Alert Service Bulletin B787-81205-SB270026-00 FLIGHT CONTROLS - Flight

Controls - Hydraulic Power Control Unit Particle Deposit Prevention -

Elevator and Aileron Power Control Unit Test

Publication: B787-81205-SB270026-00 Issue 001, 25 Nov 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 Unpublished Work.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,

MD-11, MD-80, MD-88, MD-90, P-8, Poseidon and Boeing liveries are all trademarks owned by The Boeing Company; and no trademark

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

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

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-27-00-0026-00A-932A-D, Paragraph 1., Effectivity for the

list of affected airplanes.

TITLE PAGE B787-81205-SB270026-00

Issue 001, 25 Nov 2014

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3.0

B787-81205-SB270026-00

Issue 001, 25 Nov 2014

AIRCRAFT SERVICE BULLETIN
Alert Service Bulletin B787-81205-SB270026-00

Table of Contents

Page

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

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

1. Effectivity . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13

A. Airplanes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13

B. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

2. Concurrent Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

3. Reason . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

4. Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16

5. Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16

6. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22

7. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 22

8. Weight and Balance Changes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25

9. Electrical Load Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 26

10. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 26

A. Existing Data: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 26

B. Data Supplied with this Service Bulletin: . . . . . . . . . . . . . . . . . . . . . . . . . . 26

C. Installation Requirement Modules Used in the Preparation of this Service Bulletin: . . . 26

11. Publications Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 26

12. Interchangeability and Intermixability of Parts . . . . . . . . . . . . . . . . . . . . . . . . . 26

13. Software Accomplishment Summary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 26

MATERIAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27

1. Material - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27

2. Industry Support Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27

3. Parts Necessary for Each Airplane . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27

A. Kits/Parts: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27

B. Parts and Materials Supplied by the Operator: . . . . . . . . . . . . . . . . . . . . . . . 27

C. Parts Modified and Reidentified: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 28

D. Parts Removed and Not Replaced: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 28

4. Parts Necessary to Change Spares . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 28

5. Special Tooling - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 28

6. Special Tooling Necessary to do this Service Bulletin . . . . . . . . . . . . . . . . . . . . . 28

ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 30

1. GENERAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 31

2. WORK INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 33

Appendix A – LOGIC DIAGRAM FOR PARAGRAPH 1.E. COMPLIANCE: TABLE 5 LEFT, RIGHT AND

CENTER HYDRAULIC SYSTEM FLUID MARKER INSTALLATION [Group 1-2:]. . . . . . 56

Appendix B – LOGIC DIAGRAM FOR PARAGRAPH 1.E. COMPLIANCE: TABLE 6 LEFT HYDRAULIC

SYSTEM FLUID TEST [Group 1, Configuration 2; Group 2: ]. . . . . . . . . . . . . . . . . 59

Appendix C – LOGIC DIAGRAM FOR PARAGRAPH 1.E. COMPLIANCE: TABLE 7 RIGHT HYDRAULIC

SYSTEM FLUID TEST [Group 1, Configuration 2; Group 2: ]. . . . . . . . . . . . . . . . . 62

TABLE OF CONTENTS B787-81205-SB270026-00

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B787-81205-SB270026-00

Issue 001, 25 Nov 2014

AIRCRAFT SERVICE BULLETIN
Appendix D – LOGIC DIAGRAM FOR PARAGRAPH 1.E. COMPLIANCE: TABLE 8 CENTER HYDRAULIC

SYSTEM FLUID TEST AND LEFT AND RIGHT ELEVATOR AND AILERON POWER

CONTROL UNIT INTERNAL FLOW TEST [Group 1, Configuration 2; Group 2: ]. . . . . . 65

Appendix E – LOGIC DIAGRAM FOR PARAGRAPH 1.E. COMPLIANCE: TABLE 9 WORK PACKAGE

5 AND WORK PACKAGE 6 CONDITIONS AND ACTIONS [Group 1, Configuration 2;

Group 2: ]. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 68

Appendix F – LOGIC DIAGRAM FOR PARAGRAPH 1.E. COMPLIANCE: TABLE 10 WORK PACKAGE

7 AND WORK PACKAGE 8 CONDITIONS AND ACTIONS [Group 1, Configuration 2;

Group 2: ]. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 71

Appendix G – TEST SCREENS [Group 1, Configuration 2; Group 2: ]. . . . . . . . . . . . . . . . . . . . 74

TABLE OF CONTENTS B787-81205-SB270026-00

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B787-81205-SB270026-00

Issue 001, 25 Nov 2014

AIRCRAFT SERVICE BULLETIN
Alert Service Bulletin B787-81205-SB270026-00

List of Illustrations

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

AIRPLANES SHOWN IN DATA MODULE SB B787-A-27-00-0026-00A-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 1-2:

Table 1 List of Illustrations - Alert Service Bulletin B787-81205-SB270026-00

ICN Used In

ICN-B787-A-000061-A-81205-09065-A-01-1 B787-A-27-00-0026-00A-931C-D Issue 001

ICN-B787-A-000061-A-81205-09066-A-01-1 B787-A-27-00-0026-0AA-931D-D Issue 001

ICN-B787-A-000061-A-81205-09067-A-01-1 B787-A-27-00-0026-0BA-931D-D Issue 001

ICN-B787-A-000061-A-81205-09068-A-01-1 B787-A-27-00-0026-0CA-931D-D Issue 001

ICN-B787-A-000061-A-81205-09069-A-01-1 B787-A-27-00-0026-0DA-931D-D Issue 001

ICN-B787-A-000061-A-81205-09070-A-01-1 B787-A-27-00-0026-0EA-931D-D Issue 001

ICN-B787-A-000061-A-81205-09071-A-01-1 B787-A-27-00-0026-0FA-931D-D Issue 001

ICN-B787-A-000061-A-81205-09072-A-01-1 B787-A-27-00-0026-0GA-931D-D Issue 001

ICN-B787-A-000061-A-81205-09073-A-01-1 B787-A-27-00-0026-0GA-931D-D Issue 001

ICN-B787-A-000061-A-81205-09074-A-01-1 B787-A-27-00-0026-0GA-931D-D Issue 001

Applicable To: B787-A-27-00-0026-00A-00AA-D

Model 787 End of data module Issue 001, 25 Nov 2014

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B787-81205-SB270026-00

Issue 001, 25 Nov 2014

AIRCRAFT SERVICE BULLETIN
Alert Service Bulletin B787-81205-SB270026-00

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-27-00-0026-00A-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 1-2:

Table 1 List of Effective Data Modules - Alert Service Bulletin B787-81205-SB270026-00

Data Module – Information Name Issue Issue Status Issue Date

B787-A-27-00-0026-00A-00AA-D – List of Illustrations 001 New 2014-11-25

B787-A-27-00-0026-00A-00SA-D – List of Effective Data Modules 001 New 2014-11-25

B787-A-27-00-0026-00A-931C-D – Summary 001 New 2014-11-25

B787-A-27-00-0026-00A-932A-D – PLANNING INFORMATION 001 New 2014-11-25

B787-A-27-00-0026-00A-934A-D – MATERIAL INFORMATION 001 New 2014-11-25

B787-A-27-00-0026-00A-933A-D – ACCOMPLISHMENT INSTRUCTIONS 001 New 2014-11-25

B787-A-27-00-0026-0AA-931D-D – Appendix A – LOGIC DIAGRAM FOR 001 New 2014-11-25

PARAGRAPH 1.E. COMPLIANCE: TABLE 5 LEFT, RIGHT AND CENTER

HYDRAULIC SYSTEM FLUID MARKER INSTALLATION [Group 1-2:]

B787-A-27-00-0026-0BA-931D-D – Appendix B – LOGIC DIAGRAM FOR 001 New 2014-11-25

PARAGRAPH 1.E. COMPLIANCE: TABLE 6 LEFT HYDRAULIC SYSTEM

FLUID TEST [Group 1, Configuration 2; Group 2: ]

B787-A-27-00-0026-0CA-931D-D – Appendix C – LOGIC DIAGRAM FOR 001 New 2014-11-25

PARAGRAPH 1.E. COMPLIANCE: TABLE 7 RIGHT HYDRAULIC SYSTEM

FLUID TEST [Group 1, Configuration 2; Group 2: ]

B787-A-27-00-0026-0DA-931D-D – Appendix D – LOGIC DIAGRAM FOR 001 New 2014-11-25

PARAGRAPH 1.E. COMPLIANCE: TABLE 8 CENTER HYDRAULIC

SYSTEM FLUID TEST AND LEFT AND RIGHT ELEVATOR AND AILERON

POWER CONTROL UNIT INTERNAL FLOW TEST [Group 1, Configuration

2; Group 2: ]

B787-A-27-00-0026-0EA-931D-D – Appendix E – LOGIC DIAGRAM FOR 001 New 2014-11-25

PARAGRAPH 1.E. COMPLIANCE: TABLE 9 WORK PACKAGE 5 AND

WORK PACKAGE 6 CONDITIONS AND ACTIONS [Group 1, Configuration

2; Group 2: ]

Applicable To: B787-A-27-00-0026-00A-00SA-D

Model 787 Issue 001, 25 Nov 2014

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AIRCRAFT SERVICE BULLETIN
Table 1 List of Effective Data Modules - Alert Service Bulletin B787-81205-SB270026-00

Data Module – Information Name Issue Issue Status Issue Date

B787-A-27-00-0026-0FA-931D-D – Appendix F – LOGIC DIAGRAM FOR 001 New 2014-11-25

PARAGRAPH 1.E. COMPLIANCE: TABLE 10 WORK PACKAGE 7 AND

WORK PACKAGE 8 CONDITIONS AND ACTIONS [Group 1, Configuration

2; Group 2: ]

B787-A-27-00-0026-0GA-931D-D – Appendix G – TEST SCREENS [Group 001 New 2014-11-25

1, Configuration 2; Group 2: ]

Applicable To: B787-A-27-00-0026-00A-00SA-D

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B787-81205-SB270026-00

Issue 001, 25 Nov 2014

AIRCRAFT SERVICE BULLETIN
Alert Service Bulletin B787-81205-SB270026-00

Summary

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

AIRPLANES SHOWN IN DATA MODULE SB B787-A-27-00-0026-00A-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-27-00-0026-00A-932A-D Issue 001, Spares Affected

Paragraph 1.B.

SB B787-A-27-00-0026-00A-932A-D Issue 001, Compliance

Paragraph 5.

SB B787-A-27-00-0026-00A-932A-D Issue 001, Weight and Balance Changes

Paragraph 8.

SB B787-A-27-00-0026-00A-932A-D Issue 001, Electrical Load Data

Paragraph 9.

SB B787-A-27-00-0026-00A-932A-D Issue 001, Publications Affected

Paragraph 11.

SB B787-A-27-00-0026-00A-934A-D Issue 001, Kits/Parts

Paragraph 3.A.

SB B787-A-27-00-0026-00A-934A-D Issue 001, Parts and Materials Supplied by the Operator

Paragraph 3.B.

SB B787-A-27-00-0026-00A-934A-D Issue 001, Special Tooling Necessary to do this Service Bulletin

Paragraph 6.

SB B787-A-27-00-0026-00A-932A-D Issue 001, Effectivity

Paragraph 1.

SB B787-A-27-00-0026-00A-932A-D Issue 001, Manpower

Paragraph 7.

SB B787-A-27-00-0026-00A-934A-D Issue 001, Material - Price and Availability

Paragraph 1.

Applicable To: B787-A-27-00-0026-00A-931C-D

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B787-81205-SB270026-00

Issue 001, 25 Nov 2014

AIRCRAFT SERVICE BULLETIN
Reference Title

HYDRAULIC POWER - Hydraulic System - HyJet V

Marker Installation

SB B787-81205-SB290022-00 Issue 001

FLIGHT CONTROLS - Elevator Control System -

Elevator Power Control Unit Electro-Hydraulic Servo

Valve Rate Restriction Test

SB B787-81205-SB270016-00

Description

Group 1-2:

1. CONCURRENT REQUIREMENTS

Table 1 Boeing Service Bulletins Dependencies

Service Bulletin Issue Description Dependency Type Note

HYDRAULIC POWER - Hydraulic System - Hy- Prerequisite

Jet V Marker Installation

SB B787-81205-SB290022-00

Issue 001, or later approved Issue

2. BACKGROUND

787-8 operators have experienced multiple occurrences of EICAS status message FLIGHT CONTROL SYS

with a correlated Power Control Unit (PCU) internal fault maintenance message. Boeing and Moog (787

actuation system supplier) determined the messages are due to the accumulation of very fine particle deposits

within the PCU's Electro Hydraulic Servo Valve (EHSV) that cause degraded performance due to reduced

EHSV internal hydraulic supply pressures. Failures have only occurred on airplanes that have operated with

Skydrol LD-4 hydraulic fluid. Changing the hydraulic fluid to HyJet V will significantly reduce the rate of

particle deposits in EHSVs. This service bulletin instructs operators to change their hydraulic fluid to HyJet

V and to perform an internal flow test of the left and right elevator and aileron inboard PCUs to make sure

the flow is not restricted. If the PCUs do not pass the test, replace them. If this service bulletin is not accomplished, the particle deposits can cause the flight control hydraulic PCUs to fail, which could lead to reduced

controllability of the airplane.

Accomplishment of this service bulletin terminates SB B787-81205-SB270016-00.

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

Table 2 

Planning Data Affected Data Module Reference

Data Module SB B787-A-27-00-0026-00A-932AD, Paragraph 1.B., Spares AffectedSpares Affected No

Data Module SB B787-A-27-00-0026-00A-932AD, Paragraph 5., ComplianceAD Related Yes

Data Module SB B787-A-27-00-0026-00A-932AD, Paragraph 8., Weight and Balance ChangesWeight and Balance Changed No

Applicable To: B787-A-27-00-0026-00A-931C-D

Model 787 Issue 001, 25 Nov 2014

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AIRCRAFT SERVICE BULLETIN
Table 2 

Planning Data Affected Data Module Reference

Data Module SB B787-A-27-00-0026-00A-932AD, Paragraph 9., Electrical Load DataElectrical Load Changed No

Data Module SB B787-A-27-00-0026-00A-932AD, Paragraph 11., Publications AffectedPublications Affected Yes

Data Module SB B787-A-27-00-0026-00A-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-27-00-0026-00A-934AD, Paragraph 3.A., Kits/PartsKits/Parts Required Yes

Data Module SB B787-A-27-00-0026-00A-934AD, Paragraph 3.B., Parts and Materials Supplied

by the Operator

Operator Supplied Parts/Material Yes

Data Module SB B787-A-27-00-0026-00A-934AD, Paragraph 6., Special Tooling Necessary to

do this Service Bulletin

Special Tooling Required Yes

Boeing Service Related Problem (SRP) 787 SRP-27-0227 is related to this service bulletin.

3. ACTION

(CN-AA40116J)

Do these work packages:

1. WORK PACKAGE 1: MARKER INSTALLATION

Group 1, Configuration 2; Group 2:

2. WORK PACKAGE 2: LEFT HYDRAULIC SYSTEM FLUID TEST

Group 1, Configuration 2; Group 2:

3. WORK PACKAGE 3: RIGHT HYDRAULIC SYSTEM FLUID TEST

Group 1, Configuration 2; Group 2:

4. WORK PACKAGE 4: CENTER HYDRAULIC SYSTEM FLUID TEST AND LEFT AND RIGHT ELEVATOR

AND AILERON POWER CONTROL UNIT INTERNAL FLOW TEST

Group 1-2:

4. EFFECTIVITY

787-8 Airplanes. Refer to Data Module SB B787-A-27-00-0026-00A-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.

Applicable To: B787-A-27-00-0026-00A-931C-D

Model 787 Issue 001, 25 Nov 2014

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B787-81205-SB270026-00

Issue 001, 25 Nov 2014

AIRCRAFT SERVICE BULLETIN
Refer to Data Module SB B787-A-27-00-0026-00A-932A-D, Paragraph 5., Compliance.

6. INDUSTRY SUPPORT INFORMATION

Boeing Industry Support information is provided in Program Letter BPL 6-1151-787-PGM-206, dated August

15, 2014. Additional copies of program letters are available from Boeing Fleet Support Contracts - Warranty.

