# Boeing Alert Service Bulletin 767-28A0090: U.S. DOT/FAA - Service Bulletin

- Rights: © The Boeing Company. Filed by the FAA in regulations.gov docket FAA-2011-0158, the docket of a proposed AD (Federal Register 2011-5721, 2012-19244). Not covered by OpenAirDocs’ CC0 dedication.
- Document: [Boeing Alert Service Bulletin 767-28A0090](https://openairdocs.org/service-documents/boeing/767-28a0090.md)
- Title as filed: U.S. DOT/FAA - Service Bulletin
- Pages: 119
- PDF: https://openairdocs.org/files/sha256/75/51/7551acb4b59520567e08d9f695b2946431a522331472e88d1eb9531bb9d7087d
- Page: https://openairdocs.org/service-documents/boeing/767-28a0090/file/7551acb4b595

## Text

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### Page 1

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.
9E991ECCN:
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Unpublished Work - All Rights Reserved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
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connection with this document unless provided in writing by Boeing.
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Table of Contents
Revision Transmittal Sheet ............................................ 5
Summary ...................................................... 7
1. PLANNING INFORMATION ........................................ 1 1
A. Effectivity ............................................... 1 1
1. Airplanes ............................................ 1 1
2. Spares Affected ........................................ 2 0
B. Concurrent Requirements ...................................... 2 0
C. Reason ................................................ 2 0
D. Description .............................................. 2 1
E. Compliance .............................................. 2 3
F. Approval ............................................... 2 3
G. Manpower .............................................. 2 3
H. Weight and Balance Changes .................................... 4 0
I. Electrical Load Data ......................................... 4 0
J. References .............................................. 4 1
1. Existing Data: ......................................... 4 1
2. Data supplied with this Service Bulletin: ........................... 4 1
3. Installation Drawings Used in the Preparation of this Service Bulletin: ........... 4 1
K. Publications Affected ........................................ 4 1
L. Interchangeability and Intermixability of Parts ........................... 4 2
2. MATERIAL INFORMATION ........................................ 4 3
A. Material - Price and Availability ................................... 4 3
B. Industry Support Information .................................... 4 4
C. Parts Necessary For Each Airplane ................................. 4 4
1. Kits/Parts: ........................................... 4 4
2. Parts and Materials Supplied by the Operator: ........................ 4 5
3. Parts Modified and Reidentified: ............................... 4 6
4. Parts Removed and Not Replaced: .............................. 4 6
D. Parts Necessary to Change Spares ................................. 4 6
E. Special Tooling - Price and Availability ............................... 4 6
F. Special Tooling Necessary to do this Service Bulletin ....................... 4 6
3. ACCOMPLISHMENT INSTRUCTIONS .................................. 4 7
A. GENERAL INFORMATION ..................................... 4 7
B. WORK INSTRUCTIONS ....................................... 4 8
FIGURE 1: INSPECT AND RECORD DEFUELING MOV ACTUATOR PART NUMBER ........ 7 2
FIGURE 2: REMOVE AND KEEP INDEX PLATE ............................. 7 4
FIGURE 3: REWORK INDEX PLATE ................................... 7 6
FIGURE 4: MEASURE AND RECORD ELECTRICAL RESISTANCE FROM ADAPTER PLATE TO THE
AIRPLANE SURFACE ..................................... 7 7
FIGURE 5: PREPARE ADAPTER PLATE ................................. 7 8
FIGURE 6: PUT INDEX PLATE IN POSITION FOR INSTALLATION .................. 7 9
FIGURE 7: INSTALL THE MOV ACTUATOR ............................... 8 0
FIGURE 8: CLEAN ADAPTER PLATE AND AIRPLANE SURFACE ................... 8 4
FIGURE 9: INSPECT AND RECORD FUEL JETTISON TRANSFER MOV ACTUATOR PART NUMBER -
LEFT .............................................. 8 5
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FIGURE 10: INSPECT AND RECORD FUEL JETTISON TRANSFER MOV ACTUATOR PART NUMBER -
RIGHT .............................................. 8 7
FIGURE 11: INSPECT AND RECORD FUEL JETTISON NOZZLE MOV ACTUATOR PART NUMBER - LEFT
.................................................. 8 9
FIGURE 12: INSPECT AND RECORD FUEL JETTISON NOZZLE MOV ACTUATOR PART NUMBER -
RIGHT .............................................. 9 1
FIGURE 13: INSPECT AND RECORD APU SHUTOFF MOV ACTUATOR PART NUMBER ...... 9 3
FIGURE 14: INSPECT AND RECORD APU ISOLATION MOV ACTUATOR PART NUMBER ..... 9 4
FIGURE 15: INSPECT AND RECORD ENGINE FUEL SHUTOFF MOV ACTUATOR PART NUMBER - LEFT
.................................................. 9 5
FIGURE 16: INSPECT AND RECORD ENGINE FUEL SHUTOFF MOV ACTUATOR PART NUMBER -
RIGHT .............................................. 9 6
FIGURE 17: INSPECT AND RECORD DUAL FORWARD/AFT ENGINE FUEL CROSSFEED MOV ACTUATOR
.................................................. 9 7
FIGURE 18: INSPECT AND RECORD SINGLE ENGINE FUEL CROSSFEED MOV ACTUATOR PART
NUMBER - LEFT WING .................................... 9 9
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 .............................. 1 0 4
FIGURE 21: REMOVE BRACKET AND INSTALL NEW BRACKET ON ENGINE FUEL SHUTOFF MOV
ACTUATOR DEFLECTOR - RIGHT ............................. 1 0 7
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 .... 1 1 5
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Commercial 
Airplanes
767
Service Bulletin
Revision Transmittal SheetNumber: 767-28A0090Original 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
July 03, 2008Original Issue:
April 01, 2010Revision 1:
September 02, 2010Revision 2:
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Commercial 
Airplanes
767
Service Bulletin
SummaryNumber: 767-28A0090Original 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
Elapsed HoursTotal Task HoursAirplanes
188.95 (a)(b)437.45 (a)(b)Group 1.0
188.95 (a)(b)437.45 (a)(b)Group 2.0
104.65 (a)(b)227.15 (a)(b)Group 3.0
104.65 (a)(b)227.15 (a)(b)Group 4.0
191.05 (a)(b)440.05 (a)(b)Group 5.1
182.30 (a)(b)429.30 (a)(b)Group 5.2
104.75 (a)(b)229.75 (a)(b)Group 6.1
96.00 (a)(b)219.00 (a)(b)Group 6.2
191.05 (a)(b)440.05 (a)(b)Group 7.1
104.75 (a)(b)229.75 (a)(b)Group 7.2
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Elapsed HoursTotal Task HoursAirplanes
182.30 (a)(b)429.30 (a)(b)Group 7.3
96.00 (a)(b)219.00 (a)(b)Group 7.4
104.75 (a)(b)229.75 (a)(b)Group 8.1
96.00 (a)(b)219.00 (a)(b)Group 8.2
206.90 (a)(b)485.90 (a)(b)Group 9.0
191.05 (a)(b)440.05 (a)(b)Group 10.1
104.57 (a)(b)229.75 (a)(b)Group 10.2
182.30 (a)(b)429.30 (a)(b)Group 10.3
96.00 (a)(b)219.00 (a)(b)Group 10.4
(a) Entry into the fuel tank should not be frequent.
(b) If entry into the fuel tank is not necessary, the time
needed to do the work is much less.
MATERIAL INFORMATION
Operator Supplied Parts.
Refer to Paragraph 2.A., Material - Price and Availability.
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BOEING SERVICE BULLETIN 767-28A0090
DEFUELING MOV
ENGINE FUEL
ACTUATOR
CROSS FEED
MOV ACTUATOR
FUEL JETTISON
APU FUEL SHUTOFF  NOZZLE MOV
MOV ACTUATOR  ACTUATOR
APU FUEL
ISOLATION MOV
ACTUATOR  ENGINE FUEL  FUEL JETTISON
DEFUELING MOV  SHUTOFF MOV  TRANSFER MOV
ACTUATOR  ACTUATOR  ACTUATOR
FUEL JETTISON
NOZZLE MOV  FUEL JETTISON
ACTUATOR  TRANSFER MOV
ACTUATOR
INSPECT THE MOV ACTUATORS AT THE ABOVE LOCATIONS.
- IF THE MOV ACTUATOR HAS AN UNACCEPTABLE PART
NUMBER, REPLACE THE MOV ACTUATOR.
- PREPARE AN ELECTRICAL BOND.
REAR SPAR
REAR SPAR
INDEX PLATE
ADAPTER PLATE
→ FWD
FWD <
TYPICAL MOV ACTUATOR  TYPICAL MOV ACTUATOR
INSTALLATION WITHOUT INDEX  INSTALLATION WITH INDEX PLATE
PLATE  U31989
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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.
