All pages of Appendix 2 Page 1 and 2 of Appendix 2 To revise Aircraft Maintenance Manual reference in 3. Accomplishment Instructions and to revise Fig.9 (RR-RMR13446) All pages of Appendix 3 Page 1 and 2 of Appendix 3 To revise Aircraft Maintenance Manual reference in 3. Accomplishment Instructions and to revise Fig.9 (RR-RMR13446)**Printed in Great Britain**



# RB.211−73−AH522 Transmittal - Page 2LIST 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 Jul.18/14 R 2 2 Jul.18/14 R 3 2 Jul.18/14 R 4 2 Jul.18/14 R 5 2 Jul.18/14 R 6 2 Jul.18/14 R 7 2 Jul.18/14 R 8 2 Jul.18/14 R 9 2 Jul.18/14 R 10 2 Jul.18/14 R 11 2 Jul.18/14 R 12 2 Jul.18/14 R 13 2 Jul.18/14 R 14 2 Jul.18/14 R 15 2 Jul.18/14 R 16 2 Jul.18/14 R 17 2 Jul.18/14 R 18 2 Jul.18/14 R 19 2 Jul.18/14 R 20 2 Jul.18/14 R 21 2 Jul.18/14 R 22 2 Jul.18/14 R 23 2 Jul.18/14 R 24 2 Jul.18/14 R 25 2 Jul.18/14 R 26 2 Jul.18/14 R 27 2 Jul.18/14 R 28 2 Jul.18/14 R 29 2 Jul.18/14 R 30 2 Jul.18/14 R 31 2 Jul.18/14 R 32 2 Jul.18/14 R 33 2 Jul.18/14 R 34 2 Jul.18/14 R 35 2 Jul.18/14 R 36 2 Jul.18/14 Appendix 1 R 1 2 Jul.18/14 Appendix 2 R 1 2 Jul.18/14 R 2 2 Jul.18/14**Printed in Great Britain**



# RB.211−73−AH522 Transmittal - Page 3Appendix 3 R 1 2 Jul.18/14 R 2 2 Jul.18/14**Printed in Great Britain**



# RB.211−73−AH522 Transmittal - Page 41. Planning Information A. Effectivity Airbus A330 RB211 TRENT 768-60/15 Engines, Post SB73-F343 Engines RB211 TRENT 768-60/16 Engines, Post SB73-F343 Engines RB211 TRENT 772-60/15 Engines, Post SB73-F343 Engines RB211 TRENT 772-60/16 Engines, Post SB73-F343 Engines RB211 TRENT 772B-60/15 Engines, Post SB73-F343 Engines RB211 TRENT 772B-60/16 Engines, Post SB73-F343 Engines RB211 TRENT 772C-60/15 Engines, Post SB73-F343 Engines RB211 TRENT 772C-60/16 Engines, Post SB73-F343 Engines
B. Reason Low-pressure (LP) fuel leaks from the LP fuel tube run between the Fuel/Oil Heat Exchanger (FOHE), and the LP/HP fuel pump have occurred in-service in the Trent 700 fleet. Movement of the FOHE mounts due to wear allows the fuel tubes to move excessively within the clipping points. This has resulted in excessive wear of the rubber section of the P-Clips, and the subsequent frettage between the exposed metal band and the fuel tubes. The frettage reduces the fuel tube outer wall thickness, leading to fracture of the fuel tube and the consequent fuel leak. This may cause the leakage of significant amounts of fuel and can cause IFSD and diversion events. This Non-Modification Service Bulletin (NMSB) is designed to provide proactive mitigation for wear on the clipping of the fuel pipe from the FOHE to the HP pump inlet when installed on-wing and to make sure wear on other connected pipes and clips is inspected for at engine shop visit. Revision 1 of this NMSB was R issued to correct errors reported against initial issue and to include a complete inspection of all the LP fuel pipes as per NMSB 73-G848, which will now be cancelled. Revision 2 of this NMSB is issued to revise Aircraft Maintenance Manual reference in 3. Accomplishment Instructions and to revise Fig.9 to show correct link orientation. R R R TRENT 700 - LP FUEL TUBES, CLIPS, AND FOHE MOUNTING HARDWARE - INSPECTION FOR FRETTAGE - NON-MODIFICATION SERVICE BULLETIN - MOD.73-AH522**Printed in Great Britain**



