Commercial Airplanes 767 - ltt- · PDF fileCommercial Airplanes 767 Service ... Group...

Commercial Airplanes 767

Service BulletinNumber: 767-28A0090Original Issue: July 03, 2008Revision 1: April 01, 2010ATA 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) (15CFR 730-774). An export license may be required before it is used for development, production or use by foreignpersons from specific countries. The controller of this data has the individual responsibility to abide by all exportlaws.

9E991ECCN:

BOEING PROPRIETARY, CONFIDENTIAL, AND/OR TRADE SECRETCopyright © 2008 The Boeing CompanyUnpublished Work - All Rights Reserved

Boeing claims copyright in each page of this document only to the extent that the page contains copyrightablesubject 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 moreinformation, 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 theBoeing livery are all trademarks owned by The Boeing Company; and no trademark license is granted inconnection with this document unless provided in writing by Boeing.

BOEING PROPRIETARY -Copyright © Unpublished Work - See page 1 for details.

Original Issue: July 03, 2008767-28A0090Revision 1: April 01, 2010

1 of 11813.0



2 of 118

BOEING SERVICE BULLETIN 767-28A0090

BLANK PAGE

Table of ContentsRevision Transmittal Sheet . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5Summary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 91. PLANNING INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13

A. Effectivity . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 131. Airplanes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 132. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22

B. Concurrent Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22C. Reason . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22D. Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 23E. Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25H. Weight and Balance Changes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 42I. Electrical Load Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 42J. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 43

1. Existing Data: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 432. Data supplied with this Service Bulletin: . . . . . . . . . . . . . . . . . . . . . . . . . . . 433. Installation Drawings Used in the Preparation of this Service Bulletin: . . . . . . . . . . . 43

K. Publications Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 43L. Interchangeability and Intermixability of Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . 44

2. MATERIAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 45A. Material - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 45B. Industry Support Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 46C. Parts Necessary For Each Airplane . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 46

1. Kits/Parts: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 462. Parts and Materials Supplied by the Operator: . . . . . . . . . . . . . . . . . . . . . . . . 473. Parts Modified and Reidentified: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 484. Parts Removed and Not Replaced: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 48

D. Parts Necessary to Change Spares . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 48E. Special Tooling - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 48F. Special Tooling Necessary to do this Service Bulletin . . . . . . . . . . . . . . . . . . . . . . . 48

3. ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 49A. GENERAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 49B. WORK INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 50

FIGURE 1: INSPECT AND RECORD DEFUELING MOV ACTUATOR PART NUMBER . . . . . . . . 74FIGURE 2: REMOVE AND KEEP INDEX PLATE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 75FIGURE 3: REWORK INDEX PLATE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 77FIGURE 4: MEASURE AND RECORD ELECTRICAL RESISTANCE FROM ADAPTER PLATE TO THE

AIRPLANE SURFACE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 78FIGURE 5: PREPARE ADAPTER PLATE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 79FIGURE 6: PUT INDEX PLATE IN POSITION FOR INSTALLATION . . . . . . . . . . . . . . . . . . 80FIGURE 7: INSTALL THE MOV ACTUATOR [Group 6-8] . . . . . . . . . . . . . . . . . . . . . . . . 81FIGURE 8: CLEAN ADAPTER PLATE AND AIRPLANE SURFACE . . . . . . . . . . . . . . . . . . . 85FIGURE 9: INSPECT AND RECORD FUEL JETTISON TRANSFER MOV ACTUATOR PART NUMBER -

LEFT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 86



3 of 118


FIGURE 10: INSPECT AND RECORD FUEL JETTISON TRANSFER MOV ACTUATOR PART NUMBER -RIGHT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 87

FIGURE 11: INSPECT AND RECORD FUEL JETTISON NOZZLE MOV ACTUATOR PART NUMBER - LEFT. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 88

FIGURE 12: INSPECT AND RECORD FUEL JETTISON NOZZLE MOV ACTUATOR PART NUMBER -RIGHT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 90

FIGURE 13: INSPECT AND RECORD APU SHUTOFF MOV ACTUATOR PART NUMBER . . . . . . 92FIGURE 14: INSPECT AND RECORD APU ISOLATION MOV ACTUATOR PART NUMBER . . . . . 93FIGURE 15: INSPECT AND RECORD ENGINE FUEL SHUTOFF MOV ACTUATOR PART NUMBER - LEFT

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 94FIGURE 16: INSPECT AND RECORD ENGINE FUEL SHUTOFF MOV ACTUATOR PART NUMBER -

RIGHT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 95FIGURE 17: INSPECT AND RECORD DUAL FORWARD/AFT ENGINE FUEL CROSSFEED MOV ACTUATOR

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 96FIGURE 18: INSPECT AND RECORD SINGLE ENGINE FUEL CROSSFEED MOV ACTUATOR PART

NUMBER - LEFT WING . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 98FIGURE 19: INSTALL THE MOV ACTUATOR DIRECTLY TO THE MOTOR OPERATED VALVE . . . 99FIGURE 20: REMOVE BRACKET AND INSTALL NEW BRACKET ON ENGINE FUEL SHUTOFF MOV

ACTUATOR DEFLECTOR - LEFT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 103FIGURE 21: REMOVE BRACKET AND INSTALL NEW BRACKET ON ENGINE FUEL SHUTOFF MOV

ACTUATOR DEFLECTOR - RIGHT . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 106FIGURE 22: INSTALL THE SHIM AND FORWARD ENGINE FUEL CROSSFEED MOV ACTUATOR [Group

1-5, 9-10] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 109FIGURE 23: INSTALL THE SHIM AND AFT ENGINE FUEL CROSSFEED MOV ACTUATOR [Group 1-5,

9-10] . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 114



4 of 118



Service BulletinRevision Transmittal SheetNumber: 767-28A0090

Original Issue: July 03, 2008Revision 1: April 01, 2010ATA System: 2822 2825 2826 2831


This revision includes all pages of the service bulletin.

COMPLIANCE INFORMATION RELATED TO THIS REVISION

Federal Aviation Administration (FAA) Airworthiness Directive 2009-22-13 is related to this service bulletin.

Active airplanes were added to this service bulletin effectivity as given in the following table:

Variable No.

VS901, VT522, VV001

More work is necessary on airplanes changed in accordance with the original issue of this service bulletin.

The airplanes with more work necessary were not assigned to the correct group configuration in the originalrelease of this service bulletin. This revision assigns the work packages to inspect and replace Motor OperatedValve (MOV) actuators located on the production jettison system to the following airplanes:

ReasonAdditional Work -Work Package(s)

Original Group(Original Release)

New Group (Revi-sion 1)

Variable No.

(b)(a)32VN921

(b)(a)32VN922

(b)(a)32VN966

(b)(a)32VN967

(b)(a)32VN968

(b)(a)32VN969

(b)(a)32VN970

(b)(a)32VN971

(b)(a)32VN972

(a) Add Work Packages 2, 3, 4 and 5.

(b) Airplane was not assigned to the correct group configuration in the original release of this service bulletin.



5 of 118

Airplanes were moved to a new group configuration when an inspection for the presence of Sweeney adapterplates is required. It is possible for any of the airplanes from line number 293 to 940 to have had Sweeneyadapter plates installed during production. Boeing cannot specifically confirm all configurations from line number293 to 940 due to the interchangeability of parts during production. Boeing recommends that affected airplanesbe inspected for the presence of the Sweeney adapter plates by inspecting the part markings on the adapterplate at each of the Dual Forward/Aft Engine Crossfeed Valve Actuator locations. Refer to the description inparagraph 1.A.1, Group Configuration Table to determine which groups must inspect for the presence of theSweeney adapter plates.

REASON FOR REVISION

This revision is sent to correct group configuration assignments, to correct the accomplishment instructions andto correct AMM references. The changes incorporated in this revision are as follows:

1. In paragraph 1.A.1., Airplanes, the Group Configuration table was changed to make clear which groupshave the production APU isolation installed.

2. In paragraph 1.A.1., Airplane Models, the Variable Number - Group table was changed to show the correctgroup assignment for each airplane.

