# Boeing Alert Service Bulletin 777-75A0002: Revision 1

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- Document: [Boeing Alert Service Bulletin 777-75A0002](https://openairdocs.org/service-documents/boeing/777-75a0002.md)
- Title as filed: U.S. DOT/FAA - Service Bulletin
- Pages: 20
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## Text

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### Page 1

Commercial 
Airplanes
777
Service Bulletin
Number: 777-75A0002
Original Issue: January 12, 2011
Revision 1: October 26, 2011
ATA System: 7533
SUBJECT: AIR (RB211 Trent Engines) - Compressor Control - Compressor Bleed Control System
- Intermediate Compressor 8th Stage (IP8) Bleed Air Change
Export of this technology is controlled under the United States Export Administration Regulations (EAR) (15
CFR 730-774). An export license may be required before it is used for development, production or use by foreign
persons from specific countries. The controller of this data has the individual responsibility to abide by all export
laws.
9E991ECCN:
BOEING PROPRIETARY, CONFIDENTIAL, AND/OR TRADE SECRET
Copyright © 2011 The Boeing Company
Unpublished Work - All Rights Reserved
Boeing claims copyright in each page of this document only to the extent that the page contains copyrightable
subject matter. Boeing also claims copyright in this document as a compilation and/or collective work.
This document includes proprietary information owned by The Boeing Company and/or one or more third parties.
Treatment of the document and the information it contains is governed by contract with Boeing. For more
information, contact The Boeing Company, P.O. Box 3707, Seattle, Washington 98124.
Boeing, the Boeing signature, the Boeing symbol, 707, 717, 727, 737, 747, 757, 767, 777, 787, Dreamliner,
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Table of Contents
Revision Transmittal Sheet ............................................ 5
Summary ...................................................... 7
1. PLANNING INFORMATION ........................................ 1 1
A. Effectivity ............................................... 1 1
1. Airplanes ............................................ 1 1
2. Spares Affected ........................................ 1 2
B. Concurrent Requirements ...................................... 1 2
C. Reason ................................................ 1 3
D. Description .............................................. 1 3
E. Compliance .............................................. 1 3
F. Approval ............................................... 1 4
G. Manpower .............................................. 1 4
H. Weight and Balance Changes .................................... 1 4
I. Electrical Load Data ......................................... 1 4
J. References .............................................. 1 5
1. Existing Data .......................................... 1 5
2. Data supplied with this Service Bulletin ............................ 1 5
3. Installation Drawings Used in the Preparation of this Service Bulletin ............ 1 5
K. Publications Affected ........................................ 1 5
L. Interchangeability and Intermixability of Parts ........................... 1 5
2. MATERIAL INFORMATION ........................................ 1 7
A. Material - Price and Availability ................................... 1 7
B. Industry Support Information .................................... 1 7
C. Parts Necessary For Each Airplane ................................. 1 7
1. Kits/Parts ............................................ 1 7
2. Parts and Materials Supplied by the Operator ........................ 1 7
3. Parts Modified and Reidentified ................................ 1 7
4. Parts Removed and Not Replaced .............................. 1 7
D. Parts Necessary to Change Spares ................................. 1 7
E. Special Tooling - Price and Availability ............................... 1 7
F. Special Tooling Necessary to do this Service Bulletin ....................... 1 7
3. ACCOMPLISHMENT INSTRUCTIONS .................................. 1 9
A. GENERAL INFORMATION ..................................... 1 9
B. WORK INSTRUCTIONS ....................................... 1 9
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Commercial 
Airplanes
777
Service Bulletin
Revision Transmittal SheetNumber: 777-75A0002Original Issue: January 12, 2011
Revision 1: October 26, 2011
ATA System: 7533
SUBJECT: AIR (RB211 Trent Engines) - Compressor Control - Compressor Bleed Control System
- Intermediate Compressor 8th Stage (IP8) Bleed Air Change
This revision includes all pages of the service bulletin.
COMPLIANCE INFORMATION RELATED TO THIS REVISION
No more work is necessary on the airplane(s) changed in accordance with the original issue of this service
bulletin.
