## 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**  Issue 002, 13 Jun 2016 B787-81205-SB270026-00 **Publication:**

**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 Unpublished Work.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.

**B787-81205-SB270026-00 TITLE PAGE**  **Issue 002, 13 Jun 2016 Page**  **1 of** **80** EXPORT CONTROLLED ECCN: 9E991 BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET. See title page for details. 2.0 **B787-81205-SB270026-00 Issue 002, 13 Jun 2016**  **AIRCRAFT SERVICE BULLETIN**

## Alert Service Bulletin B787-81205-SB270026-00 **Table of Contents** Page Revision Transmittal Information

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

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

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13

1. Effectivity

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15 A. Airplanes

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

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17 2. Concurrent Requirements

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17 3. Reason

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17 4. Description

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18 5. Compliance

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18 6. Approval

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 24 7. Manpower

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 24 8. Weight and Balance Changes

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27 9. Electrical Load Data

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 28 10. References

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 28 A. Existing Data:

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

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

. . . 28 11. Publications Affected

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 28 12. Interchangeability and Intermixability of Parts

. . . . . . . . . . . . . . . . . . . . . . . . . 28 13. Software Accomplishment Summary

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 28 MATERIAL INFORMATION

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29

1. Material - Price and Availability

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29 2. Industry Support Information

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29 3. Parts Necessary for Each Airplane

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 29 A. Kits/Parts:

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

. . . . . . . . . . . . . . . . . . . . . . . 29 C. Parts Modified and Reidentified:

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

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . 30 4. Parts Necessary to Change Spares

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

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

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

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 32

1. GENERAL INFORMATION

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

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 35 Appendix A

–LOGIC DIAGRAM FOR PARAGRAPH 5., COMPLIANCE: TABLE 5 LEFT, RIGHT AND

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

. . . . . . 59 Appendix B

–LOGIC DIAGRAM FOR PARAGRAPH 5., COMPLIANCE: TABLE 6 LEFT HYDRAULIC

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

. . . . . . . . . . . . . . . . . 62

**B787-81205-SB270026-00 TABLE OF CONTENTS**  **Issue 002, 13 Jun 2016 Page** **2 of** **80** EXPORT CONTROLLED ECCN: 9E991 BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET. See title page for details. **B787-81205-SB270026-00 Issue 002, 13 Jun 2016**  **AIRCRAFT SERVICE BULLETIN**Appendix C

–LOGIC DIAGRAM FOR PARAGRAPH 5., COMPLIANCE: TABLE 7 RIGHT HYDRAULIC SYSTEM FLUID TEST [Group 1, Configuration 2; Group 2: ]

. . . . . . . . . . . . . . . . . 65 Appendix D

–LOGIC DIAGRAM FOR PARAGRAPH 5., 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: ]

. . . . . . 68 Appendix E

–LOGIC DIAGRAM FOR PARAGRAPH 5., COMPLIANCE: TABLE 9 WORK PACKAGE 5

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

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 71 Appendix F

–LOGIC DIAGRAM FOR PARAGRAPH 5., COMPLIANCE: TABLE 10 WORK PACKAGE 7

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

. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 74 Appendix G

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

. . . . . . . . . . . . . . . . . . . . 77

**B787-81205-SB270026-00 TABLE OF CONTENTS**  **Issue 002, 13 Jun 2016 Page** **3 of** **80** EXPORT CONTROLLED ECCN: 9E991 BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET. See title page for details. **B787-81205-SB270026-00 Issue 002, 13 Jun 2016**  **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 **Used In ICN**  B787-A-27-00-0026-00A-931C-D Issue 002 ICN-B787-A-000061-A-81205-09065-A-01-1 B787-A-27-00-0026-0AA-931D-D Issue 002 ICN-B787-A-000061-A-81205-09066-A-02-1 B787-A-27-00-0026-0BA-931D-D Issue 002 ICN-B787-A-000061-A-81205-09067-A-02-1 B787-A-27-00-0026-0CA-931D-D Issue 002 ICN-B787-A-000061-A-81205-09068-A-02-1 B787-A-27-00-0026-0DA-931D-D Issue 002 ICN-B787-A-000061-A-81205-09069-A-02-1 B787-A-27-00-0026-0EA-931D-D Issue 002 ICN-B787-A-000061-A-81205-09070-A-02-1 B787-A-27-00-0026-0FA-931D-D Issue 002 ICN-B787-A-000061-A-81205-09071-A-02-1 B787-A-27-00-0026-0GA-931D-D Issue 002 ICN-B787-A-000061-A-81205-09072-A-01-1 B787-A-27-00-0026-0GA-931D-D Issue 002 ICN-B787-A-000061-A-81205-09073-A-01-1 B787-A-27-00-0026-0GA-931D-D Issue 002 ICN-B787-A-000061-A-81205-09074-A-01-1

**B787-A-27-00-0026-00A-00AA-D Applicable To:**  **Issue 002, 13 Jun 2016 End of data module**  Model 787 See Applicability of this data module **Page 4** **of 80**  EXPORT CONTROLLED ECCN: 9E991 BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET. See title page for details. **B787-81205-SB270026-00 Issue 002, 13 Jun 2016**  **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 **Issue Date Issue Status**  **Issue Data Module** 
**– Information Name**  2016-06-13 Changed 002 B787-A-27-00-0026-00A-00AA-D

–List of Illustrations 2016-06-13 Changed 002 B787-A-27-00-0026-00A-00SA-D

–List of Effective Data Modules 2016-06-13 New 001 B787-A-27-00-0026-00A-931B-D

–Revision Transmittal Information 2016-06-13 Changed 002 B787-A-27-00-0026-00A-931C-D

–Summary 2016-06-13 Changed 002 B787-A-27-00-0026-00A-932A-D

–PLANNING INFORMATION 2016-06-13 Changed 002 B787-A-27-00-0026-00A-934A-D

–MATERIAL INFORMATION 2016-06-13 Changed 002 B787-A-27-00-0026-00A-933A-D

– ACCOMPLISHMENT INSTRUCTIONS 2016-06-13 Changed 002 B787-A-27-00-0026-0AA-931D-D

–Appendix A

–LOGIC DIAGRAM FOR PARAGRAPH 5., COMPLIANCE: TABLE 5 LEFT, RIGHT AND CENTER HYDRAULIC SYSTEM FLUID MARKER INSTALLATION [Group 1-2:] 2016-06-13 Changed 002 B787-A-27-00-0026-0BA-931D-D

–Appendix B

–LOGIC DIAGRAM FOR PARAGRAPH 5., COMPLIANCE: TABLE 6 LEFT HYDRAULIC SYSTEM FLUID TEST [Group 1, Configuration 2; Group 2: ] 2016-06-13 Changed 002 B787-A-27-00-0026-0CA-931D-D

–Appendix C

–LOGIC DIAGRAM FOR PARAGRAPH 5., COMPLIANCE: TABLE 7 RIGHT HYDRAULIC SYSTEM FLUID TEST [Group 1, Configuration 2; Group 2: ] 2016-06-13 Changed 002 B787-A-27-00-0026-0DA-931D-D

–Appendix D

–LOGIC DIAGRAM FOR PARAGRAPH 5., 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: ] 2016-06-13 Changed 002 B787-A-27-00-0026-0EA-931D-D

–Appendix E

–LOGIC DIAGRAM FOR PARAGRAPH 5., COMPLIANCE: TABLE 9 WORK PACKAGE 5 AND WORK PACKAGE 6 CONDITIONS AND ACTIONS [Group 1, Configuration 2; Group 2: ]
**B787-A-27-00-0026-00A-00SA-D Applicable To:**  **Issue 002, 13 Jun 2016** Model 787 See Applicability of this data module **Page 5** **of 80**  EXPORT CONTROLLED ECCN: 9E991 BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET. See title page for details. **B787-81205-SB270026-00 Issue 002, 13 Jun 2016**  **AIRCRAFT SERVICE BULLETIN**Table 1 List of Effective Data Modules - Alert Service Bulletin B787-81205-SB270026-00 **Issue Date Issue Status**  **Issue Data Module** 
**– Information Name**  2016-06-13 Changed 002 B787-A-27-00-0026-0FA-931D-D

–Appendix F

–LOGIC DIAGRAM FOR PARAGRAPH 5., COMPLIANCE: TABLE 10 WORK PACKAGE 7 AND WORK PACKAGE 8 CONDITIONS AND ACTIONS [Group 1, Configuration 2; Group 2: ] 2016-06-13 Changed 002 B787-A-27-00-0026-0GA-931D-D

– Appendix G

–

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

**B787-A-27-00-0026-00A-00SA-D Applicable To:**  **Issue 002, 13 Jun 2016 End of data module**  Model 787 See Applicability of this data module **Page 6** **of 80**  EXPORT CONTROLLED ECCN: 9E991 BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET. See title page for details. **B787-81205-SB270026-00 Issue 002, 13 Jun 2016**  **AIRCRAFT SERVICE BULLETIN**

## Alert Service Bulletin B787-81205-SB270026-00 **Revision Transmittal 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 **Title Reference**  Airplanes SB B787-A-27-00-0026-00A-932A-D Issue 002, Paragraph 1.A. 