7. MANPOWER

Refer to Data Module SB B787-A-27-00-0026-00A-932A-D, Paragraph 7., Manpower.

8. MATERIAL INFORMATION

Operator Supplied Parts/Materials.

Refer to Data Module SB B787-A-27-00-0026-00A-934A-D, Paragraph 1., Material - Price and Availability.

ICN-B787-A-000061-A-81205-09065-A-01-1

Figure 1 

Applicable To: B787-A-27-00-0026-00A-931C-D

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B787-81205-SB270026-00

Issue 001, 25 Nov 2014

AIRCRAFT SERVICE BULLETIN
Alert Service Bulletin B787-81205-SB270026-00

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-27-00-0026-00A-933A-D Issue 001, Step 2. Work Instructions

Alert Service Bulletin

B787-81205-SB270026-00 – Appendix A – LOGIC

SB B787-A-27-00-0026-0AA-931D-D Issue 001

DIAGRAM FOR PARAGRAPH 1.E. COMPLIANCE:

TABLE 5 LEFT, RIGHT AND CENTER HYDRAULIC

SYSTEM FLUID MARKER INSTALLATION [Group

1-2:]

Alert Service Bulletin

B787-81205-SB270026-00 – Appendix B – LOGIC

SB B787-A-27-00-0026-0BA-931D-D Issue 001

DIAGRAM FOR PARAGRAPH 1.E. COMPLIANCE:

TABLE 6 LEFT HYDRAULIC SYSTEM FLUID TEST

[Group 1, Configuration 2; Group 2: ]

Alert Service Bulletin

B787-81205-SB270026-00 – Appendix C – LOGIC

SB B787-A-27-00-0026-0CA-931D-D Issue 001

DIAGRAM FOR PARAGRAPH 1.E. COMPLIANCE:

TABLE 7 RIGHT HYDRAULIC SYSTEM FLUID TEST

[Group 1, Configuration 2; Group 2: ]

Alert Service Bulletin

B787-81205-SB270026-00 – Appendix D – LOGIC

SB B787-A-27-00-0026-0DA-931D-D Issue 001

DIAGRAM FOR PARAGRAPH 1.E. COMPLIANCE:

TABLE 8 CENTER HYDRAULIC SYSTEM FLUID

TEST AND LEFT AND RIGHT ELEVATOR AND

AILERON POWER CONTROL UNIT INTERNAL

FLOW TEST [Group 1, Configuration 2; Group 2: ]

Alert Service Bulletin

B787-81205-SB270026-00 – Appendix E – LOGIC

SB B787-A-27-00-0026-0EA-931D-D Issue 001

DIAGRAM FOR PARAGRAPH 1.E. COMPLIANCE:

TABLE 9 WORK PACKAGE 5 AND WORK

Applicable To: B787-A-27-00-0026-00A-932A-D

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B787-81205-SB270026-00

Issue 001, 25 Nov 2014

AIRCRAFT SERVICE BULLETIN
Reference Title

PACKAGE 6 CONDITIONS AND ACTIONS [Group

1, Configuration 2; Group 2: ]

Alert Service Bulletin

B787-81205-SB270026-00 – Appendix F – LOGIC

SB B787-A-27-00-0026-0FA-931D-D Issue 001

DIAGRAM FOR PARAGRAPH 1.E. COMPLIANCE:

TABLE 10 WORK PACKAGE 7 AND WORK

PACKAGE 8 CONDITIONS AND ACTIONS [Group

1, Configuration 2; Group 2: ]

HYDRAULIC POWER - Hydraulic System - HyJet V

Marker Installation

SB B787-81205-SB290022-00 Issue 001

FLIGHT CONTROLS - Elevator Control System -

Elevator Power Control Unit Electro-Hydraulic Servo

Valve Rate Restriction Test

SB B787-81205-SB270016-00

787 AMM 07-11-01 JACKING

787 AMM 12-12-01 HYDRAULIC SYSTEMS

787 AMM 20-10-09 TUBE

787 AMM 27-02-00 PRIMARY FLIGHT CONTROL FUNCTION

787 AMM 27-11-19 AILERON POWER CONTROL UNIT

787 AMM 27-31-09 ELEVATOR POWER CONTROL UNIT

787 AMM 29-11-00 HYDRAULIC SYSTEM

787 AMM 29-21-00 RAM AIR TURBINE SYSTEM

787 AMM 32-00-15 LANDING GEAR DOOR SAFETY

787 AMM 32-00-30 LANDING GEAR DOWNLOCK PINS

CENTRAL MAINTENANCE COMPUTING

FUNCTION

787 AMM 45-11-00

HORIZONTAL STABILIZER TRAILING EDGE SKIN

PANELS

787 AMM 55-16-01

787 AMM 57-51-10 FIXED TRAILING EDGE PANELS

HYDRAULIC POWER - Main - Hydraulic Fluid

Replacement

SB B787-81205-SB290010-00

HYDRAULIC POWER - Hydraulic System - HyJet V

Marker Installation

SB B787-81205-SB290022-00

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B787-81205-SB270026-00

Issue 001, 25 Nov 2014

AIRCRAFT SERVICE BULLETIN
Description

Group 1-2:

1. Effectivity

A. Airplanes

This service bulletin is applicable to 787-8 Airplanes, line numbers 4-9, 20-21 and 23-190 in 2 Group(s).

The Variable Numbers and Group information for the applicable airplanes is given below. An equivalent

change is on subsequent production airplanes. Refer to CN-AA40116 for data about this change.

Table 1 

GROUP CONFIGURATION DESCRIPTION

1 - Airplanes delivered with HyJet V hydraulic fluid.

1 Airplanes that have only been serviced with HyJet V.

Airplanes that have been serviced with hydraulic fluids other than

HyJet V or hydraulic fluid used during system servicing cannot be

determined.

2

2 - Airplanes delivered with Skydrol LD-4.

Airplanes that have accomplished Boeing service bulletin B787-81205-

SB29-0010-00 Issue 001 to replace the hydraulic fluid with HyJet V.

1

Airplanes that have not accomplished Boeing service bulletin B787-

81205-SB29-0010-00 Issue 001 to replace the hydraulic fluid with

HyJet V.

2

Airplane Models: 787-8

Table 2 

Variable Number Group

ZA004-ZA006 1

ZA100-ZA105 2

ZA116-ZA120 2

ZA121-ZA124 1

ZA135 2

ZA136 1

ZA175-ZA176 1

ZA177-ZA185 2

ZA186-ZA189 1

ZA215-ZA220 1

ZA230-ZA232 1

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Table 2 

Variable Number Group

ZA233 2

ZA234-ZA235 1

ZA236-ZA241 2

ZA242-ZA245 1

ZA260 1

ZA261-ZA264 2

ZA265-ZA267 1

ZA270-ZA273 2

ZA274-ZA275 1

ZA285-ZA290 2

ZA291-ZA295 1

ZA317-ZA319 2

ZA320 1

ZA327 1

ZA334 1

ZA380 2

ZA381-ZA383 1

ZA384 2

ZA385-ZA389 1

ZA430 1

ZA431 2

ZA432-ZA437 1

ZA445-ZA448 1

ZA450-ZA451 2

ZA452-ZA456 1

ZA460-ZA465 2

ZA466-ZA474 1

ZA506-ZA513 2

ZA514-ZA516 1

ZA536-ZA538 2

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Table 2 

Variable Number Group

ZA539-ZA541 1

ZA560-ZA565 1

ZA576 2

ZA577-ZA580 1

ZA586 1

ZA588 1

ZA610-ZA612 1

ZA650-ZA651 1

ZA655-ZA656 1

ZA778 1

B. Spares Affected

None.

2. Concurrent Requirements

Table 3 Boeing Service Bulletins Dependencies

Service Bulletin Issue Description Dependency Type Note

HYDRAULIC POWER - Hydraulic System - Hy- Prerequisite

Jet V Marker Installation

SB B787-81205-SB290022-00

Issue 001, or later approved Issue

3. Reason

787-8 operators have experienced multiple occurrences of EICAS status message FLIGHT CONTROL

SYS with a correlated Power Control Unit (PCU) internal fault maintenance message. Boeing and Moog

(787 actuation system supplier) determined the messages are due to the accumulation of very fine particle

deposits within the PCU's Electro Hydraulic Servo Valve (EHSV) that cause degraded performance due

to reduced EHSV internal hydraulic supply pressures. Failures have only occurred on airplanes that have

operated with Skydrol LD-4 hydraulic fluid. Changing the hydraulic fluid to HyJet V will significantly reduce

the rate of particle deposits in EHSVs. This service bulletin instructs operators to change their hydraulic

fluid to HyJet V and to perform an internal flow test of the left and right elevator and aileron inboard PCUs

to make sure the flow is not restricted. If the PCUs do not pass the test, replace them. If this service bulletin

is not accomplished, the particle deposits can cause the flight control hydraulic PCUs to fail, which could

lead to reduced controllability of the airplane.

Accomplishment of this service bulletin terminates SB B787-81205-SB270016-00.

Boeing Service Related Problem (SRP) 787 SRP-27-0227 is related to this service bulletin.

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AIRCRAFT SERVICE BULLETIN
4. Description

Do these work packages:

1. WORK PACKAGE 1: MARKER INSTALLATION

Group 1, Configuration 2; Group 2:

2. WORK PACKAGE 2: LEFT HYDRAULIC SYSTEM FLUID TEST

Group 1, Configuration 2; Group 2:

3. WORK PACKAGE 3: RIGHT HYDRAULIC SYSTEM FLUID TEST

Group 1, Configuration 2; Group 2:

4. WORK PACKAGE 4: CENTER HYDRAULIC SYSTEM FLUID TEST AND LEFT AND RIGHT ELEVATOR

AND AILERON POWER CONTROL UNIT INTERNAL FLOW TEST

Group 1-2:

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

Table 4 

Affected Maintenance Zones

Model Zone

197, 335, 336, 345, 346, 434, 444, 561, 567,

661, 667

787-8

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-27-00-0026-00A-933A-D, Step 2.,

Work Instructions.

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.

Logic diagrams showing compliance tasks and compliance times are included as an aid in Data Module

Appendix A, SB B787-A-27-00-0026-0AA-931D-D, Data Module Appendix B, SB B787-A-27-00-0026-0BA931D-D, Data Module Appendix C, SB B787-A-27-00-0026-0CA-931D-D, Data Module Appendix D, SB

B787-A-27-00-0026-0DA-931D-D, Data Module Appendix E, SB B787-A-27-00-0026-0EA-931D-D and

Data Module Appendix F, SB B787-A-27-00-0026-0FA-931D-D.

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AIRCRAFT SERVICE BULLETIN
Table 5 Left, Right and Center Hydraulic System Fluid Marker Installation

Repeat Interval

(Not to Exceed)

Condition Action Compliance Time

Within 36 months -

after the Issue 001

date of this service

bulletin.

Do WORK PACKAGE 1:

MARKER INSTALLATION.*[1]

*[2]

All Airplanes

*[1] No further action required for Group 1, Configuration 1 after WORK PACKAGE 1 is done. Accomplishment of this service bulletin

terminates SB B787-81205-SB270016-00.

*[2] No further action required for Group 1, Configuration 2 and Group 2 after WORK PACKAGE 1 thru WORK PACKAGE 4 are done.

See Tables 5, 6, 7 and 8. Accomplishment of this service bulletin terminates SB B787-81205-SB270016-00.

Group 1, Configuration 2; Group 2:

Table 6 Left Hydraulic System Fluid Test

Repeat Interval

(Not to Exceed)

Condition Action Compliance Time

Within 36 months -

after the Issue 001

date of this service

bulletin.

Do WORK PACKAGE 2: LEFT

HYDRAULIC SYSTEM FLUID

TEST. *[1]

All Airplanes

No further action required for - -

WORK PACKAGE 2. *[2]

CONDITION 1: PASSES THE

HYDRAULIC FLUID TEST

Within 36 months -

after the Issue 001

date of this service

bulletin.

CONDITION 2 (ACTION 1): Do

PART 4: REPLACE HYDRAULIC FLUID and do PART

2: CYCLE HYDRAULIC FLUID.

CONDITION 2: DOES NOT

PASS THE HYDRAULIC FLUID

TEST

Within 36 months -

after the Issue 001

date of this service

bulletin.*[3]

CONDITION 2 (ACTION 2): Do

PART 3: HYDRAULIC FLUID

TEST until CONDITION 1 is

met.

*[1] It is acceptable to put the airplane back to a serviceable condition and return the airplane to service before the test results are received.

*[2] No further action required for Group 1, Configuration 2 and Group 2 after WORK PACKAGE 1 thru WORK PACKAGE 4 are done.

See Tables 5, 6, 7 and 8. Accomplishment of this service bulletin terminates SB B787-81205-SB270016-00.

*[3] CONDITION 2 (ACTION 2) can be done any time between CONDITION 2 (ACTION 1) and the Compliance Time.

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AIRCRAFT SERVICE BULLETIN
Group 1, Configuration 2; Group 2:

Table 7 Right Hydraulic System Fluid Test

Repeat Interval

(Not to Exceed)

Condition Action Compliance Time

Within 36 months -

after the Issue 001

date of this service

bulletin.

Do WORK PACKAGE 3: RIGHT

HYDRAULIC SYSTEM FLUID

TEST. *[1]

All Airplanes

No further action required for - -

WORK PACKAGE 3. *[2]

CONDITION 3: PASSES THE

HYDRAULIC FLUID TEST

Within 36 months -

after the Issue 001

date of this service

bulletin.

CONDITION 4 (ACTION 1): Do

PART 4: REPLACE HYDRAULIC FLUID and do PART

2: CYCLE HYDRAULIC FLUID.

CONDITION 4: DOES NOT

PASS THE HYDRAULIC FLUID

TEST

Within 36 months -

after the Issue 001

date of this service

bulletin. *[3]

CONDITION 4 (ACTION 2): Do

PART 3: HYDRAULIC FLUID

TEST until CONDITION 3 is

met.

*[1] It is acceptable to put the airplane back to a serviceable condition and return the airplane to service before the test results are received.

*[2] No further action required for Group 1, Configuration 2 and Group 2 after WORK PACKAGE 1 thru WORK PACKAGE 4 are done.

See Tables 5, 6 7 and 8. Accomplishment of this service bulletin terminates SB B787-81205-SB270016-00.

*[3] CONDITION 4 (ACTION 2) can be done any time between CONDITION 4 (ACTION 1) and the Compliance Time.

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AIRCRAFT SERVICE BULLETIN
Group 1, Configuration 2; Group 2:

Table 8 Center Hydraulic System Fluid Test and Left and Right Elevator and Aileron Power Control Unit 

Internal Flow Test

Repeat Interval

(Not to Exceed)

Condition Action Compliance Time

Within 36 months -

after the Issue 001

date of this service

bulletin.

Do WORK PACKAGE 4: CENTER HYDRAULIC SYSTEM

FLUID TEST AND LEFT AND

RIGHT ELEVATOR AND

AILERON POWER CONTROL

UNIT INTERNAL FLOW TEST.

*[1]

All Airplanes

Within 36 months -

after the Issue 001

date of this service

bulletin.

CONDITION 5 (ACTION 1): Do

WORK PACKAGE 5: LEFT ELEVATOR INBOARD POWER

CONTROL UNIT INTERNAL

FLOW TEST. *[3] *[4] *[5]

CONDITION 5: PASSES THE

HYDRAULIC FLUID TEST *[2]

Within 36 months -

after the Issue 001

date of this service

bulletin.

CONDITION 5 (ACTION 2): Do

WORK PACKAGE 6: RIGHT

ELEVATOR INBOARD POWER

CONTROL UNIT INTERNAL

FLOW TEST. *[3] *[4] *[5]

Within 36 months -

after the Issue 001

date of this service

bulletin.

CONDITION 5 (ACTION 3): Do

WORK PACKAGE 7: LEFT

AILERON INBOARD POWER

CONTROL UNIT INTERNAL

FLOW TEST. *[3] *[4] *[6]

Within 36 months

after the Issue 001

date of this service

bulletin.

CONDITION 5 (ACTION 4): Do

WORK PACKAGE 8: RIGHT

AILERON INBOARD POWER

CONTROL UNIT INTERNAL

FLOW TEST. *[3] *[4] *[6]

Within 36 months -

after the Issue 001

date of this service

bulletin.