3. In paragraph 1.D., Description, added maintenance zone information.

4. In paragraph 1.G., Manpower, the table titled "Work Package Versus MOV Actuator Equipment Numbers"was added.

5. In paragraph 1.G., Manpower, revised hours by removing the system level functional test requirement forthe install of the MOV actuators.

6. In paragraph 2.C.1., Kit/Parts, the tables were changed to list the correct figure numbers for parts listed inthe kits.

7. In paragraph 2.C.1., Kit/Parts, the tables were changed to list the correct applicability both tables.

8. In paragraph 2.C.2., Parts and Materials Supplied by the Operator, part numbers for consumable materialswere replaced with specification numbers to provide options to the operator when acquiring materials. BMS5-95 was added as an option to BMS 5-45.

9. In paragraph 3.A., Note, added a reference to the Interchangeable Parts 767 Motor Operated Valves (MOV)Boeing Drawing 343T0014.

10. In paragraph 3.A., Note, added a statement that all AMM references apply to procedures for the MOVactuator part numbers MA20A2027 and MA30A1001.

11. In paragraph 3.B., for all work packages, the equipment number(s) was added to the work package title.

12. In paragraph 3.B., for all work packages, Step 2.b.(1) added instruction to remove and keep the bondingjumper.

13. In paragraph 3.B., for all work packages, Step 3 was changed to remove the requirement to perform afunction test.

14. In paragraph 3.B., for Work Package 1, a note was added to make clear that most airplanes only haveequipment numbers V00108 and V00109.



6 of 118


15. In paragraph 3.B., for Work Package 2, Step 3 the AMM reference was corrected.

16. In paragraph 3.B., for Work Package 3, Step 3 the AMM reference was corrected.

17. In paragraph 3.B., for Work Package 4 and 5, the AMM references were corrected throughout.

18. In paragraph 3.B., for Work Package 6, Step 2.b.(2) the Figure 19 was listed as the correct figure for theinstall of the MOV actuator.

19. In paragraph 3.B., for Work Package 7, Step 2.b.(2) the Figure 19 was listed as the correct figure for theinstall of the MOV actuator.

20. In paragraph 3.B., for Work Package 8, Step 2.b.(6)(b)6)b){1} the paragraph reference for where to returnto "rework the bond until it is acceptable" was corrected.

21. In paragraph 3.B., for Work Package 8, Step 2.b.(6)(b)7) and Step 3 the AMM reference was corrected.

22. In Figure 5, removed Steps 3 and 4. These steps are not required.

23. In Figure 7 and 19, Illustration, Circle Note 6 was changed and Circle Note 7 was added to make moreclear where to measure the bonding resistance.

24. In Figure 7 and 19, Step 2, More Data, a reference to the AMM was provided as an accepted procedure toinstall the MOV actuator body.

25. In Figure 7 and 19, Step 5.1 and 6.1, More Data, an instruction was added to make clear that the lug andthe fasteners of the bonding jumper should be cleaned.

26. In Figure 7 and 19, Step 6 was changed and Step 7 was added to make more clear where to measure thebonding resistance.

27. In Figure 17, Illustration, Circle Notes 3 and 4 were corrected.

28. In Figure 20, Step 6, the part number of the rear deflector was corrected.

29. In Figure 22 and 23, Illustration, Circle Notes 8 was changed and Circle Note 9 was added to make moreclear where to measure the bonding resistance.

30. In Figure 22 and 23, Step 7 and 9, More Data, an instruction was added to make clear that the lug and thefasteners for the bonding jumper should be cleaned.

31. In Figure 22 and 23, Step 8 was changed and Step 9 was added to make more clear where to measurethe bonding resistance.

The data given in Information Notice 767-28A0090 IN 01 is included in this revision.

The data given in Information Notice 767-28A0090 IN 02 is included in this revision.

Vertical lines are put on the left edge of each page, except in Paragraph 1.A., Effectivity, to show the locationof important changes.

Pages with no vertical lines have no important changes.



7 of 118


REVISION HISTORY

July 03, 2008Original Issue:

April 01, 2010Revision 1:



8 of 118



Service BulletinSummaryNumber: 767-28A0090

Original Issue: July 03, 2008Revision 1: April 01, 2010ATA System: 2822 2825 2826 2831


CONCURRENT REQUIREMENTS

None.

BACKGROUND

This service bulletin gives instructions to inspect all the motor operated valve (MOV) actuators and to installnew MOV actuators where necessary. The MOV actuators are installed at each fuel system. The new MOVactuator will prevent electrical current flow through the actuator into the fuel tank. If this service bulletin is notdone it is possible that a flow of electricity into the fuel tank will supply an ignition source for the fuel fumes inthe tank.

The Boeing system safety assessment necessary for Special Federal Aviation Regulation (SFAR) 88, showedthat under specific conditions it was possible for electrical current to flow through certain MOV actuators intothe fuel tank. A new MOV actuator is available to replace the existing MOV actuator with this condition. The newMOV actuator includes an internal electrical isolator to give the MOV actuator protection against electrical energyfrom lightning, 115 VAC hot shorts, and 28 VDC internal shorts. The new MOV actuator will prevent the flow ofan 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 partnumber MA30A1001. The MOV actuator part number MA20A1001-1 is the only installed MOV actuator partnumber that is affected by this service bulletin.

This service bulletin gives instruction on how to measure the electrical resistance of bonds at the installed MOVactuator locations, how to prepare a Faying surface for the install of the new MOV actuator, how to prepareaffected 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 TankSystem Fault Tolerance Evaluation Requirements".

Section 9 of the 767 Maintenance Planning Data (MPD) Document was change.



9 of 118

ACTION (PRR B12900-253, 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 MOVactuator 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. Thismay require rework of the index plate and the adapter. This may require a tank entry to rework the interfacebetween the adapter and the airplane structure.

— If you are required to install the MA30A1001 at the dual forward/aft engine fuel crossfeed valve actuatorlocation, you must inspect for the "SWEENEY ENGR CORP" marking on the adapter. If found, you mustinstall the shim kit.

— Some airplane models have a deflector installed at the left and right engine fuel shutoff MOV actuatorlocation, where an installed wire support assembly can potentially interfere with the new MOV actuator. Ifyou are required to install the MA30A1001 at these locations, you must also install the new wire supportassembly 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 FAAAD 2009-22-13.

INDUSTRY SUPPORT INFORMATION

Boeing warranty remedies are not available for the configuration changes given in this service bulletin.

MANPOWER

Elapsed HoursTotal Task HoursAirplanes

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

191.05 (a)(b)440.05 (a)(b)Group 7.2



10 of 118


Elapsed HoursTotal Task HoursAirplanes

182.30 (a)(b)429.30 (a)(b)Group 7.3

182.30 (a)(b)429.30 (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

191.05 (a)(b)440.05 (a)(b)Group 10.2

182.30 (a)(b)429.30 (a)(b)Group 10.3

182.30 (a)(b)429.30 (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 timeneeded to do the work is much less.

MATERIAL INFORMATION

Operator Supplied Parts.

Refer to Paragraph 2.A., Material - Price and Availability.



11 of 118




12 of 118



Service BulletinNumber: 767-28A0090Original Issue: July 03, 2008Revision 1: April 01, 2010ATA System: 2822 2825 2826 2831


1. PLANNING INFORMATION

A. Effectivity

1. Airplanes

Refer to Service Bulletin Index Document D624T001 Part 3 for Airplane Variable Number, LineNumber, and Serial Number data.

This service bulletin is for the airplanes shown below. An equivalent change is on subsequentproduction airplanes. Refer to PRR B13421-6 for data about this change.

DESCRIPTIONCONFIGURATIONGROUP

767-200/300/300F airplanes with the production dual crossfeedinstallation, and with the production fuel jettison installation. Requiresan inspection to determine if the Sweeney adapters are present.

-1

767-200/300/300F airplanes with the production dual crossfeedinstallation, with the production fuel jettison installation, and with theSweeney adapters installed during production. Requires an inspectionto determine if the Sweeney adapters are present.