# RB.211−73−AH522 Page 1 of 36 Sep.20/13 Jul.18/14 RC. Description This NMSB is issued to recommend on-wing inspection of the P-clips on the LP fuel tube (P/N FW53576) and the FOHE mounts and also to inspect all the LP fuel pipes between the FOHE fuel pump and the FOHE mounts at each engine shop visit. Advise your local Rolls-Royce representative of NMSB accomplishment and any significant inspection results in the table provided (Appendix 1) or similar, and provide to Rolls-Royce. D. Compliance
ALERT This NMSB is anticipated to be the subject of an EASA/FAA Airworthiness Directive. (1) On-wing Complete the actions detailed in 3.A. Accomplishment Instructions at the following intervals: (a) Inspect within 4000 hours either from: (i) New delivery (ii) Last fuel tube inspection. This may have been in accordance with NSMB 73-G848, implementation of NMSB 73-G848 addresses all the inspections of this NMSB. (b) If elapsed time has already exceeded 3200 hours then inspect within 800 hours. (c) Following initial inspection, repeat the inspection at intervals not exceeding 4000 hours. (2) In-shop Complete the actions detailed in 3.B. Accomplishment Instructions at the following intervals: At every engine shop visit. E. Approval The technical content of this Non-Modification Service Bulletin was approved under the authority of Design Organisation Approval EASA.21J.035 on Sep.20/13, Mar.12/14 R R and re-approved on Jul.10/14.**Printed in Great Britain**



# RB.211−73−AH522 Page 2 Sep.20/13 Jul.18/14 RF. Manpower (1) On-wing (a) Time to gain access 0.5 hours (2 persons) (b) Time to inspect 1 hours (1 person) (c) Time to replace tubes and restore to serviceable condition 2 hours (2 persons) (2) In-shop (a) Time to inspect 2 hours (1 person) (b) Time to replace tubes 3 hours (2 persons)
NOTE : The parts affected by this Non-Modification Service Bulletin are accessible at overhaul and on-wing G. Material Price and Availability Not affected. H. Tooling Price and Availability Special tools are not required. I. References (1) Rolls-Royce RB211 Service Bulletin: 73-F343 Fuel - Fuel Tubes - LP Compressor Case - Introduction of revised LP Fuel Tube Assemblies, Associated Bracketry and Clipstacks (2) Rolls-Royce RB211 Non-Modification Service Bulletin: 73-G848**Printed in Great Britain**



# RB.211−73−AH522 Page 3 Sep.20/13 Jul.18/14 RLP - Fuel Tubes, Clips, and FOHE Mounting Hardware - Inspection for Frettage - Non-Modification Service Bulletin (3) Engine Manual: (a) 72-00-34, Install the Components on the Low Pressure (LP) Compressor Case (b) 72-00-34, Install the Tubes and Raceways on the Low Pressure (LP) Compressor (c) 72-00-34, Remove the Tubes and Raceways from the Low Pressure (LP) Compressor (d) 72-00-34, Remove the Components from the Low Pressure (LP) Compressor Case (4) Engine Illustrated Parts Catalogue: (a) 73-11-47, Fuel Tubes LP Compressor Case (b) 79-21-11, Fuel Oil Heat Exchanger (c) 72-34-15, LP Compressor Rear Case (d) 72-35-16, LP Compressor Case Accessory Mounts (5) Airbus A330 Aircraft Maintenance Manuals (a) 79-21-41, Removal of the Fuel Oil Heat Exchanger (b) 79-21-41, Installation of the Fuel Oil Heat Exchanger (c) 71-13-00, Open the Fan Cowl Doors (d) 71-13-00, Close the Fan Cowl Doors (e) 71-00-00, Test No.2, The Fuel and Oil Leak Test (f) 70-12-01, Removal of Rigid Tubes and Flexible Hose Assemblies (g) 70-12-01, Installation of Rigid Tubes and Flexible Hose Assemblies (6) Aircraft Illustrated Parts Catalogue: (a) 73-12-41, Pump - Fuel (b) 79-21-41, Pump - Lubrication and Scavenge Oil**Printed in Great Britain**



