### Commercial **Airplanes** 

# 767 Service Bulletin
**Number: 767-28A0090** Original Issue: July 03, 2008 Revision 2: September 02, 2010 ATA System: 2822 2825 2826 2831 **SUBJECT:**FUEL - Main and Center Tanks - Valve Actuator 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## BOEING PROPRIETARY, CONFIDENTIAL, AND/OR TRADE SECRET Copyright © 2008 The Boeing Company Unpublished Work - All Rights Reserved Boeing claims copyright in each page of this document only to the extent that the page contains copyrightable subject matter.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, 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BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 03, 2008 767-28A0090 Revision 2: September 02, 2010 1 of 119 2.0BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 03, 2008 767-28A0090 Revision 2: September 02, 2010 2 of 119 **BOEING SERVICE BULLETIN 767-28A0090**

BLANK PAGE**Table of Contents** Revision Transmittal Sheet............................................ 5 Summary...................................................... 7 1. PLANNING INFORMATION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11 A. Effectivity. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11 1. Airplanes. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11 2. Spares Affected. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20 B. Concurrent Requirements. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20 C. Reason. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20 D. Description. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21 E. Compliance. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23 F. Approval. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23 G. Manpower. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23 H. Weight and Balance Changes. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 40 I. Electrical Load Data. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 40 J. References. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 41 1. Existing Data:. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 41 2. Data supplied with this Service Bulletin:. . . . . . . . . . . . . . . . . . . . . . . . . . . 41 3. Installation Drawings Used in the Preparation of this Service Bulletin:. . . . . . . . . . . 41 K. Publications Affected. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 41 L. Interchangeability and Intermixability of Parts. . . . . . . . . . . . . . . . . . . . . . . . . . . 42 2. MATERIAL INFORMATION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 43 A. Material - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 43 B. Industry Support Information. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 44 C. Parts Necessary For Each Airplane. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 44 1. Kits/Parts:. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 44 2. Parts and Materials Supplied by the Operator:. . . . . . . . . . . . . . . . . . . . . . . . 45 3. Parts Modified and Reidentified:. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 46 4. Parts Removed and Not Replaced:. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 46 D. Parts Necessary to Change Spares. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 46 E. Special Tooling - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 46 F. Special Tooling Necessary to do this Service Bulletin. . . . . . . . . . . . . . . . . . . . . . . 46 3. ACCOMPLISHMENT INSTRUCTIONS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 47 A. GENERAL INFORMATION. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 47 B. WORK INSTRUCTIONS. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 48 FIGURE 1: INSPECT AND RECORD DEFUELING MOV ACTUATOR PART NUMBER. . . . . . . . 72 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. . . . . . . . . . . . . . . . . . 79 FIGURE 7: INSTALL THE MOV ACTUATOR. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 80 FIGURE 8: CLEAN ADAPTER PLATE AND AIRPLANE SURFACE. . . . . . . . . . . . . . . . . . . 84 FIGURE 9: INSPECT AND RECORD FUEL JETTISON TRANSFER MOV ACTUATOR PART NUMBER - LEFT. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 85

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 03, 2008 767-28A0090 Revision 2: September 02, 2010 3 of 119 **BOEING SERVICE BULLETIN 767-28A0090**FIGURE 10: INSPECT AND RECORD FUEL JETTISON TRANSFER MOV ACTUATOR PART NUMBER - RIGHT. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 87 FIGURE 11: INSPECT ANDRECORD FUEL JETTISON NOZZLE MOV ACTUATOR PART NUMBER - LEFT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 89 FIGURE 12: INSPECT AND RECORD FUEL JETTISON NOZZLE MOV ACTUATOR PART NUMBER - RIGHT. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 91 FIGURE 13: INSPECT AND RECORD APU SHUTOFF MOV ACTUATOR PART NUMBER. . . . . . 93 FIGURE 14: INSPECT AND RECORD APU ISOLATION MOV ACTUATOR PART NUMBER. . . . . 94 FIGURE 15: INSPECT AND RECORD ENGINE FUEL SHUTOFF MOV ACTUATOR PART NUMBER - LEFT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 95 FIGURE 16: INSPECT AND RECORD ENGINE FUEL SHUTOFF MOV ACTUATOR PART NUMBER - RIGHT. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 96 FIGURE 17:INSPECT AND RECORD DUAL FORWARD/AFT ENGINE FUEL CROSSFEED MOV ACTUATOR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 97 FIGURE 18: INSPECT AND RECORD SINGLE ENGINE FUEL CROSSFEED MOV ACTUATOR PART NUMBER - LEFT WING. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 99 FIGURE 19: INSTALL THE MOV ACTUATOR DIRECTLY TO THE MOTOR OPERATED VALVE . . 100 FIGURE 20: REMOVE BRACKET AND INSTALL NEW BRACKET ON ENGINE FUEL SHUTOFF MOV ACTUATOR DEFLECTOR - LEFT. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 104 FIGURE 21: REMOVE BRACKET AND INSTALL NEW BRACKET ON ENGINE FUEL SHUTOFF MOV ACTUATOR DEFLECTOR - RIGHT. . . . . . . . . . . . . . . . . . . . . . . . . . . . . 107 FIGURE 22: INSTALL THE SHIM AND FORWARD ENGINE FUEL CROSSFEED MOV ACTUATOR . 110 FIGURE 23: INSTALL THE SHIM AND AFT ENGINE FUEL CROSSFEED MOV ACTUATOR. . . . 115

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 03, 2008 767-28A0090 Revision 2: September 02, 2010 4 of 119 **BOEING SERVICE BULLETIN 767-28A0090**

### Commercial **Airplanes** 

# 767 Service Bulletin **Revision Transmittal Sheet Number: 767-28A0090**  Original Issue: July 03, 2008 Revision 2: September 02, 2010 ATA System: 2822 2825 2826 2831 **SUBJECT:**FUEL - Main and Center Tanks - Valve Actuator Inspection and Replacement This revision includes all pages of the service bulletin. **COMPLIANCE INFORMATION RELATED TO THIS REVISION**
Federal Aviation Administration (FAA) Airworthiness Directive AD 2009-22-13, is related to this service bulletin. More work is necessary on airplanes VF181-VF184 changed in accordance with the original issue or Revision 1 of this service bulletin. These airplanes must be in Group 1 since they are equipped with equipment numbers V00157, V00158, V00159 and V00160. **REASON FOR REVISION** This revision is sent to correct the effectivity, applicability, summary of hours in the Manpower tables, a number of typographical errors, and nomenclature in the figures. The changes are as follows: 1. In paragraph 1.A. Effectivity, moved VF181-VF184 from Group 4 to Group 1 to include equipment numbers V00157, V00158, V00159 and V00160. 2. In Summary, Manpower, corrected the total tasks hours and elapsed time in the summary table. 3. In paragraph 1.G, Manpower, corrected the applicability in the Work Package summary tables title: "Only the Work Packages for these Groups". 4. In Figure 7, Illustration, removed the applicability. Refer to the applicability in the Accomplishment Instructions. 5. In Figure 7, Illustration, removed the sentence "This figure has been deleted." This was a typographical error. 6. In Figure 13, Step Table, Step 1, QTY, revised the QTY to one (1). 7. In Figure 22, Illustration, removed the applicability. Refer to the applicability in the Accomplishment Instructions. 8. In Figure 23, Illustration, removed the applicability. Refer to the applicability in the Accomplishment Instructions. Vertical lines are put on the left edge of each page, except in Paragraph 1.A., Effectivity, to show the location of important changes.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 03, 2008 767-28A0090 Revision 2: September 02, 2010 5 of 119Pages with no vertical lines have no important changes. **REVISION HISTORY** July 03, 2008 Original Issue: April 01, 2010 Revision 1: September 02, 2010 Revision 2:

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 03, 2008 767-28A0090 Revision 2: September 02, 2010 6 of 119 **BOEING SERVICE BULLETIN 767-28A0090**

### Commercial **Airplanes** 

# 767 Service Bulletin **Summary Number: 767-28A0090**  Original Issue: July 03, 2008 Revision 2: September 02, 2010 ATA System: 2822 2825 2826 2831 **SUBJECT:**FUEL - Main and Center Tanks - Valve Actuator Inspection and Replacement **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 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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 03, 2008 767-28A0090 Revision 2: September 02, 2010 7 of 119**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. This may require a tank entry to rework the interface between the adapter and the airplane structure. — If you are required to install the MA30A1001 at the dual forward/aft engine fuel crossfeed valve actuator location, you must inspect for the "SWEENEY ENGR CORP" marking on the adapter. 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 Paragraph 1.A., Effectivity for the list of effected airplanes. **COMPLIANCE** Federal Aviation Administration (FAA) Airworthiness Directive 2009-22-13 is related to this service bulletin. Boeing recommends that this service bulletin be incorporated within 60 months from the effective date of FAA AD 2009-22-13. **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**  188.95 (a)(b) 437.45 (a)(b) Group 1.0 188.95 (a)(b) 437.45 (a)(b) Group 2.0 104.65 (a)(b) 227.15 (a)(b) Group 3.0 104.65 (a)(b) 227.15 (a)(b) Group 4.0 191.05 (a)(b) 440.05 (a)(b) Group 5.1 182.30 (a)(b) 429.30 (a)(b) Group 5.2 104.75 (a)(b) 229.75 (a)(b) Group 6.1 96.00 (a)(b) 219.00 (a)(b) Group 6.2 191.05 (a)(b) 440.05 (a)(b) Group 7.1 104.75 (a)(b) 229.75 (a)(b) Group 7.2

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 03, 2008 767-28A0090 Revision 2: September 02, 2010 8 of 119 **BOEING SERVICE BULLETIN 767-28A0090 Elapsed Hours**  **Total Task Hours Airplanes**  182.30 (a)(b) 429.30 (a)(b) Group 7.3 96.00 (a)(b) 219.00 (a)(b) Group 7.4 104.75 (a)(b) 229.75 (a)(b) Group 8.1 96.00 (a)(b) 219.00 (a)(b) Group 8.2 206.90 (a)(b) 485.90 (a)(b) Group 9.0 191.05 (a)(b) 440.05 (a)(b) Group 10.1 104.57 (a)(b) 229.75 (a)(b) Group 10.2 182.30 (a)(b) 429.30 (a)(b) Group 10.3 96.00 (a)(b) 219.00 (a)(b) Group 10.4 (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** Operator Supplied Parts. Refer to Paragraph 2.A., Material - Price and Availability.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 03, 2008 767-28A0090 Revision 2: September 02, 2010 9 of 119 **BOEING SERVICE BULLETIN 767-28A0090**BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 03, 2008 767-28A0090 Revision 2: September 02, 2010 10 of 119 **BOEING SERVICE BULLETIN 767-28A0090**

### Commercial **Airplanes** 

# 767 Service Bulletin
**Number: 767-28A0090** Original Issue: July 03, 2008 Revision 2: September 02, 2010 ATA System: 2822 2825 2826 2831 **SUBJECT:**FUEL - Main and Center Tanks - Valve Actuator Inspection and Replacement
**1. PLANNING INFORMATION A. Effectivity**  1. Airplanes Refer to Service Bulletin Index Document D624T001 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 B13421-6 for data about this change.
**DESCRIPTION CONFIGURATION**  **GROUP** 767-200/300/300F airplanes with the production dual crossfeed installation, and with the production fuel jettison installation. Requires an inspection to determine if the Sweeney adapters are present. - 1

767-200/300/300F airplanes with the production dual crossfeed installation, with the production fuel jettison installation, and with the Sweeney adapters installed during production. Requires an inspection to determine if the Sweeney adapters are present. - 2

767-200/300/300F airplanes with the production dual crossfeed installations, without the fuel jettison, without the APU isolation, with the center auxiliary tank defuel valve, and with the Sweeney adapters present. - 3

767-200/300/300F airplanes with the production dual crossfeed installation, without the fuel jettison installation, and without the production APU isolation installation. Requires an inspection to determine if the Sweeney adapters are present. - 4

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 03, 2008 767-28A0090 Revision 2: September 02, 2010 11 of 119**DESCRIPTION CONFIGURATION**  **GROUP** 767-200/300/300F airplanes effected by Boeing service bulletin 767-28-0034 to install the dual crossfeed, with the production jettison installation, and with the production APU isolation. Requires an inspection to determine if the Sweeney adapters are present. - 5

Made changes as given in Boeing service bulletin 767-28-0034. 1 Did not make changes as given in Boeing service bulletin 767-28-0034. 2
767-200/300/300F airplanes effected by Boeing service bulletin 767-28-0034 to install the dual crossfeed, without the production jettison installation, with the production APU isolation installation, and without the center auxiliary tank defuel valve. - 6

Made changes as given in Boeing service bulletin 767-28-0034. 1 Did not make changes as given in Boeing service bulletin 767-28-0034. 2
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, and with the production APU isolation installation. - 7

Made changes as given in Boeing service bulletin 767-28-0034, and made changes as given in Boeing service bulletin 767-28-0027. 1
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. 2

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. 3

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. 4

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 03, 2008 767-28A0090 Revision 2: September 02, 2010 12 of 119 **BOEING SERVICE BULLETIN 767-28A0090 DESCRIPTION**  **CONFIGURATION GROUP**  767-200/300/300F airplanes effected only by Boeing service bulletin 767-28-0034 to install the dual crossfeed, without the jettison installation, with the production APU isolation installation, and the center auxiliary tank defuel valve. - 8