CONDITION 6 (ACTION 1): Do

PART 4: REPLACE HYDRAULIC FLUID and do PART

2: CYCLE HYDRAULIC FLUID.

CONDITION 6: DOES NOT

PASS THE HYDRAULIC FLUID

TEST

Within 36 months -

after the Issue 001

date of this service

bulletin. *[7]

CONDITION 6 (ACTION 2): Do

PART 3: HYDRAULIC FLUID

TEST until CONDITION 5 is

met.

*[1] It is acceptable to put the airplane back to a serviceable condition and return the airplane to service before the test results are received.

*[2] CONDITION 5 (ACTION 1) thru CONDITION 5 (ACTION 4) can be done in any sequence. It is acceptable to put the airplane back

to a serviceable condition and return the airplane to service after each action independently.

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AIRCRAFT SERVICE BULLETIN
Table 8 Center Hydraulic System Fluid Test and Left and Right Elevator and Aileron Power Control Unit 

Internal Flow Test

Repeat Interval

(Not to Exceed)

Condition Action Compliance Time

*[3] No further action required for WORK PACKAGE 4 after CONDITION 5 (ACTION 1) thru CONDITION 5 (ACTION 4) are done.

*[4] No further action required for Group 1, Configuration 2 and Group 2 after WORK PACKAGE 1 thru WORK PACKAGE 4 are done.

See Tables 5, 6, 7 and 8. Accomplishment of this service bulletin terminates SB B787-81205-SB270016-00.

*[5] See table 9 for disposition of WORK PACKAGE 5 and WORK PACKAGE 6 conditions and actions.

*[6] See table 10 for disposition of WORK PACKAGE 7 and WORK PACKAGE 8 conditions and actions.

*[7] CONDITION 6 (ACTION 2) can be done any time between CONDITION 6 (ACTION 1) and the Compliance Time.

Group 1, Configuration 2; Group 2:

The Conditions, Actions and Compliance times shown in Table 9 apply to each WORK PACKAGE, 5 and

6, independently.

Group 1, Configuration 2; Group 2:

Table 9 WORK PACKAGE 5 and WORK PACKAGE 6 Conditions and Actions

Repeat Interval

(Not to Exceed)

Condition Action Compliance Time

No further action required for - -

the applicable work package.

CONDITION 5.1: THE ELEVATOR INBOARD POWER CONTROL UNIT HAS LESS THAN

300 FLIGHT HOURS IN SERVICE

Within 36 months -

after the Issue 001

date of this service

bulletin.

OPTION 1: Do PART 5: ELEVATOR INBOARD POWER CONTROL UNIT INTERNAL FLOW

TEST.

CONDITION 5.2: THE ELEVATOR INBOARD POWER CONTROL UNIT HAS 300 FLIGHT

HOURS OR MORE IN SERVICE Within 36 months -

after the Issue 001

date of this service

bulletin.

OPTION 2: Do PART 7: REPLACE THE POWER CONTROL UNIT. No further action

required for the applicable work

package.

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Table 9 WORK PACKAGE 5 and WORK PACKAGE 6 Conditions and Actions

Repeat Interval

(Not to Exceed)

Condition Action Compliance Time

No further action required for - -

the applicable work package.

CONDITION 5.2.1: THE INTERNAL FLOW THROUGH THE

ELEVATOR INBOARD POWER

CONTROL UNIT IS GREATER

THAN OR EQUAL TO 0.094

GALLONS PER MINUTE AND

IS LESS THAN OR EQUAL TO

0.560 GALLONS PER MINUTE

Within 36 months -

after the Issue 001

date of this service

bulletin.

Do PART 7: REPLACE THE

POWER CONTROL UNIT. No

further action required for the

applicable work package.

CONDITION 5.2.2: THE INTERNAL FLOW THROUGH THE

ELEVATOR INBOARD POWER

CONTROL UNIT IS LESS

THAN 0.094 GALLONS PER

MINUTE OR IS GREATER

THAN 0.560 GALLONS PER

MINUTE

Group 1, Configuration 2; Group 2:

The Conditions, Actions and Compliance times shown in Table 10 apply to apply to each WORK PACKAGE,

7 and 8, independently.

Group 1, Configuration 2; Group 2:

Table 10 WORK PACKAGE 7 and WORK PACKAGE 8 Conditions and Actions

Repeat Interval

(Not to Exceed)

Condition Action Compliance Time

No further action required for - -

the applicable work package.

CONDITION 5.3: THE

AILERON INBOARD POWER

CONTROL UNIT HAS LESS

THAN 300 FLIGHT HOURS IN

SERVICE

Within 36 months -

after the Issue 001

date of this service

bulletin.

OPTION 3: Do PART 6:

AILERON INBOARD POWER

CONTROL UNIT INTERNAL

FLOW TEST.

CONDITION 5.4: THE

AILERON INBOARD POWER

CONTROL UNIT HAS 300

FLIGHT HOURS OR MORE IN

SERVICE Within 36 months -

after the Issue 001

date of this service

bulletin.

OPTION 4: Do PART 7: REPLACE THE POWER CONTROL UNIT. No further action

required for the applicable work

package.

Applicable To: B787-A-27-00-0026-00A-932A-D

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Table 10 WORK PACKAGE 7 and WORK PACKAGE 8 Conditions and Actions

Repeat Interval

(Not to Exceed)

Condition Action Compliance Time

No further action required for - -

the applicable work package.

CONDITION 5.4.1: THE INTERNAL FLOW THROUGH THE

AILERON INBOARD POWER

CONTROL UNIT IS GREATER

THAN OR EQUAL TO 0.094

GALLONS PER MINUTE AND

IS LESS THAN OR EQUAL TO

0.297 GALLONS PER MINUTE

Within 36 months -

after the Issue 001

date of this service

bulletin.

Do PART 7: REPLACE THE

POWER CONTROL UNIT. No

further action required for the

applicable work package.

CONDITION 5.4.2: THE INTERNAL FLOW THROUGH THE

AILERON INBOARD POWER

CONTROL UNIT IS LESS

THAN 0.094 GALLONS PER

MINUTE OR IS GREATER

THAN 0.297 GALLONS PER

MINUTE

Group 1-2:

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 change 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

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AIRCRAFT SERVICE BULLETIN
Table 11 WORK PACKAGE 1: MARKER INSTALLATION

Task Number of Persons Task Hours Elapsed Hours

Install markers in accordance with *[1] *[1] *[1]

SB B787-81205-SB290022-00 Issue

001 or later approved Issue.

TOTAL FOR EACH AIRPLANE *[1] *[2] *[1] *[2]

*[1] Refer to SB B787-81205-SB290022-00 Issue 001 or later approved issue.

*[2] Task Hours and Elapsed Hours do not include the time to find airplane configuration.

WORK PACKAGE 1 must be done first or at the same time as WORK PACKAGE 2, WORK PACKAGE 3

or WORK PACKAGE 4.

Group 1, Configuration 2; Group 2:

Table 12 WORK PACKAGE 2: LEFT HYDRAULIC SYSTEM FLUID TEST

Task Number of Persons Task Hours Elapsed Hours

4.50 *[1] 13.50 3 *[1] PART 1 *[1]

1.50 *[1] 3.00 2 *[1] PART 2 *[1]

PART 3 2 1.00 0.50

4.50 *[2] 13.50 3 *[2] PART 4 *[2]

TOTAL FOR EACH AIRPLANE 1.00 0.50

*[1] Add Task Hours and Elapsed Hours for Group 2, Configuration 2.

*[2] Add Task Hours and Elapsed Hours for CONDITION 2.

Group 1, Configuration 2; Group 2:

Table 13 WORK PACKAGE 3: RIGHT HYDRAULIC SYSTEM FLUID TEST

Task Number of Persons Task Hours Elapsed Hours

4.50 *[1] 13.50 3 *[1] PART 1 *[1]

1.50 *[1] 3.00 *[1] 2 *[1] PART 2 *[1]

PART 3 2 1.00 0.50

4.50 *[2] 13.50 3 *[2] PART 4 *[2]

TOTAL FOR EACH AIRPLANE 1.00 0.50

*[1] Add Task Hours and Elapsed Hours for Group 2, Configuration 2.

*[2] Add Task Hours and Elapsed Hours for CONDITION 4.

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Group 1, Configuration 2; Group 2:

Table 14 WORK PACKAGE 4: CENTER HYDRAULIC SYSTEM FLUID TEST AND LEFT 

AND RIGHT ELEVATOR AND AILERON POWER CONTROL UNIT INTERNAL FLOW TEST

Task Number of Persons Task Hours Elapsed Hours

5.50 *[1] 16.50 3 *[1] PART 1 *[1]

3.75 *[1] 7.50 2 *[1] PART 2 *[1]

PART 3 2 1.00 0.50

5.50 *[2] 16.50 3 *[2] PART 4 *[2]

*[3] *[3] WORK PACKAGE 5 *[3]

*[3] *[3] WORK PACKAGE 6 *[3]

*[3] *[3] WORK PACKAGE 7 *[3]

*[3] *[3] WORK PACKAGE 8 *[3]

0.50 *[3] 1.00 TOTAL FOR AIRPLANE *[3]

*[1] Add Task Hours and Elapsed Hours for Group 2, Configuration 2.

*[2] Add Task Hours and Elapsed Hours for CONDITION 6.

*[3] See Tables 15 thru 18. Add Task Hours and Elapsed Hours for WORK PACKAGE 5 thru WORK PACKAGE 8.

Group 1, Configuration 2; Group 2:

Table 15 WORK PACKAGE 5: LEFT ELEVATOR INBOARD POWER CONTROL UNIT 

INTERNAL FLOW TEST

Task Number of Persons Task Hours Elapsed Hours

2.00 *[1] 4.00 2 *[1] PART 5 *[1]

14.50 *[2] 29.00 2 *[2] PART 7 *[2]

TOTAL FOR AIRPLANE *[3] *[3]

*[1] Add Task Hours and Elapsed Hours for OPTION 1.

*[2] Add Task Hours and Elapsed Hours for CONDITION 5.2.2 or OPTION 2.

*[3] Task Hours and Elapsed Hours do not include the time to find power control unit time in service.

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Group 1, Configuration 2; Group 2:

Table 16 WORK PACKAGE 6: RIGHT ELEVATOR INBOARD POWER CONTROL UNIT 

INTERNAL FLOW TEST

Task Number of Persons Task Hours Elapsed Hours

2.00 *[1] 4.00 2 *[1] PART 5 *[1]

14.50 *[2] 29.00 2 *[2] PART 7 *[2]

TOTAL FOR AIRPLANE *[3] *[3]

*[1] Add Task Hours and Elapsed Hours for OPTION 1.

*[2] Add Task Hours and Elapsed Hours for CONDITION 5.2.2 or OPTION 2.

*[3] Task Hours and Elapsed Hours do not include the time to find power control unit time in service.

Group 1, Configuration 2; Group 2:

Table 17 WORK PACKAGE 7: LEFT AILERON INBOARD POWER CONTROL UNIT INTERNAL

 FLOW TEST

Task Number of Persons Task Hours Elapsed Hours

2.00 *[1] 4.00 2 *[1] PART 6 *[1]

14.50 *[2] 29.00 2 *[2] PART 7 *[2]

TOTAL FOR AIRPLANE *[3] *[3]

*[1] Add Task Hours and Elapsed Hours for OPTION 3.

*[2] Add Task Hours and Elapsed Hours for CONDITION 5.4.2 or OPTION 4.

*[3] Task Hours and Elapsed Hours do not include the time to find power control unit time in service.

Group 1, Configuration 2; Group 2:

Table 18 WORK PACKAGE 8: RIGHT AILERON INBOARD POWER CONTROL UNIT 

INTERNAL FLOW TEST

Task Number of Persons Task Hours Elapsed Hours

2.00 *[1] 4.00 2 *[1] PART 6 *[1]

14.50 *[2] 29.00 2 *[2] PART 7 *[2]

TOTAL FOR AIRPLANE *[3] *[3]

*[1] Add Task Hours and Elapsed Hours for OPTION 3.

*[2] Add Task Hours and Elapsed Hours for CONDITION 5.4.2 or OPTION 4.

*[3] Task Hours and Elapsed Hours do not include the time to find power control unit time in service.

Group 1-2:

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-AA40116J

2. Aircraft Maintenance Manual (AMM) 787 AMM 07-11-01, 787 AMM 12-12-01, 787 AMM 20-10-

09, 787 AMM 27-02-00, 787 AMM 27-11-19, 787 AMM 27-31-09, 787 AMM 29-11-00, 787 AMM

29-21-00, 787 AMM 32-00-15, 787 AMM 32-00-30, 787 AMM 45-11-00, 787 AMM 55-16-01, 787

AMM 57-51-10

3. Boeing Program Letter (BPL) BPL 6-1151-787-PGM-206, dated August 15, 2014

4. Boeing Service Bulletin (SB) SB B787-81205-SB270016-00, SB B787-81205-SB290010-00, SB

B787-81205-SB290022-00

5. Boeing Service Related Problem (SRP) 787 SRP-27-0227

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 19 

Publication Chapter-Section

12-12, 20-10, 27-51, 27-81, 29-11, 29-18,

29-21, 29-31, 29-32, 32-32, 32-34, 32-35,

32-51, 54-64, G71-00, G78-31, G78-34,

R78-31, R78-34

787 Maintenance Manual

787 Fault Isolation Manual 27-10

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-SB270026-00

MATERIAL INFORMATION

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

AIRPLANES SHOWN IN DATA MODULE SB B787-A-27-00-0026-00A-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-27-00-0026-00A-932A-D Issue 001, References

Paragraph 10.

Description

Group 1-2:

1. Material - Price and Availability

The operator can supply the parts and materials shown in Paragraph 3., 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.

2. Industry Support Information

Boeing Industry Support information is provided in Program Letter BPL 6-1151-787-PGM-206, dated August

15, 2014. Additional copies of program letters are available from Boeing Fleet Support Contracts - Warranty.

3. Parts Necessary for Each Airplane

A. Kits/Parts:

None.

B. Parts and Materials Supplied by the Operator:

Table 1 

Part Number / QTY Name Notes

Specification

Group 1, Configuration 2

and Group 2 only. *[1]

350 gal- Hydraulic Fluid

lons

HyJet V

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Table 1 

Part Number / QTY Name Notes

Specification

*[1] ExxonMobil Oil Corporation.

Address:

Anderol Specialty Lubricants, a Division of Chemtura

215 Merry Lane

East Hanover, NJ 07936

For procurement, contact ExxonMobil Oil Corporation.

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

Boeing can supply the tool(s) shown in Paragraph 6., Special Tooling Necessary to do this Service Bulletin.

Operators are encouraged to share schedule requirements with Boeing for incorporation of the service bulletin

by e-mail to ServiceBulletinRentalLoanTools@boeing.com. The tool(s) are subject to the terms and conditions

of the Boeing standard purchase order acknowledgement. Prices are in United States Dollars. Terms: Net

30 days.

Reference this service bulletin number and submit purchase order by one of the methods:

1. Order on-line via ATA Spec 2000 or Boeing Part Page

2. Fax to (206) 662-8237

Table 2 Rental Data:

Daily Price as of

the Issue 001

date of this Service Bulletin (US

Dollars)

Tool Kit Number Name

HYDRAULIC FLUID CHECK $340.00

TOOL TSF036Z0229 *[1]

*[1] Group 1, Configuration 2 and Group 2 only.

6. Special Tooling Necessary to do this Service Bulletin

To get the tools shown below, refer to Paragraph 5., Special Tooling - Price and Availability. Maintenance

and overhaul tools in the manuals given in Data Module SB B787-A-27-00-0026-00A-932A-D, Paragraph

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

available.

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Table 3 

Tool Kit Number Name

HYDRAULIC FLUID CHECK

TOOL TSF036Z0229 *[1]

*[1] Group 1, Configuration 2 and Group 2 only.

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Alert Service Bulletin B787-81205-SB270026-00

ACCOMPLISHMENT INSTRUCTIONS

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

AIRPLANES SHOWN IN DATA MODULE SB B787-A-27-00-0026-00A-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-27-00-0026-00A-932A-D Issue 001, References

Paragraph 10.

