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.

ECCN: 9E991

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Unpublished Work - All Rights Reserved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

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2.0
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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

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BOEING SERVICE BULLETIN 767-28A0090
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

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 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

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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.

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Pages with no vertical lines have no important changes.

REVISION HISTORY

Original Issue: July 03, 2008

Revision 1: April 01, 2010

Revision 2: September 02, 2010

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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.

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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

Airplanes Total Task Hours Elapsed Hours

Group 1.0 437.45 (a)(b) 188.95 (a)(b)

Group 2.0 437.45 (a)(b) 188.95 (a)(b)

Group 3.0 227.15 (a)(b) 104.65 (a)(b)

Group 4.0 227.15 (a)(b) 104.65 (a)(b)

Group 5.1 440.05 (a)(b) 191.05 (a)(b)

Group 5.2 429.30 (a)(b) 182.30 (a)(b)

Group 6.1 229.75 (a)(b) 104.75 (a)(b)

Group 6.2 219.00 (a)(b) 96.00 (a)(b)

Group 7.1 440.05 (a)(b) 191.05 (a)(b)

Group 7.2 229.75 (a)(b) 104.75 (a)(b)

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BOEING SERVICE BULLETIN 767-28A0090
Airplanes Total Task Hours Elapsed Hours

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

Group 7.4 219.00 (a)(b) 96.00 (a)(b)

Group 8.1 229.75 (a)(b) 104.75 (a)(b)

Group 8.2 219.00 (a)(b) 96.00 (a)(b)

Group 9.0 485.90 (a)(b) 206.90 (a)(b)

Group 10.1 440.05 (a)(b) 191.05 (a)(b)

Group 10.2 229.75 (a)(b) 104.57 (a)(b)

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

Group 10.4 219.00 (a)(b) 96.00 (a)(b)

(a) Entry into the fuel tank should not be frequent.

(b) If entry into the fuel tank is not necessary, the time

needed to do the work is much less.

MATERIAL INFORMATION

Operator Supplied Parts.

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

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BOEING SERVICE BULLETIN 767-28A0090
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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.

GROUP CONFIGURATION DESCRIPTION

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 -

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GROUP CONFIGURATION DESCRIPTION

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 -

1 Made changes as given in Boeing service bulletin 767-28-0034.

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 -

1 Made changes as given in Boeing service bulletin 767-28-0034.

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

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BOEING SERVICE BULLETIN 767-28A0090
GROUP CONFIGURATION DESCRIPTION

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 -

1 Made changes as given in Boeing service bulletin 767-28-0034.

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

Variable Number Group

VA001 - VA020 8

VA301 - VA315 8

VA501 - VA526 8

VA527 - VA530 6

VA701 - VA712 8

VA713 - VA719 6

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BOEING SERVICE BULLETIN 767-28A0090
Variable Number Group

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 8

VB325 - VB332 6

VB371 - VB373 8

VB401 8

VB441 - VB444 4

VE001 - VE002 8

VE003 6

VE021 - VE023 8

VE041 - VE043 8

VE061 - VE069 8

VE083 - VE084 8

VE085 - VE086 6

VE101 - VE103 8

VE104 6

VE116 - VE117 8

VE118 6

VE121 - VE126 8

VE141 - VE143 8

VE144 - VE151 6

VE152 4

VE171 - VE172 6

VF001 - VF002 7

VF041 - VF042 7

VF051 7

VF061 - VF062 5

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BOEING SERVICE BULLETIN 767-28A0090
Variable Number Group

VF071 - VF072 5

VF091 - VF093 5

VF101 - VF102 5

VF161 5

VF162 2

VF171 - VF172 2

VF180 2

VF181 - VF184 1

VF251 2

VK001 - VK004 8

VK005 - VK011 6

VK012 - VK016 4

VK021 - VK022 6

VK031 - VK054 8

VK055 - VK056 3

VK081 - VK083 8

VK084 - VK099 6

VK100 - VK113 4

VK131 - VK133 6

VK141 - VK142 6

VK143 - VK148 4

VK161 6

VK162 - VK164 4

VK171 4

VK181 4

VK186 4

VL001 10

VL002 - VL006 7

VL011 10

VL701 - VL703 2

VL751 - VL755 2

VL806 - VL807 2

VL871 - VL873 2

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BOEING SERVICE BULLETIN 767-28A0090
Variable Number Group

VL891 - VL900 2

VL911 - VL914 2

VL931 - VL932 2

VL941 2

VN001 - VN015 7

VN016 - VN020 5

VN021 - VN041 2

VN051 - VN058 7

VN059 - VN064 5

VN081 - VN085 7

VN086 - VN092 5

VN093 - VN099 2

VN111 - VN115 7

VN116 - VN124 5

VN125 - VN127 2

VN130 - VN132 5

VN133 - VN137 2

VN151 - VN155 7

VN156 - VN158 5

VN163 - VN168 5

VN171 - VN173 7

VN174 2

VN191 - VN192 7

VN193 5

VN194 - VN198 2

VN211 - VN212 7

VN221 7

VN222 - VN224 5

VN225 2

VN231 - VN234 5

VN241 6

VN242 - VN243 2

VN251 - VN260 5

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BOEING SERVICE BULLETIN 767-28A0090
Variable Number Group

VN261 - VN276 2

VN291 5

VN292 - VN293 2

VN301 - VN306 5

VN307 - VN314 2

VN371 - VN372 5

VN376 5

VN381 5

VN382 - VN388 2

VN421 - VN427 2

VN436 2

VN471 - VN472 5

VN491 - VN497 5

VN498 - VN513 2

VN531 - VN532 5

VN536 - VN537 5

VN541 - VN542 5

VN546 - VN547 2

VN551 5

VN556 - VN557 2

VN561 - VN562 2

VN631 - VN633 5

VN634 - VN638 2

VN651 - VN652 5

VN653 - VN658 2

VN671 - VN672 5

VN676 2

VN681 - VN683 5

VN684 - VN691 2

VN731 5

VN732 2

VN751 - VN753 5

VN791 - VN792 2

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BOEING SERVICE BULLETIN 767-28A0090
Variable Number Group

VN811 - VN813 2

VN921 - VN922 2

VN931 - VN936 2

VN951 - VN953 2

VN966 - VN972 2

VQ001 - VQ021 9

VQ071 - VQ086 9

VR051 - VR060 1

VR081 1

VR084 1

VR086 - VR087 1

VR106 1

VR201 - VR209 2

VR210 - VR211 1

VR251 2

VR256 - VR257 2

VR258 - VR260 1

VR401 4

VR421 - VR423 4

VR426 4

VR441 4

VR461 4

VR471 - VR472 3

VS051 - VS056 2

VS061 2

VS066 - VS070 2

VS073 - VS078 2

VS091 - VS102 2

VS103 - VS104 1

VS111 - VS113 2

VS131 - VS133 2

VS136 - VS137 2

VS176 - VS177 2

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BOEING SERVICE BULLETIN 767-28A0090
Variable Number Group

VS186 - VS187 2

VS196 - VS203 2

VS206 - VS208 2

VS211 2

VS216 - VS217 2

VS231 1

VS246 - VS248 2

VS261 - VS262 2

VS263 1

VS266 - VS274 2

VS291 2

VS292 - VS293 1

VS301 - VS302 2

VS303 1

VS306 - VS307 2

VS308 - VS311 1

VS316 2

VS321 - VS324 2

VS331 - VS333 1

VS336 - VS337 1

VS366 - VS367 2

VS381 - VS382 2

VS391 - VS392 2

VS401 2

VS426 - VS428 1

VS466 - VS470 2

VS471 - VS472 1

VS486 2

VS496 2

VS497 1

VS506 - VS507 2

VS526 1

VS546 - VS549 1

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BOEING SERVICE BULLETIN 767-28A0090
Variable Number Group

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 1

VW701 - VW721 2

VW851 2

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.

