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 May 20/15 R 2 1 May 20/15 R 3 1 May 20/15 R 4 1 May 20/15 R 5 1 May 20/15 R 6 1 May 20/15 R 7 1 May 20/15 R 8 1 May 20/15 R 9 1 May 20/15 R 10 1 May 20/15 R 11 1 May 20/15 R 12 1 May 20/15 Appendix 1 R 1 1 May 20/15 R 2 1 May 20/15 R 3 1 May 20/15**Printed in Great Britain**



# RB.211−72−AJ035 Transmittal - Page 21. Planning Information A. Effectivity Airbus A330 RB211 TRENT 768, TRENT 772, TRENT 772B, TRENT 772C Engines as follows: (1) Engine Serial Numbers from 41001 to 42330 which are Pre SB 72-H754
B. Reason There have been a total of eleven unplanned engine removals caused by fracture of the HP/IP turbine support internal oil feed tube (EIPC 72-51-24, 02-281) on engines post SB 72-F227 standard. The oil feed tube threaded end adaptor and sealing sleeve are designed to form a sliding joint. If the sliding joint is restrained then the oil feed tube can become compressed during thermal contraction of the turbine casing at the end of the flight cycle. On each subsequent flight, the thermal growth and contraction of the turbine casing relative to the oil tube, during the heating and cooling phases of the flight cycle, applies a pull-push load cycle to the tube, which can lead to low cycle fatigue fracture. Investigation of the oil feed tube sealing sleeve (EIPC 72-51-23, 01-220) found that one of the three different suppliers of this part (Supplier A) had manufactured some sealing sleeves with the internal diameter below the drawing minimum, which can cause binding at the sliding joint. All 'Supplier A' sealing sleeves have been replaced through accomplishment of NMSB 72-AH673. Following investigation of a recent event on an engine with a (Supplier B) sealing sleeve fitted, it was established that some of the oil feed tube adaptors (EIPC 72-51-24, 02-280) have been manufactured with the outer diameter larger than drawing maximum, which can also cause binding at the sliding joint. C. Description This Non-Modification Service Bulletin (NMSB) instructs visual inspection of manufacturing markings on the sealing sleeve, to identify whether the sealing sleeve has previously been replaced in accordance with NMSB 72-AH673. If the sealing sleeve markings show that it has not previously been replaced in accordance with NMSB 72-AH673, this NMSB instructs replacement of the sealing sleeve and external oil feed tube with SB 72-H754 parts, which alleviate binding at the sliding joint. ENGINE - HP/IP TURBINE BEARING SUPPORT - INSPECTION AND REPLACEMENT OF THE OIL FEED TUBE SEALING SLEEVE - NON-MODIFICATION SERVICE BULLETIN - NON - MOD.72-AJ035**Printed in Great Britain**



# RB.211−72−AJ035 Page 1 of 12 May 11/15 May.20/15 RIt is only necessary to carry out the action once in accordance with this NMSB either on-wing or in-shop. Revision 1 of this NMSB is issued to revise 1.D. Compliance to remove the requirement to accomplish this NMSB prior to engine installation. R R D. Compliance
ALERT This Non-Modification Service Bulletin is anticipated to be the subject of an EASA/FAA Airworthiness Directive. (1) On-wing Carry out the actions detailed in 3.A. Accomplishment Instructions at the next convenient maintenance opportunity, within 24 months or 1600 engine cycles (whichever occurs sooner), of the initial issue of this NMSB. R R R (2) In-shop (a) Engines where the M51 module is undergoing a level 1 or level 2 shop visit: Carry out the actions detailed in 3.B. Accomplishment Instructions. (b) Engines where the M51 module is undergoing a level 3 or level 4 shop visit: Carry out SB 72-H754. E. Approval The technical content of this Non-Modification Service Bulletin was approved under the authority of Design Organisation Approval EASA.21J.035 on May.7/15 and was re-approved on May.19/15. R R F. Manpower (1) On-wing: (a) Time to inspect the sealing sleeve to confirm the batch number 0.25 hours (one person) (b) Time to disconnect and remove the external HP/IP oil feed tube 0.25 hours (one person)**Printed in Great Britain**