# RB.211−73−AH522 Page 4 Sep.20/13 Jul.18/14 R2. Material Information A. The following parts may be required if rejected during inspection: 73-11-47 FIG/ITEM NO. PART NO. QTY PART TITLE MAT
04045 AS48408 1 Bolt, Bihex hd, 0.190 in. dia x 0.500 in. - 04050 FW26690 1 Bracket, Assy accessory mounting - 04051 AS20625 2 Nut, 0.250 in. dia - 04052 AS12944 2 Washer, 0.250 in. dia - 04054 AS48515 2 Bolt, 0.250 in. dia x 0.938 in. - 04070 FW36334 1 Bracket, Assy accessory mounting - 04071 AS20625 2 Nut, 0.250 in. dia - 04072 AS12944 2 Washer, 0.250 in. dia - 04074 AS48515 2 Bolt, 0.250 in. dia x 0.938 in. - 04075 AS48516 1 Bolt, 0.250 in. dia x 1.000 in. - 04100 FW26589 1 Tube, assy fuel - LP pump to line disconnect - 04106 BLT5529 3 Bolt, 0.250 in. dia x 1.028 in. - 04108 AS43013- 134 1 Ring - 04110 AS20625 4 Nut, 0.250 in. dia - 04114 AS48515 4 Nut, 0.250 in. dia x 0.938 in. - 04116 AS43013- 127 1 Ring, 36.17 mm I/D x 2.62 mm - 04300 FW36335 1 Tube, assy fuel line disconnect to line disconnect - 04304 AS20625 4 Nut, 0.250 in. dia - 04306 AS48515 4 Bolt, 0.250 dia x 0.938 - 04308 AS43013- 127 1 Ring, 36.17 mm I/D x 2.62 mm - 04341 AS48410 1 Bolt, 0.190 in. dia x 0.625 in. - 04342 K8831 1 Washer, 0.190 in. dia - 04344 AS62424 1 Clip, 38.10 mm (1.500 in.) - 04347 AS12943 1 Washer, 0.190 in. dia - 04348 AS20624 1 Nut, 0.190 dia - 04500 FW26587 1 Tube, assy fuel - Line disconnect to FCOC - 04514 BLT5529 3 Bolt, 0.250 in. dia x 1.028 in. -**Printed in Great Britain**



# RB.211−73−AH522 Page 5 Sep.20/13 Jul.18/14 R04516 AS43013- 134 1 Ring - 04533 AS48409 1 Bolt, 0.190 in. dia x 0.562 in. 04534 K8831 1 Washer, 0.190 in. dia x 0.51 mm thk - 04536 AS62424 1 Clip, 38.10 mm - 04539 AS12943 1 Washer, 0.190 in. dia - 04540 AS20624 1 Nut, 0.190 in. dia - 04557 AS48409 1 Bolt, 0.190 in. dia x 0.562 in. - 04558 K8831 2 Washer, 0.190 dia x 0.51 mm thk 04560 AS62424 1 Clip, 38.10 mm - 04564 AS20624 1 Nut, 0.190 in. dia - 04565 AS48412 1 Bolt, 0.190 in. dia x 0.750 in. - 04566 K8831 2 Washer, 0.190 in. dia x 0.51 mm thk - 04568 AS62424 1 Clip, 38.10 mm - 04572 AS20624 1 Nut, 0.190 in. dia - 04576 AS62424 1 Clip, 38.10 mm - 04581 AS48408 1 Bolt, 0.190 in. dia x 0.562 in. - 04582 K8831 1 Washer, 0.190 in. dia x 0.51 mm thk - 04584 AS62424 1 Clip, 38.10 mm - 04587 AS12943 1 Washer, 0.190 in. dia - 04588 AS20624 1 Nut, 0.190 in. dia - 73-11-47 FIG/ITEM NO. NEW PART NO. QTY PART TITLE MAT
05070 FW27392 1 Bracket, angle, clipping - 05100 FW53576 1 Tube, assy fuel, FCOC to line disconnect - 05106 BLT5529 3 Bolt, 0.250 in. dia x 1.028 in. - 05108 AS43013- 134 1 Ring - 05110 AS20625 4 Nut, 0.250 in. dia - 05114 AS48515 4 Bolt, 0.190 in. dia x 0.938 in. - 05116 AS43013 1 Ring, 36.17 mm I/D 2.62 mm - 05125 AS48409 1 Bolt, 0.190 in. dia x 0.562 in. - 05126 K8831 1 Washer, 0.190 in. dia x 0.51 mm thk -**Printed in Great Britain**