-2

767-200/300/300F airplanes with the production dual crossfeedinstallations, without the fuel jettison, without the APU isolation, withthe center auxiliary tank defuel valve, and with the Sweeney adapterspresent.

-3

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

-4



13 of 118


767-200/300/300F airplanes effected by Boeing service bulletin767-28-0034 to install the dual crossfeed, with the production jettisoninstallation, and with the production APU isolation. Requires aninspection 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 bulletin767-28-0034.

2

767-200/300/300F airplanes effected by Boeing service bulletin767-28-0034 to install the dual crossfeed, without the productionjettison installation, with the production APU isolation installation,and without the center auxiliary tank defuel valve.

-6



2

767-200/300/300F airplanes effected by Boeing service bulletin767-28-0034 to install the dual crossfeed, and effected by Boeingservice bulletin 767-28-0027 to install the fuel jettison, and with theproduction APU isolation installation.

-7

Made changes as given in Boeing service bulletin 767-28-0034, andmade changes as given in Boeing service bulletin 767-28-0027.

1

Made changes as given in Boeing service bulletin 767-28-0034, butdid not make changes as given in Boeing service bulletin767-28-0027.

2

Did not make changes as given in Boeing service bulletin767-28-0034, but made changes as given in Boeing service bulletin767-28-0027.

3

Did not make changes as given in Boeing service bulletin767-28-0034, and did not make changes as given in Boeing servicebulletin 767-28-0027.

4



14 of 118



767-200/300/300F airplanes effected only by Boeing service bulletin767-28-0034 to install the dual crossfeed, without the jettisoninstallation, with the production APU isolation installation, and thecenter auxiliary tank defuel valve.

-8



2

767-400ER airplanes that require an inspection to determine if theSweeney adapters are present.

-9

767-200/300/300F airplanes effected by Boeing service bulletin767-28-0034 to install the dual crossfeed, and effected by Boeingservice bulletin 767-28-0027 to install the fuel jettison, with theproduction APU isolation installation, and with the center auxiliarytank defuel valve.

-10

Made changes as given in Boeing service bulletin 767-28-0034, andmade changes as given in Boeing service bulletin 767-28-0027.

1

Made changes as given in Boeing service bulletin 767-28-0034, butdid not make changes as given in Boeing service bulletin767-28-0027.

2

Did not make changes as given in Boeing service bulletin767-28-0034, but made changes as given in Boeing service bulletin767-28-0027.

3

Did not make changes as given in Boeing service bulletin767-28-0034, and did not make changes as given in Boeing servicebulletin 767-28-0027.

4

Airplane Models:

767-200, 767-300, 767-300F, 767-400ER

GroupVariable Number

8VA001 - VA020

8VA301 - VA315

8VA501 - VA526

6VA527 - VA530

8VA701 - VA712

6VA713 - VA719



15 of 118



8VA801 - VA810

8VB001 - VB002

8VB051 - VB055

8VB101 - VB125

8VB201 - VB202

8VB251 - VB253

8VB281 - VB284

8VB301 - VB302

8VB321 - VB324

6VB325 - VB332

8VB371 - VB373

8VB401

4VB441 - VB444

8VE001 - VE002

6VE003

8VE021 - VE023

8VE041 - VE043

8VE061 - VE069

8VE083 - VE084

6VE085 - VE086

8VE101 - VE103

6VE104

8VE116 - VE117

6VE118

8VE121 - VE126

8VE141 - VE143

6VE144 - VE151

4VE152

6VE171 - VE172

7VF001 - VF002

7VF041 - VF042

7VF051

5VF061 - VF062



16 of 118



5VF071 - VF072

5VF091 - VF093

5VF101 - VF102

5VF161

2VF162

2VF171 - VF172

2VF180

4VF181 - VF184

2VF251

8VK001 - VK004

6VK005 - VK011

4VK012 - VK016

6VK021 - VK022

8VK031 - VK054

3VK055 - VK056

8VK081 - VK083

6VK084 - VK099

4VK100 - VK113

6VK131 - VK133

6VK141 - VK142

4VK143 - VK148

6VK161

4VK162 - VK164

4VK171

4VK181

4VK186

10VL001

7VL002 - VL006

10VL011

2VL701 - VL703

2VL751 - VL755

2VL806 - VL807

2VL871 - VL873



17 of 118



2VL891 - VL900

2VL911 - VL914

2VL931 - VL932

2VL941

7VN001 - VN015

5VN016 - VN020

2VN021 - VN041

7VN051 - VN058

5VN059 - VN064

7VN081 - VN085

5VN086 - VN092

2VN093 - VN099

7VN111 - VN115

5VN116 - VN124

2VN125 - VN127

5VN130 - VN132

2VN133 - VN137

7VN151 - VN155

5VN156 - VN158

5VN163 - VN168

7VN171 - VN173

2VN174

7VN191 - VN192

5VN193

2VN194 - VN198

7VN211 - VN212

7VN221

5VN222 - VN224

2VN225

5VN231 - VN234

6VN241

2VN242 - VN243

5VN251 - VN260



18 of 118



2VN261 - VN276

5VN291

2VN292 - VN293

5VN301 - VN306

2VN307 - VN314

5VN371 - VN372

5VN376

5VN381

2VN382 - VN388

2VN421 - VN427

2VN436

5VN471 - VN472

5VN491 - VN497

2VN498 - VN513

5VN531 - VN532

5VN536 - VN537

5VN541 - VN542

2VN546 - VN547

5VN551

2VN556 - VN557

2VN561 - VN562

5VN631 - VN633

2VN634 - VN638

5VN651 - VN652

2VN653 - VN658

5VN671 - VN672

2VN676

5VN681 - VN683

2VN684 - VN691

5VN731

2VN732

5VN751 - VN753

2VN791 - VN792



19 of 118



2VN811 - VN813

2VN921 - VN922

2VN931 - VN936

2VN951 - VN953

2VN966 - VN972

9VQ001 - VQ021

9VQ071 - VQ086

1VR051 - VR060

1VR081

1VR084

1VR086 - VR087

1VR106

2VR201 - VR209

1VR210 - VR211

2VR251

2VR256 - VR257

1VR258 - VR260

4VR401

4VR421 - VR423

4VR426

4VR441

4VR461

3VR471 - VR472

2VS051 - VS056

2VS061

2VS066 - VS070

2VS073 - VS078

2VS091 - VS102

1VS103 - VS104

2VS111 - VS113

2VS131 - VS133

2VS136 - VS137

2VS176 - VS177



20 of 118



2VS186 - VS187

2VS196 - VS203

2VS206 - VS208

2VS211

2VS216 - VS217

1VS231

2VS246 - VS248

2VS261 - VS262

1VS263

2VS266 - VS274

2VS291

1VS292 - VS293

2VS301 - VS302

1VS303

2VS306 - VS307

1VS308 - VS311

2VS316

2VS321 - VS324

1VS331 - VS333

1VS336 - VS337

2VS366 - VS367

2VS381 - VS382

2VS391 - VS392

2VS401

1VS426 - VS428

2VS466 - VS470

1VS471 - VS472

2VS486

2VS496

1VS497

2VS506 - VS507

1VS526

1VS546 - VS549



21 of 118



1VS701 - VS714

1VS721 - VS732

1VS751 - VS759

1VS821 - VS825

1VS841 - VS844

1VS861

1VS881 - VS883

1VS891

1VS896

1VS901

1VT501

1VT511 - VT512

1VT521 - VT522

1VV001

2VW701 - VW721

2VW851

2. Spares Affected

Examine your spares supply for the parts or components identified in Paragraph 2.C., PartsNecessary for Each Airplane. If any parts or components are found, refer to Paragraph 2.C. forthe recommended use.

B. Concurrent Requirements

None

C. Reason

This service bulletin gives instructions to inspect all the motor operated valve (MOV) actuators and toinstall new MOV actuators where necessary. The MOV actuators are installed at each fuel system.The new MOV actuator will prevent electrical current flow through the actuator into the fuel tank. If thisservice bulletin is not done it is possible that a flow of electricity into the fuel tank will supply an ignitionsource 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 MOVactuators into the fuel tank. A new MOV actuator is available to replace the existing MOV actuator withthis condition. The new MOV actuator includes an internal electrical isolator to give the MOV actuatorprotection 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 thereliability of the fuel system.



