Alert Service Bulletin B787-81205-SB270024-00 FLIGHT CONTROLS - Spoiler

and Speedbrake Control System - Left Wing Spoiler 4 Electro-Mechanical

Actuator Wire and Bracket Separation Inspection

Publication: B787-81205-SB270024-00 Issue 001, 24 Sep 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 Unpublished Work.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.

EXPORT CONTROLLED

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-27-00-0024-00A-932A-D, Paragraph 1., Effectivity for the

list of affected airplanes.

TITLE PAGE B787-81205-SB270024-00

Issue 001, 24 Sep 2014

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2.0

B787-81205-SB270024-00

Issue 001, 24 Sep 2014

AIRCRAFT SERVICE BULLETIN
Alert Service Bulletin B787-81205-SB270024-00

Table of Contents

Page

Summary .....................................................5

PLANNING INFORMATION ..........................................9

1. Effectivity .............................................9

A. Airplanes ............................................9

B. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10

2. Concurrent Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10

3. Reason . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10

4. Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11

5. Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11

6. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12

7. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12

8. Weight and Balance Changes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13

9. Electrical Load Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13

10. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13

A. Existing Data: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13

B. Data Supplied with this Service Bulletin: . . . . . . . . . . . . . . . . . . . . . . . . . . 13

C. Installation Requirement Modules Used in the Preparation of this Service Bulletin: . . . 13

11. Publications Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13

12. Interchangeability and Intermixability of Parts . . . . . . . . . . . . . . . . . . . . . . . . . 14

13. Software Accomplishment Summary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14

MATERIAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

1. Material - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

2. Industry Support Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

3. Parts Necessary for Each Airplane . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

A. Kits/Parts: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

B. Parts and Materials Supplied by the Operator: . . . . . . . . . . . . . . . . . . . . . . . 15

C. Parts Modified and Reidentified: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

D. Parts Removed and Not Replaced: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

4. Parts Necessary to Change Spares . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16

5. Special Tooling - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16

6. Special Tooling Necessary to do this Service Bulletin . . . . . . . . . . . . . . . . . . . . . 16

ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

1. GENERAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

2. WORK INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

Task 1 – LEFT WING SPOILER 4 ELECTRO-MECHANICAL ACTUATOR WIRE W801182 AND THE

FLAP VARIABLE CAMBER TRIM UNIT SUPPORT BRACKET SEPARATION MEASUREMENT

[Group 1:]. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 21

TABLE OF CONTENTS B787-81205-SB270024-00

Issue 001, 24 Sep 2014

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B787-81205-SB270024-00

Issue 001, 24 Sep 2014

AIRCRAFT SERVICE BULLETIN
Alert Service Bulletin B787-81205-SB270024-00

List of Illustrations

THIS ALERT SERVICE BULLETIN IS SENT TO THE OPERATORS OF RECORD OF THE

AIRPLANES SHOWN IN DATA MODULE SB B787-A-27-00-0024-00A-932A-D, PARAGRAPH 1.,

Alert:

EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS SERVICE BULLETIN

TO THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS SERVICE

BULLETIN TO THE NEW OWNER.

Description

Group 1:

Table 1 List of Illustrations - Alert Service Bulletin B787-81205-SB270024-00

ICN Used In

ICN-B787-A-000061-A-81205-07155-A-01-1 B787-A-27-00-0024-00A-931C-D Issue 002

ICN-B787-A-000061-A-81205-07156-A-01-1 B787-A-27-00-0024-01A-933B-D Issue 002

Applicable To: B787-A-27-00-0024-00A-00AA-D

Model 787 End of data module Issue 002, 24 Sep 2014

See Applicability of this data module

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B787-81205-SB270024-00

Issue 001, 24 Sep 2014

AIRCRAFT SERVICE BULLETIN
Alert Service Bulletin B787-81205-SB270024-00

List of Effective Data Modules

THIS ALERT SERVICE BULLETIN IS SENT TO THE OPERATORS OF RECORD OF THE

AIRPLANES SHOWN IN DATA MODULE SB B787-A-27-00-0024-00A-932A-D, PARAGRAPH 1.,

Alert:

EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS SERVICE BULLETIN

TO THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS SERVICE

BULLETIN TO THE NEW OWNER.

