LIST OF EFFECTIVE PAGES

The effective pages to this Service Bulletin following incorporation of Revision

4 are as follows:

Page Revision Number Revision Date

Bulletin

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Appendix 1

R 1 4 Mar.21/11

Printed in Great Britain

RB.211−72−AG270

Transmittal - Page 2
1. Planning Information

A. Effectivity

Airbus A330

RB211 TRENT 700 Engines not incorporating SB72-G402

B. Reason

(1) Problem

Following inspection at shop visit, a crack was found on two Trent 800

Intermediate Pressure (IP) compressor shafts and one Trent 700 IP

compressor shaft.

In response to the first finding, Non-Modification Service Bulletin (NMSB)

72-AF260 was raised to specify an in-shop visual inspection of the rear

balance land for Trent 500, Trent 700 and Trent 800 engine fleets. An

in-shop eddy current inspection NMSB 72-AG085 has now been introduced for

Trent 700 and Trent 800 engines.

This NMSB is being issued to instruct repeat borescope inspections of the

IP compressor shaft rear balance land on Trent 700 engines.

(2) Substantiation

This NMSB instructs an on-wing borescope inspection of the IP compressor

rear balance land, gaining access through the intermediate case vane 8.

This inspection can also be performed at overhaul, if the rear of the IP

compressor module is not accessible to perform NMSB 72-AG085.

Revision 1 of this NMSB was issued to add a note to the overhaul and

on-wing parts of the Accomplishment Instructions, also to amend the units

used for torque values in the on-wing part of the Accomplishment

Instruction. Fig 3, Fig 6, Fig 7 and Fig 8 were amended for graphic

clarity.

Revision 2 of this NMSB is issued to confine the Effectivity (1.A.) to

engines which do not incorporate Service Bulletin 72-G402. Reference is

made to SB72-G402 in the Accomplishment Instructions and the note

regarding the inspection of the area around the balance weights is

deleted, with the content of the note now incorporated into the inspection

instructions.

ENGINE - IP COMPRESSOR SHAFT - BORESCOPE INSPECTION OF BALANCE LAND -

NON-MODIFICATION SERVICE BULLETIN - NON - MOD.72-AG270

Printed in Great Britain

RB.211−72−AG270

Page 1 of 29

Sep. 2/09

R Mar.21/11
R issued to amend the illustration of a properly Revision 3 of this NMSB was

R fitted balance weight (see Fig.8) and also note that this NMSB was subject

to an EASA Airworthiness Directive (AD).

Revision 4 of this NMSB is issued to amend the illustration of a properly

fitted balance weight (see Fig.8) and also to change the part name from

nut to bolt head in 3. Accomplishment Instructions.

R

R

R

(3) Effect of Bulletin on

(a) Operation

Not affected.

(b) Maintenance

Not affected.

(c) Overhaul

Not affected.

(d) Repair Schemes

Not affected.

(e) Interchangeability

Not affected.

C. Description

This NMSB instructs an on-wing borescope inspection of the IP compressor shaft

rear balance land in order to maintain serviceability.

Advise your Rolls-Royce service representative of NMSB accomplishment and

inspection results, regardless of findings (refer to Appendix 1.).

D. Compliance

ALERT

This Non-Modification Service Bulletin must be accomplished within 625 flight

cycles of the publication of this Service Bulletin, unless NMSB 72-AG085 is

accomplished within this time period on this IP compressor shaft.

This Non-Modification Service Bulletin must then be repeated on an ongoing

basis within 625 flight cycles of the last previous accomplishment of NMSB

72-AG270 or NMSB 72-AG085 on the IP compressor shaft.

This Non-Modification Service Bulletin is subject to EASA AD 2010-0266.

Printed in Great Britain

RB.211−72−AG270

Page 2

Sep. 2/09

R Mar.21/11
E. Approval

The technical content of this Non-Modification Service Bulletin was approved

under the authority of Design Organisation Approval EASA.21J.035 on Aug.27/09,

R and was re-approved on Mar.15/11. Dec.9/09, Dec.17/10, Feb.25/11

F. Manpower

(1) In service

(a) Time to gain access

1 hour (after normal engine cooling down and opening of C-ducts) (1

person).