22 of 118


This service bulletin replaces the MOV actuator part number MA20A1001-1 with the new MOV actuatorpart number MA30A1001. The MOV actuator part number MA20A1001-1 is the only installed MOVactuator part number that is affected by this service bulletin.

This service bulletin gives instruction on how to measure the electrical resistance of bonds at theinstalled MOV actuator locations, how to prepare a Faying surface for the install of the new MOVactuator, 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, "FuelTank 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 instructionsand to correct AMM references. The changes incorporated in this revision are as follows:

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 MA20A1001-1is 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 eachlocation. If the measured resistance is not acceptable, you must rework the Faying bond and theairplane parts. This may require rework of the index plate and the adapter plate. This may requirea 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 valveactuator location, you must inspect for the "SWEENEY ENGR CORP" marking on the adapterplate. If found, you must install the shim kit.

— Some airplane models have a deflector installed at the left and right engine fuel shutoff MOVactuator location, where an installed wire support assembly can potentially interfere with the newMOV actuator. If you are required to install the MA30A1001 at these locations, you must also installthe new wire support assembly on the deflector. The new wire support assembly will prevent partinterference.

— 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 theoriginal issue of this service bulletin. This revision assigns the work packages to inspect and replaceMotor Operated Valve (MOV) actuators located on the production jettison system to the followingairplanes:




Variable No.

(b)(a)32VN921

(b)(a)32VN922

(b)(a)32VN966

(b)(a)32VN967



23 of 118





Variable No.

(b)(a)32VN968

(b)(a)32VN969

(b)(a)32VN970

(b)(a)32VN971

(b)(a)32VN972

(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 Sweeneyadapter plates is required. It is possible for any of the airplanes from line number 293 to 940 to havehad Sweeney adapter plates installed during production. Boeing cannot specifically confirm allconfigurations 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 adapterplates by inspecting the part markings on the adapter plate at each of the Dual Forward/Aft EngineCrossfeed Valve Actuator locations. Refer to the description in paragraph 1.A.1, Group ConfigurationTable to determine which groups must inspect for the presence of the Sweeney adapter plates.

The work in this service bulletin is done in the maintenance zone(s) given below.

Group 1-2:

Affected Maintenance Zones

ZoneModel

133, 134, 136, 531, 532, 541, 551, 631, 632,641, 651

767-200, 767-300, 767-300F

Group 3, 10:


ZoneModel

133, 134, 136, 531, 532, 541, 551, 631, 632,641, 651

767-300

Group 4-8:


ZoneModel

133, 134, 136, 531, 532, 541, 551, 631, 632,641, 651

767-200, 767-300



24 of 118


Group 9:


ZoneModel

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 servicebulletin.

Boeing recommends that this service bulletin be incorporated within 60 months from the effective dateof FAA AD 2009-22-13.

F. Approval

This service bulletin was examined by the Federal Aviation Administration (FAA). The changes specifiedin this service bulletin comply with the applicable regulations and are FAA approved, as well as EuropeanAviation Safety Agency (EASA)/Joint Aviation Authorities (JAA) approved for all EASA/JAA approvedairplanes listed in the service bulletin effectivity. This service bulletin and its approval were based onthe airplane in its original Boeing delivery configuration or as modified by other approved Boeingchanges.

If an airplane has a non-Boeing modification or repair that affects a component or system also affectedby this service bulletin, the operator is responsible for obtaining appropriate regulatory agency approvalbefore incorporating this service bulletin.

This service bulletin has been approved by the FAA. In addition, the Manager of the FAA Seattle AircraftCertification Office approves the inspection and the replacement, as required, of the motor operatedvalve actuators, as described in this service bulletin, as an alternative method of compliance to theinspection and the replacement, as required, of the motor operated valve actuators, as described inservice bulletin 767-28A0090, dated July 3, 2008, required by paragraphs (g) and (h) of FAA AD2009-22-13. All provisions of FAA AD 2009-22-13 that are not specifically referenced in the precedingsentence 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. Thisestimate is for direct labor only, done by an experienced crew. Adjust the estimate with operator taskhour data if necessary. The estimate does not include lost time. These are some examples of lost time:

• Time to adjust to the workplace• Time to schedule the work• Time to inspect the work• Time to cure the materials• Time to make the parts• Time to find the tools.



25 of 118


Work Package Versus MOV Actuator Equipment Numbers

MOV Actuator Equipment No.Work Package No.

V00108/V00109/V001231

V001592

V001603

V001574

V001585

V000966

V000977

V000258

V000269

V0002510

V0002611

V00388/V0038912

V0002413



26 of 118


ElapsedHours

Task HoursNumber ofPersons

TasksWork Package

0.501.002PrepareWork Package 1

0.100.101Open MOV ac-tuator access

0.250.251Figure 1

0.250.251Remove MOVactuator

1.001.001Figure 2

1.001.001Figure 3

0.500.501Figure 4

8.0032.04MOV access/fuel tank entry(a)

1.002.002Removeadapter plateand adaptershaft (a)

1.001.001Figure 8 (a)

1.002.002Install adapterplate andadapter shaft(a)

0.500.501Figure 4 (a)

1.501.501Figure 5

0.500.501Figure 6

0.500.501Install indexplate

0.250.251Install MOV ac-tuator

4.008.002Close MOV ac-cess in fueltank

0.100.101Close MOV ac-tuator access

21.9552.45Total for Work Package



27 of 118


ElapsedHours


TasksWork Package



0.250.251Figure 9


1.001.001Figure 2

1.001.001Figure 3

0.500.501Figure 4



1.001.001Figure 8 (a)


0.500.501Figure 4 (a)

1.501.501Figure 5

0.500.501Figure 6








28 of 118


ElapsedHours


TasksWork Package



0.250.251Figure 10


1.001.001Figure 2

1.001.001Figure 3

0.500.501Figure 4



1.001.001Figure 8 (a)


0.500.501Figure 4 (a)

1.501.501Figure 5

0.500.501Figure 6








29 of 118


ElapsedHours


TasksWork Package



0.500.501Figure 11


1.001.001Figure 2

1.001.001Figure 3

0.500.501Figure 4



1.001.001Figure 8 (a)


0.500.501Figure 4 (a)

1.501.501Figure 5

0.500.501Figure 6








30 of 118


ElapsedHours


TasksWork Package



0.500.501Figure 12


1.001.001Figure 2

1.001.001Figure 3

0.500.501Figure 4



1.001.001Figure 8 (a)


0.500.501Figure 4 (a)

1.501.501Figure 5

0.500.501Figure 6








31 of 118


ElapsedHours


TasksWork Package



0.500.501Figure 13







0.500.501Figure 14







32 of 118


ElapsedHours


TasksWork Package



0.250.251Figure 15


2.002.001Figure 20

1.001.001Figure 2

1.001.001Figure 3

0.500.501Figure 4



1.001.001Figure 8 (a)


0.500.501Figure 4 (a)

1.501.501Figure 5

0.500.501Figure 6








33 of 118


ElapsedHours


TasksWork Package



0.250.251Figure 16


2.002.001Figure 21

1.001.001Figure 2

1.001.001Figure 3

0.500.501Figure 4



1.001.001Figure 8 (a)


0.500.501Figure 4 (a)

1.501.501Figure 5

0.500.501Figure 6








34 of 118


ElapsedHours


TasksWork Package



0.250.251Figure 15


1.001.001Figure 2

1.001.001Figure 3

0.500.501Figure 4



1.001.001Figure 8 (a)


0.500.501Figure 4 (a)

1.501.501Figure 5

0.500.501Figure 6








35 of 118


ElapsedHours


TasksWork Package



0.250.251Figure 16


1.001.001Figure 2

1.001.001Figure 3

0.500.501Figure 4



1.001.001Figure 8 (a)


0.500.501Figure 4 (a)

1.501.501Figure 5

0.500.501Figure 6








36 of 118


ElapsedHours


TasksWork Package



0.250.251Figure 17


2.002.001Figure 2 (b)

2.002.001Figure 3 (b)

1.001.001Figure 4 (b)


2.004.002Removeadapter plateand adaptershaft (a)(b)

2.002.001Figure 8. (a)(b)

2.004.002Install adapterplate andadapter shaft(a)(b)

1.001.001Figure 4 (a)(b)

3.003.001Figure 5 (b)

1.001.001Figure 6 (b)

1.001.001Install indexplate (b)

0.500.501Install MOV ac-tuator (b)(c)






37 of 118


ElapsedHours


TasksWork Package



0.250.251Figure 18


1.001.001Figure 2

1.001.001Figure 3

0.500.501Figure 4



1.001.001Figure 8. (a)


0.500.501Figure 4 (a)

1.501.501Figure 5

0.500.501Figure 6



4.008.002Close fuel tankaccess (a)



(a) This task is associated with a tank entry. A tank entry should not be likely. A tankentry 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



38 of 118


ElapsedHours


TasksWork Package

in the Accomplishment Instructions to do the work. See the Accomplishment Instruc-tions for more detail.