DESCRIPTIONCONFIGURATIONGROUP
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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DESCRIPTIONCONFIGURATIONGROUP
767-200/300/300F airplanes effected by Boeing service bulletin
767-28-0034 to install the dual crossfeed, with the production jettison
installation, and with the production APU isolation. Requires an
inspection to determine if the Sweeney adapters are present.
-5
Made changes as given in Boeing service bulletin 767-28-0034.1
Did not make changes as given in Boeing service bulletin
767-28-0034.
2
767-200/300/300F airplanes effected by Boeing service bulletin
767-28-0034 to install the dual crossfeed, without the production
jettison installation, with the production APU isolation installation,
and without the center auxiliary tank defuel valve.
-6
Made changes as given in Boeing service bulletin 767-28-0034.1
Did not make changes as given in Boeing service bulletin
767-28-0034.
2
767-200/300/300F airplanes effected by Boeing service bulletin
767-28-0034 to install the dual crossfeed, and effected by Boeing
service bulletin 767-28-0027 to install the fuel jettison, and with the
production APU isolation installation.
-7
Made changes as given in Boeing service bulletin 767-28-0034, and
made changes as given in Boeing service bulletin 767-28-0027.
1
Made changes as given in Boeing service bulletin 767-28-0034, but
did not make changes as given in Boeing service bulletin
767-28-0027.
2
Did not make changes as given in Boeing service bulletin
767-28-0034, but made changes as given in Boeing service bulletin
767-28-0027.
3
Did not make changes as given in Boeing service bulletin
767-28-0034, and did not make changes as given in Boeing service
bulletin 767-28-0027.
4
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DESCRIPTIONCONFIGURATIONGROUP
767-200/300/300F airplanes effected only by Boeing service bulletin
767-28-0034 to install the dual crossfeed, without the jettison
installation, with the production APU isolation installation, and the
center auxiliary tank defuel valve.
-8
Made changes as given in Boeing service bulletin 767-28-0034.1
Did not make changes as given in Boeing service bulletin
767-28-0034.
2
767-400ER airplanes that require an inspection to determine if the
Sweeney adapters are present.
-9
767-200/300/300F airplanes effected by Boeing service bulletin
767-28-0034 to install the dual crossfeed, and effected by Boeing
service bulletin 767-28-0027 to install the fuel jettison, with the
production APU isolation installation, and with the center auxiliary
tank defuel valve.
-10
Made changes as given in Boeing service bulletin 767-28-0034, and
made changes as given in Boeing service bulletin 767-28-0027.
1
Made changes as given in Boeing service bulletin 767-28-0034, but
did not make changes as given in Boeing service bulletin
767-28-0027.
2
Did not make changes as given in Boeing service bulletin
767-28-0034, but made changes as given in Boeing service bulletin
767-28-0027.
3
Did not make changes as given in Boeing service bulletin
767-28-0034, and did not make changes as given in Boeing service
bulletin 767-28-0027.
4
Airplane Models:
767-200, 767-300, 767-300F, 767-400ER
GroupVariable Number
8VA001 - VA020
8VA301 - VA315
8VA501 - VA526
6VA527 - VA530
8VA701 - VA712
6VA713 - VA719
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GroupVariable Number
8VA801 - VA810
8VB001 - VB002
8VB051 - VB055
8VB101 - VB125
8VB201 - VB202
8VB251 - VB253
8VB281 - VB284
8VB301 - VB302
8VB321 - VB324
6VB325 - VB332
8VB371 - VB373
8VB401
4VB441 - VB444
8VE001 - VE002
6VE003
8VE021 - VE023
8VE041 - VE043
8VE061 - VE069
8VE083 - VE084
6VE085 - VE086
8VE101 - VE103
6VE104
8VE116 - VE117
6VE118
8VE121 - VE126
8VE141 - VE143
6VE144 - VE151
4VE152
6VE171 - VE172
7VF001 - VF002
7VF041 - VF042
7VF051
5VF061 - VF062
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GroupVariable Number
5VF071 - VF072
5VF091 - VF093
5VF101 - VF102
5VF161
2VF162
2VF171 - VF172
2VF180
1VF181 - VF184
2VF251
8VK001 - VK004
6VK005 - VK011
4VK012 - VK016
6VK021 - VK022
8VK031 - VK054
3VK055 - VK056
8VK081 - VK083
6VK084 - VK099
4VK100 - VK113
6VK131 - VK133
6VK141 - VK142
4VK143 - VK148
6VK161
4VK162 - VK164
4VK171
4VK181
4VK186
10VL001
7VL002 - VL006
10VL011
2VL701 - VL703
2VL751 - VL755
2VL806 - VL807
2VL871 - VL873
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GroupVariable Number
2VL891 - VL900
2VL911 - VL914
2VL931 - VL932
2VL941
7VN001 - VN015
5VN016 - VN020
2VN021 - VN041
7VN051 - VN058
5VN059 - VN064
7VN081 - VN085
5VN086 - VN092
2VN093 - VN099
7VN111 - VN115
5VN116 - VN124
2VN125 - VN127
5VN130 - VN132
2VN133 - VN137
7VN151 - VN155
5VN156 - VN158
5VN163 - VN168
7VN171 - VN173
2VN174
7VN191 - VN192
5VN193
2VN194 - VN198
7VN211 - VN212
7VN221
5VN222 - VN224
2VN225
5VN231 - VN234
6VN241
2VN242 - VN243
5VN251 - VN260
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GroupVariable Number
2VN261 - VN276
5VN291
2VN292 - VN293
5VN301 - VN306
2VN307 - VN314
5VN371 - VN372
5VN376
5VN381
2VN382 - VN388
2VN421 - VN427
2VN436
5VN471 - VN472
5VN491 - VN497
2VN498 - VN513
5VN531 - VN532
5VN536 - VN537
5VN541 - VN542
2VN546 - VN547
5VN551
2VN556 - VN557
2VN561 - VN562
5VN631 - VN633
2VN634 - VN638
5VN651 - VN652
2VN653 - VN658
5VN671 - VN672
2VN676
5VN681 - VN683
2VN684 - VN691
5VN731
2VN732
5VN751 - VN753
2VN791 - VN792
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GroupVariable Number
2VN811 - VN813
2VN921 - VN922
2VN931 - VN936
2VN951 - VN953
2VN966 - VN972
9VQ001 - VQ021
9VQ071 - VQ086
1VR051 - VR060
1VR081
1VR084
1VR086 - VR087
1VR106
2VR201 - VR209
1VR210 - VR211
2VR251
2VR256 - VR257
1VR258 - VR260
4VR401
4VR421 - VR423
4VR426
4VR441
4VR461
3VR471 - VR472
2VS051 - VS056
2VS061
2VS066 - VS070
2VS073 - VS078
2VS091 - VS102
1VS103 - VS104
2VS111 - VS113
2VS131 - VS133
2VS136 - VS137
2VS176 - VS177
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GroupVariable Number
2VS186 - VS187
2VS196 - VS203
2VS206 - VS208
2VS211
2VS216 - VS217
1VS231
2VS246 - VS248
2VS261 - VS262
1VS263
2VS266 - VS274
2VS291
1VS292 - VS293
2VS301 - VS302
1VS303
2VS306 - VS307
1VS308 - VS311
2VS316
2VS321 - VS324
1VS331 - VS333
1VS336 - VS337
2VS366 - VS367
2VS381 - VS382
2VS391 - VS392
2VS401
1VS426 - VS428
2VS466 - VS470
1VS471 - VS472
2VS486
2VS496
1VS497
2VS506 - VS507
1VS526
1VS546 - VS549
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GroupVariable Number
1VS701 - VS714
1VS721 - VS732
1VS751 - VS759
1VS821 - VS825
1VS841 - VS844
1VS861
1VS881 - VS883
1VS891
1VS896
1VS901
1VT501
1VT511 - VT512
1VT521 - VT522
1VV001
2VW701 - VW721
2VW851
2. Spares Affected
Examine your spares supply for the parts or components identified in Paragraph 2.C., 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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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:
ReasonAdditional Work -
Work Package(s)
Original Group
(Original Release)
New Group (Revi-
sion 1)
Variable No.
(b)(a)32VN921
(b)(a)32VN922
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ReasonAdditional Work -
Work Package(s)
Original Group
(Original Release)
New Group (Revi-
sion 1)
Variable No.
(b)(a)32VN966
(b)(a)32VN967
(b)(a)32VN968
(b)(a)32VN969
(b)(a)32VN970
(b)(a)32VN971
(b)(a)32VN972
(a) Add Work Packages 2, 3, 4 and 5.
(b) Airplane was not assigned to the correct group configuration in the original 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
ZoneModel
133, 134, 136, 531, 532, 541, 551, 631, 632,
641, 651
767-200, 767-300, 767-300F
Group 3, 10:
Affected Maintenance Zones
ZoneModel
133, 134, 136, 531, 532, 541, 551, 631, 632,
641, 651
767-300
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Group 4-8:
Affected Maintenance Zones
ZoneModel
133, 134, 136, 531, 532, 541, 551, 631, 632,
641, 651
767-200, 767-300
Group 9:
Affected Maintenance Zones
ZoneModel
133, 134, 136, 531, 532, 541, 551, 631, 632,
641, 651
767-400ER
E. Compliance
Federal Aviation Administration (FAA) Airworthiness Directive 2009-22-13 is related to this 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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### Page 24