(b) Time to Inspect

1.5 hours (2 persons).

(c) Time to restore to serviceable condition

0.5 hours (1 person).

(2) At overhaul

(a) Time to gain access

0.5 hours (1 person).

(b) Time to Inspect

1.5 hours (2 persons).

(c) Time to restore to serviceable condition

0.5 hours (1 person).

G. Material Price and Availability

Item Description

OMat 238 Lockwire

OMat 2/142 Safety cable

H. Tooling Price and Availability

Rolls-Royce recommends the use of the tools specified below for the

accomplishment of this NMSB.

Printed in Great Britain

RB.211−72−AG270

Page 3

Sep. 2/09

R Mar.21/11
(1) Flexible borescope:

- Forward viewing

- Near focus, field of view 60 degrees

- Low magnification

Model used during Rolls-Royce inspection was model IPLEX 6 available from:

Olympus Industrial

KeyMed House

Stock Road

Southend-on-Sea

Essex SS2 5QH

United Kingdom

Tel: +44 (0) 1702 616333

Fax: +44 (0) 1702 465677

(2) IP rotor turning tool

HU38122-3 or HU40324.

(3) LP system immobiliser

HU80955.

I. References

(1) Rolls-Royce RB211 Service Bulletin:

72-G402

Engine - IP compressor shaft - Introduction of revised balancing weights

and balancing method

(2) Rolls-Royce RB211 Non-Modification Service Bulletins:

(a) 72-AF260

Engine - IP compressor shaft - Visual inspection of balance land

Printed in Great Britain

RB.211−72−AG270

Page 4

Sep. 2/09

R Mar.21/11
(b) 72-AG085

Engine - IP compressor shaft - Eddy current inspection of balance land

(3) On-wing

(a) Aircraft Maintenance Manual, 72-00-00, Borescope Inspection of the

Intermediate Pressure (IP) Compressor Blades

(b) Aircraft Maintenance Manual, 72-00-00, Turn the Engine Intermediate

Pressure System

(c) Standard Practices Manual, 70-01-02, Specified Types of Damage

(d) Aircraft Maintenance Manual, 70-12-04, Locking Techniques for threaded

parts

(4) At overhaul

(a) Engine Manual, 72-00-00, Intrascope Inspection of the Intermediate

Pressure (IP) Compressor Blades

(b) Standard Practices Manual, 70-01-02, Specified types of damage

(c) Engine Illustrated Parts Catalogue, 75-22-49, Cooling and Sealing Air

Tubes LP Core Engines

(d) Engine Illustrated Parts Catalogue, 72-32-31, IP Compressor Shaft

(e) Standard Practices Manual, 70-12-04, Procedures used to lock threaded

parts.

Printed in Great Britain

RB.211−72−AG270

Page 5

Sep. 2/09

R Mar.21/11
2. Material Information

A. Parts referenced in this Service Bulletin:

75-22-49

FIG

ITEM

NO.

NEW

PART

NO.

QTY PART TITLE MAT OLD

PART

NO.

INSTR

DISP

15141 AS48409 AR Bolt, 0.190 in. dia x

0.562 in., CP4402

- AS48409 -

15142 K8831 AR Washer, 0.190 in. dia x

0,51 mm thk, CP4402

- K8831 -

15144 UP11653 AR Clip, CP4402 - UP11653 -

15148 AS20624 AR Nut, 0.190 in. dia, CP4402 - AS20624 -

15100 FK19091 AR Tube, assy IP8 air -

casing disconnect

- FK19091 -

15106 AS48512 AR Bolt, 0.250 in. dia x

0.748 in.

- AS45812 -

74-21-11

FIG

ITEM

NO.

NEW

PART

NO.

QTY PART TITLE MAT OLD

PART

NO.

INSTR

DISP

01828 UL12509 AR Clip, CP4402 - UL12509 -

72-33-10

NOTE: The following parts are only replaced if found damaged when the bolts

(EIPC 75-22-49, Fig/Item 15106) are removed.

FIG

ITEM

NO.