Group 1-2:Only the Work Packages for these Groups

Total Elapsed HoursTotal Task-Hours (a)Sum of Work Packages

21.9552.45Work Package 1









188.95437.45TOTAL FOR EACH AIRPLANE

(a) See the work package tables for details.

Group 3-4:Only the Work Packages for these Groups









Group 5, 7, Configuration 1; Group 7, Configuration 2; Group 10, Configuration 1-2:Only the Work Packages for these Groups






39 of 118


Group 5, 7, Configuration 1; Group 7, Configuration 2; Group 10, Configuration 1-2:Only the Work Packages for these Groups












Group 5, Configuration 2; Group 7, Configuration 3-4; Group 10, Configuration 3-4:Only the Work Packages for these Groups














Group 6, 8, Configuration 1:Only the Work Packages for these Groups






40 of 118




















Group 9:Only the Work Packages for these Groups














41 of 118


Group 9:Only the Work Packages for these Groups




H. Weight and Balance Changes

Change in Moment(Pound-Inches)

Change in Weight(Pounds)

Airplane

+6028.0+4.4767-200

+6608.9+4.4767-300

Change in Moment(Pound-Inches)

Change in Weight(Pounds)

Work Package

+465.1+0.4Work Package 1 (a)

+465.3+0.4Work Package 2










+466.6+0.4Work Package 12 (a)

(a) Values are for one individual MOV actuator listed in the work package.

I. Electrical Load Data

Not changed.



42 of 118


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 SYSTEMINSTALLATION

k. Boeing Service Bulletin 767-28-0034 FUEL - DISTRIBUTION - DUAL CROSSFEED VALVEINSTALLATION

2. Data supplied with this Service Bulletin:

None.

3. Installation Drawings Used in the Preparation of this Service Bulletin:

TitleDrawing Number

Equipment - Engine Fuel Feed System343T0002

APU Fuel Feed Syst - Wing346T0004

Equipment Instl - Refueling System344T0002

Fuel System Diagram340T0007

K. Publications Affected

1. Publications:

Chapter-SectionPublication

28-22, 28-25, 28-26, 28-31767 Airplane Maintenance Manual (AMM)

28-22, 28-25, 28-26, 28-31767 Illustrated parts Catalog (IPC)



43 of 118


Chapter-SectionPublication

9767 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 forchanges to Damage Tolerance Inspections (DTI) required in the Maintenance Program. Thisservice 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 intermixabilityinformation.



44 of 118


2. MATERIAL INFORMATION

A. Material - Price and Availability

Boeing can supply the kits shown in Paragraph 2.C., Parts Necessary For Each Airplane as shownbelow. 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 thedate Boeing gets the purchase order.

Unit Price thru(DEC 31/08)

ROLT(Weeks)

QTYDateNameKit Number

280.002360AvailableTop Kit - Bracket Installa-tion

015T1805-1

2330JAN 30/08Top Kit - Bracket Installa-tion

015T1805-1

2330FEB 29/08Top Kit - Bracket Installa-tion

015T1805-1

2330MAR 31/08Top Kit - Bracket Installa-tion

015T1805-1

2330APR 29/08Top Kit - Bracket Installa-tion

015T1805-1

2330MAY 29/08Top Kit - Bracket Installa-tion

015T1805-1

2330JUL 07/08Top Kit - Bracket Installa-tion

015T1805-1

2310JUL 30/08Top Kit - Bracket Installa-tion

015T1805-1

716.003025AvailableTop Kit - Bracket Installand 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 thatfollow:

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



45 of 118


B. Industry Support Information

Boeing warranty remedies are not available for the configuration changes are given in this servicebulletin.

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 theSweeney adapter is present then use the kit 015T1805-2. If not present then use the kit015T1805-1.

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 bythe Operator, are necessary for each airplane. The Top Kit is divided into Figure kits foreach 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

23222120Top Kit

--11015T1805-1

1111015T1805-2

Group 6-8:

KIT 015T1805-1

NOTESExisting PartNumberName

Figure

New Part Number

2120

QTY

WIRE SUPPORTASSY

11287T0015-723

RIVET, 100 DEG22BACR15BA5AD7C

RIVET22BACR15FV6KE7



46 of 118


Group 1-5, 9-10:

KIT 015T1805-2

NOTESExisting PartNumberName

Figure

New Part Number

23222120

QTY

WIRE SUPPORTASSY

11287T0015-723

SHIM - SWEENEYMOV ADAPTER

11343T0002-29

RIVET, 100 DEG22BACR15BA5AD7C

RIVET22BACR15FV6KE7

SCREW44BACS12HM08AH10

2. Parts and Materials Supplied by the Operator:

NotesNameQTYPart Number /Specification

Replaces MA20A1001-1(S343T003-39)

MOTOR OPERATED VALVE ACTU-ATOR

11MA30A1001(S343T003-66) (a)

(b)(e)SEALANT, CATEGORY 222 oz.BMS 5-45

(c)SEALANT, LOW DENSITY22 oz.BMS 5-142

COLORED CHEMICAL CONVER-SION COATING

4 oz.BAC5626, TYPE 2CLASS A OR D

PRIMER4 oz.BMS 10-11, TYPE1

(d)BONDING JUMPER, 4 INCH (OP-TIONAL)

11BACJ40A20-4


11BACJ40A20-5


11BACJ40A20-6

(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 ofcap seal on the MOV actuator bonding jumper locations as described in the work packagesof this service bulletin.

(d) Optional: the new MOV actuator (MA30A1001) installation may require that a longer orshorter bonding jumper be installed to reach the bonding jumper mounting screw on eitherside of the MOV actuator.



47 of 118


NotesNameQTYPart 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:

NotesQTYNameExisting PartNumber

Bracket removed fromeach deflector located atthe engine fuel shutoffMOV actuator.

2WIRE SUPPORTASSY

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, maintenanceand overhaul tools in the manuals given in Paragraph 1.J., References, can be necessary. Examineoperator tool supply to make sure all necessary tools are available.



48 of 118


3. ACCOMPLISHMENT INSTRUCTIONS

A. GENERAL INFORMATION

CAUTION: KEEP THE WORK AREA, WIRES AND ELECTRICAL BUNDLES CLEAN OF METALPARTICLES OR CONTAMINATION WHEN YOU USE TOOLS. UNWANTED MATERIAL,METAL PARTICLES OR CONTAMINATION CAUGHT IN WIRE BUNDLES CAN CAUSEDAMAGE TO THE BUNDLES. DAMAGED WIRE BUNDLES CAN CAUSE SPARKS OROTHER ELECTRICAL DAMAGE.

NOTE: 1. Manual titles are referred to by acronyms. Refer to Paragraph 1.J., References, fordefinition 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 Hoursfor each package are given in Paragraph 1.G., Manpower. You can do each workpackage 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 StructuralRepair Manual, Chapter 51, Alternate fasteners are given in the 767 Structural RepairManual Chapter 51 and Boeing Drawing 767 012W6100.