SB B787-A-27-00-0026-00A-932A-D Issue 001, Manpower

Paragraph 7.

SB B787-A-27-00-0026-00A-932A-D Issue 001, Compliance

Paragraph 5.

Alert Service Bulletin

B787-81205-SB270026-00 – Appendix G – TEST

SCREENS [Group 1, Configuration 2; Group 2: ]

SB B787-A-27-00-0026-0GA-931D-D Issue 001

HYDRAULIC POWER - Hydraulic System - HyJet V

Marker Installation

SB B787-81205-SB290022-00 Issue 001

787 AMM 29-11-00 HYDRAULIC SYSTEM

787 AMM 07-11-01 JACKING

787 AMM 29-21-00 RAM AIR TURBINE SYSTEM

787 AMM 32-00-30 LANDING GEAR DOWNLOCK PINS

787 AMM 32-00-15 LANDING GEAR DOOR SAFETY

787 AMM 12-12-01 HYDRAULIC SYSTEMS

787 AMM 27-02-00 PRIMARY FLIGHT CONTROL FUNCTION

HORIZONTAL STABILIZER TRAILING EDGE SKIN

PANELS

787 AMM 55-16-01

787 AMM 20-10-09 TUBE

CENTRAL MAINTENANCE COMPUTING

FUNCTION

787 AMM 45-11-00

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Reference Title

787 AMM 57-51-10 FIXED TRAILING EDGE PANELS

787 AMM 27-11-19 AILERON POWER CONTROL UNIT

787 AMM 27-31-09 ELEVATOR POWER CONTROL UNIT

Procedure

Group 1-2:

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-27-00-0026-00A932A-D, Paragraph 10., References, for definition of the acronyms.

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

3. The work instructions are divided into work packages. Task Hours and Elapsed Hours for each

package are given in Data Module SB B787-A-27-00-0026-00A-932A-D, Paragraph 7., Manpower.

You can do each work package independently. WORK PACKAGE 1 must be done first or at

the same time as WORK PACKAGE 2, WORK PACKAGE 3 or WORK PACKAGE 4.

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

– Linear dimensions are in inches

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

0.03 inch

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

– 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 Aircraft 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 Aircraft Maintenance Manual (AMM).

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

5. Use the approved fastener, process and material substitutions in accordance with SRM Chapter

51.

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6. A Detailed Inspection is defined as: An intensive examination of a specific item, installation, or

assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented

with a direct source of good lighting at an intensity deemed appropriate. Inspection aids such

as mirrors, magnifying lenses, etc. may be necessary. Surface cleaning and elaborate procedures

may be required.

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.

8. The instructions in Step 2., Work Instructions and the Tasks can include operation of tools or

test equipment. Boeing Engineering Tool Drawings, the Illustrated Tool and Equipment Manual,

and the Special Tool and Ground Handling Drawing Index contain data on versions of the tools

or test equipment that you can use. It is permitted to use replaced tools. It is not permitted to

use superseded tools.

9. 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.

10. 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.

11. 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.

12. Refer to Appendix A , Appendix B, Appendix C, Appendix D, Appendix E and Appendix F for

logic diagrams(s). Logic diagrams are provided as an aid only. Information contained in Data

Module SB B787-A-27-00-0026-00A-932A-D, Paragraph 5., Compliance, is the primary source

for compliance times. Information in Step 2., Work Instructions, is the primary source for tasks

required for compliance.

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

technical publications.

14. 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.

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

A-27-00-0026-00A-932A-D, Paragraph 5., Compliance.

16. The CONDITIONS, ACTIONS and OPTIONS shown apply to each WORK PACKAGE, 5 and

6, independently.

17. The CONDITIONS, ACTIONS and OPTIONS shown apply to each WORK PACKAGE, 7 and

8, independently.

18. 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

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

serviceable condition. An Alternative Method of Compliance (AMOC) is not necessary for deviations to steps that are not identified as RC.

2. WORK INSTRUCTIONS

A. WORK PACKAGE 1: MARKER INSTALLATION

RC - Install markers in accordance with SB B787-81205-SB290022-00 Issue 001 or later approved

issue.

(1)

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

Group 1, Configuration 2; Group 2:

B. WORK PACKAGE 2: LEFT HYDRAULIC SYSTEM FLUID TEST

Group 2, Configuration 2:

(1) Do PART 1: INITIAL HYDRAULIC FLUID REPLACEMENT and do PART 2: CYCLE HYDRAULIC

FLUID.

Group 1, Configuration 2; Group 2:

(2) Do PART 3: HYDRAULIC FLUID TEST. Boeing will provide the test results to the operator through

the Boeing Communication System. It is acceptable to put the airplane back to a serviceable condition

and return the airplane to service before the test results are received.

(a) CONDITION 1: PASSES THE HYDRAULIC FLUID TEST

1) No further action required for WORK PACKAGE 2.

(b) CONDITION 2: DOES NOT PASS THE HYDRAULIC FLUID TEST

1) CONDITION 2 (ACTION 1): Do PART 4: REPLACE HYDRAULIC FLUID and do PART 2:

CYCLE HYDRAULIC FLUID.

2) CONDITION 2 (ACTION 2): Do PART 3: HYDRAULIC FLUID TEST until CONDITION 1

is met.

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

Group 1, Configuration 2; Group 2:

C. WORK PACKAGE 3: RIGHT HYDRAULIC SYSTEM FLUID TEST

Group 2, Configuration 2:

(1) Do PART 1: INITIAL HYDRAULIC FLUID REPLACEMENT and do PART 2: CYCLE HYDRAULIC

FLUID.

Group 1, Configuration 2; Group 2:

(2) Do PART 3: HYDRAULIC FLUID TEST. Boeing will provide the test results to the operator through

the Boeing Communication System. It is acceptable to put the airplane back to a serviceable condition

and return the airplane to service before the test results are received.

(a) CONDITION 3: PASSES THE HYDRAULIC FLUID TEST

1) No further action required for WORK PACKAGE 3.

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(b) CONDITION 4: DOES NOT PASS THE HYDRAULIC FLUID TEST

1) CONDITION 4 (ACTION 1): Do PART 4: REPLACE HYDRAULIC FLUID and do PART 2:

CYCLE HYDRAULIC FLUID.

2) CONDITION 4 (ACTION 2): Do PART 3: HYDRAULIC FLUID TEST until CONDITION 3

is met.

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

Group 1, Configuration 2; Group 2:

D. WORK PACKAGE 4: CENTER HYDRAULIC SYSTEM FLUID TEST AND LEFT AND RIGHT ELEVATOR

AND AILERON POWER CONTROL UNIT INTERNAL FLOW TEST

Group 2, Configuration 2:

(1) Do PART 1: INITIAL HYDRAULIC FLUID REPLACEMENT and do PART 2: CYCLE HYDRAULIC

FLUID.

Group 1, Configuration 2; Group 2:

(2) Do PART 3: HYDRAULIC FLUID TEST. Boeing will provide the test results to the operator through

the Boeing Communication System. It is acceptable to put the airplane back to a serviceable condition

and return the airplane to service before the test results are received.

(a) CONDITION 5: PASSES THE HYDRAULIC FLUID TEST

CONDITION 5 (ACTION 1) thru CONDITION 5 (ACTION 4) can be done in any sequence. It is

acceptable to put the airplane back to a serviceable condition and return the airplane to service

after each action independently.

1) CONDITION 5 (ACTION 1): Do WORK PACKAGE 5: LEFT ELEVATOR INBOARD POWER

CONTROL UNIT INTERNAL FLOW TEST.

2) CONDITION 5 (ACTION 2): Do WORK PACKAGE 6: RIGHT ELEVATOR INBOARD

POWER CONTROL UNIT INTERNAL FLOW TEST.

3) CONDITION 5 (ACTION 3): Do WORK PACKAGE 7: LEFT AILERON INBOARD POWER

CONTROL UNIT INTERNAL FLOW TEST.

4) CONDITION 5 (ACTION 4): Do WORK PACKAGE 8: RIGHT AILERON INBOARD POWER

CONTROL UNIT INTERNAL FLOW TEST.

5) No further action required for WORK PACKAGE 4 after CONDITION 5 (ACTION 1) thru

CONDITION 5 (ACTION 4) are done.

(b) CONDITION 6: DOES NOT PASS THE HYDRAULIC FLUID TEST

1) CONDITION 6 (ACTION 1): Do PART 4: REPLACE HYDRAULIC FLUID and do PART 2:

CYCLE HYDRAULIC FLUID.

2) CONDITION 6 (ACTION 2): Do PART 3: HYDRAULIC FLUID TEST until CONDITION 5

is met.

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

Group 1, Configuration 2; Group 2:

E. WORK PACKAGE 5: LEFT ELEVATOR INBOARD POWER CONTROL UNIT INTERNAL FLOW TEST

(1) Check maintenance records to find the left elevator inboard power control unit time in service.

(a) CONDITION 5.1: THE ELEVATOR INBOARD POWER CONTROL UNIT HAS LESS THAN

300 FLIGHT HOURS IN SERVICE

1) No further action required for WORK PACKAGE 5.

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(b) CONDITION 5.2: THE ELEVATOR INBOARD POWER CONTROL UNIT HAS 300 FLIGHT

HOURS OR MORE IN SERVICE

1) Do one of these options:

a) OPTION 1:

Do PART 5: ELEVATOR INBOARD POWER CONTROL UNIT INTERNAL FLOW TEST.

<1> CONDITION 5.2.1: THE INTERNAL FLOW THROUGH THE ELEVATOR

INBOARD POWER CONTROL UNIT IS GREATER THAN OR EQUAL TO 0.094

GALLONS PER MINUTE AND IS LESS THAN OR EQUAL TO 0.560 GALLONS

PER MINUTE

<a> No further action required for WORK PACKAGE 5.

<2> CONDITION 5.2.2: THE INTERNAL FLOW THROUGH THE ELEVATOR

INBOARD POWER CONTROL UNIT IS LESS THAN 0.094 GALLONS PER

MINUTE OR IS GREATER THAN 0.560 GALLONS PER MINUTE

<a> Do PART 7: REPLACE THE POWER CONTROL UNIT.

<b> No further action required for WORK PACKAGE 5.

b) OPTION 2:

Do PART 7: REPLACE THE POWER CONTROL UNIT.

<1> No further action required for WORK PACKAGE 5.

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

Group 1, Configuration 2; Group 2:

F. WORK PACKAGE 6: RIGHT ELEVATOR INBOARD POWER CONTROL UNIT INTERNAL FLOW

TEST

(1) Check maintenance records to find the right elevator inboard power control unit time in service.

(a) CONDITION 5.1: THE ELEVATOR INBOARD POWER CONTROL UNIT HAS LESS THAN

300 FLIGHT HOURS IN SERVICE

1) No further action required for WORK PACKAGE 6.

(b) CONDITION 5.2: THE ELEVATOR INBOARD POWER CONTROL UNIT HAS 300 FLIGHT

HOURS OR MORE IN SERVICE

1) Do one of these options:

a) OPTION 1:

Do PART 5: ELEVATOR INBOARD POWER CONTROL UNIT INTERNAL FLOW TEST.

<1> CONDITION 5.2.1: THE INTERNAL FLOW THROUGH THE ELEVATOR

INBOARD POWER CONTROL UNIT IS GREATER THAN OR EQUAL TO 0.094

GALLONS PER MINUTE AND IS LESS THAN OR EQUAL TO 0.560 GALLONS

PER MINUTE

<a> No further action required for WORK PACKAGE 6.

<2> CONDITION 5.2.2: THE INTERNAL FLOW THROUGH THE ELEVATOR

INBOARD POWER CONTROL UNIT IS LESS THAN 0.094 GALLONS PER

MINUTE OR IS GREATER THAN 0.560 GALLONS PER MINUTE

<a> Do PART 7: REPLACE THE POWER CONTROL UNIT.

<b> No further action required for WORK PACKAGE 6.

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b) OPTION 2:

Do PART 7: REPLACE THE POWER CONTROL UNIT.

<1> No further action required for WORK PACKAGE 6.

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

Group 1, Configuration 2; Group 2:

G. WORK PACKAGE 7: LEFT AILERON INBOARD POWER CONTROL UNIT INTERNAL FLOW TEST

(1) Check maintenance records to find the left aileron inboard power control unit time in service.

(a) CONDITION 5.3: THE AILERON INBOARD POWER CONTROL UNIT HAS LESS THAN 300

FLIGHT HOURS IN SERVICE

1) No further action required for WORK PACKAGE 7.

(b) CONDITION 5.4: THE AILERON INBOARD POWER CONTROL UNIT HAS 300 FLIGHT

HOURS OR MORE IN SERVICE

1) Do one of these options:

a) OPTION 3:

Do PART 6: AILERON INBOARD POWER CONTROL UNIT INTERNAL FLOW TEST.

<1> CONDITION 5.4.1: THE INTERNAL FLOW THROUGH THE AILERON INBOARD

POWER CONTROL UNIT IS GREATER THAN OR EQUAL TO 0.094 GALLONS

PER MINUTE AND IS LESS THAN OR EQUAL TO 0.297 GALLONS PER MINUTE

<a> No further action required for WORK PACKAGE 7.

<2> CONDITION 5.4.2: THE INTERNAL FLOW THROUGH THE AILERON INBOARD

POWER CONTROL UNIT IS LESS THAN 0.094 GALLONS PER MINUTE OR IS

GREATER THAN 0.297 GALLONS PER MINUTE

<a> Do PART 7: REPLACE THE POWER CONTROL UNIT.

<b> No further action required for WORK PACKAGE 7.

b) OPTION 4:

Do PART 7: REPLACE THE POWER CONTROL UNIT.

<1> No further action required for WORK PACKAGE 7.

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

Group 1, Configuration 2; Group 2:

H. WORK PACKAGE 8: RIGHT AILERON INBOARD POWER CONTROL UNIT INTERNAL FLOW TEST

(1) Check maintenance records to find the right aileron inboard power control unit time in service.

(a) CONDITION 5.3: THE AILERON INBOARD POWER CONTROL UNIT HAS LESS THAN 300

FLIGHT HOURS IN SERVICE

1) No further action required for WORK PACKAGE 8.

(b) CONDITION 5.4: THE AILERON INBOARD POWER CONTROL UNIT HAS 300 FLIGHT

HOURS OR MORE IN SERVICE

1) Do one of these options:

a) OPTION 3:

Do PART 6: AILERON INBOARD POWER CONTROL UNIT INTERNAL FLOW TEST.

Applicable To: B787-A-27-00-0026-00A-933A-D

Model 787 Issue 001, 25 Nov 2014

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<1> CONDITION 5.4.1: THE INTERNAL FLOW THROUGH THE AILERON INBOARD

POWER CONTROL UNIT IS GREATER THAN OR EQUAL TO 0.094 GALLONS

PER MINUTE AND IS LESS THAN OR EQUAL TO 0.297 GALLONS PER MINUTE

<a> No further action required for WORK PACKAGE 8.

<2> CONDITION 5.4.2: THE INTERNAL FLOW THROUGH THE AILERON INBOARD

POWER CONTROL UNIT IS LESS THAN 0.094 GALLONS PER MINUTE OR IS

GREATER THAN 0.297 GALLONS PER MINUTE

<a> Do PART 7: REPLACE THE POWER CONTROL UNIT.

<b> No further action required for WORK PACKAGE 8.

b) OPTION 4:

Do PART 7: REPLACE THE POWER CONTROL UNIT.

<1> No further action required for WORK PACKAGE 8.

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

Group 2, Configuration 2:

I. PART 1: INITIAL HYDRAULIC FLUID REPLACEMENT

RC - Replace the hydraulic fluid with HyJet V. Refer to 787 AMM 29-11-00 Hydraulic System Fluid

- Replacement as an accepted procedure.

(1)

(a) For WORK PACKAGE 2: Do the left hydraulic system.

(b) For WORK PACKAGE 3: Do the right hydraulic system.

(c) For WORK PACKAGE 4: Do the center hydraulic system. Leave the airplane on jacks after replacing the hydraulic fluid.