Description

Group 1:

Table 1 List of Effective Data Modules - Alert Service Bulletin B787-81205-SB270024-00

Data Module – Information Name Issue Issue Status Issue Date

B787-A-27-00-0024-00A-00AA-D – List of Illustrations 002 Changed 2014-09-24

B787-A-27-00-0024-00A-00SA-D – List of Effective Data Modules 002 Changed 2014-09-24

B787-A-27-00-0024-00A-931C-D – Summary 002 Changed 2014-09-24

B787-A-27-00-0024-00A-932A-D – PLANNING INFORMATION 002 Changed 2014-09-24

B787-A-27-00-0024-00A-934A-D – MATERIAL INFORMATION 002 Changed 2014-09-24

B787-A-27-00-0024-00A-933A-D – ACCOMPLISHMENT INSTRUCTIONS 002 Changed 2014-09-24

B787-A-27-00-0024-01A-933B-D – Task 1 – LEFT WING SPOILER 4 002 Changed 2014-09-24

ELECTRO-MECHANICAL ACTUATOR WIRE W801182 AND THE FLAP

VARIABLE CAMBER TRIM UNIT SUPPORT BRACKET SEPARATION

MEASUREMENT [Group 1:]

Applicable To: B787-A-27-00-0024-00A-00SA-D

Model 787 End of data module Issue 002, 24 Sep 2014

See Applicability of this data module

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B787-81205-SB270024-00

Issue 001, 24 Sep 2014

AIRCRAFT SERVICE BULLETIN
Alert Service Bulletin B787-81205-SB270024-00

Summary

THIS ALERT SERVICE BULLETIN IS SENT TO THE OPERATORS OF RECORD OF THE

AIRPLANES SHOWN IN DATA MODULE SB B787-A-27-00-0024-00A-932A-D, PARAGRAPH 1.,

Alert:

EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS SERVICE BULLETIN

TO THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS SERVICE

BULLETIN TO THE NEW OWNER.

References

Reference Title

SB B787-A-27-00-0024-00A-932A-D Issue 002, Spares Affected

Paragraph 1.B.

SB B787-A-27-00-0024-00A-932A-D Issue 002, Compliance

Paragraph 5.

SB B787-A-27-00-0024-00A-932A-D Issue 002, Weight and Balance Changes

Paragraph 8.

SB B787-A-27-00-0024-00A-932A-D Issue 002, Electrical Load Data

Paragraph 9.

SB B787-A-27-00-0024-00A-932A-D Issue 002, Publications Affected

Paragraph 11.

SB B787-A-27-00-0024-00A-934A-D Issue 002, Kits/Parts

Paragraph 3.A.

SB B787-A-27-00-0024-00A-934A-D Issue 002, Parts and Materials Supplied by the Operator

Paragraph 3.B.

SB B787-A-27-00-0024-00A-934A-D Issue 002, Special Tooling Necessary to do this Service Bulletin

Paragraph 6.

SB B787-A-27-00-0024-00A-932A-D Issue 002, Effectivity

Paragraph 1.

SB B787-A-27-00-0024-00A-934A-D Issue 002, Industry Support Information

Paragraph 2.

SB B787-A-27-00-0024-00A-932A-D Issue 002, Manpower

Paragraph 7.

Applicable To: B787-A-27-00-0024-00A-931C-D

Model 787 Issue 002, 24 Sep 2014

See Applicability of this data module

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B787-81205-SB270024-00

Issue 001, 24 Sep 2014

AIRCRAFT SERVICE BULLETIN
Description

Group 1:

1. CONCURRENT REQUIREMENTS

None.

2. BACKGROUND

Boeing found the left wing spoiler 4 electro-mechanical actuator power feeder wire W801182 does not have

enough separation to the flap variable camber trim unit support bracket outboard end when the spoiler is

deployed. This service bulletin provides instructions to measure the separation between the wire and the

bracket outboard end with the spoiler in the deployed position. If the measurement does not meet the minimum

separation requirement, this service bulletin provides instructions to inspect and adjust the wire. If the wire

does not have enough separation to the bracket outboard end when the spoiler is deployed, the wire could

be damaged by contact with the bracket which could result in an electrical short and potential loss of several

functions essential for safe flight.