6. Refer to the Boeing Standard Wiring Practices Manuals 20-10-11 and 20-10-12 forthe wire installation procedures.

7. If the length of fasteners specified in this service bulletin do not meet the installationstandards, fasteners of the same specification, or an approved substitute, one griplength 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 alternativeprocedure, the accepted alternative procedure can be used. When the words "asgiven in" are included in the instruction, the procedure in the Boeing document mustbe used.

9. For approved interchangeability of MOV actuators, refer to the Interchangeable Parts767 Motor Operated Valves (MOV) Boeing Drawing 343T0014.

10. All AMM references apply to the procedures for MOV actuator part numberMA20A2027 and MA30A1001.



49 of 118


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 workpackage always applies to equipment numbers V00108 and V00109. This work packagealso applies to equipment number V00123, if equipment number V00123 is installed onthe airplane. If equipment number V00123 is not installed on the airplane, then no workis 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 workis necessary at this location.

(1) Close access to each MOV actuator. Refer to 767 AMM 28-26-11 as an acceptedprocedure.

(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 followingsteps to install the MOV actuator with part number MA30A1001:

(1) Remove and discard the MOV actuator , and remove and keep the bonding jumper. Referto 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 airplanestructure 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 airplanestructure as given in Figure 4.

(a) If the resistance is less than 1.5 milliohms, the bond is acceptable. Do the followingsteps:



50 of 118


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 asan 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 acceptedprocedure.

(b) If the resistance is 1.5 milliohms or greater, the bond is not acceptable. Fuel tankentry is necessary to make an acceptable bond. Do the following steps:

1) Get access to the Motor Operated Valve (MOV). Refer to 767 AMM 28-26-01as an accepted procedure.

2) Remove the adapter plate and the adapter shaft. Refer to 767 AMM 28-26-01as 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 asan 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 theairplane structure as given in Figure 4.

a) If the resistance is less than 0.5 milliohms, the bond is acceptable. Do thefollowing steps:

{1} Temporarily put the index plane in position for installation as given inFigure 6.

{2} Install the index plate. Refer to 767 AMM 28-26-01 as an acceptedprocedure.

{3} Install the MOV actuator as given in Figure 7. Refer to 767 AMM28-26-11 as an accepted procedure for the install of the MOV actuatorbody.

{4} Do an operational test of the MOV. Refer to 767 AMM 28-26-11 as anaccepted procedure.

b) If the resistance is 0.5 milliohms or greater, the bond is not acceptable. Dothe following steps:



51 of 118


{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 anaccepted 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.



(1) Close access to the MOV actuator. Refer to 767 AMM 28-31-04 as an accepted procedure.












52 of 118


1) Temporarily put the index plate in position for installation as given in Figure 6.












{1} Temporarily put the index plate in position for installation as given inFigure 6.







53 of 118






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)
















54 of 118





















55 of 118






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)
















56 of 118





















57 of 118






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)
















58 of 118





















59 of 118



7) Close access to the MOV. Refer to 767 AMM 28-31-03 as an acceptedprocedure.



Group 1-10:Work Package 6 - APU FUEL SHUTOFF VALVE ACTUATOR (V00096)








(2) Install the MOV actuator as given in Figure 19. Refer to 767 AMM 28-25-02 as an acceptedprocedure 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.



Group 5-8, 10:Work Package 7 - APU FUEL ISOLATION VALVE ACTUATOR (V00097)






60 of 118






(2) Install the MOV actuator as given in Figure 19. Refer to 767 AMM 28-25-04 as an acceptedprocedure 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.



Group 1-8, 10:Work Package 8 - ENGINE FUEL SHUTOFF VALVE ACTUATOR (V00025)



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 MOVactuator deflector as given in Figure 20.

NOTE: This change must be made to accomodate any future install of part numberMA30A1001 or an MOV actuator of similar design.

(2) No more work is necessary. Close access to the MOV actuator. Refer to 767 AMM28-22-11 as an accepted procedure.




(2) Remove the wire bracket and install the new wire bracket on the engine fuel shutoff MOVactuator deflector as given in Figure 20.





61 of 118

















a) If the resistance is less than 0.5 milliohms, the bond is acceptable. Do thefollowing:



62 of 118











Group 1-8, 10:Work Package 9 - ENGINE FUEL SHUTOFF VALVE ACTUATOR (V00026)



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 MOVactuator deflector as given in Figure 21.

NOTE: This change must be made to accomodate any future install of part numberMA30A1001 or an MOV actuator of similar design.

(2) No more work is necessary. Close access to the MOV actuator. Refer to 767 AMM28-22-11 as an accepted procedure.





63 of 118



(2) Remove the wire bracket and install the new wire bracket on the engine fuel shutoff MOVactuator deflector as given in Figure 21.





















64 of 118











Group 9:Work Package 10 - ENGINE FUEL SHUTOFF VALVE ACTUATOR (V00025)











65 of 118


















a) If the resistance is less than 0.5 milliohms, the bond is acceptable. Do thefollowing:



66 of 118











Group 9:Work Package 11 - ENGINE FUEL SHUTOFF VALVE ACTUATOR (V00026)











67 of 118





















68 of 118





{4} Do an operational test of the MOV. Refer to 767 AMM 28-22-11as anaccepted procedure.






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.


(1) Close access to each MOV actuator. Refer to 767 AMM 28-22-12 as an acceptedprocedure.







69 of 118



(3) Do a visual inspection of the adapter plate. If the adapter plate is marked with "SWEENEYENGR CORP", you must use the shim kit when you install the MOV actuator with partnumber MA30A1001.







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 MOVactuator as given in Figure 22. If the adapter is not marked with "SWEENEYENGR CORP", then install the MOV actuator as give in in Figure 7. Refer to 767AMM 28-22-12 as an accepted procedure for the install of the MOV actuatorbody.

4) For the Aft Engine Fuel Crossfeed MOV actuator, install the MOV actuator: Ifthe adapter plate is marked with "SWEENEY ENGR CORP", install the MOVactuator as given in Figure 23. If the adapter is not marked with "SWEENEYENGR CORP", then install the MOV actuator as given in Figure 7. Refer to 767AMM 28-22-12 as an accepted procedure for the install of the MOV actuatorbody.


(b) If the resistance is 1.5 milliohms or greater, the bond is not acceptable. Do thefollowing steps:







70 of 118







{3} For the Forward Engine Fuel Crossfeed MOV actuator, install the MOVactuator: If the adapter plate is marked with "SWEENEY ENGR CORP",install the MOV actuator as given in Figure 22. If the adapter is notmarked with "SWEENEY ENGR CORP", then install the MOV actuatoras given in Figure 7. Refer to 767 AMM 28-22-12 as an acceptedprocedure for the install of the MOV actuator body.

{4} For the Aft Engine Fuel Crossfeed MOV actuator, install the MOVactuator: If the adapter plate is marked with "SWEENEY ENGR CORP",install the MOV actuator as given in Figure 23. If the adapter is notmarked with "SWEENEY ENGR CORP", then install the MOV actuatoras given in Figure 7. Refer to 767 AMM 28-22-12 as an acceptedprocedure for the install of the MOV actuator body.







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)






71 of 118
















(b) If the resistance is 1.5 milliohms or greater, the bond is not acceptable. Do thefollowing steps:









72 of 118














73 of 118


MORE DATAQTYIDENTIFICATIONNAMETASKSTEP

Get access to thepart number mark-ings on the MOV ac-tuator.(a)

3-MOTOR OPERATEDVALVE ACTUATOR(EXISTING)

Get1

Record the partnumber.(a)


Record2

(a) Some airplanes have a quantity of two.

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


Original Issue: July 03, 2008767-28A0090Revision 1 April 01, 2010

74 of 118


FIGURE 2: REMOVE AND KEEP INDEX PLATE(SHEET 1 OF 2)



75 of 118



Make an ink markwith a pen acrossboth the index plateand the adapterplate as a referencefor installation align-ment.

