Commercial 

Airplanes 777

Service Bulletin

Number: 777-28A0034

Original Issue: August 02, 2007

Revision 2: September 20, 2010

ATA System: 2822 2825 2826 2831

SUBJECT: FUEL - Main and Center Tank Valve Actuators - 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 © 2007 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Unpublished Work - All Rights Reserved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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BLANK PAGE
Table of Contents

Revision Transmittal Sheet ............................................ 5

Summary ...................................................... 7

1. PLANNING INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11

A. Effectivity . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11

1. Airplanes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11

2. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13

B. Concurrent Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14

C. Reason . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14

D. Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14

E. Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16

G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16

H. Weight and Balance Changes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 28

I. Electrical Load Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 28

J. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 28

1. Existing Data: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 28

2. Data supplied with this Service Bulletin: . . . . . . . . . . . . . . . . . . . . . . . . . . . 28

3. Installation Drawings Used in the Preparation of this Service Bulletin: . . . . . . . . . . . 29

K. Publications Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29

L. Interchangeability and Intermixability of Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . 29

2. MATERIAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 31

A. Material - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 31

B. Industry Support Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 31

C. Parts Necessary For Each Airplane . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 31

1. Kits/Parts: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 31

2. Parts and Materials Supplied by the Operator: . . . . . . . . . . . . . . . . . . . . . . . . 31

3. Parts Modified and Reidentified: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 32

4. Parts Removed and Not Replaced: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 32

D. Parts Necessary to Change Spares . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 32

E. Special Tooling - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 32

F. Special Tooling Necessary to do this Service Bulletin . . . . . . . . . . . . . . . . . . . . . . . 33

3. ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 35

A. GENERAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 35

B. WORK INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 35

FIGURE 1: INSPECT AND RECORD THE ENGINE FUEL SPAR MOV ACTUATOR PART NUMBER (LEFT

WING) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 54

FIGURE 2: REMOVE AND KEEP INDEX PLATE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 56

FIGURE 3: REWORK INDEX PLATE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 58

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

THE AIRPLANE STRUCTURE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 59

FIGURE 5: PREPARE ADAPTER PLATE SURFACE . . . . . . . . . . . . . . . . . . . . . . . . . . . 60

FIGURE 6: PUT INDEX PLATE IN POSITION FOR INSTALLATION . . . . . . . . . . . . . . . . . . 61

FIGURE 7: INSTALL THE MOV ACTUATOR (DIRECTLY TO THE INDEX PLATE) . . . . . . . . . . 62

FIGURE 8: CLEAN ADAPTER PLATE AND AIRPLANE SURFACE . . . . . . . . . . . . . . . . . . . 66

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BOEING SERVICE BULLETIN 777-28A0034
FIGURE 9: INSPECT AND RECORD THE ENGINE FUEL SPAR MOV ACTUATOR PART NUMBER (RIGHT

WING) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 67

FIGURE 10: INSPECT AND RECORD THE FORWARD/AFT CROSSFEED MOV ACTUATOR PART NUMBER

(LEFT WING) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 69

FIGURE 11: INSPECT AND RECORD THE APU FUEL SHUTOFF MOV ACTUATOR PART NUMBER (LEFT

WING). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 71

FIGURE 12: INSPECT AND RECORD THE APU ISOLATION MOV ACTUATOR PART NUMBER (LEFT

WING). . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 73

FIGURE 13: REWORK BRACKET AT APU ISOLATION MOV ACTUATOR AREA ONLY . . . . . . . . 75

FIGURE 14: INSPECT AND RECORD THE DEFUEL MOV ACTUATOR PART NUMBER (RIGHT WING).

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 79

FIGURE 15: INSPECT AND RECORD FUEL JETTISON NOZZLE MOV ACTUATOR PART NUMBER (INSIDE

THE LEFT WING AREA) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 81

FIGURE 16: INSPECT AND RECORD FUEL JETTISON NOZZLE MOV ACTUATOR PART NUMBER (INSIDE

THE RIGHT WING AREA) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 82

FIGURE 17: INSPECT AND RECORD FUEL JETTISON NOZZLE MOV ACTUATOR PART NUMBER (LEFT

WING) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 83

FIGURE 18: INSPECT AND RECORD FUEL JETTISON NOZZLE MOV ACTUATOR PART NUMBER (RIGHT

WING) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 84

FIGURE 19: INSPECT AND RECORD FUEL JETTISON ISOLATION MOV ACTUATOR PART NUMBER

(LEFT WING) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 85

FIGURE 20: INSPECT AND RECORD FUEL JETTISON ISOLATION MOV ACTUATOR PART NUMBER

(RIGHT WING) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 87

FIGURE 21: INSTALL THE MOV ACTUATOR . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 89

FIGURE 22: INSTALL THE FUEL JETTISON NOZZLE VALVE MOV ACTUATOR (INSIDE WING AREA)

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 93

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BOEING SERVICE BULLETIN 777-28A0034
Commercial 

Airplanes 777

Service Bulletin

Revision Transmittal Sheet Number: 777-28A0034

Original Issue: August 02, 2007

Revision 2: September 20, 2010

ATA System: 2822 2825 2826 2831

SUBJECT: FUEL - Main and Center Tank Valve Actuators - Inspection and Replacement

This revision includes all pages of the service bulletin.

COMPLIANCE INFORMATION RELATED TO THIS REVISION

Federal Aviation Administration (FAA) Notice of Proposed Rule Making NPRM 2008-NM-056-AD, is related to

this service bulletin.

No more work is necessary on the airplane(s) changed in accordance with the original issue or Revision 1 of

this service bulletin.

REASON FOR REVISION

This revision is sent to inform operators of the following corrections to apply cap seal to the fasteners of the

Motor Operated Valve (MOV) actuator bonding jumper fasteners:

– In paragraph 2.C., Parts Necessary For Each Airplane, the QTY for BMS 5-95 was increased to reflect the

approximate total amount to consume when applying cap seal to the bonding jumper fasteners.

– In paragraph 2.C., Parts Necessary For Each Airplane, footnote (e) was added to clarify optional part

numbers for BMS 5-95 when applying cap seal on the bonding jumper fasteners.

– In Figure 7, Figure 21, and Figure 22, for the install of the MOV actuator, the step table was revised to add

a step to apply cap seal on the bonding jumper fasteners after measuring the electrical bond resistance.

– In Figure 7, Figure 21, and Figure 22, footnote (f) was added to clarify optional part numbers for BMS 5-95

when applying cap seal on the bonding jumper fasteners.

The information given in Information Notice 777-28A0034 IN 3 is included in this revision.

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

of important changes.

Pages with no vertical lines have no important changes.

REVISION HISTORY

Original Issue: August 02, 2007

Revision 1: May 20, 2010

Revision 2: September 20, 2010

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BLANK PAGE
Commercial 

Airplanes 777

Service Bulletin

Summary Number: 777-28A0034

Original Issue: August 02, 2007

Revision 2: September 20, 2010

ATA System: 2822 2825 2826 2831

SUBJECT: FUEL - Main and Center Tank Valve Actuators - Inspection and Replacement

CONCURRENT REQUIREMENTS

None

BACKGROUND

This service bulletin gives instruction to inspect all the motor operated valve (MOV) actuators and to install new

MOV actuators where necessary. The MOV actuators are installed at each fuel system. The new MOV actuator

will prevent electrical current flow through the actuator into the fuel tank. If this service bulletin is not done it is

possible that a flow of electricity into the fuel tank will supply an ignition source for the fuel fumes in the tank.

The Boeing system safety assessment necessary for Special Federal Aviation Regulation (SFAR) 88, showed

that under specific conditions it was possible for electrical current to flow through certain MOV actuators into

the fuel tank. A new MOV actuator is available to replace the existing MOV actuator with this condition. The new

MOV actuator includes an internal electrical isolator to give the MOV actuator protection against electrical energy

from lightning, 115 VAC hot shorts, and 28 VDC internal shorts. The new MOV actuator will prevent the flow of

an electrical current into the fuel tank and increase the reliability of the fuel system.

This service bulletin replaces the MOV actuator part number MA20A1001-1 with the new MOV actuator part

number MA30A1001. The MOV actuator part number MA20A1001-1 is the only installed MOV actuator part

number that is affected by this service bulletin.

This service bulletin gives instruction on how to measure the electrical resistance of bonds at the installed MOV

actuator locations, how to prepare a Faying surface for the install of the new MOV actuator, how to prepare

affected airplane parts, and how to install the new MOV actuator.

This service bulletin is the result of a safety assessment conducted by Boeing under SFAR 88, "Fuel Tank

System Fault Tolerance Evaluation Requirements".

Section 9 of the Maintenance Planning Data (MPD) document was changed.

ACTION (PRR 61777-187, PRR 61998-3)

The following actions are necessary:

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— 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 MOV actuator part number MA20A1001-1

is the only installed MOV actuator part number that is affected by this service bulletin.

— If you are required to install the MOV actuator part number MA30A1001, you must do an electrical resistance

check of 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.

— Remove, rework, and reinstall the bracket at the APU Isolation MOV actuator location to prevent part

interference with the new MOV actuator part number MA30A1001.

— Close access to each MOV actuator.

EFFECTIVITY

777 -200 /-200LR /-300 /-300ER airplanes. Refer to Paragraph 1.A., Effectivity for the list of affected airplanes.

COMPLIANCE

Federal Aviation Administration (FAA) Notice of Proposed Rule Making 2008-NM-056-AD, is related to this

service bulletin.