Boeing Service Related Problem (SRP) 787 SRP-27-244 is related to 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-27-00-0024-00A-932AD, Paragraph 1.B., Spares AffectedSpares Affected No

Data Module SB B787-A-27-00-0024-00A-932AD, Paragraph 5., ComplianceAD Related No

Data Module SB B787-A-27-00-0024-00A-932AD, Paragraph 8., Weight and Balance ChangesWeight and Balance Changed No

Data Module SB B787-A-27-00-0024-00A-932AD, Paragraph 9., Electrical Load DataElectrical Load Changed No

Data Module SB B787-A-27-00-0024-00A-932AD, Paragraph 11., Publications AffectedPublications Affected Yes

Data Module SB B787-A-27-00-0024-00A-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-27-00-0024-00A-934AD, Paragraph 3.A., Kits/PartsKits/Parts Required No

Data Module SB B787-A-27-00-0024-00A-934AD, Paragraph 3.B., Parts and Materials Supplied

by the Operator

Operator Supplied Parts/Material No

Data Module SB B787-A-27-00-0024-00A-934AD, Paragraph 6., Special Tooling Necessary to

do this Service Bulletin

Special Tooling Required No

Applicable To: B787-A-27-00-0024-00A-931C-D

Model 787 Issue 002, 24 Sep 2014

See Applicability of this data module

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B787-81205-SB270024-00

Issue 001, 24 Sep 2014

AIRCRAFT SERVICE BULLETIN
3. ACTION

(CN-AA45701C)

Do the following:

1. Deactivate the spoilers in the UP position.

2. Remove and keep the left wing lower fixed trailing edge panel 561CB.

3. Measure the separation between the left wing spoiler 4 electro-mechanical actuator wire W801182 and

the flap variable camber trim unit support bracket outboard end. If the separation is less than 0.5 inch:

A. Do a general visual inspection of the wire for chafing. If the wire is chafed, replace the wire.

B. Adjust the wire to get a minimum separation of 0.5 inch.

4. Install the kept left wing lower fixed trailing edge panel 561CB.

5. Activate the spoilers.

4. EFFECTIVITY

787-8 Airplanes. Refer to Data Module SB B787-A-27-00-0024-00A-932A-D, Paragraph 1., Effectivity for

the list of affected airplanes.

5. COMPLIANCE

Refer to Data Module SB B787-A-27-00-0024-00A-932A-D, Paragraph 5., Compliance.

6. INDUSTRY SUPPORT INFORMATION

Boeing warranty remedies are available for airplanes in warranty as of January 14, 2014. Please refer to

Data Module SB B787-A-27-00-0024-00A-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-27-00-0024-00A-932A-D, Paragraph 7., Manpower.

8. MATERIAL INFORMATION

None.

Applicable To: B787-A-27-00-0024-00A-931C-D

Model 787 Issue 002, 24 Sep 2014

See Applicability of this data module

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B787-81205-SB270024-00

Issue 001, 24 Sep 2014

AIRCRAFT SERVICE BULLETIN
ICN-B787-A-000061-A-81205-07155-A-01-1

Figure 1 

Applicable To: B787-A-27-00-0024-00A-931C-D

Model 787 End of data module Issue 002, 24 Sep 2014

See Applicability of this data module

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B787-81205-SB270024-00

Issue 001, 24 Sep 2014

AIRCRAFT SERVICE BULLETIN
Alert Service Bulletin B787-81205-SB270024-00

PLANNING INFORMATION

THIS ALERT SERVICE BULLETIN IS SENT TO THE OPERATORS OF RECORD OF THE

AIRPLANES SHOWN IN PARAGRAPH 1., EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED

Alert:

OR SOLD, SEND THIS SERVICE BULLETIN TO THE NEW OPERATOR. IF APPLICABLE SPARES

HAVE BEEN SOLD, SEND THIS SERVICE BULLETIN TO THE NEW OWNER.

