P.O. Box 31, DERBY 

DE24 8BJ, UK 

Telephone: 44 (0) 1332 242424 

Fax: 44 (0) 1332 249936 

1 - Rol Is-Royce 

PUBLICATION TRANSMITTAL 

The technical information contained in this document has been approved under the authority 

of - See Planning Information, Approval. 

Date Jul. 7/14 

RB211 TRENT 500 SERIES PROPULSION SYSTEMS NON-MODIFICATION SERVICE BULLETIN 

ALERT 

This document transmits Revision 1 to Service Bulletin RB211-72-AH058 

Document History 

Service Bulletin Revision Status 

Initial Issue Dec.13/12 

Bulletin Revision 1 

Supplement Revi si on Status 

Remove Incorporate 

Pages 1 to 18 of the Pages 1 to 19 of the 

Service Bulletin Service Bulletin 

ALERT 

Reason for change 

To revise 1 .A. Effectivity 

to reflect that the 

inspection procedure i n 

this NMSB is not required 

for engines that have 

incorporated SB 72-AH555. 

Updated 1.B. Reason, 1.D. 

Compliance, 1.E. Approval 

and 1.1. References. 

Transmittal - Page 1 of 3 

CHECK THAT ALL PREVIOUS TRANSMllTALS HAVE BEEN INCORPORATED 

If any have not been received please advise Customer Data Services, Rolls-Royce plc, Derby, England 

O Rolls-Royce plc (date as above) Printed in Great Britain 
All pages of

Appendix 1

Page 1 of Appendix 1 To revise 1.A. Effectivity

to reflect that the

inspection procedure in

this NMSB is not required

for engines that have

incorporated SB 72-AH555.

Updated 1.B. Reason, 1.D.

Compliance, 1.E. Approval

and 1.I. References.

Printed in Great Britain

RB.211−72−AH058

Transmittal - Page 2
LIST OF EFFECTIVE PAGES

The effective pages to this Service Bulletin following incorporation of Revision

1 are as follows:

Page Revision Number Revision Date

Bulletin

R 1 1 Jul.7/14

R 2 1 Jul.7/14

R 3 1 Jul.7/14

R 4 1 Jul.7/14

R 5 1 Jul.7/14

R 6 1 Jul.7/14

R 7 1 Jul.7/14

R 8 1 Jul.7/14

R 9 1 Jul.7/14

R 10 1 Jul.7/14

R 11 1 Jul.7/14

R 12 1 Jul.7/14

R 13 1 Jul.7/14

R 14 1 Jul.7/14

R 15 1 Jul.7/14

R 16 1 Jul.7/14

R 17 1 Jul.7/14

R 18 1 Jul.7/14

R 19 1 Jul.7/14

Appendix 1

R 1 1 Jul.7/14

Printed in Great Britain

RB.211−72−AH058

Transmittal - Page 3
1. Planning Information

A. Effectivity

Airbus A340

ALL RB211 TRENT 553-61, TRENT 553A2-61, TRENT 556-61, TRENT 556A2-61, TRENT

R 556B-61, TRENT 556B2-61, TRENT 560-61, TRENT 560A2-61 Engines pre SB 72-AH555.

B. Reason

(1) Problem

Cracking of the rear balance land has previously been found in Trent 800

and Trent 700 IP compressor shafts. The balancing feature and method is

similar on Trent 500 engines although the disc geometry is different from

Trent 700 and Trent 800 engines

Non-Modification Service Bulletin (NMSB) 72-AF260 was issued to specify an

in-shop visual inspection of the rear balance land and applied to Trent

500, Trent 700 and Trent 800 engines. NMSB 72-AF260 now applies to Trent

500 engines only.

NMSB 72-G448 specifies an enhanced crack detection technique, eddy current

inspection for the rear balance land when the rear of the IPC module is

exposed and a borescope inspection of the balance land when it is not

exposed. This inspection is to be done in-shop on Trent 500 and Trent 900

engines.