Made changes as given in Boeing service bulletin 767-28-0034. 1 Did not make changes as given in Boeing service bulletin 767-28-0034. 2
767-400ER airplanes that require an inspection to determine if the Sweeney adapters are present. - 9
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, with the production APU isolation installation, and with the center auxiliary tank defuel valve. - 10

Made changes as given in Boeing service bulletin 767-28-0034, and made changes as given in Boeing service bulletin 767-28-0027. 1
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. 2

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. 3

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. 4

Airplane Models: 767-200, 767-300, 767-300F, 767-400ER**Group Variable Number** 8 VA001 - VA020 8 VA301 - VA315 8 VA501 - VA526 6 VA527 - VA530 8 VA701 - VA712 6 VA713 - VA719

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 03, 2008 767-28A0090 Revision 2: September 02, 2010 13 of 119 **BOEING SERVICE BULLETIN 767-28A0090 Group**  **Variable Number**8 VA801 - VA810 8 VB001 - VB002 8 VB051 - VB055 8 VB101 - VB125 8 VB201 - VB202 8 VB251 - VB253 8 VB281 - VB284 8 VB301 - VB302 8 VB321 - VB324 6 VB325 - VB332 8 VB371 - VB373 8 VB401 4 VB441 - VB444 8 VE001 - VE002 6 VE003 8 VE021 - VE023 8 VE041 - VE043 8 VE061 - VE069 8 VE083 - VE084 6 VE085 - VE086 8 VE101 - VE103 6 VE104 8 VE116 - VE117 6 VE118 8 VE121 - VE126 8 VE141 - VE143 6 VE144 - VE151 4 VE152 6 VE171 - VE172 7 VF001 - VF002 7 VF041 - VF042 7 VF051 5 VF061 - VF062

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 03, 2008 767-28A0090 Revision 2: September 02, 2010 14 of 119 **BOEING SERVICE BULLETIN 767-28A0090 Group**  **Variable Number**5 VF071 - VF072 5 VF091 - VF093 5 VF101 - VF102 5 VF161 2 VF162 2 VF171 - VF172 2 VF180 1 VF181 - VF184 2 VF251 8 VK001 - VK004 6 VK005 - VK011 4 VK012 - VK016 6 VK021 - VK022 8 VK031 - VK054 3 VK055 - VK056 8 VK081 - VK083 6 VK084 - VK099 4 VK100 - VK113 6 VK131 - VK133 6 VK141 - VK142 4 VK143 - VK148 6 VK161 4 VK162 - VK164 4 VK171 4 VK181 4 VK186 10 VL001 7 VL002 - VL006 10 VL011 2 VL701 - VL703 2 VL751 - VL755 2 VL806 - VL807 2 VL871 - VL873

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 03, 2008 767-28A0090 Revision 2: September 02, 2010 15 of 119 **BOEING SERVICE BULLETIN 767-28A0090 Group**  **Variable Number**2 VL891 - VL900 2 VL911 - VL914 2 VL931 - VL932 2 VL941 7 VN001 - VN015 5 VN016 - VN020 2 VN021 - VN041 7 VN051 - VN058 5 VN059 - VN064 7 VN081 - VN085 5 VN086 - VN092 2 VN093 - VN099 7 VN111 - VN115 5 VN116 - VN1242 VN125 - VN127 5 VN130 - VN132 2 VN133 - VN137 7 VN151 - VN155 5 VN156 - VN158 5 VN163 - VN168 7 VN171 - VN1732 VN174 7 VN191 - VN192 5 VN193 2 VN194 - VN198 7 VN211 - VN212 7 VN221 5 VN222 - VN2242 VN225 5 VN231 - VN234 6 VN241 2 VN242 - VN243 5 VN251 - VN260

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 03, 2008 767-28A0090 Revision 2: September 02, 2010 16 of 119 **BOEING SERVICE BULLETIN 767-28A0090 Group**  **Variable Number**2 VN261 - VN276 5 VN291 2 VN292 - VN293 5 VN301 - VN306 2 VN307 - VN314 5 VN371 - VN372 5 VN376 5 VN381 2 VN382 - VN388 2 VN421 - VN4272 VN436 5 VN471 - VN472 5 VN491 - VN4972 VN498 - VN513 5 VN531 - VN532 5 VN536 - VN537 5 VN541 - VN542 2 VN546 - VN547 5 VN551 2 VN556 - VN5572 VN561 - VN562 5 VN631 - VN6332 VN634 - VN638 5 VN651 - VN652 2 VN653 - VN658 5 VN671 - VN672 2 VN676 5 VN681 - VN6832 VN684 - VN691 5 VN731 2 VN732 5 VN751 - VN7532 VN791 - VN792

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 03, 2008 767-28A0090 Revision 2: September 02, 2010 17 of 119 **BOEING SERVICE BULLETIN 767-28A0090 Group**  **Variable Number**2 VN811 - VN8132 VN921 - VN922 2 VN931 - VN936 2 VN951 - VN9532 VN966 - VN972 9 VQ001 - VQ021 9 VQ071 - VQ0861 VR051 - VR060 1 VR081 1 VR084 1 VR086 - VR087 1 VR106 2 VR201 - VR209 1 VR210 - VR211 2 VR251 2 VR256 - VR257 1 VR258 - VR260 4 VR401 4 VR421 - VR4234 VR426 4 VR441 4 VR461 3 VR471 - VR472 2 VS051 - VS056 2 VS061 2 VS066 - VS070 2 VS073 - VS078 2 VS091 - VS102 1 VS103 - VS104 2 VS111 - VS113 2 VS131 - VS133 2 VS136 - VS137 2 VS176 - VS177

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 03, 2008 767-28A0090 Revision 2: September 02, 2010 18 of 119 **BOEING SERVICE BULLETIN 767-28A0090 Group**  **Variable Number**2 VS186 - VS187 2 VS196 - VS203 2 VS206 - VS208 2 VS211 2 VS216 - VS217 1 VS231 2 VS246 - VS248 2 VS261 - VS262 1 VS263 2 VS266 - VS274 2 VS291 1 VS292 - VS293 2 VS301 - VS302 1 VS303 2 VS306 - VS307 1 VS308 - VS311 2 VS316 2 VS321 - VS324 1 VS331 - VS333 1 VS336 - VS337 2 VS366 - VS367 2 VS381 - VS382 2 VS391 - VS392 2 VS401 1 VS426 - VS428 2 VS466 - VS470 1 VS471 - VS472 2 VS486 2 VS496 1 VS497 2 VS506 - VS507 1 VS526 1 VS546 - VS549

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 03, 2008 767-28A0090 Revision 2: September 02, 2010 19 of 119 **BOEING SERVICE BULLETIN 767-28A0090 Group**  **Variable Number**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 VS901 1 VT501 1 VT511 - VT512 1 VT521 - VT522 1 VV001 2 VW701 - VW7212 VW851 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 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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 03, 2008 767-28A0090 Revision 2: September 02, 2010 20 of 119 **BOEING SERVICE BULLETIN 767-28A0090**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 changed. Revision 1 is sent to correct group configuration assignments, to correct the accomplishment instructions and to correct AMM references. Revision 2 is sent to correct the effectivity, applicability, summary of hours in the Manpower tables, a number of typographical errors, and nomenclature in the figures. **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 forward/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. Revision 1 - More work is necessary on airplanes changed by the original issue. The airplanes with more work necessary were not assigned to the correct group configuration in the original issue of this service bulletin. This revision assigns the work packages to inspect and replace Motor Operated Valve (MOV) actuators located on the production jettison system to the following airplanes:
**Reason Additional Work -**  **Work Package(s) Original Group**  **(Original Release) New Group (Revi**  **sion 1) Variable No.**  (b) (a) 3 2 VN921 (b) (a) 3 2 VN922

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 03, 2008 767-28A0090 Revision 2: September 02, 2010 21 of 119 **BOEING SERVICE BULLETIN 767-28A0090 Reason**  **Additional Work - Work Package(s)**  **Original Group (Original Release)** **New Group (Revi sion 1)**  **Variable No.** (b) (a) 3 2 VN966 (b) (a) 3 2 VN967 (b) (a) 3 2 VN968 (b) (a) 3 2 VN969 (b) (a) 3 2 VN970 (b) (a) 3 2 VN971 (b) (a) 3 2 VN972 (a) Add Work Packages 2, 3, 4 and 5. (b) Airplane was not assigned to the correct group configuration in the original issue of this service bulletin. Airplanes were moved to a new group configuration when an inspection for the presence of Sweeney adapter plates is required. It is possible for any of the airplanes from line number 293 to 940 to have had Sweeney adapter plates installed during production. Boeing cannot specifically confirm all configurations from line number 293 to 940 due to the interchangeability of parts during production. Boeing recommends that affected airplanes be inspected for the presence of the Sweeney adapter plates by inspecting the part markings on the adapter plate at each of the Dual Forward/Aft Engine Crossfeed Valve Actuator locations. Refer to the description in paragraph 1.A.1, Group Configuration Table to determine which groups must inspect for the presence of the Sweeney adapter plates. Revision 2 - More work is necessary on airplanes VF181-VF184 changed in accordance with the original issue or Revision 1 of this service bulletin. These airplanes must be in Group 1 since they are equipped with equipment number V00175, V00158 and V00160. The work in this service bulletin is done in the maintenance zone(s) given below. **Group 1-2:**
**Affected Maintenance Zones Zone**  **Model** 133, 134, 136, 531, 532, 541, 551, 631, 632, 641, 651 767-200, 767-300, 767-300F

**Group 3, 10:**
**Affected Maintenance Zones Zone**  **Model** 133, 134, 136, 531, 532, 541, 551, 631, 632, 641, 651 767-300

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 03, 2008 767-28A0090 Revision 2: September 02, 2010 22 of 119 **BOEING SERVICE BULLETIN 767-28A0090 Group 4-8:** 
**Affected Maintenance Zones Zone**  **Model** 133, 134, 136, 531, 532, 541, 551, 631, 632, 641, 651 767-200, 767-300

**Group 9:**
**Affected Maintenance Zones Zone**  **Model** 133, 134, 136, 531, 532, 541, 551, 631, 632, 641, 651 767-400ER
**E. Compliance** Federal Aviation Administration (FAA) Airworthiness Directive 2009-22-13 is related to this service bulletin. Boeing recommends that this service bulletin be incorporated within 60 months from the effective date of FAA AD 2009-22-13. **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. This service bulletin has been approved by the FAA. In addition, the Manager of the FAA Seattle Aircraft Certification Office approves the inspection and the replacement, as required, of the motor operated valve actuators, as described in this service bulletin, as an alternative method of compliance to the inspection and the replacement, as required, of the motor operated valve actuators, as described in service bulletin 767-28A0090, dated July 3, 2008, required by paragraphs (g) and (h) of FAA AD 2009-22-13. All provisions of FAA AD 2009-22-13 that are not specifically referenced in the preceding sentence remain fully applicable and must be complied with. **G. Manpower** The table below shows an estimate of the task hours necessary to do this work 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:

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 03, 2008 767-28A0090 Revision 2: September 02, 2010 23 of 119 **BOEING SERVICE BULLETIN 767-28A0090**• 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.** V00108/V00109/V00123 1 V00159 2 V00160 3 V00157 4 V00158 5 V00096 6 V00097 7 V00025 8 V00026 9 V00025 10 V00026 11 V00388/V00389 12 V00024 13

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 03, 2008 767-28A0090 Revision 2: September 02, 2010 24 of 119 **BOEING SERVICE BULLETIN 767-28A0090 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 Install MOV ac- tuator 4.00 8.00 2 Close MOV ac- cess in fuel tank 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: July 03, 2008 767-28A0090 Revision 2: September 02, 2010 25 of 119 **BOEING SERVICE BULLETIN 767-28A0090 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 Install MOV ac- tuator 4.00 8.00 2 Close MOV ac- cess in fuel tank 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: July 03, 2008 767-28A0090 Revision 2: September 02, 2010 26 of 119 **BOEING SERVICE BULLETIN 767-28A0090 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 0.25 0.25 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 Install MOV ac- tuator 4.00 8.00 2 Close MOV ac- cess in fuel tank 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: July 03, 2008 767-28A0090 Revision 2: September 02, 2010 27 of 119 **BOEING SERVICE BULLETIN 767-28A0090 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 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 Install MOV ac- tuator 4.00 8.00 2 Close MOV ac- cess in fuel tank 0.10 0.10 1 Close MOV ac- tuator access 21.20 52.70 Total for Work Package

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 03, 2008 767-28A0090 Revision 2: September 02, 2010 28 of 119 **BOEING SERVICE BULLETIN 767-28A0090 Elapsed**  **Hours Task Hours**  **Number of Persons**  **Tasks 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 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 Install MOV ac- tuator 4.00 8.00 2 Close MOV ac- cess in fuel tank 0.10 0.10 1 Close MOV ac- tuator access 21.20 52.70 Total for Work Package

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 03, 2008 767-28A0090 Revision 2: September 02, 2010 29 of 119 **BOEING SERVICE BULLETIN 767-28A0090 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 0.50 0.50 1 Figure 13 0.25 0.25 1 Remove MOV actuator 0.25 0.25 1 Install MOV ac- tuator 0.50 0.50 1 Close MOV ac- tuator access 2.10 2.60 Total for 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 14 0.25 0.25 1 Remove MOV actuator 0.25 0.25 1 Install MOV ac- tuator 0.50 0.50 1 Close MOV ac- tuator access 2.10 2.60 Total for Work Package