NEW

PART

NO.

QTY PART TITLE MAT OLD

PART

NO.

INSTR

DISP

05315 AGS3732 AR Insert, screw thread,

0.250 in. dia x 1.5 in.

- AGS3732 -

71-52-12

Printed in Great Britain

RB.211−72−AG270

Page 6

Sep. 2/09

R Mar.21/11
FIG

ITEM

NO.

NEW

PART

NO.

QTY PART TITLE MAT OLD

PART

NO.

INSTR

DISP

02086 UL12510 AR Clip, CP4394 - UL12510 -

02225 AS48408 AR Bolt, 0.190 in. dia X

0.500 in. CP4391

- AS48408 -

02226 K8831 AR Washer, 0.190 in. X 0,51

mm thk, CP4391

- K8831 -

02228 UL12509 AR Clip, CP4391 - UL12509 -

02232 AS20624 AR Nut, 0.190 in. dia, CP4391 - AS20624 -

02233 AS48408 AR Bolt, 0.190 in. dia X

X 0.500, CP4393

- AS48408 -

02234 K8831 AR Washer, 0.190 in. X

0,51 mm thk, CP4393

- K8831 -

02236 UL12510 AR Clip, CP4393 - UL12510 -

02240 AS20624 AR Nut, 0.190 in. dia

CP4393

- AS20624 -

71-52-11

FIG

ITEM

NO.

NEW

PART

NO.

QTY PART TITLE MAT OLD

PART

NO.

INSTR

DISP

02115 AS48410 AR Bolt, 0.190 in. dia X

0.625, CP4394

- AS48410 -

02116 K8831 AR Washer, 0.190 in. X 0,51

mm thk, CP4394

- K8831 -

02118 UL12509 AR Clip, CP4394 - UL12509 -

02122 AS20624 AR Nut, 0.190 in. dia, CP4394 - AS20624 -

02323 AS48408 AR Bolt, 0.190 in. dia X

0.500 in., CP4392

- AS48408 -

02324 K8831 AR Washer, 0.190 in. X 0,51

mm thk, CP4392

- K8831 -

02326 UL12509 AR Clip, CP4392 - UL12509 -

Printed in Great Britain

RB.211−72−AG270

Page 7

Sep. 2/09

R Mar.21/11
FIG

ITEM

NO.

NEW

PART

NO.

QTY PART TITLE MAT OLD

PART

NO.

INSTR

DISP

02330 AS20624 AR Nut, 0.190 in. dia, CP4392 - AS20624 -

02483 AS48408 AR Bolt, 0.190 in. dia X

0.500 in., CP4508

- AS48408 -

02484 K8831 AR Washer, 0.190 in. X 0,51

mm thk, CP4508

- K8831 -

02486 UL12510 AR Clip, CP4508 - UL12510 -

02490 AS20624 AR Nut, 0.190 in. dia, CP4508 - AS20624 -

Printed in Great Britain

RB.211−72−AG270

Page 8

Sep. 2/09

R Mar.21/11
3. Accomplishment Instructions

A. At overhaul

NOTE: Some steps may not be required since certain parts may already have been

disassembled or the applicable system is not available.

NOTE: All Fig/Item references quoted below are for the EIPC.

(1) Prepare the engine for borescope inspection of the Intermediate Pressure

(IP) compressor stage 8 balance land (EIPC Ref. 72-32-31, IP compressor

shaft).

(a) Fit the IP compressor turning tool (HU38122-3 or HU40324).

(b) Gain access to the intermediate case, vane 8, by removing the air tube

(EIPC Ref. 75-22-49, Fig/Item No. 15-100). Refer to Fig.1.

CAUTION: YOU MUST HOLD THE TUBE(S) WHEN YOU LOOSEN/TIGHTEN THE

CONNECTIONS. MAKE SURE THAT THE TUBE(S) CANNOT TWIST. DAMAGE TO

THE TUBE(S) CAN OCCUR IF THEY DO TWIST.

(i) Remove and retain the clipstacks CP4402, CP4508, CP4394,

CP4393, CP4392 and CP4391. Refer to Fig.1, Fig.9, Fig.10,

Fig.11, Fig.12, Fig.13 and Fig.14.

