This document transmits Revision 1 to Service Bulletin RB211-72-H754 and Revision

1 to the Supplement

Document History

Service Bulletin Revision Status Supplement Revision Status

Initial Issue Oct.1/14 Initial Issue Oct.1/14

Bulletin Revision 1

Remove Incorporate Reason for change

All pages of the

Service Bulletin

Pages 1 to 16 of the

Service Bulletin

Amend Accomplishment

Instructions at 3.C.(4)(a),

3.C.(5)(b) and 3.C.(5)(f).

Supplement Revision 1

Remove Incorporate Reason for change

All pages Page 1 Amend Accomplishment

Instructions at 3.C.(4)(a),

3.C.(5)(b) and 3.C.(5)(f).

Printed in Great Britain

Jul.29/15

RB211 TRENT 700 SERIES PROPULSION SYSTEMS SERVICE BULLETIN

RB.211−72−H754

Transmittal - Page 1 of 2

Date
LIST OF EFFECTIVE PAGES

The effective pages to this Service Bulletin following incorporation of Revision

1 to the Bulletin and Revision 1 to the Supplement are as follows:

Page Revision Number Revision Date

Bulletin

R 1 1 Jul.29/15

R 2 1 Jul.29/15

R 3 1 Jul.29/15

R 4 1 Jul.29/15

R 5 1 Jul.29/15

R 6 1 Jul.29/15

R 7 1 Jul.29/15

R 8 1 Jul.29/15

R 9 1 Jul.29/15

R 10 1 Jul.29/15

R 11 1 Jul.29/15

R 12 1 Jul.29/15

R 13 1 Jul.29/15

R 14 1 Jul.29/15

R 15 1 Jul.29/15

R 16 1 Jul.29/15

Supplement

R 1 1 Jul.29/15

Printed in Great Britain

RB.211−72−H754

Transmittal - Page 2
1. Planning Information

A. Effectivity

Airbus A330

(1) RB211 TRENT768-60 Engines prior to Serial No.42535

RB211 TRENT772-60 Engines prior to Serial No.42535

RB211 TRENT129AA, TRENT130AA, TRENT131AA, TRENT132AA, TRENT135AA,

TRENT137AA, TRENT138AA, TRENT139AA, TRENT140AA, TRENT141AA, TRENT142AA,

SE100390, SE100411, SE100412, SE100418, SE100419, SE100420, SE100421,

SE100424, SE100426, SE100427, SE100428, SE100429, SE100430, SE100431,

SE100436, SE100437, SE100438, SE100545, SE100546, SE100547, SE100548,

SE100549, SE100550, SE100551, SE100552 Core Engines

RB211 M05821AA, M05821AB, M05825AA, M05825AB, M05826AA, M05827AA,

M05828AA, M05829AA, M05100395 51 (05) Modules

(2) RB211 TRENT768-60/15 Engines prior to Serial No.42535

RB211 TRENT768-60/16 Engines prior to Serial No.42535

RB211 TRENT772-60/15 Engines prior to Serial No.42535

RB211 TRENT772-60/16 Engines prior to Serial No.42535

RB211 TRENT129AA, TRENT130AA, TRENT131AA, TRENT132AA, TRENT135AA,

TRENT136AA, TRENT137AA, TRENT138AA, TRENT139AA, TRENT140AA, TRENT141AA,

TRENT142AA, SE100390, SE100411, SE100412, SE100413, SE100418, SE100419,

SE100420, SE100421, SE100424, SE100425, SE100426, SE100427, SE100428,

SE100429, SE100430, SE100431, SE100436, SE100437, SE100438, SE100439,

SE100545, SE100546, SE100547, SE100548, SE100549, SE100550, SE100551,

SE100552 Core Engines

RB211 M05821AA, M05821AB, M05825AA, M05825AB, M05826AA, M05827AA,

M05828AA, M05829AA, M05100395 51 (05) Modules

(3) RB211 TRENT772B-60 Engines prior to Serial No.42535

RB211 TRENT129AA, TRENT130AA, TRENT135AA, TRENT137AA, TRENT138AA,

TRENT139AA, TRENT142AA, SE100390, SE100411, SE100412, SE100418, SE100419,

SE100424, SE100426, SE100427, SE100428, SE100431, SE100436, SE100437,

SE100438, SE100545, SE100546, SE100547, SE100548, SE100549, SE100550,

