LIST OF EFFECTIVE PAGES The effective pages to this Service Bulletin following incorporation of Revision 2 are as follows: Page Revision Number Revision Date

Bulletin R 1 2 Jun.13/12 R 2 2 Jun.13/12 R 3 2 Jun.13/12 R 4 2 Jun.13/12 R 5 2 Jun.13/12 R 6 2 Jun.13/12 R 7 2 Jun.13/12 R 8 2 Jun.13/12 R 9 2 Jun.13/12 R 10 2 Jun.13/12 R 11 2 Jun.13/12 R 12 2 Jun.13/12 R 13 2 Jun.13/12 R 14 2 Jun.13/12 R 15 2 Jun.13/12 R 16 2 Jun.13/12 Appendix 1 R 1 2 Jun.13/12**Printed in Great Britain**



# RB.211−73−AG797 Transmittal - Page 21. Planning Information A. Effectivity Airbus A340 - 500/600 RB211 TRENT 553-61 Engines RB211 TRENT 553A2-61 Engines RB211 TRENT 556-61 Engines RB211 TRENT 556A2-61 Engines RB211 TRENT 556B-61 Engines RB211 TRENT 556B2-61 Engines RB211 TRENT 560-61 Engines RB211 TRENT 560A2-61 Engines This Non-Modification Service Bulletin (NMSB) does not apply to engines which have been inspected per NMSB 73-G723.
B. Reason Problem Low-pressure fuel leaks from the LP fuel tubes which run between the low-pressure and high-pressure fuel pumps have occurred in-service in the Trent 500 fleet. These have resulted from frettage between the securing clips and the low-pressure fuel tube outer surface, which reduces the fuel tube wall thickness, leading to fracture of the fuel tube wall and consequent fuel leak. This may cause the leakage of significant amounts of fuel and can cause IFSD and Diversion events. NMSB 73-G723 was issued to inspect the components, gather data and provide mitigation on engines passing through shop visit. This NMSB was designed to gather information and provide proactive mitigation for the condition also for those engines installed on-wing which would not be covered by NMSB 73-G723. This NMSB does not apply to engines which have been inspected per NMSB 73-G723. ENGINE - LP FUEL TUBES AND CLIPS - INSPECTION FOR FRETTAGE - NON-MODIFICATION SERVICE BULLETIN - NON - MOD.73-AG797**Printed in Great Britain**



# RB.211−73−AG797 Page 1 of 16 Oct.26/11 Jun.13/12 RRevision 1 of this NMSB is issued add Fig.1 reference to Accomplishment Instructions (3.A.(4)), to add reference to SB 73-F738 R and to incorporate reference to clip position 100180 in Accomplishment Instructions (3.A.(4)(a) and 3.A.(6)) and to correct frettage dimensions in Accomplishment Instructions (3.A.(5)(c)). C. Description This NMSB is issued to recommend on-wing inspection of the low-pressure fuel tubes and associated hardware. Advise your Rolls-Royce representative of NMSB accomplishment and inspection results, regardless of findings. Return Appendix 1 (or similar form) to your Rolls-Royce service representative. D. Compliance
ALERT This Non-Modification Service Bulletin is anticipated to be the subject of an EASA Airworthiness Directive. On wing: If the engine has not been inspected to NMSB 73-G723 Initial issue or later approved version, it is recommended that the actions detailed in section 3.A. (Accomplishment Instructions, On-wing) be carried out at first opportunity within 1600 engine flying hours from the effective date for the release of this NMSB. E. Approval The technical content of this Non-Modification Service Bulletin was approved under the authority of Design Organisation Approval EASA.21J.035 on Oct.25/11 and re-approved on Jan.31/12. F. Manpower (1) Time to gain access 0.5 hours (2) Time to inspect 2 hours (3) Time to replace tubes (if needed; includes Test 2 Fuel and Oil Leak Test) 3 hours**Printed in Great Britain**