Boeing recommends that operators accomplish this service bulletin be incorporated within 60 months after the

original issue date on this service bulletin.

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 1 327.35 (a)(b) 142.35 (a) (b)

Group 2 427.05 (a)(b) 182.05 (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

Boeing Supplied Kits/Parts.

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

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BLANK PAGE
Commercial 

Airplanes 777

Service Bulletin

Number: 777-28A0034

Original Issue: August 02, 2007

Revision 2: September 20, 2010

ATA System: 2822 2825 2826 2831

SUBJECT: FUEL - Main and Center Tank Valve Actuators - Inspection and Replacement

1. PLANNING INFORMATION

A. Effectivity

1. Airplanes

Refer to Service Bulletin Index Document D624W001 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 61998-3 for data about this change.

GROUP CONFIGURATION DESCRIPTION

777-200/-300 airplanes with jettison nozzle MOV actuator located

inside the rear wing area.

1 -

777-200LR/-300ER airplanes with jettison nozzle MOV actuator

located on the rear wing spar.

2 -

Airplane Models:

777-200, 777-200LR, 777-300, 777-300ER

Variable Number Group

WA001 - WA017 1

WA076 - WA080 1

WA086 - WA093 1

WA101 - WA104 1

WA116 - WA119 1

WA131 - WA137 1

WA171 - WA175 1

WA196 - WA198 1

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Variable Number Group

WA206 - WA212 1

WA221 - WA223 1

WA231 - WA232 1

WA241 - WA250 1

WA261 - WA266 1

WA281 - WA282 1

WA301 - WA304 1

WB001 - WB021 1

WB031 - WB046 1

WB051 - WB088 1

WB101 - WB106 1

WB121 - WB125 1

WB131 - WB141 1

WB151 - WB155 1

WB161 - WB177 1

WB181 - WB194 1

WB201 - WB215 1

WB231 - WB247 1

WB271 - WB273 1

WB276 - WB286 1

WB291 - WB302 1

WB306 - WB307 1

WB311 - WB337 1

WB341 - WB342 1

WB366 - WB368 1

WB371 - WB388 1

WB406 1

WB411 - WB413 1

WB416 - WB437 1

WB446 - WB453 1

WB476 1

WB481 - WB484 1

WB501 - WB511 1

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BOEING SERVICE BULLETIN 777-28A0034
Variable Number Group

WB531 - WB537 1

WB551 - WB554 1

WB591 - WB597 1

WB601 - WB606 1

WB611 - WB622 1

WB631 - WB638 1

WB646 - WB649 1

WC051 - WC073 1

WC101 - WC104 1

WC111 - WC116 1

WC241 - WC243 1

WC281 - WC290 1

WC301 - WC308 1

WC361 - WC364 1

WC371 - WC374 1

WC381 - WC390 1

WC441 1

WC446 - WC448 1

WC456 - WC458 1

WC486 - WC489 1

WD001 - WD002 2

WD501 - WD504 2

WD521 - WD532 2

WD561 - WD563 2

WD581 - WD586 2

WD606 2

WD621 - WD625 2

WD651 - WD652 2

WD671 - WD675 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.

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BOEING SERVICE BULLETIN 777-28A0034
B. Concurrent Requirements

None.

C. Reason

This service bulletin gives instruction to inspect all the motor operated valve (MOV) actuators and to

install new MOV actuators where necessary. The MOV actuators are installed at each fuel system.

The new MOV actuator will prevent electrical current flow through the actuator into the fuel tank. If this

service bulletin is not done it is possible that a flow of electricity into the fuel tank will supply an ignition

source for the fuel fumes in the tank.

The Boeing system safety assessment necessary for Special Federal Aviation Regulation (SFAR) 88,

showed that under specific conditions it was possible for electrical current to flow through certain MOV

actuators into the fuel tank. A new MOV actuator is available to replace the existing MOV actuator with

this condition. The new MOV actuator includes an internal electrical isolator to give the MOV actuator

protection against electrical energy from lightning, 115 VAC hot shorts, and 28 VDC internal shorts.

The new MOV actuator will prevent the flow of an electrical current into the fuel tank and increase the

reliability of the fuel system.

This service bulletin replaces the MOV actuator part number MA20A1001-1 with the new MOV actuator

part number MA30A1001. The MOV actuator part number MA20A1001-1 is the only installed MOV

actuator part number that is affected by this service bulletin.

This service bulletin gives instruction on how to measure the electrical resistance of bonds at the

installed MOV actuator locations, how to prepare a Faying surface for the install of the new MOV

actuator, how to prepare affected airplane parts, and how to install the new MOV actuator.

This service bulletin is the result of a safety assessment conducted by Boeing under SFAR 88, "Fuel

Tank System Fault Tolerance Evaluation Requirements".

Section 9 of the Maintenance Planning Data (MPD) document was changed.

Revision 1 is sent to correct the accomplishment instructions and to correct the MOV actuator part

number.

Revision 2 is sent to add a step to apply BMS 5-95 as cap seal on the bonding jumper fasteners, to

clarify the quantity of BMS 5-95 consumed, and to clarify optional part numbers for BMS 5-95 when

installing the MOV actuator.

D. Description

The following actions are necessary:

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BOEING SERVICE BULLETIN 777-28A0034
— 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 MOV actuator

part number MA20A1001-1 is the only installed MOV actuator part number that is affected by this

service bulletin.

— If you are required to install the MOV actuator part number MA30A1001, you must do an electrical

resistance check of 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.

— Remove, rework, and reinstall the bracket at the APU Isolation MOV actuator location to prevent

part interference with the new MOV actuator part number MA30A1001.

— Close access to each MOV actuator.

Revision 1 - No more work is necessary on airplanes changed as shown in the original issue of this

service bulletin.

Revision 2 - No more work is necessary on airplanes changed in accordance with the original issue or

Revision 1 of this service bulletin.

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

Group 1:

Affected Maintenance Zones

Model Zone

777-200, 777-300 531, 533, 543, 551, 631, 633, 643, 651

Group 2:

Affected Maintenance Zones

Model Zone

777-200LR, 777-300ER 531, 533, 543, 551, 631, 633, 643, 651

E. Compliance

Federal Aviation Administration (FAA) Notice of Proposed Rule Making 2008-NM-056-AD, is related

to this service bulletin.

Boeing recommends that operators accomplish this service bulletin be incorporated within 60 months

after the original issue date on this service bulletin.

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BOEING SERVICE BULLETIN 777-28A0034
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.

G. Manpower

The tables below shows an estimate of the task hours necessary to do these work packages 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:

• 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 V28164

2 V28264

3 V28163/V28263

4 V28023

5 V28031

6 V28310

7 V28166

8 V28266

9 V28166

10 V28266

11 V28165

12 V28265

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Work Packages for All Groups

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

Figure 7 1 0.25 0.25

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

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Work Packages for All Groups

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

Figure 7 1 0.25 0.25

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

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Work Packages for All Groups

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 0.50 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

Figure 7 1 0.25 0.25

Close fuel tank 2 8.00 4.00

access (a)

Close MOV ac- 1 0.10 0.10

tuator access

Total for Work Package 52.70 22.20

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Work Packages for All Groups

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 21 1 0.25 0.25

Close MOV ac- 1 0.50 0.50

tuator access

Total for Work Package 2.6 2.1

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 13 1 2.00 2.00

Figure 21 1 0.25 0.25

Close MOV ac- 1 0.50 0.50

tuator access

Total for Work Package 4.6 4.1

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Work Packages for All Groups

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 14 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

Figure 7 1 0.25 0.25

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

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Work Packages for All Groups

Elapsed

Hours

Number of Task Hours

Persons

Work Package Tasks

Work Package 7 Prepare 2 1.00 0.50

Open MOV ac- 1 0.10 0.10

tuator access

Figure 15 1 0.50 0.50

Remove MOV 1 0.25 0.25

actuator

Figure 22 1 0.25 0.25

Close MOV ac- 1 0.50 0.50

tuator access

Total for Work Package 2.6 2.1

Work Package 8 Prepare 2 1.00 0.50

Open MOV ac- 1 0.10 0.10

tuator access

Figure 16 1 0.50 0.50

Remove MOV 1 0.25 0.25

actuator

Figure 22 1 0.25 0.25

Close MOV ac- 1 0.50 0.50

tuator access

Total for Work Package 2.6 2.1

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Work Packages for All Groups

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 17 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

Figure 7 1 0.25 0.25

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

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Work Packages for All Groups

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 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

Figure 7 1 0.25 0.25

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

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Work Packages for All Groups

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 19 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

Figure 7 1 0.25 0.25

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

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BOEING SERVICE BULLETIN 777-28A0034
Work Packages for All Groups

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 20 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

Figure 7 1 0.25 0.25

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) 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 is not satisfactory.

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BOEING SERVICE BULLETIN 777-28A0034
Group 1:

Only the Work Packages for this Group

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

Work Package 1 52.45 21.95

Work Package 2 52.45 21.95

Work Package 3 52.70 22.20

Work Package 4 2.60 2.10

Work Package 5 4.60 4.10

Work Package 6 52.45 21.95

Work Package 7 2.60 2.10

Work Package 8 2.60 2.10

Work Package 11 52.45 21.95

Work Package 12 52.45 21.95

TOTAL FOR EACH AIRPLANE 327.35 142.35

(a) See the Work Package tables for details.