References

Reference Title

SB B787-A-27-00-0024-00A-933A-D Issue 002, Step 2. Work Instructions

SWPM 20-10-11 Standard Wiring Practices Manual

SWPM 20-10-12 Standard Wiring Practices Manual

SWPM 20-10-19 Standard Wiring Practices Manual

787 AMM 27-61-00 SPOILER AND SPEEDBRAKE CONTROL SYSTEM

787 AMM 57-51-10 FIXED TRAILING EDGE PANELS

Description

Group 1:

1. Effectivity

A. Airplanes

This service bulletin is applicable to 787-8 Airplanes, line numbers 7-9, 23-24, 27, 29, 31, 33-35, 37-

42, 44-78, 80, 82-84, 86-89, 91-92, 94-99, 101-103, 105-108, 111, 117 in 1 Group(s). The Variable

Numbers and Group information for the applicable airplanes is given below. Refer to CN-AA45701 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-ZA120 1

Applicable To: B787-A-27-00-0024-00A-932A-D

Model 787 Issue 002, 24 Sep 2014

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AIRCRAFT SERVICE BULLETIN
Table 2 

Variable Number Group

ZA135 1

ZA177-ZA186 1

ZA233 1

ZA236-ZA241 1

ZA243 1

ZA260-ZA264 1

ZA270-ZA274 1

ZA285-ZA291 1

ZA317-ZA320 1

ZA380 1

ZA384 1

ZA430-ZA431 1

ZA450-ZA451 1

ZA460-ZA466 1

ZA506-ZA514 1

ZA536-ZA538 1

ZA576 1

B. Spares Affected

None.

2. Concurrent Requirements

None.

3. Reason

Boeing found the left wing spoiler 4 electro-mechanical actuator power feeder wire W801182 does not

have enough separation to the flap variable camber trim unit support bracket outboard end when the

spoiler is deployed. This service bulletin provides instructions to measure the separation between the wire

and the bracket outboard end with the spoiler in the deployed position. If the measurement does not meet

the minimum separation requirement, this service bulletin provides instructions to inspect and adjust the

wire. If the wire does not have enough separation to the bracket outboard end when the spoiler is deployed,

the wire could be damaged by contact with the bracket which could result in an electrical short and potential

loss of several functions essential for safe flight.

Boeing Service Related Problem (SRP) 787 SRP-27-244 is related to this service bulletin.

Applicable To: B787-A-27-00-0024-00A-932A-D

Model 787 Issue 002, 24 Sep 2014

See Applicability of this data module

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B787-81205-SB270024-00

Issue 001, 24 Sep 2014

AIRCRAFT SERVICE BULLETIN
4. Description

Do the following:

1. Deactivate the spoilers in the UP position.

2. Remove and keep the left wing lower fixed trailing edge panel 561CB.

3. Measure the separation between the left wing spoiler 4 electro-mechanical actuator wire W801182 and

the flap variable camber trim unit support bracket outboard end. If the separation is less than 0.5 inch:

A. Do a general visual inspection of the wire for chafing. If the wire is chafed, replace the wire.

B. Adjust the wire to get a minimum separation of 0.5 inch.

4. Install the kept left wing lower fixed trailing edge panel 561CB.

5. Activate the spoilers.

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

Table 3 

Affected Maintenance Zones

Model Zone

787-8 562

5. Compliance

Do the required actions in accordance with Data Module SB B787-A-27-00-0024-00A-933A-D, Step 2.,

Work Instructions.

Table 4 Measure The Separation Between The Left Wing Spoiler 4 Electro-Mechanical Actuator

 Wire W801182 And The Flap Variable Camber Trim Unit Support Bracket

Repeat Interval

(Not to Exceed)

Condition Action Compliance Time

Within 24 months -

after the Issue 001

date of this service

bulletin.

Do PART 1: MEASURE

THE SEPARATION BETWEEN THE LEFT WING

SPOILER 4 ELECTROMECHANICAL ACTUATOR WIRE W801182 AND

THE FLAP VARIABLE

CAMBER TRIM UNIT

SUPPORT BRACKET.