# RB.211−73−AH522 Page 6 Sep.20/13 Jul.18/14 R05128 AS62424 1 Clip, 38.10 mm (1.500 in.) - 05131 AS12943 1 Washer, 0.190 in. dia - 05132 AS20624 1 Nut, 0.190 in. dia - 05141 AS48408 1 Bolt, 0.190 in. dia x 0.500 in. - 05142 K8831 1 Washer, 0.190 in. dia x 0.51 mm thk - 05144 AS62424 1 Clip, 38.10 mm (1.500 in.) -05150 K8831 1 Washer, 0.190 in. dia x 0.51mm thk05152 AS62424 1 Clip, 38.10 mm (1.500 in.) - 05155 AS12943 1 Washer, 0.190 in. dia - 05156 AS20624 1 Nut, 0.190 in. dia - 05165 AS48410 1 Bolt, 0.190 in. x 0.625 in. - 05166 K8831 1 Washer, 0.190 in. dia x 0.51 mm thk - 05168 AS62424 1 Clip, 38.10 mm (1.500 in.) - 05171 AS12943 1 Washer, 0.190 in. dia - 05172 AS20624 1 Nut, 0.190 in. dia - 05500 FW53577 1 Tube, assy fuel - line disconnect to HP pump - 05514 BLT5529 3 Bolt, 0.250 in. dia x 1.028 in. - 05516 AS43013- 134 1 Ring -

79-21-11 FIG/ITEM NO. NEW PART NO. QTY PART TITLE MAT
01015 FK24907 1 Bracket, angle bonding lead - 01031 AS20626 1 Nut, 0.3125 in. - 01035 AS54722 1 Bolt - 01036 BLT5477 2 Bolt, 0.3125 in. dia x 1.240 in. - 01070 AS20626 1 Nut, 0.3125 in. - 01072 AS12945 1 Washer - 01074 AS54744 1 Bolt, 0.3125 in. dia x 2.750 in. - 01280 FK10141 1 Bracket, assy of FCOC support strut - 01282 BLT5477 2 Bolt, 0.3125 in. dia x 1.240 in. - 01284 AS12945 2 Washer - 01300 FK19290 1 Strut, assy FOHE support - Front - 01302 AS20626 1 Nut, 0.3125 in. - 01306 AS54722 1 Bolt - 01310 UP11630 2 Spacer - 01350 FK10129 1 Bracket, assy of FCOC mounting - Upper - 01352 AS20625 2 Nut, 0.250 in. dia -**Printed in Great Britain**



# RB.211−73−AH522 Page 7 Sep.20/13 Jul.18/14 R01354 AS48521 2 Bolt, 0.250 in. dia x 1.312 in. - 01356 AS12944 4 Washer, 0.250 in. dia - 01400 FK19924 1 Plate, assy FCOC support - 01402 AS20626 1 Nut, 0.3125 in. - 01404 AS54722 1 Bolt - 01500 FK19264 1 Strut, assy FOHE support - Lower - 01502 AS20626 1 Nut, 0.3125 in. - 01504 AS54722 1 Bolt - 01510 UP11630 1 Spacer - 01512 AS20626 1 Nut, 0.3125in. - 01513 AS12945 1 Washer - 01514 BLT5579 1 Bolt, 0.3125 in. dia x 1.500 in. LG - 01560 FK19265 1 Link, assy FOHE support - Lower - 01562 AS20626 1 Nut, 0.3125 in. - 01564 AS54722 1 Bolt - 01580 FK19266 1 Link, assy FOHE support - Upper -