SE100551, SE100552 Core Engines

ENGINE - IP TURBINE CASE - INTRODUCTION OF A REVISED OIL FEED TUBE ASSEMBLY WITH

INCREASED RADIAL CLEARANCE BETWEEN THE UNION NUT AND SEALING SLEEVE - MOD.72-H754

Printed in Great Britain

RB.211−72−H754

Page 1 of 16

Oct 1/14

R Jul.29/15
RB211 M05825AA, M05825AB, M05826AA, M05829AA, M05100395 51 (05) Modules

(4) RB211 TRENT772B-60/15 Engines prior to Serial No.425354

RB211 TRENT772B-60/16 Engines prior to Serial No.42535

RB211 TRENT129AA, TRENT130AA, TRENT135AA, TRENT136AA, TRENT137AA,

TRENT138AA, TRENT139AA, TRENT142AA, SE100390, SE100411, SE100412,

SE100413, SE100418, SE100419, SE100424, SE100425, SE100426, SE100427,

SE100428, SE100431, SE100436, SE100437, SE100438, SE100439, SE100545,

SE100546, SE100547, SE100548, SE100549, SE100550, SE100551, SE100552 Core

Engines

RB211 M05825AA, M05825AB, M05826AA, M05829AA, M05100395 51 (05) Modules

(5) RB211 TRENT772C-60 Engines prior to Serial No.42535

RB211 SE100390, SE100411, SE100412, SE100436, SE100437, SE100438 Core

Engines

RB211 M05100395 51 (05) Modules

(6) RB211 TRENT772C-60/15 Engines prior to Serial No.42535

RB211 TRENT772C-60/16 Engines prior to Serial No.42535

RB211 SE100390, SE100411, SE100412, SE100413, SE100436, SE100437,

SE100438, SE100439 Core Engines

RB211 M05100395 51 (05) Modules

B. Concurrent Requirements

There are no concurrent modifications required for this Service Bulletin,

however, in order to obtain data which may be required for engine service

management, it is necessary to accomplish NMSB72-AH673 (see 1.K, References)

prior to the accomplishment of this Service Bulletin

C. Reason

(1) Problem

Oil leakage may occur as a result of cracking of the HP/IP support

structure internal oil feed tube assembly.

The problem is attributed to radial contact between the IP turbine casing

sealing sleeve and the external oil feed tube union nut due to

differential thermal expansion of the IP turbine casing and the oil feed

tube. In addition, under adverse tolerance conditions, the problem can be

made worse by possible binding of the internal oil feed tube end adaptor

spherical with the inner bore of the sealing sleeve.

Printed in Great Britain

RB.211−72−H754

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(2) Evidence

The problem has been reported on several engines in service resulting in

unplanned engine removals.

(3) Substantiation

The changes introduced by this Service Bulletin have been the subject of a

satisfactory engineering analysis including successful stress and

vibration assessment, trial installation and engine testing.

(4) Objective

Incorporation of this Service Bulletin (Modification) is designed to

maintain reliability.

(5) Effect of Bulletin on:

(a) Operation

Not affected

(b) Maintenance

Not affected

(c) Overhaul

Affected (see 1.L., Other Publications Affected)

(d) Repair Schemes

Affected

(e) Interchangeability

Affected (see 1.M., Interchangeability of Parts)

D. Description

(1) This Service Bulletin introduces a revised IP turbine casing sealing

sleeve and external oil feed tube assembly, including an additional

fitting instruction.