# RB.211−73−AG797 Page 2 Oct.26/11 Jun.13/12 R(4) Time to restore to serviceable condition 0.5 hours G. Material Price and Availability Not applicable H. Tooling Price and Availability Not applicable I. References (1) Rolls-Royce RB211 Service Bulletins: SB 73-F737 Engine - Fuel and Control - Fuel Tubes - LP Compressor Case - Introduction of a revised LP Fuel Tube Incorporating Rigid End Fittings SB 73-F738 Fuel and Control - Fuel Tubes LP Compressor Case - Introduction of revised LP Fuel Tubes Incorporating Rigid End Fittings SB 79-AG346 Oil - Fuel Oil Heat Exchanger - Introduction of a Fuel Oil Heat Exchanger Featuring a revised Cooler Matrix (2) Rolls-Royce RB211 Non-Modification Service Bulletin: NMSB 73-G723 Engine - LP Fuel Tubes, Clips and FOHE Mounts - Inspection for Frettage - Non-Modification Service Bulletin (3) Aircraft Maintenance Manual: (a) 24-41-00, Deactivation/Reactivation, AC External Power Control (b) 71-13-00, Maintenance Practices, Opening/Closing Fan Cowl Doors (c) 70-20-01, Maintenance Processes - Stripping and Cleaning, Maintenance Practices, Non - Aqueous Liquid Degreasing (d) 73-11-00, Inspection/Check, Inspection of the Fuel Distribution Tubes (e) 73-11-00, Plumbing, Maintenance Practices, Draining of the LP Fuel Supply from the Fuel Oil Heat Exchanger Drain Point**Printed in Great Britain**



# RB.211−73−AG797 Page 3 Oct.26/11 Jun.13/12 R(f) 73-11-00, Plumbing, Maintenance Practices, Draining of the LP Fuel Supply from the Fuel Pump Drain Point (g) 70-12-01, Removal/Installation, Removal of Rigid Tubes (h) 70-12-01, Removal/Installation, Installation of Rigid Tubes (i) 71-00-00, Adjustment/Test, Test No.2, The Fuel and Oil Leak Test**Printed in Great Britain**



# RB.211−73−AG797 Page 4 Oct.26/11 Jun.13/12 R2. Material Information A. Consumable OMat 2-101 Lint-free Cloth B. The following parts may be required if rejected during inspection: 73-11-47
FIG ITEM NO. PART NO. QTY PART TITLE MAT

04100 FK30710 1 Tube, assy fuel - LP pump to line disconnect, Pre SB 73-F738 -

04100A FW57604 1 Tube, assy fuel - LP pump to line disconnect, SB 73-F738 PT01 -

04104 RR188C 3 Ring, V80756, Pre SB 73-F738 -
04106 BLT5529 3 Bolt, 0.25 in. dia x 1.028, x 1.028, Pre SB 73-F738 -
04106A AS48516 3 Bolt, 0.25 in. dia x 1.000, SB 73-F738 PT01 -
04107 AS43013-129 2 Ring, Pre SB 73-F738 -
04108 AS43013-134 1 Ring - 04500 FW17689 1 Tube, assy fuel pump to FCOC, Pre SB 73-F738 -
04500A FW57605 1 Tube, assy fuel pump to FCOC, SB 73-F738 PT01 -
04502 AS20625 4 Nut, 0.25 in. dia - 04504 AS12944 4 Washer, 0.25 in. dia - 04506 AS48516 4 Bolt, 0.25 in. dia x 1 - 04508 AS43013-130 1 Ring -**Printed in Great Britain**