All Airplanes

CONDITION 1: SEPARA- No further action required. - -

TION IS GREATER THAN

OR EQUAL TO 0.5 INCH

Applicable To: B787-A-27-00-0024-00A-932A-D

Model 787 Issue 002, 24 Sep 2014

See Applicability of this data module

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B787-81205-SB270024-00

Issue 001, 24 Sep 2014

AIRCRAFT SERVICE BULLETIN
Table 4 Measure The Separation Between The Left Wing Spoiler 4 Electro-Mechanical Actuator

 Wire W801182 And The Flap Variable Camber Trim Unit Support Bracket

Repeat Interval

(Not to Exceed)

Condition Action Compliance Time

Before further -

flight.

Do PART 2: GENERAL

VISUAL INSPECTION OF

THE LEFT WING SPOILER 4 ELECTRO-MECHANICAL ACTUATOR WIRE

W801182 for chafing.

CONDITION 2: SEPARATION IS LESS THAN 0.5

INCH

Before further -

flight.

Do PART 3: ADJUST THE

LEFT WING SPOILER 4

ELECTRO-MECHANICAL

ACTUATOR WIRE

W801182.

CONDITION 3: NO

CHAFING FOUND

Before further -

flight.

CONDITION 4 (ACTION

1): Replace the wire.

CONDITION 4: CHAFING

FOUND

Before further -

flight.

CONDITION 4 (ACTION

2): Do PART 3: ADJUST

THE LEFT WING SPOILER 4 ELECTRO-MECHANICAL ACTUATOR WIRE

W801182.

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

– Time to inspect the work

– Time to cure the materials

– Time to make the parts

– Time to find the tools

Applicable To: B787-A-27-00-0024-00A-932A-D

Model 787 Issue 002, 24 Sep 2014

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AIRCRAFT SERVICE BULLETIN
Table 5 

Number of Per- Task Hours Elapsed Hours

sons

Task

Open Access 1 2.50 2.50

PART 1, Task 1 1 0.05 0.05

0.05 *[1] 0.05 1 *[1] PART 2 *[1]

0.50 *[1] 0.50 1 *[1] PART 3 *[1]

1.15 *[2] 1.15 Replace wire and 1 *[2]

test *[2]

Close Access 1 2.50 2.50

TOTAL FOR EACH AIRPLANE 5.05 5.05

*[1] Add Task hours if PART 2 and PART 3 are required.

*[2] Add Task hours if wire is replaced.

8. Weight and Balance Changes

None.

9. Electrical Load Data

Not changed.

10. References

A. Existing Data:

1. Change Notice CN-AA45701C

2. Aircraft Maintenance Manual (AMM) 787 AMM 27-61-00, 787 AMM 57-51-10

3. Boeing Service Related Problem (SRP) 787 SRP-27-244

4. Standard Wiring Practices Manual (SWPM) SWPM 20-10-11, SWPM 20-10-12, SWPM 20-10-19

B. Data Supplied with this Service Bulletin:

None.

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

11. Publications Affected

Table 6 

Publication Chapter-Section

787 Maintenance Manual 27-61

Applicable To: B787-A-27-00-0024-00A-932A-D

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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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Alert Service Bulletin B787-81205-SB270024-00

MATERIAL INFORMATION

THIS ALERT SERVICE BULLETIN IS SENT TO THE OPERATORS OF RECORD OF THE

AIRPLANES SHOWN IN DATA MODULE SB B787-A-27-00-0024-00A-932A-D, PARAGRAPH 1.,

Alert:

EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS SERVICE BULLETIN

TO THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS SERVICE

BULLETIN TO THE NEW OWNER.

References

Reference Title

SB B787-A-27-00-0024-00A-932A-D Issue 002, References

Paragraph 10.

Description

Group 1:

1. Material - Price and Availability

None.

2. Industry Support Information

Boeing warranty remedies are available for 787 airplanes in warranty as of January 14, 2014. For task hour

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

Contracts - Warranty. The parts for airplanes in warranty as of that date will be supplied at no charge. Send

a purchase order for the parts to Boeing Material Management. Please refer to this service bulletin number

and reference the airplane variable numbers in your purchase order. 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:

None.

C. Parts Modified and Reidentified:

None.

D. Parts Removed and Not Replaced:

None.