Following inspection at shop visit, the first instance of cracking was

confirmed in a Trent 500 IP compressor shaft rear balance land. NMSB

R issued to specify repeat on-wing borescope 72-AH058 was subsequently

inspections for Trent 500 engines.

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

compressor rear balance land, gaining access through the intermediate case

vane 8. This inspection can also be performed in-shop, in accordance with

NMSB 72-G448.

R

R

R

R

Revision 1 of this NMSB has been issued to reflect that this inspection is

not required for engines that have incorporated SB 72-AH555, which

introduces a revised balancing method for the IP compressor rotor, see

1.I. References.

R

R

R

R

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

NON-MODIFICATION SERVICE BULLETIN - NON - MOD.72-AH058

Printed in Great Britain

RB.211−72−AH058

Page 1 of 19

Dec 13/12

R Jul. 7/14
R (2) Safety Intent

The safety intent of this NMSB is to prevent threat to the rotor

integrity, which, if not corrected, could lead to IP compressor rotor

shaft failure and consequent non-contained high energy debris.

R

R

R

C. Description

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

shaft rear balance land in order to maintain serviceability and obtain data to

support engineering analysis.

Send copies of the NMSB inspection results to your Rolls-Royce service

representative by completion of Appendix 1 (borescope inspection) or send an

equivalent form containing the same information.

A record of accomplishment should be attached to the engine record.

D. Compliance

(1) On-wing

ALERT

This NMSB must be accomplished within 340 flight cycles of the publication

date of this NMSB, unless NMSB 72-G448 is accomplished within this time

period on this IP compressor shaft.

This NMSB must then be repeated on an ongoing basis within 340 flight

cycles of the last previous accomplishment of NMSB 72-AH058 or NMSB

72-G448 on the IP compressor shaft.

This Non-Modification Service Bulletin is anticipated to be the subject of

a European Aviation Safety Agency (EASA) and Federal Aviation

Administration (FAA) Airworthiness Directive.

R

R

R

(2) At overhaul

Not applicable.

E. Approval

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

under the authority of Design Organisation Approval EASA.21J.035 on Dec.13/12

and was re-approved on Jun.24/14.

R

R

Printed in Great Britain

RB.211−72−AH058

Page 2

Dec 13/12

R Jul. 7/14
F. Manpower

(1) On-wing

(a) Time to gain access

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

R person).

(b) Time to inspect

R 1.5 hours (two persons).

(c) Time to restore to serviceable condition

R 0.5 hours (one person).

(2) At overhaul

Not applicable.

G. Material Price and Availability

OMat 4/46 - Jointing Compound

OMat 2/142 - Safety Cable

H. Tooling Price and Availability

The following equipment is required to perform the inspection

(1) 4mm or 6mm flexible borescope with forward viewing and side view tips

(2) IP Rotor turning tool HU40324 (Trent 500)

(3) Borescope guide tube HU82346 or, as an alternative, a locally manufactured

nylon guide tube (made in accordance with the approximate dimensions given

in Fig.9) may be required to assist the correct positioning of the probe

viewing tip during inspection.

(4) LP system immobiliser HU41764-1 or HU44525-1

I. References

(1) 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−AH058

Page 3

Dec 13/12

R Jul. 7/14
(b) 72-G448

Engine - IP Compressor Shaft - In shop Eddy Current Inspection of

Balance Land

R (2) Rolls-Royce RB211 Service Bulletin:

R 72-AH555

Engine - IP Compressor Blades - Introduction of revised method of

balancing the rear of the IP compressor rotor

R

R

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

Pressure System

Printed in Great Britain

RB.211−72−AH058

Page 4

Dec 13/12

R Jul. 7/14
2. Material Information

A. Parts required to accomplish this NMSB:

75-22-49

FIG

ITEM

NO.

NEW

PART

NO.

QTY PART TITLE MAT OLD

PART

NO.

