Service Bulletin B787-81205-SB280015-00 FUEL - Fuel Distribution - Fuel

Shutoff Valve Actuator Test and Replacement

Publication: B787-81205-SB280015-00 Issue 002, 19 Jun 2014

BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET

Copyright © 2014 Boeing. Unpublished Work. All rights reserved.

Treatment of this data module and its content is governed by contract with Boeing. Rights to use this data module are licensed on a per

aircraft basis and such rights may not be transferable. For more information, contact The Boeing Company. 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, KC-46, KDC-10, MD-10,

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license is granted in connection with this document unless provided in writing by Boeing.

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Export of this technology is controlled under the United States Export Administration Regulations (EAR) (15 CFR 300-774). An export license

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has the individual responsibility to abide by all export laws.

ECCN: 9E991

The applicability information below is referenced at the lower left of each page to indicate the page applicability.

These references are valid for this print copy only.

PM Applicability (Publication Module applicability)

787-8 Airplanes. Refer to Data Module SB B787-A-28-00-0015-00A-932A-D, Paragraph 1., Effectivity for the

list of affected airplanes.

TITLE PAGE B787-81205-SB280015-00

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3.0

B787-81205-SB280015-00

Issue 002, 19 Jun 2014

AIRCRAFT SERVICE BULLETIN
Service Bulletin B787-81205-SB280015-00

Table of Contents

Page

Revision Transmittal Information ........................................5

Summary .....................................................6

PLANNING INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10

1. Effectivity . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10

A. Airplanes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10

B. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11

2. Concurrent Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11

3. Reason . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11

4. Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12

5. Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12

6. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

7. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

8. Weight and Balance Changes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16

9. Electrical Load Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

10. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

A. Existing Data: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

B. Data Supplied with this Service Bulletin: . . . . . . . . . . . . . . . . . . . . . . . . . . 17

C. Installation Requirement Modules Used in the Preparation of this Service Bulletin: . . . 17

11. Publications Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

12. Interchangeability and Intermixability of Parts . . . . . . . . . . . . . . . . . . . . . . . . . 17

13. Software Accomplishment Summary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

MATERIAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18

1. Material - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18

2. Industry Support Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18

3. Parts Necessary for Each Airplane . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18

A. Kits/Parts: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18

B. Parts and Materials Supplied by the Operator: . . . . . . . . . . . . . . . . . . . . . . . 18

C. Parts Modified and Reidentified: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

D. Parts Removed and Not Replaced: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

4. Parts Necessary to Change Spares . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

5. Special Tooling - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

6. Special Tooling Necessary to do this Service Bulletin . . . . . . . . . . . . . . . . . . . . . 19

ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20

1. GENERAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20

2. WORK INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22

TABLE OF CONTENTS B787-81205-SB280015-00

Issue 002, 19 Jun 2014

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B787-81205-SB280015-00

Issue 002, 19 Jun 2014

AIRCRAFT SERVICE BULLETIN
Service Bulletin B787-81205-SB280015-00

List of Illustrations

Description

Group 1:

Table 1 List of Illustrations - Service Bulletin B787-81205-SB280015-00

ICN Used In

ICN-B787-A-000061-A-81205-06437-A-01-1 B787-A-28-00-0015-00A-931C-D Issue 002

Applicable To: B787-A-28-00-0015-00A-00AA-D

Model 787 End of data module Issue 002, 19 Jun 2014

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Service Bulletin B787-81205-SB280015-00

List of Effective Data Modules

Description

Group 1:

Table 1 List of Effective Data Modules - Service Bulletin B787-81205-SB280015-00

Data Module – Information Name Issue Issue Status Issue Date

B787-A-28-00-0015-00A-00AA-D – List of Illustrations 002 Changed 2014-06-19

B787-A-28-00-0015-00A-00SA-D – List of Effective Data Modules 002 Changed 2014-06-19

B787-A-28-00-0015-00A-931B-D – Revision Transmittal Information 001 New 2014-06-19

B787-A-28-00-0015-00A-931C-D – Summary 002 Changed 2014-06-19

B787-A-28-00-0015-00A-932A-D – PLANNING INFORMATION 002 Changed 2014-06-19

B787-A-28-00-0015-00A-934A-D – MATERIAL INFORMATION 002 Changed 2014-06-19

B787-A-28-00-0015-00A-933A-D – ACCOMPLISHMENT INSTRUCTIONS 002 Changed 2014-06-19

Applicable To: B787-A-28-00-0015-00A-00SA-D

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AIRCRAFT SERVICE BULLETIN
Service Bulletin B787-81205-SB280015-00

Revision Transmittal Information

References

Reference Title

SB B787-A-28-00-0015-00A-932A-D Issue 002, Airplanes

Paragraph 1.A.

Description

Group 1:

This revision includes all pages of the service bulletin.

1. COMPLIANCE INFORMATION RELATED TO THIS REVISION

No more work is necessary on airplanes changed or inspected in accordance with Issue 001 of this service

bulletin.

2. REASON FOR REVISION

This issue is sent to make these changes:

1. Change the compliance time for the terminating action from 60 months to 36 months.

2. Include the reference to the Eaton service bulletin 53-0037-28-01.

3. Include a note in the General Information section to inform operators that the external power is required

for the PART 2 : APU FUEL SHUTOFF VALVE ACTUATOR TEST.

4. Clarify the engine and APU fuel shutoff valve actuator test procedures.

As a part of a service bulletin validation program, the engine and APU fuel shutoff valve actuator tests in

this service bulletin were completed on airplane ZA188 before the release of Issue 002 of this service bulletin.

These sections were changed:

1. Planning Information - Paragraph 5, Compliance

2. Material Information - Paragraph 3, Parts Necessary for Each Airplane

3. Accomplishment Instructions - Paragraph 2, Work Instructions

Change marks are added, except in Data Module SB B787-A-28-00-0015-00A-932A-D, Paragraph 1.A.,

Airplanes and format changes, to show the location of all content changes.

3. REVISION HISTORY

Table 1 

Issue 1: January 30, 2014

Issue 2: June 19, 2014

Applicable To: B787-A-28-00-0015-00A-931B-D

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B787-81205-SB280015-00

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AIRCRAFT SERVICE BULLETIN
Service Bulletin B787-81205-SB280015-00

Summary

References

Reference Title

SB B787-A-28-00-0015-00A-932A-D Issue 002, Spares Affected

Paragraph 1.B.