The changes are:

(a) A revised IP turbine casing sealing sleeve is introduced similar to

the existing item except for:

(i) The bore depth is increased from 16,90 mm (0.665 in.) to 17,20

mm (0.677 in.).

Printed in Great Britain

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(ii) The internal bore diameter tolerance is changed to increase the

minimum diameter from 17,448 mm (0.6869 in.) to 17,460 mm

(0.6874 in.) to ensure a cold build clearance with the internal

threaded adaptor spherical to minimise spherical binding.

(iii) A 15 degree taper is introduced to the sealing sleeve inner

bore to reduce the risk of binding.

(iv) A 5 degree taper is introduced to the sealing sleeve

anti-rotation slots to reduce the potential of binding during

assembly.

(v) A non-functional change in the form of a blind hole is

introduced adjacent to the existing wire locking hole on the

top flange for identification purposes only.

(b) A revised tee connector to IP turbine casing oil feed tube assembly is

introduced similar to the existing item except the nominal length of

the union nut is reduced from 13,44 mm (0.529 in.) to 12,54 mm (0.493

in.). This maximises the clearance between the union nut and the

sealing sleeve.

(c) An additional fitting instruction is introduced to cover the fitment

of the sealing sleeve to the IP turbine case.

(2) This Service Bulletin is in two parts as follows:

(a) Part 1

New production and in-service applications

(b) Part 2

Reserved for possible future use

E. Compliance

(1) ON-WING

OPTIONAL

This Service Bulletin is optional and incorporation is subject to customer

choice.

(2) IN-SHOP

RECOMMENDED

It is recommended that this Service Bulletin be accomplished on engines at

rework level of Module Refurbishment.

Printed in Great Britain

RB.211−72−H754

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F. Approval

The technical content of Modification 72-H754 was approved by a representative

of the European Aviation Safety Agency (EASA) on 14th April 2014, EASA

certificate No.EASA.C.10048830.

G. Manpower

(1) On-wing

(a) To gain access:

2 man hours, including 1 hour cool-down time.

(b) To embody:

1 man hour

(c) To return engine to serviceable condition:

1 man hour

(d) Test 2, the Fuel and Oil Leak test is also required. This test

includes ground running.

(2) In-shop

Not affected

NOTE: The parts affected by this Service Bulletin are accessible in-shop.

H. Material Price and Availability

Modification kit not required; parts supplied as single line items.

For prices and availability of future spares see supplement to this bulletin.

I. Tooling Price and Availability

Existing tooling required for sealing sleeve removal:

Impact extractor HU29255 with extraction adaptor HU45296

Or

Facom U.49P6 expansion puller dia 18mm - 60mm

Facom U.53H3 expansion puller adaptor

Facom U.49AM slide hammer

Printed in Great Britain

RB.211−72−H754

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R Jul.29/15
Or

Locally sourced equivalent hand tools

Adjustable grips (locally supplied)

Adjustable spanner (locally supplied)

J. Weight and Balance

(1) Weight Change

None

(2) Moment Arm

No effect

(3) Datum

Power Plant Station (PPS) 100

K. References

(1) Engine Manual:

(a) Task 72-00-51-000-801 - Remove the Tubes, Electrical Harnesses and

Components for Access to Remove the Intermediate Pressure (IP) Turbine

Module

(b) Task 72-00-51-400-804 - Install the Tubes, Electrical Harnesses and

Components, Removed for Access, on the Intermediate Pressure (IP)

Turbine Module

(c) Task 72-51-20-000-801 - Disassemble the Intermediate Pressure (IP)

Turbine Case and Vanes

(d) Task 72-51-20-400-801 - Assemble the Intermediate Pressure (IP)

Turbine Case and Vanes

(2) Aircraft Maintenance Manual:

(a) 70-12-04, Locking Techniques - Wire Locking

(b) 70-51-00, Torque Tightening Techniques

(c) 71-00-00, Test 2 - Fuel and Oil Leak Test

(d) 78-30-00, Open the Thrust Reverser Cowl Doors

(e) 78-30-00, Close the Thrust Reverser Cowl Doors

Printed in Great Britain

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L. Other Publications Affected

(1) For effect on Illustrated Parts Catalogue (IPC) see 2., Material

Information.