Group 2, Configuration 2:

J. PART 2: CYCLE HYDRAULIC FLUID

(1) Do these steps to cycle the hydraulic fluid :

(a) For WORK PACKAGE 2 and WORK PACKAGE 3: Do one of these options:

1) OPTION 5: Put the airplane back to a serviceable condition and fly 1 or more flight cycles.

2) OPTION 6: Do these steps to operate the flight surfaces and thrust reversers:

a) Make sure all hydraulic carts are disconnected.

b) Make sure that these circuit breakers are closed on the circuit breaker indication and

control (CBIC) panel:

Table 1 WORK PACKAGE 2:

Designation CB

AIL REU LOB PWR CE2711305

AUTO SPDBRK ACT CTRLR PWR CE2761413

ELEV REU LOB PWR CE2731307

FLAPERON REU LIB PWR CE2711206

FLAPERON REU ROB PWR CE2711306

Applicable To: B787-A-27-00-0026-00A-933A-D

Model 787 Issue 001, 25 Nov 2014

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Table 1 WORK PACKAGE 2:

Designation CB

RUD REU MID PWR CE2721308

T/R DIRECTIONAL CTRL VLV-L ENGINE CE7834811

T/R LEVEL INTLK-L ENGINE CE7834813

T/R TRK LOCK VLV-L ENGINE CE7834814

Table 2 WORK PACKAGE 3:

Designation CB

AIL REU ROB PWR CE2711405

AUTO SPDBRK ACT CTRLR PWR CE2761413

ELEV REU ROB PWR CE2731407

FLAPERON REU LOB PWR CE2711406

RUD REU LWR PWR CE2721408

T/R DIRECTIONAL CTRL VLV-R ENGINE CE7834821

T/R LEVEL INTLK-R ENGINE CE7834823

T/R TRK LOCK VLV-R ENGINE CE7834824

c) Pressurize the hydraulic system with the engine-driven pump (EDP). For WORK

PACKAGE 2, do the left EDP. For WORK PACKAGE 3, do the right EDP. Refer to 787

AMM 29-11-00 Hydraulic System (with an Engine-Driven Pump) - Pressurization as an

accepted procedure.

WARNING: KEEP ALL PERSONS AND EQUIPMENT AWAY FROM THE FLIGHT CONTROL SURFACES AND THE FLIGHT CONTROL DRIVE MECHANISMS.

THESE COMPONENTS WILL MOVE. THIS CAN CAUSE INJURIES TO

PERSONS AND DAMAGE TO EQUIPMENT.

d) RC - Operate the elevator with the EDP. Do these steps 3 times:

<1> Use the flight controls synoptic page to make sure that the elevator moves fully.

<2> Push the control column fully forward.

<3> Push the control column fully aft.

<4> Push the control column to the neutral position.

e) Pressurize the hydraulic system with an electric motor pump (EMP). For WORK PACKAGE 2, do the left EMP. For WORK PACKAGE 3, do the right EMP. Refer to 787 AMM

29-11-00 Hydraulic System (with an Electric Motor Pump) - Pressurization as an accepted

procedure.

Applicable To: B787-A-27-00-0026-00A-933A-D

Model 787 Issue 001, 25 Nov 2014

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WARNING: KEEP ALL PERSONS AND EQUIPMENT AWAY FROM THE FLIGHT CONTROL SURFACES AND THE FLIGHT CONTROL DRIVE MECHANISMS.

THESE COMPONENTS WILL MOVE. THIS CAN CAUSE INJURIES TO

PERSONS AND DAMAGE TO EQUIPMENT.

f) RC - Operate the elevator with the EMP. Do these steps 9 times:

<1> Use the flight controls synoptic page to make sure that the elevator moves fully.

<2> Push the control column fully forward.

<3> Push the control column fully aft.

<4> Push the control column to the neutral position.

WARNING: KEEP ALL PERSONS AND EQUIPMENT AWAY FROM THE FLIGHT CONTROL SURFACES AND THE FLIGHT CONTROL DRIVE MECHANISMS.

THESE COMPONENTS WILL MOVE. THIS CAN CAUSE INJURIES TO

PERSONS AND DAMAGE TO EQUIPMENT.

g) RC - Operate the rudder with the EMP. Do these steps 15 times:

<1> Use the flight controls synoptic page to make sure that the rudder moves fully.

<2> Push the right rudder pedal fully forward.

<3> Push the left rudder pedal fully forward.

<4> Let the rudder pedals move to the neutral position.

WARNING: KEEP ALL PERSONS AND EQUIPMENT AWAY FROM THE FLIGHT CONTROL SURFACES AND THE FLIGHT CONTROL DRIVE MECHANISMS.

THESE COMPONENTS WILL MOVE. THIS CAN CAUSE INJURIES TO

PERSONS AND DAMAGE TO EQUIPMENT.

h) RC - Operate the flaperons with the EMP. Do these steps 5 times:

<1> Use the flight controls synoptic page to make sure that the flaperons moves fully.

<2> Turn the control wheel from the neutral position to fully right.

<3> Turn the control wheel from fully right to fully left.

<4> Turn the control wheel from fully left to the neutral position.

WARNING: KEEP ALL PERSONS AND EQUIPMENT AWAY FROM THE FLIGHT CONTROL SURFACES AND THE FLIGHT CONTROL DRIVE MECHANISMS.

THESE COMPONENTS WILL MOVE. THIS CAN CAUSE INJURIES TO

PERSONS AND DAMAGE TO EQUIPMENT.

i) RC - Operate the spoilers with the EMP. Do these steps 11 times:

<1> Use the flight controls synoptic page to make sure that the spoilers moves fully.

<2> Move the speedbrake lever from the DOWN position to the UP position.

<3> Move the speedbrake lever from the UP position to the DOWN position.

Applicable To: B787-A-27-00-0026-00A-933A-D

Model 787 Issue 001, 25 Nov 2014

See Applicability of this data module

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AIRCRAFT SERVICE BULLETIN
WARNING: KEEP ALL PERSONS AND EQUIPMENT AWAY FROM THE FLIGHT CONTROL SURFACES AND THE FLIGHT CONTROL DRIVE MECHANISMS.

THESE COMPONENTS WILL MOVE. THIS CAN CAUSE INJURIES TO

PERSONS AND DAMAGE TO EQUIPMENT.

j) RC - Operate the ailerons with the EMP. Do these steps 15 times:

<1> Use the flight controls synoptic page to make sure that the ailerons moves fully.

<2> Turn the control wheel from the neutral position to fully right.

<3> Turn the control wheel from fully right to fully left.

<4> Turn the control wheel from fully left to the neutral position.

k) To operate the thrust reverser, have one person push and hold the TEST ENABLE switch

in the TEST position.

NOTE: The TEST ENABLE switch is at the 7 o'clock position on the aft bulkhead of

the inlet cowl. 

NOTE: If your release the test enable switch, it will cause the EEC to immediately close

the isolation valve and stop the movement of the translating sleeves. No

movement of the translating sleeves can occur unless you push and hold the

test enable switch. 

WARNING: KEEP ALL PERSONNEL AND EQUIPMENT AWAY FROM THE AREA THAT

IS AFT OF THE APPLICABLE THRUST REVERSER. IF YOU IGNORE THIS

INSTRUCTION, INJURIES TO PERSONNEL AND DAMAGE TO EQUIPMENT

CAN OCCUR WHEN THE THRUST REVERSER EXTENDS.

WARNING: MAKE SURE THAT THE AREA AROUND THE SPOILERS IS CLEAR OF

PERSONS AND EQUIPMENT. THE SPOILERS CAN MOVE QUICKLY. THIS

CAN CAUSE INJURIES TO PERSONS OR DAMAGE TO EQUIPMENT.

CAUTION: DO NOT OPEN THE THRUST REVERSER IF THE TRANSLATING SLEEVES

ARE EXTENDED. THE EXTENDED SLEEVES CAN HIT THE STRUT PANELS. DAMAGE TO EQUIPMENT CAN OCCUR.

CAUTION: DO NOT EXTEND THE THRUST REVERSER SLEEVE IF THE THRUST

REVERSER IS OPEN. DAMAGE TO THE THRUST REVERSER AND ADJACENT STRUCTURES CAN OCCUR.

l) RC - Operate the thrust reverser with the EMP. Do these steps 4 times:

<1> Make sure that the thrust reversers deploy and stow fully.

<2> While one person holds the TEST ENABLE switch, move the left reverse thrust

lever up and aft until it engages the interlock stop.

NOTE: The extend time of the translating sleeves is 3 seconds. 

<3> While one person holds the TEST ENABLE switch, move the left reverse thrust

lever forward and down to the retract position.

Applicable To: B787-A-27-00-0026-00A-933A-D

Model 787 Issue 001, 25 Nov 2014

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NOTE: The retract time of the translating sleeves is less than 8 seconds. 

<a> Hold the TEST ENABLE switch until 12 to 15 seconds after the translating

sleeves retract fully

(b) For WORK PACKAGE 4: Do one of these options:

1) OPTION 7: Do these steps to fly 1 or more flight cycles:

a) Lower the airplane from jacks. Refer to 787 AMM 07-11-01 Lift the Airplane on Jacks -

Handling as an accepted procedure

b) Put the airplane back to a serviceable condition and fly 1 or more flight cycles.

2) OPTION 8: Do these steps to operate the flight surfaces, ram air turbine (RAT) and landing

gear:

a) Make sure all hydraulic carts are disconnected.

b) Make sure that these circuit breakers are closed on the circuit breaker indication and

control (CBIC) panel:

Table 3 WORK PACKAGE 4:

Designation CB

MLG BYPASS VLV-ENABLE 1 CE3231801

MLG BYPASS VLV-ENABLE 2 CE3231802

NLG BYPASS VLV-ENABLE 1 CE3231803

NLG BYPASS VLV-ENABLE 2 CE3231804

AIL REU LIB PWR CE2711106

AIL REU RIB PWR CE2711205

AUTO SPDBRK ACT CTRLR PWR CE2761413

ELEV REU LIB PWR CE2731108

ELEV REU RIB PWR CE2731207

FLAPERON REU RIB PWR CE2711107

RUD REU UPR PWR CE2721109

ELECT ACTR-SPLR 10 CK2761501

ELECT ACTR-SPLR 11 CK2761503

ELECT ACTR-SPLR 4 CK2761504

ELECT ACTR-SPLR 5 CK2761502

ALTN EXTEND ISLN VLV CLOSE-1 CE2911831

ALTN EXTEND ISLN VLV CLOSE-2 CE2911832

HYD ISLN VLV-NLG OPEN 1 CE2911819

HYD ISLN VLV-NLG OPEN 2 CE2911820

Applicable To: B787-A-27-00-0026-00A-933A-D

Model 787 Issue 001, 25 Nov 2014

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AIRCRAFT SERVICE BULLETIN
c) Pressurize the hydraulic system with the C2 electric motor pump (EMP). Refer to 787

AMM 29-11-00 Hydraulic System (with an Electric Motor Pump) - Pressurization as an

accepted procedure.

d) RC - Do these steps to operate the elevator with the C2 EMP:

<1> Use the flight controls synoptic page to make sure that the elevator moves fully.

<2> Push the control column fully forward.

<3> Push the control column fully aft.

<4> Push the control column to the neutral position.

e) Pressurize the hydraulic system with the C1 EMP. Refer to 787 AMM 29-11-00 Hydraulic

System (with an Electric Motor Pump) - Pressurization as an accepted procedure.

f) RC - Operate the Ram Air Turbine (RAT) with the C1 EMP. Do these steps 4 times:

<1> Extend the RAT. Do not install the RAT protective cover or the RAT blade protective

cover. Refer to 787 AMM 29-21-00 Ram Air Turbine Extension - Operation as an

accepted procedure.

<2> Retract the RAT. Refer to 787 AMM 29-21-00 Ram Air Turbine Retraction - Operation as an accepted procedure.

WARNING: KEEP ALL PERSONS AND EQUIPMENT AWAY FROM THE FLIGHT CONTROL SURFACES AND THE FLIGHT CONTROL DRIVE MECHANISMS.

THESE COMPONENTS WILL MOVE. THIS CAN CAUSE INJURIES TO

PERSONS AND DAMAGE TO EQUIPMENT.

g) RC - Operate the elevators with the C1 EMP. Do these steps 6 times:

<1> Use the flight controls synoptic page to make sure that the elevators moves fully.

<2> Push the control column fully forward.

<3> Push the control column fully aft.

<4> Push the control column to the neutral position.

WARNING: KEEP ALL PERSONS AND EQUIPMENT AWAY FROM THE FLIGHT CONTROL SURFACES AND THE FLIGHT CONTROL DRIVE MECHANISMS.

THESE COMPONENTS WILL MOVE. THIS CAN CAUSE INJURIES TO

PERSONS AND DAMAGE TO EQUIPMENT.

h) RC - Operate the rudder with the C1 EMP. Do these steps 15 times:

<1> Use the flight controls synoptic page to make sure that the rudder moves fully.

<2> Push the right rudder pedal fully forward.

<3> Push the left rudder pedal fully forward.

<4> Let the rudder pedals move to the neutral position.

Applicable To: B787-A-27-00-0026-00A-933A-D

Model 787 Issue 001, 25 Nov 2014

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AIRCRAFT SERVICE BULLETIN
WARNING: KEEP ALL PERSONS AND EQUIPMENT AWAY FROM THE FLIGHT CONTROL SURFACES AND THE FLIGHT CONTROL DRIVE MECHANISMS.

THESE COMPONENTS WILL MOVE. THIS CAN CAUSE INJURIES TO

PERSONS AND DAMAGE TO EQUIPMENT.

i) RC - Operate the flaperons with the C1 EMP. Do these steps 6 times:

<1> Use the flight controls synoptic page to make sure that the flaperons moves fully.

<2> Turn the control wheel from the neutral position to fully right.

<3> Turn the control wheel from fully right to fully left.

<4> Turn the control wheel from fully left to the neutral position.

WARNING: KEEP ALL PERSONS AND EQUIPMENT AWAY FROM THE FLIGHT CONTROL SURFACES AND THE FLIGHT CONTROL DRIVE MECHANISMS.

THESE COMPONENTS WILL MOVE. THIS CAN CAUSE INJURIES TO

PERSONS AND DAMAGE TO EQUIPMENT.

j) RC - Operate the spoilers with the C1 EMP. Do these steps 12 times:

<1> Use the flight controls synoptic page to make sure that the spoilers moves fully.

<2> Move the speedbrake lever from the DOWN position to the UP position.

<3> Move the speedbrake lever from the UP position to the DOWN position.

WARNING: KEEP ALL PERSONS AND EQUIPMENT AWAY FROM THE FLIGHT CONTROL SURFACES AND THE FLIGHT CONTROL DRIVE MECHANISMS.

THESE COMPONENTS WILL MOVE. THIS CAN CAUSE INJURIES TO

PERSONS AND DAMAGE TO EQUIPMENT.

k) RC - Operate the ailerons with the C1 EMP. Do these steps 15 times:

<1> Use the flight controls synoptic page to make sure that the ailerons moves fully.

<2> Turn the control wheel from the neutral position to fully right.

<3> Turn the control wheel from fully right to fully left.

<4> Turn the control wheel from fully left to the neutral position.

WARNING: KEEP ALL PERSONS AND EQUIPMENT AWAY FROM THE FLIGHT CONTROL SURFACES AND THE FLIGHT CONTROL DRIVE MECHANISMS.

THESE COMPONENTS WILL MOVE. THIS CAN CAUSE INJURIES TO

PERSONS AND DAMAGE TO EQUIPMENT.

l) RC - Do these steps to operate the flaps with the C1 EMP.

<1> Move the flap lever from the UP detent to the 5 detent.

<2> Move the flap lever from the 5 detent to the UP detent.

m) With landing gear pins removed and door safety valves in the STOW position, retract

the landing gear.

Applicable To: B787-A-27-00-0026-00A-933A-D

Model 787 Issue 001, 25 Nov 2014

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n) Extend the landing gear using the alternate extend system.

o) RC - Retract and extend the landing gear 2 times using the landing gear lever.

p) Do these steps to operate the landing gear with the C1 EMP:

<1> If the downlock pins are installed in the nose or main landing gear, remove them.

Refer to 787 AMM 32-00-30 Landing Gear Downlock Pins - Removal as an accepted

procedure.