 Time to adjust to the workplace
 Time to schedule the work
 Time to inspect the work
 Time to cure the materials
 Time to make the parts
 Time to find the tools.
Work Package Versus MOV Actuator Equipment Numbers
MOV Actuator Equipment No.Work Package No.
V00108/V00109/V001231
V001592
V001603
V001574
V001585
V000966
V000977
V000258
V000269
V0002510
V0002611
V00388/V0038912
V0002413
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Elapsed
Hours
Task HoursNumber of
Persons
TasksWork Package
0.501.002PrepareWork Package 1
0.100.101Open MOV ac-
tuator access
0.250.251Figure 1
0.250.251Remove MOV
actuator
1.001.001Figure 2
1.001.001Figure 3
0.500.501Figure 4
8.0032.04MOV access/
fuel tank entry
(a)
1.002.002Remove
adapter plate
and adapter
shaft (a)
1.001.001Figure 8 (a)
1.002.002Install adapter
plate and
adapter shaft
(a)
0.500.501Figure 4 (a)
1.501.501Figure 5
0.500.501Figure 6
0.500.501Install index
plate
0.250.251Install MOV ac-
tuator
4.008.002Close MOV ac-
cess in fuel
tank
0.100.101Close MOV ac-
tuator access
21.9552.45Total for Work Package
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Elapsed
Hours
Task HoursNumber of
Persons
TasksWork Package
0.501.002PrepareWork Package 2
0.100.101Open MOV ac-
tuator access
0.250.251Figure 9
0.250.251Remove MOV
actuator
1.001.001Figure 2
1.001.001Figure 3
0.500.501Figure 4
8.0032.04MOV access/
fuel tank entry
(a)
1.002.002Remove
adapter plate
and adapter
shaft (a)
1.001.001Figure 8 (a)
1.002.002Install adapter
plate and
adapter shaft
(a)
0.500.501Figure 4 (a)
1.501.501Figure 5
0.500.501Figure 6
0.500.501Install index
plate
0.250.251Install MOV ac-
tuator
4.008.002Close MOV ac-
cess in fuel
tank
0.100.101Close MOV ac-
tuator access
21.9552.45Total for Work Package
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Elapsed
Hours
Task HoursNumber of
Persons
TasksWork Package
0.501.002PrepareWork Package 3
0.100.101Open MOV ac-
tuator access
0.250.251Figure 10
0.250.251Remove MOV
actuator
1.001.001Figure 2
1.001.001Figure 3
0.500.501Figure 4
8.0032.04MOV access/
fuel tank entry
(a)
1.002.002Remove
adapter plate
and adapter
shaft (a)
1.001.001Figure 8 (a)
1.002.002Install adapter
plate and
adapter shaft
(a)
0.500.501Figure 4 (a)
1.501.501Figure 5
0.500.501Figure 6
0.500.501Install index
plate
0.250.251Install MOV ac-
tuator
4.008.002Close MOV ac-
cess in fuel
tank
0.100.101Close MOV ac-
tuator access
21.9552.45Total for Work Package
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Elapsed
Hours
Task HoursNumber of
Persons
TasksWork Package
0.501.002PrepareWork Package 4
0.100.101Open MOV ac-
tuator access
0.500.501Figure 11
0.250.251Remove MOV
actuator
1.001.001Figure 2
1.001.001Figure 3
0.500.501Figure 4
8.0032.04MOV access/
fuel tank entry
(a)
1.002.002Remove
adapter plate
and adapter
shaft (a)
1.001.001Figure 8 (a)
1.002.002Install adapter
plate and
adapter shaft
(a)
0.500.501Figure 4 (a)
1.501.501Figure 5
0.500.501Figure 6
0.500.501Install index
plate
0.250.251Install MOV ac-
tuator
4.008.002Close MOV ac-
cess in fuel
tank
0.100.101Close MOV ac-
tuator access
21.2052.70Total for Work Package
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### Page 29