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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:

Additional Work - Reason

Work Package(s)

Original Group

(Original Release)

New Group (Revision 1)Variable No.

VN921 2 3 (a) (b)

VN922 2 3 (a) (b)

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BOEING SERVICE BULLETIN 767-28A0090
Additional Work - Reason

Work Package(s)

Original Group

(Original Release)

New Group (Revision 1)Variable No.

VN966 2 3 (a) (b)

VN967 2 3 (a) (b)

VN968 2 3 (a) (b)

VN969 2 3 (a) (b)

VN970 2 3 (a) (b)

VN971 2 3 (a) (b)

VN972 2 3 (a) (b)

(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

Model Zone

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

641, 651

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

Group 3, 10:

Affected Maintenance Zones

Model Zone

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

641, 651

767-300

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BOEING SERVICE BULLETIN 767-28A0090
Group 4-8:

Affected Maintenance Zones

Model Zone

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

641, 651

767-200, 767-300

Group 9:

Affected Maintenance Zones

Model Zone

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:

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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

Work Package No. MOV Actuator Equipment No.

1 V00108/V00109/V00123

2 V00159

3 V00160

4 V00157

5 V00158

6 V00096

7 V00097

8 V00025

9 V00026

10 V00025

11 V00026

12 V00388/V00389

13 V00024

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BOEING SERVICE BULLETIN 767-28A0090
Elapsed

Hours

Number of Task Hours

Persons

Work Package Tasks

Work Package 1 Prepare 2 1.00 0.50

Open MOV ac- 1 0.10 0.10

tuator access

Figure 1 1 0.25 0.25

Remove MOV 1 0.25 0.25

actuator

Figure 2 1 1.00 1.00

Figure 3 1 1.00 1.00

Figure 4 1 0.50 0.50

MOV access/ 4 32.0 8.00

fuel tank entry

(a)

Remove 2 2.00 1.00

adapter plate

and adapter

shaft (a)

Figure 8 (a) 1 1.00 1.00

Install adapter 2 2.00 1.00

plate and

adapter shaft

(a)

Figure 4 (a) 1 0.50 0.50

Figure 5 1 1.50 1.50

Figure 6 1 0.50 0.50

Install index 1 0.50 0.50

plate

Install MOV ac- 1 0.25 0.25

tuator

Close MOV ac- 2 8.00 4.00

cess in fuel

tank

Close MOV ac- 1 0.10 0.10

tuator access

Total for Work Package 52.45 21.95

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BOEING SERVICE BULLETIN 767-28A0090
Elapsed

Hours

Number of Task Hours

Persons

Work Package Tasks

Work Package 2 Prepare 2 1.00 0.50

Open MOV ac- 1 0.10 0.10

tuator access

Figure 9 1 0.25 0.25

Remove MOV 1 0.25 0.25

actuator

Figure 2 1 1.00 1.00

Figure 3 1 1.00 1.00

Figure 4 1 0.50 0.50

MOV access/ 4 32.0 8.00

fuel tank entry

(a)

Remove 2 2.00 1.00

adapter plate

and adapter

shaft (a)

Figure 8 (a) 1 1.00 1.00

Install adapter 2 2.00 1.00

plate and

adapter shaft

(a)

Figure 4 (a) 1 0.50 0.50

Figure 5 1 1.50 1.50

Figure 6 1 0.50 0.50

Install index 1 0.50 0.50

plate

Install MOV ac- 1 0.25 0.25

tuator

Close MOV ac- 2 8.00 4.00

cess in fuel

tank

Close MOV ac- 1 0.10 0.10

tuator access

Total for Work Package 52.45 21.95

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BOEING SERVICE BULLETIN 767-28A0090
Elapsed

Hours

Number of Task Hours

Persons

Work Package Tasks

Work Package 3 Prepare 2 1.00 0.50

Open MOV ac- 1 0.10 0.10

tuator access

Figure 10 1 0.25 0.25

Remove MOV 1 0.25 0.25

actuator

Figure 2 1 1.00 1.00

Figure 3 1 1.00 1.00

Figure 4 1 0.50 0.50

MOV access/ 4 32.0 8.00

fuel tank entry

(a)

Remove 2 2.00 1.00

adapter plate

and adapter

shaft (a)

Figure 8 (a) 1 1.00 1.00

Install adapter 2 2.00 1.00

plate and

adapter shaft

(a)

Figure 4 (a) 1 0.50 0.50

Figure 5 1 1.50 1.50

Figure 6 1 0.50 0.50

Install index 1 0.50 0.50

plate

Install MOV ac- 1 0.25 0.25

tuator

Close MOV ac- 2 8.00 4.00

cess in fuel

tank

Close MOV ac- 1 0.10 0.10

tuator access

Total for Work Package 52.45 21.95

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BOEING SERVICE BULLETIN 767-28A0090
Elapsed

Hours

Number of Task Hours

Persons

Work Package Tasks

Work Package 4 Prepare 2 1.00 0.50

Open MOV ac- 1 0.10 0.10

tuator access

Figure 11 1 0.50 0.50

Remove MOV 1 0.25 0.25

actuator

Figure 2 1 1.00 1.00

Figure 3 1 1.00 1.00

Figure 4 1 0.50 0.50

MOV access/ 4 32.0 8.00

fuel tank entry

(a)

Remove 2 2.00 1.00

adapter plate

and adapter

shaft (a)

Figure 8 (a) 1 1.00 1.00

Install adapter 2 2.00 1.00

plate and

adapter shaft

(a)

Figure 4 (a) 1 0.50 0.50

Figure 5 1 1.50 1.50

Figure 6 1 0.50 0.50

Install index 1 0.50 0.50

plate

Install MOV ac- 1 0.25 0.25

tuator

Close MOV ac- 2 8.00 4.00

cess in fuel

tank

Close MOV ac- 1 0.10 0.10

tuator access

Total for Work Package 52.70 21.20

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BOEING SERVICE BULLETIN 767-28A0090
Elapsed