WARNING: MAKE SURE THE AREA AROUND THE LANDING GEAR AND ITS

DOORS ARE CLEAR OF PERSONS AND EQUIPMENT DURING A

LANDING GEAR RETRACTION AND EXTENSION TEST. THIS WILL

HELP PREVENT INJURY TO PERSONS AND DAMAGE TO EQUIPMENT.

<2> Activate the landing gear doors. Refer to 787 AMM 32-00-15 Landing Gear Door

- Activation as an accepted procedure.

WARNING: MAKE SURE THE AREA AROUND THE LANDING GEAR AND ITS

DOORS ARE CLEAR OF PERSONS AND EQUIPMENT DURING A

LANDING GEAR RETRACTION AND EXTENSION TEST. THIS WILL

HELP PREVENT INJURY TO PERSONS AND DAMAGE TO EQUIPMENT.

<3> Move the control lever for the landing gear to the UP position.

WARNING: MAKE SURE THE AREA AROUND THE LANDING GEAR AND ITS

DOORS ARE CLEAR OF PERSONS AND EQUIPMENT DURING A

LANDING GEAR RETRACTION AND EXTENSION TEST. THIS WILL

HELP PREVENT INJURY TO PERSONS AND DAMAGE TO EQUIPMENT.

<4> Do these steps to extend the landing gear:

<a> Push and hold the ALTN GEAR switch on the P2 panel to DOWN to extend

the landing gear.

<b> Move the control lever for the landing gear to the DOWN position.

WARNING: MAKE SURE THE AREA AROUND THE LANDING GEAR AND ITS

DOORS ARE CLEAR OF PERSONS AND EQUIPMENT DURING A

LANDING GEAR RETRACTION AND EXTENSION TEST. THIS WILL

HELP PREVENT INJURY TO PERSONS AND DAMAGE TO EQUIPMENT.

<5> RC - Operate the landing gear. Do these steps 2 times:

<a> Move the control lever for the landing gear to the UP position.

<b> Move the control lever for the landing gear to the DOWN position.

Applicable To: B787-A-27-00-0026-00A-933A-D

Model 787 Issue 001, 25 Nov 2014

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WARNING: MAKE SURE THE AREA AROUND THE LANDING GEAR AND ITS

DOORS ARE CLEAR OF PERSONS AND EQUIPMENT DURING A

LANDING GEAR RETRACTION AND EXTENSION TEST. THIS WILL

HELP PREVENT INJURY TO PERSONS AND DAMAGE TO EQUIPMENT.

<6> Move the control lever for the landing gear to the UP position.

q) Move the door safety valve handles to the SAFE position. Refer to 787 AMM 32-00-15

Landing Gear Door - Deactivation as an accepted procedure

r) Install the downlock pins in the nose and main landing gear. Refer to 787 AMM 32-00-

30 Landing Gear Downlock Pins - Installation as an accepted procedure

s) Lower the airplane from jacks. Refer to 787 AMM 07-11-01 Lift the Airplane on Jacks -

Handling as an accepted procedure.

Group 1, Configuration 2; Group 2:

K. PART 3: HYDRAULIC FLUID TEST

RC - Take a 16 ounce or more sample of the hydraulic fluid. It is acceptable to take two 8 ounce

bottle samples from the same hydraulic system. Refer to 787 AMM 29-11-00, Hydraulic Fluid Sampling

- Inspection, as an accepted procedure.

(1)

(2) Label each sample with the following information:

(a) airplane

(b) flight cycles

(c) flight hours

(d) hydraulic system sampled (left, right or center)

(3) Ship the hydraulic fluid sample to the following address:

The Boeing Company

2-10 Bldg, Door S25 Seattle Receive

7701 14th Avenue South

Seattle, WA 98108-4002 USA

Route To: Will Call

Attention: Steve Millett (Composition Testing)

NOTE: Multiple hydraulic fluid samples can be shipped in the same shipping container as long as

the bottles are properly labeled and contained to prevent cross contamination. 

(4) Send a message to Boeing through the Boeing Communication System with the following information:

(a) MODEL: 787-8

(b) ATA: 2700-00

(c) SUBJECT: 787 Hydraulic Fluid Test

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(d) Shipping information including airway bill number and courier company

(e) Airplane, flight cycles, flight hours and system of fluid arriving in shipment.

Group 1, Configuration 2; Group 2:

L. PART 4: REPLACE HYDRAULIC FLUID

(1) RC - Do one of these options:

(a) OPTION 9: Replace the hydraulic fluid with HyJet V. Refer to 787 AMM 29-11-00 Hydraulic

System Fluid - Replacement as an accepted procedure.

1) For WORK PACKAGE 2: Do the left hydraulic system.

2) For WORK PACKAGE 3: Do the right hydraulic system.

3) For WORK PACKAGE 4: Do the center hydraulic system. Leave the airplane on jacks after

replacing the hydraulic fluid.

(b) OPTION 10: Drain and fill the hydraulic system reservoir. Refer to 787 AMM 12-12-01 Hydraulic

Reservoir - Drain Liquid and 787 AMM 12-12-01 Hydraulic Reservoir (Task Selection) - Servicing

as accepted procedures.

1) For WORK PACKAGE 2: Do the left hydraulic system.

2) For WORK PACKAGE 3: Do the right hydraulic system.

3) For WORK PACKAGE 4: Do the center hydraulic system.

Group 1, Configuration 2; Group 2:

M. PART 5: ELEVATOR INBOARD POWER CONTROL UNIT INTERNAL FLOW TEST

Do these steps for the elevator inboard power control unit (PCU) internal flow test. For WORK

PACKAGE 5, do the left elevator. For WORK PACKAGE 6, do the right elevator. The elevator inboard

(1)

PCU internal flow test can be done for WORK PACKAGE 5 and WORK PACKAGE 6 at the same

time.

(2) Prepare for the test and install tool TSF036Z0229:

(a) Use the pitch trim switches on the captain's or first officer's control wheel to move the stabilizer

to the 4 unit position.

(b) On the control stand, put the L2 and R2 STAB CUTOUT switches to the CUTOUT position.

1) Attach a DO NOT OPERATE tag on the L2 and R2 STAB CUTOUT switches.

(c) Depressurize the center hydraulic system and reservoir. Refer to 787 AMM 29-11-00 as an accepted procedure.

(d) Put the FLIGHT CONTROL SURFACE switch for the TAIL in the LOCK position and install a

DO NOT OPERATE tag on the switch. Refer to 787 AMM 27-02-00 Flight Control Surface Lock

Switches - Operation as an accepted procedure.

(e) Remove Flight Control Electronic (FCE) cabinet power.

Applicable To: B787-A-27-00-0026-00A-933A-D

Model 787 Issue 001, 25 Nov 2014

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EXPORT CONTROLLED ECCN: 9E991

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B787-81205-SB270026-00

Issue 001, 25 Nov 2014

AIRCRAFT SERVICE BULLETIN
1) Open these circuit breakers and lock with DO NOT CLOSE tags on the circuit breaker indication and control (CBIC) panel:

Table 4 

Designation CB

FCE CABINET-C1 BACKUP CE2709811

FCE CABINET-L BACKUP CE2709831

FCE CABINET-C2 BACKUP CE2709821

FCE CABINET-R BACKUP CE2709841

(f) Gain access to the elevator PCUs:

1) For WORK PACKAGE 5, open panel 335CB - Horizontal Stabilizer TE Panel and 335FBX

- Horizontal Stabilizer TE Seal - Mid. Refer to 787 AMM 55-16-01 Horizontal Stabilizer

Trailing Edge Skin Panel - Removal as an accepted procedure.

2) For WORK PACKAGE 6, open panel 345CB - Horizontal Stabilizer TE Panel and 345FBX

- Horizontal Stabilizer TE Seal - Mid. Refer to 787 AMM 55-16-01 Horizontal Stabilizer

Trailing Edge Skin Panel - Removal as an accepted procedure.

(g) RC - Remove and keep the hydraulic return line between the elevator inboard PCU and the rib

hinge. Refer to 787 AMM 20-10-09 Tube Assembly - Flareless - Removal as an accepted procedure.

(h) RC - Install tool TSF036Z0229 between the elevator inboard PCU and rib hinge.

(i) Make sure the hose between the tool TSF036Z0229 and the PCU is connected to the tee fitting

on the tool furthest away from the ball valve.

CAUTION: IF THE BALL VALVE OF TOOL TSF036Z0229 IS NOT OPEN WHEN THE HYDRAULIC

SYSTEM IS PRESSURIZED, THE HIGH FLOW RATES CAN DAMAGE THE TOOL.

(j) Make sure the ball valve on the tool is in the open position.

(k) Supply FCE cabinet power.

1) Unlock these DO NOT CLOSE tags and close these circuit breakers on the CBIC panel:

Table 5 

Designation CB

FCE CABINET-C1 BACKUP CE2709811

FCE CABINET-L BACKUP CE2709831

FCE CABINET-C2 BACKUP CE2709821

FCE CABINET-R BACKUP CE2709841

(l) Put the FLIGHT CONTROL SURFACE switch for the TAIL in the NORM position and remove

the DO NOT OPERATE tag. Refer to 787 AMM 27-02-00 Flight Control Surface Lock Switches

- Operation as an accepted procedure.

Applicable To: B787-A-27-00-0026-00A-933A-D

Model 787 Issue 001, 25 Nov 2014

See Applicability of this data module

Page 47 of 77

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B787-81205-SB270026-00

Issue 001, 25 Nov 2014

AIRCRAFT SERVICE BULLETIN
(m) On the control stand, put the L2 and R2 STAB CUTOUT switches to the NORM position and

remove the DO NOT OPERATE tags.

(n) Do these steps to pressurize the center hydraulic system and inspect the tool TSF036Z0229

connections for leaks:

1) Pressurize the center hydraulic system. Refer to 787 AMM 29-11-00 as an accepted procedure.

2) Operate the elevators. Do these steps 7 times:

a) Use the flight controls synoptic page to make sure that the elevators moves fully.

b) Push the control column fully forward.

c) Push the control column fully aft.

d) Push the control column to the neutral position.

3) Do a detailed visual inspection for hydraulic fluid leaks at the tool TSF036Z0229 connections.

If leaks are found, fix them.

(o) For the center hydraulic system, turn the applicable switch on the hydraulic system control

panel (P5) to the OFF position:

1) HYDRAULIC PRIMARY C1 ELEC

2) HYDRAULIC PRIMARY C2 ELEC

(3) Test Procedure:

(a) Make sure page 2 of the Flight Controls Maintenance Pages is showing. Refer to Data Module

Appendix G, SB B787-A-27-00-0026-0GA-931D-D Figure 1 for illustration of this screen.

WARNING: KEEP ALL PERSONS AND EQUIPMENT AWAY FROM THE FLIGHT CONTROL

SURFACES AND THE FLIGHT CONTROL DRIVE MECHANISMS. THESE COMPONENTS WILL MOVE. THIS CAN CAUSE INJURIES TO PERSONS AND DAMAGE

TO EQUIPMENT.

(b) Start the applicable Central Maintenance Computing Function (CMCF) ground test: 27 Primary

Flight Control System, LRU Replacement, Left or Right Elevator Major Rig. Refer to 787 AMM

45-11-00 Start a Ground Test - Software Operation as an accepted procedure.

(c) After the test starts, continue through the test procedure until the GROUND TESTS screen

shows the following. Refer to Data Module Appendix G, SB B787-A-27-00-0026-0GA-931D-D

Figure 2 for illustration of this screen.

"The surface may now be ramped through 20 warm up/bleed cycles."

(d) Prepare to monitor the DELTA PRESS readout for the elevator inboard PCU on Page 2 of the

Flight Controls Maintenance Pages. Refer to Data Module Appendix G, SB B787-A-27-00-0026-

0GA-931D-D Figure 1 for illustration of this screen.

(e) On the GROUND TESTS screen, select the SKIP WARMUP AND BLEED and then click the

CONTINUE buttons. Refer to Data Module Appendix G, SB B787-A-27-00-0026-0GA-931D-D

Figure 2 for illustration of this screen.

Applicable To: B787-A-27-00-0026-00A-933A-D

Model 787 Issue 001, 25 Nov 2014

See Applicability of this data module

Page 48 of 77

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B787-81205-SB270026-00

Issue 001, 25 Nov 2014

AIRCRAFT SERVICE BULLETIN
(f) When the DELTA PRESS for the elevator inboard PCU is between -4400 psi and -5500 psi on

Page 2 of the Flight Controls Maintenance Pages, push the STOP TEST button on the GROUND

TESTS screen.

NOTE: A warning screen will show, do not push any additional buttons at this time. 

(g) Make sure the DELTA PRESS readout for the elevator inboard PCU on Page 2 of the Flight

Controls Maintenance Pages remains between -4400 psi and -5500 psi.

CAUTION: IF YOU DO NOT OBEY THIS STEP CORRECTLY, YOU WILL HAVE TO RERIG THE SURFACE.

1) If the GROUND TESTS screen shows "Select position adjustments below until the elevator

being rigged is at the external alignment feature", the STOP TEST button was not pushed

in time. Refer to Data Module Appendix G, SB B787-A-27-00-0026-0GA-931D-D Figure 3

for illustration of this screen. Push the STOP TEST button and start the Test Procedure

again. Do not push CONTINUE on this GROUND TESTS screen. If you push CONTINUE,

you will need to re-rig the surface.

2) If the DELTA PRESS is not between -4400 psi and -5500 psi, Push the STOP TEST button

on the GROUND TESTS screen and start the Test Procedure again.

(h) RC - Close the ball valve on tool TSF036Z0229.

(i) RC- Read and record the flow through the indicator of tool TSF036Z0229 ten or more minutes

after the ball valve is closed.

(j) Open the ball valve on tool TSF036Z0229.

(k) Push the STOP TEST button on the GROUND TESTS warning screen.

(4) Remove the tool:

(a) On the control stand, put the L2 and R2 STAB CUTOUT switches to the CUTOUT position.

1) Attach a DO NOT OPERATE tag on the L2 and R2 STAB CUTOUT switches.

(b) Depressurize the center hydraulic system and reservoir. Refer to 787 AMM 29-11-00 as an accepted procedure.

(c) Put the FLIGHT CONTROL SURFACE switch for the TAIL in the LOCK position and install a

DO NOT OPERATE tag on the switch. Refer to 787 AMM 27-02-00 Flight Control Surface Lock

Switches - Operation as an accepted procedure.

(d) Remove FCE cabinet power.

1) Open these circuit breakers and lock with DO NOT CLOSE tags on the CBIC panel:

Table 6 

Designation CB

FCE CABINET-C1 BACKUP CE2709811

FCE CABINET-L BACKUP CE2709831

FCE CABINET-C2 BACKUP CE2709821

FCE CABINET-R BACKUP CE2709841

Applicable To: B787-A-27-00-0026-00A-933A-D

Model 787 Issue 001, 25 Nov 2014

See Applicability of this data module

Page 49 of 77

EXPORT CONTROLLED ECCN: 9E991

BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET. See title page for details.

B787-81205-SB270026-00

Issue 001, 25 Nov 2014

AIRCRAFT SERVICE BULLETIN
(e) RC - Disconnect and remove tool TSF036Z0229 between the elevator inboard PCU and the rib

hinge.

(f) RC - Install the kept hydraulic return line between the elevator inboard PCU and rib hinge. Refer

to 787 AMM 20-10-09 Tube Assembly - Flareless - Installation as an accepted procedure.

(g) Supply FCE cabinet power.

1) Unlock these DO NOT CLOSE tags and close these circuit breakers on the CBIC panel:

Table 7 

Designation CB

FCE CABINET-C1 BACKUP CE2709811

FCE CABINET-L BACKUP CE2709831

FCE CABINET-C2 BACKUP CE2709821

FCE CABINET-R BACKUP CE2709841

(h) Put the FLIGHT CONTROL SURFACE switch for the TAIL in the NORM position and remove

the DO NOT OPERATE tag. Refer to 787 AMM 27-02-00 Flight Control Surface Lock Switches

- Operation as an accepted procedure.

(i) On the control stand, put the L2 and R2 STAB CUTOUT switches to the NORM position and

remove the DO NOT OPERATE tag.