REASON FOR REVISION
This revision is sent to add the Revision 1 of Boeing Service Bulletin 777-31-0177 and to call out the latest
Revision of Rolls-Royce Service Bulletin RB.211-75-G466 in Paragraph 1.B., Concurrent Requirements, and
to change the warranty statement.
These sections were changed:
1. In Paragraph 1.B., Concurrent Requirements, added the Revision 1 of Boeing Service Bulletin 777-31-0177
and called out the latest Revision of Rolls-Royce Service Bulletin RB.211-75-G466.
2. In Summary, Industry Support Information and in Paragraph 2.B., Industry Support Information, changed
the warranty statement.
Vertical lines are put on the left edge of each page, except in Paragraph 1.A., Effectivity, to show the location
of important changes.
Pages with no vertical lines have no important changes.
REVISION HISTORY
January 12, 2011Original Issue:
October 26, 2011Revision 1:
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Commercial 
Airplanes
777
Service Bulletin
SummaryNumber: 777-75A0002Original Issue: January 12, 2011
Revision 1: October 26, 2011
ATA System: 7533
SUBJECT: AIR (RB211 Trent Engines) - Compressor Control - Compressor Bleed Control System
- Intermediate Compressor 8th Stage (IP8) Bleed Air Change
CONCURRENT REQUIREMENTS
Refer to Paragraph 1.B., Concurrent Requirements.
BACKGROUND
This service bulletin gives instructions to change the intermediate compressor 8th stage (IP8) bleed valve outlet
screen for Number 1, Number 2, and Number 4 bleed valves. Additionally, tubing is revised to reverse the
Number 1 and Number 2 bleed valve schedule. This action provides revised IP8 bleed air mixing to reduce
temperatures experienced by the inner wall of the thrust reverser (TR) during flight to prevent inner wall and
fitting damage. If you do not do this service bulletin, the thrust reverser could be damaged by excessive heat
which could result in thrust reverser separation at departure which could in turn cause a runway excursion
because of thrust asymmetry from forward thrust on a Refused Take Off (RTO).
Accomplishment of the service bulletin will improve the thermal protection of the thrust reverser. The existing
Thermal Protection System (TPS) as modified by Boeing Service Bulletins 777-78-0071 and 777-78-0082, was
developed to protect the thrust reverser inner wall from the engine side of the thrust reverser. The changes
provided by this service bulletin will add thermal protection to the thrust reverser inner wall from the fan duct
side of the thrust reverser. Thermal degradation has caused structural pieces of the thrust reverser inner wall
to separate from the thrust reverser in flight. Poor mixing of IP8 bleed air contributes to the overheating that
results in disbondments and delaminations in the inner wall and weakens the compression and drag link fittings.
Thirteen 777 Rolls-Royce TR events related to thermal damage of the TR inner wall have occurred since 2003.
The events have included such things as Air Turn Backs (ATB), In Flight Shut Downs (IFSD), TR inner wall
panel collapse, engine fire loop messages, and TR inner wall panel sections and parts being liberated from the
airplane. No hull loss or personal injury has occurred from these events.
Boeing Service Related Problem (SRP) 777-SRP-78-0052 is related to this service bulletin.
ACTION
On both engines, open thrust reversers and modify all three intermediate compressor 8th stage (IP8) bleed
valves. Modify tubing between right upper and lower bleed valves. Refer to Rolls-Royce SB RB.211-75-G466
for detailed instructions.
EFFECTIVITY
777-200/-300 Airplanes with Rolls-Royce RB211 Trent 800 engines. Refer to Paragraph 1.A.1., Airplanes for
the list of affected airplanes.
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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.
Boeing recommends that the change given in this service bulletin be done on each engine within three years
after the original issue date of this service bulletin.
INDUSTRY SUPPORT INFORMATION
Boeing warranty remedies are not available for the configuration changes given in this service bulletin.
MANPOWER
Manpower Table
Elapsed HoursTask HoursNumber of PersonsTask
1.002.002Open Access
1.002.002Close Access
2.04.0TOTAL FOR EACH ENGINE
The time to do Rolls-Royce SB RB.211-75-G466 and Boeing Service Bulletin 777-31-0177 is not included.
