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 R 1 4 Mar.21/11 R 2 4 Mar.21/11 R 3 4 Mar.21/11 R 4 4 Mar.21/11 R 5 4 Mar.21/11 R 6 4 Mar.21/11 R 7 4 Mar.21/11 R 8 4 Mar.21/11 R 9 4 Mar.21/11 R 10 4 Mar.21/11 R 11 4 Mar.21/11 R 12 4 Mar.21/11 R 13 4 Mar.21/11 R 14 4 Mar.21/11 R 15 4 Mar.21/11 R 16 4 Mar.21/11 R 17 4 Mar.21/11 R 18 4 Mar.21/11 R 19 4 Mar.21/11 R 20 4 Mar.21/11 R 21 4 Mar.21/11 R 22 4 Mar.21/11 R 23 4 Mar.21/11 R 24 4 Mar.21/11 R 25 4 Mar.21/11 R 26 4 Mar.21/11 R 27 4 Mar.21/11 R 28 4 Mar.21/11 R 29 4 Mar.21/11 Appendix 1 R 1 4 Mar.21/11Printed in Great Britain



# RB.211−72−AG270 Transmittal - Page 21. 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-AG270Printed in Great Britain



# RB.211−72−AG270 Page 1 of 29 Sep. 2/09 Mar.21/11 RRevision 3 of this NMSB was R issued to amend the illustration of a properly fitted balance weight (see Fig.8) and also note that this NMSB was R 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 Mar.21/11 RE. 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, Dec.9/09, Dec.17/10, Feb.25/11 R and was re-approved on Mar.15/11. 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 Mar.21/11 R(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 landPrinted in Great Britain



# RB.211−72−AG270 Page 4 Sep. 2/09 Mar.21/11 R(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 Mar.21/11 R2. 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 -

71-52-12Printed in Great Britain



# RB.211−72−AG270 Page 6 Sep. 2/09 Mar.21/11 RFIG 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 Mar.21/11 RFIG 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 Mar.21/11 R3. 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 Mar.21/11 RCAUTION : 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 Mar.21/11 R(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 RejectPrinted in Great Britain



# RB.211−72−AG270 Page 11 Sep. 2/09 Mar.21/11 RB. 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 Mar.21/11 R(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 Mar.21/11 R(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 Mar.21/11 R(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 Mar.21/11 RDisassembly of Air Tube (Part No. FK19091) Fig.1Printed in Great Britain



# RB.211−72−AG270 Page 16 Sep. 2/09 Mar.21/11 RIllustration of Borescope Articulation Fig.2Printed in Great Britain



# RB.211−72−AG270 Page 17 Sep. 2/09 Mar.21/11 RView From Direction 1 Fig.3Printed in Great Britain



# RB.211−72−AG270 Page 18 Sep. 2/09 Mar.21/11 RView From Direction 2 Fig.4Printed in Great Britain



# RB.211−72−AG270 Page 19 Sep. 2/09 Mar.21/11 RIdentification of Zones To Be Inspected Fig.5Printed in Great Britain



# RB.211−72−AG270 Page 20 Sep. 2/09 Mar.21/11 RPosition of Crack in the First Trent 800 Finding Fig.6Printed in Great Britain



# RB.211−72−AG270 Page 21 Sep. 2/09 Mar.21/11 RPosition of Crack in the First Trent 700 Finding Fig.7Printed in Great Britain



# RB.211−72−AG270 Page 22 Sep. 2/09 Mar.21/11 RR

Properly Fitted Balance Weight R Fig.8 RPrinted in Great Britain



# RB.211−72−AG270 Page 23 Sep. 2/09 Mar.21/11 RClipstack CP4402 Fig.9Printed in Great Britain



# RB.211−72−AG270 Page 24 Sep. 2/09 Mar.21/11 RClipstack CP4508 Fig.10Printed in Great Britain



# RB.211−72−AG270 Page 25 Sep. 2/09 Mar.21/11 RClipstack CP4394 Fig.11Printed in Great Britain



# RB.211−72−AG270 Page 26 Sep. 2/09 Mar.21/11 RClipstack CP4393 Fig.12Printed in Great Britain



# RB.211−72−AG270 Page 27 Sep. 2/09 Mar.21/11 RClipstack CP4392 Fig.13Printed in Great Britain



# RB.211−72−AG270 Page 28 Sep. 2/09 Mar.21/11 RClipstack CP4391 Fig.14Printed in Great Britain



# RB.211−72−AG270 Page 29 Sep. 2/09 Mar.21/11 RNon-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 1Printed in Great Britain



# RB.211−72−AG270 Appendix 1 - Page 1 of 1 Sep. 2/09 Mar.21/11 R