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 03, 2008 767-28A0090 Revision 2: September 02, 2010 30 of 119 **BOEING SERVICE BULLETIN 767-28A0090 Elapsed**  **Hours Task Hours**  **Number of Persons**  **Tasks Work Package** 

0.50 1.00 2 Prepare Work Package 8 0.10 0.10 1 Open MOV ac- tuator access 0.25 0.25 1 Figure 15 0.25 0.25 1 Remove MOV actuator 2.00 2.00 1 Figure 20 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 Install MOV ac- tuator 4.00 8.00 2 Close MOV ac- cess in fuel tank 0.10 0.10 1 Close MOV ac- tuator access 23.95 54.45 Total for Work Package

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 03, 2008 767-28A0090 Revision 2: September 02, 2010 31 of 119 **BOEING SERVICE BULLETIN 767-28A0090 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 16 0.25 0.25 1 Remove MOV actuator 2.00 2.00 1 Figure 21 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 Install MOV ac- tuator 4.00 8.00 2 Close MOV ac- cess in fuel tank 0.10 0.10 1 Close MOV ac- tuator access 23.95 54.45 Total for Work Package

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 03, 2008 767-28A0090 Revision 2: September 02, 2010 32 of 119 **BOEING SERVICE BULLETIN 767-28A0090 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 15 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 Install MOV ac- tuator 4.00 8.00 2 Close MOV ac- cess in fuel tank 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: July 03, 2008 767-28A0090 Revision 2: September 02, 2010 33 of 119 **BOEING SERVICE BULLETIN 767-28A0090 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 16 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 Install MOV ac- tuator 4.00 8.00 2 Close MOV ac- cess in fuel tank 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: July 03, 2008 767-28A0090 Revision 2: September 02, 2010 34 of 119 **BOEING SERVICE BULLETIN 767-28A0090 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 17 0.25 0.25 1 Remove MOV actuator 2.00 2.00 1 Figure 2 (b) 2.00 2.00 1 Figure 3 (b) 1.00 1.00 1 Figure 4 (b) 8.00 32.0 4 MOV access/ fuel tank entry (a) 2.00 4.00 2 Remove adapter plate and adapter shaft (a)(b) 2.00 2.00 1 Figure 8. (a)(b) 2.00 4.00 2 Install adapter plate and adapter shaft (a)(b) 1.00 1.00 1 Figure 4 (a)(b) 3.00 3.00 1 Figure 5 (b) 1.00 1.00 1 Figure 6 (b) 1.00 1.00 1 Install index plate (b) 0.50 0.50 1 Install MOV ac- tuator (b)(c) 4.00 8.00 2 Close MOV ac- cess in fuel tank 0.10 0.10 1 Close MOV ac- tuator access 30.70 63.20 Total for Work Package

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 03, 2008 767-28A0090 Revision 2: September 02, 2010 35 of 119 **BOEING SERVICE BULLETIN 767-28A0090 Elapsed**  **Hours Task Hours**  **Number of Persons**  **Tasks Work Package** 

0.50 1.00 2 Prepare Work Package 13 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 Install MOV ac- tuator 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) 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 work package applies to the two MOV actuators. (c) 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

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 03, 2008 767-28A0090 Revision 2: September 02, 2010 36 of 119 **BOEING SERVICE BULLETIN 767-28A0090 Elapsed**  **Hours Task Hours**  **Number of Persons**  **Tasks Work Package** in the Accomplishment Instructions to do the work. See the Accomplishment Instructions for more detail. **Group 1-2: Only the Work Packages for these Groups**  **Total Elapsed Hours Total Task-Hours (a)**  **Sum of Work Packages** 21.95 52.45 Work Package 1 21.95 52.45 Work Package 2 21.95 52.45 Work Package 3 21.20 52.70 Work Package 4 21.20 52.70 Work Package 5 2.10 2.60 Work Package 6 23.95 54.45 Work Package 8 23.95 54.45 Work Package 9 30.70 63.20 Work Package 12 188.95 437.45 TOTAL FOR EACH AIRPLANE (a) See the work package tables for details. **Group 3-4: Only the Work Packages for these Groups**  **Total Elapsed Hours Total Task-Hours (a)**  **Sum of Work Packages** 21.95 52.45 Work Package 1 2.10 2.60 Work Package 6 23.95 54.45 Work Package 8 23.95 54.45 Work Package 9 30.70 63.20 Work Package 12 104.65 227.15 TOTAL FOR EACH AIRPLANE (a) See the work package tables for details. **Group 5, 7, 10, Configuration 1: Only the Work Packages for these Groups**  **Total Elapsed Hours Total Task-Hours (a)**  **Sum of Work Packages** 21.95 52.45 Work Package 1 21.95 52.45 Work Package 2

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 03, 2008 767-28A0090 Revision 2: September 02, 2010 37 of 119 **BOEING SERVICE BULLETIN 767-28A0090 Group 5, 7, 10, Configuration 1:**  **Only the Work Packages for these Groups Total Elapsed Hours**  **Total Task-Hours (a) Sum of Work Packages**  21.95 52.45 Work Package 3 21.20 52.70 Work Package 4 21.20 52.70 Work Package 5 2.10 2.60 Work Package 6 2.10 2.60 Work Package 7 23.95 54.45 Work Package 8 23.95 54.45 Work Package 9 30.70 63.20 Work Package 12 191.05 440.05 TOTAL FOR EACH AIRPLANE (a) See the work package tables for details. **Group 5, Configuration 2; Group 7, 10, Configuration 3: Only the Work Packages for these Groups**  **Total Elapsed Hours Total Task-Hours (a)**  **Sum of Work Packages** 21.95 52.45 Work Package 1 21.95 52.45 Work Package 2 21.95 52.45 Work Package 3 21.20 52.70 Work Package 4 21.20 52.70 Work Package 5 2.10 2.60 Work Package 6 2.10 2.60 Work Package 7 23.95 54.45 Work Package 8 23.95 54.45 Work Package 9 21.95 52.45 Work Package 13 182.30 429.30 TOTAL FOR EACH AIRPLANE (a) See the work package tables for details.**Group 6, Configuration 1; Group 7, Configuration 2; Group 8, Configuration 1; Group 10, Configu ration 2:**  **Only the Work Packages for these Groups Total Elapsed Hours**  **Total Task-Hours (a) Sum of Work Packages**  21.95 52.45 Work Package 1

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 03, 2008 767-28A0090 Revision 2: September 02, 2010 38 of 119 **BOEING SERVICE BULLETIN 767-28A0090 Group 6, Configuration 1; Group 7, Configuration 2; Group 8, Configuration 1; Group 10, Configu**  **ration 2: Only the Work Packages for these Groups**  **Total Elapsed Hours Total Task-Hours (a)**  **Sum of Work Packages** 2.10 2.60 Work Package 6 2.10 2.60 Work Package 7 23.95 54.45 Work Package 8 23.95 54.45 Work Package 9 30.70 63.20 Work Package 12 104.75 229.75 TOTAL FOR EACH AIRPLANE (a) See the work package tables for details.**Group 6, Configuration 2; Group 7, Configuration 4; Group 8, Configuration 2; Group 10, Configu ration 4:**  **Only the Work Packages for these Groups Total Elapsed Hours**  **Total Task-Hours (a) Sum of Work Packages**  21.95 52.45 Work Package 1 2.10 2.60 Work Package 6 2.10 2.60 Work Package 7 23.95 54.45 Work Package 8 23.95 54.45 Work Package 9 21.95 52.45 Work Package 13 96.00 219.00 TOTAL FOR EACH AIRPLANE (a) See the work package tables for details. **Group 9: Only the Work Packages for these Groups**  **Total Elapsed Hours Total Task-Hours (a)**  **Sum of Work Packages** 21.95 52.45 Work Package 1 21.95 52.45 Work Package 2 21.95 52.45 Work Package 3 21.20 52.70 Work Package 4 21.20 52.70 Work Package 5 2.10 2.60 Work Package 6 21.95 52.45 Work Package 10 21.95 52.45 Work Package 11

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 03, 2008 767-28A0090 Revision 2: September 02, 2010 39 of 119 **BOEING SERVICE BULLETIN 767-28A0090 Group 9:**  **Only the Work Packages for these Groups Total Elapsed Hours**  **Total Task-Hours (a) Sum of Work Packages**  30.70 63.20 Work Package 12 21.95 52.45 Work Package 13 206.90 485.90 TOTAL FOR EACH AIRPLANE (a) See the work package tables for details. **H. Weight and Balance Changes Change in Moment**  **(Pound-Inches) Change in Weight**  **(Pounds) Airplane** 

+6028.0 +4.4 767-200 +6608.9 +4.4 767-300 **Change in Moment (Pound-Inches)**  **Change in Weight (Pounds)**  **Work Package**

+465.1 +0.4 Work Package 1 (a) +465.3 +0.4 Work Package 2 +465.3 +0.4 Work Package 3 +582.4 +0.4 Work Package 4 +582.4 +0.4 Work Package 5 +474.0 +0.4 Work Package 6 +474.0 +0.4 Work Package 7 +483.2 +0.4 Work Package 8 +483.2 +0.4 Work Package 9 +483.2 +0.4 Work Package 10 +483.2 +0.4 Work Package 11 +466.6 +0.4 Work Package 12 (a) (a) Values are for one individual MOV actuator listed in the work package.
**I. Electrical Load Data** Not changed.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 03, 2008 767-28A0090 Revision 2: September 02, 2010 40 of 119 **BOEING SERVICE BULLETIN 767-28A0090 J. References**  1. Existing Data: a. Engineering Change Memo PRR B12900-253, PRR B13421-6 b. Standard Overhaul Practices Manual (SOPM) 20-30-03, 20-41-02, 20-43-03 c. Standard Wiring Practices Manual (SWPM) 20-20-00, 20-20-00 d. 767 Aircraft Maintenance Manual (AMM) 28-22-01, 28-22-02, 28-22-11, 28-22-12, 28-25-02, 28-25-04, 28-26-01, 28-26-11, 28-31-03, 28-31-04, 28-31-05, 28-31-06 e. Boeing Structural Repair Manual 767-200 SRM 51-40-02, 767-200 SRM 51-40-08 f. Boeing Structural Repair Manual 767-300 SRM 51-40-02, 767-300 SRM 51-40-08 g. Boeing Structural Repair Manual 767-300F SRM 51-40-02, 767-300F SRM 51-40-08 h. Boeing Structural Repair Manual 767-400 SRM 51-40-02, 767-400 SRM 51-40-08 i. FAA Airworthiness Directive 2009-22-13 j. Boeing Service Bulletin 767-28-0027 FUEL - DUMP - FUEL JETTISON SYSTEM INSTALLATION k. 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:
**Title Drawing Number**  Equipment - Engine Fuel Feed System 343T0002 APU Fuel Feed Syst - Wing 346T0004 Equipment Instl - Refueling System 344T0002 Fuel System Diagram 340T0007

**K. Publications Affected** 1. Publications: **Chapter-Section Publication**  28-22, 28-25, 28-26, 28-31 767 Airplane Maintenance Manual (AMM) 28-22, 28-25, 28-26, 28-31 767 Illustrated parts Catalog (IPC)

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 03, 2008 767-28A0090 Revision 2: September 02, 2010 41 of 119 **BOEING SERVICE BULLETIN 767-28A0090 Chapter-Section**  **Publication** 9 767 Maintenance Planning Data (MPD) document 2. Damage Tolerance Based Structural Inspections: Boeing has evaluated this service bulletin for effects on Fatigue Critical Structure (FCS) and for changes to Damage Tolerance Inspections (DTI) required in the Maintenance Program. This service bulletin 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: July 03, 2008 767-28A0090 Revision 2: September 02, 2010 42 of 119 **BOEING SERVICE BULLETIN 767-28A0090 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.
**Unit Price thru (DEC 31/08)**  **ROLT (Weeks)**  **QTY Date**  **Name Kit Number** 

280.00 23 60 Available Top Kit - Bracket Installa- tion 015T1805-1

23 30 JAN 30/08 Top Kit - Bracket Installa- tion 015T1805-1

23 30 FEB 29/08 Top Kit - Bracket Installa- tion 015T1805-1

23 30 MAR 31/08 Top Kit - Bracket Installa- tion 015T1805-1

23 30 APR 29/08 Top Kit - Bracket Installa- tion 015T1805-1

23 30 MAY 29/08 Top Kit - Bracket Installa- tion 015T1805-1

23 30 JUL 07/08 Top Kit - Bracket Installa- tion 015T1805-1

23 10 JUL 30/08 Top Kit - Bracket Installa- tion 015T1805-1

716.00 30 225 Available Top Kit - Bracket Install and Shim Install 015T1805-2
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

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 03, 2008 767-28A0090 Revision 2: September 02, 2010 43 of 119 **BOEING SERVICE BULLETIN 767-28A0090 B. Industry Support Information**  Boeing warranty remedies are not available for the configuration changes are given in this service bulletin. **C. Parts Necessary For Each Airplane** 1. Kits/Parts: **NOTE:**Parts are duplicated between kits. Only one type of kit is needed for each airplane. If the Sweeney adapter is present then use the kit 015T1805-2. If not present then use the kit 015T1805-1. To get the kits/parts shown below, refer to Paragraph 2.A., Material - Price and Availability. **NOTE:**One top kit and the items shown in Paragraph 2.C.2., Parts and Materials Supplied by the Operator, are necessary for each airplane. The Top Kit is divided into Figure kits for each installation figure shown in the table below. To get the kits/parts shown below, refer to Paragraph 2.A., Material - Price and Availability. **Figure Kit 23**  **22 21**  **20 Top Kit** 