## Description **Group 1-2:** This revision includes all pages of the service bulletin. **1. COMPLIANCE INFORMATION RELATED TO THIS REVISION**  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. Effects of this revision on Airplanes on which Issue 001 was previously done: None. **2. REASON FOR REVISION**  This issue is sent to correct typographical errors and make corrections to the accomplishment instructions. These sections were changed: 1. Accomplishment Instructions - Paragraph 2, Work Instructions, I(1), Step (c): Updated Step. 2. Accomplishment Instructions - Paragraph 2, Work Instructions, J(1)(a) 2), Step c): Updated Step. 3. Accomplishment Instructions - Paragraph 2, Work Instructions, J(1)(a) 2), Step e): Added Step. 4. Accomplishment Instructions - Paragraph 2, Work Instructions, J(1) Step (b): Added Step. 5. Accomplishment Instructions - Paragraph 2, Work Instructions, J(1)(c) 2), Step e): Added Step. 6. Accomplishment Instructions - Paragraph 2, Work Instructions, J(1)(c) 2), Steps n), o), p): Added Warning note.

**B787-A-27-00-0026-00A-931B-D Applicable To:**  **Issue 001, 13 Jun 2016** Model 787 See Applicability of this data module **Page 7** **of 80**  EXPORT CONTROLLED ECCN: 9E991 BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET. See title page for details. **B787-81205-SB270026-00 Issue 002, 13 Jun 2016**  **AIRCRAFT SERVICE BULLETIN**7. Accomplishment Instructions - Paragraph 2, Work Instructions, J(1)(c) 2), Steps q)<5><a>, q)<5><b>,

q)<6>: Updated step. 8. Accomplishment Instructions - Paragraph 2, Work Instructions, J(1)(c) 2), Step q)<7>: Added Step and Warning note. 9. Accomplishment Instructions - Paragraph 2, Work Instructions, J(1)(c) 2), Step r): Added Step. 10. Accomplishment Instructions - Paragraph 2, Work Instructions, M(2), Step (a): Added Step. 11. Accomplishment Instructions - Paragraph 2, Work Instructions, N(4), Step (a): Added Step. 12. Accomplishment Instructions - Paragraph 2, Work Instructions, N(4), Step (b): Corrected reference. 13. Accomplishment Instructions - Paragraph 2, Work Instructions, N(4), Step (g): Corrected reference. 14. Accomplishment Instructions - Paragraph 2, Work Instructions, N(4), Step (h) 4): Added Step. 15. Appendix A: Updated title and logic diagram. 16. Appendix B: Updated title and logic diagram. 17. Appendix C: Updated title and logic diagram. 18. Appendix D: Updated title and logic diagram. 19. Appendix E: Updated title and logic diagram.. 20. Appendix F: Updated title and logic diagram. Change marks are added, except in Data Module SB B787-A-27-00-0026-00A-932A-D, Paragraph 1.A., Airplanes and format changes, to show the location of all content changes. **3. REVISION HISTORY**  Table 1 November 25, 2014 Issue 1: June 13, 2016 Issue 2:

**B787-A-27-00-0026-00A-931B-D Applicable To:**  **Issue 001, 13 Jun 2016 End of data module**  Model 787 See Applicability of this data module **Page 8** **of 80**  EXPORT CONTROLLED ECCN: 9E991 BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET. See title page for details. **B787-81205-SB270026-00 Issue 002, 13 Jun 2016**  **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 **Title Reference**  Spares Affected SB B787-A-27-00-0026-00A-932A-D Issue 002, Paragraph 1.B. Compliance SB B787-A-27-00-0026-00A-932A-D Issue 002, Paragraph 5. Weight and Balance Changes SB B787-A-27-00-0026-00A-932A-D Issue 002, Paragraph 8. Electrical Load Data SB B787-A-27-00-0026-00A-932A-D Issue 002, Paragraph 9. Publications Affected SB B787-A-27-00-0026-00A-932A-D Issue 002, Paragraph 11. Kits/Parts SB B787-A-27-00-0026-00A-934A-D Issue 002, Paragraph 3.A. Parts and Materials Supplied by the Operator SB B787-A-27-00-0026-00A-934A-D Issue 002, Paragraph 3.B. Special Tooling Necessary to do this Service Bulletin SB B787-A-27-00-0026-00A-934A-D Issue 002, Paragraph 6. Effectivity SB B787-A-27-00-0026-00A-932A-D Issue 002, Paragraph 1. Manpower SB B787-A-27-00-0026-00A-932A-D Issue 002, Paragraph 7. Material - Price and Availability SB B787-A-27-00-0026-00A-934A-D Issue 002, Paragraph 1.

**B787-A-27-00-0026-00A-931C-D Applicable To:**  **Issue 002, 13 Jun 2016** Model 787 See Applicability of this data module **Page 9** **of 80**  EXPORT CONTROLLED ECCN: 9E991 BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET. See title page for details. **B787-81205-SB270026-00 Issue 002, 13 Jun 2016**  **AIRCRAFT SERVICE BULLETIN Title** 

**Reference** 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 **Note Dependency Type**  **Description Service Bulletin Issue**  Prerequisite HYDRAULIC POWER - Hydraulic System - Hy- Jet V Marker Installation SB B787-81205-SB290022-00Issue 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 surethe 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 **Data Module Reference Affected**  **Planning Data** Data Module SB B787-A-27-00-0026-00A-932AD, Paragraph 1.B., Spares Affected No Spares Affected
Data Module SB B787-A-27-00-0026-00A-932AD, Paragraph 5., Compliance Yes AD Related
Data Module SB B787-A-27-00-0026-00A-932AD, Paragraph 8., Weight and Balance Changes No Weight and Balance Changed

**B787-A-27-00-0026-00A-931C-D Applicable To:**  **Issue 002, 13 Jun 2016** Model 787 See Applicability of this data module **Page 10** **of 80**  EXPORT CONTROLLED ECCN: 9E991 BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET. See title page for details. **B787-81205-SB270026-00 Issue 002, 13 Jun 2016**  **AIRCRAFT SERVICE BULLETIN**Table 2 **Data Module Reference Affected**  **Planning Data** Data Module SB B787-A-27-00-0026-00A-932AD, Paragraph 9., Electrical Load Data No Electrical Load Changed
Data Module SB B787-A-27-00-0026-00A-932AD, Paragraph 11., Publications Affected Yes Publications Affected
Data Module SB B787-A-27-00-0026-00A-932AD, Paragraph 11., Publications Affected No Airplane Flight Operations Affected (Flight CrewOperations Manual and/or FAA Approved Airplane Flight Manual) Data Module SB B787-A-27-00-0026-00A-934AD, Paragraph 3.A., Kits/Parts Yes Kits/Parts Required
Data Module SB B787-A-27-00-0026-00A-934AD, Paragraph 3.B., Parts and Materials Supplied by the Operator Yes Operator Supplied Parts/Material

Data Module SB B787-A-27-00-0026-00A-934AD, Paragraph 6., Special Tooling Necessary to do this Service Bulletin Yes Special Tooling Required

Boeing Service Related Problem (SRP) 787 SRP-27-0227 is related to this service bulletin. **3. ACTION**  (CN-AC40116J) 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.

