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 DateLIST 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 21. 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 Jul.29/15 RRB211 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 Page 2 Oct 1/14 Jul.29/15 R(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**



# RB.211−72−H754 Page 3 Oct 1/14 Jul.29/15 R(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 Page 4 Oct 1/14 Jul.29/15 RF. 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 Page 5 Oct 1/14 Jul.29/15 ROr 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**



# RB.211−72−H754 Page 6 Oct 1/14 Jul.29/15 RL. 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 Page 7 Oct 1/14 Jul.29/15 R2. 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 Page 8 Oct 1/14 Jul.29/15 R(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 Page 9 Oct 1/14 Jul.29/15 R3. 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**



# RB.211−72−H754 Page 10 Oct 1/14 Jul.29/15 R(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 Page 11 Oct 1/14 Jul.29/15 R(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: (a) Align the internal oil feed tube R and install the sealing sleeve (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 tube R at the IP turbine case and to the T-connector of oil feed 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**



# RB.211−72−H754 Page 12 Oct 1/14 Jul.29/15 R(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). (f) Torque the tube connector to the internal oil feed tube R 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 Page 13 Oct 1/14 Jul.29/15 RRemove/Install Oil Feed Tube Assembly And Sealing Sleeve Fig.1**Printed in Great Britain**



# RB.211−72−H754 Page 14 Oct 1/14 Jul.29/15 RClip positions 4396 and 4397 Fig.2**Printed in Great Britain**



# RB.211−72−H754 Page 15 Oct 1/14 Jul.29/15 RClip positions 4398 and 4405 Fig.3**Printed in Great Britain**



# RB.211−72−H754 Page 16 Oct 1/14 Jul.29/15 RSUPPLEMENT - 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 Jul.29/15 R