(ii) Disconnect the rear end of the air tube (EIPC Ref. 75-22-49,

Fig/Item No. 15-100) from the air tubes (EIPC Ref. 75-22-49,

Fig/Item No. 16-500 and 16-100). Refer to Fig.1.

(iii) Disconnect the front end of the air tube (EIPC Ref. 75-22-49,

Fig/Item No. 15-100) from the intermediate case by removing the

4 bolts (EIPC Ref. 75-22-49, Fig/Item No. 15-106). Refer to

Fig.1.

NOTE: If the inserts are damaged when the bolts are removed,

replace them as required (see 2. Material Information).

(iv) Retain the air tube (EIPC Ref. 75-22-49, Fig/Item No. 15-100)

and the 4 bolts (EIPC Ref. 75-22-49, Fig/Item No. 15-106).

(2) Perform the borescope inspection of the Intermediate Pressure (IP)

compressor stage 8 balance land.

(a) Insert the borescope into the intermediate case, vane 8. The vane will

guide the borescope to the rear of the IP compressor drum. Articulate

the borescope to view the balance land at the rear of the IP

compressor stage 8 from two directions. Refer to Fig.2. The view from

the borescope should be similar to that shown in Fig.3 and Fig.4.

Printed in Great Britain

RB.211−72−AG270

Page 9

Sep. 2/09

R Mar.21/11
CAUTION: YOU MUST MAKE SURE THAT THE BORESCOPE IS NOT IN THE PATH OF

ANY ROTATING COMPONENTS WHEN YOU TURN THE ENGINE. IF THE

BORESCOPE AND ROTATING COMPONENT TOUCH, DAMAGE TO EITHER THE

ROTATING COMPONENT OR BORESCOPE WILL OCCUR.

(b) Inspect zone A of the balance land, as shown in Fig.5, over the entire

circumference (the criteria for this inspection is in Accomplishment

Instructions (3.A.(3))). Look for the following:

(i) Cracks (for example of previous crack position, refer to Fig.6

and Fig.7).

(ii) Dents or nicks.

(iii) Balance weights and surrounding area

(1) Check for gaps between balance weight, clamp, washer or bolt

head,

R

R which indicate that the balance weight is loose. Fig.8

illustrates a properly fitted balance weight.

(2) Carefully inspect the area around the balance weights.

Carefully inspect all around the edge of the clamp plate to

make sure there is no cracking that has started underneath

the clamp plate.

NOTE: In some instances no balance weights will be fitted to

the balance land (because they were not needed to

balance the IP Compressor Shaft at the previous shop

visit or because SB72-G402 has been accomplished). If

SB72-G402 has been accomplished it is not necessary to

complete the inspection (see 1.A., Effectivity),

otherwise complete the inspection of zone A of the

balance land over the entire circumference.

(c) Withdraw the borescope from the intermediate case, vane 8.

(d) Install the air tube (EIPC Ref. 75-22-49, Fig/Item No. 15-100).

CAUTION: YOU MUST HOLD THE TUBE(S) WHEN YOU LOOSEN/TIGHTEN THE

CONNECTIONS. MAKE SURE THAT THE TUBE(S) CANNOT TWIST. DAMAGE TO

THE TUBE(S) CAN OCCUR IF THEY DO TWIST.

(i) Attach the air tube (EIPC Ref. 75-22-49, Fig/Item No. 15-100)

to the intermediate case with 4 bolts (EIPC Ref. 75-22-49,

Fig/Item No. 15-106). Torque tighten the bolts to 11,5 Nm (100

lbfin.).

Printed in Great Britain

RB.211−72−AG270

Page 10

Sep. 2/09

R Mar.21/11
(ii) Attach the adaptor of the air tube (EIPC Ref. 75-22-49,

Fig/Item No. 15-100) to the tube coupling nuts of air tubes

(EIPC Ref. 75-22-49, Fig/Item No. 16-500 and 16-100) and torque

to 37 Nm (325 lbfin.). Safety with OMat 2/142 Safety cable or

OMat 238 lockwire in accordance with SPM 70-12-04, Procedures

used to lock threaded parts. Refer to Fig.1.