**B787-A-27-00-0026-00A-931C-D Applicable To:**  **Issue 002, 13 Jun 2016** Model 787 See Applicability of this data module **Page 11** **of 80**  EXPORT CONTROLLED ECCN: 9E991 BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET. See title page for details. **B787-81205-SB270026-00 Issue 002, 13 Jun 2016**  **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

**B787-A-27-00-0026-00A-931C-D Applicable To:**  **Issue 002, 13 Jun 2016 End of data module**  Model 787 See Applicability of this data module **Page 12** **of 80**  EXPORT CONTROLLED ECCN: 9E991 BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET. See title page for details. **B787-81205-SB270026-00 Issue 002, 13 Jun 2016**  **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

**Title Reference**  Work Instructions SB B787-A-27-00-0026-00A-933A-D Issue 002, Step 2. Alert Service Bulletin B787-81205-SB270026-00

–Appendix A

– LOGIC SB B787-A-27-00-0026-0AA-931D-D Issue 002 DIAGRAM FOR PARAGRAPH 5., 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 002 DIAGRAM FOR PARAGRAPH 5., 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 002 DIAGRAM FOR PARAGRAPH 5., 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 002 DIAGRAM FOR PARAGRAPH 5., 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 002 DIAGRAM FOR PARAGRAPH 5., COMPLIANCE: TABLE 9 WORK PACKAGE 5 AND WORK

**B787-A-27-00-0026-00A-932A-D Applicable To:**  **Issue 002, 13 Jun 2016** Model 787 See Applicability of this data module **Page 13** **of 80**  EXPORT CONTROLLED ECCN: 9E991 BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET. See title page for details. **B787-81205-SB270026-00 Issue 002, 13 Jun 2016**  **AIRCRAFT SERVICE BULLETIN Title** 

**Reference** 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 002 DIAGRAM FOR PARAGRAPH 5., 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

JACKING 787 AMM 07-11-01 HYDRAULIC SYSTEMS 787 AMM 12-12-01 TUBE 787 AMM 20-10-09 PRIMARY FLIGHT CONTROL FUNCTION 787 AMM 27-02-00 AILERON POWER CONTROL UNIT 787 AMM 27-11-19 ELEVATOR POWER CONTROL UNIT 787 AMM 27-31-09 HYDRAULIC SYSTEM 787 AMM 29-11-00 RAM AIR TURBINE SYSTEM 787 AMM 29-21-00 LANDING GEAR DOOR SAFETY 787 AMM 32-00-15 LANDING GEAR DOWNLOCK PINS 787 AMM 32-00-30 CENTRAL MAINTENANCE COMPUTING FUNCTION 787 AMM 45-11-00
HORIZONTAL STABILIZER TRAILING EDGE SKIN PANELS 787 AMM 55-16-01
FIXED TRAILING EDGE PANELS 787 AMM 57-51-10 HYDRAULIC POWER - Hydraulic System - HyJet V Marker Installation SB B787-81205-SB290022-00

**B787-A-27-00-0026-00A-932A-D Applicable To:**  **Issue 002, 13 Jun 2016** Model 787 See Applicability of this data module **Page 14** **of 80**  EXPORT CONTROLLED ECCN: 9E991 BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET. See title page for details. **B787-81205-SB270026-00 Issue 002, 13 Jun 2016**  **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 **DESCRIPTION CONFIGURATION**  **GROUP** Airplanes delivered with HyJet V hydraulic fluid.

- 1 Airplanes that have only been serviced with HyJet V.

1 Airplanes that have been serviced with hydraulic fluids other than

HyJet V or hydraulic fluid used during system servicing cannot be determined. 2

Airplanes delivered with Skydrol LD-4.

- 2 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 **Group Variable Number**  1 ZA004-ZA006 2 ZA100-ZA105 2 ZA116-ZA120 1 ZA121-ZA124 2 ZA135 1 ZA136 1 ZA175-ZA176 2 ZA177-ZA185 1 ZA186-ZA189 1 ZA215-ZA220 1 ZA230-ZA232

**B787-A-27-00-0026-00A-932A-D Applicable To:**  **Issue 002, 13 Jun 2016** Model 787 See Applicability of this data module **Page 15** **of 80**  EXPORT CONTROLLED ECCN: 9E991 BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET. See title page for details. **B787-81205-SB270026-00 Issue 002, 13 Jun 2016**  **AIRCRAFT SERVICE BULLETIN**Table 2 **Group Variable Number**  2 ZA233 1 ZA234-ZA235 2 ZA236-ZA241 1 ZA242-ZA245 1 ZA260 2 ZA261-ZA264 1 ZA265-ZA267 2 ZA270-ZA273 1 ZA274-ZA275 2 ZA285-ZA290 1 ZA291-ZA295 2 ZA317-ZA319 1 ZA320 1 ZA327 1 ZA334 2 ZA380 1 ZA381-ZA383 2 ZA384 1 ZA385-ZA389 1 ZA430 2 ZA431 1 ZA432-ZA437 1 ZA445-ZA448 2 ZA450-ZA451 1 ZA452-ZA456 2 ZA460-ZA465 1 ZA466-ZA474 2 ZA506-ZA513 1 ZA514-ZA516 2 ZA536-ZA538

**B787-A-27-00-0026-00A-932A-D Applicable To:**  **Issue 002, 13 Jun 2016** Model 787 See Applicability of this data module **Page 16** **of 80**  EXPORT CONTROLLED ECCN: 9E991 BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET. See title page for details. **B787-81205-SB270026-00 Issue 002, 13 Jun 2016**  **AIRCRAFT SERVICE BULLETIN**Table 2 **Group Variable Number**  1 ZA539-ZA541 1 ZA560-ZA565 2 ZA576 1 ZA577-ZA580 1 ZA586 1 ZA588 1 ZA610-ZA612 1 ZA650-ZA651 1 ZA655-ZA656 1 ZA778
**B. Spares Affected**  None. **2. Concurrent Requirements**  Table 3 Boeing Service Bulletins Dependencies **Note Dependency Type**  **Description Service Bulletin Issue**  Prerequisite HYDRAULIC POWER - Hydraulic System - Hy- Jet V Marker Installation SB B787-81205-SB290022-00Issue 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. Issue 2 is sent to correct typographical errors and make corrections to the accomplishment instructions..

**B787-A-27-00-0026-00A-932A-D Applicable To:**  **Issue 002, 13 Jun 2016** Model 787 See Applicability of this data module **Page 17** **of 80**  EXPORT CONTROLLED ECCN: 9E991 BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET. See title page for details. **B787-81205-SB270026-00 Issue 002, 13 Jun 2016**  **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:** Effects of this revision on Airplanes on which Issue 001 was previously done: None. The work in this service bulletin is done in the maintenance zone(s) given below. Table 4 **Affected Maintenance Zones Zone**  **Model** 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 ModuleAppendix 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.

**B787-A-27-00-0026-00A-932A-D Applicable To:**  **Issue 002, 13 Jun 2016** Model 787 See Applicability of this data module **Page 18** **of 80**  EXPORT CONTROLLED ECCN: 9E991 BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET. See title page for details. **B787-81205-SB270026-00 Issue 002, 13 Jun 2016**  **AIRCRAFT SERVICE BULLETIN**Table 5 Left, Right and Center Hydraulic System Fluid Marker Installation **Repeat Interval (Not to Exceed)**  **Compliance Time Action**  **Condition**

- 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)**  **Compliance Time Action**  **Condition**

- 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): DoPART 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.

**B787-A-27-00-0026-00A-932A-D Applicable To:**  **Issue 002, 13 Jun 2016** Model 787 See Applicability of this data module **Page 19** **of 80**  EXPORT CONTROLLED ECCN: 9E991 BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET. See title page for details. **B787-81205-SB270026-00 Issue 002, 13 Jun 2016**  **AIRCRAFT SERVICE BULLETIN Group 1, Configuration 2; Group 2:**  Table 7 Right Hydraulic System Fluid Test **Repeat Interval (Not to Exceed)**  **Compliance Time Action**  **Condition**

- 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): DoPART 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.

**B787-A-27-00-0026-00A-932A-D Applicable To:**  **Issue 002, 13 Jun 2016** Model 787 See Applicability of this data module **Page 20** **of 80**  EXPORT CONTROLLED ECCN: 9E991 BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET. See title page for details. **B787-81205-SB270026-00 Issue 002, 13 Jun 2016**  **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)**  **Compliance Time Action**  **Condition**

- 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): DoWORK 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): DoPART 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.
**B787-A-27-00-0026-00A-932A-D Applicable To:**  **Issue 002, 13 Jun 2016** Model 787 See Applicability of this data module **Page 21** **of 80**  EXPORT CONTROLLED ECCN: 9E991 BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET. See title page for details. **B787-81205-SB270026-00 Issue 002, 13 Jun 2016**  **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)**  **Compliance Time Action**  **Condition**
*[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)**  **Compliance Time Action**  **Condition**

- - No further action required for the applicable work package.CONDITION 5.1: THE ELEVATOR INBOARD POWER CONTROL UNIT HAS LESS THAN300 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 FLIGHTHOURS 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.

**B787-A-27-00-0026-00A-932A-D Applicable To:**  **Issue 002, 13 Jun 2016** Model 787 See Applicability of this data module **Page 22** **of 80**  EXPORT CONTROLLED ECCN: 9E991 BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET. See title page for details. **B787-81205-SB270026-00 Issue 002, 13 Jun 2016**  **AIRCRAFT SERVICE BULLETIN**Table 9 WORK PACKAGE 5 and WORK PACKAGE 6 Conditions and Actions **Repeat Interval (Not to Exceed)**  **Compliance Time Action**  **Condition**

- - 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)**  **Compliance Time Action**  **Condition**

- - 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.

