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

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Table of Contents

Revision Transmittal Sheet ............................................ 5

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

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

A. Effectivity . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11

1. Airplanes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11

2. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12

B. Concurrent Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12

C. Reason . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13

D. Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13

E. Compliance . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13

F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14

G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14

H. Weight and Balance Changes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14

I. Electrical Load Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14

J. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

1. Existing Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

2. Data supplied with this Service Bulletin . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

3. Installation Drawings Used in the Preparation of this Service Bulletin . . . . . . . . . . . . 15

K. Publications Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

L. Interchangeability and Intermixability of Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . 15

2. MATERIAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

A. Material - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

B. Industry Support Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

C. Parts Necessary For Each Airplane . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

1. Kits/Parts . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

2. Parts and Materials Supplied by the Operator . . . . . . . . . . . . . . . . . . . . . . . . 17

3. Parts Modified and Reidentified . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

4. Parts Removed and Not Replaced . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

D. Parts Necessary to Change Spares . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

E. Special Tooling - Price and Availability . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17

F. Special Tooling Necessary to do this Service Bulletin . . . . . . . . . . . . . . . . . . . . . . . 17

3. ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

A. GENERAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

B. WORK INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 19

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Commercial 

Airplanes 777

Service Bulletin

Revision Transmittal Sheet 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

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

Original Issue: January 12, 2011

Revision 1: October 26, 2011

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Commercial 

Airplanes 777

Service Bulletin

Summary 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

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

Task Number of Persons Task Hours Elapsed Hours

Open Access 2 2.00 1.00

Close Access 2 2.00 1.00

TOTAL FOR EACH ENGINE 4.0 2.0

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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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.

GROUP CONFIGURATION DESCRIPTION

777-200/-300 airplanes through line number 796 with Rolls-Royce

RB211 Trent 800 engines.

1 -

Airplane Models:

777-200, 777-300

Variable Number Group

WA001 1

WA086 - WA093 1

WA101 - WA104 1

WA196 - WA198 1

WB031 - WB042 1

WB044 - WB046 1

WB101 - WB106 1

WB161 - WB177 1

WB181 - WB194 1

WB201 - WB215 1

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Variable Number Group

WB231 - WB247 1

WB416 - WB439 1

WB446 - WB453 1

WB501 - WB512 1

WB601 - WB606 1

WB611 - WB622 1

WB631 - WB638 1

WB646 - WB649 1

WC051 - WC073 1

WC101 - WC104 1

WC456 - WC459 1

WC486 - WC493 1

WC531 - WC536 1

WC566 - WC567 1

WC571 - WC574 1

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:

Company Service Bulletin Description

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

Boeing 777-31-0177 Original Issue or Revision 1

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BOEING SERVICE BULLETIN 777-75A0002
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

Model Zone

777-200, 777-300 411, 421

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 SERVICE BULLETIN 777-75A0002
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

Task Number of Persons Task Hours Elapsed Hours

Open Access 2 2.00 1.00

Close Access 2 2.00 1.00

TOTAL FOR EACH ENGINE 4.0 2.0

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

Airplane (Pounds)

All + 10.2 + 10259

I. Electrical Load Data

Not changed.

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BOEING SERVICE BULLETIN 777-75A0002
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:

Publication Chapter-Section

777 FAA Approved Airplane Flight Manual AFM-DPI

777 Aircraft Maintenance Manual 75-33

777 System Schematic Manual 75-33

777 Fault Isolation Manual 75-34

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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BLANK PAGE
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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BOEING SERVICE BULLETIN 777-75A0002

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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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BOEING SERVICE BULLETIN 777-75A0002
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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