# RB.211−73−AG797 Page 5 Oct.26/11 Jun.13/12 RFIG ITEM NO. PART NO. QTY PART TITLE MAT

04512 RR188C 3 Ring, V80756, Pre SB 73-F738 -
04514 BLT5529 3 Bolt, 0.25 in. dia x 1.028, Pre SB 73-F738 -
04514A AS48516 3 Bolt, 0.25 in. dia x 1.000, Pre SB 73-F738 PT01 -
04515 AS43013-129 2 Ring, Pre SB 73-F738 -
04516 AS43013-134 1 Ring - 04525 AS48408 1 Bolt, 0.190 in. dia x 0.50 - 04526 K8831 1 Washer, 0.190 in. dia x 0.51 in. thk -
04528 AS62426 1 Clip, 41.27 mm - 1.625 in. - 04532 AS20624 1 Nut, 0.190 in. dia - 04533 AS48408 1 Bolt, 0.190 in. dia x 0.50 - 04534 K8831 1 Washer, 0.190 in. dia x 0.51 in. thk -
04536 AS62426 1 Clip, 41.27 mm - 1.625 in. - 04540 AS20624 1 Nut, 0.190 in. dia - 04541 AS48408 1 Bolt, 0.190 in. dia x 0.50 in. - 04542 K8831 1 Washer, 0.190 in. dia x 0.51 in. thk -
04544 AS62426 1 Clip, 41.27 mm - 1.625 in. - 04548 AS20624 1 Nut, 0.190 in. dia - 04549 AS48434 1 Bolt, 0.190 in. dia x 2.125 in. -
04550 K8831 1 Washer, 0.190 in. dia x 0.51 in. thk -**Printed in Great Britain**



# RB.211−73−AG797 Page 6 Oct.26/11 Jun.13/12 RFIG ITEM NO. PART NO. QTY PART TITLE MAT

04552 AS62426 1 Clip, 41.27 mm - 1.625 in. - 04554 UP10482 1 Spacer, 25 mm - 04555 UP10480 1 Spacer, 15 mm - 04556 AS20624 1 Nut, 0.190 in. dia - 73-11-47
FIG ITEM NO. PART NO. QTY PART TITLE MAT

05100 FK30713 1 Tube, assy fuel - LP filter to line disconnect, Pre SB 73-F737 -

05100A FW57578 1 Tube, assy fuel - LP filter to HP pump, SB 73-F737 -

05104 RR188C 3 Ring, V80756, Pre SB 73-F737 -
05107 AS43013-129 2 Ring, Pre SB 73-F737 -
05108 AS43013-134 1 Ring - 05112 RR188C 3 Ring, V80756, Pre SB 73-F737 -
05114 BLT5529 3 Bolt, 0.25 in. dia x 1.028, Pre SB 73-F737 -
05114A AS48516 3 Bolt, 0.25 in. dia x 1.000, SB 73-F738 PT01 -
05115 AS43013-129 2 Ring, Pre SB 73-F737 -
05116 AS43013-134 1 Ring - 05125 AS48408 1 Bolt, 0.190 in. dia x 0.500 in. -**Printed in Great Britain**



# RB.211−73−AG797 Page 7 Oct.26/11 Jun.13/12 RFIG ITEM NO. PART NO. QTY PART TITLE MAT

05126 K8831 1 Washer, 0.190 in. dia x 0.51 in. thk -
05128 AS62426 1 Clip, 41.27 mm (1.625 in.) - 05132 AS20624 1 Nut, 0.190 in. dia - 05133 AS48409 1 Bolt, 0.190 in. dia x 0.500 in. pre SB 73-F737 -
05134 K8831 1 Washer, 0.190 in. dia x 0.51 in. thk pre SB 73-F737 -

05136 AS62426 1 Clip, 41,27 mm (1.625 in.) pre SB 73-F737 -
05149 AS48408 1 Bolt, 0.190 in. dia x 0.500 in. -
05150 K8831 1 Washer, 0.190 in. dia x 0.51 in. thk -
05152 AS62426 1 Clip, 41,27 mm (1.625 in.) - 05157 AS48412 1 Bolt, 0.190 in. dia x 0.750 in. -
05158 K8831 1 Washer, 0.190 in. dia x 0.51 in. thk -
05160 AS62426 1 Clip, 41,27 mm (1.625 in.) - 05162 UP10478 1 Spacer, 5mm - 05164 AS20624 1 Nut, 0.190 in. dia - 05165 AS48410 1 Bolt, 0.190 in. dia x 0.620 in. SB 73-F737 PT01 -
05166 K8831 1 Washer, 0.190 in. dia x 0.51 in. thk SB 73-F737 PT01 -