SB B787-A-28-00-0015-00A-932A-D Issue 002, Compliance

Paragraph 5.

SB B787-A-28-00-0015-00A-932A-D Issue 002, Weight and Balance Changes

Paragraph 8.

SB B787-A-28-00-0015-00A-932A-D Issue 002, Electrical Load Data

Paragraph 9.

SB B787-A-28-00-0015-00A-932A-D Issue 002, Publications Affected

Paragraph 11.

SB B787-A-28-00-0015-00A-934A-D Issue 002, Kits/Parts

Paragraph 3.A.

SB B787-A-28-00-0015-00A-934A-D Issue 002, Parts and Materials Supplied by the Operator

Paragraph 3.B.

SB B787-A-28-00-0015-00A-934A-D Issue 002, Special Tooling Necessary to do this Service Bulletin

Paragraph 6.

SB B787-A-28-00-0015-00A-932A-D Issue 002, Effectivity

Paragraph 1.

SB B787-A-28-00-0015-00A-934A-D Issue 002, Industry Support Information

Paragraph 2.

SB B787-A-28-00-0015-00A-932A-D Issue 002, Manpower

Paragraph 7.

SB B787-A-28-00-0015-00A-934A-D Issue 002, Material - Price and Availability

Paragraph 1.

Description

Group 1:

1. CONCURRENT REQUIREMENTS

None.

Applicable To: B787-A-28-00-0015-00A-931C-D

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Issue 002, 19 Jun 2014

AIRCRAFT SERVICE BULLETIN
2. BACKGROUND

This service bulletin gives instructions to test the engine and Auxiliary Power Unit (APU) fuel shutoff valve

actuators to make sure that the valve operation and indication are working correctly. This service bulletin

also provides the terminating action to replace the engine and APU fuel shutoff valve actuators and an option

to replace the fuel crossfeed and defuel/isolation valve actuators. Incorporation of this service bulletin prevents

possible operational disruptions.

The fuel shutoff valve actuator circuit design provides common input power through micro-switches to both

the motor and position indication. It was identified that the valve actuator circuitry has a potential latent failure

condition previously not identified during its development. The latent failure condition is with respect to the

potential for a stuck micro-switch which could lead to a disagreement between the valve command and position indication. In a case where a command is sent to change valve position and one of the internal microswitches is stuck in the depressed state, power would immediately provide indication that the valve transitioned

to its commanded state when in reality the motor never received power to rotate. Changes were made to

the actuator micro-switch circuit by the supplier to provide independence between the valve command and

indication functions which prevent the latent failure condition. Refer to Fleet Team Digest 787-FTD-28-13002

for additional information.

Boeing Service Related Problem (SRP) 787 SRP-28-0147 is related to this service bulletin.

As a part of a service bulletin validation program, the engine and APU fuel shutoff valve actuator tests in

this service bulletin were completed on airplane ZA188 before the release of Issue 002 of this service bulletin.

This table is provided to operators for planning purposes only. Refer to the applicable sections for more information.

Table 1 

Planning Data Affected Data Module Reference

Data Module SB B787-A-28-00-0015-00A-932AD, Paragraph 1.B., Spares AffectedSpares Affected No

Data Module SB B787-A-28-00-0015-00A-932AD, Paragraph 5., ComplianceAD Related Yes

Data Module SB B787-A-28-00-0015-00A-932AD, Paragraph 8., Weight and Balance ChangesWeight and Balance Changed No

Data Module SB B787-A-28-00-0015-00A-932AD, Paragraph 9., Electrical Load DataElectrical Load Changed No

Data Module SB B787-A-28-00-0015-00A-932AD, Paragraph 11., Publications AffectedPublications Affected No

Data Module SB B787-A-28-00-0015-00A-932AD, Paragraph 11., Publications AffectedAirplane Flight Operations Affected (Flight Crew No

Operations Manual and/or FAA Approved Airplane Flight Manual)

Data Module SB B787-A-28-00-0015-00A-934AD, Paragraph 3.A., Kits/PartsKits/Parts Required No

Applicable To: B787-A-28-00-0015-00A-931C-D

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Table 1 

Planning Data Affected Data Module Reference

Data Module SB B787-A-28-00-0015-00A-934AD, Paragraph 3.B., Parts and Materials Supplied

by the Operator

Operator Supplied Parts/Material Yes

Data Module SB B787-A-28-00-0015-00A-934AD, Paragraph 6., Special Tooling Necessary to

do this Service Bulletin

Special Tooling Required No

3. ACTION

(CN-AC36420A)

Testing: Do the engine and APU fuel shutoff valve actuator test and replace the valve actuator if necessary.

Terminating Action: Replace the engine and APU fuel shutoff valve actuators.

Option: Replace the fuel crossfeed and defuel/isolation valve actuators.

4. EFFECTIVITY

787-8 Airplanes. Refer to Data Module SB B787-A-28-00-0015-00A-932A-D, Paragraph 1., Effectivity for

the list of affected airplanes.

5. COMPLIANCE

The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to this

service bulletin. The Airworthiness Directive will make the compliance tasks and times given in this service

bulletin mandatory.

Refer to Data Module SB B787-A-28-00-0015-00A-932A-D, Paragraph 5., Compliance.

6. INDUSTRY SUPPORT INFORMATION

Boeing warranty remedies are available for airplanes in warranty as of February 21, 2013. Please refer to

Data Module SB B787-A-28-00-0015-00A-934A-D, Paragraph 2., Industry Support Information. The warranty

remedies will expire eight years from the original release date of this service bulletin.

7. MANPOWER

Refer to Data Module SB B787-A-28-00-0015-00A-932A-D, Paragraph 7., Manpower.

8. MATERIAL INFORMATION

Operator Supplied Parts/Materials.

Refer to Data Module SB B787-A-28-00-0015-00A-934A-D, Paragraph 1., Material - Price and Availability.