Elapsed
Hours
Task HoursNumber of
Persons
TasksWork Package
0.501.002PrepareWork Package 5
0.100.101Open MOV ac-
tuator access
0.500.501Figure 12
0.250.251Remove MOV
actuator
1.001.001Figure 2
1.001.001Figure 3
0.500.501Figure 4
8.0032.04MOV access/
fuel tank entry
(a)
1.002.002Remove
adapter plate
and adapter
shaft (a)
1.001.001Figure 8 (a)
1.002.002Install adapter
plate and
adapter shaft
(a)
0.500.501Figure 4 (a)
1.501.501Figure 5
0.500.501Figure 6
0.500.501Install index
plate
0.250.251Install MOV ac-
tuator
4.008.002Close MOV ac-
cess in fuel
tank
0.100.101Close MOV ac-
tuator access
21.2052.70Total for Work Package
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### Page 30

Elapsed
Hours
Task HoursNumber of
Persons
TasksWork Package
0.501.002PrepareWork Package 6
0.100.101Open MOV ac-
tuator access
0.500.501Figure 13
0.250.251Remove MOV
actuator
0.250.251Install MOV ac-
tuator
0.500.501Close MOV ac-
tuator access
2.102.60Total for Work Package
0.501.002PrepareWork Package 7
0.100.101Open MOV ac-
tuator access
0.500.501Figure 14
0.250.251Remove MOV
actuator
0.250.251Install MOV ac-
tuator
0.500.501Close MOV ac-
tuator access
2.102.60Total for Work Package
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### Page 31

Elapsed
Hours
Task HoursNumber of
Persons
TasksWork Package
0.501.002PrepareWork Package 8
0.100.101Open MOV ac-
tuator access
0.250.251Figure 15
0.250.251Remove MOV
actuator
2.002.001Figure 20
1.001.001Figure 2
1.001.001Figure 3
0.500.501Figure 4
8.0032.04MOV access/
fuel tank entry
(a)
1.002.002Remove
adapter plate
and adapter
shaft (a)
1.001.001Figure 8 (a)
1.002.002Install adapter
plate and
adapter shaft
(a)
0.500.501Figure 4 (a)
1.501.501Figure 5
0.500.501Figure 6
0.500.501Install index
plate
0.250.251Install MOV ac-
tuator
4.008.002Close MOV ac-
cess in fuel
tank
0.100.101Close MOV ac-
tuator access
23.9554.45Total for Work Package
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### Page 32

Elapsed
Hours
Task HoursNumber of
Persons
TasksWork Package
0.501.002PrepareWork Package 9
0.100.101Open MOV ac-
tuator access
0.250.251Figure 16
0.250.251Remove MOV
actuator
2.002.001Figure 21
1.001.001Figure 2
1.001.001Figure 3
0.500.501Figure 4
8.0032.04MOV access/
fuel tank entry
(a)
1.002.002Remove
adapter plate
and adapter
shaft (a)
1.001.001Figure 8 (a)
1.002.002Install adapter
plate and
adapter shaft
(a)
0.500.501Figure 4 (a)
1.501.501Figure 5
0.500.501Figure 6
0.500.501Install index
plate
0.250.251Install MOV ac-
tuator
4.008.002Close MOV ac-
cess in fuel
tank
0.100.101Close MOV ac-
tuator access
23.9554.45Total for Work Package
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### Page 33

Elapsed
Hours
Task HoursNumber of
Persons
TasksWork Package
0.501.002PrepareWork Package 10
0.100.101Open MOV ac-
tuator access
0.250.251Figure 15
0.250.251Remove MOV
actuator
1.001.001Figure 2
1.001.001Figure 3
0.500.501Figure 4
8.0032.04MOV access/
fuel tank entry
(a)
1.002.002Remove
adapter plate
and adapter
shaft (a)
1.001.001Figure 8 (a)
1.002.002Install adapter
plate and
adapter shaft
(a)
0.500.501Figure 4 (a)
1.501.501Figure 5
0.500.501Figure 6
0.500.501Install index
plate
0.250.251Install MOV ac-
tuator
4.008.002Close MOV ac-
cess in fuel
tank
0.100.101Close MOV ac-
tuator access
21.9552.45Total for Work Package
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### Page 34

Elapsed
Hours
Task HoursNumber of
Persons
TasksWork Package
0.501.002PrepareWork Package 11
0.100.101Open MOV ac-
tuator access
0.250.251Figure 16
0.250.251Remove MOV
actuator
1.001.001Figure 2
1.001.001Figure 3
0.500.501Figure 4
8.0032.04MOV access/
fuel tank entry
(a)
1.002.002Remove
adapter plate
and adapter
shaft (a)
1.001.001Figure 8 (a)
1.002.002Install adapter
plate and
adapter shaft
(a)
0.500.501Figure 4 (a)
1.501.501Figure 5
0.500.501Figure 6
0.500.501Install index
plate
0.250.251Install MOV ac-
tuator
4.008.002Close MOV ac-
cess in fuel
tank
0.100.101Close MOV ac-
tuator access
21.9552.45Total for Work Package
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### Page 35