Hours

Number of Task Hours

Persons

Work Package Tasks

Work Package 5 Prepare 2 1.00 0.50

Open MOV ac- 1 0.10 0.10

tuator access

Figure 12 1 0.50 0.50

Remove MOV 1 0.25 0.25

actuator

Figure 2 1 1.00 1.00

Figure 3 1 1.00 1.00

Figure 4 1 0.50 0.50

MOV access/ 4 32.0 8.00

fuel tank entry

(a)

Remove 2 2.00 1.00

adapter plate

and adapter

shaft (a)

Figure 8 (a) 1 1.00 1.00

Install adapter 2 2.00 1.00

plate and

adapter shaft

(a)

Figure 4 (a) 1 0.50 0.50

Figure 5 1 1.50 1.50

Figure 6 1 0.50 0.50

Install index 1 0.50 0.50

plate

Install MOV ac- 1 0.25 0.25

tuator

Close MOV ac- 2 8.00 4.00

cess in fuel

tank

Close MOV ac- 1 0.10 0.10

tuator access

Total for Work Package 52.70 21.20

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BOEING SERVICE BULLETIN 767-28A0090
Elapsed

Hours

Number of Task Hours

Persons

Work Package Tasks

Work Package 6 Prepare 2 1.00 0.50

Open MOV ac- 1 0.10 0.10

tuator access

Figure 13 1 0.50 0.50

Remove MOV 1 0.25 0.25

actuator

Install MOV ac- 1 0.25 0.25

tuator

Close MOV ac- 1 0.50 0.50

tuator access

Total for Work Package 2.60 2.10

Work Package 7 Prepare 2 1.00 0.50

Open MOV ac- 1 0.10 0.10

tuator access

Figure 14 1 0.50 0.50

Remove MOV 1 0.25 0.25

actuator

Install MOV ac- 1 0.25 0.25

tuator

Close MOV ac- 1 0.50 0.50

tuator access

Total for Work Package 2.60 2.10

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BOEING SERVICE BULLETIN 767-28A0090
Elapsed

Hours

Number of Task Hours

Persons

Work Package Tasks

Work Package 8 Prepare 2 1.00 0.50

Open MOV ac- 1 0.10 0.10

tuator access

Figure 15 1 0.25 0.25

Remove MOV 1 0.25 0.25

actuator

Figure 20 1 2.00 2.00

Figure 2 1 1.00 1.00

Figure 3 1 1.00 1.00

Figure 4 1 0.50 0.50

MOV access/ 4 32.0 8.00

fuel tank entry

(a)

Remove 2 2.00 1.00

adapter plate

and adapter

shaft (a)

Figure 8 (a) 1 1.00 1.00

Install adapter 2 2.00 1.00

plate and

adapter shaft

(a)

Figure 4 (a) 1 0.50 0.50

Figure 5 1 1.50 1.50

Figure 6 1 0.50 0.50

Install index 1 0.50 0.50

plate

Install MOV ac- 1 0.25 0.25

tuator

Close MOV ac- 2 8.00 4.00

cess in fuel

tank

Close MOV ac- 1 0.10 0.10

tuator access

Total for Work Package 54.45 23.95

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BOEING SERVICE BULLETIN 767-28A0090
Elapsed

Hours

Number of Task Hours

Persons

Work Package Tasks

Work Package 9 Prepare 2 1.00 0.50

Open MOV ac- 1 0.10 0.10

tuator access

Figure 16 1 0.25 0.25

Remove MOV 1 0.25 0.25

actuator

Figure 21 1 2.00 2.00

Figure 2 1 1.00 1.00

Figure 3 1 1.00 1.00

Figure 4 1 0.50 0.50

MOV access/ 4 32.0 8.00

fuel tank entry

(a)

Remove 2 2.00 1.00

adapter plate

and adapter

shaft (a)

Figure 8 (a) 1 1.00 1.00

Install adapter 2 2.00 1.00

plate and

adapter shaft

(a)

Figure 4 (a) 1 0.50 0.50

Figure 5 1 1.50 1.50

Figure 6 1 0.50 0.50

Install index 1 0.50 0.50

plate

Install MOV ac- 1 0.25 0.25

tuator

Close MOV ac- 2 8.00 4.00

cess in fuel

tank

Close MOV ac- 1 0.10 0.10

tuator access

Total for Work Package 54.45 23.95

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32 of 119

BOEING SERVICE BULLETIN 767-28A0090
Elapsed

Hours

Number of Task Hours

Persons

Work Package Tasks

Work Package 10 Prepare 2 1.00 0.50

Open MOV ac- 1 0.10 0.10

tuator access

Figure 15 1 0.25 0.25

Remove MOV 1 0.25 0.25

actuator

Figure 2 1 1.00 1.00

Figure 3 1 1.00 1.00

Figure 4 1 0.50 0.50

MOV access/ 4 32.0 8.00

fuel tank entry

(a)

Remove 2 2.00 1.00

adapter plate

and adapter

shaft (a)

Figure 8 (a) 1 1.00 1.00

Install adapter 2 2.00 1.00

plate and

adapter shaft

(a)

Figure 4 (a) 1 0.50 0.50

Figure 5 1 1.50 1.50

Figure 6 1 0.50 0.50

Install index 1 0.50 0.50

plate

Install MOV ac- 1 0.25 0.25

tuator

Close MOV ac- 2 8.00 4.00

cess in fuel

tank

Close MOV ac- 1 0.10 0.10

tuator access

Total for Work Package 52.45 21.95

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33 of 119

BOEING SERVICE BULLETIN 767-28A0090
Elapsed

Hours

Number of Task Hours

Persons

Work Package Tasks

Work Package 11 Prepare 2 1.00 0.50

Open MOV ac- 1 0.10 0.10

tuator access

Figure 16 1 0.25 0.25

Remove MOV 1 0.25 0.25

actuator

Figure 2 1 1.00 1.00

Figure 3 1 1.00 1.00

Figure 4 1 0.50 0.50

MOV access/ 4 32.0 8.00

fuel tank entry

(a)

Remove 2 2.00 1.00

adapter plate

and adapter

shaft (a)

Figure 8 (a) 1 1.00 1.00

Install adapter 2 2.00 1.00

plate and

adapter shaft

(a)

Figure 4 (a) 1 0.50 0.50

Figure 5 1 1.50 1.50

Figure 6 1 0.50 0.50

Install index 1 0.50 0.50

plate

Install MOV ac- 1 0.25 0.25

tuator

Close MOV ac- 2 8.00 4.00

cess in fuel

tank

Close MOV ac- 1 0.10 0.10

tuator access

Total for Work Package 52.45 21.95

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Elapsed

Hours

Number of Task Hours

Persons

Work Package Tasks

Work Package 12 Prepare 2 1.00 0.50

Open MOV ac- 1 0.10 0.10

tuator access

Figure 17 1 0.25 0.25

Remove MOV 1 0.25 0.25

actuator

Figure 2 (b) 1 2.00 2.00

Figure 3 (b) 1 2.00 2.00

Figure 4 (b) 1 1.00 1.00

MOV access/ 4 32.0 8.00

fuel tank entry

(a)