Applicable To: B787-A-28-00-0015-00A-931C-D

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ICN-B787-A-000061-A-81205-06437-A-01-1

Figure 1 

Applicable To: B787-A-28-00-0015-00A-931C-D

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Service Bulletin B787-81205-SB280015-00

PLANNING INFORMATION

References

Reference Title

SB B787-A-28-00-0015-00A-933A-D Issue 002, Step 2. Work Instructions

787 AMM 24-00-02 CIRCUIT BREAKER INDICATION AND CONTROL

787 AMM 28-22-02 ENGINE FUEL SHUTOFF VALVE ACTUATOR

787 AMM 28-22-04 FUEL CROSSFEED VALVE ACTUATOR

787 AMM 28-25-03 APU FUEL SHUTOFF VALVE ACTUATOR

787 AMM 28-26-02 DEFUEL/ISOLATION VALVE ACTUATOR

787 AMM 31-61-00 PRIMARY DISPLAY SYSTEM

ONBOARD BOEING ELECTRONIC DISTRIBUTION

SYSTEM

787 AMM 46-13-00

Description

Group 1:

1. Effectivity

A. Airplanes

This service bulletin is for the airplanes shown below. An equivalent change is on subsequent production

airplanes. Refer to CN-AA36420 for data about this change.

Table 1 

GROUP CONFIGURATION DESCRIPTION

1 - 787-8 airplanes.

Airplane Models: 787-8

Table 2 

Variable Number Group

ZA100-ZA105 1

ZA116-ZA122 1

ZA135 1

ZA176-ZA186 1

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Table 2 

Variable Number Group

ZA233 1

ZA235-ZA243 1

ZA260-ZA264 1

ZA270-ZA274 1

ZA285-ZA292 1

ZA317-ZA320 1

ZA380-ZA387 1

ZA430-ZA431 1

ZA433-ZA434 1

ZA450-ZA453 1

ZA460-ZA468 1

ZA506-ZA514 1

ZA536-ZA540 1

ZA561-ZA562 1

ZA576-ZA577 1

B. Spares Affected

Examine your spares supply for the parts or components identified below. If any parts or components

are found, refer to Data Module SB B787-A-28-00-0015-00A-933A-D, Step 2., Work Instructions for

the recommended action.

Table 3 

Part Number Name

53-0037 Valve Actuator

2. Concurrent Requirements

None.

3. Reason

This service bulletin gives instructions to test the engine and Auxiliary Power Unit (APU) fuel shutoff valve

actuators to make sure that the valve operation and indication are working correctly. This service bulletin

also provides the terminating action to replace the engine and APU fuel shutoff valve actuators and an

option to replace the fuel crossfeed and defuel/isolation valve actuators. Incorporation of this service bulletin

prevents possible operational disruptions.

The fuel shutoff valve actuator circuit design provides common input power through micro-switches to both

the motor and position indication. It was identified that the valve actuator circuitry has a potential latent

Applicable To: B787-A-28-00-0015-00A-932A-D

Model 787 Issue 002, 19 Jun 2014

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Issue 002, 19 Jun 2014

AIRCRAFT SERVICE BULLETIN
failure condition previously not identified during its development. The latent failure condition is with respect

to the potential for a stuck micro-switch which could lead to a disagreement between the valve command

and position indication. In a case where a command is sent to change valve position and one of the internal

micro-switches is stuck in the depressed state, power would immediately provide indication that the valve

transitioned to its commanded state when in reality the motor never received power to rotate. Changes

were made to the actuator micro-switch circuit by the supplier to provide independence between the valve

command and indication functions which prevent the latent failure condition. Refer to Fleet Team Digest

787-FTD-28-13002 for additional information.

Boeing Service Related Problem (SRP) 787 SRP-28-0147 is related to this service bulletin.

As a part of a service bulletin validation program, the engine and APU fuel shutoff valve actuator tests in

this service bulletin were completed on airplane ZA188 before the release of Issue 002 of this service bulletin.

Issue 002 is sent to make these changes:

1. Change the compliance time for the terminating action from 60 months to 36 months.

2. Include the reference to the Eaton service bulletin 53-0037-28-01.

3. Include a note in the General Information section to inform operators that the external power is required

for the PART 2 : APU FUEL SHUTOFF VALVE ACTUATOR TEST.

4. Clarify the engine and APU fuel shutoff valve actuator test procedures.

4. Description

Testing: Do the engine and APU fuel shutoff valve actuator test and replace the valve actuator if necessary.

Terminating Action: Replace the engine and APU fuel shutoff valve actuators.

Option: Replace the fuel crossfeed and defuel/isolation valve actuators.

Issue 002 - No more work is necessary on airplanes changed in accordance with Issue 001 of this service

bulletin.

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

Table 4 

Affected Maintenance Zones

Model Zone

787-8 143, 552, 562

5. Compliance

The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to this

service bulletin. The Airworthiness Directive will make the compliance tasks and times given in this service

bulletin mandatory.

Do the required actions in accordance with Data Module SB B787-A-28-00-0015-00A-933A-D, Step 2.,

Work Instructions.

The Conditions, Actions and Compliance times shown apply to each fuel shutoff valve independently.

Applicable To: B787-A-28-00-0015-00A-932A-D

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AIRCRAFT SERVICE BULLETIN
When more than one OPTION is given for a CONDITION, do only one of the OPTION numbers. When

more than one ACTION is given for a CONDITION number or an OPTION number, do all of the ACTION

numbers for that CONDITION number or OPTION number.

Table 5 TESTING: ENGINE FUEL SHUTOFF VALVE ACTUATOR TEST

Repeat Interval

(Not to Exceed)

Condition Action Compliance Time

Within 3 months -

after the Issue 002

date of this service

bulletin.

Do PART 1: ENGINE FUEL SHUTOFF VALVE ACTUATOR TEST.*[1]

All airplanes

10 days. OPTION 1: Repeat PART - *[2]

1: ENGINE FUEL SHUTOFF VALVE ACTUATOR

TEST.

CONDITION 1: NO LATENT FAILURE CONDITION FOUND ON ALL

ENGINE FUEL SHUTOFF

VALVE ACTUATORS. OPTION 2: Do PART 5: - -

TERMINATING ACTION -

ENGINE FUEL SHUTOFF

VALVE ACTUATOR REPLACEMENT.*[2]

Before further -

flight.

OPTION 3 (ACTION 1): Do

PART 3: ENGINE FUEL

SHUTOFF VALVE ACTUATOR REPLACEMENT for

any engine fuel shutoff

valve that has the latent

failure condition.

CONDITION 2: LATENT

FAILURE CONDITION

FOUND ON ANY ENGINE

FUEL SHUTOFF VALVE

ACTUATOR

Within 10 days af- -

ter PART 3: ENGINE FUEL

SHUTOFF VALVE

ACTUATOR REPLACEMENT was

accomplished.