Elapsed
Hours
Task HoursNumber of
Persons
TasksWork Package
0.501.002PrepareWork Package 12
0.100.101Open MOV ac-
tuator access
0.250.251Figure 17
0.250.251Remove MOV
actuator
2.002.001Figure 2 (b)
2.002.001Figure 3 (b)
1.001.001Figure 4 (b)
8.0032.04MOV access/
fuel tank entry
(a)
2.004.002Remove
adapter plate
and adapter
shaft (a)(b)
2.002.001Figure 8. (a)(b)
2.004.002Install adapter
plate and
adapter shaft
(a)(b)
1.001.001Figure 4 (a)(b)
3.003.001Figure 5 (b)
1.001.001Figure 6 (b)
1.001.001Install index
plate (b)
0.500.501Install MOV ac-
tuator (b)(c)
4.008.002Close MOV ac-
cess in fuel
tank
0.100.101Close MOV ac-
tuator access
30.7063.20Total for Work Package
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### Page 36

Elapsed
Hours
Task HoursNumber of
Persons
TasksWork Package
0.501.002PrepareWork Package 13
0.100.101Open MOV ac-
tuator access
0.250.251Figure 18
0.250.251Remove MOV
actuator
1.001.001Figure 2
1.001.001Figure 3
0.500.501Figure 4
8.0032.04MOV access/
fuel tank entry
(a)
1.002.002Remove
adapter plate
and adapter
shaft (a)
1.001.001Figure 8. (a)
1.002.002Install adapter
plate and
adapter shaft
(a)
0.500.501Figure 4 (a)
1.501.501Figure 5
0.500.501Figure 6
0.500.501Install index
plate
0.250.251Install MOV ac-
tuator
4.008.002Close fuel tank
access (a)
0.100.101Close MOV ac-
tuator access
21.9552.45Total for Work Package
(a) This task is associated with a tank entry. A tank entry should not be likely. A tank
entry is only required if the electrical bonding resistance measure in not satisfactory.
(b) This work package applies to the two MOV actuators.
(c) If a visual inspection has determined that a Sweeney adapter assembly is installed,
then the shim kit must be installed. Either Figure 22 or Figure 23 will be referred to
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### Page 37