Remove 2 4.00 2.00

adapter plate

and adapter

shaft (a)(b)

Figure 8. (a)(b) 1 2.00 2.00

Install adapter 2 4.00 2.00

plate and

adapter shaft

(a)(b)

Figure 4 (a)(b) 1 1.00 1.00

Figure 5 (b) 1 3.00 3.00

Figure 6 (b) 1 1.00 1.00

Install index 1 1.00 1.00

plate (b)

Install MOV ac- 1 0.50 0.50

tuator (b)(c)

Close MOV ac- 2 8.00 4.00

cess in fuel

tank

Close MOV ac- 1 0.10 0.10

tuator access

Total for Work Package 63.20 30.70

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Elapsed

Hours

Number of Task Hours

Persons

Work Package Tasks

Work Package 13 Prepare 2 1.00 0.50

Open MOV ac- 1 0.10 0.10

tuator access

Figure 18 1 0.25 0.25

Remove MOV 1 0.25 0.25

actuator

Figure 2 1 1.00 1.00

Figure 3 1 1.00 1.00

Figure 4 1 0.50 0.50

MOV access/ 4 32.0 8.00

fuel tank entry

(a)

Remove 2 2.00 1.00

adapter plate

and adapter

shaft (a)

Figure 8. (a) 1 1.00 1.00

Install adapter 2 2.00 1.00

plate and

adapter shaft

(a)

Figure 4 (a) 1 0.50 0.50

Figure 5 1 1.50 1.50

Figure 6 1 0.50 0.50

Install index 1 0.50 0.50

plate

Install MOV ac- 1 0.25 0.25

tuator

Close fuel tank 2 8.00 4.00

access (a)

Close MOV ac- 1 0.10 0.10

tuator access

Total for Work Package 52.45 21.95

(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

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Elapsed

Hours

Number of Task Hours

Persons

Work Package Tasks

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

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

Work Package 1 52.45 21.95

Work Package 2 52.45 21.95

Work Package 3 52.45 21.95

Work Package 4 52.70 21.20

Work Package 5 52.70 21.20

Work Package 6 2.60 2.10

Work Package 8 54.45 23.95

Work Package 9 54.45 23.95

Work Package 12 63.20 30.70

TOTAL FOR EACH AIRPLANE 437.45 188.95

(a) See the work package tables for details.

Group 3-4:

Only the Work Packages for these Groups

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

Work Package 1 52.45 21.95

Work Package 6 2.60 2.10

Work Package 8 54.45 23.95

Work Package 9 54.45 23.95

Work Package 12 63.20 30.70

TOTAL FOR EACH AIRPLANE 227.15 104.65

(a) See the work package tables for details.

Group 5, 7, 10, Configuration 1:

Only the Work Packages for these Groups

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

Work Package 1 52.45 21.95

Work Package 2 52.45 21.95

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Group 5, 7, 10, Configuration 1:

Only the Work Packages for these Groups

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

Work Package 3 52.45 21.95

Work Package 4 52.70 21.20

Work Package 5 52.70 21.20

Work Package 6 2.60 2.10

Work Package 7 2.60 2.10

Work Package 8 54.45 23.95

Work Package 9 54.45 23.95

Work Package 12 63.20 30.70

TOTAL FOR EACH AIRPLANE 440.05 191.05

(a) See the work package tables for details.

Group 5, Configuration 2; Group 7, 10, Configuration 3:

Only the Work Packages for these Groups

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

Work Package 1 52.45 21.95

Work Package 2 52.45 21.95

Work Package 3 52.45 21.95

Work Package 4 52.70 21.20

Work Package 5 52.70 21.20

Work Package 6 2.60 2.10

Work Package 7 2.60 2.10

Work Package 8 54.45 23.95

Work Package 9 54.45 23.95

Work Package 13 52.45 21.95

TOTAL FOR EACH AIRPLANE 429.30 182.30

(a) See the work package tables for details.

Group 6, Configuration 1; Group 7, Configuration 2; Group 8, Configuration 1; Group 10, Configuration 2:

Only the Work Packages for these Groups

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

Work Package 1 52.45 21.95

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Group 6, Configuration 1; Group 7, Configuration 2; Group 8, Configuration 1; Group 10, Configuration 2:

Only the Work Packages for these Groups

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

Work Package 6 2.60 2.10

Work Package 7 2.60 2.10

Work Package 8 54.45 23.95

Work Package 9 54.45 23.95

Work Package 12 63.20 30.70

TOTAL FOR EACH AIRPLANE 229.75 104.75

(a) See the work package tables for details.

Group 6, Configuration 2; Group 7, Configuration 4; Group 8, Configuration 2; Group 10, Configuration 4:

Only the Work Packages for these Groups

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

Work Package 1 52.45 21.95

Work Package 6 2.60 2.10

Work Package 7 2.60 2.10

Work Package 8 54.45 23.95

Work Package 9 54.45 23.95

Work Package 13 52.45 21.95

TOTAL FOR EACH AIRPLANE 219.00 96.00

(a) See the work package tables for details.

Group 9:

Only the Work Packages for these Groups

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

Work Package 1 52.45 21.95

Work Package 2 52.45 21.95

Work Package 3 52.45 21.95

Work Package 4 52.70 21.20

Work Package 5 52.70 21.20

Work Package 6 2.60 2.10

Work Package 10 52.45 21.95

Work Package 11 52.45 21.95

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Group 9:

Only the Work Packages for these Groups

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

Work Package 12 63.20 30.70

Work Package 13 52.45 21.95

TOTAL FOR EACH AIRPLANE 485.90 206.90

(a) See the work package tables for details.

H. Weight and Balance Changes

Change in Moment

(Pound-Inches)

Change in Weight

(Pounds)

Airplane

767-200 +4.4 +6028.0

767-300 +4.4 +6608.9

Change in Moment

(Pound-Inches)

Change in Weight

(Pounds)

Work Package

Work Package 1 (a) +0.4 +465.1

Work Package 2 +0.4 +465.3

Work Package 3 +0.4 +465.3

Work Package 4 +0.4 +582.4

Work Package 5 +0.4 +582.4

Work Package 6 +0.4 +474.0

Work Package 7 +0.4 +474.0

Work Package 8 +0.4 +483.2

Work Package 9 +0.4 +483.2

Work Package 10 +0.4 +483.2

Work Package 11 +0.4 +483.2

Work Package 12 (a) +0.4 +466.6

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

I. Electrical Load Data

Not changed.