**B787-A-27-00-0026-00A-932A-D Applicable To:**  **Issue 002, 13 Jun 2016** Model 787 See Applicability of this data module **Page 23** **of 80**  EXPORT CONTROLLED ECCN: 9E991 BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET. See title page for details. **B787-81205-SB270026-00 Issue 002, 13 Jun 2016**  **AIRCRAFT SERVICE BULLETIN**Table 10 WORK PACKAGE 7 and WORK PACKAGE 8 Conditions and Actions **Repeat Interval (Not to Exceed)**  **Compliance Time Action**  **Condition**

- - 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 EuropeanAviation 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

**B787-A-27-00-0026-00A-932A-D Applicable To:**  **Issue 002, 13 Jun 2016** Model 787 See Applicability of this data module **Page 24** **of 80**  EXPORT CONTROLLED ECCN: 9E991 BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET. See title page for details. **B787-81205-SB270026-00 Issue 002, 13 Jun 2016**  **AIRCRAFT SERVICE BULLETIN**Table 11 WORK PACKAGE 1: MARKER INSTALLATION **Elapsed Hours Task Hours**  **Number of Persons Task**  *[1] *[1] *[1] Install markers in accordance with SB B787-81205-SB290022-00 Issue 001 or later approved Issue. *[1] *[2] *[1] *[2] TOTAL FOR EACH AIRPLANE *[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 **Elapsed Hours Task Hours**  **Number of Persons Task**  4.50 *[1] 13.50 *[1] 3 PART 1 *[1]
1.50 *[1] 3.00 *[1] 2 PART 2 *[1] 0.50 1.00 2 PART 3 4.50 *[2] 13.50 *[2] 3 PART 4 *[2] 0.50 1.00 TOTAL FOR EACH AIRPLANE *[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 **Elapsed Hours Task Hours**  **Number of Persons Task**  4.50 *[1] 13.50 *[1] 3 PART 1 *[1]
1.50 *[1] 3.00 *[1] 2 *[1] PART 2 *[1] 0.50 1.00 2 PART 3 4.50 *[2] 13.50 *[2] 3 PART 4 *[2] 0.50 1.00 TOTAL FOR EACH AIRPLANE *[1] Add Task Hours and Elapsed Hours for Group 2, Configuration 2. *[2] Add Task Hours and Elapsed Hours for CONDITION 4.

**B787-A-27-00-0026-00A-932A-D Applicable To:**  **Issue 002, 13 Jun 2016** Model 787 See Applicability of this data module **Page 25** **of 80**  EXPORT CONTROLLED ECCN: 9E991 BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET. See title page for details. **B787-81205-SB270026-00 Issue 002, 13 Jun 2016**  **AIRCRAFT SERVICE BULLETIN 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 **Elapsed Hours Task Hours**  **Number of Persons Task**  5.50 *[1] 16.50 *[1] 3 PART 1 *[1]
3.75 *[1] 7.50 *[1] 2 PART 2 *[1] 0.50 1.00 2 PART 3 5.50 *[2] 16.50 *[2] 3 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 *[3] TOTAL FOR AIRPLANE *[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 **Elapsed Hours Task Hours**  **Number of Persons Task**  2.00 *[1] 4.00 *[1] 2 PART 5 *[1]
14.50 *[2] 29.00 *[2] 2 PART 7 *[2] *[3] *[3] TOTAL FOR AIRPLANE *[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.

**B787-A-27-00-0026-00A-932A-D Applicable To:**  **Issue 002, 13 Jun 2016** Model 787 See Applicability of this data module **Page 26** **of 80**  EXPORT CONTROLLED ECCN: 9E991 BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET. See title page for details. **B787-81205-SB270026-00 Issue 002, 13 Jun 2016**  **AIRCRAFT SERVICE BULLETIN Group 1, Configuration 2; Group 2:**  Table 16 WORK PACKAGE 6: RIGHT ELEVATOR INBOARD POWER CONTROL UNIT INTERNAL FLOW TEST **Elapsed Hours Task Hours**  **Number of Persons Task**  2.00 *[1] 4.00 *[1] 2 PART 5 *[1]
14.50 *[2] 29.00 *[2] 2 PART 7 *[2] *[3] *[3] TOTAL FOR AIRPLANE *[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 **Elapsed Hours**

**Task Hours Number of Persons**  **Task** 2.00 *[1] 4.00 *[1] 2 PART 6 *[1]
14.50 *[2] 29.00 *[2] 2 PART 7 *[2] *[3] *[3] TOTAL FOR AIRPLANE *[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 **Elapsed Hours Task Hours**  **Number of Persons Task**  2.00 *[1] 4.00 *[1] 2 PART 6 *[1]
14.50 *[2] 29.00 *[2] 2 PART 7 *[2] *[3] *[3] TOTAL FOR AIRPLANE *[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.

**B787-A-27-00-0026-00A-932A-D Applicable To:**  **Issue 002, 13 Jun 2016** Model 787 See Applicability of this data module **Page 27** **of 80**  EXPORT CONTROLLED ECCN: 9E991 BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET. See title page for details. **B787-81205-SB270026-00 Issue 002, 13 Jun 2016**  **AIRCRAFT SERVICE BULLETIN 9.**  **Electrical Load Data**

Not changed. **10. References**  **A. Existing Data:**  1. Change Notice CN-AA40116J, CN-AC40116J 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-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 **Chapter-Section Publication**  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

27-10 787 Fault Isolation Manual 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.

**B787-A-27-00-0026-00A-932A-D Applicable To:**  **Issue 002, 13 Jun 2016 End of data module**  Model 787 See Applicability of this data module **Page 28** **of 80**  EXPORT CONTROLLED ECCN: 9E991 BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET. See title page for details. **B787-81205-SB270026-00 Issue 002, 13 Jun 2016**  **AIRCRAFT SERVICE BULLETIN**

## 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 **Title Reference**  References SB B787-A-27-00-0026-00A-932A-D Issue 002, 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 **Notes Name**  **QTY Part Number /**  **Specification** Group 1, Configuration 2 and Group 2 only. *[1] Hydraulic Fluid 350 gal- lons HyJet V

**B787-A-27-00-0026-00A-934A-D Applicable To:**  **Issue 002, 13 Jun 2016** Model 787 See Applicability of this data module **Page 29** **of 80**  EXPORT CONTROLLED ECCN: 9E991 BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET. See title page for details. **B787-81205-SB270026-00 Issue 002, 13 Jun 2016**  **AIRCRAFT SERVICE BULLETIN**Table 1 **Notes Name**  **QTY Part Number /**  **Specification** *[1]ExxonMobil Oil Corporation. Address: Anderol Specialty Lubricants, a Division of Chemtura, 215 Merry Lane, East Hanover, NJ 07936, USA. 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 Ser vice Bulletin (US**  **Dollars) Name**  **Tool Kit Number**

$340.00

HYDRAULIC FLUID CHECK 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.

**B787-A-27-00-0026-00A-934A-D Applicable To:**  **Issue 002, 13 Jun 2016** Model 787 See Applicability of this data module **Page 30** **of 80**  EXPORT CONTROLLED ECCN: 9E991 BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET. See title page for details. **B787-81205-SB270026-00 Issue 002, 13 Jun 2016**  **AIRCRAFT SERVICE BULLETIN**Table 3 **Name Tool Kit Number**  HYDRAULIC FLUID CHECK TOOL TSF036Z0229 *[1]
*[1] Group 1, Configuration 2 and Group 2 only.