INSTR

DISP

21100 FW17133 AR Air Tube - FW17133 -

21106 AS48510 AR Bolt - AS48510 -

21112 AS12944 AR Washer - AS12944 -

21113 CU37148 AR Washer - CU37148 -

21114 AS48513 AR Bolt - AS48513 -

21125 AS48408 AR Bolt (CP101919) - AS48408 -

21126 K8831 AR Washer (CP101919) - K8831 -

21128 UP11470 AR Clip (CP101919) - UP11470 -

21132 AS20624 AR Nut (CP101919) - AS20624 -

NOTE: Quantity As Required (AR) up to a maximum of 3.

Printed in Great Britain

RB.211−72−AH058

Page 5

Dec 13/12

R Jul. 7/14
3. Accomplishment Instructions

A. On-Wing Borescope Inspection of Trent 500 Engines

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

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

MINUTES AND GET MEDICAL AID.

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

CAUSE INJURY.

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

POWER LOSS OR OTHER ANOMALIES 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.

CAUTION: DO NOT START THE BORESCOPE INSPECTION UNTIL THE ENGINE HAS COOLED TO

WITHIN THE BORESCOPE MANUFACTURERS RECOMMENDATIONS. THE ENGINE IS HOT

IMMEDIATELY AFTER THE ENGINE IS STOPPED AND CAN CAUSE BURNS AND DAMAGE

TO BORESCOPE INSPECTION EQUIPMENT.

(1) Prepare Engine for Inspection

(a) Prepare the engine for Borescope Inspection of the Intermediate

Pressure (IP) Compressor Stage 8 Balance Land.

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

accordance with AMM, 72-00-00, Turn the Engine Intermediate Pressure

System.

(c) Safely open the left and right thrust reversers as in accordance with

AMM, 72-00-00, Turn the Engine Intermediate Pressure System.

(d) Use the LP system immobiliser (HU41764-1 or HU44525-1) to prevent

movement of the LP compressor in accordance with AMM, 72-00-00, Turn

the Engine Intermediate Pressure System.

(e) Attach the Rolls-Royce Trent IP Turning Tool (HU40324) to turn the IP

system in accordance AMM, 72-00-00, Turn the Engine Intermediate

Pressure System.

Printed in Great Britain

RB.211−72−AH058

Page 6

Dec 13/12

R Jul. 7/14
CAUTION: YOU MUST HOLD THE TUBE(S) WHEN YOU LOOSEN OR TIGHTEN THE

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

IF THE TUBE(S) DO TWIST.

(f) Gain access to the intermediate case, vane 8 by removing the IP8

buffer air tube (P/N FW17133). See Fig.1.

(i) Disconnect air tube (P/N FW17134) or (P/N FW69876) from the IP8

buffer air tube (P/N FW17133) at the intermediate case

diaphragm. See Fig.1.

(ii) Remove and retain the two bolts (P/N AS48513), two washers (P/N

CU37148) and (P/N AS12944) that attach the IP8 buffer air tube

(P/N FW17133) to the intermediate case diaphragm. See Fig.1.

(iii) Remove and retain the clipstack CP101919. See Fig.2.

(iv) Remove and retain the three bolts (P/N AS48510) to allow

removal of the IP8 buffer air tube (P/N FW17133). See Fig.1.

(2) Perform the initial borescope inspection of the IP compressor stage 8 disc

balance land using the forward viewing tip. See Fig.3.

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

ROTATING COMPONENT WHEN YOU TURN THE ENGINE. IF THE BORESCOPE

AND THE ROTATING COMPONENT TOUCH, DAMAGE TO EITHER THE ROTATING

COMPONENT OR THE BORESCOPE WILL OCCUR.

(a) Insert the borescope with a forward viewing tip fitted into the

intermediate case vane 8 offtake hole. The vane will guide the

borescope towards the rear of the IP compressor stage 8 disc.

Articulate the borescope to view the balance land rear face as shown

in Fig.3.

(b) Use the HU40324 turning tool to slowly rotate the IP compressor and

inspect the balance land over the entire circumference of the balance

land. Note that together with the final inspection zone A of the

balance land should be inspected over the entire circumference. See

Fig.4.

(c) Look for cracks, dents or nicks and loose balance weights, see Fig.5

and Fig.6. For acceptance criteria refer to step 3.A.(5).

NOTE: 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.

(d) Record the results in Appendix 1.