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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:

Drawing Number Title

343T0002 Equipment - Engine Fuel Feed System

346T0004 APU Fuel Feed Syst - Wing

344T0002 Equipment Instl - Refueling System

340T0007 Fuel System Diagram

K. Publications Affected

1. Publications:

Publication Chapter-Section

767 Airplane Maintenance Manual (AMM) 28-22, 28-25, 28-26, 28-31

767 Illustrated parts Catalog (IPC) 28-22, 28-25, 28-26, 28-31

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BOEING SERVICE BULLETIN 767-28A0090
Publication Chapter-Section

767 Maintenance Planning Data (MPD) document 9

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.

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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)

Kit Number Name Date QTY

Top Kit - Bracket Installa- Available 60 23 280.00

tion

015T1805-1

Top Kit - Bracket Installa- JAN 30/08 30 23

tion

015T1805-1

Top Kit - Bracket Installa- FEB 29/08 30 23

tion

015T1805-1

Top Kit - Bracket Installa- MAR 31/08 30 23

tion

015T1805-1

Top Kit - Bracket Installa- APR 29/08 30 23

tion

015T1805-1

Top Kit - Bracket Installa- MAY 29/08 30 23

tion

015T1805-1

Top Kit - Bracket Installa- JUL 07/08 30 23

tion

015T1805-1

Top Kit - Bracket Installa- JUL 30/08 10 23

tion

015T1805-1

Top Kit - Bracket Install Available 225 30 716.00

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

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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

Top Kit 20 21 22 23

015T1805-1 1 1 - -

015T1805-2 1 1 1 1

Group 6-8:

KIT 015T1805-1

NOTES

Existing Part

Name Number

Figure

New Part Number

20 21

QTY

WIRE SUPPORT

ASSY

287T0015-723 1 1

BACR15BA5AD7C 2 2 RIVET, 100 DEG

BACR15FV6KE7 2 2 RIVET

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Group 1-5, 9-10:

KIT 015T1805-2

NOTES

Existing Part

Name Number

Figure

New Part Number

20 21 22 23

QTY

WIRE SUPPORT

ASSY

287T0015-723 1 1

SHIM - SWEENEY

MOV ADAPTER

343T0002-29 1 1

BACR15BA5AD7C 2 2 RIVET, 100 DEG

BACR15FV6KE7 2 2 RIVET

BACS12HM08AH10 4 4 SCREW

2. Parts and Materials Supplied by the Operator:

Part Number / QTY Name Notes

Specification

Replaces MA20A1001-1

(S343T003-39)

MOTOR OPERATED VALVE ACTUATORMA30A1001 11

(S343T003-66) (a)

BMS 5-45 22 oz. SEALANT, CATEGORY 2 (b)(e)

BMS 5-142 22 oz. SEALANT, LOW DENSITY (c)

COLORED CHEMICAL CONVERSION COATINGBAC5626, TYPE 2 4 oz.

CLASS A OR D

BMS 10-11, TYPE 4 oz. PRIMER

1

BONDING JUMPER, 4 INCH (OP- (d)

TIONAL)

BACJ40A20-4 11

BONDING JUMPER, 5 INCH (OP- (d)

TIONAL)

BACJ40A20-5 11

BONDING JUMPER, 6 INCH (OP- (d)

TIONAL)

BACJ40A20-6 11

(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.

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Part Number / QTY Name Notes

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:

Existing Part Name QTY Notes

Number

Bracket removed from

each deflector located at

the engine fuel shutoff

MOV actuator.

WIRE SUPPORT 2

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.

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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.

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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:

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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:

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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:

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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:

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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:

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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:

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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:

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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:

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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:

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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:

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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.

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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.

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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:

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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:

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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:

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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.

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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:

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{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.

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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:

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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.

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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.

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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.

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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.

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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.

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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.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

Get access to the

part number markings on the MOV actuator.(a)

MOTOR OPERATED - 3

VALVE ACTUATOR

(EXISTING)

1 Get

Record the part

number.(a)

MOTOR OPERATED - 3

VALVE ACTUATOR

(EXISTING)

2 Record

FIGURE 1: INSPECT AND RECORD DEFUELING MOV ACTUATOR PART NUMBER

(SHEET 1 OF 2)

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BOEING SERVICE BULLETIN 767-28A0090
STEP TASK NAME IDENTIFICATION QTY MORE DATA

(a) Some airplanes have a quantity of two.

FIGURE 1: INSPECT AND RECORD DEFUELING MOV ACTUATOR PART NUMBER

(SHEET 2 OF 2)

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BOEING SERVICE BULLETIN 767-28A0090
FIGURE 2: REMOVE AND KEEP INDEX PLATE

(SHEET 1 OF 2)

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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.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

Make an ink mark

with a pen across

both the index plate

and the adapter

plate as a reference

for installation alignment.

1 Make REFERENCE MARK - -

Remove lockwire

from the index plate

mounting screws.

2 Remove LOCKWIRE - -

INDEX PLATE - 3

MOUNTING SCREW

3 Remove / Keep

4 Remove / Keep INDEX PLATE - - Keep for rework.

FIGURE 2: REMOVE AND KEEP INDEX PLATE

(SHEET 2 OF 2)

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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.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

Remove anodized

material from the index plate locations

using an abrasive

pad. Refer to SWPM

20-20-00 as an accepted procedure.

1 Remove ANODIZED FINISH - -

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

accepted procedure.

2 Clean INDEX PLATE - 1

FIGURE 3: REWORK INDEX PLATE

(SHEET 1 OF 1)

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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.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

Measure the electrical resistance in milliohms from the

adapter plate to the

rear wing spar. Refer to SWPM 20-20-

00 as an accepted

procedure.

ELECTRICAL BOND - -

RESISTANCE

1 Measure

Record the electrical

resistance in milliohms.

ELECTRICAL BOND - -

RESISTANCE

2 Record

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

AIRPLANE SURFACE

(SHEET 1 OF 1)

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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.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

Remove surface

material from

adapter plate contact surface locations using an abrasive pad. Refer to

SWPM 20-20-00 as

an accepted procedure.

1 Clean ADAPTER PLATE - 1

Clean contact surface locations. Refer

to SWPM 20-20-00

as an accepted procedure.

2 Clean ADAPTER PLATE - 1

Use a minimum

amount of sealant to

reduce squeeze out.

BMS 5-45 (BMS 5-95 -

optional)

SEALANT, CATEGORY 23 Apply

FIGURE 5: PREPARE ADAPTER PLATE

(SHEET 1 OF 1)

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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.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

Put index plate

against adapter

plate and hold.

INDEX PLATE - 1

MOUNTING SCREW

1 Put / Hold

Insert the kept screw

only.

INDEX PLATE - 1

MOUNTING SCREW

2 Insert

Tighten screw to

hold plate in place.

INDEX PLATE - 1

MOUNTING SCREW

3 Tighten

FIGURE 6: PUT INDEX PLATE IN POSITION FOR INSTALLATION

(SHEET 1 OF 1)

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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.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

Apply a Faying bond

to the index plate.

(a)

BMS 5-45 (BMS 5-95 -

optional)

SEALANT, CATEGORY 21 Apply

Do not connect the

bonding jumper to

the MOV actuator.