05167 AS12943 1 Washer, 0.190 in. dia SB 73-F737 PT01 -**Printed in Great Britain**



# RB.211−73−AG797 Page 8 Oct.26/11 Jun.13/12 RFIG ITEM NO. PART NO. QTY PART TITLE MAT

05168 AS62426 1 Clip, 41,27 mm (1.625 in.) SB 73-F737 PT01 -
05172 AS20624 1 Nut, 0.190 in. dia SB 73-F737 PT01 -**Printed in Great Britain**



# RB.211−73−AG797 Page 9 Oct.26/11 Jun.13/12 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. WARNING : YOU MUST NOT LET ENGINE OIL STAY ON YOUR SKIN. FLUSH THE OIL FROM YOUR SKIN WITH WATER. THE OIL IS POISONOUS AND CAN BE ABSORBED INTO YOUR BODY. 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 ENSURE THAT MAINTENANCE TASKS HAVE BEEN COMPLETED AS DEFINED. MAINTENANCE GUIDELINES SHOULD BE REVISED, WHERE POSSIBLE, TO PROMOTE THIS RECOMMENDATION. CAUTION: YOU MUST NOT LET ENGINE FUEL OR OIL FALL ON THE ENGINE. UNWANTED FUEL OR OIL MUST BE REMOVED IMMEDIATELY WITH A CLEAN LINT-FREE CLOTH. THE FUEL OR OIL CAN CAUSE DAMAGE TO THE SURFACE PROTECTION AND TO SOME PARTS. (1) Energize the aircraft electrical, refer to Aircraft Maintenance Manual (AMM) 24-41-00, Maintenance Practices. (2) Get access to the avionics compartment, then open, safety and tag this (these) circuit breaker(s):
PANEL DESIGNATION FIN LOCATION For 4040 EM1: 722VU FADEC B ENG 1 13KS1 K46 722VU FUEL LP MOT 2 ENG 1 2QG1 U44 742VU FUEL LP MOT 1 ENG 1 1QG1 K75 742VU FADEC A ENG 1 12KS1 N74 For 4040 EM2: 722VU FADEC B ENG 2 13KS2 D43 722VU FUEL LP MOT 2 ENG 2 2QG2 U45 742VU FUEL LP MOT 1 ENG 2 1QG2 K76 742VU FADEC A ENG 2 12KS2 Q73 For 4040 EM3: 722VU FADEC B ENG 3 13KS3 K47 722VU FUEL LP MOT 2 ENG 3 2QG3 Q43 742VU FUEL LP MOT 1 ENG 3 1QG3 K77**Printed in Great Britain**