- - 1 1 015T1805-1 1 1 1 1 015T1805-2 **Group 6-8:**
**KIT 015T1805-1**

**NOTES Existing Part**  **Number Name**  **Figure**

**New Part Number 21**  **20 QTY** WIRE SUPPORT ASSY 1 1 287T0015-723
RIVET, 100 DEG 2 2 BACR15BA5AD7C RIVET 2 2 BACR15FV6KE7

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 03, 2008 767-28A0090 Revision 2: September 02, 2010 44 of 119 **BOEING SERVICE BULLETIN 767-28A0090 Group 1-5, 9-10:** 
**KIT 015T1805-2**

**NOTES Existing Part**  **Number Name**  **Figure**

**New Part Number 23**  **22 21**  **20 QTY**  WIRE SUPPORT ASSY 1 1 287T0015-723
SHIM - SWEENEY MOV ADAPTER 1 1 343T0002-29
RIVET, 100 DEG 2 2 BACR15BA5AD7C RIVET 2 2 BACR15FV6KE7 SCREW 4 4 BACS12HM08AH10

2. Parts and Materials Supplied by the Operator:
**Notes Name**  **QTY Part Number /**  **Specification** Replaces MA20A1001-1 (S343T003-39)MOTOR OPERATED VALVE ACTUATOR 11 MA30A1001 (S343T003-66) (a) (b)(e) SEALANT, CATEGORY 2 22 oz. BMS 5-45 (c) SEALANT, LOW DENSITY 22 oz. BMS 5-142 COLORED CHEMICAL CONVERSION COATING 4 oz. BAC5626, TYPE 2 CLASS A OR D PRIMER 4 oz. BMS 10-11, TYPE 1 (d) BONDING JUMPER, 4 INCH (OP- TIONAL) 11 BACJ40A20-4 (d) BONDING JUMPER, 5 INCH (OP- TIONAL) 11 BACJ40A20-5 (d) BONDING JUMPER, 6 INCH (OP- TIONAL) 11 BACJ40A20-6 (a) Supplier: ITT Aerospace Controls 28150 Industry Drive, Valencia, CA, 91355 USA (b) For fuel tank or areas exposed to fuel vapor. (c) BMS 5-45 or BMS 5-95 can be used as a substitute for BMS 5-142 for the application of cap seal on the MOV actuator bonding jumper locations as described in the work packages of this service bulletin. (d) Optional: 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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 03, 2008 767-28A0090 Revision 2: September 02, 2010 45 of 119 **BOEING SERVICE BULLETIN 767-28A0090 Notes**  **Name QTY**  **Part Number / Specification**  (e) BMS 5-95 Pressure and Environmental Sealant-Chromate Type is optional (BAC5117- 6).
3. Parts Modified and Reidentified: None. 4. Parts Removed and Not Replaced:
**Notes QTY**  **Name Existing Part**  **Number** Bracket removed from each deflector located at the engine fuel shutoff MOV actuator. 2 WIRE SUPPORT ASSY 287T0015-7

**D. Parts Necessary to Change Spares** None. **E. Special Tooling - Price and Availability** None. **F. Special Tooling Necessary to do this Service Bulletin** No special tools or equipment are necessary to do the change in this service bulletin. But, maintenance and overhaul tools in the manuals given in Paragraph 1.J., References, can be necessary. Examine operator tool supply to make sure all necessary tools are available.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 03, 2008 767-28A0090 Revision 2: September 02, 2010 46 of 119 **BOEING SERVICE BULLETIN 767-28A0090 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. 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. 9. For approved interchangeability of MOV actuators, refer to the Interchangeable Parts 767 Motor Operated Valves (MOV) Boeing Drawing 343T0014. 10. All AMM references apply to the procedures for MOV actuator part number MA20A2027 and MA30A1001.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 03, 2008 767-28A0090 Revision 2: September 02, 2010 47 of 119 **BOEING SERVICE BULLETIN 767-28A0090 B. WORK INSTRUCTIONS**  **Group 1-10: Work Package 1 - DEFUELING VALVE ACTUATOR (V00108/V00109/V00123)**  1. Get access to each MOV actuator. Refer to 767 AMM 28-26-11 as an accepted procedure. **NOTE:**Most airplanes only have equipment numbers V00108 and V00109 installed. This work package always applies to equipment numbers V00108 and V00109. This work package also applies to equipment number V00123, if equipment number V00123 is installed on the airplane. If equipment number V00123 is not installed on the airplane, then no work is required for equipment number V00123. 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. (1) Close access to each MOV actuator. Refer to 767 AMM 28-26-11 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 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) Prepare the adapter plate as given in Figure 5. (5) Measure and record the electrical bond resistance 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:

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 03, 2008 767-28A0090 Revision 2: September 02, 2010 48 of 119 **BOEING SERVICE BULLETIN 767-28A0090**1) Temporarily put the index plane in position for installation as given in Figure 6. 2) Install the index plate. Refer to 767 AMM 28-26-01 as an accepted procedure. 3) Install the MOV actuator as given in Figure 7. Refer to 767 AMM 28-26-11 as an accepted procedure for the install of the MOV actuator body. 4) Do an operational test of the MOV. Refer to 767 AMM 28-26-11 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 28-26-01 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) Prepare the adapter plate as given in Figure 5. 6) Measure and record the electrical bond resistance 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 plane in position for installation as given in Figure 6. {2} Install the index plate. Refer to 767 AMM 28-26-01 as an accepted procedure. {3} Install the MOV actuator as given in Figure 7. Refer to 767 AMM 28-26-11 as an accepted procedure for the install of the MOV actuator body. {4} Do an operational test of the MOV. 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:

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 03, 2008 767-28A0090 Revision 2: September 02, 2010 49 of 119 **BOEING SERVICE BULLETIN 767-28A0090**{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 767 AMM 28-26-01 as an accepted procedure. 3. Close access to the MOV actuator. Refer to 767 AMM 28-26-11 as an accepted procedure. 4. Put the airplane in a serviceable condition or do another work package. **Group 1-2, 5; Group 7, Configuration 1, 3; Group 9; Group 10, Configuration 1, 3: Work Package 2 - FUEL JETTISON TRANSFER VALVE ACTUATOR - Left (V00159)**  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. (1) Close access to the MOV actuator. Refer to 767 AMM 28-31-04 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 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) Prepare the adapter plate as given in Figure 5. (5) Measure and record the electrical bond resistance 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:

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 03, 2008 767-28A0090 Revision 2: September 02, 2010 50 of 119 **BOEING SERVICE BULLETIN 767-28A0090**1) Temporarily put the index plate in position for installation as given in Figure 6. 2) Install the index plate. Refer to 767 AMM 28-31-06 as an accepted procedure. 3) Install the MOV actuator as given in Figure 7. Refer to 767 AMM 28-31-04 as an accepted procedure for the install of the MOV actuator body. 4) Do an operational test of the MOV. 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. 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) Prepare the adapter plate as given in Figure 5. 6) Measure and record the electrical bond resistance 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 767 AMM 28-31-06 as an accepted procedure. {3} Install the MOV actuator as given in Figure 7. Refer to 767 AMM 28-31-04 as an accepted procedure for the install of the MOV actuator body. {4} Do an operational test of the MOV. 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:

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 03, 2008 767-28A0090 Revision 2: September 02, 2010 51 of 119 **BOEING SERVICE BULLETIN 767-28A0090**{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 767 AMM 28-31-06 as an accepted procedure. 3. Close access to the MOV actuator. Refer to 767 AMM 28-31-04 as an accepted procedure. 4. Put the airplane in a serviceable condition or do another work package. **Group 1-2, 5; Group 7, Configuration 1, 3; Group 9; Group 10, Configuration 1, 3: Work Package 3 - FUEL JETTISON TRANSFER VALVE ACTUATOR - Right (V00160)**  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. (1) Close access to the MOV actuator. Refer to 767 AMM 28-31-04 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 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) Prepare the adapter plate as given in Figure 5. (5) Measure and record the electrical bond resistance 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:

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 03, 2008 767-28A0090 Revision 2: September 02, 2010 52 of 119 **BOEING SERVICE BULLETIN 767-28A0090**1) Temporarily put the index plate in position for installation as given in Figure 6. 2) Install the index plate. Refer to 767 AMM 28-31-06 as an accepted procedure. 3) Install the MOV actuator as given in Figure 7. Refer to 767 AMM 28-31-04 as an accepted procedure for the install of the MOV actuator body. 4) Do an operational test of the MOV. 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. 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) Prepare the adapter plate as given in Figure 5. 6) Measure and record the electrical bond resistance 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 767 AMM 28-31-06 as an accepted procedure. {3} Install the MOV actuator as given in Figure 7. Refer to 767 AMM 28-31-04 as an accepted procedure for the install of the MOV actuator body. {4} Do an operational test of the MOV. 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:

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 03, 2008 767-28A0090 Revision 2: September 02, 2010 53 of 119 **BOEING SERVICE BULLETIN 767-28A0090**{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 767 AMM 28-31-06 as an accepted procedure. 3. Close access to the MOV actuator. Refer to 767 AMM 28-31-04 as an accepted procedure. 4. Put the airplane in a serviceable condition or do another work package. **Group 1-2, 5; Group 7, Configuration 1, 3; Group 9; Group 10, Configuration 1, 3: Work Package 4 - FUEL JETTISON NOZZLE VALVE ACTUATOR - Left (V00157)**  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. 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 the MOV actuator. Refer to 767 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 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) Prepare the adapter plate as given in Figure 5. (5) Measure and record the electrical bond resistance 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:

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 03, 2008 767-28A0090 Revision 2: September 02, 2010 54 of 119 **BOEING SERVICE BULLETIN 767-28A0090**1) Temporarily put the index plate in position for installation as given in Figure 6. 2) Install the index plate. Refer to 767 AMM 28-31-03 as an accepted procedure. 3) Install the MOV actuator as given in Figure 7. Refer to 767 AMM 28-31-05 as an accepted procedure for the install of the MOV actuator body. 4) Do an operational test of the MOV. 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. 4) Install the adapter plate and the adapter shaft. Refer to 767 AMM 28-31-03 as an accepted procedure. 5) Prepare the adapter plate as given in Figure 5. 6) Measure and record the electrical bond resistance 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 767 AMM 28-31-03 as an accepted procedure. {3} Install the MOV actuator as given in Figure 7. Refer to 767 AMM 28-31-05 as an accepted procedure for the install of the MOV actuator body. {4} Do an operational test of the MOV. 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:

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 03, 2008 767-28A0090 Revision 2: September 02, 2010 55 of 119 **BOEING SERVICE BULLETIN 767-28A0090**{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 767 AMM 28-31-03 as an accepted procedure. 3. Close access to the MOV actuator. Refer to 767 AMM 28-31-05 as an accepted procedure. 4. Put the airplane in a serviceable condition or do another work package. **Group 1-2, 5; Group 7, Configuration 1, 3; Group 9; Group 10, Configuration 1, 3: Work Package 5 - FUEL JETTISON NOZZLE VALVE ACTUATOR - Right (V00158)**  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. (1) Close access to the MOV actuator. Refer to 767 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 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) Prepare the adapter plate as given in Figure 5. (5) Measure and record the electrical bond resistance 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:

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 03, 2008 767-28A0090 Revision 2: September 02, 2010 56 of 119 **BOEING SERVICE BULLETIN 767-28A0090**1) Temporarily put the index plate in position for installation as given in Figure 6. 2) Install the index plate. Refer to 767 AMM 28-31-03 as an accepted procedure. 3) Install the MOV actuator as given in Figure 7. Refer to 767 AMM 28-31-05 as an accepted procedure for the install of the MOV actuator body. 4) Do an operational test of the MOV. 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. 4) Install the adapter plate and the adapter shaft. Refer to 767 AMM 28-31-03 as an accepted procedure. 5) Prepare the adapter plate as given in Figure 5. 6) Measure and record the electrical bond resistance 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 767 AMM 28-31-03 as an accepted procedure. {3} Install the MOV actuator as given in Figure 7. Refer to 767 AMM 28-31-05 as an accepted procedure for the install of the MOV actuator body. {4} Do an operational test of the MOV. 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:

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 03, 2008 767-28A0090 Revision 2: September 02, 2010 57 of 119 **BOEING SERVICE BULLETIN 767-28A0090**{1} Return to step 2.b.(5)(b)2) and rework the bond until it is acceptable. 7) Close access to the MOV. Refer to 767 AMM 28-31-03 as an accepted procedure. 3. Close access to the MOV actuator. Refer to 767 AMM 28-31-05 as an accepted procedure. 4. Put the airplane in a serviceable condition or do another work package. **Group 1-10: Work Package 6 - APU FUEL SHUTOFF VALVE ACTUATOR (V00096)**  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. (1) Close access to the MOV actuator. Refer to 767 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: (1) Remove and discard the MOV actuator , and remove and keep the bonding jumper. Refer to 767 AMM 28-25-02 as an accepted procedure. (2) Install the MOV actuator as given in Figure 19. Refer to 767 AMM 28-25-02 as an accepted procedure for the install of the MOV actuator body. (3) Do an operational test of the MOV. Refer to 767 AMM 28-25-02 as an accepted procedure. 3. Close access to the MOV actuator. Refer to 767 AMM 28-25-02 as an accepted procedure. 4. Put the airplane in a serviceable condition or do another work package. **Group 5-8, 10: Work Package 7 - APU FUEL ISOLATION VALVE ACTUATOR (V00097)**  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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 03, 2008 767-28A0090 Revision 2: September 02, 2010 58 of 119 **BOEING SERVICE BULLETIN 767-28A0090**(1) Close access to the MOV actuator. Refer to 767 AMM 28-25-04 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 767 AMM 28-25-04 as an accepted procedure. (2) Install the MOV actuator as given in Figure 19. Refer to 767 AMM 28-25-04 as an accepted procedure for the install of the MOV actuator body. (3) Do an operational test of the MOV. Refer to 767 AMM 28-25-04 as an accepted procedure. 3. Close access to the MOV actuator. Refer to 767 AMM 28-25-04 as an accepted procedure. 4. Put the airplane in a serviceable condition or do another work package. **Group 1-8, 10: Work Package 8 - ENGINE FUEL SHUTOFF VALVE ACTUATOR (V00025)**  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. (1) Remove the wire bracket and install the new wire bracket on the engine fuel shut off MOV actuator deflector as given in Figure 20. **NOTE:**This change must be made to accomodate any future install of part number MA30A1001 or an MOV actuator of similar design. (2) No more work is necessary. Close access to the MOV actuator. Refer to 767 AMM 28-22-11 as an accepted procedure. (3) 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 767 AMM 28-22-11 as an accepted procedure. (2) Remove the wire bracket and install the new wire bracket on the engine fuel shutoff MOV actuator deflector as given in Figure 20. (3) 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.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 03, 2008 767-28A0090 Revision 2: September 02, 2010 59 of 119 **BOEING SERVICE BULLETIN 767-28A0090**(4) Rework the index plate as given in Figure 3. (5) Prepare the adapter plate as given in Figure 5. (6) Measure and record the electrical bond resistance 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 767 AMM 28-22-01 as an accepted procedure. 3) Install the MOV actuator as given in Figure 7. Refer to 767 AMM 28-22-11 as an accepted procedure for the install of the MOV actuator body. 4) Do an operational test of the MOV. Refer to 767 AMM 28-22-11 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 28-22-01 as an accepted procedure. 2) Remove the adapter plate and the adapter shaft. Refer to 767 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 767 AMM 28-22-01 as an accepted procedure. 5) Prepare the adapter plate as given in Figure 5. 6) Measure and record the electrical bond resistance 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:

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 03, 2008 767-28A0090 Revision 2: September 02, 2010 60 of 119 **BOEING SERVICE BULLETIN 767-28A0090**{1} Temporarily put the index plate in position for installation as given in Figure 6. {2} Install the index plate. Refer to 767 AMM 28-22-01 as an accepted procedure. {3} Install the MOV actuator as given in Figure 7. Refer to 767 AMM 28-22-11 as an accepted procedure for the install of the MOV actuator body. {4} Do an operational test of the MOV. Refer to 767 AMM 28-22-11 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.(6)(b)2) and rework the bond until it is acceptable. 7) Close access to the Motor Operated Valve. Refer to 767 AMM 28-22-01 as an accepted procedure. 3. Close access to the MOV actuator. Refer to 767 AMM 28-22-11 as an accepted procedure. 4. Put the airplane in a serviceable condition or do another work package. **Group 1-8, 10: Work Package 9 - ENGINE FUEL SHUTOFF VALVE ACTUATOR (V00026)**  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 16. a. If the MOV actuator is not part number MA20A1001-1, the part is acceptable. (1) Remove the wire bracket and install the new wire bracket on the engine fuel shut off MOV actuator deflector as given in Figure 21. **NOTE:**This change must be made to accomodate any future install of part number MA30A1001 or an MOV actuator of similar design. (2) No more work is necessary. Close access to the MOV actuator. Refer to 767 AMM 28-22-11 as an accepted procedure. (3) 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: July 03, 2008 767-28A0090 Revision 2: September 02, 2010 61 of 119 **BOEING SERVICE BULLETIN 767-28A0090**(1) Remove and discard the MOV actuator , and remove and keep the bonding jumper. Refer to 767 AMM 28-22-11 as an accepted procedure. (2) Remove the wire bracket and install the new wire bracket on the engine fuel shutoff MOV actuator deflector as given in Figure 21. (3) 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. (4) Rework the index plate as given in Figure 3. (5) Prepare the adapter plate as given in Figure 5. (6) Measure and record the electrical bond resistance 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 767 AMM 28-22-01 as an accepted procedure. 3) Install the MOV actuator as given in Figure 7. Refer to 767 AMM 28-22-11 as an accepted procedure for the install of the MOV actuator body. 4) Do an operational test of the MOV. Refer to 767 AMM 28-22-11 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 28-22-01 as an accepted procedure. 2) Remove the adapter plate and the adapter shaft. Refer to 767 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 767 AMM 28-22-01 as an accepted procedure. 5) Prepare the adapter plate as given in Figure 5. 6) Measure and record the electrical bond resistance 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: July 03, 2008 767-28A0090 Revision 2: September 02, 2010 62 of 119 **BOEING SERVICE BULLETIN 767-28A0090**{1} Temporarily put the index plate in position for installation as given in Figure 6. {2} Install the index plate. Refer to 767 AMM 28-22-01 as an accepted procedure. {3} Install the MOV actuator as given in Figure 7. Refer to 767 AMM 28-22-11 as an accepted procedure for the install of the MOV actuator body. {4} Do an operational test of the MOV. Refer to 767 AMM 28-22-11 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.(6)(b)2) and rework the bond until it is acceptable. 7) 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. Refer to 767 AMM 28-22-11 as an accepted procedure. 4. Put the airplane in a serviceable condition or do another work package. **Group 9: Work Package 10 - ENGINE FUEL SHUTOFF VALVE ACTUATOR (V00025)**  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. (1) Close access to the MOV actuator. Refer to 767 AMM 28-22-11 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 767 AMM 28-22-11 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: July 03, 2008 767-28A0090 Revision 2: September 02, 2010 63 of 119 **BOEING SERVICE BULLETIN 767-28A0090 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) Prepare the adapter plate as given in Figure 5. (5) Measure and record the electrical bond resistance 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 767 AMM 28-22-01 as an accepted procedure. 3) Install the MOV actuator as given in Figure 7. Refer to 767 AMM 28-22-11 as an accepted procedure for the install of the MOV actuator body. 4) Do an operational test of the MOV. Refer to 767 AMM 28-22-11 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 28-22-01 as an accepted procedure. 2) Remove the adapter plate and the adapter shaft. Refer to 767 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 767 AMM 28-22-01 as an accepted procedure. 5) Prepare the adapter plate as given in Figure 5. 6) Measure and record the electrical bond resistance 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:

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 03, 2008 767-28A0090 Revision 2: September 02, 2010 64 of 119 **BOEING SERVICE BULLETIN 767-28A0090**{1} Temporarily put the index plate in position for installation as given in Figure 6. {2} Install the index plate. Refer to 767 AMM 28-22-01 as an accepted procedure. {3} Install the MOV actuator as given in Figure 7. Refer to 767 AMM 28-22-11 as an accepted procedure for the install of the MOV actuator body. {4} Do an operational test of the MOV. Refer to 767 AMM 28-22-11 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.(5)(b)2) and rework the bond until it is acceptable. 7) 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. Refer to 767 AMM 28-22-11 as an accepted procedure. 4. Put the airplane in a serviceable condition or do another work package. **Group 9: Work Package 11 - ENGINE FUEL SHUTOFF VALVE ACTUATOR (V00026)**  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 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 the MOV actuator. Refer to 767 AMM 28-22-11 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 767 AMM 28-22-11 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: July 03, 2008 767-28A0090 Revision 2: September 02, 2010 65 of 119 **BOEING SERVICE BULLETIN 767-28A0090 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) Prepare the adapter plate as given in Figure 5. (5) Measure and record the electrical bond resistance 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 767 AMM 28-22-01 as an accepted procedure. 3) Install the MOV actuator as given in Figure 7. Refer to 767 AMM 28-22-11 as an accepted procedure for the install of the MOV actuator body. 4) Do an operational test of the MOV. Refer to 767 AMM 28-22-11 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 28-22-01 as an accepted procedure. 2) Remove the adapter plate and the adapter shaft. Refer to 767 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 767 AMM 28-22-01 as an accepted procedure. 5) Prepare the adapter plate as given in Figure 5. 6) Measure and record the electrical bond resistance 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: July 03, 2008 767-28A0090 Revision 2: September 02, 2010 66 of 119 **BOEING SERVICE BULLETIN 767-28A0090**{1} Temporarily put the index plate in position for installation as given in Figure 6. {2} Install the index plate. Refer to 767 AMM 28-22-01 as an accepted procedure. {3} Install the MOV actuator as given in Figure 7. Refer to 767 AMM 28-22-11 as an accepted procedure for the install of the MOV actuator body. {4} Do an operational test of the MOV. Refer to 767 AMM 28-22-11as 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 767 AMM 28-26-01 as an accepted procedure. 3. Close access to the MOV actuator. Refer to 767 AMM 28-22-11 as an accepted procedure. 4. Put the airplane in a serviceable condition or do another work package. **Group 1-4; Group 5-7, Configuration 1; Group 7, Configuration 2; Group 8, Configuration 1; Group 9; Group 10, Configuration 1-2:**  **Work Package 12 - DUAL FORWARD/AFT ENGINE FUEL CROSSFEED VALVE ACTUATOR (V00388/V00389)**  1. Get access to each MOV actuator. Refer to 767 AMM 28-22-12 as an accepted procedure. 2. Read and record the part number of each 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 767 AMM 28-22-12 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 767 AMM 28-22-12 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: July 03, 2008 767-28A0090 Revision 2: September 02, 2010 67 of 119 **BOEING SERVICE BULLETIN 767-28A0090 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) Do a visual inspection of the adapter plate. If the adapter plate is marked with "SWEENEY ENGR CORP", you must use the shim kit when you install the MOV actuator with part number MA30A1001. (4) Rework the index plate as given in Figure 3. (5) Prepare the adapter plate as given in Figure 5. (6) Measure and record the electrical bond resistance 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 767 AMM 28-22-02 as an accepted procedure. 3) For the Forward Engine Fuel Crossfeed MOV actuator, install the MOV actuator: If the adapter plate is marked with "SWEENEY ENGR CORP", install the MOV actuator as given in Figure 22. If the adapter is not marked with "SWEENEY ENGR CORP", then install the MOV actuator as give in in Figure 7. Refer to 767 AMM 28-22-12 as an accepted procedure for the install of the MOV actuator body. 4) For the Aft Engine Fuel Crossfeed MOV actuator, install the MOV actuator: If the adapter plate is marked with "SWEENEY ENGR CORP", install the MOV actuator as given in Figure 23. If the adapter is not marked with "SWEENEY ENGR CORP", then install the MOV actuator as given in Figure 7. Refer to 767 AMM 28-22-12 as an accepted procedure for the install of the MOV actuator body. 5) Do an operational test of the MOV. Refer to 767 AMM 28-22-12 as an accepted procedure. (b) If the resistance is 1.5 milliohms or greater, the bond is not acceptable. Do the following steps: 1) Get access to the Motor Operated Valve (MOV). Refer to 767 AMM 28-22-02 as an accepted procedure. 2) Remove the adapter plate and the adapter shaft. Refer to 767 AMM 28-22-02 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 767 AMM 28-22-02 as an accepted procedure.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 03, 2008 767-28A0090 Revision 2: September 02, 2010 68 of 119 **BOEING SERVICE BULLETIN 767-28A0090**5) Prepare the adapter plate as given in Figure 5. 6) Measure and record the electrical bond resistance 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 767 AMM 28-22-02 as an accepted procedure. {3} For the Forward Engine Fuel Crossfeed MOV actuator, install the MOV actuator: If the adapter plate is marked with "SWEENEY ENGR CORP", install the MOV actuator as given in Figure 22. If the adapter is not marked with "SWEENEY ENGR CORP", then install the MOV actuator as given in Figure 7. Refer to 767 AMM 28-22-12 as an accepted procedure for the install of the MOV actuator body. {4} For the Aft Engine Fuel Crossfeed MOV actuator, install the MOV actuator: If the adapter plate is marked with "SWEENEY ENGR CORP", install the MOV actuator as given in Figure 23. If the adapter is not marked with "SWEENEY ENGR CORP", then install the MOV actuator as given in Figure 7. Refer to 767 AMM 28-22-12 as an accepted procedure for the install of the MOV actuator body. {5} Do an operational test of the MOV. Refer to 767 AMM 28-22-12 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.(6)(b)2) and rework the bond until it is acceptable. 7) Close access to the Motor Operated Valve. Refer to 767 AMM 28-22-02 as an accepted procedure. 3. Close access to the MOV actuator. Refer to 767 AMM 28-22-12 as an accepted procedure. 4. Put the airplane in a serviceable condition or do another work package. **Group 5-6, Configuration 2; Group 7, Configuration 3-4; Group 8, Configuration 2; Group 10, Configuration 3-4:**  **Work Package 13 - SINGLE ENGINE FUEL CROSSFEED VALVE ACTUATOR (V00024)** 1. Get access to the MOV actuator. Refer to 767 AMM 28-22-12 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: July 03, 2008 767-28A0090 Revision 2: September 02, 2010 69 of 119 **BOEING SERVICE BULLETIN 767-28A0090**(1) Close access to the MOV actuator. Refer to 767 AMM 28-22-12 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 767 AMM 28-22-12 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) Prepare the adapter plate as given in Figure 5. (5) Measure and record the electrical bond resistance 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 767 AMM 28-22-02 as an accepted procedure. 3) Install the MOV actuator as given in Figure 7. Refer to 767 AMM 28-22-12 as an accepted procedure for the install of the MOV actuator body. 4) Do an operational test of the MOV. Refer to 767 AMM 28-22-12 as an accepted procedure. (b) If the resistance is 1.5 milliohms or greater, the bond is not acceptable. Do the following steps: 1) Get access to the Motor Operated Valve (MOV). Refer to 767 AMM 28-22-02 as an accepted procedure. 2) Remove the adapter plate and the adapter shaft. Refer to 767 AMM 28-22-02 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 767 AMM 28-22-02 as an accepted procedure. 5) Prepare the adapter plate as given in Figure 5. 6) Measure and record the electrical bond resistance from the adapter plate to the airplane structure as given in Figure 4.