Elapsed
Hours
Task HoursNumber of
Persons
TasksWork Package
in the Accomplishment Instructions to do the work. See the Accomplishment Instruc-
tions for more detail.
Group 1-2:
Only the Work Packages for these Groups
Total Elapsed HoursTotal Task-Hours (a)Sum of Work Packages
21.9552.45Work Package 1
21.9552.45Work Package 2
21.9552.45Work Package 3
21.2052.70Work Package 4
21.2052.70Work Package 5
2.102.60Work Package 6
23.9554.45Work Package 8
23.9554.45Work Package 9
30.7063.20Work Package 12
188.95437.45TOTAL FOR EACH AIRPLANE
(a) See the work package tables for details.
Group 3-4:
Only the Work Packages for these Groups
Total Elapsed HoursTotal Task-Hours (a)Sum of Work Packages
21.9552.45Work Package 1
2.102.60Work Package 6
23.9554.45Work Package 8
23.9554.45Work Package 9
30.7063.20Work Package 12
104.65227.15TOTAL FOR EACH AIRPLANE
(a) See the work package tables for details.
Group 5, 7, 10, Configuration 1:
Only the Work Packages for these Groups
Total Elapsed HoursTotal Task-Hours (a)Sum of Work Packages
21.9552.45Work Package 1
21.9552.45Work Package 2
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Group 5, 7, 10, Configuration 1:
Only the Work Packages for these Groups
Total Elapsed HoursTotal Task-Hours (a)Sum of Work Packages
21.9552.45Work Package 3
21.2052.70Work Package 4
21.2052.70Work Package 5
2.102.60Work Package 6
2.102.60Work Package 7
23.9554.45Work Package 8
23.9554.45Work Package 9
30.7063.20Work Package 12
191.05440.05TOTAL FOR EACH AIRPLANE
(a) See the work package tables for details.
Group 5, Configuration 2; Group 7, 10, Configuration 3:
Only the Work Packages for these Groups
Total Elapsed HoursTotal Task-Hours (a)Sum of Work Packages
21.9552.45Work Package 1
21.9552.45Work Package 2
21.9552.45Work Package 3
21.2052.70Work Package 4
21.2052.70Work Package 5
2.102.60Work Package 6
2.102.60Work Package 7
23.9554.45Work Package 8
23.9554.45Work Package 9
21.9552.45Work Package 13
182.30429.30TOTAL FOR EACH AIRPLANE
(a) See the work package tables for details.
Group 6, Configuration 1; Group 7, Configuration 2; Group 8, Configuration 1; Group 10, Configu-
ration 2:
Only the Work Packages for these Groups
Total Elapsed HoursTotal Task-Hours (a)Sum of Work Packages
21.9552.45Work Package 1
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Group 6, Configuration 1; Group 7, Configuration 2; Group 8, Configuration 1; Group 10, Configu-
ration 2:
Only the Work Packages for these Groups
Total Elapsed HoursTotal Task-Hours (a)Sum of Work Packages
2.102.60Work Package 6
2.102.60Work Package 7
23.9554.45Work Package 8
23.9554.45Work Package 9
30.7063.20Work Package 12
104.75229.75TOTAL FOR EACH AIRPLANE
(a) See the work package tables for details.
Group 6, Configuration 2; Group 7, Configuration 4; Group 8, Configuration 2; Group 10, Configu-
ration 4:
Only the Work Packages for these Groups
Total Elapsed HoursTotal Task-Hours (a)Sum of Work Packages
21.9552.45Work Package 1
2.102.60Work Package 6
2.102.60Work Package 7
23.9554.45Work Package 8
23.9554.45Work Package 9
21.9552.45Work Package 13
96.00219.00TOTAL FOR EACH AIRPLANE
(a) See the work package tables for details.
Group 9:
Only the Work Packages for these Groups
Total Elapsed HoursTotal Task-Hours (a)Sum of Work Packages
21.9552.45Work Package 1
21.9552.45Work Package 2
21.9552.45Work Package 3
21.2052.70Work Package 4
21.2052.70Work Package 5
2.102.60Work Package 6
21.9552.45Work Package 10
21.9552.45Work Package 11
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Group 9:
Only the Work Packages for these Groups
Total Elapsed HoursTotal Task-Hours (a)Sum of Work Packages
30.7063.20Work Package 12
21.9552.45Work Package 13
206.90485.90TOTAL FOR EACH AIRPLANE
(a) See the work package tables for details.
H. Weight and Balance Changes
Change in Moment
(Pound-Inches)
Change in Weight
(Pounds)
Airplane
+6028.0+4.4767-200
+6608.9+4.4767-300
Change in Moment
(Pound-Inches)
Change in Weight
(Pounds)
Work Package
+465.1+0.4Work Package 1 (a)
+465.3+0.4Work Package 2
+465.3+0.4Work Package 3
+582.4+0.4Work Package 4
+582.4+0.4Work Package 5
+474.0+0.4Work Package 6
+474.0+0.4Work Package 7
+483.2+0.4Work Package 8
+483.2+0.4Work Package 9
+483.2+0.4Work Package 10
+483.2+0.4Work Package 11
+466.6+0.4Work Package 12 (a)
(a) Values are for one individual MOV actuator listed in the work package.
I. Electrical Load Data
Not changed.
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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:
TitleDrawing Number
Equipment - Engine Fuel Feed System343T0002
APU Fuel Feed Syst - Wing346T0004
Equipment Instl - Refueling System344T0002
Fuel System Diagram340T0007
K. Publications Affected
1. Publications:
Chapter-SectionPublication
28-22, 28-25, 28-26, 28-31767 Airplane Maintenance Manual (AMM)
28-22, 28-25, 28-26, 28-31767 Illustrated parts Catalog (IPC)
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Chapter-SectionPublication
9767 Maintenance Planning Data (MPD) document
2. Damage Tolerance Based Structural Inspections:
Boeing has evaluated this service bulletin for effects on Fatigue Critical Structure (FCS) and 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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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)
QTYDateNameKit Number
280.002360AvailableTop Kit - Bracket Installa-
tion
015T1805-1
2330JAN 30/08Top Kit - Bracket Installa-
tion
015T1805-1
2330FEB 29/08Top Kit - Bracket Installa-
tion
015T1805-1
2330MAR 31/08Top Kit - Bracket Installa-
tion
015T1805-1
2330APR 29/08Top Kit - Bracket Installa-
tion
015T1805-1
2330MAY 29/08Top Kit - Bracket Installa-
tion
015T1805-1
2330JUL 07/08Top Kit - Bracket Installa-
tion
015T1805-1
2310JUL 30/08Top Kit - Bracket Installa-
tion
015T1805-1
716.0030225AvailableTop Kit - Bracket Install
and Shim Install
015T1805-2
The kits are subject to the terms and conditions of the Boeing standard purchase order acknowledgment.
After the Unit Price date, new price and ROLT data is applicable. Prices are in United States dollars.
Terms: Net 30 days.
Reference this service bulletin and submit your purchase order by one of the methods that
follow:
1. Order on-line via ATA Spec 2000 or Boeing Part Page
2. Fax to (206) 662-7145
3. Spares Customer Support - MC 36-65 Boeing Spares Department P.O. Box 3707 Seattle,
Washington 98124-2207 USA
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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
23222120Top Kit
--11015T1805-1
1111015T1805-2
Group 6-8:
KIT 015T1805-1
NOTES
Existing Part
NumberName
Figure
New Part Number
2120
QTY
WIRE SUPPORT
ASSY
11287T0015-723
RIVET, 100 DEG22BACR15BA5AD7C
RIVET22BACR15FV6KE7
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Group 1-5, 9-10:
KIT 015T1805-2
NOTES
Existing Part
NumberName
Figure
New Part Number
23222120
QTY
WIRE SUPPORT
ASSY
11287T0015-723
SHIM - SWEENEY
MOV ADAPTER
11343T0002-29
RIVET, 100 DEG22BACR15BA5AD7C
RIVET22BACR15FV6KE7
SCREW44BACS12HM08AH10
2. Parts and Materials Supplied by the Operator:
NotesNameQTYPart Number /
Specification
Replaces MA20A1001-1
(S343T003-39)
MOTOR OPERATED VALVE ACTU-
ATOR
11MA30A1001
(S343T003-66) (a)
(b)(e)SEALANT, CATEGORY 222 oz.BMS 5-45
(c)SEALANT, LOW DENSITY22 oz.BMS 5-142
COLORED CHEMICAL CONVER-
SION COATING
4 oz.BAC5626, TYPE 2
CLASS A OR D
PRIMER4 oz.BMS 10-11, TYPE
1
(d)BONDING JUMPER, 4 INCH (OP-
TIONAL)
11BACJ40A20-4
(d)BONDING JUMPER, 5 INCH (OP-
TIONAL)
11BACJ40A20-5
(d)BONDING JUMPER, 6 INCH (OP-
TIONAL)
11BACJ40A20-6
(a) Supplier: ITT Aerospace Controls 28150 Industry Drive, Valencia, CA, 91355 USA
(b) For fuel tank or areas exposed to fuel vapor.
(c) BMS 5-45 or BMS 5-95 can be used as a substitute for BMS 5-142 for the application 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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NotesNameQTYPart Number /
Specification
(e) BMS 5-95 Pressure and Environmental Sealant-Chromate Type is optional (BAC5117-
6).
3. Parts Modified and Reidentified:
None.
4. Parts Removed and Not Replaced:
NotesQTYNameExisting Part
Number
Bracket removed from
each deflector located at
the engine fuel shutoff
MOV actuator.
2WIRE SUPPORT
ASSY
287T0015-7
D. Parts Necessary to Change Spares
None.
E. Special Tooling - Price and Availability
None.
F. Special Tooling Necessary to do this Service Bulletin
No special tools or equipment are necessary to do the change in this service bulletin. But, maintenance
and overhaul tools in the manuals given in Paragraph 1.J., References, can be necessary. Examine
operator tool supply to make sure all necessary tools are available.
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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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{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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{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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1) Temporarily put the index plate in position for installation as given in Figure 6.
2) Install the index plate. Refer to 767 AMM 28-31-06 as an accepted procedure.
3) Install the MOV actuator as given in Figure 7. Refer to 767 AMM 28-31-04 as
an accepted procedure for the install of the MOV actuator body.
4) Do an operational test of the MOV. Refer to 767 AMM 28-31-04 as an accepted
procedure.
(b) If the resistance is 1.5 milliohms or greater, the bond is not acceptable. Fuel tank
entry is necessary to make an acceptable bond. Do the following steps:
1) Get access to the Motor Operated Valve (MOV). Refer to 767 AMM 28-31-06
as an accepted procedure.
2) Remove the adapter plate and the adapter shaft. Refer to 767 AMM 28-31-06
as an accepted procedure.
3) Clean the adapter plate and the airplane structure as given in Figure 8.
4) Install the adapter plate and the adapter shaft. Refer to 767 AMM 28-31-06 as
an accepted procedure.
5) Prepare the adapter plate as given in Figure 5.
6) Measure and record the electrical bond resistance from the adapter plate to the
airplane structure as given in Figure 4.
a) If the resistance is less than 0.5 milliohms, the bond is acceptable. Do the
following steps:
{1} Temporarily put the index plate in position for installation as given in
Figure 6.
{2} Install the index plate. Refer to 767 AMM 28-31-06 as an accepted
procedure.
{3} Install the MOV actuator as given in Figure 7. Refer to 767 AMM
28-31-04 as an accepted procedure for the install of the MOV actuator
body.
{4} Do an operational test of the MOV. Refer to 767 AMM 28-31-04 as an
accepted procedure.
b) If the resistance is 0.5 milliohms or greater, the bond is not acceptable. Do
the following steps:
BOEING PROPRIETARY -
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{1} Return to step 2.b.(5)(b)2) and rework the bond until it is acceptable.
7) Close access to the Motor Operated Valve. Refer to 767 AMM 28-31-06 as an
accepted procedure.
3. Close access to the MOV actuator. Refer to 767 AMM 28-31-04 as an accepted procedure.
4. Put the airplane in a serviceable condition or do another work package.
Group 1-2, 5; Group 7, Configuration 1, 3; Group 9; Group 10, Configuration 1, 3:
Work Package 4 - FUEL JETTISON NOZZLE VALVE ACTUATOR - Left (V00157)
1. Get access to the MOV actuator. Refer to 767 AMM 28-31-05 as an accepted procedure.
2. Read and record the part number of the MOV actuator as given in Figure 11.
a. If the MOV actuator is not part number MA20A1001-1, the part is acceptable. No more work
is necessary at this location.
(1) Close access to the MOV actuator. Refer to 767 AMM 28-31-05 as an accepted procedure.
(2) Put the airplane in a serviceable condition or do another work package.
b. If the MOV actuator is part number MA20A1001-1, the part is not acceptable. Do the following
steps to install the MOV actuator with part number MA30A1001:
(1) Remove and discard the MOV actuator , and remove and keep the bonding jumper. Refer
to 767 AMM 28-31-05 as an accepted procedure.
(2) Remove and keep the index plate as given in Figure 2.
NOTE: Make an ink mark across the index plate, the adapter plate, and the airplane
structure with a pen as a reference for installation alignment.
(3) Rework the index plate as given in Figure 3.
(4) Prepare the adapter plate as given in Figure 5.
(5) Measure and record the electrical bond resistance from the adapter plate to the airplane
structure as given in Figure 4.
(a) If the resistance is less than 1.5 milliohms, the bond is acceptable. Do the following
steps:
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: July 03, 2008
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### Page 55