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

Printed in Great Britain

RB.211−72−AH058

Page 7

Dec 13/12

R Jul. 7/14
(3) Perform the final borescope inspection of the IP compressor stage 8 disc

balance land using the side viewing tip. See Fig.3.

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

ROTATING COMPONENT WHEN YOU TURN THE ENGINE. IF THE BORESCOPE

AND THE ROTATING COMPONENT TOUCH, DAMAGE TO EITHER THE ROTATING

COMPONENT OR THE BORESCOPE WILL OCCUR.

(a) Insert the borescope with a side viewing tip fitted into the guide

tube so that the tip of the borescope is just short of the guide tube

end. Face the curved end of the guide tube towards the front of the

engine and insert it into the intermediate case vane 8. The guide tube

will need to be straightened by hand to go into the vane. Push the

guide tube into the engine until its end is in the cavity behind the

stage 8 disc when it will then spring back to its original shape.

(b) Push the borescope through the guide tube until the viewing tip

emerges from the guide tube. Rotate and articulate the borescope until

it views the balance land recess outer diameter and chamfer as shown

in Fig.3.

(c) Use the HU40324 turning tool to slowly rotate the IP compressor and

inspect the balance land over the entire circumference of the balance

land. Note that together with the initial inspection zone A of the

balance land should be inspected over the entire circumference. See

Fig.4.

(d) Look for cracks, dents or nicks and loose balance weights (See Fig.6

and 7). For acceptance criteria, refer to step 3.A.(5).

NOTE: 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.

(e) Record the results in Appendix 1.

(f) Withdraw the borescope until the viewing tip is inside the guide tube

and then withdraw the borescope and guide tube through the

intermediate case vane 8.

(4) Restore the engine to a serviceable condition.

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

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

OCCUR IF THE TUBE(S) DO TWIST.

(a) Install the IP8 buffer air tube (P/N FW17133). See Fig.1.

(i) Clean the mating faces of the tube flange (P/N FW17133) and the

intermediate case diaphragm.

Printed in Great Britain

RB.211−72−AH058

Page 8

Dec 13/12

R Jul. 7/14
(ii) Apply a thin layer of OMat 4/46, jointing compound to the

mating faces of the flange and the compressor intermediate case

diaphragm. See Fig.8.

(iii) Let OMat 4/46, jointing compound dry for a minimum of 10

minutes.

(iv) Make sure all of OMat 4/46, jointing compound is removed from

the bolt holes.

(v) Attach the IP8 buffer air tube (P/N FW17133) to the compressor

intermediate case diaphragm with two bolts (P/N AS48513), two

washers (P/N AS12944) and (P/N CU37148), see Fig.1.

(vi) Torque tighten the two bolts (P/N AS48513) to 11,5 Nm (100

lbfin).

(vii) After 10 minutes, torque the bolts (P/N AS48513) again to 11,5

Nm (100 lbfin).

(viii) Attach the IP8 buffer air tube (P/N FW17133) to the compressor

intermediate case with the three bolts (P/N AS48510). Refer to

Fig.1.

(ix) Torque tighten the three bolts (P/N AS48510) to 11,5 Nm (100

lbfin).

(x) Attach the IP8 buffer air tube (P/N FW17133) to the bracket

(P/N FK32426) at the clip position CP101919, using bolt (P/N

AS48408), washer (P/N K8831) and nut (P/N AS20624). See Fig.2.

(xi) Torque tighten the nut (P/N AS20624) to 6,2 Nm (55 lbfin).

(xii) Connect the tube (P/N FW17134 or P/N FW69876) to tube (P/N

FW17133). See Fig.1.

(xiii) Torque tighten the union nut on the tube (P/N FW17134 or P/N

FW69876) to 67 Nm (590 lbfin).

(xiv) Secure the union nut on tube (P/N FW17134 or P/N FW69876) with

OMat 2/142 safety cable.

(b) Make the Engine ready for operation

(i) Remove the Rolls-Royce Trent IP turning tool (HU40324) and LP

system immobiliser (HU41764-1 or HU44525-1) in accordance with

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

Intermediate Pressure System.