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 03, 2008 767-28A0090 Revision 2: September 02, 2010 70 of 119 **BOEING SERVICE BULLETIN 767-28A0090**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 767 AMM 28-22-02 as an accepted procedure. {3} Install the MOV actuator as given in Figure 7. Refer to 767 AMM 28-22-12 as an accepted procedure for the install of the MOV actuator body. {4} Do an operational test of the MOV. Refer to 767 AMM 28-22-12 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 767 AMM 28-22-02 as an accepted procedure. 3. Close access to the MOV actuator. Refer to 767 AMM 28-22-12 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: July 03, 2008 767-28A0090 Revision 2: September 02, 2010 71 of 119 **BOEING SERVICE BULLETIN 767-28A0090**The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary for this figure.
**MORE DATA QTY**  **IDENTIFICATION NAME**  **TASK STEP**  Get access to thepart number markings on the MOV actuator.(a) 3

- MOTOR OPERATED VALVE ACTUATOR (EXISTING) Get 1

Record the part number.(a) 3

- MOTOR OPERATED VALVE ACTUATOR (EXISTING) Record 2

**FIGURE 1: INSPECT AND RECORD DEFUELING MOV ACTUATOR PART NUMBER (SHEET 1 OF 2)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 03, 2008 767-28A0090 Revision 2 September 02, 2010 72 of 119 **BOEING SERVICE BULLETIN 767-28A0090 MORE DATA**  **QTY IDENTIFICATION**  **NAME TASK**  **STEP** (a) Some airplanes have a quantity of two.

**FIGURE 1: INSPECT AND RECORD DEFUELING MOV ACTUATOR PART NUMBER (SHEET 2 OF 2)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 03, 2008 767-28A0090 Revision 2 September 02, 2010 73 of 119 **BOEING SERVICE BULLETIN 767-28A0090 FIGURE 2: REMOVE AND KEEP INDEX PLATE**  **(SHEET 1 OF 2)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 03, 2008 767-28A0090 Revision 2 September 02, 2010 74 of 119 **BOEING SERVICE BULLETIN 767-28A0090**The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary for this figure.
**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 lockwire from the index plate mounting screws. - - LOCKWIRE Remove 2

3

- INDEX PLATE MOUNTING SCREW Remove / Keep 3 Keep for rework.

- - 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: July 03, 2008 767-28A0090 Revision 2 September 02, 2010 75 of 119 **BOEING SERVICE BULLETIN 767-28A0090**The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary for this figure.
**MORE DATA QTY**  **IDENTIFICATION NAME**  **TASK STEP**  Remove anodizedmaterial from the index plate locations using an abrasive pad. Refer to SWPM20-20-00 as an accepted procedure. - - ANODIZED FINISH Remove 1

Clean contact surfaces. Refer to SWPM 20-20-00 as an accepted procedure. 1

- INDEX PLATE Clean 2

**FIGURE 3: REWORK INDEX PLATE (SHEET 1 OF 1)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 03, 2008 767-28A0090 Revision 2 September 02, 2010 76 of 119 **BOEING SERVICE BULLETIN 767-28A0090**The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary for this figure.
**MORE DATA QTY**  **IDENTIFICATION NAME**  **TASK STEP**  Measure the electrical resistance in milliohms from the adapter plate to therear wing spar. Refer to SWPM 20-20- 00 as an accepted procedure. - - ELECTRICAL BOND RESISTANCE Measure 1

Record the electricalresistance in milliohms. - - ELECTRICAL BOND RESISTANCE Record 2

**FIGURE 4: MEASURE AND RECORD ELECTRICAL RESISTANCE FROM ADAPTER PLATE TO THE AIRPLANE SURFACE**  **(SHEET 1 OF 1)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 03, 2008 767-28A0090 Revision 2 September 02, 2010 77 of 119 **BOEING SERVICE BULLETIN 767-28A0090**The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary for this figure.
**MORE DATA QTY**  **IDENTIFICATION NAME**  **TASK STEP**  Remove surface material fromadapter plate contact surface locations using an abrasive pad. Refer to SWPM 20-20-00 asan accepted procedure. 1

- ADAPTER PLATE Clean 1

Clean contact surface locations. Refer to SWPM 20-20-00as an accepted procedure. 1

- ADAPTER PLATE Clean 2

Use a minimum amount of sealant to reduce squeeze out. - BMS 5-45 (BMS 5-95 optional)SEALANT, CATEGORY 2 Apply 3

**FIGURE 5: PREPARE ADAPTER PLATE (SHEET 1 OF 1)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 03, 2008 767-28A0090 Revision 2 September 02, 2010 78 of 119 **BOEING SERVICE BULLETIN 767-28A0090**The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary for this figure.
**MORE DATA QTY**  **IDENTIFICATION NAME**  **TASK STEP**  Put index plate against adapter plate and hold. 1

- INDEX PLATE MOUNTING SCREW Put / Hold 1

Insert the kept screw only. 1

- INDEX PLATE MOUNTING SCREW Insert 2 Tighten screw to hold plate in place. 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: July 03, 2008 767-28A0090 Revision 2 September 02, 2010 79 of 119 **BOEING SERVICE BULLETIN 767-28A0090**The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary for this figure.
**MORE DATA QTY**  **IDENTIFICATION NAME**  **TASK STEP**  Apply a Faying bond to the index plate. (a) - BMS 5-45 (BMS 5-95 optional)SEALANT, CATEGORY 2 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 (SHEET 1 OF 4)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 03, 2008 767-28A0090 Revision 2 September 02, 2010 80 of 119 **BOEING SERVICE BULLETIN 767-28A0090 MORE DATA**  **QTY IDENTIFICATION**  **NAME TASK**  **STEP** Measure the electrical bond resistance of the Faying bond from the mountingfoot of the MOV actuator to a point on the primary airplane structure. (a) (b) 1

- ELECTRICAL BOND RESISTANCE Measure 3

Measure the length of bonding jumper from the attach point on the MOV actuator to the attach point on the airplane structure. Use the shortest bonding jumper that allows no tention. You can select a length from 4-to-6 inches. (a) 1

- BONDING JUMPER Measure 4

If you determined that the bonding jumper is too short, remove the bonding jumper and do the following sub-tasks. 1

- BONDING JUMPER Remove

Select one length from 4-to-6 inches. (a) 1 BACJ40A20-4 BONDING JUMPER, 4 INCH (OPTIONAL) Get

Select one length from 4-to-6 inches. (a) 1 BACJ40A20-5 BONDING JUMPER, 5 INCH (OPTIONAL) Get

Select one length from 4-to-6 inches. (a) 1 BACJ40A20-6 BONDING JUMPER, 6 INCH (OPTIONAL) Get

**FIGURE 7: INSTALL THE MOV ACTUATOR (SHEET 2 OF 4)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 03, 2008 767-28A0090 Revision 2 September 02, 2010 81 of 119 **BOEING SERVICE BULLETIN 767-28A0090 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 bondingjumper to the airplane structure. Use the shortest bonding jumper that allows no tension. You can select a length from 4-to-6 inches. 1

- BONDING JUMPER Attach

Torque fasteners. (a) 1

- BONDING JUMPER Torque
Clean the surface of the bonding jumper lug and fasteners, and the airplane structure. (a) 1

- BONDING JUMPER Clean 6

Measure the electrical bond of the Faying bond from the lug on the end of the bonding jumper to a point on the airplane structure. (a) (c) 1

- BONDING JUMPER Measure

Apply a cap seal to the bonding jumper fasteners. (a) 1

- BONDING JUMPER Apply

**FIGURE 7: INSTALL THE MOV ACTUATOR (SHEET 3 OF 4)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 03, 2008 767-28A0090 Revision 2 September 02, 2010 82 of 119 **BOEING SERVICE BULLETIN 767-28A0090 MORE DATA**  **QTY IDENTIFICATION**  **NAME TASK**  **STEP** Attach the bonding jumper to the MOV actuator. 1

- BONDING JUMPER Attach 7

Torque fasteners. (a) 1

- BONDING JUMPER Torque
Measure the electrical bond resistance of the Faying bond from the lug on the end of the bonding jumper to the foot on the MOV actuator. (a) (d) (e) 1

- BONDING JUMPER Measure

Apply a cap seal to the bonding jumper fasteners. (a) 1

- BONDING JUMPER Apply

(a) Refer to SWPM 20-20-00 as an accepted procedure (b) If the measured electrical bond 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 bond resistance of the Faying bond is not acceptable, rework the Faying bond as necessary. (c) If the measured electrical bond resistance of the Faying bond from the lug on the end of the bonding jumper to a point on the airplane structure is less than 1.5 milliohms, the Faying bond is acceptable. If the measured electrical bond resistance of the Faying bond is not acceptable, rework the Faying bond as necessary. (d) If the measured electrical bond 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 on the MOV actuator is less than 1.5 milliohms,the Faying bond is acceptable. If the measured electrical bond 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.

**FIGURE 7: INSTALL THE MOV ACTUATOR (SHEET 4 OF 4)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 03, 2008 767-28A0090 Revision 2 September 02, 2010 83 of 119 **BOEING SERVICE BULLETIN 767-28A0090**The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary for this figure.
**MORE DATA QTY**  **IDENTIFICATION NAME**  **TASK STEP**  Clean contact surfaces. Refer to SWPM 20-20-00 as an accepted procedure. 1

- ADAPTER PLATE Clean 1

Clean contact surfaces. Refer to SWPM 20-20-00 as an 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: July 03, 2008 767-28A0090 Revision 2 September 02, 2010 84 of 119 **BOEING SERVICE BULLETIN 767-28A0090**The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary for this figure.
**MORE DATA QTY**  **IDENTIFICATION NAME**  **TASK STEP**  Get access to thepart number markings on the MOV actuator. 1

- MOTOR OPERATED VALVE ACTUATOR (EXISTING) Get 1

**FIGURE 9: INSPECT AND RECORD FUEL JETTISON TRANSFER MOV ACTUATOR PART NUMBER - LEFT**  **(SHEET 1 OF 2)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 03, 2008 767-28A0090 Revision 2 September 02, 2010 85 of 119 **BOEING SERVICE BULLETIN 767-28A0090 MORE DATA**  **QTY IDENTIFICATION**  **NAME TASK**  **STEP** Record the part number. 1

- MOTOR OPERATED VALVE ACTUATOR (EXISTING) Record 2

**FIGURE 9: INSPECT AND RECORD FUEL JETTISON TRANSFER MOV ACTUATOR PART NUMBER - LEFT**  **(SHEET 2 OF 2)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 03, 2008 767-28A0090 Revision 2 September 02, 2010 86 of 119 **BOEING SERVICE BULLETIN 767-28A0090**The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary for this figure.
**MORE DATA QTY**  **IDENTIFICATION NAME**  **TASK STEP**  Get access to thepart number markings on the MOV actuator. 1

- MOTOR OPERATED VALVE ACTUATOR (EXISTING) Get 1

**FIGURE 10: INSPECT AND RECORD FUEL JETTISON TRANSFER MOV ACTUATOR PART NUMBER - RIGHT**  **(SHEET 1 OF 2)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 03, 2008 767-28A0090 Revision 2 September 02, 2010 87 of 119 **BOEING SERVICE BULLETIN 767-28A0090 MORE DATA**  **QTY IDENTIFICATION**  **NAME TASK**  **STEP** Record the part number. 1

- MOTOR OPERATED VALVE ACTUATOR (EXISTING) Record 2

**FIGURE 10: INSPECT AND RECORD FUEL JETTISON TRANSFER MOV ACTUATOR PART NUMBER - RIGHT**  **(SHEET 2 OF 2)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 03, 2008 767-28A0090 Revision 2 September 02, 2010 88 of 119 **BOEING SERVICE BULLETIN 767-28A0090 FIGURE 11: INSPECT AND RECORD FUEL JETTISON NOZZLE MOV ACTUATOR PART NUMBER - LEFT**  **(SHEET 1 OF 2)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 03, 2008 767-28A0090 Revision 2 September 02, 2010 89 of 119 **BOEING SERVICE BULLETIN 767-28A0090**The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary for this figure.
**MORE DATA QTY**  **IDENTIFICATION NAME**  **TASK STEP**  Get access to thepart number markings on the MOV actuator. 1