OPTION 3 (ACTION 2): Do

PART 1: ENGINE FUEL

SHUTOFF VALVE ACTUATOR TEST.

Before further -

flight.

OPTION 4: Do PART 5:

TERMINATING ACTION -

ENGINE FUEL SHUTOFF

VALVE ACTUATOR REPLACEMENT. *[2]

*[1] Accomplishment of PART 5: TERMINATING ACTION - ENGINE FUEL SHUTOFF VALVE ACTUATOR REPLACEMENT

can be done instead of PART 1: ENGINE FUEL SHUTOFF VALVE ACTUATOR TEST.

*[2] Accomplishment of PART 5: TERMINATING ACTION - ENGINE FUEL SHUTOFF VALVE ACTUATOR REPLACEMENT

is terminating action to the repeat test in PART 1.

Applicable To: B787-A-28-00-0015-00A-932A-D

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Table 6 TESTING: APU FUEL SHUTOFF VALVE ACTUATOR TEST

Repeat Interval

(Not to Exceed)

Condition Action Compliance Time

Within 3 months -

after the Issue 002

date of this service

bulletin.

Do PART 2: APU FUEL

SHUTOFF VALVE ACTUATOR TEST.*[1]

All airplanes

10 days. OPTION 5: Repeat PART - *[2]

2: APU FUEL SHUTOFF

VALVE ACTUATOR TEST.

CONDITION 3: NO LATENT FAILURE CONDITION FOUND ON APU

FUEL SHUTOFF VALVE

ACTUATOR OPTION 6: Do PART 6: - -

TERMINATING ACTION -

APU FUEL SHUTOFF

VALVE ACTUATOR REPLACEMENT.*[2]

Before further -

flight.

OPTION 7 (ACTION 1): Do

PART 4: APU FUEL

SHUTOFF VALVE ACTUATOR REPLACEMENT.

CONDITION 4: LATENT

FAILURE CONDITION

FOUND ON APU FUEL

SHUTOFF VALVE ACTUATOR Within 10 days af- -

ter PART 4: APU

FUEL SHUTOFF

VALVE ACTUATOR REPLACEMENT was accomplished.

OPTION 7 (ACTION 2): Do

PART 2: APU FUEL

SHUTOFF VALVE ACTUATOR TEST.

Before further -

flight.

OPTION 8: Do PART 6:

TERMINATING ACTION -

APU FUEL SHUTOFF

VALVE ACTUATOR REPLACEMENT.*[2]

*[1] Accomplishment of Do PART 6: TERMINATING ACTION - APU FUEL SHUTOFF VALVE ACTUATOR REPLACEMENT

can be done instead of PART 2: APU FUEL SHUTOFF VALVE ACTUATOR TEST.

*[2] Accomplishment of PART 6: TERMINATING ACTION - APU FUEL SHUTOFF VALVE ACTUATOR REPLACEMENT

is terminating action to the repeat test in PART 2.

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Table 7 TERMINATING ACTION: ENGINE AND APU FUEL SHUTOFF VALVE ACTUATOR 

REPLACEMENT

Repeat Interval

(Not to Exceed)

Condition Action Compliance Time

Within 36 months -

after the Issue 001

date of this service

bulletin.

Do PART 5: TERMINATING ACTION - ENGINE

FUEL SHUTOFF VALVE

ACTUATOR REPLACEMENT.

All airplanes

Within 36 months -

after the Issue 001

date of this service

bulletin.

Do PART 6: TERMINATING ACTION - APU FUEL

SHUTOFF VALVE ACTUATOR REPLACEMENT.

Table 8 OPTION: FUEL CROSSFEED AND DEFUEL/ISOLATION VALVE ACTUATOR 

REPLACEMENT

Repeat Interval

(Not to Exceed)

Condition Action Compliance Time

- - Do PART 7: FUEL *[1]

CROSSFEED VALVE ACTUATOR REPLACEMENT.

All airplanes

- - Do PART 8: DEFUEL/ISO- *[1]

LATION VALVE ACTUATOR REPLACEMENT.

*[1] No compliance time is given. Boeing recommends this service bulletin be done to introduce improvements and prevent

possible operational disruptions.

6. 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.

7. Manpower

The table below shows an estimate of the task hours necessary to do this inspection 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

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– Time to inspect the work

– Time to cure the materials

– Time to make the parts

– Time to find the tools

Table 9 TESTING: ENGINE AND APU FUEL SHUTOFF VALVE ACTUATOR TEST

Number of Per- Task Hours Elapsed Hours

sons

Task

Part 1 1 1.00 1.00

Part 2 1 0.50 0.50

3.25*[1] 3.25 Part 3 1 *[1]

3.25 *[2] 3.25 Part 4 1 *[2]

TOTAL FOR EACH AIRPLANE 1.50 1.50

*[1] Part 3 replacement is dependant upon results of Part 1 test. The estimate given in Part 3 is for removal, installation and test of the left or right engine fuel shutoff valve. If the work in Part 3 is necessary, the estimate given in Part 3 must be added to obtain the required total for each airplane.

*[2] Part 4 replacement is dependant upon results of Part 2 test. The estimate given in Part 4 is for removal, installation and test of the APU fuel shutoff valve. If the work in Part 4 is necessary, the estimate given in Part 4 must be added to obtain the required total for each airplane.

Table 10 TERMINATING ACTION: ENGINE AND APU FUEL SHUTOFF VALVE 

ACTUATOR REPLACEMENT

Number of Per- Task Hours Elapsed Hours

sons

Task

Part 5 2 6.50 3.25

Part 6 1 3.25 3.25

TOTAL FOR EACH AIRPLANE 9.75 6.50

Table 11 OPTION: FUEL CROSSFEED AND DEFUEL/ISOLATION VALVE 

ACTUATOR REPLACEMENT

Number of Per- Task Hours Elapsed Hours

sons

Task

Part 7 1 3.25 3.25

Part 8 2 6.50 3.25

TOTAL FOR EACH AIRPLANE 9.75 6.50

8. Weight and Balance Changes

None.

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9. Electrical Load Data

Not changed.