MATERIAL INFORMATION
Operator Supplied Parts/Materials. Refer to Rolls-Royce SB RB.211-75-G466.
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BOEING SERVICE BULLETIN 777-75A0002
COMPRESSOR
GAS GENERATOR
FAIRING
MODIFY UPPER
RIGHT (NUMBER 2)
BLEED VALVE
MODIFY TUBING (NOT
SHOWN) FROM BLEED
VALVES TO BLEED VALVE
CONTROLLER  MODIFY LOWER
RIGHT (NUMBER 1)
BLEED VALVE
MODIFY TUBING (NOT
SHOWN) FROM BLEED
VALVES TO BLEED VALVE
CONTROLLER
MODIFY LOWER LEFT
(NUMBER 4) BLEED
VALVE  1983394
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Commercial 
Airplanes
777
Service Bulletin
Number: 777-75A0002
Original Issue: January 12, 2011
Revision 1: October 26, 2011
ATA System: 7533
SUBJECT: AIR (RB211 Trent Engines) - Compressor Control - Compressor Bleed Control System
- Intermediate Compressor 8th Stage (IP8) Bleed Air Change
1.    PLANNING INFORMATION
A. Effectivity
1. Airplanes
Refer to Service Bulletin Index Document D624W001 Part 3 for Airplane Variable Number, Line
Number, and Serial Number data.
This service bulletin is for the airplanes shown below.
DESCRIPTIONCONFIGURATIONGROUP
777-200/-300 airplanes through line number 796 with Rolls-Royce
RB211 Trent 800 engines.
-1
Airplane Models:
777-200, 777-300
GroupVariable Number
1WA001
1WA086 - WA093
1WA101 - WA104
1WA196 - WA198
1WB031 - WB042
1WB044 - WB046
1WB101 - WB106
1WB161 - WB177
1WB181 - WB194
1WB201 - WB215
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GroupVariable Number
1WB231 - WB247
1WB416 - WB439
1WB446 - WB453
1WB501 - WB512
1WB601 - WB606
1WB611 - WB622
1WB631 - WB638
1WB646 - WB649
1WC051 - WC073
1WC101 - WC104
1WC456 - WC459
1WC486 - WC493
1WC531 - WC536
1WC566 - WC567
1WC571 - WC574
2. Spares Affected
Modify spare engines in accordance with Rolls-Royce SB RB.211-75-G466.
B. Concurrent Requirements
The service bulletins listed below must be done before or at the same time as this service bulletin:
DescriptionService BulletinCompany
AIR - IP BLEED VALVES - INTRODUCTION
OF AN IP8 BLEED VALVE FEATURING A
REVISED SILENCER AND ASSOCIATED
CORE ENGINE DRESSINGS CHANGES
Rolls-Royce SB RB.211-75-G466 dated
Jun.20/11
Rolls-Royce
INDICATING/RECORDING SYSTEMS -
Airplane Information Management System -
Aero Engine Data Base Software Upgrade
777-31-0177 Original Issue or Revision 1Boeing
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C. Reason
This service bulletin gives instructions to change the intermediate compressor 8th stage (IP8) bleed
valve outlet screen for Number 1, Number 2, and Number 4 bleed valves. Additionally, tubing is revised
to reverse the Number 1 and Number 2 bleed valve schedule. This action provides revised IP8 bleed
air mixing to reduce temperatures experienced by the inner wall of the thrust reverser (TR) during flight
to prevent inner wall and fitting damage. If you do not do this service bulletin, the thrust reverser could
be damaged by excessive heat which could result in thrust reverser separation at departure which
could in turn cause a runway excursion because of thrust asymmetry from forward thrust on a Refused
Take Off (RTO).
Accomplishment of the service bulletin will improve the thermal protection of the thrust reverser. The
existing Thermal Protection System (TPS) as modified by Boeing Service Bulletins 777-78-0071 and
777-78-0082, was developed to protect the thrust reverser inner wall from the engine side of the thrust
reverser. The changes provided by this service bulletin will add thermal protection to the thrust reverser
inner wall from the fan duct side of the thrust reverser. Thermal degradation has caused structural
pieces of the thrust reverser inner wall to separate from the thrust reverser in flight. Poor mixing of IP8
bleed air contributes to the overheating that results in disbondments and delaminations in the inner
wall and weakens the compression and drag link fittings.