- MOTOR OPERATED VALVE ACTUATOR (EXISTING) Get 1

Record the part number. 1

- MOTOR OPERATED VALVE ACTUATOR (EXISTING) Record 2

**FIGURE 11: INSPECT AND RECORD FUEL JETTISON NOZZLE MOV ACTUATOR PART NUMBER - LEFT (SHEET 2 OF 2)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 03, 2008 767-28A0090 Revision 2 September 02, 2010 90 of 119 **BOEING SERVICE BULLETIN 767-28A0090 FIGURE 12: INSPECT AND RECORD FUEL JETTISON NOZZLE MOV ACTUATOR PART NUMBER - RIGHT**  **(SHEET 1 OF 2)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 03, 2008 767-28A0090 Revision 2 September 02, 2010 91 of 119 **BOEING SERVICE BULLETIN 767-28A0090**The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary for this figure.
**MORE DATA QTY**  **IDENTIFICATION NAME**  **TASK STEP**  Get access to thepart number markings on the MOV actuator. 1

- MOTOR OPERATED VALVE ACTUATOR (EXISTING) Get 1

Record the part number. 1

- MOTOR OPERATED VALVE ACTUATOR (EXISTING) Record 2

**FIGURE 12: INSPECT AND RECORD FUEL JETTISON NOZZLE MOV ACTUATOR PART NUMBER - RIGHT (SHEET 2 OF 2)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 03, 2008 767-28A0090 Revision 2 September 02, 2010 92 of 119 **BOEING SERVICE BULLETIN 767-28A0090**The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary for this figure.
**MORE DATA QTY**  **IDENTIFICATION NAME**  **TASK STEP**  Get access to thepart number markings on the MOV actuator. 1

- MOTOR OPERATED VALVE ACTUATOR (EXISTING) Get 1

Record the part number. 1

- MOTOR OPERATED VALVE ACTUATOR (EXISTING) Record 2

**FIGURE 13: INSPECT AND RECORD APU SHUTOFF MOV ACTUATOR PART NUMBER (SHEET 1 OF 1)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 03, 2008 767-28A0090 Revision 2 September 02, 2010 93 of 119 **BOEING SERVICE BULLETIN 767-28A0090**The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary for this figure.
**MORE DATA QTY**  **IDENTIFICATION NAME**  **TASK STEP**  Get access to thepart number markings on the MOV actuator. 1

- MOTOR OPERATED VALVE ACTUATOR (EXISTING) Get 1

Record the part number. 1

- MOTOR OPERATED VALVE ACTUATOR (EXISTING) Record 2

**FIGURE 14: INSPECT AND RECORD APU ISOLATION MOV ACTUATOR PART NUMBER (SHEET 1 OF 1)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 03, 2008 767-28A0090 Revision 2 September 02, 2010 94 of 119 **BOEING SERVICE BULLETIN 767-28A0090**The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary for this figure.
**MORE DATA QTY**  **IDENTIFICATION NAME**  **TASK STEP**  Get access to thepart number markings on the MOV actuator. 1

- MOTOR OPERATED VALVE ACTUATOR (EXISTING) Get 1

Record the part number. 1

- MOTOR OPERATED VALVE ACTUATOR (EXISTING) Record 2

**FIGURE 15: INSPECT AND RECORD ENGINE FUEL SHUTOFF MOV ACTUATOR PART NUMBER - LEFT (SHEET 1 OF 1)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 03, 2008 767-28A0090 Revision 2 September 02, 2010 95 of 119 **BOEING SERVICE BULLETIN 767-28A0090**The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary for this figure.
**MORE DATA QTY**  **IDENTIFICATION NAME**  **TASK STEP**  Get access to thepart number markings on the MOV actuator. 1

- MOTOR OPERATED VALVE ACTUATOR (EXISTING) Get 1

Record the part number. 1

- MOTOR OPERATED VALVE ACTUATOR (EXISTING) Record 2

**FIGURE 16: INSPECT AND RECORD ENGINE FUEL SHUTOFF MOV ACTUATOR PART NUMBER - RIGHT (SHEET 1 OF 1)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 03, 2008 767-28A0090 Revision 2 September 02, 2010 96 of 119 **BOEING SERVICE BULLETIN 767-28A0090**The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary for this figure.
**MORE DATA QTY**  **IDENTIFICATION NAME**  **TASK STEP**  Get access to thepart number markings on the forward MOV actuator. 1

- MOTOR OPERATED VALVE ACTUATOR (EXISTING) Get 1

**FIGURE 17: INSPECT AND RECORD DUAL FORWARD/AFT ENGINE FUEL CROSSFEED MOV ACTUATOR (SHEET 1 OF 2)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 03, 2008 767-28A0090 Revision 2 September 02, 2010 97 of 119 **BOEING SERVICE BULLETIN 767-28A0090 MORE DATA**  **QTY IDENTIFICATION**  **NAME TASK**  **STEP** Record the part number. 1

- MOTOR OPERATED VALVE ACTUATOR (EXISTING) Record 2

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

- MOTOR OPERATED VALVE ACTUATOR (EXISTING) Get 3

Record the part number. 1

- MOTOR OPERATED VALVE ACTUATOR (EXISTING) Record 4

**FIGURE 17: INSPECT AND RECORD DUAL FORWARD/AFT ENGINE FUEL CROSSFEED MOV ACTUATOR (SHEET 2 OF 2)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 03, 2008 767-28A0090 Revision 2 September 02, 2010 98 of 119 **BOEING SERVICE BULLETIN 767-28A0090**The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary for this figure.
**MORE DATA QTY**  **IDENTIFICATION NAME**  **TASK STEP**  Get access to thepart number markings on the MOV actuator. 1

- MOTOR OPERATED VALVE ACTUATOR (EXISTING) Get 1

Record the part number. 1

- MOTOR OPERATED VALVE ACTUATOR (EXISTING) Record 2

**FIGURE 18: INSPECT AND RECORD SINGLE ENGINE FUEL CROSSFEED MOV ACTUATOR PART NUMBER - LEFT WING**  **(SHEET 1 OF 1)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 03, 2008 767-28A0090 Revision 2 September 02, 2010 99 of 119 **BOEING SERVICE BULLETIN 767-28A0090**The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary for this figure.
**MORE DATA QTY**  **IDENTIFICATION NAME**  **TASK STEP**  Apply a Faying bond to the index plate. (a) - BMS 5-45 (BMS 5-95 optional)SEALANT, CATEGORY 2 Apply 1

Do not connect the bonding jumper to the MOV actuator. Refer to the AMM asan accepted procedure for the install of the MOV actuator body. 1 MA30A1001 MOTOR OPERATED VALVE ACTUATOR Install (New) 2

**FIGURE 19: INSTALL THE MOV ACTUATOR DIRECTLY TO THE MOTOR OPERATED VALVE (SHEET 1 OF 4)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 03, 2008 767-28A0090 Revision 2 September 02, 2010 100 of 119 **BOEING SERVICE BULLETIN 767-28A0090 MORE DATA**  **QTY IDENTIFICATION**  **NAME TASK**  **STEP** Measure the electrical bond resistance of the Faying bond from the mountingfoot of the MOV actuator to a point on the primary airplane structure. (a) (b) 1

- ELECTRICAL BOND RESISTANCE Measure 3

Measure the length of bonding jumper from the attach point on the MOV actuator to the attach point on the airplane structure. Use the shortest bonding jumper that allows no tention. You can select a length from 4-to-6 inches. (a) 1

- BONDING JUMPER Measure 4

If you determined that the bonding jumper is too short, remove the bonding jumper and do the following sub-tasks. 1

- BONDING JUMPER Remove

Select one length from 4-to-6 inches. (a) 1 BACJ40A20-4 BONDING JUMPER, 4 INCH (OPTIONAL) Get

Select one length from 4-to-6 inches. (a) 1 BACJ40A20-5 BONDING JUMPER, 5 INCH (OPTIONAL) Get

Select one length from 4-to-6 inches. (a) 1 BACJ40A20-6 BONDING JUMPER, 6 INCH (OPTIONAL) Get

**FIGURE 19: INSTALL THE MOV ACTUATOR DIRECTLY TO THE MOTOR OPERATED VALVE (SHEET 2 OF 4)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 03, 2008 767-28A0090 Revision 2 September 02, 2010 101 of 119 **BOEING SERVICE BULLETIN 767-28A0090 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 bondingjumper to the airplane structure. Use the shortest bonding jumper that allows no tension. You can select a length from 4-to-6 inches. 1

- BONDING JUMPER Attach

Torque fasteners. (a) 1

- BONDING JUMPER Torque
Clean the surface of the bonding jumper lug and fasteners, and the airplane structure. (a) 1

- BONDING JUMPER Clean 6

Measure the electrical bond of the Faying bond from the lug on the end of the bonding jumper to a point on the airplane structure. (a) (c) 1

- BONDING JUMPER Measure

Apply a cap seal to the bonding jumper fasteners. (a) 1

- BONDING JUMPER Apply

**FIGURE 19: INSTALL THE MOV ACTUATOR DIRECTLY TO THE MOTOR OPERATED VALVE (SHEET 3 OF 4)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 03, 2008 767-28A0090 Revision 2 September 02, 2010 102 of 119 **BOEING SERVICE BULLETIN 767-28A0090 MORE DATA**  **QTY IDENTIFICATION**  **NAME TASK**  **STEP** Attach the bonding jumper to the MOV actuator. 1

- BONDING JUMPER Attach 7

Torque fasteners. (a) 1

- BONDING JUMPER Torque
Measure the electrical bond resistance of the Faying bond from the lug on the end of the bonding jumper to the foot on the MOV actuator. (a) (d) (e) 1

- BONDING JUMPER Measure

Apply a cap seal to the bonding jumper fasteners. (a) 1

- BONDING JUMPER Apply

(a) Refer to SWPM 20-20-00 as an accepted procedure (b) If the measured electrical bond 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 bond resistance of the Faying bond is not acceptable, rework the Faying bond as necessary. (c) If the measured electrical bond resistance of the Faying bond from the lug on the end of the bonding jumper to a point on the airplane structure is less than 1.5 milliohms, the Faying bond is acceptable. If the measured electrical bond resistance of the Faying bond is not acceptable, rework the Faying bond as necessary. (d) If the measured electrical bond 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 on the MOV actuator is less than 1.5 milliohms,the Faying bond is acceptable. If the measured electrical bond 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.

**FIGURE 19: INSTALL THE MOV ACTUATOR DIRECTLY TO THE MOTOR OPERATED VALVE (SHEET 4 OF 4)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 03, 2008 767-28A0090 Revision 2 September 02, 2010 103 of 119 **BOEING SERVICE BULLETIN 767-28A0090 FIGURE 20: REMOVE BRACKET AND INSTALL NEW BRACKET ON ENGINE FUEL SHUTOFF MOV**  **ACTUATOR DEFLECTOR - LEFT (SHEET 1 OF 3)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 03, 2008 767-28A0090 Revision 2 September 02, 2010 104 of 119 **BOEING SERVICE BULLETIN 767-28A0090**The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary for this figure.
**MORE DATA QTY**  **IDENTIFICATION NAME**  **TASK STEP**  Disconnect the wire assembly from the support bracket. 1

- WIRE ASSEMBLY Disconnect 1

Make a reference mark with ink along the lower edge of the wire support bracket for use as a reference line. 1

- REFERENCE MARK Make 2

Drill out the rivets to remove. Removeand discard the support bracket. (c) 1 287T0015-7 WIRE SUPPORT AS- SY Remove 3

Countersink lightfrom .01 to .02 inches deep on the deflector at 120 degree on both sides and install rivets in the old support bracket pilot holes as double flush plugs. (c) (d) 2 BACR15FV6KE7 RIVET Install (New) 4

Shave each rivet head and each rivet button flush to the part surface to finish as a double flush plug. (c) 2 BACR15FV6KE7 RIVET Microshave

1 287T0015-723 WIRE SUPPORT AS- SY Install (New) 5
Countersink on thedeflector at 100 degrees. Install the new support bracket on the deflector. (c) (d) 2 BACR15BA5AD7C RIVET, 100 DEG Install (New)

Clean and prepare the surface area for finish. (e) 1 112T1074-5 DEFLECTOR, REAR SPAR WING Clean 6

**FIGURE 20: REMOVE BRACKET AND INSTALL NEW BRACKET ON ENGINE FUEL SHUTOFF MOV ACTUATOR DEFLECTOR - LEFT**  **(SHEET 2 OF 3)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 03, 2008 767-28A0090 Revision 2 September 02, 2010 105 of 119 **BOEING SERVICE BULLETIN 767-28A0090 MORE DATA**  **QTY IDENTIFICATION**  **NAME TASK**  **STEP** (a) (b)

- BAC5626, TYPE 2, CLASS A OR D COLORED CHEMICALCONVERSION COATING Apply 7

(a) (b)

- BMS 10-11, TYPE 1 PRIMER Apply 1

- WIRE ASSEMBLY Connect 8 (a) Refer to SOPM 20-41-02 as an accepted procedure. (b) Refer to SOPM 20-43-03 as an accepted procedure. (c) Refer to SRM 51-40-02 as an accepted procedure. (d) Refer to SRM 51-40-08 as accepted procedures. (e) Refer to SOPM 20-30-03 as an accepted procedure.