1) Temporarily put the index plate in position for installation as given in Figure 6.
2) Install the index plate. Refer to 767 AMM 28-31-03 as an accepted procedure.
3) Install the MOV actuator as given in Figure 7. Refer to 767 AMM 28-31-05 as
an accepted procedure for the install of the MOV actuator body.
4) Do an operational test of the MOV. Refer to 767 AMM 28-31-05 as an accepted
procedure.
(b) If the resistance is 1.5 milliohms or greater, the bond is not acceptable. Fuel tank
entry is necessary to make an acceptable bond. Do the following steps:
1) Get access to the Motor Operated Valve (MOV). Refer to 767 AMM 28-31-03
as an accepted procedure.
2) Remove the adapter plate and the adapter shaft. Refer to 767 AMM 28-31-03
as an accepted procedure.
3) Clean the adapter plate and the airplane structure as given in Figure 8.
4) Install the adapter plate and the adapter shaft. Refer to 767 AMM 28-31-03 as
an accepted procedure.
5) Prepare the adapter plate as given in Figure 5.
6) Measure and record the electrical bond resistance from the adapter plate to the
airplane structure as given in Figure 4.
a) If the resistance is less than 0.5 milliohms, the bond is acceptable. Do the
following steps:
{1} Temporarily put the index plate in position for installation as given in
Figure 6.
{2} Install the index plate. Refer to 767 AMM 28-31-03 as an accepted
procedure.
{3} Install the MOV actuator as given in Figure 7. Refer to 767 AMM
28-31-05 as an accepted procedure for the install of the MOV actuator
body.
{4} Do an operational test of the MOV. Refer to 767 AMM 28-31-05 as an
accepted procedure.
b) If the resistance is 0.5 milliohms or greater, the bond is not acceptable. Do
the following steps:
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: July 03, 2008
767-28A0090Revision 2: September 02, 2010
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### Page 56

{1} Return to step 2.b.(5)(b)2) and rework the bond until it is acceptable.
7) Close access to the Motor Operated Valve. Refer to 767 AMM 28-31-03 as an
accepted procedure.
3. Close access to the MOV actuator. Refer to 767 AMM 28-31-05 as an accepted procedure.
4. Put the airplane in a serviceable condition or do another work package.
Group 1-2, 5; Group 7, Configuration 1, 3; Group 9; Group 10, Configuration 1, 3:
Work Package 5 - FUEL JETTISON NOZZLE VALVE ACTUATOR - Right (V00158)
1. Get access to the MOV actuator. Refer to 767 AMM 28-31-05 as an accepted procedure.
2. Read and record the part number of the MOV actuator as given in Figure 12.
a. If the MOV actuator is not part number MA20A1001-1, the part is acceptable. No more work
is necessary at this location.
(1) Close access to the MOV actuator. Refer to 767 AMM 28-31-05 as an accepted procedure.
(2) Put the airplane in a serviceable condition or do another work package.
b. If the MOV actuator is part number MA20A1001-1, the part is not acceptable. Do the following
steps to install the MOV actuator with part number MA30A1001:
(1) Remove and discard the MOV actuator , and remove and keep the bonding jumper. Refer
to 767 AMM 28-31-05 as an accepted procedure.
(2) Remove and keep the index plate as given in Figure 2.
NOTE: Make an ink mark across the index plate, the adapter plate, and the airplane
structure with a pen as a reference for installation alignment.
(3) Rework the index plate as given in Figure 3.
(4) Prepare the adapter plate as given in Figure 5.
(5) Measure and record the electrical bond resistance from the adapter plate to the airplane
structure as given in Figure 4.
(a) If the resistance is less than 1.5 milliohms, the bond is acceptable. Do the following
steps:
BOEING PROPRIETARY -
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Original Issue: July 03, 2008
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### Page 57

1) Temporarily put the index plate in position for installation as given in Figure 6.
2) Install the index plate. Refer to 767 AMM 28-31-03 as an accepted procedure.
3) Install the MOV actuator as given in Figure 7. Refer to 767 AMM 28-31-05 as
an accepted procedure for the install of the MOV actuator body.
4) Do an operational test of the MOV. Refer to 767 AMM 28-31-05 as an accepted
procedure.
(b) If the resistance is 1.5 milliohms or greater, the bond is not acceptable. Fuel tank
entry is necessary to make an acceptable bond. Do the following steps:
1) Get access to the Motor Operated Valve (MOV). Refer to 767 AMM 28-31-03
as an accepted procedure.
2) Remove the adapter plate and the adapter shaft. Refer to 767 AMM 28-31-03
as an accepted procedure.
3) Clean the adapter plate and the airplane structure as given in Figure 8.
4) Install the adapter plate and the adapter shaft. Refer to 767 AMM 28-31-03 as
an accepted procedure.
5) Prepare the adapter plate as given in Figure 5.
6) Measure and record the electrical bond resistance from the adapter plate to the
airplane structure as given in Figure 4.
a) If the resistance is less than 0.5 milliohms, the bond is acceptable. Do the
following steps:
{1} Temporarily put the index plate in position for installation as given in
Figure 6.
{2} Install the index plate. Refer to 767 AMM 28-31-03 as an accepted
procedure.
{3} Install the MOV actuator as given in Figure 7. Refer to 767 AMM
28-31-05 as an accepted procedure for the install of the MOV actuator
body.
{4} Do an operational test of the MOV. Refer to 767 AMM 28-31-05 as an
accepted procedure.
b) If the resistance is 0.5 milliohms or greater, the bond is not acceptable. Do
the following steps:
BOEING PROPRIETARY -
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### Page 58