(2) Engine Manual:

(a) Task 72-51-20-400-801, Installation.

(b) Task 72-51-23-200-805, Inspection/Check.

M. Interchangeability of Parts

It is essential that parts are fitted as a Service Bulletin set.

Printed in Great Britain

RB.211−72−H754

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2. Material Information

A. The parts required to accomplish this Service Bulletin:

All Engines, Core Engines and Modules 51 (05)

72-51-23

Part 1 of SB

FIG

ITEM

NO.

NEW

PART

NO.

QTY PART TITLE MAT OLD

PART

NO.

INSTR

DISP

01220 KH28323 1 Sleeve-sealing - oil

feed tube

- FW15003 (1)

All Engines and Core Engines

79-22-49

Part 1 of SB

FIG

ITEM

NO.

NEW

PART

NO.

QTY PART TITLE MAT OLD

PART

NO.

INSTR

DISP

02100 KH28324 1 Tube, assy - oil feed

- tee conn to disconn

to casing disconn

(vane 8)

- FW14193 (1)

02241 KH28325 1 Union - UP11943 (2)

B. Parts to be reworked:

None

C. New production parts:

The following parts will be made available as future spares:

None

D. Instruction disposition codes:

(1) Not interchangeable. The new part must not be replaced by the old part in

isolation, and the old part must not be replaced by the new part in

isolation.

Printed in Great Britain

RB.211−72−H754

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(2) Part of oil feed tube assembly at ATA chapter reference 79-22-49, Fig/Item

02-100.

Printed in Great Britain

RB.211−72−H754

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3. Accomplishment Instructions

A. The revised oil feed tube assembly and sealing sleeve introduced by this

Service Bulletin are interchangeable with the existing items only when fitted

as a complete set (see 1.M. Interchangeability of Parts). Remove the existing

and install the new oil feed tube assembly and sealing sleeve in-shop or

on-wing in accordance with Part B. or Part C. of these Accomplishment

Instructions respectively.

B. In-shop - Remove the existing items and install the new Oil Feed Tube Assembly

(79-22-49, 02-100) and the new Sealing Sleeve (72-51-23, 01-220).

(1) Remove the oil tube assembly (79-22-49, 02-100) in accordance with Engine

Manual Task 72-00-51-000-801 (see 1.K., References). Refer also to Fig.1

(2) Remove the sealing sleeve (72-51-23, 01-220) in accordance with Engine

Manual Task 72-51-20-000-801 (see 1.K., References). Refer also to Fig.1

(3) Install the sealing sleeve (72-51-23, 01-220) in accordance with Engine

Manual Task 72-51-20-400-801 (see 1.K., References)) except use the

following procedure in place of Subtask 72-51-20-440-014:

CAUTION: TOOLING MUST NOT BE USED TO FORCE THE SEALING SLEEVE INTO

POSITION IN THE IP TURBINE CASE. DAMAGE WILL OCCUR TO THE

SEALING SLEEVE OR THE IP TURBINE CASE IF FORCE IS USED.

(a) Align the internal oil feed tube (72-51-24, 02-281) and install the

sealing sleeve (72-51-23, 01-220) by hand, using no more than light

pressure, to the IP turbine case

(b) Align the sealing sleeve with the bolt holes in the IP turbine case

and make sure that the sealing sleeve (72-51-23, 01-220) is seated on

the turbine case

(c) Install the two bolts (72-51-23, 01-229) to attach the sealing sleeve

to the IP turbine case

(d) Torque tighten the two bolts (72-51-23, 01-229) to 4,5 Nm (40 lbfin)

(4) Install the oil tube assembly (79-22-49, 02-100) in accordance with Engine

Manual Task 72-00-51-400-804 (see 1.K., References)

C. On-wing - Remove the existing items and install the new Oil Feed Tube Assembly

Printed in Great Britain

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(KH28324) and the new Sealing Sleeve (KH28323).