# RB.211−73−AG797 Page 10 Oct.26/11 Jun.13/12 R742VU FADEC A ENG 3 12KS3 Q74 For 4040 EM4: 722VU FADEC B ENG 4 13KS4 D44 722VU FUEL LP MOT 2 ENG 4 2QG4 Q44 742VU FUEL LP MOT 1 ENG 4 1QG4 K78 742VU FADEC A ENG 4 12KS4 N75 (3) Get access: open the Fan Cowl Doors, refer to AMM 71-13-00, Maintenance Practices For 4040EM1: 415AL 416AR For 4040EM2: 425AL 426AR For 4040EM3: 435AL 436AR For 4040EM4: 445AL 446AR
CAUTION: YOU MUST NOT PUT OIL THAT HAS COME FROM THE ENGINE BACK INTO THE OIL SYSTEM. CONTAMINATION IN THE OIL CAN CAUSE DAMAGE TO SOME PARTS OR FAILURE OF THE OIL. CAUTION: YOU MUST NOT PUT FUEL THAT HAS COME FROM THE ENGINE BACK INTO THE FUEL SYSTEM. CONTAMINATION IN THE FUEL CAN CAUSE DAMAGE TO SOME PARTS. (4) Remove and check the clips holding the LP fuel tube run from the LP fuel pump to the FOHE (AIPC 73-11-47, 72-160/72-160A and 73-11-47, 72-150/72-150A) and the clips holding the LP fuel tube run from the LP filter to the HP fuel pump (73-11-47, 73-140/73-140A). See Fig.1 and Fig.2. (a) Visually check each of the clips for obvious evidence of damage that may have affected the fuel tubes (e.g. significant damage to rubber and/or dust/debris at location of clip): Pre SB 73-F737 and pre SB 73-F738: Engines Inspect the clipping points 100181, 102321, 100282, 100187, 102252, 100178, 100180, 102259, 102321, 100186 and 102260 Post SB 73-F737 and SB 73-F738: Engines Inspect the clipping points 100181, 102321, 100282, 102374, 102252, 100178, 100180, 102259, 102321, 100186 and 102260**Printed in Great Britain**



# RB.211−73−AG797 Page 11 Oct.26/11 Jun.13/12 R(b) Remove, inspect and replace (as necessary) each retaining clip one at a time, start from either top or bottom of the tube run.
NOTE : This is to prevent alteration to the system alignment and stressing of the tube and clips.
NOTE : During removal of the clip look for any significant relaxation or strain that suggests poor alignment of the tubes and stressing of certain clipping positions. If necessary loosen adjacent clips and carefully manipulate the tube alignment to minimize any strain in the system. Make a note if alignment issues are seen. (c) Visually inspect the clips:
Obvious excessive damage Take a photo and reject

Cracked Distressed Rubber Take a photo and reject
Worn/damaged internal diameter of rubber Take a photo and reject

Evidence of internal corrosion/wear/material transfer to the tube surface (powdery

deposits at ends of rubber section) Take a photo and reject

(5) Inspect the LP fuel tube run from the LP fuel pump to the FOHE and the LP fuel tube run from the LP filter to the HP fuel pump (see Fig.2). (a) Clean the fuel tubes in accordance with AMM Task 70-20-01-100-805. (b) Dry the tubes with a clean Material No OMat 2-101 (lint-free cloth) . (c) Visually check the fuel tubes surface near p-clips location for evidence of damage/wear in accordance with AMM Task 73-11-00-200-802-A.
NOTE : Take particular care to inspect the entire exposed surface of the tube, a mirror may be used in areas where direct line of sight access is difficult. Reject and replace the tube if evidence of contact frettage to a depth of greater than 0.1 mm (0.004 in.) on the outer surface of a bend or 0.2 mm (0.008 in.) in any other area is evident.**Printed in Great Britain**