10. References

A. Existing Data:

1. Change Notice CN-AA36420D

2. Aircraft Maintenance Manual (AMM) 787 AMM 24-00-02, 787 AMM 28-22-02, 787 AMM 28-22-

04, 787 AMM 28-25-03, 787 AMM 28-26-02, 787 AMM 31-61-00, 787 AMM 46-13-00

3. Boeing Service Related Problem (SRP) 787 SRP-28-0147

4. 787 Fleet Team Digest 787-FTD-28-13002

5. Eaton Service Bulletin 53-0037-28-01

B. Data Supplied with this Service Bulletin:

None.

C. Installation Requirement Modules Used in the Preparation of this Service Bulletin:

None.

11. Publications Affected

Table 12 

Publication Chapter-Section

787 Wiring Diagram Manual 28-21, 28-22, 28-25

ZA1-33, ZA1-34, ZA5-21, ZA5-51, ZA5-52,

ZA5-61, ZA6-21, ZA6-51, ZA6-52, ZA6-61

787 Illustrated Parts Data

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.

12. Interchangeability and Intermixability of Parts

Accomplishment of this service bulletin does not affect interchangeability or intermixability of parts.

13. Software Accomplishment Summary

Not Affected.

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Service Bulletin B787-81205-SB280015-00

MATERIAL INFORMATION

References

Reference Title

SB B787-A-28-00-0015-00A-932A-D Issue 002, References

Paragraph 10.

Description

Group 1:

1. Material - Price and Availability

The operator can supply the parts and materials shown in Paragraph 3., Parts Necessary for Each Airplane.

2. Industry Support Information

Boeing warranty remedies are available for 787 airplanes in warranty as of February 21, 2013. For task hour

and material reimbursement for airplanes in warranty as of that date, send a warranty claim to Boeing Fleet

Support Contracts - Warranty. The warranty remedies will expire eight years from the original release date

of this service bulletin.

3. Parts Necessary for Each Airplane

A. Kits/Parts:

None.

B. Parts and Materials Supplied by the Operator:

Table 1 

Part Number / QTY Name Existing Part Number Notes

Specification

As Valve Actuator - *[1] *[2]

Required

53-0037

53-0049 3 Valve Actuator 53-0037 *[3] *[4]

53-0049 3 Valve Actuator 53-0037 *[5] *[4]

*[1] The part is only necessary if the existing Engine or APU fuel shutoff valve actuator is found to have the latent failure condition

during the test in the TESTING section.

*[2] Return the part with latent failure condition and order the part number directly from Eaton Aerospace Ltd, Abbey Park, Southampton

Rd, Titchfield Hamshire P014 4QA, United Kingdom

*[3] The parts are necessary for the TERMINATING ACTION section

*[4] Return the existing part and order the part number directly from Eaton Aerospace Ltd, Abbey Park, Southampton Rd, Titchfield

Hamshire P014 4QA, United Kingdom. Refer to the Eaton service bulletin 53-0037-28-01 for additional information.

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Table 1 

Part Number / QTY Name Existing Part Number Notes

Specification

*[5] The parts are necessary for the OPTION section..

C. Parts Modified and Reidentified:

None.

D. Parts Removed and Not Replaced:

None.

4. Parts Necessary to Change Spares

None.

5. Special Tooling - Price and Availability

None.

6. 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 Data Module SB B787-A-28-00-0015-00A-932A-D, Paragraph 10.,

References, can be necessary. Examine operator tool supply to make sure all necessary tools are available.

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Service Bulletin B787-81205-SB280015-00

ACCOMPLISHMENT INSTRUCTIONS

References

Reference Title

SB B787-A-28-00-0015-00A-932A-D Issue 002, References

Paragraph 10.

SB B787-A-28-00-0015-00A-932A-D Issue 002, Compliance

Paragraph 5.

ONBOARD BOEING ELECTRONIC DISTRIBUTION

SYSTEM

787 AMM 46-13-00

787 AMM 28-22-00 ENGINE FUEL FEED SYSTEM

787 AMM 24-00-02 CIRCUIT BREAKER INDICATION AND CONTROL

787 AMM 31-61-00 PRIMARY DISPLAY SYSTEM

787 AMM 28-22-02 ENGINE FUEL SHUTOFF VALVE ACTUATOR

787 AMM 28-25-03 APU FUEL SHUTOFF VALVE ACTUATOR

787 AMM 28-22-04 FUEL CROSSFEED VALVE ACTUATOR

787 AMM 28-26-02 DEFUEL/ISOLATION VALVE ACTUATOR

Procedure

Group 1:

1. 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 Data Module SB B787-A-28-00-0015-00A932A-D, Paragraph 10., References, for definition of the acronyms.

2. Obey all of the warnings and cautions given in the specified manual sections.

3. Unless shown differently, these dimensions and tolerances are used:

– Linear dimensions are in inches

– Tolerance on linear dimensions, other than rivet and bolt edge margins, is plus or minus

0.03 inch

– Tolerance on rivet and bolt edge margin is plus or minus 0.05 inch

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– Angular tolerance is plus or minus 2 degrees

– Hole dimensions for standard solid rivets and fasteners are in SRM Chapter 51

– Torque Values:

– Values for structural fasteners are given in 787 Structural Repair Manual, Chapter 51.

– Values for airframe maintenance tasks are included in Chapter 20 of 787 Airplane

Maintenance Manual (AMM).

– Values for electrical maintenance tasks are included in Chapter 20 of Standard Wiring

Practices Manual (SWPM).

– Values for engine maintenance tasks are included in Chapter 70 of 787 Airplane Maintenance Manual (AMM).

– Non-standard torque values for maintenance tasks are included in the applicable installation step.

4. These work instructions refer to procedures included in 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 "in accordance with" are included in the

instruction, the procedure in the Boeing document must be used.

5. Refer to 787 AMM 46-13-00 for onboard electronic distribution system maintenance practices

and operation as an accepted procedure.

6. If it is necessary to remove more parts for access, you can remove those parts. If you can get

access without removing identified parts, it is not necessary to remove all of the identified parts.

Jacking and shoring limitations must be observed.

7. This service bulletin includes functional test procedures for the systems changed by this service

bulletin. More functional tests can possibly be necessary in accordance with standard maintenance practices because of interruption to other airplane systems.

8. If shading is used, shaded areas in Figures are to separate the non-critical and non-authoritative

information from the critical and authoritative information.

9. When more than one OPTION is given for a CONDITION, do only one of the OPTION numbers.

When more than one ACTION is given for a CONDITION number or an OPTION number, do

all of the ACTION numbers for that CONDITION number or OPTION number.