Thirteen 777 Rolls-Royce TR events related to thermal damage of the TR inner wall have occurred
since 2003. The events have included such things as Air Turn Backs (ATB), In Flight Shut Downs
(IFSD), TR inner wall panel collapse, engine fire loop messages, and TR inner wall panel sections and
parts being liberated from the airplane. No hull loss or personal injury has occurred from these events.
Boeing Service Related Problem (SRP) 777-SRP-78-0052 is related to this service bulletin.
Revision 1 is sent to add the Revision 1 of Boeing Service Bulletin 777-31-0177 and to call out the
latest Revision of Rolls-Royce Service Bulletin RB.211-75-G466 in Paragraph 1.B., Concurrent
Requirements, and to change the warranty statement.
D. Description
On both engines, open thrust reversers and modify all three intermediate compressor 8th stage (IP8)
bleed valves. Modify tubing between right upper and lower bleed valves. Refer to Rolls-Royce SB
RB.211-75-G466 for detailed instructions.
Revision 1 - No more work is necessary on the airplane(s) changed in accordance with the original
issue of this service bulletin.
The work in this service bulletin is done in the maintenance zone(s) given below.
Affected Maintenance Zones
ZoneModel
411, 421777-200, 777-300
E. 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.
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Boeing recommends that the change given in this service bulletin be done on each engine, within three
years after the original issue date of this service bulletin.
F. Approval
This service bulletin was examined by the Federal Aviation Administration (FAA). The changes specified
in this service bulletin comply with the applicable regulations and are FAA approved, as well as European
Aviation Safety Agency (EASA)/Joint Aviation Authorities (JAA) approved for all EASA/JAA approved
airplanes listed in the service bulletin effectivity. This service bulletin and its approval were based on
the airplane in its original Boeing delivery configuration or as modified by other approved Boeing
changes.
If an airplane has a non-Boeing modification or repair that affects a component or system also affected
by this service bulletin, the operator is responsible for obtaining appropriate regulatory agency approval
before incorporating this service bulletin.
G. Manpower
The table below shows an estimate of the task hours necessary to do this change for each engine.
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.
Manpower Table - Work Package 1 or 2
Elapsed HoursTask HoursNumber of PersonsTask
1.002.002Open Access
1.002.002Close Access
2.04.0TOTAL FOR EACH ENGINE
The time to do Rolls-Royce SB RB.211-75-G466 and Boeing Service Bulletin 777-31-0177 is not
included.
H. Weight and Balance Changes
Change in Moment
(Pound-Inches)
Change in Weight
(Pounds)Airplane
+ 10259+ 10.2All
I. Electrical Load Data
Not changed.
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J. References
1. Existing Data
a. Boeing Service Bulletin 777-31-0177, 777-78-0071, 777-78-0082
b. Boeing Service Related Problem (SRP) 777-SRP-78-0052
c. 777 Aircraft Maintenance Manual (AMM) 75-33-16
d. Rolls-Royce Service Bulletin RB.211-75-G466
2. Data supplied with this Service Bulletin
None.
3. Installation Drawings Used in the Preparation of this Service Bulletin
None
K. Publications Affected
1. Publications:
Chapter-SectionPublication
AFM-DPI777 FAA Approved Airplane Flight Manual
75-33777 Aircraft Maintenance Manual
75-33777 System Schematic Manual
75-34777 Fault Isolation Manual
2. Damage Tolerance Based Structural Inspections:
Boeing has evaluated the repairs and/or changes in this service bulletin for effects on Fatigue
Critical Structure (FCS) and for changes to Damage Tolerance Inspections (DTI) required in the
Maintenance Program. This service bulletin does not affect FCS, therefore DTIs are not necessary.
L. Interchangeability and Intermixability of Parts
Accomplishment of this service bulletin does not affect interchangeability or intermixability of engines
on an airplane providing Boeing Service Bulletin 777-31-0177 is accomplished previously or concurrently.