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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-27-00-0024-00A-932A-D, Paragraph 10.,

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

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Alert Service Bulletin B787-81205-SB270024-00

ACCOMPLISHMENT INSTRUCTIONS

THIS ALERT SERVICE BULLETIN IS SENT TO THE OPERATORS OF RECORD OF THE

AIRPLANES SHOWN IN DATA MODULE SB B787-A-27-00-0024-00A-932A-D, PARAGRAPH 1.,

Alert:

EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS SERVICE BULLETIN

TO THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS SERVICE

BULLETIN TO THE NEW OWNER.

References

Reference Title

SB B787-A-27-00-0024-00A-932A-D Issue 002, References

Paragraph 10.

SB B787-A-27-00-0024-00A-932A-D Issue 002, Compliance

Paragraph 5.

Alert Service Bulletin

B787-81205-SB270024-00 – Task 1 – LEFT WING

SB B787-A-27-00-0024-01A-933B-D Issue 002

SPOILER 4 ELECTRO-MECHANICAL ACTUATOR

WIRE W801182 AND THE FLAP VARIABLE

CAMBER TRIM UNIT SUPPORT BRACKET

SEPARATION MEASUREMENT [Group 1:]

SWPM 20-10-11 Standard Wiring Practices Manual

SWPM 20-10-12 Standard Wiring Practices Manual

SWPM 20-10-19 Standard Wiring Practices Manual

SWPM 20-10-11 Standard Wiring Practices Manual

787 AMM 27-61-00 SPOILER AND SPEEDBRAKE CONTROL SYSTEM

787 AMM 57-51-10 FIXED TRAILING EDGE PANELS

Procedure

Group 1:

1. GENERAL INFORMATION

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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-27-00-0024-00A932A-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

– 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. Refer to the SWPM 20-10-11 and SWPM 20-10-12 for the wire installation procedures, and

SWPM 20-10-19 for the wire separation requirements, as accepted procedures.

5. The necessary conditions for selection of clamp type and size are included in SWPM 20-10-12.

If any wire bundle support clamp specified in this service bulletin does not make a correct fit on

the wire bundle, refer to SWPM 20-10-12 as an accepted procedure to select a clamp that fits

correctly.

6. A General Visual Inspection is defined as: A visual examination of an interior or exterior area,

installation or assembly to detect obvious damage, failure or irregularity. This level of inspection

is made from within touching distance unless otherwise specified. A mirror may be necessary

to ensure visual access to all surfaces in the inspection area. This level of inspection is made

under normal available lighting conditions such as daylight, hangar lighting, flashlight or droplight and may require removal or opening of access panels or doors. Stands, ladders or platforms

may be required to gain proximity to the area being checked.

7. 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.

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8. 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.

9. Where the work instructions include installation of a kept part, a new or serviceable part with

the same part number can be installed as an alternative to the kept part.

10. 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.

11. Use of colors in Tasks is based on guidance from the S1000D International specification for

technical publications.

12. 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.

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

A-27-00-0024-00A-932A-D, Paragraph 5., Compliance.

14. The CONDITIONS, ACTIONS and OPTIONS shown apply to each separation measurement

independently.

2. WORK INSTRUCTIONS

A. Left Wing Spoiler 4 Electro-Mechanical Actuator Wire and Bracket Separation Inspection

(1) Deactivate the spoilers in the UP position. Refer to 787 AMM 27-61-00 as an accepted procedure.

(2) Remove and keep left wing lower fixed trailing edge panel 561CB. Refer to 787 AMM 57-51-10 as

an accepted procedure.

(3) Do PART 1: MEASURE THE SEPARATION BETWEEN THE LEFT WING SPOILER 4 ELECTROMECHANICAL ACTUATOR WIRE W801182 AND THE FLAP VARIABLE CAMBER TRIM UNIT

SUPPORT BRACKET.

(a) CONDITION 1: SEPARATION IS GREATER THAN OR EQUAL TO 0.5 INCH.

1) No further action required.

(b) CONDITION 2: SEPARATION IS LESS THAN 0.5 INCH.

1) Do PART 2: GENERAL VISUAL INSPECTION OF THE LEFT WING SPOILER 4 ELECTROMECHANICAL ACTUATOR WIRE W801182 for chafing.

a) CONDITION 3: NO CHAFING FOUND.