10. The compliance times for the actions in Step 2., Work Instructions are in Data Module SB B787-

A-28-00-0015-00A-932A-D, Paragraph 5., Compliance.

11. The CONDITIONS, ACTIONS and OPTIONS shown apply to each fuel shutoff valve actuator

independently.

12. Some steps in the Work Instructions are identified as Required for Compliance (RC). If this

service bulletin is mandated by an Airworthiness Directive (AD), then the steps identified as RC

must be done to comply with the AD. Alternative procedures for steps not identified with RC can

be used if the RC steps can still be done as specified, and the airplane can be put back in a

serviceable condition. If a step in the Work Instructions identified as RC has substeps, then all

of the substeps in the RC step must also be done. An Alternative Method of Compliance (AMOC)

is not necessary for deviations to steps that are not identified as RC and is a substep of an RC

step.

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13. The external electrical ground power is required for the PART 2: APU FUEL SHUTOFF VALVE

ACTUATOR TEST. Refer to 787 AMM 28-22-00 as an accepted procedure.

2. WORK INSTRUCTIONS

A. Do the TESTING: ENGINE AND APU FUEL SHUTOFF VALVE ACTUATOR TEST or TERMINATING

ACTION: ENGINE AND APU FUEL SHUTOFF VALVE ACTUATOR REPLACEMENT.

(1) TESTING: ENGINE AND APU FUEL SHUTOFF VALVE ACTUATOR TEST

(a) RC - Do PART 1: ENGINE FUEL SHUTOFF VALVE ACTUATOR TEST.

1) CONDITION 1: NO LATENT FAILURE CONDITION FOUND ON ALL FUEL SHUTOFF

VALVE ACTUATORS

a) OPTION 1: Repeat PART 1: ENGINE FUEL SHUTOFF VALVE ACTUATOR TEST.

b) OPTION 2: Do PART 5: TERMINATING ACTION - ENGINE FUEL SHUTOFF VALVE

ACTUATOR REPLACEMENT to terminate the repeat test.

2) CONDITION 2: LATENT FAILURE CONDITION FOUND ON ANY ENGINE FUEL SHUTOFF

VALVE ACTUATOR

a) OPTION 3:

<1> OPTION 3 (ACTION 1): Do PART 3: ENGINE FUEL SHUTOFF VALVE ACTUATOR

REPLACEMENT for any engine fuel shutoff valve that has the latent failure condition.

<2> OPTION 3 (ACTION 2): Do PART 1: ENGINE FUEL SHUTOFF VALVE ACTUATOR

TEST.

b) OPTION 4: Do PART 5: TERMINATING ACTION - ENGINE FUEL SHUTOFF VALVE

ACTUATOR REPLACEMENT to terminate the repeat test.

(b) RC - Do PART 2: APU FUEL SHUTOFF VALVE ACTUATOR TEST.

1) CONDITION 3: NO LATENT FAILURE CONDITION FOUND ON APU FUEL SHUTOFF

VALVE ACTUATOR

a) OPTION 5: Repeat PART 2: APU FUEL SHUTOFF VALVE ACTUATOR TEST.

b) OPTION 6: Do PART 6: TERMINATING ACTION - APU FUEL SHUTOFF VALVE ACTUATOR REPLACEMENT to terminate the repeat test.

2) CONDITION 4: LATENT FAILURE CONDITION FOUND ON APU FUEL SHUTOFF VALVE

ACTUATOR

a) OPTION 7:

<1> OPTION 7 (ACTION 1): Do PART 4: APU FUEL SHUTOFF VALVE ACTUATOR

REPLACEMENT.

<2> OPTION 7 (ACTION 2): Do PART 2: APU FUEL SHUTOFF VALVE ACTUATOR

TEST.

b) OPTION 8: Do PART 6: TERMINATING ACTION - APU FUEL SHUTOFF VALVE ACTUATOR REPLACEMENT to terminate the repeat test.

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(2) TERMINATING ACTION: ENGINE AND APU FUEL SHUTOFF VALVE ACTUATOR REPLACEMENT

(a) RC - Do PART 5: TERMINATING ACTION - ENGINE FUEL SHUTOFF VALVE ACTUATOR

REPLACEMENT.

(b) RC - Do PART 6: TERMINATING ACTION - APU FUEL SHUTOFF VALVE ACTUATOR REPLACEMENT.

B. OPTION: FUEL CROSSFEED AND DEFUEL/ISOLATION VALVE ACTUATOR REPLACEMENT

(1) Do PART 7: FUEL CROSSFEED VALVE ACTUATOR REPLACEMENT.

(2) Do PART 8: DEFUEL/ISOLATION VALVE ACTUATOR REPLACEMENT.

C. Put the airplane back to a serviceable condition.

D. RC - PART 1: ENGINE FUEL SHUTOFF VALVE ACTUATOR TEST

(1) Make sure that no active or latched Engine SOV messages exist.

(2) Make sure that the following circuit breakers are closed using the Circuit Breaker Indication and

Control (CBIC). Refer to 787 AMM 24-00-02 as an accepted procedure.

Table 1 

Circuit Breaker Number Nomenclature

CE7621813 SPAR VLV/EEC RESET CHB CTRL-L ENGINE

CE7621823 SPAR VLV/EEC RESET CHB CTRL-R ENGINE

(3) Open the following circuit breakers using the CBIC. Refer to 787 AMM 24-00-02 as an accepted

procedure.

Table 2 

Circuit Breaker Number Nomenclature

CE2822803 ENG SOV - L

CE2822804 ENG SOV - R

CE2825804 FUEL SHUTOFF MODULE

(4) Open the following thermal circuit breakers and attach a DO-NOT-CLOSE tag.

Table 3 

Circuit Breaker Number Nomenclature Panel Grid

CT7411811 IGNITION 1 CHAN A-L ENGINE P300 E5

CT7411812 IGNITION 2 CHAN B-L ENGINE P400 G15

CT7411821 IGNITION 1 CHAN A-R ENGINE P400 F8

CT7411822 IGNITION 2 CHAN B-R ENGINE P300 F5

(5) Make sure that the L and R FUEL CONTROL switches on the P8 Control Stand are in the CUTOFF

position.

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(6) Make sure that the left and right Engine Fire handles on the P8 Control Stand are in normal stowed

position.