{1} Return to step 2.b.(5)(b)2) and rework the bond until it is acceptable.
7) Close access to the MOV. Refer to 767 AMM 28-31-03 as an accepted
procedure.
3. Close access to the MOV actuator. Refer to 767 AMM 28-31-05 as an accepted procedure.
4. Put the airplane in a serviceable condition or do another work package.
Group 1-10:
Work Package 6 - APU FUEL SHUTOFF VALVE ACTUATOR (V00096)
1. Get access to the MOV actuator. Refer to 767 AMM 28-25-02 as an accepted procedure.
2. Read and record the part number of the MOV actuator as given in Figure 13.
a. If the MOV actuator is not part number MA20A1001-1, the part is acceptable. No more work
is necessary at this location.
(1) Close access to the MOV actuator. Refer to 767 AMM 28-25-02 as an accepted procedure.
(2) Put the airplane in a serviceable condition or do another work package.
b. If the MOV actuator is part number MA20A1001-1, the part is not acceptable. Do the following
steps to install the MOV actuator with part number MA30A1001:
(1) Remove and discard the MOV actuator , and remove and keep the bonding jumper. Refer
to 767 AMM 28-25-02 as an accepted procedure.
(2) Install the MOV actuator as given in Figure 19. Refer to 767 AMM 28-25-02 as an accepted
procedure for the install of the MOV actuator body.
(3) Do an operational test of the MOV. Refer to 767 AMM 28-25-02 as an accepted procedure.
3. Close access to the MOV actuator. Refer to 767 AMM 28-25-02 as an accepted procedure.
4. Put the airplane in a serviceable condition or do another work package.
Group 5-8, 10:
Work Package 7 - APU FUEL ISOLATION VALVE ACTUATOR (V00097)
1. Get access to the MOV actuator. Refer to 767 AMM 28-25-04 as an accepted procedure.
2. Read and record the part number of the MOV actuator as given in Figure 14.
a. If the MOV actuator is not part number MA20A1001-1, the part is acceptable. No more work
is necessary at this location.
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
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### Page 59

(1) Close access to the MOV actuator. Refer to 767 AMM 28-25-04 as an accepted procedure.
(2) Put the airplane in a serviceable condition or do another work package.
b. If the MOV actuator is part number MA20A1001-1, the part is not acceptable. Do the following
steps to install the MOV actuator with part number MA30A1001:
(1) Remove and discard the MOV actuator , and remove and keep the bonding jumper. Refer
to 767 AMM 28-25-04 as an accepted procedure.
(2) Install the MOV actuator as given in Figure 19. Refer to 767 AMM 28-25-04 as an accepted
procedure for the install of the MOV actuator body.
(3) Do an operational test of the MOV. Refer to 767 AMM 28-25-04 as an accepted procedure.
3. Close access to the MOV actuator. Refer to 767 AMM 28-25-04 as an accepted procedure.
4. Put the airplane in a serviceable condition or do another work package.
Group 1-8, 10:
Work Package 8 - ENGINE FUEL SHUTOFF VALVE ACTUATOR (V00025)
1. Get access to the MOV actuator. Refer to 767 AMM 28-22-11 as an accepted procedure.
2. Read and record the part number of the MOV actuator as given in Figure 15.
a. If the MOV actuator is not part number MA20A1001-1, the part is acceptable.
(1) Remove the wire bracket and install the new wire bracket on the engine fuel shut off MOV
actuator deflector as given in Figure 20.
NOTE: This change must be made to accomodate any future install of part number
MA30A1001 or an MOV actuator of similar design.
(2) No more work is necessary. Close access to the MOV actuator. Refer to 767 AMM
28-22-11 as an accepted procedure.
(3) Put the airplane in a serviceable condition or do another work package.
b. If the MOV actuator is part number MA20A1001-1, the part is not acceptable. Do the following
steps to install the MOV actuator with part number MA30A1001:
(1) Remove and discard the MOV actuator , and remove and keep the bonding jumper. Refer
to 767 AMM 28-22-11 as an accepted procedure.
(2) Remove the wire bracket and install the new wire bracket on the engine fuel shutoff MOV
actuator deflector as given in Figure 20.
(3) Remove and keep the index plate as given in Figure 2.
NOTE: Make an ink mark across the index plate, the adapter plate, and the airplane
structure with a pen as a reference for installation alignment.
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: July 03, 2008
767-28A0090Revision 2: September 02, 2010
59 of 119
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### Page 60

(4) Rework the index plate as given in Figure 3.
(5) Prepare the adapter plate as given in Figure 5.
(6) Measure and record the electrical bond resistance from the adapter plate to the airplane
structure as given in Figure 4.
(a) If the resistance is less than 1.5 milliohms, the bond is acceptable. Do the following
steps:
1) Temporarily put the index plate in position for installation as given in Figure 6.
2) Install the index plate. Refer to 767 AMM 28-22-01 as an accepted procedure.
3) Install the MOV actuator as given in Figure 7. Refer to 767 AMM 28-22-11 as
an accepted procedure for the install of the MOV actuator body.
4) Do an operational test of the MOV. Refer to 767 AMM 28-22-11 as an accepted
procedure.
(b) If the resistance is 1.5 milliohms or greater, the bond is not acceptable. Fuel tank
entry is necessary to make an acceptable bond. Do the following steps:
1) Get access to the Motor Operated Valve (MOV). Refer to 767 AMM 28-22-01
as an accepted procedure.
2) Remove the adapter plate and the adapter shaft. Refer to 767 AMM 28-22-01
as an accepted procedure.
3) Clean the adapter plate and the airplane structure as given in Figure 8.
4) Install the adapter plate and the adapter shaft. Refer to 767 AMM 28-22-01 as
an accepted procedure.
5) Prepare the adapter plate as given in Figure 5.
6) Measure and record the electrical bond resistance from the adapter plate to the
airplane structure as given in Figure 4.
a) If the resistance is less than 0.5 milliohms, the bond is acceptable. Do the
following:
BOEING PROPRIETARY -
Copyright © Unpublished Work - See page 1 for details.
Original Issue: July 03, 2008
767-28A0090Revision 2: September 02, 2010
60 of 119
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