Group 2:

Only the Work Packages for this Group

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

Work Package 1 52.45 21.95

Work Package 2 52.45 21.95

Work Package 3 52.70 22.20

Work Package 4 2.60 2.10

Work Package 5 4.60 4.10

Work Package 6 52.45 21.95

Work Package 9 52.45 21.95

Work Package 10 52.45 21.95

Work Package 11 52.45 21.95

Work Package 12 52.45 21.95

TOTAL FOR EACH AIRPLANE 427.05 182.05

(a) See the Work Package tables for details.

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BOEING SERVICE BULLETIN 777-28A0034
H. Weight and Balance Changes

Change in Moment

(Pound-Inches)

Change in Weight

(Pounds)

Airplane

777-200 +4.1 +5448.9

777-300 +4.1 +6199.2

Change in Moment (Pound-Inches)Work Package Change in Weight (Pounds)

Work Package 1 +0.4 +483.2

Work Package 2 +0.4 +483.2

Work Package 3 +0.4 +466.6

Work Package 4 +0.4 +474.0

Work Package 5 +0.4 +474.0

Work Package 6 +0.4 +465.1

Work Package 7 +0.4 +582.4

Work Package 8 +0.4 +582.4

Work Package 9 +0.4 +582.4

Work Package 10 +0.4 +582.4

Work Package 11 +0.4 +465.3

Work Package 12 +0.4 +465.3

I. Electrical Load Data

Not changed.

J. References

1. Existing Data:

a. Engineering Change Memo PRR 61998-3

b. Standard Overhaul Practices Manual (SOPM) 20-30-03, 20-43-03, 20-50-10

c. Standard Wiring Practices Manual (SWPM) 20-20-00

d. 777 Aircraft Maintenance Manual (AMM) 28-22-01, 28-22-02, 28-22-02, 28-22-03, 28-22-04,

28-25-02, 28-25-05, 28-26-01, 28-26-02, 28-31-02, 28-31-03, 28-31-04, 28-31-05

e. FAA Notice of Proposed Rule Making 2008-NM-056-AD.

2. Data supplied with this Service Bulletin:

None.

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BOEING SERVICE BULLETIN 777-28A0034
3. Installation Drawings Used in the Preparation of this Service Bulletin:

Drawing Number Title

343W3001 Equipment Inst - Engine Fuel Feed System

344W3001 Equipment Inst - Refueling and Jettison System (left wing)

344W3001 Equipment Inst - Refueling and Jettison System (right wing)

346W3001 Equipment Inst - APU Fuel Feed (wing)

112W1003 Rear Spar Assy - Wing

K. Publications Affected

Publication Chapter-Section

777 Maintenance Manual 28-22, 28-25, 28-26, 28-31

777 Illustrated Parts Catalog 28-22, 28-25, 28-26, 28-31

777 Maintenance Planning Data 9

1. Publications:

None.

2. Damage Tolerance Based Structural Inspections:

Boeing has evaluated the repairs and/or changes in 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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BLANK PAGE
2. MATERIAL INFORMATION

A. Material - Price and Availability

The operator can supply the parts and materials shown in Paragraph 2.C., Parts Necessary For Each

Airplane. As an alternative, operators can purchase the parts from Boeing Spares. This service bulletin

does not show the Boeing price and supply data.

B. Industry Support Information

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

C. Parts Necessary For Each Airplane

1. Kits/Parts:

None.

2. Parts and Materials Supplied by the Operator:

Group 1:

Part Number / QTY Name Notes

Specification

Replaces MA20A1001-1

(S343T003-39)

MA30A1001 11 Motor Operated Valve Actuator

(S343T003-66) (a)

pressure and environmental sealant- (b) (c) (e)

chromate type, class B

BMS 5-95 66 oz

BACJ40A20-5 6 bonding jumper, 5 inch (d)

BACJ40A20-6 3 bonding jumper, 6 inch (d)

BACJ40A20-7 1 bonding jumper, 7 inch (d)

BACJ40A20-9 1 bonding jumper, 9 inch (d)

colored chemical conversion coating

for aluminum, type 2, class A or D

BAC 5626 4 oz.

chemical and solvent resistant finish

(primer)

BMS 10-11 4 oz.

(a) Supplier: ITT Aerospace Controls 28150 Industry Drive, Valencia, CA, 91355 USA.

(b) For use on surfaces outside of a fuel tank that may be exposed to fuel.

(c) BMS 5-45 Fuel Tank Sealant is optional (BAC5117-6).

(d) The new MOV actuator (MA30A1001) installation may require that a longer bonding

jumper be installed to reach the bonding jumper mounting screw on either side of the

MOV actuator.

(e) BMS 5-45 or BMS 5-145 can be used as a substitute for BMS 5-95 for the application of

cap seal on the MOV actuator bonding jumper fasteners as described in the work packages

of this service bulletin.

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BOEING SERVICE BULLETIN 777-28A0034
Group 2:

Part Number / QTY Name Notes

Specification

Replaces MA20A1001-1

(S343T003-39)

MA30A1001 11 Motor Operated Valve Actuator

(S343T003-66) (a)

Pressure and Environmental (b) (c) (e)

Sealant-Chromate Type

BMS 5-95 66 oz

BACJ40A20-5 6 bonding jumper, 5 inch (d)

BACJ40A20-6 1 bonding jumper, 6 inch (d)

BACJ40A20-7 3 bonding jumper, 7 inch (d)

BACJ40A20-9 1 bonding jumper, 9 inch (d)

colored chemical conversion coating

for aluminum, type 2, class A or D

BAC 5626 4 oz.

chemical and solvent resistant finish

(primer)

BMS 10-11 4 oz.

(a) Supplier: ITT Aerospace Controls 28150 Industry Drive, Valencia, CA, 91355 USA

(b) For use on surfaces outside of a fuel tank that may be exposed to fuel

(c) BMS 5-45 Fuel Tank Sealant is optional (BAC5117-6).

(d) The new MOV actuator (MA30A1001) installation may require that a longer bonding

jumper be installed to reach the bonding jumper mounting screw on either side of the

MOV actuator.

(e) BMS 5-45 or BMS 5-145 can be used as a substitute for BMS 5-95 for the application of

cap seal on the MOV actuator bonding jumper fasteners as described in the work packages

of this service bulletin.

3. Parts Modified and Reidentified:

None.

4. Parts Removed and Not Replaced:

None.

D. Parts Necessary to Change Spares

None.

E. Special Tooling - Price and Availability

None.

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BOEING SERVICE BULLETIN 777-28A0034
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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BOEING SERVICE BULLETIN 777-28A0034

BLANK PAGE
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:

— Torque limits to tighten nuts and bolts are given in Structural Repair Manual,

Chapter 51.

5. For approved fastener and process material substitutions, refer to 777 Structural

Repair Manual, Chapter 51, Alternate fasteners are given in 777 Structural Repair

Manual Chapter 51 and Boeing Drawing 777 012W6100.

6. Refer to the Boeing Standard Wiring Practices Manuals 20-10-11 and 20-10-12 for

the wire installation procedures.

7. 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.

8. All AMM references refer to the post 777-28A0034 procedures in the AMM.

B. WORK INSTRUCTIONS

Group 1-2:

Work Package 1 - ENGINE FUEL SPAR VALVE ACTUATOR - LEFT (V28164)

1. Get access to the MOV actuator. Refer to 777 AMM 28-22-02 as an accepted procedure.

2. Read and record the part number of the MOV actuator as given in Figure 1.

a. If the MOV actuator is not part number MA20A1001-1, the part is acceptable. No more work

is necessary at this location.

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BOEING SERVICE BULLETIN 777-28A0034
(1) Close Access to each MOV actuator. Refer to 777 AMM 28-22-02 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 777 AMM 28-22-02 as an accepted procedure.

(2) Remove and keep the index plate as given in Figure 2.

NOTE: Make an ink mark with a pen across the index plate, the adapter plate, and the

airplane structure as a reference for installation alignment.

(3) Rework the index plate as given in Figure 3.

(4) Prepare the adapter plate surface as given in Figure 5.

(5) Measure and record the electrical resistance of the bond from the adapter plate to the

airplane structure as given in Figure 4.

(a) If the resistance is less than 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 777 AMM 28-22-01 as an accepted procedure.

3) Install the MOV actuator as given in Figure 7. Refer to 777 AMM 28-22-02 as

an accepted procedure for the install of the MOV actuator body.

4) Do an operational test of MOV actuator. Refer to 777 AMM 28-22-02 as an

accepted procedure.

(b) If the resistance is 1.5 milliohms or greater, the bond is not acceptable. A 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 777 AMM 28-22-01

as an accepted procedure.

2) Remove the adapter plate and adapter shaft. Refer to 777 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 777 AMM 28-22-01 as

an accepted procedure.

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BOEING SERVICE BULLETIN 777-28A0034
5) Prepare the adapter plate surface as given in Figure 5.

6) Measure and record the electrical resistance of the bond from the adapter plate

to the airplane structure as given in Figure 4.

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

following steps:

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

Figure 6.

{2} Install the index plate. Refer to 777 AMM 28-22-01 as an accepted

procedure.

{3} Install the MOV actuator as given in Figure 7. Refer to 777 AMM

28-22-02 as an accepted procedure for the install of the MOV actuator

body.

{4} Do an operational test of MOV actuator. Refer to 777 AMM 28-22-02

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 777 AMM 28-22-01 as an

accepted procedure.