MOTOR OPERATED MA30A1001 1

VALVE ACTUATOR

2 Install (New)

FIGURE 7: INSTALL THE MOV ACTUATOR

(SHEET 1 OF 4)

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BOEING SERVICE BULLETIN 767-28A0090
STEP TASK NAME IDENTIFICATION QTY MORE DATA

Measure the electrical bond resistance

of the Faying bond

from the mounting

foot of the MOV actuator to a point on the

primary airplane

structure. (a) (b)

ELECTRICAL BOND - 1

RESISTANCE

3 Measure

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)

4 Measure BONDING JUMPER - 1

If you determined

that the bonding

jumper is too short,

remove the bonding

jumper and do the

following sub-tasks.

Remove BONDING JUMPER - 1

Select one length

from 4-to-6 inches.

(a)

BONDING JUMPER, 4 BACJ40A20-4 1

INCH (OPTIONAL)

Get

Select one length

from 4-to-6 inches.

(a)

BONDING JUMPER, 5 BACJ40A20-5 1

INCH (OPTIONAL)

Get

Select one length

from 4-to-6 inches.

(a)

BONDING JUMPER, 6 BACJ40A20-6 1

INCH (OPTIONAL)

Get

FIGURE 7: INSTALL THE MOV ACTUATOR

(SHEET 2 OF 4)

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BOEING SERVICE BULLETIN 767-28A0090
STEP TASK NAME IDENTIFICATION QTY MORE DATA

Clean the surface of

the bonding jumper

lug and fasteners,

and the airplane

structure. (a)

5 Clean BONDING JUMPER - 1

Attach the bonding

jumper to the airplane structure. Use

the shortest bonding

jumper that allows

no tension. You can

select a length from

4-to-6 inches.

Attach BONDING JUMPER - 1

Torque fasteners.

(a)

Torque BONDING JUMPER - 1

Clean the surface of

the bonding jumper

lug and fasteners,

and the airplane

structure. (a)

6 Clean BONDING JUMPER - 1

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)

Measure BONDING JUMPER - 1

Apply a cap seal to

the bonding jumper

fasteners. (a)

Apply BONDING JUMPER - 1

FIGURE 7: INSTALL THE MOV ACTUATOR

(SHEET 3 OF 4)

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BOEING SERVICE BULLETIN 767-28A0090
STEP TASK NAME IDENTIFICATION QTY MORE DATA

Attach the bonding

jumper to the MOV

actuator.

7 Attach BONDING JUMPER - 1

Torque fasteners.

(a)

Torque BONDING JUMPER - 1

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)

Measure BONDING JUMPER - 1

Apply a cap seal to

the bonding jumper

fasteners. (a)

Apply BONDING JUMPER - 1

(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)

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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.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

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

accepted procedure.

1 Clean ADAPTER PLATE - 1

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

accepted procedure.

2 Clean AIRPLANE SURFACE - -

FIGURE 8: CLEAN ADAPTER PLATE AND AIRPLANE SURFACE

(SHEET 1 OF 1)

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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.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

Get access to the

part number markings on the MOV actuator.

MOTOR OPERATED - 1

VALVE ACTUATOR

(EXISTING)

1 Get

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

LEFT

(SHEET 1 OF 2)

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BOEING SERVICE BULLETIN 767-28A0090
STEP TASK NAME IDENTIFICATION QTY MORE DATA

Record the part

number.

MOTOR OPERATED - 1

VALVE ACTUATOR

(EXISTING)

2 Record

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

LEFT

(SHEET 2 OF 2)

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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.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

Get access to the

part number markings on the MOV actuator.

MOTOR OPERATED - 1

VALVE ACTUATOR

(EXISTING)

1 Get

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

RIGHT

(SHEET 1 OF 2)

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BOEING SERVICE BULLETIN 767-28A0090
STEP TASK NAME IDENTIFICATION QTY MORE DATA

Record the part

number.

MOTOR OPERATED - 1

VALVE ACTUATOR

(EXISTING)

2 Record

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

RIGHT

(SHEET 2 OF 2)

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BOEING SERVICE BULLETIN 767-28A0090
FIGURE 11: INSPECT AND RECORD FUEL JETTISON NOZZLE MOV ACTUATOR PART NUMBER - LEFT

(SHEET 1 OF 2)

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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.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

Get access to the

part number markings on the MOV actuator.

MOTOR OPERATED - 1

VALVE ACTUATOR

(EXISTING)

1 Get

Record the part

number.

MOTOR OPERATED - 1

VALVE ACTUATOR

(EXISTING)

2 Record

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

(SHEET 2 OF 2)

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BOEING SERVICE BULLETIN 767-28A0090
FIGURE 12: INSPECT AND RECORD FUEL JETTISON NOZZLE MOV ACTUATOR PART NUMBER - RIGHT

(SHEET 1 OF 2)

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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.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

Get access to the

part number markings on the MOV actuator.

MOTOR OPERATED - 1

VALVE ACTUATOR

(EXISTING)

1 Get

Record the part

number.

MOTOR OPERATED - 1

VALVE ACTUATOR

(EXISTING)

2 Record

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

(SHEET 2 OF 2)

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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.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

Get access to the

part number markings on the MOV actuator.

MOTOR OPERATED - 1

VALVE ACTUATOR

(EXISTING)

1 Get

Record the part

number.

MOTOR OPERATED - 1

VALVE ACTUATOR

(EXISTING)

2 Record

FIGURE 13: INSPECT AND RECORD APU SHUTOFF MOV ACTUATOR PART NUMBER

(SHEET 1 OF 1)

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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.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

Get access to the

part number markings on the MOV actuator.

MOTOR OPERATED - 1

VALVE ACTUATOR

(EXISTING)

1 Get

Record the part

number.

MOTOR OPERATED - 1

VALVE ACTUATOR

(EXISTING)

2 Record

FIGURE 14: INSPECT AND RECORD APU ISOLATION MOV ACTUATOR PART NUMBER

(SHEET 1 OF 1)

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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.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

Get access to the

part number markings on the MOV actuator.

MOTOR OPERATED - 1

VALVE ACTUATOR

(EXISTING)

1 Get

Record the part

number.

MOTOR OPERATED - 1

VALVE ACTUATOR

(EXISTING)

2 Record

FIGURE 15: INSPECT AND RECORD ENGINE FUEL SHUTOFF MOV ACTUATOR PART NUMBER - LEFT

(SHEET 1 OF 1)

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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.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

Get access to the

part number markings on the MOV actuator.

MOTOR OPERATED - 1

VALVE ACTUATOR

(EXISTING)

1 Get

Record the part

number.

MOTOR OPERATED - 1

VALVE ACTUATOR

(EXISTING)

2 Record

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

(SHEET 1 OF 1)

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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.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

Get access to the

part number markings on the forward

MOV actuator.