**FIGURE 20: REMOVE BRACKET AND INSTALL NEW BRACKET ON ENGINE FUEL SHUTOFF MOV ACTUATOR DEFLECTOR - LEFT**  **(SHEET 3 OF 3)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 03, 2008 767-28A0090 Revision 2 September 02, 2010 106 of 119 **BOEING SERVICE BULLETIN 767-28A0090 FIGURE 21: REMOVE BRACKET AND INSTALL NEW BRACKET ON ENGINE FUEL SHUTOFF MOV**  **ACTUATOR DEFLECTOR - RIGHT (SHEET 1 OF 3)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 03, 2008 767-28A0090 Revision 2 September 02, 2010 107 of 119 **BOEING SERVICE BULLETIN 767-28A0090**The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary for this figure.
**MORE DATA QTY**  **IDENTIFICATION NAME**  **TASK STEP**  Disconnect the wire assembly from the support bracket. 1

- WIRE ASSEMBLY Disconnect 1

Make a reference mark with ink along the lower edge of the wire support bracket for use as a reference line. 1

- REFERENCE MARK Make 2

Drill out the rivets to remove. Removeand discard the support bracket. (c) 1 287T0015-7 WIRE SUPPORT AS- SY Remove 3

Countersink lightfrom .01 to .02 inches deep on the deflector at 120 degree on both sides and install rivets in the old support bracket pilot holes as double flush plugs. (c)(d) 2 BACR15FV6KE7 RIVET Install (New) 4

Shave each rivet head and each rivet button flush to the part surface to finish as a double flush plug. (c) 2 BACR15FV6KE7 RIVET Microshave

1 287T0015-723 WIRE SUPPORT AS- SY Install (New) 5
Countersink on thedeflector at 100 degrees. Install the new support bracket on the deflector. (c) (d) 2 BACR15BA5AD7C RIVET, 100 DEG Install (New)

Clean and prepare the surface area for finish. (e) 1 112T1074-6 DEFLECTOR, REAR SPAR WING Clean 6

**FIGURE 21: REMOVE BRACKET AND INSTALL NEW BRACKET ON ENGINE FUEL SHUTOFF MOV ACTUATOR DEFLECTOR - RIGHT**  **(SHEET 2 OF 3)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 03, 2008 767-28A0090 Revision 2 September 02, 2010 108 of 119 **BOEING SERVICE BULLETIN 767-28A0090 MORE DATA**  **QTY IDENTIFICATION**  **NAME TASK**  **STEP** (a) (b)

- BAC5626, TYPE 2, CLASS A OR D COLORED CHEMICALCONVERSION COATING Apply 7

(a) (b)

- BMS 10-11, TYPE 1 PRIMER Apply 1

- WIRE ASSEMBLY Connect 8 (a) Refer to SOPM 20-41-02 as an accepted procedure. (b) Refer to SOPM 20-43-03 as an accepted procedure. (c) Refer to SRM 51-40-02 as an accepted procedure. (d) Refer to SRM 51-40-08 as an accepted procedure (e) Refer to SOPM 20-30-03 as accepted procedure.

**FIGURE 21: REMOVE BRACKET AND INSTALL NEW BRACKET ON ENGINE FUEL SHUTOFF MOV ACTUATOR DEFLECTOR - RIGHT**  **(SHEET 3 OF 3)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 03, 2008 767-28A0090 Revision 2 September 02, 2010 109 of 119 **BOEING SERVICE BULLETIN 767-28A0090 FIGURE 22: INSTALL THE SHIM AND FORWARD ENGINE FUEL CROSSFEED MOV ACTUATOR**  **(SHEET 1 OF 5)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 03, 2008 767-28A0090 Revision 2 September 02, 2010 110 of 119 **BOEING SERVICE BULLETIN 767-28A0090**The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary for this figure.
**MORE DATA QTY**  **IDENTIFICATION NAME**  **TASK STEP**  Apply a Faying bond to the index plate. (a) - BMS 5-45 (BMS 5-95 optional)SEALANT, CATEGORY 2 Apply 1

Install on index plate. 1 343T0002-29 SHIM - SWEENEY MOV ADAPTER Install (New) 2 Apply a Faying bond to the shim plate around the holes. - BMS 5-45 (BMS 5-95 optional)SEALANT, CATEGORY 2 Apply 3

Do not connect the Bonding Jumper to the MOV actuator. 1 MA30A1001 MOTOR OPERATED VALVE ACTUATOR Install (New) 4

4 BACS12HM08AH10 SCREW Install (New) Measure the electrical bonding resistance of the Fayingbond for the mounting foot of the MOV actuator to a pointon the primary airplane structure. (a) (b) 1

- ELECTRICAL BOND RESISTANCE Measure 5

**FIGURE 22: INSTALL THE SHIM AND FORWARD ENGINE FUEL CROSSFEED MOV ACTUATOR (SHEET 2 OF 5)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 03, 2008 767-28A0090 Revision 2 September 02, 2010 111 of 119 **BOEING SERVICE BULLETIN 767-28A0090 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 4-to-6 inches. (a) 1

- BONDING JUMPER Measure 6

If you determined that the bonding jumper is too short, remove the bonding jumper and do the following sub-tasks. 1

- BONDING JUMPER Remove

You can select a length from 4-to-6 inches. (a) 1 BACJ40A20-4 BONDING JUMPER, 4 INCH (OPTIONAL) Get

1 BACJ40A20-5 BONDING JUMPER, 5 INCH (OPTIONAL) Get

1 BACJ40A20-6 BONDING JUMPER, 6 INCH (OPTIONAL) Get
Clean the surface of the bonding jumper lug, fasteners, andthe airplane structure. (a) - - BONDING JUMPER Clean 7

Attach the bondingjumper to the airplane structure. Use the shortest bonding jumper that allows no tension. You can select a length from 4-to-6 inches. (a) 1

- BONDING JUMPER Attach

Torque fasteners. (a) 1

- BONDING JUMPER Torque

**FIGURE 22: INSTALL THE SHIM AND FORWARD ENGINE FUEL CROSSFEED MOV ACTUATOR (SHEET 3 OF 5)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 03, 2008 767-28A0090 Revision 2 September 02, 2010 112 of 119 **BOEING SERVICE BULLETIN 767-28A0090 MORE DATA**  **QTY IDENTIFICATION**  **NAME TASK**  **STEP** Clean the surface of the bonding jumper lug, fasteners, and MOV actuator. (a) 1

- BONDING JUMPER Clean 8

Measure the electrical bonding resistance of the Faying bond from the lug onthe end of the bonding jumper to a point on the airplane structure. (a) (c) - - ELECTRICAL BOND Measure

Apply a cap seal to the bonding jumper fasteners. (a) - BMS 5-142, CLASS B (BMS 5-45, CLASS B or BMS 5-95, CLASS B optional)SEALANT, LOW DENSITY Apply

Attach the bonding jumper to the MOV actuator. 1

- BONDING JUMPER Attach 9

Torque fasteners. (a) 1

- BONDING JUMPER Torque
Measure the electrical bonding resistance of the Faying bond from the lug onthe end of the bonding jumper that is installed at the MOV actuator to the footon the MOV actuator. (a) (d) (e) - - ELECTRICAL BOND RESISTANCE Measure

Apply a cap seal to the bonding jumper fasteners. (a) - BMS 5-142, CLASS B (BMS 5-45, CLASS B or BMS 5-95, CLASS B optional)SEALANT, LOW DENSITY Apply

(a) Refer to SWPM 20-20-00 as an accepted procedure. (b) If the measured electrical bonding 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 bonding resistance of the Faying bond is not acceptable, rework the Faying bond as necessary. (c) If the measured electrical bonding resistance of the Faying bond from the lug on the end of the bonding jumper to a point on the airplane structure is less than 1.5 milliohms, the Faying bond is acceptable. If the measured electrical bonding resistance of the Faying bond is not acceptable, rework the Faying bond as necessary.

**FIGURE 22: INSTALL THE SHIM AND FORWARD ENGINE FUEL CROSSFEED MOV ACTUATOR (SHEET 4 OF 5)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 03, 2008 767-28A0090 Revision 2 September 02, 2010 113 of 119 **BOEING SERVICE BULLETIN 767-28A0090 MORE DATA**  **QTY IDENTIFICATION**  **NAME TASK**  **STEP** (d) If the measured electrical bonding 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 on the MOV actuator is less than 1.5 milliohms, the Faying bond is acceptable. If the measured electrical bonding 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.

**FIGURE 22: INSTALL THE SHIM AND FORWARD ENGINE FUEL CROSSFEED MOV ACTUATOR (SHEET 5 OF 5)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 03, 2008 767-28A0090 Revision 2 September 02, 2010 114 of 119 **BOEING SERVICE BULLETIN 767-28A0090 FIGURE 23: INSTALL THE SHIM AND AFT ENGINE FUEL CROSSFEED MOV ACTUATOR**  **(SHEET 1 OF 5)**

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 03, 2008 767-28A0090 Revision 2 September 02, 2010 115 of 119 **BOEING SERVICE BULLETIN 767-28A0090**The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY numbers shown below are the number of parts necessary for this figure.
**MORE DATA QTY**  **IDENTIFICATION NAME**  **TASK STEP**  Apply a Faying bond to the index plate. (a) - BMS 5-45 (BMS 5-95 optional)SEALANT, CATEGORY 2 Apply 1

Install on index plate. 1 343T0002-29 SHIM - SWEENEY MOV ADAPTER Install (New) 2 Apply a Faying bond to the shim plate around the holes. - BMS5-45 SEALANT, CATEGO- RY 2 Apply 3

Do not connect the Bonding Jumper to the MOV actuator. 1 MA30A1001 MOTOR OPERATED VALVE ACTUATOR Install (New) 4

4 BACS12HM08AH10 SCREW Install (New) Measure the electrical bonding resistance of the Fayingbond for the mounting foot of the MOV actuator to a pointon the primary airplane structure. (a) (b) 1

- ELECTRICAL BOND RESISTANCE Measure 5

**FIGURE 23: INSTALL THE SHIM AND AFT ENGINE FUEL CROSSFEED MOV ACTUATOR (SHEET 2 OF 5)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 03, 2008 767-28A0090 Revision 2 September 02, 2010 116 of 119 **BOEING SERVICE BULLETIN 767-28A0090 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 4-to-6 inches. (a) 1

- BONDING JUMPER Measure 6

If you determined that the bonding jumper is too short, remove the bonding jumper and do the following sub-tasks. 1

- BONDING JUMPER Remove

You can select a length from 4-to-6 inches. (a) 1 BACJ40A20-4 BONDING JUMPER, 4 INCH (OPTIONAL) Get

1 BACJ40A20-5 BONDING JUMPER, 5 INCH (OPTIONAL) Get

1 BACJ40A20-6 BONDING JUMPER, 6 INCH (OPTIONAL) Get
Clean the surface of the bonding jumper lug, fasteners, andthe airplane structure. (a) - - BONDING JUMPER Clean 7

Attach the bondingjumper to the airplane structure. Use the shortest bonding jumper that allows no tension. You can select a length from 4-to-6 inches. (a) 1

- BONDING JUMPER Attach

Torque fasteners. (a) 1

- BONDING JUMPER Torque

**FIGURE 23: INSTALL THE SHIM AND AFT ENGINE FUEL CROSSFEED MOV ACTUATOR (SHEET 3 OF 5)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 03, 2008 767-28A0090 Revision 2 September 02, 2010 117 of 119 **BOEING SERVICE BULLETIN 767-28A0090 MORE DATA**  **QTY IDENTIFICATION**  **NAME TASK**  **STEP** Clean the surface of the bonding jumper lug, fasteners, and MOV actuator. (a) 1

- BONDING JUMPER Clean 8

Measure the electrical bonding resistance of the Faying bond from the lug onthe end of the bonding jumper to a point on the airplane structure. (a) (c) - - ELECTRICAL BOND Measure

Apply a cap seal to the bonding jumper fasteners. (a) - BMS 5-142, CLASS B (BMS 5-45, CLASS B or BMS 5-95, CLASS B optional)SEALANT, LOW DENSITY Apply

Attach the bonding jumper to the MOV actuator. 1

- BONDING JUMPER Attach 9

Torque fasteners. (a) 1

- BONDING JUMPER Torque
Measure the electrical bonding resistance of the Faying bond from the lug onthe end of the bonding jumper that is installed at the MOV actuator to the footon the MOV actuator. (a) (d) (e) - - ELECTRICAL BOND RESISTANCE Measure

Apply a cap seal to the bonding jumper fasteners. (a) - BMS 5-142, CLASS B (BMS 5-45, CLASS B or BMS 5-95, CLASS B optional)SEALANT, LOW DENSITY Apply

(a) Refer to SWPM 20-20-00 as an accepted procedure. (b) If the measured electrical bonding 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 bonding resistance of the Faying bond is not acceptable, rework the Faying bond as necessary. (c) If the measured electrical bonding resistance of the Faying bond from the lug on the end of the bonding jumper to a point on the airplane structure is less than 1.5 milliohms, the Faying bond is acceptable. If the measured electrical bonding resistance of the Faying bond is not acceptable, rework the Faying bond as necessary.

**FIGURE 23: INSTALL THE SHIM AND AFT ENGINE FUEL CROSSFEED MOV ACTUATOR (SHEET 4 OF 5)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 03, 2008 767-28A0090 Revision 2 September 02, 2010 118 of 119 **BOEING SERVICE BULLETIN 767-28A0090 MORE DATA**  **QTY IDENTIFICATION**  **NAME TASK**  **STEP** (d) If the measured electrical bonding 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 on the MOV actuator is less than 1.5 milliohms, the Faying bond is acceptable. If the measured electrical bonding 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.

**FIGURE 23: INSTALL THE SHIM AND AFT ENGINE FUEL CROSSFEED MOV ACTUATOR (SHEET 5 OF 5)** 

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. Original Issue: July 03, 2008 767-28A0090 Revision 2 September 02, 2010 119 of 119 **BOEING SERVICE BULLETIN 767-28A0090**