**B787-A-27-00-0026-00A-934A-D Applicable To:**  **Issue 002, 13 Jun 2016 End of data module**  Model 787 See Applicability of this data module **Page 31** **of 80**  EXPORT CONTROLLED ECCN: 9E991 BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET. See title page for details. **B787-81205-SB270026-00 Issue 002, 13 Jun 2016**  **AIRCRAFT SERVICE BULLETIN**

## 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 **Title Reference**  References SB B787-A-27-00-0026-00A-932A-D Issue 002, Paragraph 10. Manpower SB B787-A-27-00-0026-00A-932A-D Issue 002, Paragraph 7. Compliance SB B787-A-27-00-0026-00A-932A-D Issue 002, 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 002

HYDRAULIC POWER - Hydraulic System - HyJet V Marker Installation SB B787-81205-SB290022-00 Issue 001
HYDRAULIC SYSTEM 787 AMM 29-11-00 JACKING 787 AMM 07-11-01 RAM AIR TURBINE SYSTEM 787 AMM 29-21-00 LANDING GEAR DOWNLOCK PINS 787 AMM 32-00-30 LANDING GEAR DOOR SAFETY 787 AMM 32-00-15 HYDRAULIC SYSTEMS 787 AMM 12-12-01 PRIMARY FLIGHT CONTROL FUNCTION 787 AMM 27-02-00 HORIZONTAL STABILIZER TRAILING EDGE SKIN PANELS 787 AMM 55-16-01

TUBE 787 AMM 20-10-09 CENTRAL MAINTENANCE COMPUTING FUNCTION 787 AMM 45-11-00

**B787-A-27-00-0026-00A-933A-D Applicable To:**  **Issue 002, 13 Jun 2016** Model 787 See Applicability of this data module **Page 32** **of 80**  EXPORT CONTROLLED ECCN: 9E991 BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET. See title page for details. **B787-81205-SB270026-00 Issue 002, 13 Jun 2016**  **AIRCRAFT SERVICE BULLETIN Title** 

**Reference** FIXED TRAILING EDGE PANELS 787 AMM 57-51-10 ELEVATOR POWER CONTROL UNIT 787 AMM 27-31-09 AILERON POWER CONTROL UNIT 787 AMM 27-11-19 

## 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.

**B787-A-27-00-0026-00A-933A-D Applicable To:**  **Issue 002, 13 Jun 2016** Model 787 See Applicability of this data module **Page 33** **of 80**  EXPORT CONTROLLED ECCN: 9E991 BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET. See title page for details. **B787-81205-SB270026-00 Issue 002, 13 Jun 2016**  **AIRCRAFT SERVICE BULLETIN**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 servicebulletin. 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

**B787-A-27-00-0026-00A-933A-D Applicable To:**  **Issue 002, 13 Jun 2016** Model 787 See Applicability of this data module **Page 34** **of 80**  EXPORT CONTROLLED ECCN: 9E991 BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET. See title page for details. **B787-81205-SB270026-00 Issue 002, 13 Jun 2016**  **AIRCRAFT SERVICE BULLETIN**be used if the RC steps can still be done as specified, and the airplane can be put back in aserviceable 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**  No further action required for WORK PACKAGE 2. 1) **(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**  No further action required for WORK PACKAGE 3. 1)

**B787-A-27-00-0026-00A-933A-D Applicable To:**  **Issue 002, 13 Jun 2016** Model 787 See Applicability of this data module **Page 35** **of 80**  EXPORT CONTROLLED ECCN: 9E991 BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET. See title page for details. **B787-81205-SB270026-00 Issue 002, 13 Jun 2016**  **AIRCRAFT SERVICE BULLETIN (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** Check maintenance records to find the left elevator inboard power control unit time in service. (1) **(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.

**B787-A-27-00-0026-00A-933A-D Applicable To:**  **Issue 002, 13 Jun 2016** Model 787 See Applicability of this data module **Page 36** **of 80**  EXPORT CONTROLLED ECCN: 9E991 BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET. See title page for details. **B787-81205-SB270026-00 Issue 002, 13 Jun 2016**  **AIRCRAFT SERVICE BULLETIN (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.

**B787-A-27-00-0026-00A-933A-D Applicable To:**  **Issue 002, 13 Jun 2016** Model 787 See Applicability of this data module **Page 37** **of 80**  EXPORT CONTROLLED ECCN: 9E991 BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET. See title page for details. **B787-81205-SB270026-00 Issue 002, 13 Jun 2016**  **AIRCRAFT SERVICE BULLETIN 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** Check maintenance records to find the left aileron inboard power control unit time in service. (1) **(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** Check maintenance records to find the right aileron inboard power control unit time in service. (1) **(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.

**B787-A-27-00-0026-00A-933A-D Applicable To:**  **Issue 002, 13 Jun 2016** Model 787 See Applicability of this data module **Page 38** **of 80**  EXPORT CONTROLLED ECCN: 9E991 BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET. See title page for details. **B787-81205-SB270026-00 Issue 002, 13 Jun 2016**  **AIRCRAFT SERVICE BULLETIN <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.Do not activate the landing gear doors after replacing the hydraulic fluid. Leave the airplane on jacks after replacing the hydraulic fluid. **Group 2, Configuration 2: J.**  **PART 2: CYCLE HYDRAULIC FLUID** Do these steps to cycle the hydraulic fluid : (1) (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: **CB Designation**  CE2711305 AIL REU LOB PWR CE2761413 AUTO SPDBRK ACT CTRLR PWR CE2731307 ELEV REU LOB PWR CE2711206 FLAPERON REU LIB PWR CE2711306 FLAPERON REU ROB PWR

**B787-A-27-00-0026-00A-933A-D Applicable To:**  **Issue 002, 13 Jun 2016** Model 787 See Applicability of this data module **Page 39** **of 80**  EXPORT CONTROLLED ECCN: 9E991 BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET. See title page for details. **B787-81205-SB270026-00 Issue 002, 13 Jun 2016**  **AIRCRAFT SERVICE BULLETIN**Table 1 WORK PACKAGE 2: **CB Designation**  CE2721308 RUD REU MID PWR CE7834811 T/R DIRECTIONAL CTRL VLV-L ENGINE CE7834813 T/R LEVEL INTLK-L ENGINE CE7834814 T/R TRK LOCK VLV-L ENGINE
Table 2 WORK PACKAGE 3: **CB Designation**  CE2711405 AIL REU ROB PWR CE2761413 AUTO SPDBRK ACT CTRLR PWR CE2731407 ELEV REU ROB PWR CE2711406 FLAPERON REU LOB PWR CE2721408 RUD REU LWR PWR CE7834821 T/R DIRECTIONAL CTRL VLV-R ENGINE CE7834823 T/R LEVEL INTLK-R ENGINE CE7834824 T/R TRK LOCK VLV-R ENGINE 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. Do not dry-motor the engine. **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) Depressurize the hydraulic system. Refer to 787 AMM 29-11-00 as an accepted procedure. f) 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.

**B787-A-27-00-0026-00A-933A-D Applicable To:**  **Issue 002, 13 Jun 2016** Model 787 See Applicability of this data module **Page 40** **of 80**  EXPORT CONTROLLED ECCN: 9E991 BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET. See title page for details. **B787-81205-SB270026-00 Issue 002, 13 Jun 2016**  **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. g) 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. h) 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. i) 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. j) 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.

**B787-A-27-00-0026-00A-933A-D Applicable To:**  **Issue 002, 13 Jun 2016** Model 787 See Applicability of this data module **Page 41** **of 80**  EXPORT CONTROLLED ECCN: 9E991 BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET. See title page for details. **B787-81205-SB270026-00 Issue 002, 13 Jun 2016**  **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. k) 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. l) 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. m) 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.

**B787-A-27-00-0026-00A-933A-D Applicable To:**  **Issue 002, 13 Jun 2016** Model 787 See Applicability of this data module **Page 42** **of 80**  EXPORT CONTROLLED ECCN: 9E991 BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET. See title page for details. **B787-81205-SB270026-00 Issue 002, 13 Jun 2016**  **AIRCRAFT SERVICE BULLETIN**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) Depressurize the hydraulic system. Refer to 787 AMM 29-11-00 as an accepted procedure. (c) 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: **CB Designation**  CE3231801 MLG BYPASS VLV-ENABLE 1 CE3231802 MLG BYPASS VLV-ENABLE 2 CE3231803 NLG BYPASS VLV-ENABLE 1 CE3231804 NLG BYPASS VLV-ENABLE 2 CE2711106 AIL REU LIB PWR CE2711205 AIL REU RIB PWR CE2761413 AUTO SPDBRK ACT CTRLR PWR CE2731108 ELEV REU LIB PWR CE2731207 ELEV REU RIB PWR CE2711107 FLAPERON REU RIB PWR CE2721109 RUD REU UPR PWR CK2761501 ELECT ACTR-SPLR 10 CK2761503 ELECT ACTR-SPLR 11 CK2761504 ELECT ACTR-SPLR 4 CK2761502 ELECT ACTR-SPLR 5 CE2911831 ALTN EXTEND ISLN VLV CLOSE-1 CE2911832 ALTN EXTEND ISLN VLV CLOSE-2

**B787-A-27-00-0026-00A-933A-D Applicable To:**  **Issue 002, 13 Jun 2016** Model 787 See Applicability of this data module **Page 43** **of 80**  EXPORT CONTROLLED ECCN: 9E991 BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET. See title page for details. **B787-81205-SB270026-00 Issue 002, 13 Jun 2016**  **AIRCRAFT SERVICE BULLETIN**Table 3 WORK PACKAGE 4: **CB Designation**  CE2911819 HYD ISLN VLV-NLG OPEN 1 CE2911820 HYD ISLN VLV-NLG OPEN 2 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) Depressurize the hydraulic system. Refer to 787 AMM 29-11-00 as an accepted procedure. f) 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. g) 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. h) 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.