# RB.211−72−AJ035 Page 2 May 11/15 May.20/15 R(c) Time to replace the sealing sleeve 0.5 hours (one person) (d) Time to install the modified external oil feed tube and restore to a serviceable condition 0.25 hours (one person) (e) Ground running requirement Fuel and oil leak test
NOTE : The leak test is only required if the oil feed tube is disconnected. (2) In-shop (a) Time to inspect the sealing sleeve to confirm the batch number 0.25 hours (one person) (b) Time to remove the external HP/IP oil feed tube and remove the sealing sleeve 0.5 hours (one person) G. Material Price and Availability All materials required to accomplish NMSB 72-AJ035 are detailed in section 2. Material Information H. Tooling Price and Availability (1) Torque wrench (up to 1500 lbfin.) (2) Tooling/Consumables required for oil tube cutting procedure (Appendix 3): (a) HU40179-1 (b) Portable electric drill - 230 RPM (c) Pipe cutting tool or tube cropping tool (swarf-free cutting process) (locally supplied) (d) Vacuum cleaner - with 8mm diameter suction hose (locally supplied) (e) Engine Oil (OMat 1011)**Printed in Great Britain**



# RB.211−72−AJ035 Page 3 May 11/15 May.20/15 R(3) Tooling required for sealing sleeve removal (a) Impact extractor HU29255 with extraction adaptor HU45296
Or (b) Facom U.49P6 expansion puller dia 18mm - 60mm Facom U.53H3 expansion puller adaptor Facom U.49AM slide hammer
Or (c) Locally sourced equivalent hand tools (d) Adjustable grips (locally supplied) (e) Adjustable spanner (locally supplied) I. References (1) Rolls-Royce RB211 Service Bulletins: (a) 72-F227 Engine - HP/IP Bearing Support - Introduction of an HP/IP Turbine Bearings Support Structure with revised Oil and Air Service Tubes and Associated Insulated Heatshield Covers (b) 79-D102 Oil - Oil System Tubes and Fittings - Core Engine - Introduction of revised HP/IP Turbine Structure Oil Tubes (c) 72-H754 Engine - IP Turbine Case - Introduction of a revised Oil Feed Tube Assembly with increased Radial Clearance between the Union Nut and Sealing Sleeve (2) Rolls-Royce RB211 Non-Modification Service Bulletin: 72-AH673 Engine - HP/IP Turbine Bearing Support - Inspection and replacement of the Oil Feed Tube Sealing Sleeve - Non-Modification Service Bulletin (3) Aircraft Maintenance Manual: (a) Task 71-00-00-700-827-A, Test No.2 - Fuel and Oil Leak Test**Printed in Great Britain**



# RB.211−72−AJ035 Page 4 May 11/15 May.20/15 R(b) Task 70-51-00, PB 201, Torque Tightening Techniques (c) Task 70-12-04-910-804-A, Locking Techniques - Wire Locking (d) Task 78-30-00-010-803-A, Open the Thrust Reverser Cowl Doors (e) Task 78-30-00-410-803-A, Close the Thrust Reverser Cowl Doors (4) Engine Manual: (a) Task 72-00-51-000-801, Remove the Tubes, the Electrical Harnesses and the Components for Access to Remove the Intermediate Pressure (IP) Turbine Module. (b) Task 72-00-51-400-804, Install the Tubes, the Electrical Harnesses and the Components for, 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) Case and Vanes. (e) Task 72-00-00-700-802, Test 2 - Fuel and Oil Leak Test (5) Standard Practices Manual (a) 70-51-00, Procedures used to Torque Tighten Components (b) 70-12-04, Procedures Used to Lock Threaded Parts - LOCK THREADED PARTS**Printed in Great Britain**



# RB.211−72−AJ035 Page 5 May 11/15 May.20/15 R2. Material Information A. The following parts are required to accomplish this NMSB if inspection confirms that the sealing sleeve has not previously been replaced in accordance with NMSB 72-AH673:

EIPC, Fig/Item Part No. Qty Description Mat

79-22-49, 02-100 KH28324 1 External Oil Feed Tube - 72-51-23, 01-220 KH28323 1 Oil Feed Sealing Sleeve -**Printed in Great Britain**