Printed in Great Britain

RB.211−72−AH058

Page 9

Dec 13/12

R Jul. 7/14
(ii) Return the engine to operating condition in accordance with

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

Intermediate Pressure System

(5) Acceptance Criteria

(a) Cracked - Reject, inform Rolls-Royce as soon as practically possible.

(b) Dented or Nicked:

(i) Reject within 20 cycles. Supply pictures of dent or nick to

Rolls-Royce Technical Help Desk.

(c) Loose balance weights:

(i) Reject within 20 cycles. Supply pictures of balance weights to

Rolls-Royce Technical Help Desk.

NOTE: If any of the acceptance criteria in step 3.A.(5) are not

met; retain and quarantine the balance weights, clamp

plates, bolts and washers and IP compressor shaft when

removed within 20 cycles. Refer to Rolls-Royce via your

local representative within 2 weeks of the inspection.

(6) Record the inspection results on the inspection sheet provided in Appendix

1 or similar form containing the same information.

(7) Accomplishment of this Non-Modification Service Bulletin should be

recorded in the engine logbook.

Printed in Great Britain

RB.211−72−AH058

Page 10

Dec 13/12

R Jul. 7/14
Trent 500 Engines - Location of IP8 Buffer Air Tube

Fig.1

Printed in Great Britain

RB.211−72−AH058

Page 11

Dec 13/12

R Jul. 7/14
Clip Position 101919

Fig.2

Printed in Great Britain

RB.211−72−AH058

Page 12

Dec 13/12

R Jul. 7/14
Trent 500 Engines - Borescope View Directions

Fig.3

Printed in Great Britain

RB.211−72−AH058

Page 13

Dec 13/12

R Jul. 7/14
Trent 500 Engines - Identification of Zone A - The Zone to be inspected

Fig.4

Printed in Great Britain

RB.211−72−AH058

Page 14

Dec 13/12

R Jul. 7/14
Previously seen Crack Position on Trent 700 Engine

Fig.5

Printed in Great Britain

RB.211−72−AH058

Page 15

Dec 13/12

R Jul. 7/14
Properly Fitted Balance Weight

Fig.6

Printed in Great Britain

RB.211−72−AH058

Page 16

Dec 13/12

R Jul. 7/14
Previously seen Crack Position on Trent 800 Engine

Fig.7

Printed in Great Britain

RB.211−72−AH058

Page 17

Dec 13/12

R Jul. 7/14
Jointing Compound Application

Fig.8

Printed in Great Britain

RB.211−72−AH058

Page 18

Dec 13/12

R Jul. 7/14
deh0013727

288 mm

290 mm

326 mm

38 mm

52°

Ø 7.5 mm

Ø 10 mm

97 mm

R 35.5 mm

Nylon Guide Tube

Fig.9

Printed in Great Britain

RB.211−72−AH058

Page 19

Dec 13/12

R Jul. 7/14
1. This form is to be completed for every shaft inspected in accordance with

Accomplishment Instructions (3.A.).

2. Record Accomplishment of this Non-Modification Service Bulletin in accordance

with local Service Bulletin tracking procedures

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

inspection results regardless of findings.

Trent 500 Visual Borescope Inspection Results

Form to be completed for every engine inspected, results to be sent to Rolls-Royce,

via your local representative.

Feedback Sheet NMSB 72-AH058 Visual Borescope Inspection of IPC 8 Balance Land

Operator

Date of Inspection

Engine Serial Number

Engine Mark

Engine CSN

Engine TSN

IPC Shaft Part No.

IPC Shaft Ser No.

IPC Shaft CSN

IPC Shaft TSN

Borescope Inspection Result (if none, record N/A, if

finding record dimensions and position)

Initial Inspection Final Inspection

Cracking

Dents or Nicks on the

Balance Land

Loose Balance Weights

Inspected by: Stamp:

APPENDIX 1

Printed in Great Britain

RB.211−72−AH058

Appendix 1 - Page 1 of 1

Dec 13/12

R Jul. 7/14