**B787-A-27-00-0026-00A-933A-D Applicable To:**  **Issue 002, 13 Jun 2016** Model 787 See Applicability of this data module **Page 44** **of 80**  EXPORT CONTROLLED ECCN: 9E991 BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET. See title page for details. **B787-81205-SB270026-00 Issue 002, 13 Jun 2016**  **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 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. **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 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. k) 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. l) 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.

**B787-A-27-00-0026-00A-933A-D Applicable To:**  **Issue 002, 13 Jun 2016** Model 787 See Applicability of this data module **Page 45** **of 80**  EXPORT CONTROLLED ECCN: 9E991 BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET. See title page for details. **B787-81205-SB270026-00 Issue 002, 13 Jun 2016**  **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. m) 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. **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. n) With landing gear pins removed and door safety valves in the STOW position, retract the landing gear. **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. o) Extend the landing gear using the alternate extend system. **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. p) RC - Retract and extend the landing gear 2 times using the landing gear lever. q) 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 WILLHELP 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.

**B787-A-27-00-0026-00A-933A-D Applicable To:**  **Issue 002, 13 Jun 2016** Model 787 See Applicability of this data module **Page 46** **of 80**  EXPORT CONTROLLED ECCN: 9E991 BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET. See title page for details. **B787-81205-SB270026-00 Issue 002, 13 Jun 2016**  **AIRCRAFT SERVICE BULLETIN 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 WILLHELP 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 WILLHELP 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 WILLHELP 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.Wait until the landing gear is fully retracted before proceeding to the next step. <b> Move the control lever for the landing gear to the DOWN position.Wait until the landing gear is fully extended before proceeding to the next step. **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 WILLHELP PREVENT INJURY TO PERSONS AND DAMAGE TO EQUIPMENT. <6> Move the control lever for the landing gear to the UP position.Wait until the landing gear is fully retracted before proceeding to the next step. **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 WILLHELP PREVENT INJURY TO PERSONS AND DAMAGE TO EQUIPMENT. <7> Move the control lever for the landing gear to the DOWN position. Wait until the landing gear is fully extended before proceeding to the next step.

**B787-A-27-00-0026-00A-933A-D Applicable To:**  **Issue 002, 13 Jun 2016** Model 787 See Applicability of this data module **Page 47** **of 80**  EXPORT CONTROLLED ECCN: 9E991 BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET. See title page for details. **B787-81205-SB270026-00 Issue 002, 13 Jun 2016**  **AIRCRAFT SERVICE BULLETIN**r) Depressurize the hydraulic system. Refer to 787 AMM 29-11-00 as an accepted procedure. s) 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 t) 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 u) 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 (d) Shipping information including airway bill number and courier company (e) Airplane, flight cycles, flight hours and system of fluid arriving in shipment.

**B787-A-27-00-0026-00A-933A-D Applicable To:**  **Issue 002, 13 Jun 2016** Model 787 See Applicability of this data module **Page 48** **of 80**  EXPORT CONTROLLED ECCN: 9E991 BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET. See title page for details. **B787-81205-SB270026-00 Issue 002, 13 Jun 2016**  **AIRCRAFT SERVICE BULLETIN Group 1, Configuration 2; Group 2:** 

**L. PART 4: REPLACE HYDRAULIC FLUID**  RC - Do one of these options: (1) (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) Pressurize the center hydraulic system and reservoir. Refer to 787 AMM 29-11-00 as an accepted procedure. (b) Use the pitch trim switches on the captain's or first officer's control wheel to move the stabilizer to the 4 unit position. (c) 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. (d) Depressurize the center hydraulic system and reservoir. Refer to 787 AMM 29-11-00 as an accepted procedure. (e) 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. (f) Remove Flight Control Electronic (FCE) cabinet power.

**B787-A-27-00-0026-00A-933A-D Applicable To:**  **Issue 002, 13 Jun 2016** Model 787 See Applicability of this data module **Page 49** **of 80**  EXPORT CONTROLLED ECCN: 9E991 BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET. See title page for details. **B787-81205-SB270026-00 Issue 002, 13 Jun 2016**  **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 **CB Designation**  CE2709811 FCE CABINET-C1 BACKUP CE2709831 FCE CABINET-L BACKUP CE2709821 FCE CABINET-C2 BACKUP CE2709841 FCE CABINET-R BACKUP (g) 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. (h) RC - Remove and keep the hydraulic return line between the elevator inboard PCU and the ribhinge. Refer to 787 AMM 20-10-09 Tube Assembly - Flareless - Removal as an accepted procedure. (i) RC - Install tool TSF036Z0229 between the elevator inboard PCU and rib hinge. (j) 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. (k) Make sure the ball valve on the tool is in the open position. (l) Supply FCE cabinet power. 1) Unlock these DO NOT CLOSE tags and close these circuit breakers on the CBIC panel: Table 5 **CB Designation**  CE2709811 FCE CABINET-C1 BACKUP CE2709831 FCE CABINET-L BACKUP CE2709821 FCE CABINET-C2 BACKUP CE2709841 FCE CABINET-R BACKUP (m) 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.

**B787-A-27-00-0026-00A-933A-D Applicable To:**  **Issue 002, 13 Jun 2016** Model 787 See Applicability of this data module **Page 50** **of 80**  EXPORT CONTROLLED ECCN: 9E991 BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET. See title page for details. **B787-81205-SB270026-00 Issue 002, 13 Jun 2016**  **AIRCRAFT SERVICE BULLETIN**(n) On the control stand, put the L2 and R2 STAB CUTOUT switches to the NORM position and remove the DO NOT OPERATE tags. (o) 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. (p) 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.

**B787-A-27-00-0026-00A-933A-D Applicable To:**  **Issue 002, 13 Jun 2016** Model 787 See Applicability of this data module **Page 51** **of 80**  EXPORT CONTROLLED ECCN: 9E991 BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET. See title page for details. **B787-81205-SB270026-00 Issue 002, 13 Jun 2016**  **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 **CB Designation**  CE2709811 FCE CABINET-C1 BACKUP CE2709831 FCE CABINET-L BACKUP CE2709821 FCE CABINET-C2 BACKUP CE2709841 FCE CABINET-R BACKUP

**B787-A-27-00-0026-00A-933A-D Applicable To:**  **Issue 002, 13 Jun 2016** Model 787 See Applicability of this data module **Page 52** **of 80**  EXPORT CONTROLLED ECCN: 9E991 BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET. See title page for details. **B787-81205-SB270026-00 Issue 002, 13 Jun 2016**  **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 **CB Designation**  CE2709811 FCE CABINET-C1 BACKUP CE2709831 FCE CABINET-L BACKUP CE2709821 FCE CABINET-C2 BACKUP CE2709841 FCE CABINET-R BACKUP (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.

**B787-A-27-00-0026-00A-933A-D Applicable To:**  **Issue 002, 13 Jun 2016** Model 787 See Applicability of this data module **Page 53** **of 80**  EXPORT CONTROLLED ECCN: 9E991 BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET. See title page for details. **B787-81205-SB270026-00 Issue 002, 13 Jun 2016**  **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 **CB Designation**  CE2709811 FCE CABINET-C1 BACKUP CE2709831 FCE CABINET-L BACKUP CE2709821 FCE CABINET-C2 BACKUP CE2709841 FCE CABINET-R BACKUP (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 rearspar. 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.

**B787-A-27-00-0026-00A-933A-D Applicable To:**  **Issue 002, 13 Jun 2016** Model 787 See Applicability of this data module **Page 54** **of 80**  EXPORT CONTROLLED ECCN: 9E991 BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET. See title page for details. **B787-81205-SB270026-00 Issue 002, 13 Jun 2016**  **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 **CB Designation**  CE2709811 FCE CABINET-C1 BACKUP CE2709831 FCE CABINET-L BACKUP CE2709821 FCE CABINET-C2 BACKUP CE2709841 FCE CABINET-R BACKUP (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.