3. Close access to the MOV actuator. Refer to 777 AMM 28-22-02 as an accepted procedure.

4. Put the airplane in a serviceable condition or do another work package.

Group 1-2:

Work Package 2 - ENGINE FUEL SPAR VALVE ACTUATOR - RIGHT (V28264)

1. Get access to the MOV actuator. Refer to 777 AMM 28-22-02 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 each MOV actuator. Refer to 777 AMM 28-22-02 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:

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BOEING SERVICE BULLETIN 777-28A0034
(1) Remove and discard the MOV actuator, and remove and keep the bonding jumper. Refer

to 777 AMM 28-22-02 as an accepted procedure.

(2) Remove and keep the index plate as given in Figure 2.

NOTE: Make an ink mark with a pen across the index plate, the adapter plate, and the

airplane structure as a reference for installation alignment.

(3) Rework the index plate as given in Figure 3.

(4) Prepare the adapter plate surface as given in Figure 5.

(5) Measure and record the electrical resistance of the bond from the adapter plate to the

airplane structure as given in Figure 4.

(a) If the resistance is less than 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 777 AMM 28-22-01 as an accepted procedure.

3) Install the MOV actuator as given in Figure 7. Refer to 777 AMM 28-22-02 as

an accepted procedure for the install of the MOV actuator body.

4) Do an operational test of MOV actuator. Refer to 777 AMM 28-22-02 as an

accepted procedure.

(b) If the resistance is 1.5 milliohms or greater, the bond is not acceptable. A 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 777 AMM 28-22-01

as an accepted procedure.

2) Remove the adapter plate and adapter shaft. Refer to 777 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 777 AMM 28-22-01 as

an accepted procedure.

5) Prepare the adapter plate surface as given in Figure 5.

6) Measure and record the electrical resistance of the bond from the adapter plate

to the airplane structure as given in Figure 4.

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

following steps:

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BOEING SERVICE BULLETIN 777-28A0034
{1} Temporarily put the index plate in position for installation as given in

Figure 6.

{2} Install the index plate. Refer to 777 AMM 28-22-01 as an accepted

procedure.

{3} Install the MOV actuator as given in Figure 7. Refer to 777 AMM

28-22-02 as an accepted procedure for the install of the MOV actuator

body.

{4} Do an operational test of MOV actuator. Refer to 777 AMM 28-22-02

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 777 AMM 28-22-01 as an

accepted procedure.

3. Close access to the MOV actuator. Refer to 777 AMM 28-22-02 as an accepted procedure.

4. Put the airplane in a serviceable condition or do another work package.

Group 1-2:

Work Package 3 - FORWARD/AFT CROSSFEED VALVE ACTUATOR - LEFT (V28163/V28263)

1. Get access to each MOV actuator. Refer to 777 AMM 28-22-04 as an accepted procedure.

2. For each MOV actuator, read and record the part number of each 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 each MOV actuator. Refer to 777 AMM 28-22-04 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 777 AMM 28-22-04 as an accepted procedure.

(2) Remove and keep the index plate as given in Figure 2.

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BOEING SERVICE BULLETIN 777-28A0034
NOTE: Make an ink mark with a pen across the index plate, the adapter plate, and the

airplane structure as a reference for installation alignment.

(3) Rework the index plate as given in Figure 3.

(4) Prepare the adapter plate surface as given in Figure 5.

(5) Measure and record the electrical resistance of the bond from the adapter plate to the

airplane structure as given in Figure 4.

(a) If the resistance is less than 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 777 AMM 28-22-03 as an accepted procedure.

3) Install the MOV actuator as given in Figure 7. Refer to 777 AMM 28-22-04 as

an accepted procedure for the install of the MOV actuator body.

4) Do an operational test of MOV actuator. Refer to 777 AMM 28-22-04 as an

accepted procedure.

(b) If the resistance is 1.5 milliohms or greater, the bond is not acceptable. A 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 777 AMM 28-22-03

as an accepted procedure.

2) Remove the adapter plate and adapter shaft. Refer to 777 AMM 28-22-03 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 777 AMM 28-22-03 as

an accepted procedure.

5) Prepare the adapter plate surface as given in Figure 5.

6) Measure and record the electrical resistance of the bond from the adapter plate

to the airplane structure as given in Figure 4.

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

following steps:

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BOEING SERVICE BULLETIN 777-28A0034
{1} Temporarily put the index plate in position for installation as given in

Figure 6.

{2} Install the index plate. Refer to 777 AMM 28-22-03 as an accepted

procedure.

{3} Install the MOV actuator as given in Figure 7. Refer to 777 AMM

28-22-04 as an accepted procedure for the install of the MOV actuator

body.

{4} Do an operational test of MOV actuator. Refer to 777 AMM 28-22-04

as an accepted procedure.

b) If the resistance is 0.5 milliohms or greater, the bond is not acceptable. Do

the following steps:

{1} Return to step 2.b.(5)(b)2) and rework the bond until it is acceptable.

7) Close access to the Motor Operated Valve. Refer to 777 AMM 28-22-03 as an

accepted procedure.

3. For each MOV actuator, close access to the MOV actuator. Refer to 777 AMM 28-22-04 as an

accepted procedure.

4. Put the airplane in a serviceable condition or do another work package.

Group 1-2:

Work Package 4 - APU FUEL SHUTOFF VALVE ACTUATOR - LEFT (V28023)

1. Get access to the MOV actuator. Refer to 777 AMM 28-25-02 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 each MOV actuator. Refer to 777 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:

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BOEING SERVICE BULLETIN 777-28A0034
(1) Remove and discard the MOV actuator, and remove and keep the bonding jumper. Refer

to 777 AMM 28-25-02 as an accepted procedure.

(2) Install the MOV actuator as given in Figure 21. Refer to 777 AMM 28-25-02 as an accepted

procedure for the install of the MOV actuator body.

(3) Do an operational test of MOV actuator. Refer to 777 AMM 28-25-02 as an accepted

procedure.

3. When you are done with the work, close access to the MOV actuator. Refer to 777 AMM 28-25-02

as an accepted procedure.

4. Put the airplane in a serviceable condition or do another work package.

Group 1-2:

Work Package 5 - APU FUEL ISOLATION VALVE ACTUATOR - LEFT (V28031)

1. Get access to the MOV actuator. Refer to 777 AMM 28-25-05 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 each MOV actuator. Refer to 777 AMM 28-25-05 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 777 AMM 28-25-05 as an accepted procedure.

(2) Remove, Rework, and Install the bracket at APU Isolation MOV actuator to provided

space for the new actuator. Do work as given in Figure 13.

(3) Install the MOV actuator as given in Figure 21. Refer to 777 AMM 28-25-05 as an accepted

procedure for the install of the MOV actuator body.

(4) Do an operational test of MOV actuator. Refer to 777 AMM 28-25-05 as an accepted

procedure.

3. Close access to the MOV actuator. Refer to 777 AMM 28-25-05 as an acceptable procedure.

4. Put the airplane in a serviceable condition or do another work package.

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BOEING SERVICE BULLETIN 777-28A0034
Group 1-2:

Work Package 6 - DEFUEL VALVE ACTUATOR - RIGHT (V28310)

1. Get access to the MOV actuator. Refer to 777 AMM 28-26-02 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.

(1) Close Access to each MOV actuator. Refer to 777 AMM 28-26-02 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 777 AMM 28-26-02 as an accepted procedure.

(2) Remove and keep the index plate as given in Figure 2.

NOTE: Make an ink mark with a pen across the index plate, the adapter plate, and the

airplane structure as a reference for installation alignment.

(3) Rework the index plate as given in Figure 3.

(4) Prepare the adapter plate surface as given in Figure 5.

(5) Measure and record the electrical resistance of the bond from the adapter plate to the

airplane structure as given in Figure 4.

(a) If the resistance is less than 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 777 AMM 28-26-01 as an accepted procedure.

3) Install the MOV actuator as given in Figure 7. Refer to 777 AMM 28-26-02 as

an accepted procedure for the install of the MOV actuator body.

4) Do an operational test of MOV actuator. Refer to 777 AMM 28-26-02 as an

accepted procedure.

(b) If the resistance is 1.5 milliohms or greater, the bond is not acceptable. A fuel tank

entry is necessary to make an acceptable bond. Do the following steps:

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BOEING SERVICE BULLETIN 777-28A0034
1) Get access to the Motor Operated Valve (MOV). Refer to 777 AMM 28-26-01

as an accepted procedure.

2) Remove the adapter plate and adapter shaft. Refer to 777 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 777 AMM 28-26-01 as

an accepted procedure.

5) Prepare the adapter plate surface as given in Figure 5.

6) Measure and record the electrical resistance of the bond from the adapter plate

to the airplane structure as given in Figure 4.

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

following steps:

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

Figure 6.

{2} Install the index plate. Refer to 777 AMM 28-26-01 as an accepted

procedure.

{3} Install the MOV actuator as given in Figure 7. Refer to 777 AMM

28-26-02 as an accepted procedure for the install of the MOV actuator

body.

{4} Do an operational test of MOV actuator. Refer to 777 AMM 28-26-02

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 777 AMM 28-26-01 as an

accepted procedure.

3. Close access to the MOV actuator. Refer to both 777 AMM 28-26-02 as an accepted procedure.

4. Put the airplane in a serviceable condition or do another work package.

Group 1:

Work Package 7 - FUEL JETTISON NOZZLE VALVE ACTUATOR - LEFT (V28166)

1. Get access to the MOV actuator. Refer to 777 AMM 28-31-03 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.

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BOEING SERVICE BULLETIN 777-28A0034
(1) Close Access to each MOV actuator. Refer to 777 AMM 28-31-03 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 777 AMM 28-31-03 as an accepted procedure.