(j) Do these steps to pressurize the hydraulic system and inspect the hydraulic return line to elevator

inboard PCU connection for leaks where the tool was installed:

1) Pressurize the center hydraulic system. Refer to 787 AMM 29-11-00 as an accepted procedure.

2) Operate the elevators. Do these steps 7 times:

a) Use the flight controls synoptic page to make sure that the elevators moves fully.

b) Push the control column fully forward.

c) Push the control column fully aft.

d) Push the control column to the neutral position.

3) Do a detailed visual inspection for hydraulic fluid leaks at the elevator inboard PCU hydraulic

return line connections. If leaks are found, fix them.

(k) Close access to the elevator PCUs:

1) For WORK PACKAGE 5, close panel 335CB - Horizontal Stabilizer TE Panel and 335FBX

- Horizontal Stabilizer TE Seal - Mid. Refer to 787 AMM 55-16-01 Horizontal Stabilizer

Trailing Edge Skin Panel - Installation as an accepted procedure.

2) For WORK PACKAGE 6, close panel 345CB - Horizontal Stabilizer TE Panel and 345FBX

- Horizontal Stabilizer TE Seal - Mid. Refer to 787 AMM 55-16-01 Horizontal Stabilizer

Trailing Edge Skin Panel - Installation as an accepted procedure.

Applicable To: B787-A-27-00-0026-00A-933A-D

Model 787 Issue 001, 25 Nov 2014

See Applicability of this data module

Page 50 of 77

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Issue 001, 25 Nov 2014

AIRCRAFT SERVICE BULLETIN
Group 1, Configuration 2; Group 2:

N. PART 6: AILERON INBOARD POWER CONTROL UNIT INTERNAL FLOW TEST

Do these steps for the aileron inboard power control unit (PCU) internal flow test. For WORK

PACKAGE 7, do the left aileron. For WORK PACKAGE 8, do the right aileron. The aileron inboard

(1)

PCU internal flow test can be done at the same time for WORK PACKAGE 7 and WORK PACKAGE

8.

(2) Prepare for the test and install tool TSF036Z0229:

(a) Depressurize the center hydraulic system and reservoir. Refer to 787 AMM 29-11-00 as an accepted procedure.

(b) Put the FLIGHT CONTROL SURFACE switch for the WINGS in the LOCK position and install

a DO NOT OPERATE tag. Refer to 787 AMM 27-02-00 Flight Control Surface Lock Switches -

Operation as an accepted procedure.

(c) Remove Flight Control Electronic (FCE) cabinet power.

1) Open these circuit breakers and lock with DO NOT CLOSE tags on the circuit breaker indication and control (CBIC) panel:

Table 8 

Designation CB

FCE CABINET-C1 BACKUP CE2709811

FCE CABINET-L BACKUP CE2709831

FCE CABINET-C2 BACKUP CE2709821

FCE CABINET-R BACKUP CE2709841

(d) Gain access to the aileron PCUs:

1) For WORK PACKAGE 7, open panel 561YB and 561ZB - Wing Lower Fixed Trailing Edge

Panel. Refer to 787 AMM 57-51-10 Wing Trailing Edge Panel - Removal as an accepted

procedure.

2) For WORK PACKAGE 8, open panel 661YB and 661ZB - Wing Lower Fixed Trailing Edge

Panel. Refer to 787 AMM 57-51-10 Wing Trailing Edge Panel - Removal as an accepted

procedure.

(e) RC - Remove and keep the hydraulic return line between the aileron inboard PCU and the rear

spar. Refer to 787 AMM 20-10-09 Tube Assembly - Flareless - Removal as an accepted procedure.

(f) RC - Install tool TSF036Z0229 between the aileron inboard PCU and the rear spar.

(g) Make sure the hose between the tool TSF036Z0229 and the PCU is connected to the tee fitting

on the tool furthest away from the ball valve.

CAUTION: IF THE BALL VALVE OF TOOL TSF036Z0229 IS NOT OPEN WHEN THE HYDRAULIC

SYSTEM IS PRESSURIZED, THE HIGH FLOW RATES CAN DAMAGE THE TOOL.

(h) Make sure the ball valve on the tool is in the open position.

Applicable To: B787-A-27-00-0026-00A-933A-D

Model 787 Issue 001, 25 Nov 2014

See Applicability of this data module

Page 51 of 77

EXPORT CONTROLLED ECCN: 9E991

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B787-81205-SB270026-00

Issue 001, 25 Nov 2014

AIRCRAFT SERVICE BULLETIN
(i) Supply FCE cabinet power.

1) Unlock these DO NOT CLOSE tags and close these circuit breakers on the CBIC panel:

Table 9 

Designation CB

FCE CABINET-C1 BACKUP CE2709811

FCE CABINET-L BACKUP CE2709831

FCE CABINET-C2 BACKUP CE2709821

FCE CABINET-R BACKUP CE2709841

(j) Put the FLIGHT CONTROL SURFACE switch for the WINGS in the NORM position and remove

the DO NOT OPERATE tag. Refer to 787 AMM 27-02-00 Flight Control Surface Lock Switches

- Operation as an accepted procedure.

(k) Do these steps to pressurize the center hydraulic system and inspect the tool TSF036Z0229

connections for leaks:

1) Pressurize the center hydraulic system. Refer to 787 AMM 29-11-00 as an accepted procedure.

2) Operate the ailerons. Do these steps 7 times:

a) Use the flight controls synoptic page to make sure that the ailerons moves fully.

b) Turn the control wheel from the neutral position to fully right.

c) Turn the control wheel from fully right to fully left.

d) Turn the control wheel from fully left to the neutral position.

3) Do a detailed visual inspection for hydraulic fluid leaks at the tool TSF036Z0229 connections.

If leaks are found, fix them.

(l) For the center hydraulic system, turn the applicable switch on the hydraulic system control

panel (P5) to the OFF position:

1) HYDRAULIC PRIMARY C1 ELEC

2) HYDRAULIC PRIMARY C2 ELEC

(3) Test Procedure:

(a) Make sure page 2 of the Flight Controls Maintenance Pages is showing. Refer to Data Module

Appendix G, SB B787-A-27-00-0026-0GA-931D-D Figure 1 for illustration of this screen.

Applicable To: B787-A-27-00-0026-00A-933A-D

Model 787 Issue 001, 25 Nov 2014

See Applicability of this data module

Page 52 of 77

EXPORT CONTROLLED ECCN: 9E991

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B787-81205-SB270026-00

Issue 001, 25 Nov 2014

AIRCRAFT SERVICE BULLETIN
WARNING: KEEP ALL PERSONS AND EQUIPMENT AWAY FROM THE FLIGHT CONTROL

SURFACES AND THE FLIGHT CONTROL DRIVE MECHANISMS. THESE COMPONENTS WILL MOVE. THIS CAN CAUSE INJURIES TO PERSONS AND DAMAGE

TO EQUIPMENT.

(b) Start the applicable Central Maintenance Computing Function (CMCF) ground test: 27 Primary

Flight Control System, LRU Replacement, Left or Right Aileron Major Rig. Refer to 787 AMM

45-11-00 Start a Ground Test - Software Operation as an accepted procedure.

(c) After the test starts, continue through the test procedure until the GROUND TESTS screen

shows the following. Refer to Data Module Appendix G, SB B787-A-27-00-0026-0GA-931D-D

Figure 2 for illustration of this screen.

"The surface may now be ramped through 20 warm up/bleed cycles"

(d) Prepare to monitor the DELTA PRESS readout for the aileron inboard PCU on Page 2 of the

Flight Controls Maintenance Pages. Refer to Data Module Appendix G, SB B787-A-27-00-0026-

0GA-931D-D Figure 1 for illustration of this screen.

(e) On the GROUND TESTS screen, select the SKIP WARMUP AND BLEED and then click the

CONTINUE buttons. Refer to Data Module Appendix G, SB B787-A-27-00-0026-0GA-931D-D

Figure 2 for illustration of this screen.

(f) When the DELTA PRESS for the aileron inboard PCU is between -4400 psi and -5500 psi on

Page 2 of the Flight Controls Maintenance Pages, push the STOP TEST button on the GROUND

TESTS screen.

NOTE: A warning screen will show, do not push any additional buttons at this time. 

(g) Make sure the DELTA PRESS readout for the aileron inboard PCU on Page 2 of the Flight

Controls Maintenance Pages remains between -4400 psi and -5500 psi.

CAUTION: IF YOU DO NOT OBEY THIS STEP CORRECTLY, YOU WILL HAVE TO RERIG THE SURFACE.

1) If the GROUND TESTS screen shows "Select position adjustments below until the aileron

being rigged is at the external alignment feature", the STOP TEST button was not pushed

in time. Refer to Data Module Appendix G, SB B787-A-27-00-0026-0GA-931D-D Figure 3

for illustration of this screen. Push the STOP TEST button and start the Test Procedure

again. Do not push CONTINUE on this GROUND TESTS screen. If you push CONTINUE,

you will need to re-rig the surface.

2) If the DELTA PRESS is not between -4400 psi and -5500 psi, Push the STOP TEST button

on the GROUND TESTS screen and start the Test Procedure again.

(h) RC - Close the ball valve on tool TSF036Z0229.

(i) RC - Read and record the flow through the indicator of tool TSF036Z0229 ten or more minutes

after the ball valve is closed.

(j) Open the ball valve on tool TSF036Z0229.

(k) Push the STOP TEST button on the GROUND TESTS warning screen.

(4) Remove the tool:

Applicable To: B787-A-27-00-0026-00A-933A-D

Model 787 Issue 001, 25 Nov 2014

See Applicability of this data module

Page 53 of 77

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Issue 001, 25 Nov 2014

AIRCRAFT SERVICE BULLETIN
(a) Make sure the center hydraulic system and reservoir is depressurized. Refer to 787 AMM 27-

11-19 Aileron Power Control Unit Removal, as an accepted procedure.

(b) Make sure the FLIGHT CONTROL SURFACE switch for the WINGS is in the LOCK position

and a DO NOT OPERATE tag is installed. Refer to 787 AMM 27-11-19 Aileron Power Control

Unit - Removal, as an accepted procedure.

(c) Remove FCE cabinet power.

1) Open these circuit breakers and lock with DO NOT CLOSE tags on the CBIC panel:

Table 10 

Designation CB

FCE CABINET-C1 BACKUP CE2709811

FCE CABINET-L BACKUP CE2709831

FCE CABINET-C2 BACKUP CE2709821

FCE CABINET-R BACKUP CE2709841

(d) RC - Disconnect and remove tool TSF036Z0229 between the aileron inboard PCU and the rear

spar.

(e) RC - Install the kept hydraulic return line between the aileron inboard PCU and rear spar. Refer

to 787 AMM 20-10-09 Tube Assembly - Flareless - Installation as an accepted procedure.

(f) Supply FCE cabinet power.

1) Unlock these DO NOT CLOSE tags and close these circuit breakers on the CBIC panel:

Table 11 

Designation CB

FCE CABINET-C1 BACKUP CE2709811

FCE CABINET-L BACKUP CE2709831

FCE CABINET-C2 BACKUP CE2709821

FCE CABINET-R BACKUP CE2709841

(g) Put the FLIGHT CONTROL SURFACE switch for the WINGS in the NORM position and remove

the DO NOT OPERATE tag. Refer to 787 AMM 27-11-19 Aileron Power Control Unit - Removal,

as an accepted procedure.

(h) Do these steps to pressurize the hydraulic system and inspect the hydraulic return line to aileron

inboard PCU connection for leaks where the tool was installed:

1) Pressurize the center hydraulic system. Refer to 787 AMM 29-11-00 as an accepted procedure.

2) Operate the ailerons. Do these steps 7 times:

a) Use the flight controls synoptic page to make sure that the ailerons moves fully.

Applicable To: B787-A-27-00-0026-00A-933A-D

Model 787 Issue 001, 25 Nov 2014

See Applicability of this data module

Page 54 of 77

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Issue 001, 25 Nov 2014

AIRCRAFT SERVICE BULLETIN
b) Turn the control wheel from the neutral position to fully right.

c) Turn the control wheel from fully right to fully left.

d) Turn the control wheel from fully left to the neutral position.

3) Do a detailed visual inspection for hydraulic fluid leaks at the aileron inboard PCU hydraulic

return line connections. If leaks are found, fix them.

(i) Close access to the aileron PCUs:

1) For WORK PACKAGE 7, close panel 561YB and 561ZB - Wing Lower Fixed Trailing Edge

Panel. Refer to 787 AMM 57-51-10 Wing Trailing Edge Panel - Installation as an accepted

procedure.

2) For WORK PACKAGE 8, close panel 661YB and 661ZB - Wing Lower Fixed Trailing Edge

Panel. Refer to 787 AMM 57-51-10 Wing Trailing Edge Panel - Installation as an accepted

procedure.

Group 1, Configuration 2; Group 2:

O. PART 7: REPLACE THE POWER CONTROL UNIT

(1) RC - For WORK PACKAGE 5, replace the left elevator inboard power control unit. Refer to 787 AMM

27-31-09 as an accepted procedure.

(2) RC - For WORK PACKAGE 6, replace the right elevator inboard power control unit. Refer to 787

AMM 27-31-09 as an accepted procedure.

(3) RC - For WORK PACKAGE 7, replace the left aileron inboard power control unit. Refer to 787 AMM

27-11-19 as an accepted procedure.

(4) RC - For WORK PACKAGE 8, replace the right aileron inboard power control unit. Refer to 787 AMM

27-11-19 as an accepted procedure.

Applicable To: B787-A-27-00-0026-00A-933A-D

Model 787 End of data module Issue 001, 25 Nov 2014

See Applicability of this data module

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EXPORT CONTROLLED ECCN: 9E991

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B787-81205-SB270026-00

Issue 001, 25 Nov 2014

AIRCRAFT SERVICE BULLETIN
Alert Service Bulletin B787-81205-SB270026-00

Appendix A – LOGIC DIAGRAM FOR PARAGRAPH 1.E. COMPLIANCE:

TABLE 5 LEFT, RIGHT AND CENTER HYDRAULIC SYSTEM FLUID MARKER

INSTALLATION [Group 1-2:]

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

AIRPLANES SHOWN IN DATA MODULE SB B787-A-27-00-0026-00A-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-27-00-0026-00A-932A-D Issue 001, Compliance

Paragraph 5.

SB B787-A-27-00-0026-00A-933A-D Issue 001, Step 2. Work Instructions

FLIGHT CONTROLS - Elevator Control System -

Elevator Power Control Unit Electro-Hydraulic Servo

Valve Rate Restriction Test

SB B787-81205-SB270016-00

Procedure

Group 1-2:

1. Logic diagrams are provided as an aid only. Information contained in Data Module SB B787-A-27-

00-0026-00A-932A-D, Paragraph 5., Compliance, is the primary source for compliance times. InforNOTE:

mation in Data Module SB B787-A-27-00-0026-00A-933A-D, Step 2., Work Instructions, is the primary source for tasks required for compliance. 

The table below gives the description for the parts and conditions called out in the logic diagram.

Table 1 Description Table

Title Description

WORK PACKAGE 1 MARKER INSTALLATION

Applicable To: B787-A-27-00-0026-0AA-931D-D

Model 787 Issue 001, 25 Nov 2014

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Issue 001, 25 Nov 2014

AIRCRAFT SERVICE BULLETIN
The table below gives the description for the flag notes called out in the logic diagram.

Table 2 Flag Notes

Flag Note More Data

No further action required for Group 1, Configuration 1 after WORK PACKAGE 1 is done.

Accomplishment of this service bulletin terminates SB B787-81205-SB270016-00. (TERMINATING ACTION)

[1]

No further action required for Group 1, Configuration 2 and Group 2 after WORK PACKAGE

1 thru WORK PACKAGE 4 are done. See Appendix A, B, C and D. Accomplishment of

this service bulletin terminates SB B787-81205-SB270016-00. (TERMINATING ACTION)

[2]

Applicable To: B787-A-27-00-0026-0AA-931D-D

Model 787 Issue 001, 25 Nov 2014

See Applicability of this data module

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AIRCRAFT SERVICE BULLETIN
ICN-B787-A-000061-A-81205-09066-A-01-1

Figure 1 

Applicable To: B787-A-27-00-0026-0AA-931D-D

Model 787 End of data module Issue 001, 25 Nov 2014

See Applicability of this data module

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Issue 001, 25 Nov 2014

AIRCRAFT SERVICE BULLETIN
Alert Service Bulletin B787-81205-SB270026-00

Appendix B – LOGIC DIAGRAM FOR PARAGRAPH 1.E. COMPLIANCE:

TABLE 6 LEFT HYDRAULIC SYSTEM FLUID TEST [Group 1, Configuration

2; Group 2: ]

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

AIRPLANES SHOWN IN DATA MODULE SB B787-A-27-00-0026-00A-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-27-00-0026-00A-932A-D Issue 001, Compliance

Paragraph 5.