# RB.211−73−AG797 Page 12 Oct.26/11 Jun.13/12 R(d) If the fuel tube is rejected, remove it in accordance with AMM Task 70-12-01-000-801-A and replace it with new in accordance with AMM Task 70-12-01-400-801-A. (6) Fit clips back to each of the following locations: Pre SB 73-F737 and pre SB 73-F738: Engines Inspect the clipping points 100181, 102321, 100282, 100187, 102252, 100178, 100180, 102259, 102321, 100186 and 102260 Post SB 73-F737 and SB 73-F738: Engines Inspect the clipping points 100181, 102321, 100282, 102374, 102252, 100178, 100180, 102259, 102321, 100186 and 102260 (7) Get access to the avionics compartment, then remove safety clips(s) and the tag(s) and close this (these) circuit breaker(s):
PANEL DESIGNATION FIN LOCATION For 4040 EM1: 722VU FADEC B ENG 1 13KS1 K46 722VU FUEL LP MOT 2 ENG 1 2QG1 U44 742VU FUEL LP MOT 1 ENG 1 1QG1 K75 742VU FADEC A ENG 1 12KS1 N74 For 4040 EM2: 722VU FADEC B ENG 2 13KS2 D43 722VU FUEL LP MOT 2 ENG 2 2QG2 U45 742VU FUEL LP MOT 1 ENG 2 1QG2 K76 742VU FADEC A ENG 2 12KS2 Q73 For 4040 EM3: 722VU FADEC B ENG 3 13KS3 K47 722VU FUEL LP MOT 2 ENG 3 2QG3 Q43 742VU FUEL LP MOT 1 ENG 3 1QG3 K77 742VU FADEC A ENG 3 12KS3 Q74 For 4040 EM4: 722VU FADEC B ENG 4 13KS4 D44 722VU FUEL LP MOT 2 ENG 4 2QG4 Q44 742VU FUEL LP MOT 1 ENG 4 1QG4 K78 742VU FADEC A ENG 4 12KS4 N75 (8) If any tube is replaced, do a leak check of the fuel oil heat exchanger installation in accordance with AMM, 71-00-00, Adjustment/Test, Test No.2, The Fuel and Oil Leak Test. (9) Close Access: (a) Make sure that the work area is clean and clear of tools and other items.**Printed in Great Britain**



# RB.211−73−AG797 Page 13 Oct.26/11 Jun.13/12 R(b) Close the fan cowl doors in accordance with AMM 71-13-00, Maintenance Practices. For 4040EM1: 415AL 416AR For 4040EM2: 425AL 426AR For 4040EM3: 435AL 436AR For 4040EM4: 445AL 446AR (10) De-energise the aircraft electrical circuit in accordance with AMM 24-41-00, Maintenance Practices. B. Reporting evidences

If any p-clip or a pipe is rejected then quarantine the pipe and record the results in Appendix 1 or similar form. Send the recorded results to Rolls-Royce, via your local Field Service representatives, for onward transmittal to Service Engineering. The proforma attached as Appendix 1 to this NMSB shows the information required and may be used to return data to Rolls-Royce. C. Record of accomplishment.

Accomplishment of this Non-Modification Service Bulletin should be recorded in accordance with local SB tracking system procedures.**Printed in Great Britain**



# RB.211−73−AG797 Page 14 Oct.26/11 Jun.13/12 RFuel Tubes LP Compressor Case Fig.1**Printed in Great Britain**



# RB.211−73−AG797 Page 15 Oct.26/11 Jun.13/12 RFuel Tubes LP Compressor Case Fig.2**Printed in Great Britain**



# RB.211−73−AG797 Page 16 Oct.26/11 Jun.13/12 RThis form (or similar) to be completed for every engine/component inspected results to be sent to Rolls-Royce via your Service Representative

Feedback Sheet NMSB 73-AG797 Date: Operator: Engine Serial Number: Aircraft: Hours Cycles Engine Life: Life since last shop visit: Life since embodiment of SB 79-AG346: Life since embodiment of SB 73-F737 (if applicable): Life since embodiment of SB 73-F738 (if applicable): Fuel Tubes Condition Observations (material transfer from clips/fretted/dented/worn-please specify depth) FW57605 (SB 73-F738) FW17689 (pre SB 73-F738) FW57604 (SB 73-F738) FK30710 (pre SB 73-F738) FW57578 (SB 73-F737) FK30713 (pre SB 73-F737) Clips Condition Observations (material transfer/dust/worn/cracked/metal band exposed) 102252 100178 100180 102259 102321 100186 102260 100181 102321 100282 102374 (SB 73-F737) 100187 (pre SB 73-F737) NOTES: APPENDIX 1**Printed in Great Britain**



# RB.211−73−AG797 Appendix 1 - Page 1 of 1 Oct.26/11 Jun.13/12 R