(2) Install the MOV actuator as given in Figure 22. Refer to 777 AMM 28-31-03 as an accepted

procedure as an accepted procedure for the install of the MOV actuator body.

(3) Do an operational test of MOV actuator. Refer to 777 AMM 28-31-03 as an accepted

procedure.

3. Close access to the MOV actuator. Refer to 777 AMM 28-31-03 as an accepted procedure.

4. Put the airplane in a serviceable condition or do another work package.

Group 1:

Work Package 8 - FUEL JETTISON NOZZLE VALVE ACTUATOR - RIGHT (V28266)

1. Get access to the MOV actuator. Refer to 777 AMM 28-31-03 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 each MOV actuator. Refer to 777 AMM 28-31-03 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 777 AMM 28-31-03 as an accepted procedure.

(2) Install the MOV actuator as given in Figure 22. Refer to 777 AMM 28-31-03 as an accepted

procedure for the install of the MOV actuator body.

(3) Do an operational test of MOV actuator. Refer to 777 AMM 28-31-03 as an accepted

procedure.

3. Close access to the MOV actuator. Refer to 777 AMM 28-31-03 as an accepted procedure.

4. Put the airplane in a serviceable condition or do another work package.

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BOEING SERVICE BULLETIN 777-28A0034
Group 2:

Work Package 9 - FUEL JETTISON NOZZLE VALVE ACTUATOR - LEFT (V8166)

1. Get access to the MOV actuator. Refer to 777 AMM 28-31-03 as an accepted procedure.

2. Read and record the part number of the 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 777 AMM 28-31-03 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 777 AMM 28-31-03 as an accepted procedure.

(2) Remove and keep the index plate as given in Figure 2.

NOTE: Make an ink mark with a pen across the index plate, the adapter plate, and the

airplane structure as a reference for installation alignment.

(3) Rework the index plate as given in Figure 3.

(4) Prepare the adapter plate surface as given in Figure 5.

(5) Measure and record the electrical resistance of the bond from the adapter plate to the

airplane structure as given in Figure 4.

(a) If the resistance is less than 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 777 AMM 28-31-02 as an accepted procedure.

3) Install the MOV actuator as given in Figure 7. Refer to 777 AMM 28-31-03 as

an accepted procedure for the install of the MOV actuator body.

4) Do an operational test of MOV actuator. Refer to 777 AMM 28-31-03 as an

accepted procedure.

(b) If the resistance is 1.5 milliohms or greater, the bond is not acceptable. A fuel tank

entry is necessary to make an acceptable bond. Do the following steps:

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BOEING SERVICE BULLETIN 777-28A0034
1) Get access to the Motor Operated Valve (MOV). Refer to 777 AMM 28-31-02

as an accepted procedure.

2) Remove the adapter plate and adapter shaft. Refer to 777 AMM 28-31-02 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 777 AMM 28-31-02 as

an accepted procedure.

5) Prepare the adapter plate surface as given in Figure 5.

6) Measure and record the electrical resistance of the bond from the adapter plate

to the airplane structure as given in Figure 4.

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

following steps:

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

Figure 6.

{2} Install the index plate. Refer to 777 AMM 28-31-02 as an accepted

procedure.

{3} Install the MOV actuator as given in Figure 7. Refer to 777 AMM

28-31-03 as an accepted procedure for the install of the MOV actuator

body.

{4} Do an operational test of MOV actuator. Refer to 777 AMM 28-31-03

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 777 AMM 28-31-02 as an

accepted procedure.

3. Close access to the MOV actuator. Refer to 777 AMM 28-31-03 as an accepted procedure.

4. Put the airplane in a serviceable condition or do another work package.

Group 2:

Work Package 10 - FUEL JETTISON NOZZLE VALVE ACTUATOR - RIGHT (V28266)

1. Get access to the MOV actuator. Refer to 777 AMM 28-31-03 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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Original Issue: August 02, 2007

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BOEING SERVICE BULLETIN 777-28A0034
(1) Close Access to each MOV actuator. Refer to 777 AMM 28-31-03 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 777 AMM 28-31-03 as an accepted procedure.

(2) Remove and keep the index plate as given in Figure 2.

NOTE: Make an ink mark with a pen across the index plate, the adapter plate, and the

airplane structure as a reference for installation alignment.

(3) Rework the index plate as given in Figure 3.

(4) Prepare the adapter plate surface as given in Figure 5.

(5) Measure and record the electrical resistance of the bond from the adapter plate to the

airplane structure as given in Figure 4.

(a) If the resistance is less than 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 777 AMM 28-31-02 as an accepted procedure.

3) Install the MOV actuator as given in Figure 7. Refer to 777 AMM 28-31-03 as

an accepted procedure for the install of the MOV actuator body.

4) Do an operational test of MOV actuator. Refer to 777 AMM 28-31-03 as an

accepted procedure.

(b) If the resistance is 1.5 milliohms or greater, the bond is not acceptable. A 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 777 AMM 28-31-02

as an accepted procedure.

2) Remove the adapter plate and adapter shaft. Refer to 777 AMM 28-31-02 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 777 AMM 28-31-02 as

an accepted procedure.

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BOEING SERVICE BULLETIN 777-28A0034
5) Prepare the adapter plate surface as given in Figure 5.

6) Measure and record the electrical resistance of the bond from the adapter plate

to the airplane structure as given in Figure 4.

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

following steps:

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

Figure 6.

{2} Install the index plate. Refer to 777 AMM 28-31-02 as an accepted

procedure.

{3} Install the MOV actuator as given in Figure 7. Refer to 777 AMM

28-31-03 as an accepted procedure for the install of the MOV actuator

body.

{4} Do an operational test of MOV actuator. Refer to 777 AMM 28-31-03

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 777 AMM 28-31-02 as an

accepted procedure.

3. Close access to the MOV actuator. Refer to 777 AMM 28-31-03 as an accepted procedure.

4. Put the airplane in a serviceable condition or do another work package.

Group 1-2:

Work Package 11 - FUEL JETTISON ISOLATION VALVE ACTUATOR - LEFT (V28165)

1. Get access to the MOV actuator. Refer to 777 AMM 28-31-05 as an accepted procedure.

2. Read and record the part number of the MOV actuator as given in Figure 19.

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 777 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:

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BOEING SERVICE BULLETIN 777-28A0034
(1) Remove and discard the MOV actuator, and remove and keep the bonding jumper. Refer

to 777 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 with a pen across the index plate, the adapter plate, and the

airplane structure as a reference for installation alignment.

(3) Rework the index plate as given in Figure 3.

(4) Prepare the adapter plate surface as given in Figure 5.

(5) Measure and record the electrical resistance of the bond from the adapter plate to the

airplane structure as given in Figure 4.

(a) If the resistance is less than 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 777 AMM 28-31-04 as an accepted procedure.

3) Install the MOV actuator as given in Figure 7. Refer to 777 AMM 28-31-05 as

an accepted procedure for the install of the MOV actuator body.

4) Do an operational test of MOV actuator. Refer to 777 AMM 28-31-05 as an

accepted procedure.

(b) If the resistance is 1.5 milliohms or greater, the bond is not acceptable. A 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 777 AMM 28-31-04

as an accepted procedure.

2) Remove the adapter plate and adapter shaft. Refer to 777 AMM 28-31-04 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 777 AMM 28-31-04 as

an accepted procedure.

5) Prepare the adapter plate surface as given in Figure 5.

6) Measure and record the electrical resistance of the bond from the adapter plate

to the airplane structure as given in Figure 4.

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

following steps:

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BOEING SERVICE BULLETIN 777-28A0034
{1} Temporarily put the index plate in position for installation as given in

Figure 6.

{2} Install the index plate. Refer to 777 AMM 28-31-04 as an accepted

procedure.

{3} Install the MOV actuator as given in Figure 7. Refer to 777 AMM

28-31-05 as an accepted procedure for the install of the MOV actuator

body.

{4} Do an operational test of MOV actuator. Refer to 777 AMM 28-31-05

as an accepted procedure.

b) If the resistance is 0.5 milliohms or greater, the bond is not acceptable. Do

the following steps:

{1} Return to step 2.b.(5)(b)2) and rework the bond until it is acceptable.

7) Close access to the Motor Operated Valve. Refer to 777 AMM 28-31-04 as an

accepted procedure.

3. Close access to the MOV actuator. Refer to 777 AMM 28-31-05 as an accepted procedure.

4. Put the airplane in a serviceable condition or do another work package.

Group 1-2:

Work Package 12 - FUEL JETTISON ISOLATION VALVE ACTUATOR - RIGHT (V28265)

1. Get access to the MOV actuator. Refer to 777 AMM 28-31-05 as an accepted procedure.

2. Read and record the part number of the MOV actuator as given in Figure 20.

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 777 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 777 AMM 28-31-05 as an accepted procedure.

(2) Remove and keep the index plate as given in Figure 2.

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BOEING SERVICE BULLETIN 777-28A0034
NOTE: Make an ink mark with a pen across the index plate, the adapter plate, and the

airplane structure as a reference for installation alignment.

(3) Rework the index plate as given in Figure 3.

(4) Prepare the adapter plate surface as given in Figure 5.