Intermixability of modified and unmodified parts installed in accordance with Rolls-Royce SB
RB.211-75-G466 on one engine is not permitted.
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2.    MATERIAL INFORMATION
A. Material - Price and Availability
Refer to Rolls-Royce SB RB.211-75-G466.
B. Industry Support Information
Boeing warranty remedies are not available for the configuration changes given in this service bulletin.
C. Parts Necessary For Each Airplane
1. Kits/Parts
Refer to Rolls-Royce SB RB.211-75-G466.
2. Parts and Materials Supplied by the Operator
Refer to Rolls-Royce SB RB.211-75-G466.
3. Parts Modified and Reidentified
Refer to Rolls-Royce SB RB.211-75-G466.
4. Parts Removed and Not Replaced
Refer to Rolls-Royce SB RB.211-75-G466.
D. Parts Necessary to Change Spares
Refer to Rolls-Royce SB RB.211-75-G466.
E. Special Tooling - Price and Availability
Refer to Rolls-Royce SB RB.211-75-G466.
F. Special Tooling Necessary to do this Service Bulletin
Refer to Rolls-Royce SB RB.211-75-G466.
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3.    ACCOMPLISHMENT INSTRUCTIONS
A. GENERAL INFORMATION
WARNING: IN ORDER TO REDUCE THE POTENTIAL FOR MULTIPLE-ENGINE IN-FLIGHT
SHUTDOWN, POWER LOSS, OR OTHER ANOMALY DUE TO MAINTENANCE ERROR,
BOEING RECOMMENDS THAT OPERATORS AVOID PERFORMING MAINTENANCE
ON MULTIPLE ENGINES INSTALLED ON THE SAME AIRCRAFT AT THE SAME TIME.
IF IT IS NOT POSSIBLE TO AVOID MAINTENANCE ON MORE THAN ONE ENGINE
AT THE SAME TIME, BOEING RECOMMENDS THAT ADDITIONAL CONTROLS ARE
APPLIED IN ORDER TO MAKE SURE THAT MAINTENANCE TASKS HAVE BEEN
COMPLETED AS DEFINED. MAINTENANCE GUIDELINES SHOULD BE REVISED,
WHERE POSSIBLE, TO PROMOTE THIS RECOMMENDATION.
CAUTION: KEEP THE WORK AREA, WIRES AND ELECTRICAL BUNDLES CLEAN OF METAL
PARTICLES OR CONTAMINATION WHEN YOU USE TOOLS. UNWANTED MATERIAL,
METAL PARTICLES OR CONTAMINATION CAUGHT IN WIRE BUNDLES CAN CAUSE
DAMAGE TO THE BUNDLES. DAMAGED WIRE BUNDLES CAN CAUSE SPARKS OR
OTHER ELECTRICAL DAMAGE.
NOTE: 1. Manual titles are referred to by acronyms. Refer to Paragraph 1.J., References, for
definition of the acronyms.
2. Obey all of the warnings and cautions given in the specified manual sections.
3. The work instructions are divided into work packages. Task Hours and Elapsed Hours
for each package are given in Paragraph 1.G., Manpower. You can do each work
package independently.
4. These work instructions refer to procedures included in other Boeing and supplier
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
or supplier document must be used.
B. WORK INSTRUCTIONS
1. Work Package 1 - Left Engine
a. Gain access for removal of bleed valves. Refer to 777 AMM 75-33-16 as an accepted
procedure.
NOTE: Thrust reversers may be either opened or removed.
b. Replace bleed valve parts and tubing in accordance with Rolls-Royce SB RB.211-75-G466
dated June 20, 2011.
c. Put the airplane back to a serviceable condition.
2. Work Package 2 - Right Engine
a. Gain access for removal of bleed valves. Refer to 777 AMM 75-33-16 as an accepted
procedure.
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NOTE: Thrust reversers may be either opened or removed.
b. Replace bleed valve parts and tubing in accordance with Rolls-Royce SB RB.211-75-G466
dated June 20, 2011.
c. Put the airplane back to a serviceable condition.
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