**B787-A-27-00-0026-00A-933A-D Applicable To:**  **Issue 002, 13 Jun 2016** Model 787 See Applicability of this data module **Page 55** **of 80**  EXPORT CONTROLLED ECCN: 9E991 BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET. See title page for details. **B787-81205-SB270026-00 Issue 002, 13 Jun 2016**  **AIRCRAFT SERVICE BULLETIN WARNING** **:** KEEP ALL PERSONS AND EQUIPMENT AWAY FROM THE FLIGHT CONTROLSURFACES 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:

**B787-A-27-00-0026-00A-933A-D Applicable To:**  **Issue 002, 13 Jun 2016** Model 787 See Applicability of this data module **Page 56** **of 80**  EXPORT CONTROLLED ECCN: 9E991 BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET. See title page for details. **B787-81205-SB270026-00 Issue 002, 13 Jun 2016**  **AIRCRAFT SERVICE BULLETIN**(a) Make sure the center hydraulic system and reservoir is depressurized. Refer to787 AMM 29- 11-00 Hydraulic System - Center - Depressurization, 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 to787 AMM 27-02-00 Flight Control Surface Lock Switches - Operation, 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 **CB Designation**  CE2709811 FCE CABINET-C1 BACKUP CE2709831 FCE CABINET-L BACKUP CE2709821 FCE CABINET-C2 BACKUP CE2709841 FCE CABINET-R BACKUP (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 **CB Designation**  CE2709811 FCE CABINET-C1 BACKUP CE2709831 FCE CABINET-L BACKUP CE2709821 FCE CABINET-C2 BACKUP CE2709841 FCE CABINET-R BACKUP (g) Put the FLIGHT CONTROL SURFACE switch for the WINGS in the NORM position and remove the DO NOT OPERATE tag. Refer to787 AMM 27-02-00 Flight Control Surface Lock Switches - Operation, 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.

**B787-A-27-00-0026-00A-933A-D Applicable To:**  **Issue 002, 13 Jun 2016** Model 787 See Applicability of this data module **Page 57** **of 80**  EXPORT CONTROLLED ECCN: 9E991 BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET. See title page for details. **B787-81205-SB270026-00 Issue 002, 13 Jun 2016**  **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. 4) Depressurize the center hydraulic system and reservoir. Refer to 787 AMM 29-11-00 as an accepted procedure. (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.

**B787-A-27-00-0026-00A-933A-D Applicable To:**  **Issue 002, 13 Jun 2016 End of data module**  Model 787 See Applicability of this data module **Page 58** **of 80**  EXPORT CONTROLLED ECCN: 9E991 BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET. See title page for details. **B787-81205-SB270026-00 Issue 002, 13 Jun 2016**  **AIRCRAFT SERVICE BULLETIN**

## Alert Service Bulletin B787-81205-SB270026-00

**Appendix A**
**–**

**LOGIC DIAGRAM FOR PARAGRAPH 5., 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 **Title Reference**  Compliance SB B787-A-27-00-0026-00A-932A-D Issue 002, Paragraph 5. Work Instructions SB B787-A-27-00-0026-00A-933A-D Issue 002, Step 2. 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 **Description Title**  MARKER INSTALLATION WORK PACKAGE 1

**B787-A-27-00-0026-0AA-931D-D Applicable To:**  **Issue 002, 13 Jun 2016** Model 787 See Applicability of this data module **Page 59** **of 80**  EXPORT CONTROLLED ECCN: 9E991 BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET. See title page for details. **B787-81205-SB270026-00 Issue 002, 13 Jun 2016**  **AIRCRAFT SERVICE BULLETIN**The table below gives the description for the flag notes called out in the logic diagram. Table 2 Flag Notes **More Data Flag Note**  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]

**B787-A-27-00-0026-0AA-931D-D Applicable To:**  **Issue 002, 13 Jun 2016** Model 787 See Applicability of this data module **Page 60** **of 80**  EXPORT CONTROLLED ECCN: 9E991 BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET. See title page for details. **B787-81205-SB270026-00 Issue 002, 13 Jun 2016**  **AIRCRAFT SERVICE BULLETIN**ICN-B787-A-000061-A-81205-09066-A-02-1 Figure 1

**B787-A-27-00-0026-0AA-931D-D Applicable To:**  **Issue 002, 13 Jun 2016 End of data module**  Model 787 See Applicability of this data module **Page 61** **of 80**  EXPORT CONTROLLED ECCN: 9E991 BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET. See title page for details. **B787-81205-SB270026-00 Issue 002, 13 Jun 2016**  **AIRCRAFT SERVICE BULLETIN**

## Alert Service Bulletin B787-81205-SB270026-00 **Appendix B**
**–**

**LOGIC DIAGRAM FOR PARAGRAPH 5., 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 **Title Reference**  Compliance SB B787-A-27-00-0026-00A-932A-D Issue 002, Paragraph 5. Work Instructions SB B787-A-27-00-0026-00A-933A-D Issue 002, Step 2. 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 **Description Title**  LEFT HYDRAULIC SYSTEM FLUID TEST WORK PACKAGE 2 CYCLE HYDRAULIC FLUID PART 2 HYDRAULIC FLUID TEST PART 3 REPLACE HYDRAULIC FLUID PART 4 PASSES THE HYDRAULIC FLUID TEST CONDITION 1 DOES NOT PASS THE HYDRAULIC FLUID TEST CONDITION 2

**B787-A-27-00-0026-0BA-931D-D Applicable To:**  **Issue 002, 13 Jun 2016** Model 787 See Applicability of this data module **Page 62** **of 80**  EXPORT CONTROLLED ECCN: 9E991 BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET. See title page for details. **B787-81205-SB270026-00 Issue 002, 13 Jun 2016**  **AIRCRAFT SERVICE BULLETIN**The table below gives the description for the flag notes called out in the logic diagram. Table 2 Flag Notes **More Data Flag Note**  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]

**B787-A-27-00-0026-0BA-931D-D Applicable To:**  **Issue 002, 13 Jun 2016** Model 787 See Applicability of this data module **Page 63** **of 80**  EXPORT CONTROLLED ECCN: 9E991 BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET. See title page for details. **B787-81205-SB270026-00 Issue 002, 13 Jun 2016**  **AIRCRAFT SERVICE BULLETIN**ICN-B787-A-000061-A-81205-09067-A-02-1 Figure 1

**B787-A-27-00-0026-0BA-931D-D Applicable To:**  **Issue 002, 13 Jun 2016 End of data module**  Model 787 See Applicability of this data module **Page 64** **of 80**  EXPORT CONTROLLED ECCN: 9E991 BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET. See title page for details. **B787-81205-SB270026-00 Issue 002, 13 Jun 2016**  **AIRCRAFT SERVICE BULLETIN**

## Alert Service Bulletin B787-81205-SB270026-00

**Appendix C**
**–**

**LOGIC DIAGRAM FOR PARAGRAPH 5., 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 **Title Reference**  Compliance SB B787-A-27-00-0026-00A-932A-D Issue 002, Paragraph 5. Work Instructions SB B787-A-27-00-0026-00A-933A-D Issue 002, Step 2. 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 **Description Title**  RIGHT HYDRAULIC SYSTEM FLUID TEST WORK PACKAGE 3 CYCLE HYDRAULIC FLUID PART 2 HYDRAULIC FLUID TEST PART 3 REPLACE HYDRAULIC FLUID PART 4 PASSES THE HYDRAULIC FLUID TEST CONDITION 3 DOES NOT PASS THE HYDRAULIC FLUID TEST CONDITION 4

**B787-A-27-00-0026-0CA-931D-D Applicable To:**  **Issue 002, 13 Jun 2016** Model 787 See Applicability of this data module **Page 65** **of 80**  EXPORT CONTROLLED ECCN: 9E991 BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET. See title page for details. **B787-81205-SB270026-00 Issue 002, 13 Jun 2016**  **AIRCRAFT SERVICE BULLETIN**The table below gives the description for the flag notes called out in the logic diagram. Table 2 Flag Notes **More Data Flag Note**  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]

**B787-A-27-00-0026-0CA-931D-D Applicable To:**  **Issue 002, 13 Jun 2016** Model 787 See Applicability of this data module **Page 66** **of 80**  EXPORT CONTROLLED ECCN: 9E991 BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET. See title page for details. **B787-81205-SB270026-00 Issue 002, 13 Jun 2016**  **AIRCRAFT SERVICE BULLETIN**ICN-B787-A-000061-A-81205-09068-A-02-1 Figure 1

**B787-A-27-00-0026-0CA-931D-D Applicable To:**  **Issue 002, 13 Jun 2016 End of data module**  Model 787 See Applicability of this data module **Page 67** **of 80**  EXPORT CONTROLLED ECCN: 9E991 BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET. See title page for details. **B787-81205-SB270026-00 Issue 002, 13 Jun 2016**  **AIRCRAFT SERVICE BULLETIN**