(5) Measure and record the electrical resistance of the bond from the adapter plate to the

airplane structure as given in Figure 4.

(a) If the resistance is less than 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 777 AMM 28-31-04 as an accepted procedure.

3) Install the MOV actuator as given in Figure 7. Refer to 777 AMM 28-31-05 as

an accepted procedure for the install of the MOV actuator body.

4) Do an operational test of MOV actuator. Refer to 777 AMM 28-31-05 as an

accepted procedure.

(b) If the resistance is 1.5 milliohms or greater, the bond is not acceptable. A 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 777 AMM 28-31-04

as an accepted procedure.

2) Remove the adapter plate and adapter shaft. Refer to 777 AMM 28-31-04 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 777 AMM 28-31-04 as

an accepted procedure.

5) Prepare the adapter plate surface as given in Figure 5.

6) Measure and record the electrical resistance of the bond from the adapter plate

to the airplane structure as given in Figure 4.

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

following steps:

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BOEING SERVICE BULLETIN 777-28A0034
{1} Temporarily put the index plate in position for installation as given in

Figure 6.

{2} Install the index plate. Refer to 777 AMM 28-31-04 as an accepted

procedure.

{3} Install the MOV actuator as given in Figure 7. Refer to 777 AMM

28-31-05 as an accepted procedure for the install of the MOV actuator

body.

{4} Do an operational test of MOV actuator. Refer to 777 AMM 28-31-05

as an accepted procedure.

b) If the resistance is 0.5 milliohms or greater, the bond is not acceptable. Do

the following steps:

{1} Return to step 2.b.(5)(b)2) and rework the bond until it is acceptable.

7) Close access to the Motor Operated Valve. Refer to 777 AMM 28-31-04 as an

accepted procedure.

3. Close access to the MOV actuator. Refer to 777 AMM 28-31-05 as an accepted procedure.

4. Put the airplane in a serviceable condition or do another work package.

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BOEING SERVICE BULLETIN 777-28A0034
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 the figure.

FIGURE 1: INSPECT AND RECORD THE ENGINE FUEL SPAR MOV ACTUATOR PART NUMBER (LEFT

WING)

(SHEET 1 OF 2)

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BOEING SERVICE BULLETIN 777-28A0034
STEP TASK NAME IDENTIFICATION QTY MORE DATA

Get access to the

part number markings on the MOV ac-

- 1 tuator.

Motor Operated Valve

1 Get Actuator

Record the part

- 1 number.

Motor Operated Valve

2 Record Actuator

FIGURE 1: INSPECT AND RECORD THE ENGINE FUEL SPAR MOV ACTUATOR PART NUMBER (LEFT

WING)

(SHEET 2 OF 2)

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BOEING SERVICE BULLETIN 777-28A0034
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 the figure.

FIGURE 2: REMOVE AND KEEP INDEX PLATE

(SHEET 1 OF 2)

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BOEING SERVICE BULLETIN 777-28A0034
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 align1 Make Reference Mark - - ment.

Remove from the index plate mounting

2 Remove Lockwire - - screws.

- 3

Index Plate Mounting

3 Remove / Keep Screw

4 Remove / Keep Index Plate - 1 Keep for rework.

FIGURE 2: REMOVE AND KEEP INDEX PLATE

(SHEET 2 OF 2)

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BOEING SERVICE BULLETIN 777-28A0034
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 the figure.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

(a) Remove anodized material from

the index plate contact surface locations using an abrasive pad. Refer to

SOPM 20-30-03 as

an accepted proce1 Remove Anodized Material - - dure.

Clean contact surfaces. Refer to

SOPM 20-30-03 as

an accepted proce2 Clean Index Plate - - dure.

(a) Make sure not to remove the reference mark needed for alignment.

FIGURE 3: REWORK INDEX PLATE

(SHEET 1 OF 1)

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BOEING SERVICE BULLETIN 777-28A0034
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 the figure.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

Measure electrical

resistance from the

adapter plate to the

rear wing spar. Refer to SWPM 20-20-

00 as an accepted

procedure.

1 Measure Electrical Bond - 1

Record the electrical

resistance in milliohms.

2 Record Electrical Bond - 1

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

AIRPLANE STRUCTURE

(SHEET 1 OF 1)

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BOEING SERVICE BULLETIN 777-28A0034
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 the figure.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

Remove surface

material from

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

SOPM 20-30-03 as

an accepted procedure.

1 Clean Adapter Plate - -

Clean contact surface locations. Refer

to SOPM 20-30-03

as an accepted procedure.

2 Clean Adapter Plate - -

Use a minimum

amount of sealant to

reduce squeeze out.

BMS 5-95 (BMS 5-45 -

optional)

Pressure and Environmental Sealant-Chromate Type

3 Apply

FIGURE 5: PREPARE ADAPTER PLATE SURFACE

(SHEET 1 OF 1)

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BOEING SERVICE BULLETIN 777-28A0034
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 the figure.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

Align reference

markings made during index plate removal.

1 Put / Hold Index Plate - 1

Insert the kept bottom screw only.Index Plate Mounting - 1

Screw

2 Insert

Tighten only to hold

index plate in place

for install.

Index Plate Mounting - 1

Screw

3 Tighten

FIGURE 6: PUT INDEX PLATE IN POSITION FOR INSTALLATION

(SHEET 1 OF 1)

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BOEING SERVICE BULLETIN 777-28A0034
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 the figure.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

Apply a Faying bond

to the index plate.

(a)

BMS 5-95 (BMS 5-45 -

optional)

Pressure and Environmental Sealant-Chromate Type1 Apply

Do not connect the

bonding jumper to

the MOV actuator.

Motor Operated Valve MA30A1001 1

Actuator

2 Install (New)

FIGURE 7: INSTALL THE MOV ACTUATOR (DIRECTLY TO THE INDEX PLATE)

(SHEET 1 OF 4)

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BOEING SERVICE BULLETIN 777-28A0034
STEP TASK NAME IDENTIFICATION QTY MORE DATA

Measure the electrical resistance of the

Faying bond from

the foot of the MOV

actuator to the airplane structure. (a)

(b)

3 Measure Electrical Bond - -

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 5-to-9

inches. (a)

Bonding Jumper, 5 IN BACJ40A20-5 1

(optional)

4 Measure

If you determined

that the bonding

jumper is too short,

remove the bonding

jumper and do the

following sub-tasks.

Bonding Jumper, 5 IN BACJ40A20-5 1

(optional)

Remove

You can select a

length from 5-to-9

inches.(a)

Bonding Jumper, 5 IN BACJ40A20-5 1

(optional)

Get

Bonding Jumper, 6 IN BACJ40A20-6 1

(optional)

Bonding Jumper, 7 IN BACJ40A20-7 1

(optional)

Bonding Jumper, 9 IN BACJ40A20-9 1

(optional)

FIGURE 7: INSTALL THE MOV ACTUATOR (DIRECTLY TO THE INDEX PLATE)

(SHEET 2 OF 4)

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BOEING SERVICE BULLETIN 777-28A0034
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

jumpers to the airplane structure. Use

the shortest bonding

jumper that allows

no tension. You can

select a length from

5-to-9 inches. (a)

Attach Bonding Jumper - 1

Apply a Faying bond

at the airplane structure for the bonding

jumper of the correct

length. (a)

BMS 5-95 (BMS 5-45 -

optional)

Pressure and Environmental Sealant-Chromate TypeApply

Torque fasteners.

(a)

Torque Bonding Jumper - 1

Clean the surface of

the bonding jumper

lug and fasteners,

and the MOV actuator. (a)

6 Clean Bonding Jumper - 1

Measure the electrical 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 - -

FIGURE 7: INSTALL THE MOV ACTUATOR (DIRECTLY TO THE INDEX PLATE)

(SHEET 3 OF 4)

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BOEING SERVICE BULLETIN 777-28A0034
STEP TASK NAME IDENTIFICATION QTY MORE DATA

Attach the bonding

jumper to the MOV

actuator.

7 Attach Bonding Jumper - -

Apply a Faying bond

at the MOV actuator

for the bonding

jumper. (a)

BMS 5-95 (BMS 5-45 1

optional)

Pressure and Environmental Sealant-Chromate TypeApply

Torque fasteners.

(a)

Torque Bonding Jumper - 1

Measure the electrical 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 of the MOV

actuator. (a) (d) (e)

Measure Electrical Bond - -

Apply cap seal to the

bonding jumper fasteners.(a) (f)

BMS 5-95 (BMS 5-45 -

optional)

Pressure and Environmental Sealant-Chromate Type8 Apply

(a) Refer to SWPM 20-20-00 as an accepted procedure.

(b) If the measured electrical 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 resistance

of the Faying bond is not acceptable, rework the Faying Bond as necessary.

(c) If the measured 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 resistance of the Faying bond is not acceptable, rework the Faying Bond as necessary.

(d) If the measured 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 of the MOV actuator is less than 1.5 milliohms, the Faying bond is acceptable. If the measured electrical 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.

(f) BMS 5-45 or BMS 5-145 can be used as a substitute for BMS 5-95 for the application of cap seal on the

MOV actuator bonding jumper fasteners as described in the work packages of this service bulletin.

FIGURE 7: INSTALL THE MOV ACTUATOR (DIRECTLY TO THE INDEX PLATE)

(SHEET 4 OF 4)

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BOEING SERVICE BULLETIN 777-28A0034
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 the figure.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

Clean contact surfaces. Refer to

SOPM 20-30-03 as

an accepted proce1 Clean Adapter Plate - 1 dure.

