actuator must be installed by Figure 7 to do steps that are not included in the AMM task. 4) Install the MOV actuator as given in Figure 7. Refer to 767 AMM 28-31-05 as an accepted procedure. 5) Test the operation of the MOV actuator. Refer to 767 AMM 28-31-05 as an accepted procedure. (b) If the resistance is 1.5 milliohms or greater, the bond is not acceptable. 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 767 AMM 28-31-06 as an accepted procedure. 2) Remove the adapter plate and the adapter shaft. Refer to 767 AMM 28-31-06 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 767 AMM 28-31-06 as an accepted procedure. 5) Measure and record the electrical resistance of the bond from the adapter plate to the airplane structure as given in Figure 4. ### Page 59 July 03, 2008 767-28A0090 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 59 of 118 BOEING SERVICE BULLETIN 767-28A0090 ALERT ALERT {a} If the resistance is less than 0.5 milliohms, the bond is acceptable. Do the following steps: 1} Prepare the adapter plate as given in Figure 5. 2} Temporarily put the index plate in position for installation as given in Figure 6. 3} Install the index plate. Refer to 767 AMM 28-31-06-824-060 as an accepted procedure. Refer to the adapter shaft alignment task, if the index plate cannot be visually aligned using the reference mark. NOTE: Do not install the MOV actuator according to the AMM task. The MOV actuator must be installed by Figure 7 to do steps that are not included in the AMM task. 4} Install the MOV actuator as given in Figure 7. Refer to 767 AMM 28-31-05 as an accepted procedure. 5} Test the operation of the MOV actuator. Refer to 767 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.(4)(b)2) and rework the bond until it is acceptable. 6) Close access to the MOV. Refer to 767 AMM 28-31-06 as an accepted procedure. 3. Close access to the MOV actuator and do a function test of the MOV actuator. Refer to 767 AMM 28-31-05 as an accepted procedure. 4. Put the airplane in a serviceable condition. Group 1-9: Work Package 6 - APU FUEL SHUTOFF VALVE ACTUATOR. 1. Get access to the MOV Actuator. Refer to 767 AMM 28-25-02 as an accepted procedure. 2. Read and record the part number of the MOV actuator as given in Figure 13. a. If the MOV actuator is not part number MA20A1001-1, the part is acceptable. No more work is necessary at this location. However, if you decide to install the MOV actuator with part number MA30A1001 for reasons not related to this service bulletin, you must do the steps below so that the electrical bond for part number MA30A1001 is acceptable. 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. Refer to 767 AMM 28-25-02 as an accepted procedure. ### Page 60 July 03, 2008 767-28A0090 BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 60 of 118 BOEING SERVICE BULLETIN 767-28A0090 ALERT ALERT (2) Install the MOV actuator as given in Figure 18. Refer to 767 AMM 28-25-02 as an accepted procedure. (3) Test the operation of the MOV actuator. Refer to 767 AMM 28-25-02 as an accepted procedure. 3. Close access to the MOV actuator and do a function test of the MOV actuator. Refer to 767 AMM 28-25-02 as an accepted procedure. 4. Put the airplane in a serviceable condition. Group 5-8: Work Package 7 - APU FUEL ISOLATION VALVE ACTUATOR. 1. Get access to the MOV Actuator. Refer to 767 AMM 28-25-04 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. However, if you decide to install the MOV actuator with part number MA30A1001, you must do the steps below. 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. Refer to 767 AMM 28-25-04 as an accepted procedure. (2) Install the MOV actuator as given in Figure 18. Refer to 767 AMM 28-25-04 as an accepted procedure. (3) Test the operation of the MOV actuator. Refer to 767 AMM 28-25-04 as an accepted procedure. 3. Close access to the MOV actuator and do a function test of the MOV actuator. Refer to 767 AMM 28-25-04 as an accepted procedure. 4. Put the airplane in a serviceable condition. Group 1-8: Work Package 8 - ENGINE FUEL SHUTOFF VALVE ACTUATOR (left wing). 1. Get access to the MOV actuator. Refer to 767 AMM 28-22-11 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. However, if you decide to install the MOV actuator with part number MA30A1001 for reasons not related to this service bulletin, you must do the steps below so that the electrical bond for part number MA30A1001 is acceptable. 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: The text continues at https://openairdocs.org/service-documents/boeing/767-28a0090/file/f71b80f356f5.md?from=61 --- OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain, except the copies of manufacturers’ service documents, which belong to their rights holders.