--REFERENCE MARKMake1

Remove lockwirefrom the index platemounting screws.

--LOCKWIRERemove2

3-INDEX PLATEMOUNTING SCREW

Remove / Keep3

Keep for rework.--INDEX PLATERemove / Keep4

FIGURE 2: REMOVE AND KEEP INDEX PLATE(SHEET 2 OF 2)



76 of 118



Remove anodizedmaterial from the in-dex plate locationsusing an abrasivepad. Refer to SWPM20-20-00 as an ac-cepted procedure.

--ANODIZED FINISHRemove1

Clean contact sur-faces. Refer to SW-PM 20-20-00 as anaccepted procedure.

1-INDEX PLATEClean2

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



77 of 118



Measure the electri-cal resistance in mil-liohms from theadapter plate to therear wing spar. Re-fer to SWPM 20-20-00 as an acceptedprocedure.

--ELECTRICAL BONDRESISTANCE

Measure1

Record the electricalresistance in mil-liohms.


Record2

FIGURE 4: MEASURE AND RECORD ELECTRICAL RESISTANCE FROM ADAPTER PLATE TO THEAIRPLANE SURFACE

(SHEET 1 OF 1)



78 of 118



Remove surfacematerial fromadapter plate con-tact surface loca-tions using an abra-sive pad. Refer toSWPM 20-20-00 asan accepted proce-dure.

1-ADAPTER PLATEClean1

Clean contact sur-face locations. Referto SWPM 20-20-00as an accepted pro-cedure.


Use a minimumamount of sealant toreduce squeeze out.

-BMS 5-45 (BMS 5-95optional)

SEALANT, CATEGO-RY 2

Apply3

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



79 of 118



Put index plateagainst adapterplate and hold.


Put / Hold1

Insert the kept screwonly.


Insert2

Tighten screw tohold plate in place.


Tighten3

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



80 of 118


This Figure applies only to: Group 6-8.

This figure has been deleted.


Apply a Faying bondto the index plate.(a)



Apply1

Do not connect thebonding jumper tothe MOV actuator.

1MA30A1001MOTOR OPERATEDVALVE ACTUATOR

Install (New)2

FIGURE 7: INSTALL THE MOV ACTUATOR(SHEET 1 OF 4)



81 of 118



Measure the electri-cal bond resistanceof the Faying bondfrom the mountingfoot of the MOV actu-ator to a point on theprimary airplanestructure. (a) (b)

1-ELECTRICAL BONDRESISTANCE

Measure3

Measure the lengthof bonding jumperfrom the attach pointon the MOV actuatorto the attach pointon the airplanestructure. Use theshortest bondingjumper that allowsno tention. You canselect a length from4-to-6 inches. (a)

1-BONDING JUMPERMeasure4

If you determinedthat the bondingjumper is too short,remove the bondingjumper and do thefollowing sub-tasks.

1-BONDING JUMPERRemove

Select one lengthfrom 4-to-6 inches.(a)

1BACJ40A20-4BONDING JUMPER, 4INCH (OPTIONAL)

Get



Get



Get




82 of 118



Clean the surface ofthe bonding jumperlug and fasteners,and the airplanestructure. (a)

1-BONDING JUMPERClean5

Attach the bondingjumper to the air-plane structure. Usethe shortest bondingjumper that allowsno tension. You canselect a length from4-to-6 inches.

1-BONDING JUMPERAttach

Torque fasteners.(a)

1-BONDING JUMPERTorque



Measure the electri-cal bond of the Fay-ing bond from thelug on the end of thebonding jumper to apoint on the airplanestructure. (a) (c)

1-BONDING JUMPERMeasure

Apply a cap seal tothe bonding jumperfasteners. (a)

1-BONDING JUMPERApply




83 of 118



Attach the bondingjumper to the MOVactuator.

1-BONDING JUMPERAttach7



Measure the electri-cal bond resistanceof the Faying bondfrom the lug on theend of the bondingjumper to the foot onthe MOV actuator.(a) (d) (e)




(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 theairplane structure is less than 2.5 milliohms, the Faying bond is acceptable. If the measured electricalbond 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 bondingjumper to a point on the airplane structure is less than 1.5 milliohms, the Faying bond is acceptable. Ifthe measured electrical bond resistance of the Faying bond is not acceptable, rework the Faying bondas necessary.

(d) If the measured electrical bond resistance of the Faying bond from the lug on the end of the bondingjumper 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 ac-ceptable, rework the Faying bond as necessary

(e) The purpose of this step is to measure the electrical continuity across the manufactured joint of the MOVactuator body.




84 of 118






--AIRPLANE SURFACEClean2

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



85 of 118



Get access to thepart number mark-ings on the MOV ac-tuator.


Get1

Record the partnumber.


Record2

FIGURE 9: INSPECT AND RECORD FUEL JETTISON TRANSFER MOV ACTUATOR PART NUMBER -LEFT

(SHEET 1 OF 1)



86 of 118





Get1



Record2

FIGURE 10: INSPECT AND RECORD FUEL JETTISON TRANSFER MOV ACTUATOR PART NUMBER -RIGHT

(SHEET 1 OF 1)



87 of 118


FIGURE 11: INSPECT AND RECORD FUEL JETTISON NOZZLE MOV ACTUATOR PART NUMBER - LEFT(SHEET 1 OF 2)



88 of 118





Get1



Record2

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



89 of 118


FIGURE 12: INSPECT AND RECORD FUEL JETTISON NOZZLE MOV ACTUATOR PART NUMBER - RIGHT(SHEET 1 OF 2)



90 of 118





Get1



Record2

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



91 of 118





Get1



Record2

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



92 of 118





Get1



Record2

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



93 of 118





Get1



Record2

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



94 of 118





Get1



Record2

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



95 of 118



Get access to thepart number mark-ings on the forwardMOV actuator.


Get1



Record2

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



96 of 118



Get access to thepart number mark-ings on the aft MOVactuator.


Get3



Record4

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



97 of 118





Get1



Record2

FIGURE 18: INSPECT AND RECORD SINGLE ENGINE FUEL CROSSFEED MOV ACTUATOR PART NUMBER- LEFT WING

(SHEET 1 OF 1)



98 of 118






Apply1

Do not connect thebonding jumper tothe MOV actuator.Refer to the AMM asan accepted proce-dure for the install ofthe MOV actuatorbody.


Install (New)2

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



99 of 118



Measure the electri-cal bond resistanceof the Faying bondfrom the mountingfoot of the MOV actu-ator to a point on theprimary airplanestructure. (a) (b)


Measure3

Measure the lengthof bonding jumperfrom the attach pointon the MOV actuatorto the attach pointon the airplanestructure. Use theshortest bondingjumper that allowsno tention. You canselect a length from4-to-6 inches. (a)






Get



Get



Get




100 of 118





Attach the bondingjumper to the air-plane structure. Usethe shortest bondingjumper that allowsno tension. You canselect a length from4-to-6 inches.






Measure the electri-cal bond of the Fay-ing bond from thelug on the end of thebonding jumper to apoint on the airplanestructure. (a) (c)







101 of 118







Measure the electri-cal bond resistanceof the Faying bondfrom the lug on theend of the bondingjumper to the foot onthe MOV actuator.(a) (d) (e)




(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 theairplane structure is less than 2.5 milliohms, the Faying bond is acceptable. If the measured electricalbond 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 bondingjumper to a point on the airplane structure is less than 1.5 milliohms, the Faying bond is acceptable. Ifthe measured electrical bond resistance of the Faying bond is not acceptable, rework the Faying bondas necessary.

(d) If the measured electrical bond resistance of the Faying bond from the lug on the end of the bondingjumper 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 ac-ceptable, rework the Faying bond as necessary





102 of 118


FIGURE 20: REMOVE BRACKET AND INSTALL NEW BRACKET ON ENGINE FUEL SHUTOFF MOVACTUATOR DEFLECTOR - LEFT

(SHEET 1 OF 3)



103 of 118



Disconnect the wireassembly from thesupport bracket.

1-WIRE ASSEMBLYDisconnect1

Make a referencemark with ink alongthe lower edge ofthe wire supportbracket for use as areference line.