## Alert Service Bulletin B787-81205-SB270026-00 **Appendix D**
**–**

**LOGIC DIAGRAM FOR PARAGRAPH 5., 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 **Title Reference**  Compliance SB B787-A-27-00-0026-00A-932A-D Issue 002, Paragraph 5. Work Instructions SB B787-A-27-00-0026-00A-933A-D Issue 002, Step 2. 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 **Description Title**  CENTER HYDRAULIC SYSTEM FLUID TEST AND LEFT AND RIGHT ELEVATOR AND AILERON POWER CONTROL UNIT INTERNAL FLOW TEST WORK PACKAGE 4
LEFT ELEVATOR INBOARD POWER CONTROL UNIT INTERNAL FLOW TEST WORK PACKAGE 5 RIGHT ELEVATOR INBOARD POWER CONTROL UNIT INTERNAL FLOW TEST WORK PACKAGE 6
LEFT AILERON INBOARD POWER CONTROL UNIT INTERNAL FLOW TEST WORK PACKAGE 7 RIGHT AILERON INBOARD POWER CONTROL UNIT INTERNAL FLOW TEST WORK PACKAGE 8
**B787-A-27-00-0026-0DA-931D-D Applicable To:**  **Issue 002, 13 Jun 2016** Model 787 See Applicability of this data module **Page 68** **of 80**  EXPORT CONTROLLED ECCN: 9E991 BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET. See title page for details. **B787-81205-SB270026-00 Issue 002, 13 Jun 2016**  **AIRCRAFT SERVICE BULLETIN**Table 1 Description Table **Description Title**  CYCLE HYDRAULIC FLUID PART 2 HYDRAULIC FLUID TEST PART 3 REPLACE HYDRAULIC FLUID PART 4 PASSES THE HYDRAULIC FLUID TEST CONDITION 5 DOES NOT PASS THE HYDRAULIC FLUID TEST CONDITION 6 The table below gives the description for the flag notes called out in the logic diagram. Table 2 Flag Notes **More Data Flag Note**  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]

**B787-A-27-00-0026-0DA-931D-D Applicable To:**  **Issue 002, 13 Jun 2016** Model 787 See Applicability of this data module **Page 69** **of 80**  EXPORT CONTROLLED ECCN: 9E991 BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET. See title page for details. **B787-81205-SB270026-00 Issue 002, 13 Jun 2016**  **AIRCRAFT SERVICE BULLETIN**ICN-B787-A-000061-A-81205-09069-A-02-1 Figure 1

**B787-A-27-00-0026-0DA-931D-D Applicable To:**  **Issue 002, 13 Jun 2016 End of data module**  Model 787 See Applicability of this data module **Page 70** **of 80**  EXPORT CONTROLLED ECCN: 9E991 BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET. See title page for details. **B787-81205-SB270026-00 Issue 002, 13 Jun 2016**  **AIRCRAFT SERVICE BULLETIN**

## Alert Service Bulletin B787-81205-SB270026-00

**Appendix E**
**–**

**LOGIC DIAGRAM FOR PARAGRAPH 5., 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 **Title Reference**  Compliance SB B787-A-27-00-0026-00A-932A-D Issue 002, Paragraph 5. Work Instructions SB B787-A-27-00-0026-00A-933A-D Issue 002, Step 2.



## 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 **Description Title**  ELEVATOR INBOARD POWER CONTROL UNIT INTERNAL FLOW TEST PART 5 REPLACE THE POWER CONTROL UNIT PART 7 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

**B787-A-27-00-0026-0EA-931D-D Applicable To:**  **Issue 002, 13 Jun 2016** Model 787 See Applicability of this data module **Page 71** **of 80**  EXPORT CONTROLLED ECCN: 9E991 BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET. See title page for details. **B787-81205-SB270026-00 Issue 002, 13 Jun 2016**  **AIRCRAFT SERVICE BULLETIN**Table 1 Description Table **Description Title**  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

**B787-A-27-00-0026-0EA-931D-D Applicable To:**  **Issue 002, 13 Jun 2016** Model 787 See Applicability of this data module **Page 72** **of 80**  EXPORT CONTROLLED ECCN: 9E991 BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET. See title page for details. **B787-81205-SB270026-00 Issue 002, 13 Jun 2016**  **AIRCRAFT SERVICE BULLETIN**ICN-B787-A-000061-A-81205-09070-A-02-1 Figure 1

**B787-A-27-00-0026-0EA-931D-D Applicable To:**  **Issue 002, 13 Jun 2016 End of data module**  Model 787 See Applicability of this data module **Page 73** **of 80**  EXPORT CONTROLLED ECCN: 9E991 BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET. See title page for details. **B787-81205-SB270026-00 Issue 002, 13 Jun 2016**  **AIRCRAFT SERVICE BULLETIN**

## Alert Service Bulletin B787-81205-SB270026-00 **Appendix F**
**–**

**LOGIC DIAGRAM FOR PARAGRAPH 5., 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 **Title Reference**  Compliance SB B787-A-27-00-0026-00A-932A-D Issue 002, Paragraph 5. Work Instructions SB B787-A-27-00-0026-00A-933A-D Issue 002, Step 2.



## 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 **Description Title**  AILERON INBOARD POWER CONTROL UNIT INTERNAL FLOW TEST PART 6 REPLACE THE POWER CONTROL UNIT PART 7 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

**B787-A-27-00-0026-0FA-931D-D Applicable To:**  **Issue 002, 13 Jun 2016** Model 787 See Applicability of this data module **Page 74** **of 80**  EXPORT CONTROLLED ECCN: 9E991 BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET. See title page for details. **B787-81205-SB270026-00 Issue 002, 13 Jun 2016**  **AIRCRAFT SERVICE BULLETIN**Table 1 Description Table **Description Title**  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

**B787-A-27-00-0026-0FA-931D-D Applicable To:**  **Issue 002, 13 Jun 2016** Model 787 See Applicability of this data module **Page 75** **of 80**  EXPORT CONTROLLED ECCN: 9E991 BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET. See title page for details. **B787-81205-SB270026-00 Issue 002, 13 Jun 2016**  **AIRCRAFT SERVICE BULLETIN**ICN-B787-A-000061-A-81205-09071-A-02-1 Figure 1

**B787-A-27-00-0026-0FA-931D-D Applicable To:**  **Issue 002, 13 Jun 2016 End of data module**  Model 787 See Applicability of this data module **Page 76** **of 80**  EXPORT CONTROLLED ECCN: 9E991 BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET. See title page for details. **B787-81205-SB270026-00 Issue 002, 13 Jun 2016**  **AIRCRAFT SERVICE BULLETIN**

## 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.

**B787-A-27-00-0026-0GA-931D-D Applicable To:**  **Issue 002, 13 Jun 2016** Model 787 See Applicability of this data module **Page 77** **of 80**  EXPORT CONTROLLED ECCN: 9E991 BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET. See title page for details. **B787-81205-SB270026-00 Issue 002, 13 Jun 2016**  **AIRCRAFT SERVICE BULLETIN**

## 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

**B787-A-27-00-0026-0GA-931D-D Applicable To:**  **Issue 002, 13 Jun 2016** Model 787 See Applicability of this data module **Page 78** **of 80**  EXPORT CONTROLLED ECCN: 9E991 BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET. See title page for details. **B787-81205-SB270026-00 Issue 002, 13 Jun 2016**  **AIRCRAFT SERVICE BULLETIN**ICN-B787-A-000061-A-81205-09073-A-01-1

Figure 2 GROUND TESTS - SKIP WARMUP AND BLEED SCREEN (TYPICAL - RIGHT AILERON SHOWN)

**B787-A-27-00-0026-0GA-931D-D Applicable To:**  **Issue 002, 13 Jun 2016** Model 787 See Applicability of this data module **Page 79** **of 80**  EXPORT CONTROLLED ECCN: 9E991 BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET. See title page for details. **B787-81205-SB270026-00 Issue 002, 13 Jun 2016**  **AIRCRAFT SERVICE BULLETIN**ICN-B787-A-000061-A-81205-09074-A-01-1

Figure 3 GROUND TESTS - SURFACE WILL MOVE SCREEN (TYPICAL - RIGHT AILERON SHOWN)

**B787-A-27-00-0026-0GA-931D-D Applicable To:**  **Issue 002, 13 Jun 2016 End of data module**  Model 787 See Applicability of this data module **Page 80** **of 80**  EXPORT CONTROLLED ECCN: 9E991 BOEING PROPRIETARY, CONFIDENTIAL AND/OR TRADE SECRET. See title page for details. **B787-81205-SB270026-00 Issue 002, 13 Jun 2016**  **AIRCRAFT SERVICE BULLETIN**