Clean contact surfaces. Refer to

SOPM 20-30-03 as

an accepted proce2 Clean Airplane Surface - - dure.

FIGURE 8: CLEAN ADAPTER PLATE AND AIRPLANE SURFACE

(SHEET 1 OF 1)

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BOEING SERVICE BULLETIN 777-28A0034
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 the figure.

FIGURE 9: INSPECT AND RECORD THE ENGINE FUEL SPAR MOV ACTUATOR PART NUMBER (RIGHT

WING)

(SHEET 1 OF 2)

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BOEING SERVICE BULLETIN 777-28A0034
STEP TASK NAME IDENTIFICATION QTY MORE DATA

Get access to the

part number markings on the MOV ac-

- 1 tuator.

Motor Operated Valve

1 Get Actuator

Record the part

- 1 number.

Motor Operated Valve

2 Record Actuator

FIGURE 9: INSPECT AND RECORD THE ENGINE FUEL SPAR MOV ACTUATOR PART NUMBER (RIGHT

WING)

(SHEET 2 OF 2)

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BOEING SERVICE BULLETIN 777-28A0034
FIGURE 10: INSPECT AND RECORD THE FORWARD/AFT CROSSFEED MOV ACTUATOR PART NUMBER

(LEFT WING)

(SHEET 1 OF 2)

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BOEING SERVICE BULLETIN 777-28A0034
STEP TASK NAME IDENTIFICATION QTY MORE DATA

Get access to the

part number markings on the MOV actuator.

Motor Operated Valve - 1

Actuator

1 Get

Record the part

number of forward

crossfeed MOV Actuator.

Motor Operated Valve - 1

Actuator

2 Record

Get access to the

part number markings on the MOV actuator.

Motor Operated Valve - 1

Actuator

3 Get

Record the part

number of forward

crossfeed MOV Actuator.

Motor Operated Valve - 1

Actuator

4 Record

FIGURE 10: INSPECT AND RECORD THE FORWARD/AFT CROSSFEED MOV ACTUATOR PART NUMBER

(LEFT WING)

(SHEET 2 OF 2)

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BOEING SERVICE BULLETIN 777-28A0034
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 the figure.

FIGURE 11: INSPECT AND RECORD THE APU FUEL SHUTOFF MOV ACTUATOR PART NUMBER (LEFT

WING).

(SHEET 1 OF 2)

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BOEING SERVICE BULLETIN 777-28A0034
STEP TASK NAME IDENTIFICATION QTY MORE DATA

Get access to the

part number markings on the MOV ac-

- 1 tuator.

Motor Operated Valve

1 Get Actuator

Record the part

- 1 number.

Motor Operated Valve

2 Record Actuator

FIGURE 11: INSPECT AND RECORD THE APU FUEL SHUTOFF MOV ACTUATOR PART NUMBER (LEFT

WING).

(SHEET 2 OF 2)

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BOEING SERVICE BULLETIN 777-28A0034
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 the figure.

FIGURE 12: INSPECT AND RECORD THE APU ISOLATION MOV ACTUATOR PART NUMBER (LEFT

WING).

(SHEET 1 OF 2)

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BOEING SERVICE BULLETIN 777-28A0034
STEP TASK NAME IDENTIFICATION QTY MORE DATA

Get access to the

part number markings on the MOV ac-

- 1 tuator.

Motor Operated Valve

1 Get Actuator

Record the part

- 1 number.

Motor Operated Valve

2 Record Actuator

FIGURE 12: INSPECT AND RECORD THE APU ISOLATION MOV ACTUATOR PART NUMBER (LEFT

WING).

(SHEET 2 OF 2)

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BOEING SERVICE BULLETIN 777-28A0034
FIGURE 13: REWORK BRACKET AT APU ISOLATION MOV ACTUATOR AREA ONLY

(SHEET 1 OF 4)

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BOEING SERVICE BULLETIN 777-28A0034
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 the figure.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

Locate the bracket

on the left wing rear

spar, attached to rib

number six, near the

APU isolation valve

actuator area.

1 Locate Bracket 287W1224-387 1

FIGURE 13: REWORK BRACKET AT APU ISOLATION MOV ACTUATOR AREA ONLY

(SHEET 2 OF 4)

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BOEING SERVICE BULLETIN 777-28A0034
STEP TASK NAME IDENTIFICATION QTY MORE DATA

Remove all wire harnesses, P-clamps

and jumper cables

needed to get access to the Bracket.

(a) (b)

2 Remove / Keep Wire Harness Generic - -

Clean and prepare

area as given in this

figure. Refer to

SOPM 20-30-03 as

an acceptable procedure.

3 Clean Bracket 287W1224-387 1

Cut out a 1.0 X 0.35

inch area from the

bracket as given in

this figure. (c) (d)

4 Cut Bracket 287W1224-387 1

Chamfer all corners

to a 0.25 inch radius.

5 Chamfer Bracket 287W1224-387 1

Mark this part with

the new part number. Refer to SOPM

20-50-10 as an accepted procedure.

6 Identify Bracket 287W1224-435 1

Apply chemical

coating to the area

of bracket where the

finish was removed.

Colored Chemical Con- BAC 5626 -

version Coating for Aluminum, Type 2, Class

A or D

7 Apply

Apply primer to the

area of bracket

where the finish was

removed. Refer to

SOPM 20-43-03 as

an accepted procedure.

Chemical and Solvent BMS 10-11 -

Resistant Finish

(primer)

Apply

Install all kept wire

harnesses, Pclamps and jumper

cables. (a) (b)

8 Install (Kept) Wire Harness Generic - -

(a) If you need to remove and install the bracket to make the modification, refer to SWPM 20-20-00 as an

accepted procedure for the install of driven rivet electrical bonds (Category 7).

(b) If you need to remove and install the bracket to make the modification, refer to SWPM 20-20-00 as an

accepted procedure for fastener selection.

FIGURE 13: REWORK BRACKET AT APU ISOLATION MOV ACTUATOR AREA ONLY

(SHEET 3 OF 4)

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BOEING SERVICE BULLETIN 777-28A0034
STEP TASK NAME IDENTIFICATION QTY MORE DATA

(c) You may want to drill a 0.25 inch radius at the inner corner before you cut. Refer to the figure.

(d) Keep a .33 inch minimum edge margin from the P-clamp attach hole. Refer to the figure.

FIGURE 13: REWORK BRACKET AT APU ISOLATION MOV ACTUATOR AREA ONLY

(SHEET 4 OF 4)

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BOEING SERVICE BULLETIN 777-28A0034
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 the figure.

FIGURE 14: INSPECT AND RECORD THE DEFUEL MOV ACTUATOR PART NUMBER (RIGHT WING).

(SHEET 1 OF 2)

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BOEING SERVICE BULLETIN 777-28A0034
STEP TASK NAME IDENTIFICATION QTY MORE DATA

Get access to the

part number markings on the MOV ac-

- 1 tuator.

Motor Operated Valve

1 Get Actuator

Record the part

- 1 number.

Motor Operated Valve

2 Record Actuator

FIGURE 14: INSPECT AND RECORD THE DEFUEL MOV ACTUATOR PART NUMBER (RIGHT WING).

(SHEET 2 OF 2)

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80 of 96

BOEING SERVICE BULLETIN 777-28A0034
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 the figure.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

Get access to the

part number markings on the MOV ac-

- 1 tuator.

Motor Operated Valve

1 Get Actuator

Record the part

- 1 number.

Motor Operated Valve

2 Record Actuator

FIGURE 15: INSPECT AND RECORD FUEL JETTISON NOZZLE MOV ACTUATOR PART NUMBER (INSIDE

THE LEFT WING AREA)

(SHEET 1 OF 1)

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BOEING SERVICE BULLETIN 777-28A0034
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 the figure.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

Get access to the

part number markings on the MOV ac-

- 1 tuator.

Motor Operated Valve

1 Get Actuator

Record the part

- 1 number.

Motor Operated Valve

2 Record Actuator

FIGURE 16: INSPECT AND RECORD FUEL JETTISON NOZZLE MOV ACTUATOR PART NUMBER (INSIDE

THE RIGHT WING AREA)

(SHEET 1 OF 1)

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82 of 96

BOEING SERVICE BULLETIN 777-28A0034
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 the figure.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

Get access to the

part number markings on the MOV ac-

- 1 tuator.

Motor Operated Valve

1 Get Actuator

Record the part

- 1 number.

Motor Operated Valve

2 Record Actuator

FIGURE 17: INSPECT AND RECORD FUEL JETTISON NOZZLE MOV ACTUATOR PART NUMBER (LEFT

WING)

(SHEET 1 OF 1)

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83 of 96

BOEING SERVICE BULLETIN 777-28A0034
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 the figure.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

Get access to the

part number markings on the MOV ac-

- 1 tuator.

Motor Operated Valve

1 Get Actuator

Record the part

- 1 number.

Motor Operated Valve

2 Record Actuator

FIGURE 18: INSPECT AND RECORD FUEL JETTISON NOZZLE MOV ACTUATOR PART NUMBER (RIGHT

WING)

(SHEET 1 OF 1)

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BOEING SERVICE BULLETIN 777-28A0034
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 the figure.

FIGURE 19: INSPECT AND RECORD FUEL JETTISON ISOLATION MOV ACTUATOR PART NUMBER

(LEFT WING)

(SHEET 1 OF 2)

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85 of 96

BOEING SERVICE BULLETIN 777-28A0034
STEP TASK NAME IDENTIFICATION QTY MORE DATA

Get access to the

part number markings on the MOV ac-

- 1 tuator.