Do PART 3: ADJUST THE LEFT WING SPOILER 4 ELECTRO-MECHANICAL

ACTUATOR WIRE W801182.

<1>

b) CONDITION 4: CHAFING FOUND.

<1> CONDITION 4 (ACTION 1): Replace the wire. Refer to SWPM 20-10-11 as an

accepted procedure.

<2> CONDITION 4 (ACTION 2): Do PART 3: ADJUST THE LEFT WING SPOILER 4

ELECTRO-MECHANICAL ACTUATOR WIRE W801182.

Applicable To: B787-A-27-00-0024-00A-933A-D

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(4) Install kept left wing lower fixed trailing edge panel 561CB. Refer to 787 AMM 57-51-10 as an accepted procedure

(5) Activate the spoilers. Refer to 787 AMM 27-61-00 as an accepted procedure.

(6) If the wire was replaced, do a Spoilers (Electric) - System Test. Refer to 787 AMM 27-61-00 as an

accepted procedure.

(7) Put the airplane back to a serviceable condition.

B. PART 1: MEASURE THE SEPARATION BETWEEN THE LEFT WING SPOILER 4

ELECTRO-MECHANICAL ACTUATOR WIRE W801182 AND THE FLAP VARIABLE CAMBER TRIM

UNIT SUPPORT BRACKET

(1) Measure the separation between the left wing spoiler 4 electro-mechanical actuator wire W801182

and the flap variable camber trim unit support bracket outboard end in accordance with Data Module

Task 1, SB B787-A-27-00-0024-01A-933B-D.

C. PART 2: GENERAL VISUAL INSPECTION OF THE LEFT WING SPOILER 4 ELECTRO-MECHANICAL

ACTUATOR WIRE W801182

(1) Do a general visual inspection of the wire W801182 adjacent to the bracket for chafing.

D. PART 3: ADJUST THE LEFT WING SPOILER 4 ELECTRO-MECHANICAL ACTUATOR WIRE W801182

(1) Adjust wire W801182 to get a minimum separation of 0.5 inch between wire W801182 and the

bracket outboard end. Loosen adjacent clamps as required. Tighten any loosened clamps after wire

adjustment. Refer to SWPM 20-10-11 and SWPM 20-10-12 as accepted procedures.

Applicable To: B787-A-27-00-0024-00A-933A-D

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Alert Service Bulletin B787-81205-SB270024-00

Task 1 – LEFT WING SPOILER 4 ELECTRO-MECHANICAL ACTUATOR

WIRE W801182 AND THE FLAP VARIABLE CAMBER TRIM UNIT SUPPORT

BRACKET SEPARATION MEASUREMENT [Group 1:]

THIS ALERT SERVICE BULLETIN IS SENT TO THE OPERATORS OF RECORD OF THE

AIRPLANES SHOWN IN DATA MODULE SB B787-A-27-00-0024-00A-932A-D, PARAGRAPH 1.,

Alert:

EFFECTIVITY. IF AN AIRPLANE HAS BEEN LEASED OR SOLD, SEND THIS SERVICE BULLETIN

TO THE NEW OPERATOR. IF APPLICABLE SPARES HAVE BEEN SOLD, SEND THIS SERVICE

BULLETIN TO THE NEW OWNER.

Preliminary Requirements

Required Conditions

Action/Condition Data Module/Technical Publication

Alert Service Bulletin B787-81205-SB270024-00 - B787-A-27-00-0024-00A-933A-D Issue 002

ACCOMPLISHMENT INSTRUCTIONS

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Procedure

This Task applies to Group 1:

ICN-B787-A-000061-A-81205-07156-A-01-1

Figure 1 

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1. The step numbers shown below agree with the numbers shown in the circle symbols in the Task. The QTY

numbers shown below are the number of parts necessary for this Task.

Table 1 

Step Action Name Identification Qty More Data

Measure the separation between the left

wing spoiler 4 electro-mechanical actuator wire W801182

and the flap variable

camber trim unit

support bracket outboard end.

1 Measure SEPARATION - 1

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