(iii) Install the clipstacks CP4402, CP4508, CP4394, CP4393, CP4392

and CP4391. Torque tighten the nuts (Part No.AS20624) 6 off to

6,2 Nm (55 lbfin.). Refer to Fig.1, Fig.9, Fig.10, Fig.11,

Fig.12, Fig.13 and Fig.14.

(e) Make sure all tools and equipment are removed from the work area.

(f) Remove the Rolls-Royce Trent IP rotor turning tool (HU40324 or

HU38122-3).

(3) Acceptance criteria.

PROCEDURE

(a) Cracked

RELATED DATA

Reject.

Inform Rolls-Royce as soon as

practically possible.

(b) Dented or nicked Reject

(c) Loose balance weights Reject

Printed in Great Britain

RB.211−72−AG270

Page 11

Sep. 2/09

R Mar.21/11
B. On-wing

WARNING: DO NOT TOUCH HOT PARTS WITHOUT APPLICABLE GLOVES. HOT PARTS CAN CAUSE

INJURY.

WARNING: DO NOT TOUCH THE COMPONENTS OF THE OIL SYSTEM IF THE ENGINE IS HOT THESE

COMPONENTS STAY HOTTER THAN OTHER COMPONENTS. HOT COMPONENTS CAN BURN.

CAUTION: IN ORDER TO REDUCE THE POTENTIAL FOR MULTIPLE-ENGINE IN-FLIGHT SHUTDOWN,

POWER LOSS OR OTHER ANOMALY 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

MAKE SURE THAT MAINTENANCE TASKS HAVE BEEN COMPLETED AS DEFINED.

MAINTENANCE GUIDELINES SHOULD BE REVISED, WHERE POSSIBLE, TO PROMOTE

THIS RECOMMENDATION.

CAUTION: DO NOT START A BORESCOPE INSPECTION FOR 2-3 HOURS AFTER ENGINE HAS

STOPPED. THE ENGINE IS HOT IMMEDIATELY AFTER THE ENGINE IS STOPPED AND

CAN CAUSE BURNS AND DAMAGE TO BORESCOPE INSPECTION EQUIPMENT.

(1) Prepare the engine for borescope inspection of the Intermediate Pressure

(IP) compressor stage 8 balance land.

(a) Energize the ground service network in accordance with Aircraft

Maintenance Manual (AMM), 72-00-00, Borescope Inspection of the

Intermediate Pressure (IP) Compressor Blades.

(b) Get access to the avionics compartment in accordance with AMM,

72-00-00, Borescope Inspection of the Intermediate Pressure (IP)

Compressor Blades.

(c) Open the applicable circuit breakers and install safety tags in

accordance with AMM, 72-00-00, Borescope Inspection of the

Intermediate Pressure (IP) Compressor Blades.

(d) Open the fan cowl doors in accordance with AMM, 72-00-00, Borescope

Inspection of the Intermediate Pressure (IP) Compressor Blades.

(e) Deactivate the thrust reverser in accordance with AMM, 72-00-00,

Borescope Inspection of the Intermediate Pressure (IP) Compressor

Blades.

(f) Open the thrust reverser cowl doors in accordance with AMM, 72-00-00,

Borescope Inspection of the Intermediate Pressure (IP) Compressor

Blades.

(g) Use the LP system immobiliser (HU80955) to prevent movement of the LP

compressor rotor.

Printed in Great Britain

RB.211−72−AG270

Page 12

Sep. 2/09

R Mar.21/11
(h) Turn the engine IP system in accordance with AMM, 72-00-00, Turn the

Engine Intermediate Pressure System.

(i) Gain access to the intermediate case, vane 8, by removing the air tube

(Part No. FK19091). Refer to Fig.1.

CAUTION: YOU MUST HOLD THE TUBE(S) WHEN YOU LOOSEN/TIGHTEN THE

CONNECTIONS. MAKE SURE THAT THE TUBE(S) CANNOT TWIST. DAMAGE TO

THE TUBE(S) CAN OCCUR IF THEY DO TWIST.