Motor Operated Valve

1 Get Actuator

Record the part

- 1 number.

Motor Operated Valve

2 Record Actuator

FIGURE 19: INSPECT AND RECORD FUEL JETTISON ISOLATION MOV ACTUATOR PART NUMBER

(LEFT WING)

(SHEET 2 OF 2)

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BOEING SERVICE BULLETIN 777-28A0034
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 the figure.

FIGURE 20: INSPECT AND RECORD FUEL JETTISON ISOLATION MOV ACTUATOR PART NUMBER

(RIGHT WING)

(SHEET 1 OF 2)

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87 of 96

BOEING SERVICE BULLETIN 777-28A0034
STEP TASK NAME IDENTIFICATION QTY MORE DATA

Get access to the

part number markings on the MOV ac-

- 1 tuator.

Motor Operated Valve

1 Get Actuator

Record the part

- 1 number.

Motor Operated Valve

2 Record Actuator

FIGURE 20: INSPECT AND RECORD FUEL JETTISON ISOLATION MOV ACTUATOR PART NUMBER

(RIGHT WING)

(SHEET 2 OF 2)

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BOEING SERVICE BULLETIN 777-28A0034
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 the figure.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

Apply a Faying bond

to the index plate.

(a)

BMS 5-95 (BMS 5-45 -

optional)

Pressure and Environmental Sealant-Chromate Type1 Apply

Do not connect the

bonding jumper to

the MOV actuator.

Motor Operated Valve MA30A1001 1

Actuator

2 Install (New)

FIGURE 21: INSTALL THE MOV ACTUATOR

(SHEET 1 OF 4)

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BOEING SERVICE BULLETIN 777-28A0034
STEP TASK NAME IDENTIFICATION QTY MORE DATA

Measure the electrical resistance of the

Faying bond from

the foot of the MOV

actuator to the airplane structure. (a)

(b)

3 Measure Electrical Bond - -

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 5-to-9

inches. (a)

Bonding Jumper, 5 IN BACJ40A20-5 1

(optional)

4 Measure

If you determined

that the bonding

jumper is too short,

remove the bonding

jumper and do the

following sub-tasks.

Bonding Jumper, 5 IN BACJ40A20-5 1

(optional)

Remove

You can select a

length from 5-to-9

inches.(a)

Bonding Jumper, 5 IN BACJ40A20-5 1

(optional)

Get

Bonding Jumper, 6 IN BACJ40A20-6 1

(optional)

Bonding Jumper, 7 IN BACJ40A20-7 1

(optional)

Bonding Jumper, 9 IN BACJ40A20-9 1

(optional)

FIGURE 21: INSTALL THE MOV ACTUATOR

(SHEET 2 OF 4)

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BOEING SERVICE BULLETIN 777-28A0034
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

jumpers to the airplane structure. Use

the shortest bonding

jumper that allows

no tension. You can

select a length from

5-to-9 inches. (a)

Attach Bonding Jumper - 1

Apply a Faying bond

at the airplane structure for the bonding

jumper of the correct

length. (a)

BMS 5-95 (BMS 5-45 -

optional)

Pressure and Environmental Sealant-Chromate TypeApply

Torque fasteners.

(a)

Torque Bonding Jumper - 1

Clean the surface of

the bonding jumper

lug and fasteners,

and the MOV actuator. (a)

6 Clean Bonding Jumper - 1

Measure the electrical 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 - -

FIGURE 21: INSTALL THE MOV ACTUATOR

(SHEET 3 OF 4)

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BOEING SERVICE BULLETIN 777-28A0034
STEP TASK NAME IDENTIFICATION QTY MORE DATA

Attach the bonding

jumper to the MOV

actuator.

7 Attach Bonding Jumper - -

Apply a Faying bond

at the MOV actuator

for the bonding

jumper. (a)

BMS 5-95 (BMS 5-45 1

optional)

Pressure and Environmental Sealant-Chromate TypeApply

Torque fasteners.

(a)

Torque Bonding Jumper - 1

Measure the electrical 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 of the MOV

actuator. (a) (d) (e)

Measure Electrical Bond - -

Apply cap seal to the

bonding jumper fasteners. (a) (f)

BMS 5-95 (BMS 5-45 -

optional)

Pressure and Environmental Sealant-Chromate Type8 Apply

(a) Refer to SWPM 20-20-00 as an accepted procedure.

(b) If the measured electrical 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 resistance

of the Faying bond is not acceptable, rework the Faying Bond as necessary.

(c) If the measured 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 resistance of the Faying bond is not acceptable, rework the Faying Bond as necessary.

(d) If the measured 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 of the MOV actuator is less than 1.5 milliohms, the Faying bond is acceptable. If the measured electrical 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.

(f) BMS 5-45 or BMS 5-145 can be used as a substitute for BMS 5-95 for the application of cap seal on the

MOV actuator bonding jumper fasteners as described in the work packages of this service bulletin.

FIGURE 21: INSTALL THE MOV ACTUATOR

(SHEET 4 OF 4)

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Revision 2 September 20, 2010 777-28A0034

92 of 96

BOEING SERVICE BULLETIN 777-28A0034
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 the figure.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

Apply a Faying bond

to the index plate.

(a)

BMS 5-95 (BMS 5-45 -

optional)

Pressure and Environmental Sealant-Chromate Type1 Apply

Do not connect the

bonding jumper to

the MOV actuator.

Motor Operated Valve MA30A1001 1

Actuator

2 Install (New)

Measure the electrical resistance of the

Faying bond from

the foot of the MOV

actuator to the airplane structure. (a)

(b)

3 Measure Electrical Bond - -

FIGURE 22: INSTALL THE FUEL JETTISON NOZZLE VALVE MOV ACTUATOR (INSIDE WING AREA)

(SHEET 1 OF 4)

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Original Issue: August 02, 2007

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93 of 96

BOEING SERVICE BULLETIN 777-28A0034
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 5-to-9

inches. (a)

Bonding Jumper, 5 IN BACJ40A20-5 1

(optional)

4 Measure

If you determined

that the bonding

jumper is too short,

remove the bonding

jumper and do the

following sub-tasks.

Bonding Jumper, 5 IN BACJ40A20-5 1

(optional)

Remove

You can select a

length from 5-to-9

inches.(a)

Bonding Jumper, 5 IN BACJ40A20-5 1

(optional)

Get

Bonding Jumper, 6 IN BACJ40A20-6 1

(optional)

Bonding Jumper, 7 IN BACJ40A20-7 1

(optional)

Bonding Jumper, 9 IN BACJ40A20-9 1

(optional)

FIGURE 22: INSTALL THE FUEL JETTISON NOZZLE VALVE MOV ACTUATOR (INSIDE WING AREA)

(SHEET 2 OF 4)

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94 of 96

BOEING SERVICE BULLETIN 777-28A0034
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

jumpers to the airplane structure. Use

the shortest bonding

jumper that allows

no tension. You can

select a length from

5-to-9 inches. (a)

Attach Bonding Jumper - 1

Apply a Faying bond

at the airplane structure for the bonding

jumper of the correct

length. (a)

BMS 5-95 (BMS 5-45 -

optional)

Pressure and Environmental Sealant-Chromate TypeApply

Torque fasteners.

(a)

Torque Bonding Jumper - 1

Clean the surface of

the bonding jumper

lug and fasteners,

and the MOV actuator. (a)

6 Clean Bonding Jumper - 1

Measure the electrical 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 - -

FIGURE 22: INSTALL THE FUEL JETTISON NOZZLE VALVE MOV ACTUATOR (INSIDE WING AREA)

(SHEET 3 OF 4)

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95 of 96

BOEING SERVICE BULLETIN 777-28A0034
STEP TASK NAME IDENTIFICATION QTY MORE DATA

Attach the bonding

jumper to the MOV

actuator.

7 Attach Bonding Jumper - -

Apply a Faying bond

at the MOV actuator

for the bonding

jumper. (a)

BMS 5-95 (BMS 5-45 1

optional)

Pressure and Environmental Sealant-Chromate TypeApply

Torque fasteners.

(a)

Torque Bonding Jumper - 1

Measure the electrical 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 of the MOV

actuator. (a) (d) (e)

Measure Electrical Bond - -

Apply cap seal to the

bonding jumper fasteners.(a) (f)

BMS 5-95 (BMS 5-45 -

optional)

Pressure and Environmental Sealant-Chromate Type8 Apply

(a) Refer to SWPM 20-20-00 as an accepted procedure.

(b) If the measured electrical 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 resistance

of the Faying bond is not acceptable, rework the Faying Bond as necessary.

(c) If the measured 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 resistance of the Faying bond is not acceptable, rework the Faying Bond as necessary.

(d) If the measured 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 of the MOV actuator is less than 1.5 milliohms, the Faying bond is acceptable. If the measured electrical 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.

(f) BMS 5-45 or BMS 5-145 can be used as a substitute for BMS 5-95 for the application of cap seal on the

MOV actuator bonding jumper fasteners as described in the work packages of this service bulletin.

FIGURE 22: INSTALL THE FUEL JETTISON NOZZLE VALVE MOV ACTUATOR (INSIDE WING AREA)

(SHEET 4 OF 4)

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Original Issue: August 02, 2007

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96 of 96

BOEING SERVICE BULLETIN 777-28A0034