WARNING: YOU MUST BE CAREFUL WHEN YOU WORK ON THE ENGINE AFTER THE ENGINE IS

SHUTDOWN. THE ENGINE CAN STAY HOT FOR ALMOST ONE HOUR.

WARNING: YOU MUST NOT TOUCH HOT PARTS WITHOUT APPLICABLE GLOVES. HOT PARTS CAN

CAUSE INJURY. IF YOU GET AN INJURY, PUT IT IN COLD WATER FOR 10

MINUTES. THEN GET MEDICAL AID.

CAUTION: IN ORDER TO REDUCE THE POTENTIAL FOR MULTIPLE ENGINE EVENTS DUE TO

MAINTENANCE ERROR, ROLLS-ROYCE 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, ROLLS-ROYCE RECOMMENDS THAT

ADDITIONAL CONTROLS ARE APPLIED IN ORDER TO ENSURE THAT MAINTENANCE

TASKS HAVE BEEN COMPLETED AS DEFINED. MAINTENANCE GUIDELINES SHOULD BE

REVISED, WHERE POSSIBLE, TO PROMOTE THIS RECOMMENDATION.

(1) Gain access:

(a) Open the thrust reverser cowl doors in accordance with Aircraft

Maintenance Manual, 78-30-00, Maintenance Practices (see 1.K.,

References).

(b) Locate the oil feed tube (FW14193) and oil feed tube sealing sleeve

(FW15003) at the 9 o'clock position when looking from the rear of the

engine. Refer to Fig.1.

(2) Remove the oil feed tube assembly (FW14193):

(a) Refer to Fig.1

(b) Remove the safety cable (or lockwire) from the oil feed tube union nut

connectors at the IP turbine casing and at the T-connector of oil feed

tube (FK14871).

CAUTION: DO NOT EXCEED 1500 LBF/IN TORQUE WHEN DISCONNECTING THE UNION

NUT. EXCEEDING THIS TORQUE VALUE MAY DAMAGE THE INTERNAL OIL TUBE

(c) Slacken the oil feed tube union nut that connects to the internal oil

feed tube at the IP turbine casing

(d) Slacken the oil feed tube union nut that connects to the oil feed tube

(FK14871) T-connector

(e) Remove and disassemble the following clip positions (CP):

CP4396, CP4397, CP4398, CP4405. Refer to Fig.2 and Fig.3.

Printed in Great Britain

RB.211−72−H754

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(f) Disconnect the oil feed tube union nut connectors that connect to the

internal oil feed tube and to the T-connector of oil feed tube

(FK14871)

(g) Remove the oil feed tube (FW14193).

(3) Remove the sealing sleeve (FW15003) from the IP turbine case:

(a) Refer to Fig.1

(b) Remove the two bolts (AS48408) that secure the sealing sleeve

(FW15003) to the IP turbine case.

(c) Insert the expansion puller into the sealing sleeve and adjust the

expansion puller using an adjustable spanner and adjustable grips to

secure the expansion puller to the sleeve. Refer to 1.I., Tooling

Price and Availability.

(d) Assemble the expansion puller and slide hammer.

(e) Using the slide hammer, carefully remove the sleeve.

CAUTION: TOOLING MUST NOT BE USED TO FORCE THE SEALING SLEEVE INTO

POSITION IN THE IP TURBINE CASE. DAMAGE WILL OCCUR TO THE

SEALING SLEEVE OR THE IP TURBINE CASE IF FORCE IS USED.