# RB.211−72−AJ035 Page 6 May 11/15 May.20/15 R3. Accomplishment Instructions A. On-wing

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) If available via maintenance records, determine if engine has a sealing sleeve with identity marking '102013', '102013L' or '112013'. If the sealing sleeve has been replaced during accomplishment of NMSB 72-AH673, then this guarantees the sealing sleeve will have the marking 102013, 102013L or 112013. (a) If the maintenance records show that the sealing sleeve has identity marking '102013', '102013L' or '112013' then proceed to step (6). (b) If the sealing sleeve does not have identity marking '102013', '102013L' or '112013' then proceed to step (2). (2) Gain access: (a) Open the thrust reverser cowl doors in accordance with Aircraft Maintenance Manual, Task 78-30-00-010-803-A. (b) Locate the oil feed tube (Part No. FW14193 or KH28324) and the oil feed tube sealing sleeve (Part No. FW15003 or KH28323) at the 9 o'clock position when looking from the rear of the engine. Refer to Fig.1. (3) Inspect the markings on the sealing sleeve (Part No. FW15003 or KH28323) in-situ. (a) If the sealing sleeve has part number KH28323 the proceed to step (6).**Printed in Great Britain**



# RB.211−72−AJ035 Page 7 May 11/15 May.20/15 R(b) If the sealing sleeve has part number FW15003, then check for identification number: (i) If the sealing sleeve has identification marking '102013', '102013L' or '112013' (refer to Fig.2a and Fig.2b), then proceed to step (6). (ii) If the sealing sleeve does not have identification marking '102013', '102013L' or '112013' (refer to Fig.2a and Fig.2b), then proceed to step (4). (iii) If the sealing sleeve markings cannot be identified then proceed to step (4).
CAUTION : DO NOT EXCEED 1500 LB/IN TORQUE WHEN DISCONNECTING THE UNION NUT. EXCEEDING THIS TORQUE VALUE MAY DAMAGE THE INTERNAL OIL TUBE CAUTION : TOOLING CAN BE USED DURING SEALING SLEEVE REMOVAL, BUT TOOLING MUST NOT BE USED DURING SEALING SLEEVE INSTALLATION. SEALING SLEEVES ARE INSTALLED USING ONLY FINGER PRESSURE. (4) Accomplish in accordance with 3.C. On-wing Accomplishment Instructions of SB 72-H754 (refer to 1.I. References).
NOTE : Based on previous service experience, the HP/IP oil feed tube union nut is not susceptible to seizure. If the union nut cannot be disconnected, carry out the union nut cutting procedure in Appendix 1 to remove the union nut.
NOTE : The sealing sleeve bore diameter can vary slightly due to tolerances at manufacturing. If a sealing sleeve cannot be installed using only finger pressure, then install a different sealing sleeve with part number KH28323 until such time as one can be fitted with finger pressure only.
NOTE : The correct procedure for torque tightening the tube connectors is provided by AMM 70-51-00. This task instructs a sequence of torque tightening the union nut, then releasing it half a turn, and repeating several times, to ensure correct bedding of the union. (5) Restore the engine to a serviceable condition. (a) Close the thrust reverser cowl doors in accordance with Aircraft Maintenance Manual 78-30-00.**Printed in Great Britain**



# RB.211−72−AJ035 Page 8 May 11/15 May.20/15 R(b) Carry out the fuel and oil leak test in accordance with AMM 71-00-00, Test 2, Fuel and Oil Leak Test.
NOTE : 1. It is particularly important that developer is applied around each disturbed tube union, and examined carefully after the test. 2. The leak test is only required if the oil feed tube was disconnected during this procedure. (6) Accomplishment of this Non-Modification Service Bulletin and if applicable accomplishment of SB 72-H754 should be recorded in the engine logbook. B. In-shop (1) Locate the oil feed tube (EIPC 79-22-49, 02-100) at the 9 o'clock position when looking from the rear of the engine. Refer to Fig.1. (2) Inspect the markings on the sealing sleeve (EIPC 72-51-23, 01-220, Part No.FW15003 or KH28323) in-situ. (a) If the sealing sleeve has part number KH28323 then proceed to step (4). (b) If the sealing sleeve has part number FW15003, then check for batch identification number: (i) If the sealing sleeve has identification marking '102013', '102013L' or '112013' (refer to Fig.2a and Fig.2b), then proceed to step (4). (ii) If the sealing sleeve does not have identification marking '102013', '102013L' or '112013' (refer to Fig.2a and Fig.2b), then proceed to step (3). (iii) If the sealing sleeve markings cannot be identified from the sleeve markings then continue with step (3).**Printed in Great Britain**