MOTOR OPERATED - 1

VALVE ACTUATOR

(EXISTING)

1 Get

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

(SHEET 1 OF 2)

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97 of 119

BOEING SERVICE BULLETIN 767-28A0090
STEP TASK NAME IDENTIFICATION QTY MORE DATA

Record the part

number.

MOTOR OPERATED - 1

VALVE ACTUATOR

(EXISTING)

2 Record

Get access to the

part number markings on the aft MOV

actuator.

MOTOR OPERATED - 1

VALVE ACTUATOR

(EXISTING)

3 Get

Record the part

number.

MOTOR OPERATED - 1

VALVE ACTUATOR

(EXISTING)

4 Record

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

(SHEET 2 OF 2)

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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.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

Get access to the

part number markings on the MOV actuator.

MOTOR OPERATED - 1

VALVE ACTUATOR

(EXISTING)

1 Get

Record the part

number.

MOTOR OPERATED - 1

VALVE ACTUATOR

(EXISTING)

2 Record

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

- LEFT WING

(SHEET 1 OF 1)

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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.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

Apply a Faying bond

to the index plate.

(a)

BMS 5-45 (BMS 5-95 -

optional)

SEALANT, CATEGORY 21 Apply

Do not connect the

bonding jumper to

the MOV actuator.

Refer to the AMM as

an accepted procedure for the install of

the MOV actuator

body.

MOTOR OPERATED MA30A1001 1

VALVE ACTUATOR

2 Install (New)

FIGURE 19: INSTALL THE MOV ACTUATOR DIRECTLY TO THE MOTOR OPERATED VALVE

(SHEET 1 OF 4)

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BOEING SERVICE BULLETIN 767-28A0090
STEP TASK NAME IDENTIFICATION QTY MORE DATA

Measure the electrical bond resistance

of the Faying bond

from the mounting

foot of the MOV actuator to a point on the

primary airplane

structure. (a) (b)

ELECTRICAL BOND - 1

RESISTANCE

3 Measure

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)

4 Measure BONDING JUMPER - 1

If you determined

that the bonding

jumper is too short,

remove the bonding

jumper and do the

following sub-tasks.

Remove BONDING JUMPER - 1

Select one length

from 4-to-6 inches.

(a)

BONDING JUMPER, 4 BACJ40A20-4 1

INCH (OPTIONAL)

Get

Select one length

from 4-to-6 inches.

(a)

BONDING JUMPER, 5 BACJ40A20-5 1

INCH (OPTIONAL)

Get

Select one length

from 4-to-6 inches.

(a)

BONDING JUMPER, 6 BACJ40A20-6 1

INCH (OPTIONAL)

Get

FIGURE 19: INSTALL THE MOV ACTUATOR DIRECTLY TO THE MOTOR OPERATED VALVE

(SHEET 2 OF 4)

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BOEING SERVICE BULLETIN 767-28A0090
STEP TASK NAME IDENTIFICATION QTY MORE DATA

Clean the surface of

the bonding jumper

lug and fasteners,

and the airplane

structure. (a)

5 Clean BONDING JUMPER - 1

Attach the bonding

jumper to the airplane structure. Use

the shortest bonding

jumper that allows

no tension. You can

select a length from

4-to-6 inches.

Attach BONDING JUMPER - 1

Torque fasteners.

(a)

Torque BONDING JUMPER - 1

Clean the surface of

the bonding jumper

lug and fasteners,

and the airplane

structure. (a)

6 Clean BONDING JUMPER - 1

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)

Measure BONDING JUMPER - 1

Apply a cap seal to

the bonding jumper

fasteners. (a)

Apply BONDING JUMPER - 1

FIGURE 19: INSTALL THE MOV ACTUATOR DIRECTLY TO THE MOTOR OPERATED VALVE

(SHEET 3 OF 4)

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BOEING SERVICE BULLETIN 767-28A0090
STEP TASK NAME IDENTIFICATION QTY MORE DATA

Attach the bonding

jumper to the MOV

actuator.

7 Attach BONDING JUMPER - 1

Torque fasteners.

(a)

Torque BONDING JUMPER - 1

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)

Measure BONDING JUMPER - 1

Apply a cap seal to

the bonding jumper

fasteners. (a)

Apply BONDING JUMPER - 1

(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)

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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)

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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.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

Disconnect the wire

assembly from the

support bracket.

1 Disconnect WIRE ASSEMBLY - 1

Make a reference

mark with ink along

the lower edge of

the wire support

bracket for use as a

reference line.

2 Make REFERENCE MARK - 1

Drill out the rivets to

remove. Remove

and discard the support bracket. (c)

WIRE SUPPORT AS- 287T0015-7 1

SY

3 Remove

Countersink light

from .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)

4 Install (New) RIVET BACR15FV6KE7 2

Shave each rivet

head and each rivet

button flush to the

part surface to finish

as a double flush

plug. (c)

Microshave RIVET BACR15FV6KE7 2

WIRE SUPPORT AS- 287T0015-723 1

SY

5 Install (New)

Countersink on the

deflector at 100 degrees. Install the

new support bracket

on the deflector. (c)

(d)

Install (New) RIVET, 100 DEG BACR15BA5AD7C 2

Clean and prepare

the surface area for

finish. (e)

DEFLECTOR, REAR 112T1074-5 1

SPAR WING

6 Clean

FIGURE 20: REMOVE BRACKET AND INSTALL NEW BRACKET ON ENGINE FUEL SHUTOFF MOV

ACTUATOR DEFLECTOR - LEFT

(SHEET 2 OF 3)

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BOEING SERVICE BULLETIN 767-28A0090
STEP TASK NAME IDENTIFICATION QTY MORE DATA

BAC5626, TYPE 2, - (a) (b)

CLASS A OR D

COLORED CHEMICAL

CONVERSION COATING

7 Apply

Apply PRIMER BMS 10-11, TYPE 1 - (a) (b)

8 Connect WIRE ASSEMBLY - 1

(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)

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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)

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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.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

Disconnect the wire

assembly from the

support bracket.

1 Disconnect WIRE ASSEMBLY - 1

Make a reference

mark with ink along

the lower edge of

the wire support

bracket for use as a

reference line.

2 Make REFERENCE MARK - 1

Drill out the rivets to

remove. Remove

and discard the support bracket. (c)

WIRE SUPPORT AS- 287T0015-7 1

SY

3 Remove

Countersink light

from .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)

4 Install (New) RIVET BACR15FV6KE7 2

Shave each rivet

head and each rivet

button flush to the

part surface to finish

as a double flush

plug. (c)

Microshave RIVET BACR15FV6KE7 2

WIRE SUPPORT AS- 287T0015-723 1

SY

5 Install (New)

Countersink on the

deflector at 100 degrees. Install the

new support bracket

on the deflector. (c)

(d)

Install (New) RIVET, 100 DEG BACR15BA5AD7C 2

Clean and prepare

the surface area for

finish. (e)

DEFLECTOR, REAR 112T1074-6 1

SPAR WING

6 Clean

FIGURE 21: REMOVE BRACKET AND INSTALL NEW BRACKET ON ENGINE FUEL SHUTOFF MOV

ACTUATOR DEFLECTOR - RIGHT

(SHEET 2 OF 3)

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BOEING SERVICE BULLETIN 767-28A0090
STEP TASK NAME IDENTIFICATION QTY MORE DATA

BAC5626, TYPE 2, - (a) (b)

CLASS A OR D

COLORED CHEMICAL

CONVERSION COATING

7 Apply

Apply PRIMER BMS 10-11, TYPE 1 - (a) (b)

8 Connect WIRE ASSEMBLY - 1

(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)

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BOEING SERVICE BULLETIN 767-28A0090
FIGURE 22: INSTALL THE SHIM AND FORWARD ENGINE FUEL CROSSFEED MOV ACTUATOR

(SHEET 1 OF 5)

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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.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

Apply a Faying bond

to the index plate.