(7) Display the Fuel Management Maintenance page on the Central Maintenance Computing Function

(CMCF) . Refer to 787 AMM 31-61-00 as an accepted procedure.

(8) LEFT ENGINE FUEL SHUTOFF VALVE ACTUATOR TEST

(a) Display the circuit breaker status for the left engine fuel shutoff valve on the flight deck display

using CBIC. Refer to 787 AMM 24-00-02 as an accepted procedure.

(b) Close the circuit breaker CE2822803 using CBIC. Refer to 787 AMM 24-00-02 as an accepted

procedure.

(c) On the CBIC data display screen, open the data screen of the circuit breaker CE2822803 and

monitor the LOAD CURRENT value during this test. Refer to 787 AMM 24-00-02 as an accepted

procedure.

(d) Make sure that the STATUS for the L FUEL SPAR VALVE shown on the Fuel Management

Maintenance page is CLOSED.

(e) Set the L FUEL CONTROL switch on the P8 Control Stand to RUN position and make sure

the following is observed during the test. The valve may require up to 15 seconds to reach its

commanded position.

1) The COMMAND for the L FUEL SPAR VALVE shows as OPEN condition on the Fuel

Management Maintenance page.

2) The STATUS for the L FUEL SPAR VALVE shows as IN/TRANS and then OPEN on the

Fuel Management Maintenance page.

3) The LOAD CURRENT value for the circuit breaker CE2822803 changes to a value of 0.1

Amps or more during the valve transition.

(f) Set the L FUEL CONTROL switch on the P8 Control Stand to CUTOFF position and make

sure the following is observed during the test. The valve may require up to 15 seconds to reach

its commanded position.

1) The COMMAND for the L FUEL SPAR VALVE shows as CLOSE condition on the Fuel

Management Maintenance page.

2) The STATUS for the L FUEL SPAR VALVE shows as IN/TRANS and then CLOSE on the

Fuel Management Maintenance page.

3) The LOAD CURRENT for the circuit breaker CE2822803 changes to a value of 0.1 Amps

or more during the valve transition.

(g) Open the circuit breaker CE2822803 using CBIC. Refer to 787 AMM 24-00-02 as an accepted

procedure.

(h) The condition of the left engine fuel shutoff valve actuator is determined as follows:

1) If the LOAD CURRENT value for the circuit breaker changed, as required during the test,

the left engine fuel shutoff valve actuator has passed the test and does not have the latent

failure condition.

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2) If the LOAD CURRENT for the circuit breaker did not change, as required during the test,

the left engine fuel shutoff valve actuator has failed this test and has the latent failure condition.

(9) RIGHT ENGINE FUEL SHUTOFF VALVE ACTUATOR TEST

(a) Display the circuit breaker status for the right engine fuel shutoff valve on the flight deck display

using CBIC. Refer to 787 AMM 24-00-02 as an accepted procedure.

(b) Close the circuit breaker CE2822804 using CBIC. Refer to 787 AMM 24-00-02 as an accepted

procedure.

(c) On the CBIC data display screen, open the data screen of the circuit breaker CE2822804 to

monitor the LOAD CURRENT value during this test. Refer to 787 AMM 24-00-02 as an accepted

procedure.

(d) Make sure that the STATUS for the R FUEL SPAR VALVE on the Fuel Management Maintenance page is CLOSED.

(e) Set the R FUEL CONTROL switch on the P8 Control Stand to RUN position and make sure

the following is observed during the test. The valve may require up to 15 seconds to reach its

commanded position.

1) The COMMAND for the R FUEL SPAR VALVE shows as OPEN condition on the Fuel

Management Maintenance page.

2) The STATUS for the R FUEL SPAR VALVE shows as IN/TRANS and then OPEN on the

Fuel Management Maintenance page.

3) The LOAD CURRENT value for the circuit breaker CE2822804 changes to a value of 0.1

Amps or more during the valve transition.

(f) Set the R FUEL CONTROL switch on the P8 Control Stand to CUTOFF position and make

sure the following is observed during the test. The valve may require up to 15 seconds to reach

its commanded position.

1) The COMMAND for the R FUEL SPAR VALVE shows as CLOSE on the Fuel Management

Maintenance page.

2) The STATUS for the R FUEL SPAR VALVE shows as IN/TRANS and then CLOSE on the

Fuel Management Maintenance page.

3) The LOAD CURRENT value for the circuit breaker CE2822804 changes to a value of 0.1

Amps or more during the valve transition.

(g) Open the circuit breaker CE2822804 using CBIC. Refer to 787 AMM 24-00-02 as an accepted

procedure.

(h) The condition of the right engine fuel shutoff valve actuator is determined as follows:

1) If the LOAD CURRENT value for the circuit breaker changed, as required during the test,

the right engine fuel shutoff valve actuator has passed the test and does not have the latent

failure condition.

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2) If the LOAD CURRENT for the circuit breaker did not change, as required during the test,

the right engine fuel shutoff valve actuator has failed this test and has the latent failure

condition.

(10) Close the following circuit breakers using the CBIC. Refer to 787 AMM 24-00-02 as an accepted

procedure.

Table 4 

Circuit Breaker Number Nomenclature

CE2822803 ENG SOV - L

CE2822804 ENG SOV - R

CE2825804 FUEL SHUTOFF MODULE

(11) Close the following thermal circuit breakers and remove the DO-NOT-CLOSE tag.

Table 5 

Circuit Breaker Number Nomenclature Panel Grid

CT7411811 IGNITION 1 CHAN A-L ENGINE P300 E5

CT7411812 IGNITION 2 CHAN B-L ENGINE P400 G15

CT7411821 IGNITION 1 CHAN A-R ENGINE P400 F8

CT7411822 IGNITION 2 CHAN B-R ENGINE P300 F5

E. RC - PART 2: APU FUEL SHUTOFF VALVE ACTUATOR TEST

Provide external electrical ground power to the airplane. Refer to 787 AMM 28-22-00 as an accepted

procedure.

(1)

(2) Make sure that no active or latched APU FUEL SOV messages exist.

(3) Make sure the following circuit breakers are opened using the Circuit Breaker Indication and Control

(CBIC). Refer to 787 AMM 24-00-02 as an accepted procedure.

Table 6 

Circuit Breaker Number Nomenclature

CE2825801 APU DC PUMP

CE2825804 FUEL SHUTOFF MODULE

(4) Set the GND TEST switch on the Cargo Fire/Engine Control panel to ENABLE position.