# RB.211−72−AJ035 Page 9 May 11/15 May.20/15 RCAUTION : TOOLING CAN BE USED DURING SEALING SLEEVE REMOVAL, BUT TOOLING MUST NOT BE USED DURING SEALING SLEEVE INSTALLATION. SEALING SLEEVES ARE INSTALLED USING ONLY FINGER PRESSURE. (3) Accomplish in accordance with SB 72-H754 (refer to 1.I. References), 3.B. In-shop Accomplishment Instructions.
NOTE : The sealing sleeve bore diameter can vary slightly due to tolerances at manufacturing. If a sealing sleeve cannot be installed using only finger pressure, then install a different sealing sleeve with part number KH28323 until such time as one can be fitted with finger pressure only.
NOTE : The correct procedure for torque tightening the tube connectors is provided by AMM 70-51-00. This task instructs a sequence of torque tightening the union nut, then releasing it half a turn, and repeating several times, to ensure correct bedding of the union. (4) Accomplishment of this Non-Modification Service Bulletin and if applicable accomplishment of SB 72-H754 should be recorded in the engine logbook.**Printed in Great Britain**



# RB.211−72−AJ035 Page 10 May 11/15 May.20/15 ROil Feed Tube (9 o'clock position on the IP Turbine Casing) Fig.1**Printed in Great Britain**



# RB.211−72−AJ035 Page 11 May 11/15 May.20/15 R**Printed in Great Britain**



# RB.211−72−AJ035 Page 12 May 11/15 May.20/15 RProcedure for Cutting off a Seized Union Nut 1. Effectivity A. This procedure is applicable to the external HP/IP Turbine Oil Tube Post SB 79-D102 standard. 2. Description of Procedure The procedure cuts through the thrust shoulder of the union nut. This removes the axial load from the union nut threads, which reduces the torque required to unscrew the nut. The union nut and external tube are destroyed in the procedure. The depth stop on the cutting tool prevents the cutting tool from making contact with the internal oil tube end fitting, so the internal oil tube is not damaged by this procedure. 3. Tools and Consumables Refer to 1.H. Tooling Prices and Availability 4. Material Requirements Refer to 2. Material Information 5. Procedure A. Disconnect the external oil tube connector and all tube clips. B. Cut the external tube a maximum length of 30 mm from the union nut, refer to Fig.3. Use a manual pipe cutting tool or a cropping tool to avoid making any cutting debris. C. If the tool is open ended, close the end of the cut tube using a temporary bung, to prevent ingress of contamination. D. Lubricate the shoulder of the union nut with clean engine oil.
CAUTION : WHEN THE CUTTING TOOL BREAKS THROUGH THE UNION NUT SHOULDER, THE NUT CAN TURN WITH THE CUTTING TOOL. WHEN THIS HAPPENS, STOP CUTTING IMMEDIATELY, BECAUSE IF THE NUT IS ROTATED THROUGH SEVERAL TURNS, THE CUTTING TOOL CAN MAKE CONTACT WITH THE INTERNAL OIL TUBE END FITTING E. Cut through the shoulder of the union nut, using the hole cutting tool and the electric drill. F. Remove all swarf, using the vacuum cleaner. G. Remove the union nut. Do not allow any debris to drop into the open end of the internal oil tube. APPENDIX 1**Printed in Great Britain**



# RB.211−72−AJ035 Appendix 1 - Page 1 of 3 May 11/15 May.20/15 RH. Clean the internal oil tube end fitting. Inspect the end fitting to confirm that there is no damage.**Printed in Great Britain**



# RB.211−72−AJ035 Appendix 1 - Page 2 May 11/15 May.20/15 RUnion Nut Cutting Tool shown in-situ on the HP/IP Turbine External Oil Tube Fig.3**Printed in Great Britain**



# RB.211−72−AJ035 Appendix 1 - Page 3 May 11/15 May.20/15 R