(i) Remove and retain the clipstacks CP4402, CP4508, CP4394,

CP4393, CP4392 and CP4391. Refer to Fig.1, Fig.9, Fig.10,

Fig.11, Fig.12, Fig.13 and Fig.14.

(ii) Disconnect the rear end of the air tube (Part No. FK19091) from

the air tubes (Part No. FK12411 and FK12412). Refer to Fig.1.

(iii) Disconnect the front end of the air tube (Part No. FK19091)

from the intermediate case by removing the 4 bolts (Part No.

AS48512). Refer to Fig.1.

NOTE: If the inserts are damaged when the bolts are removed,

replace them as required (see 2. Material Information).

(iv) Retain the air tube (Part No. FK19091) and the 4 bolts (Part

No. AS48512).

(2) Perform the borescope inspection of the Intermediate Pressure (IP)

compressor stage 8 balance land.

(a) Insert the borescope into the intermediate case, vane 8. The vane will

guide the borescope to the rear of the IP compressor drum. Articulate

the borescope to view the balance land at the rear of the IP

compressor stage 8 from two directions. Refer to Fig.2. The view from

the borescope should be similar to that shown in Fig.3 and Fig.4.

CAUTION: YOU MUST MAKE SURE THAT THE BORESCOPE IS NOT IN THE PATH OF

ANY ROTATING COMPONENTS WHEN YOU TURN THE ENGINE. IF THE

BORESCOPE AND ROTATING COMPONENT TOUCH, DAMAGE TO EITHER THE

ROTATING COMPONENT OR BORESCOPE WILL OCCUR.

(b) Inspect zone A of the balance land, as shown in Fig.5, over the entire

circumference (the criteria for this inspection is in Accomplishment

Instructions (3.B.(4))). Look for the following:

(i) Cracks (for example of previous crack position, refer to Fig.6

and Fig.7).

(ii) Dents or nicks.

Printed in Great Britain

RB.211−72−AG270

Page 13

Sep. 2/09

R Mar.21/11
(iii) Balance weights and surrounding area

(1) Check for gaps between balance weight, clamp, washer or bolt

head,

R

R which indicate that the balance weight is loose. Fig.8

illustrates a properly fitted balance weight.

(2) Carefully inspect the area around the balance weights.

Carefully inspect all around the edge of the clamp plate to

make sure there is no cracking that has started underneath

the clamp plate.

NOTE: In some instances no balance weights will be fitted to

the balance land (because they were not needed to

balance the IP Compressor Shaft at the previous shop

visit or because SB72-G402 has been accomplished). If

SB72-G402 has been accomplished it is not necessary to

complete the inspection (see 1.A., Effectivity),

otherwise complete the inspection of zone A of the

balance land over the entire circumference.

(c) Withdraw the borescope from the intermediate case, vane 8.

(3) Put the aircraft back to serviceable condition.

(a) Install the air tube (Part No. FK19091).

CAUTION: YOU MUST HOLD THE TUBE(S) WHEN YOU LOOSEN/TIGHTEN THE

CONNECTIONS. MAKE SURE THAT THE TUBE(S) CANNOT TWIST. DAMAGE

TO THE TUBE(S) CAN OCCUR IF THEY DO TWIST.

(i) Attach the air tube (Part No. FK19091) to the intermediate case

with 4 bolts (Part No. AS48512). Torque tighten the bolts to

1.13 m.daN (100 lbfin.).

(ii) Attach the adaptor of air tube (Part No. FK19091) to the tube

coupling nuts of air tubes (Part No. FK12411 and FK12412) and

torque to 3.7 m.daN (325 lbfin.). Safety with OMat 2/142 Safety

cable or OMat 238 lockwire in accordance with AMM 70-12-04,

Locking Techniques for threaded parts. Refer to Fig.1.

(iii) Install the clipstacks CP4402, CP4508, CP4394, CP4393, CP4392

and CP4391. Torque tighten the nuts (Part No.AS20624) 6 off to

0.62 m.daN (55 lbfin.). Refer to Fig.1, Fig.9, Fig.10, Fig.11,

Fig.12, Fig.13 and Fig.14.