(5) Make sure that the following circuit breakers are closed using the CBIC. Refer to 787 AMM 24-00-

02 as an accepted procedure.

Table 7 

Circuit Breaker Number Nomenclature

CE2825802 APU SOV CLOSE

CE2825803 APU SOV OPEN

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(6) Make sure that the APU Fire handle on the P5 Overhead panel is in normal stowed position.

(7) Display the Fuel Management Maintenance page on the Central Maintenance Computing Function

(CMCF). Refer to 787 AMM 31-61-00 as an accepted procedure.

(8) Display the CE2825803 circuit breaker status for the APU fuel shutoff valve using the CBIC on the

flight deck display. Refer to 787 AMM 24-00-02 as an accepted procedure.

(9) Make sure that the STATUS for the APU FUEL FEED S/O VLV shown on the Fuel Management

Maintenance page is CLOSED.

(10) On the CBIC data display screen, open the data screen of the circuit breaker CE2825803 to monitor

the LOAD CURRENT value during this test. Refer to 787 AMM 24-00-02 as an accepted procedure.

(11) Make sure that the CMCF ground test passes after it is initiated.

ATA Chapter: 28 Fuel Quality Management Systems

Test Type: LRU Replacement Test

Name: APU FUEL SHUTOFF VALVE

Make sure the following is observed during the ground test.

(a) The STATUS for the APU FUEL FEED S/O VLV shows as IN/TRANS and then OPEN on the

Fuel Management Maintenance page during the CMCF ground test sequence.

(b) The LOAD CURRENT value for the circuit breaker CE2825803 changes to a value of 0.1 Amps

or more during the valve transition from IN/TRANS to OPEN.

NOTE: It is not necessary to observe the LOAD CURRENT value during the valve transition

from IN/TRANS to CLOSE. 

(12) After the ground test passes successfully, exit the data screen for the circuit breaker CE2825803

on the CBIC display. Refer to 787 AMM 24-00-02 as an accepted procedure.

(13) On the CBIC display, open the data screen for circuit breaker CE2825802 to monitor the LOAD

CURRENT value for the steps that follow.

(14) Make sure that the CMCF ground test passes after it is initiated

ATA Chapter: 28 Fuel Quality Management Systems

Test Type: LRU Replacement Test

Name: APU FUEL SHUTOFF VALVE

Make sure the following is observed during the ground test.

(a) The STATUS for the APU FUEL FEED S/O VLV shows the following sequence: IN/TRANS

and then OPEN and back to CLOSE on the Fuel Management Maintenance page during the

CMCF Ground Test sequence.

(b) The LOAD CURRENT value for the circuit breaker CE2825802 changes to a value of 0.1 Amps

or more during the valve transition from IN/TRANS to CLOSE.

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NOTE: It is not necessary to observe the LOAD CURRENT value during the valve transition

from IN/TRANS to OPEN. 

(15) After the CMCF Ground Test passes successfully, exit the data screen for the circuit breaker

CE2825802 on CBIC display.

(16) Set the GND TEST switch on the Cargo Fire/Engine Control panel to NORM position.

(17) The condition of the APU fuel shutoff valve actuator is determined as follows:

(a) If the LOAD CURRENT value for the circuit breaker changed, as required during the test, the

APU fuel shutoff valve actuator has passed the test and does not have the latent failure condition.

(b) If the LOAD CURRENT for the circuit breaker did not change, as required during the test, the

APU fuel shutoff valve actuator has failed this test and has the latent failure condition.

(18) Close these circuit breakers using the Circuit Breaker Indication and Control (CBIC). Refer to 787

AMM 24-00-02 as an accepted procedure.

Table 8 

Circuit Breaker Number Nomenclature

CE2825801 APU DC PUMP

CE2825804 FUEL SHUTOFF MODULE

F. PART 3: ENGINE FUEL SHUTOFF VALVE ACTUATOR REPLACEMENT

Remove the left or right engine fuel shutoff valve actuator. Refer to 787 AMM 28-22-02 as an accepted

procedure.

(1)

(2) Install a new or serviceable left or right engine fuel shutoff valve actuator with part number 53-0037

and do the installation test. Refer to 787 AMM 28-22-02 as an accepted procedure.

G. PART 4: APU FUEL SHUTOFF VALVE ACTUATOR REPLACEMENT

Remove the APU engine fuel shutoff valve actuator. Refer to 787 AMM 28-25-03 as an accepted

procedure.

(1)

(2) Install a new or serviceable APU fuel shutoff valve actuator with part number 53-0037 and do the

installation test. Refer to 787 AMM 28-25-03 as an accepted procedure.

H. RC - PART 5: TERMINATING ACTION - ENGINE FUEL SHUTOFF VALVE ACTUATOR REPLACEMENT

Remove the left and right engine fuel shutoff valve actuator. Refer to 787 AMM 28-22-02 as an accepted procedure.(1)

(2) Install the new left and right engine fuel shutoff valve actuator with part number 53-0049 and do the

installation test. Refer to 787 AMM 28-22-02 as an accepted procedure.

I. RC - PART 6: TERMINATING ACTION - APU FUEL SHUTOFF VALVE ACTUATOR REPLACEMENT

Remove the APU engine fuel shutoff valve actuator. Refer to 787 AMM 28-25-03 as an accepted

procedure.

(1)

(2) Install the new APU fuel shutoff valve actuator with part number 53-0049 and do the installation test.

Refer to 787 AMM 28-25-03 as an accepted procedure.

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J. PART 7: FUEL CROSSFEED VALVE ACTUATOR REPLACEMENT

(1) Remove the fuel crossfeed valve actuator. Refer to 787 AMM 28-22-04 as an accepted procedure.

(2) Install the fuel crossfeed valve actuator with part number 53-0049 and do the installation test. Refer

to 787 AMM 28-22-04 as an accepted procedure.

K. PART 8: DEFUEL/ISOLATION VALVE ACTUATOR REPLACEMENT

(1) Remove the left and right defuel/isolation valve actuators. Refer to 787 AMM 28-26-02 as an accepted

procedure.

(2) Install a new left or right defuel/isolation valve actuator with part number 53-0049 and do the installation test. Refer to 787 AMM 28-26-02as an accepted procedure.

Applicable To: B787-A-28-00-0015-00A-933A-D

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