SB B787-A-27-00-0026-00A-933A-D Issue 001, Step 2. Work Instructions

FLIGHT CONTROLS - Elevator Control System -

Elevator Power Control Unit Electro-Hydraulic Servo

Valve Rate Restriction Test

SB B787-81205-SB270016-00

Procedure

Group 1, Configuration 2; Group 2:

1. Logic diagrams are provided as an aid only. Information contained in Data Module SB B787-A-27-

00-0026-00A-932A-D, Paragraph 5., Compliance, is the primary source for compliance times. InforNOTE:

mation in Data Module SB B787-A-27-00-0026-00A-933A-D, Step 2., Work Instructions, is the primary source for tasks required for compliance. 

The table below gives the description for the parts and conditions called out in the logic diagram.

Table 1 Description Table

Title Description

WORK PACKAGE 2 LEFT HYDRAULIC SYSTEM FLUID TEST

PART 2 CYCLE HYDRAULIC FLUID

PART 3 HYDRAULIC FLUID TEST

PART 4 REPLACE HYDRAULIC FLUID

CONDITION 1 PASSES THE HYDRAULIC FLUID TEST

CONDITION 2 DOES NOT PASS THE HYDRAULIC FLUID TEST

Applicable To: B787-A-27-00-0026-0BA-931D-D

Model 787 Issue 001, 25 Nov 2014

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The table below gives the description for the flag notes called out in the logic diagram.

Table 2 Flag Notes

Flag Note More Data

It is acceptable to put the airplane back to a serviceable condition and return the airplane

to service before the test results are received.

[1]

No further action required for Group 1, Configuration 2 and Group 2 after WORK PACKAGE

1 thru WORK PACKAGE 4 are done. See Appendix A, B, C and D. Accomplishment of

this service bulletin terminates SB B787-81205-SB270016-00. (TERMINATING ACTION)

[2]

CONDITION 2 (ACTION 2) can be done any time between CONDITION 2 (ACTION 1)

and the Compliance Time.

[3]

Applicable To: B787-A-27-00-0026-0BA-931D-D

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ICN-B787-A-000061-A-81205-09067-A-01-1

Figure 1 

Applicable To: B787-A-27-00-0026-0BA-931D-D

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AIRCRAFT SERVICE BULLETIN
Alert Service Bulletin B787-81205-SB270026-00

Appendix C – LOGIC DIAGRAM FOR PARAGRAPH 1.E. COMPLIANCE:

TABLE 7 RIGHT HYDRAULIC SYSTEM FLUID TEST [Group 1, Configuration

2; Group 2: ]

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

AIRPLANES SHOWN IN DATA MODULE SB B787-A-27-00-0026-00A-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-27-00-0026-00A-932A-D Issue 001, Compliance

Paragraph 5.

SB B787-A-27-00-0026-00A-933A-D Issue 001, Step 2. Work Instructions

FLIGHT CONTROLS - Elevator Control System -

Elevator Power Control Unit Electro-Hydraulic Servo

Valve Rate Restriction Test

SB B787-81205-SB270016-00

Procedure

Group 1, Configuration 2; Group 2:

1. Logic diagrams are provided as an aid only. Information contained in Data Module SB B787-A-27-

00-0026-00A-932A-D, Paragraph 5., Compliance, is the primary source for compliance times. InforNOTE:

mation in Data Module SB B787-A-27-00-0026-00A-933A-D, Step 2., Work Instructions, is the primary source for tasks required for compliance. 

The table below gives the description for the parts and conditions called out in the logic diagram.

Table 1 Description Table

Title Description

WORK PACKAGE 3 RIGHT HYDRAULIC SYSTEM FLUID TEST

PART 2 CYCLE HYDRAULIC FLUID

PART 3 HYDRAULIC FLUID TEST

PART 4 REPLACE HYDRAULIC FLUID

CONDITION 3 PASSES THE HYDRAULIC FLUID TEST

CONDITION 4 DOES NOT PASS THE HYDRAULIC FLUID TEST

Applicable To: B787-A-27-00-0026-0CA-931D-D

Model 787 Issue 001, 25 Nov 2014

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AIRCRAFT SERVICE BULLETIN
The table below gives the description for the flag notes called out in the logic diagram.

Table 2 Flag Notes

Flag Note More Data

It is acceptable to put the airplane back to a serviceable condition and return the airplane

to service before the test results are received.

[1]

No further action required for Group 1, Configuration 2 and Group 2 after WORK PACKAGE

1 thru WORK PACKAGE 4 are done. See Appendix A, B, C and D. Accomplishment of

this service bulletin terminates SB B787-81205-SB270016-00. (TERMINATING ACTION)

[2]

CONDITION 4 (ACTION 2) can be done any time between CONDITION 4 (ACTION 1)

and the Compliance Time.

[3]

Applicable To: B787-A-27-00-0026-0CA-931D-D

Model 787 Issue 001, 25 Nov 2014

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ICN-B787-A-000061-A-81205-09068-A-01-1

Figure 1 

Applicable To: B787-A-27-00-0026-0CA-931D-D

Model 787 End of data module Issue 001, 25 Nov 2014

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Alert Service Bulletin B787-81205-SB270026-00

Appendix D – LOGIC DIAGRAM FOR PARAGRAPH 1.E. COMPLIANCE:

TABLE 8 CENTER HYDRAULIC SYSTEM FLUID TEST AND LEFT AND RIGHT

ELEVATOR AND AILERON POWER CONTROL UNIT INTERNAL FLOW TEST

[Group 1, Configuration 2; Group 2: ]

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

AIRPLANES SHOWN IN DATA MODULE SB B787-A-27-00-0026-00A-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-27-00-0026-00A-932A-D Issue 001, Compliance

Paragraph 5.

SB B787-A-27-00-0026-00A-933A-D Issue 001, Step 2. Work Instructions

FLIGHT CONTROLS - Elevator Control System -

Elevator Power Control Unit Electro-Hydraulic Servo

Valve Rate Restriction Test

SB B787-81205-SB270016-00

Procedure

Group 1, Configuration 2; Group 2:

1. Logic diagrams are provided as an aid only. Information contained in Data Module SB B787-A-27-

00-0026-00A-932A-D, Paragraph 5., Compliance, is the primary source for compliance times. InforNOTE:

mation in Data Module SB B787-A-27-00-0026-00A-933A-D, Step 2., Work Instructions, is the primary source for tasks required for compliance. 

The table below gives the description for the parts and conditions called out in the logic diagram.

Table 1 Description Table

Title Description

CENTER HYDRAULIC SYSTEM FLUID TEST AND LEFT AND RIGHT ELEVATOR AND AILERON POWER CONTROL UNIT INTERNAL FLOW TESTWORK PACKAGE 4

WORK PACKAGE 5 LEFT ELEVATOR INBOARD POWER CONTROL UNIT INTERNAL FLOW TEST

RIGHT ELEVATOR INBOARD POWER CONTROL UNIT INTERNAL FLOW

TEST

WORK PACKAGE 6

WORK PACKAGE 7 LEFT AILERON INBOARD POWER CONTROL UNIT INTERNAL FLOW TEST

WORK PACKAGE 8 RIGHT AILERON INBOARD POWER CONTROL UNIT INTERNAL FLOW TEST

Applicable To: B787-A-27-00-0026-0DA-931D-D

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Table 1 Description Table

Title Description

PART 2 CYCLE HYDRAULIC FLUID

PART 3 HYDRAULIC FLUID TEST

PART 4 REPLACE HYDRAULIC FLUID

CONDITION 5 PASSES THE HYDRAULIC FLUID TEST

CONDITION 6 DOES NOT PASS THE HYDRAULIC FLUID TEST

The table below gives the description for the flag notes called out in the logic diagram.

Table 2 Flag Notes

Flag Note More Data

It is acceptable to put the airplane back to a serviceable condition and return the airplane

to service before the test results are received.

[1]

CONDITION 5 (ACTION 1) thru CONDITION 5 (ACTION 4) can be done in any sequence.

It is acceptable to put the airplane back to a serviceable condition and return the airplane

to service after each action independently.

[2]

No further action required for WORK PACKAGE 4 after CONDITION 5 (ACTION 1) thru

CONDITION 5 (ACTION 4) are done.

[3]

No further action required for Group 1, Configuration 2 and Group 2 after WORK PACKAGE

1 thru WORK PACKAGE 4 are done. See Appendix A, B, C and D. Accomplishment of

this service bulletin terminates SB B787-81205-SB270016-00. (TERMINATING ACTION)

[4]

See Appendix E for disposition of WORK PACKAGE 5 and WORK PACKAGE 6 conditions

and actions.

[5]

See Appendix F for disposition of WORK PACKAGE 7 and WORK PACKAGE 8 conditions

and actions.

[6]

CONDITION 6 (ACTION 2) can be done any time between CONDITION 6 (ACTION 1)

and the Compliance Time.

[7]

Applicable To: B787-A-27-00-0026-0DA-931D-D

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ICN-B787-A-000061-A-81205-09069-A-01-1

Figure 1 

Applicable To: B787-A-27-00-0026-0DA-931D-D

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B787-81205-SB270026-00

Issue 001, 25 Nov 2014

AIRCRAFT SERVICE BULLETIN
Alert Service Bulletin B787-81205-SB270026-00

Appendix E – LOGIC DIAGRAM FOR PARAGRAPH 1.E. COMPLIANCE:

TABLE 9 WORK PACKAGE 5 AND WORK PACKAGE 6 CONDITIONS AND

ACTIONS [Group 1, Configuration 2; Group 2: ]

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

AIRPLANES SHOWN IN DATA MODULE SB B787-A-27-00-0026-00A-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-27-00-0026-00A-932A-D Issue 001, Compliance

Paragraph 5.

SB B787-A-27-00-0026-00A-933A-D Issue 001, Step 2. Work Instructions

Procedure

Group 1, Configuration 2; Group 2:

1. Logic diagrams are provided as an aid only. Information contained in Data Module SB B787-A-27-

00-0026-00A-932A-D, Paragraph 5., Compliance, is the primary source for compliance times. InforNOTE:

mation in Data Module SB B787-A-27-00-0026-00A-933A-D, Step 2., Work Instructions, is the primary source for tasks required for compliance. 

The Conditions, Actions and Compliance times shown in Appendix E apply to each WORK PACKAGE, 5

and 6, independently.

The table below gives the description for the parts and conditions called out in the logic diagram.

Table 1 Description Table

Title Description

PART 5 ELEVATOR INBOARD POWER CONTROL UNIT INTERNAL FLOW TEST

PART 7 REPLACE THE POWER CONTROL UNIT

THE ELEVATOR INBOARD POWER CONTROL UNIT HAS LESS THAN 300

FLIGHT HOURS IN SERVICE

CONDITION 5.1

THE ELEVATOR INBOARD POWER CONTROL UNIT HAS 300 FLIGHT HOURS

OR MORE IN SERVICE

CONDITION 5.2

Applicable To: B787-A-27-00-0026-0EA-931D-D

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Table 1 Description Table

Title Description

THE INTERNAL FLOW THROUGH THE ELEVATOR INBOARD POWER CONTROL UNIT IS GREATER THAN OR EQUAL TO 0.094 GALLONS PER MINUTE

AND IS LESS THAN OR EQUAL TO 0.560 GALLONS PER MINUTE

CONDITION 5.2.1

THE INTERNAL FLOW THROUGH THE ELEVATOR INBOARD POWER CONTROL UNIT IS LESS THAN 0.094 GALLONS PER MINUTE OR IS GREATER

THAN 0.560 GALLONS PER MINUTE

CONDITION 5.2.2

Applicable To: B787-A-27-00-0026-0EA-931D-D

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ICN-B787-A-000061-A-81205-09070-A-01-1

Figure 1 

Applicable To: B787-A-27-00-0026-0EA-931D-D

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Alert Service Bulletin B787-81205-SB270026-00

Appendix F – LOGIC DIAGRAM FOR PARAGRAPH 1.E. COMPLIANCE:

TABLE 10 WORK PACKAGE 7 AND WORK PACKAGE 8 CONDITIONS AND

ACTIONS [Group 1, Configuration 2; Group 2: ]

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

AIRPLANES SHOWN IN DATA MODULE SB B787-A-27-00-0026-00A-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-27-00-0026-00A-932A-D Issue 001, Compliance

Paragraph 5.

SB B787-A-27-00-0026-00A-933A-D Issue 001, Step 2. Work Instructions

Procedure

Group 1, Configuration 2; Group 2:

1. Logic diagrams are provided as an aid only. Information contained in Data Module SB B787-A-27-

00-0026-00A-932A-D, Paragraph 5., Compliance, is the primary source for compliance times. InforNOTE:

mation in Data Module SB B787-A-27-00-0026-00A-933A-D, Step 2., Work Instructions, is the primary source for tasks required for compliance. 

The Conditions, Actions and Compliance times shown in Appendix F apply to each WORK PACKAGE, 7

and 8, independently.

The table below gives the description for the parts and conditions called out in the logic diagram.

Table 1 Description Table

Title Description

PART 6 AILERON INBOARD POWER CONTROL UNIT INTERNAL FLOW TEST

PART 7 REPLACE THE POWER CONTROL UNIT

THE AILERON INBOARD POWER CONTROL UNIT HAS LESS THAN 300

FLIGHT HOURS IN SERVICE

CONDITION 5.3

THE AILERON INBOARD POWER CONTROL UNIT HAS 300 FLIGHT HOURS

OR MORE IN SERVICE

CONDITION 5.4

Applicable To: B787-A-27-00-0026-0FA-931D-D

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Table 1 Description Table

Title Description

THE INTERNAL FLOW THROUGH THE AILERON INBOARD POWER CONTROL

UNIT IS GREATER THAN OR EQUAL TO 0.094 GALLONS PER MINUTE AND

IS LESS THAN OR EQUAL TO 0.297 GALLONS PER MINUTE

CONDITION 5.4.1

THE INTERNAL FLOW THROUGH THE AILERON INBOARD POWER CONTROL

UNIT IS LESS THAN 0.094 GALLONS PER MINUTE OR IS GREATER THAN

0.297 GALLONS PER MINUTE

CONDITION 5.4.2

Applicable To: B787-A-27-00-0026-0FA-931D-D

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ICN-B787-A-000061-A-81205-09071-A-01-1

Figure 1 

Applicable To: B787-A-27-00-0026-0FA-931D-D

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Alert Service Bulletin B787-81205-SB270026-00

Appendix G – TEST SCREENS [Group 1, Configuration 2; Group 2: ]

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

AIRPLANES SHOWN IN DATA MODULE SB B787-A-27-00-0026-00A-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.

Applicable To: B787-A-27-00-0026-0GA-931D-D

Model 787 Issue 001, 25 Nov 2014

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Procedure

Group 1, Configuration 2; Group 2:

1.

ICN-B787-A-000061-A-81205-09072-A-01-1

Figure 1 FLIGHT CONTROL MAINTENANCE PAGES - PAGE 2

Applicable To: B787-A-27-00-0026-0GA-931D-D

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ICN-B787-A-000061-A-81205-09073-A-01-1

Figure 2 GROUND TESTS - SKIP WARMUP AND BLEED SCREEN (TYPICAL - RIGHT AILERON SHOWN)

Applicable To: B787-A-27-00-0026-0GA-931D-D

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ICN-B787-A-000061-A-81205-09074-A-01-1

Figure 3 GROUND TESTS - SURFACE WILL MOVE SCREEN (TYPICAL - RIGHT AILERON SHOWN)

Applicable To: B787-A-27-00-0026-0GA-931D-D

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