(4) Install the sealing sleeve (KH28323) to the IP turbine case:

R and install the sealing sleeve (a) Align the internal oil feed tube

(KH28323) by hand, using no more than light pressure, to the IP

turbine case

(b) Align the sealing sleeve with the bolt holes in the IP turbine case

and make sure that the sealing sleeve (KH28323) is seated on the

turbine case

(c) Install the two bolts (AS48408) to attach the sealing sleeve to the IP

turbine case

(d) Torque tighten the two bolts (AS48408) to 4,5 Nm (40 lbfin)

(5) Install the oil feed tube assembly (KH28324):

(a) Refer to AMM 70-51-00, Standard Practices (see 1.K., References).

(b) Connect the oil feed tube assembly (KH28324) to the internal oil feed

R at the IP turbine case and to the T-connector of oil feed tube tube

(FK14871). Tighten the tube connectors sufficiently to keep the tube

at right angles to the end face of the tube connectors only - do not

fully tighten the connectors at this stage

Printed in Great Britain

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(c) Install the following clip positions (CP):

CP4396, CP4397, CP4398, CP4405. Refer to Fig.2 and Fig.3

(d) Torque the tube connector to the T-connector of oil feed tube

(FK14871) to 33 Nm (295 lbfin.). Refer to AMM 70-51-00, Standard

Practices (see 1.K., References).

(e) Safety the union nut with OMat 238 lockwire or OMat 2-142 safety

cable. Refer to AMM 70-12-04, Standard Practices (see 1.K.,

References).

R (f) Torque the tube connector to the internal oil feed tube at the IP

turbine case to 27 Nm (240 lbfin.). Refer to AMM 70-51-00, Standard

Practices (see 1.K., References).

(g) Safety the union nut with OMat 238 lockwire. Refer to AMM 70-12-04,

Standard Practices (see 1.K., References).

NOTE: Lockwire is recommended in preference to safety cable, in order

to give the necessary freedom of movement between the oil tube

and IPT casing.

(h) Torque the clip nuts at clip positions 4396, 4397, 4398 and 4405 to

6,2 Nm (55 lbfin.)

(6) Close access and return the aircraft to a serviceable condition:

(a) Close the thrust reverser cowl doors in accordance with Aircraft

Maintenance Manual 78-30-00, Maintenance Practices (see 1.K.,

References).

(b) Carry out the fuel and oil leak test in accordance with AMM 71-00-00,

Test 2, Fuel and Oil Leak Test (see 1.K., References).

D. A record of accomplishment is required.

The Service Bulletin number and relevant Service Bulletin part(s) shall be

recorded in the engine log book when this Service Bulletin part is fitted in its

entirety.

Printed in Great Britain

RB.211−72−H754

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Remove/Install Oil Feed Tube Assembly And Sealing Sleeve

Fig.1

Printed in Great Britain

RB.211−72−H754

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Clip positions 4396 and 4397

Fig.2

Printed in Great Britain

RB.211−72−H754

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Clip positions 4398 and 4405

Fig.3

Printed in Great Britain

RB.211−72−H754

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SUPPLEMENT - PRICE AND AVAILABILITY

This is a technical document not a quotation; any prices and delivery given are in

good faith without engagement.

Alternative parts may be supplied instead of parts listed. See Material Information

disposition instructions.

1. Modification Kit

Not applicable. Parts supplied as single line items.

2. The parts required to accomplish this Service Bulletin:

Part No. Qty

Unit Price

US Dollars

KH28323 1 Price to be supplied on request.

KH28324 1 Price to be supplied on request.

KH28325 1 Price to be supplied on request.

3. Tools

None

ENGINE - IP TURBINE CASE - INTRODUCTION OF A REVISED OIL FEED TUBE ASSEMBLY WITH

INCREASED RADIAL CLEARANCE BETWEEN THE UNION NUT AND SEALING SLEEVE - MOD.72-H754

Printed in Great Britain

RB.211−72−H754

Supplement Page 1 of 1

Oct 1/14

R Jul.29/15