1-REFERENCE MARKMake2

Drill out the rivets toremove. Removeand discard the sup-port bracket. (c)

1287T0015-7WIRE SUPPORT AS-SY

Remove3

Countersink lightfrom .01 to .02 inch-es deep on the de-flector at 120 degreeon both sides andinstall rivets in theold support bracketpilot holes as doubleflush plugs. (c) (d)

2BACR15FV6KE7RIVETInstall (New)4

Shave each rivethead and each rivetbutton flush to thepart surface to finishas a double flushplug. (c)

2BACR15FV6KE7RIVETMicroshave


Install (New)5

Countersink on thedeflector at 100 de-grees. Install thenew support bracketon the deflector. (c)(d)

2BACR15BA5AD7CRIVET, 100 DEGInstall (New)

Clean and preparethe surface area forfinish. (e)

1112T1074-5DEFLECTOR, REARSPAR WING

Clean6

(a) (b)-BAC5626, TYPE 2,CLASS A OR D

COLORED CHEMICALCONVERSION COAT-ING

Apply7

(a) (b)-BMS 10-11, TYPE 1PRIMERApply


(SHEET 2 OF 3)



104 of 118



1-WIRE ASSEMBLYConnect8

(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.


(SHEET 3 OF 3)



105 of 118


FIGURE 21: REMOVE BRACKET AND INSTALL NEW BRACKET ON ENGINE FUEL SHUTOFF MOVACTUATOR DEFLECTOR - RIGHT

(SHEET 1 OF 3)



106 of 118



Disconnect the wireassembly from thesupport bracket.

1-WIRE ASSEMBLYDisconnect1

Make a referencemark with ink alongthe lower edge ofthe wire supportbracket for use as areference line.

1-REFERENCE MARKMake2

Drill out the rivets toremove. Removeand discard the sup-port bracket. (c)


Remove3

Countersink lightfrom .01 to .02 inch-es deep on the de-flector at 120 degreeon both sides andinstall rivets in theold support bracketpilot holes as doubleflush plugs. (c)(d)

2BACR15FV6KE7RIVETInstall (New)4

Shave each rivethead and each rivetbutton flush to thepart surface to finishas a double flushplug. (c)

2BACR15FV6KE7RIVETMicroshave


Install (New)5

Countersink on thedeflector at 100 de-grees. Install thenew support bracketon the deflector. (c)(d)

2BACR15BA5AD7CRIVET, 100 DEGInstall (New)

Clean and preparethe surface area forfinish. (e)

1112T1074-6DEFLECTOR, REARSPAR WING

Clean6

(a) (b)-BAC5626, TYPE 2,CLASS A OR D

COLORED CHEMICALCONVERSION COAT-ING

Apply7

(a) (b)-BMS 10-11, TYPE 1PRIMERApply


(SHEET 2 OF 3)



107 of 118



1-WIRE ASSEMBLYConnect8

(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.


(SHEET 3 OF 3)



108 of 118


This Figure applies only to: Group 1-5, 9-10.

FIGURE 22: INSTALL THE SHIM AND FORWARD ENGINE FUEL CROSSFEED MOV ACTUATOR(SHEET 1 OF 5)



109 of 118






Apply1

Install on indexplate.

1343T0002-29SHIM - SWEENEYMOV ADAPTER

Install (New)2

Apply a Faying bondto the shim platearound the holes.



Apply3

Do not connect theBonding Jumper tothe MOV actuator.


Install (New)4

4BACS12HM08AH10SCREWInstall (New)

Measure the electri-cal bonding resis-tance of the Fayingbond for the mount-ing foot of the MOVactuator to a pointon the primary air-plane structure. (a)(b)


Measure5




110 of 118



Measure the lengthof the bondingjumper from the at-tach point on theMOV actuator to theattach point on theairplane structure.Use the shortestbonding jumper thatallows no tension.You can select alength from 4-to-6inches. (a)




You can select alength from 4-to-6inches. (a)


Get


Get


Get

Clean the surface ofthe bonding jumperlug, fasteners, andthe airplane struc-ture. (a)

--BONDING JUMPERClean7

Attach the bondingjumper to the air-plane structure. Usethe shortest bondingjumper that allowsno tension. You canselect a length from4-to-6 inches. (a)







111 of 118



Clean the surface ofthe bonding jumperlug, fasteners, andMOV actuator. (a)


Measure the electri-cal bonding resis-tance of the Fayingbond from the lug onthe end of the bond-ing jumper to a pointon the airplanestructure. (a) (c)

--ELECTRICAL BONDMeasure


-BMS 5-142, CLASS B(BMS 5-45, CLASS Bor BMS 5-95, CLASS Boptional)

SEALANT, LOW DEN-SITY

Apply





Measure the electri-cal bonding resis-tance of the Fayingbond from the lug onthe end of the bond-ing jumper that is in-stalled at the MOVactuator to the footon the MOV actua-tor. (a) (d) (e)


Measure




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 theairplane structure is less than 2.5 milliohms, the Faying bond is acceptable. If the measured electricalbonding 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 bondingjumper to a point on the airplane structure is less than 1.5 milliohms, the Faying bond is acceptable. Ifthe measured electrical bonding resistance of the Faying bond is not acceptable, rework the Faying bondas necessary.




112 of 118



(d) If the measured electrical bonding resistance of the Faying bond from the lug on the end of the bondingjumper 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 notacceptable, rework the Faying bond as necessary.





113 of 118


This Figure applies only to: Group 1-5, 9-10.

FIGURE 23: INSTALL THE SHIM AND AFT ENGINE FUEL CROSSFEED MOV ACTUATOR(SHEET 1 OF 5)



114 of 118






Apply1

Install on indexplate.

1343T0002-29SHIM - SWEENEYMOV ADAPTER

Install (New)2

Apply a Faying bondto the shim platearound the holes.

-BMS5-45SEALANT, CATEGO-RY 2

Apply3

Do not connect theBonding Jumper tothe MOV actuator.


Install (New)4

4BACS12HM08AH10SCREWInstall (New)

Measure the electri-cal bonding resis-tance of the Fayingbond for the mount-ing foot of the MOVactuator to a pointon the primary air-plane structure. (a)(b)


Measure5




115 of 118



Measure the lengthof the bondingjumper from the at-tach point on theMOV actuator to theattach point on theairplane structure.Use the shortestbonding jumper thatallows no tension.You can select alength from 4-to-6inches. (a)




You can select alength from 4-to-6inches. (a)


Get


Get


Get

Clean the surface ofthe bonding jumperlug, fasteners, andthe airplane struc-ture. (a)

--BONDING JUMPERClean7

Attach the bondingjumper to the air-plane structure. Usethe shortest bondingjumper that allowsno tension. You canselect a length from4-to-6 inches. (a)







116 of 118



Clean the surface ofthe bonding jumperlug, fasteners, andMOV actuator. (a)


Measure the electri-cal bonding resis-tance of the Fayingbond from the lug onthe end of the bond-ing jumper to a pointon the airplanestructure. (a) (c)

--ELECTRICAL BONDMeasure




Apply





Measure the electri-cal bonding resis-tance of the Fayingbond from the lug onthe end of the bond-ing jumper that is in-stalled at the MOVactuator to the footon the MOV actua-tor. (a) (d) (e)


Measure




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 theairplane structure is less than 2.5 milliohms, the Faying bond is acceptable. If the measured electricalbonding 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 bondingjumper to a point on the airplane structure is less than 1.5 milliohms, the Faying bond is acceptable. Ifthe measured electrical bonding resistance of the Faying bond is not acceptable, rework the Faying bondas necessary.




117 of 118



(d) If the measured electrical bonding resistance of the Faying bond from the lug on the end of the bondingjumper 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 notacceptable, rework the Faying bond as necessary.





118 of 118


Commercial Airplanes 767 - ltt- · PDF fileCommercial Airplanes 767 Service ... Group...

Documents

Transcript of Commercial Airplanes 767 - ltt- · PDF fileCommercial Airplanes 767 Service ... Group...