(b) Make sure all tools and equipment are removed from the work area.

(c) Remove the Rolls-Royce Trent IP rotor turning tool (HU40324 or

HU38122-3) in accordance with AMM, 72-00-00, Turn the Engine

Intermediate Pressure System.

Printed in Great Britain

RB.211−72−AG270

Page 14

Sep. 2/09

R Mar.21/11
(d) Remove the LP system immobiliser (HU80955).

(e) Close up the engine and put the aircraft back to its usual condition.

(i) Close the thrust reverser cowl doors in accordance with AMM,

72-00-00, Borescope Inspection of the Intermediate Pressure

(IP) Compressor Blades.

(ii) Activate the thrust reverser in accordance with AMM, 72-00-00,

Borescope Inspection of the Intermediate Pressure (IP)

Compressor Blades.

(iii) Remove safety tags and close the applicable circuit breakers in

accordance with AMM, 72-00-00, Borescope Inspection of the

Intermediate Pressure (IP) Compressor Blades.

(iv) Close the fan cowl doors in accordance with AMM, 72-00-00,

Borescope Inspection of the Intermediate Pressure (IP)

Compressor Blades.

(v) De-energize the ground service network in accordance with AMM,

72-00-00, Borescope Inspection of the Intermediate Pressure

(IP) Compressor Blades.

(4) Acceptance criteria.

PROCEDURE

(a) Cracked

RELATED DATA

Reject.

Inform Rolls-Royce as soon as

practically possible.

(b) Dented or nicked Reject within 20 cycles. Supply

pictures of dent or nick to

Rolls-Royce Technical Helpdesk.

(c) Loose balance weights Reject within 20 cycles. Supply

pictures of balance weights to

Rolls-Royce Technical Helpdesk.

(5) Record Engine Serial Number, Engine Hours Since New, Engine Cycles Since

New, IP Compressor Shaft Part Number, IP Compressor Shaft Serial Number,

IP Compressor Shaft Cycles Since New, IP Compressor Shaft Hours Since New

and the results of the inspection from Accomplishment Instructions

3.B.(2)(b)).

C. Accomplishment of this Non-Modification Service Bulletin should be recorded in

the engine logbook or in accordance with the local SB tracking system

procedures.

Printed in Great Britain

RB.211−72−AG270

Page 15

Sep. 2/09

R Mar.21/11
Disassembly of Air Tube (Part No. FK19091)

Fig.1

Printed in Great Britain

RB.211−72−AG270

Page 16

Sep. 2/09

R Mar.21/11
Illustration of Borescope Articulation

Fig.2

Printed in Great Britain

RB.211−72−AG270

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View From Direction 1

Fig.3

Printed in Great Britain

RB.211−72−AG270

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View From Direction 2

Fig.4

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RB.211−72−AG270

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Identification of Zones To Be Inspected

Fig.5

Printed in Great Britain

RB.211−72−AG270

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Position of Crack in the First Trent 800 Finding

Fig.6

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RB.211−72−AG270

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Position of Crack in the First Trent 700 Finding

Fig.7

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RB.211−72−AG270

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R

R Properly Fitted Balance Weight

R Fig.8

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RB.211−72−AG270

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Clipstack CP4402

Fig.9

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RB.211−72−AG270

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Clipstack CP4508

Fig.10

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RB.211−72−AG270

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Clipstack CP4394

Fig.11

Printed in Great Britain

RB.211−72−AG270

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Clipstack CP4393

Fig.12

Printed in Great Britain

RB.211−72−AG270

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Clipstack CP4392

Fig.13

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RB.211−72−AG270

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Clipstack CP4391

Fig.14

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RB.211−72−AG270

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Non-Modification Service Bulletin 72-AG270

1. Record accomplishment of this Non-Modification Service Bulletin in accordance

with local Service Bulletin tracking system procedures.

2. Advise your local Rolls-Royce service representative of NMSB accomplishment and

inspection results regardless of findings.

APPENDIX 1

Printed in Great Britain

RB.211−72−AG270

Appendix 1 - Page 1 of 1

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