(a)

BMS 5-45 (BMS 5-95 -

optional)

SEALANT, CATEGORY 21 Apply

Install on index

plate.

SHIM - SWEENEY 343T0002-29 1

MOV ADAPTER

2 Install (New)

Apply a Faying bond

to the shim plate

around the holes.

BMS 5-45 (BMS 5-95 -

optional)

SEALANT, CATEGORY 23 Apply

Do not connect the

Bonding Jumper to

the MOV actuator.

MOTOR OPERATED MA30A1001 1

VALVE ACTUATOR

4 Install (New)

Install (New) SCREW BACS12HM08AH10 4

Measure the electrical bonding resistance of the Faying

bond for the mounting foot of the MOV

actuator to a point

on the primary airplane structure. (a)

(b)

ELECTRICAL BOND - 1

RESISTANCE

5 Measure

FIGURE 22: INSTALL THE SHIM AND FORWARD ENGINE FUEL CROSSFEED MOV ACTUATOR

(SHEET 2 OF 5)

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BOEING SERVICE BULLETIN 767-28A0090
STEP TASK NAME IDENTIFICATION QTY MORE DATA

Measure the length

of the 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 tension.

You can select a

length from 4-to-6

inches. (a)

6 Measure BONDING JUMPER - 1

If you determined

that the bonding

jumper is too short,

remove the bonding

jumper and do the

following sub-tasks.

Remove BONDING JUMPER - 1

You can select a

length from 4-to-6

inches. (a)

BONDING JUMPER, 4 BACJ40A20-4 1

INCH (OPTIONAL)

Get

BONDING JUMPER, 5 BACJ40A20-5 1

INCH (OPTIONAL)

Get

BONDING JUMPER, 6 BACJ40A20-6 1

INCH (OPTIONAL)

Get

Clean the surface of

the bonding jumper

lug, fasteners, and

the airplane structure. (a)

7 Clean BONDING JUMPER - -

Attach the bonding

jumper to the airplane structure. Use

the shortest bonding

jumper that allows

no tension. You can

select a length from

4-to-6 inches. (a)

Attach BONDING JUMPER - 1

Torque fasteners.

(a)

Torque BONDING JUMPER - 1

FIGURE 22: INSTALL THE SHIM AND FORWARD ENGINE FUEL CROSSFEED MOV ACTUATOR

(SHEET 3 OF 5)

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BOEING SERVICE BULLETIN 767-28A0090
STEP TASK NAME IDENTIFICATION QTY MORE DATA

Clean the surface of

the bonding jumper

lug, fasteners, and

MOV actuator. (a)

8 Clean BONDING JUMPER - 1

Measure the electrical bonding resistance of the Faying

bond from the lug on

the end of the bonding jumper to a point

on the airplane

structure. (a) (c)

Measure ELECTRICAL BOND - -

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 DENSITYApply

Attach the bonding

jumper to the MOV

actuator.

9 Attach BONDING JUMPER - 1

Torque fasteners.

(a)

Torque BONDING JUMPER - 1

Measure the 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. (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 DENSITYApply

(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)

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(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)

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FIGURE 23: INSTALL THE SHIM AND AFT ENGINE FUEL CROSSFEED MOV ACTUATOR

(SHEET 1 OF 5)

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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.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

Apply a Faying bond

to the index plate.

(a)

BMS 5-45 (BMS 5-95 -

optional)

SEALANT, CATEGORY 21 Apply

Install on index

plate.

SHIM - SWEENEY 343T0002-29 1

MOV ADAPTER

2 Install (New)

Apply a Faying bond

to the shim plate

around the holes.

SEALANT, CATEGO- BMS5-45 -

RY 2

3 Apply

Do not connect the

Bonding Jumper to

the MOV actuator.

MOTOR OPERATED MA30A1001 1

VALVE ACTUATOR

4 Install (New)

Install (New) SCREW BACS12HM08AH10 4

Measure the electrical bonding resistance of the Faying

bond for the mounting foot of the MOV

actuator to a point

on the primary airplane structure. (a)

(b)

ELECTRICAL BOND - 1

RESISTANCE

5 Measure

FIGURE 23: INSTALL THE SHIM AND AFT ENGINE FUEL CROSSFEED MOV ACTUATOR

(SHEET 2 OF 5)

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Measure the length

of the 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 tension.

You can select a

length from 4-to-6

inches. (a)

6 Measure BONDING JUMPER - 1

If you determined

that the bonding

jumper is too short,

remove the bonding

jumper and do the

following sub-tasks.

Remove BONDING JUMPER - 1

You can select a

length from 4-to-6

inches. (a)

BONDING JUMPER, 4 BACJ40A20-4 1

INCH (OPTIONAL)

Get

BONDING JUMPER, 5 BACJ40A20-5 1

INCH (OPTIONAL)

Get

BONDING JUMPER, 6 BACJ40A20-6 1

INCH (OPTIONAL)

Get

Clean the surface of

the bonding jumper

lug, fasteners, and

the airplane structure. (a)

7 Clean BONDING JUMPER - -

Attach the bonding

jumper to the airplane structure. Use

the shortest bonding

jumper that allows

no tension. You can

select a length from

4-to-6 inches. (a)

Attach BONDING JUMPER - 1

Torque fasteners.

(a)

Torque BONDING JUMPER - 1

FIGURE 23: INSTALL THE SHIM AND AFT ENGINE FUEL CROSSFEED MOV ACTUATOR

(SHEET 3 OF 5)

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Clean the surface of

the bonding jumper

lug, fasteners, and

MOV actuator. (a)

8 Clean BONDING JUMPER - 1

Measure the electrical bonding resistance of the Faying

bond from the lug on

the end of the bonding jumper to a point

on the airplane

structure. (a) (c)

Measure ELECTRICAL BOND - -

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 DENSITYApply

Attach the bonding

jumper to the MOV

actuator.

9 Attach BONDING JUMPER - 1

Torque fasteners.

(a)

Torque BONDING JUMPER - 1

Measure the 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. (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 DENSITYApply

(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)

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(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)

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BOEING SERVICE BULLETIN 767-28A0090