72-34-15 FIG/ITEM NO. NEW PART NO. QTY PART TITLE MAT 02330 FK11165 1 Bracket, assy FCOC forward mounting - 02340 FK11164 1 Bracket, assy FCOC brace mounting - 04321 BLT5512 4 Bolt - 04330 AS12945 4 Washer - 72-35-16 FIG/ITEM NO. NEW PART NO. QTY PART TITLE MAT
05445 FEB5032 1 Strap, Bonding lower - FCOC to rear fancase - 05446 AS20624 1 Nut, 0.190 in. dia - 05447 AS12943 2 Washer, 0.190 in. dia - 05448 AS48410 1 Bolt, 0.190 dia x 0.625 in. - 05480 FK10140 1 Bracket, assy of FCOC mounting - Lower - 05502 AS20625 2 Nut, 0.250 in. dia - 05504 AS12944 3 Washer, 0.250 in. dia - 05505 AS48518 2 Bolt, 0.250 in. dia x 1.125 in. - 05507 AS48408 2 Bolt, 0.190 in. dia x 0.500 in. -**Printed in Great Britain**



# RB.211−73−AH522 Page 8 Sep.20/13 Jul.18/14 R79-11-11 01035 FW26692 1 Bracket, clipping - oil tank top flange -**Printed in Great Britain**



# RB.211−73−AH522 Page 9 Sep.20/13 Jul.18/14 R3. Accomplishment Instructions A. On-wing - Inspect the fuel tube under the p-clips on the fuel tube (P/N FW53576), FOHE to HP fuel pump. Also inspect the FOHE mounting hardware. Refer to Fig.1 through Fig.10.

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 IN-FLIGHT SHUT DOWN, 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, WERE POSSIBLE, TO PROMOTE THIS RECOMMENDATION. (1) Gain access (a) Open the fan cowl doors; refer to Aircraft Maintenance Manual (AMM) 71-13-00. (i) For 4030EM1 (POWERPLANT- DEMOUNTABLE, ENG1): 415AL 416AL (ii) For 4030EM2 (POWERPLANT- DEMOUNTABLE, ENG2): 425AL 426AR (b) Put suitable access platform into a safe position. (2) Visually inspect all clip positions (CP4881, CP2607 and CP2427) on the FOHE to HP fuel pump fuel pipe upper section (P/N FW53576) for damage/wear. Refer to Fig.1, Fig.3, Fig.4 and Fig.5. (a) Remove clip CP4881 to inspect the fuel tube in accordance with criteria as specified in step 3.A.(2)(c). (i) Clipping positions CP4881, CP2607 and CP2427 are located on fuel tube FW53576 (FOHE outlet to HP fuel pump inlet). Refer to Fig.1, Fig.3, Fig.4 and Fig.5. (ii) Do not refit this clip, replace with new at each inspection in accordance with Aircraft Maintenance Manual 70-12-01. Refer to Service Bulletin 73-F343 for specific installation instructions and Fig.3, Fig.4 and Fig.5 for clipping point details.**Printed in Great Britain**



# RB.211−73−AH522 Page 10 Sep.20/13 Jul.18/14 R(iii) If a fuel tube is rejected, remove and replace it in accordance with Aircraft Maintenance Manual 70-12-01. Refer to Service Bulletin 73-F343 for specific installation instructions and Fig.2, Fig.3, Fig.4 and Fig.5 for tube and clipping point details. (b) Make sure clip and tube are returned to a serviceable condition before moving to the next task.
NOTE : During removal of the clips look for any significant relaxation of 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 minimise any strain in the system. Make a note on the proforma (Appendix 1) if alignment issues are seen. (c) Fuel tube acceptance and rejection criteria. Contact frettage to a depth greater than 0.1 mm (0.004 in.) on the outer surface of a bend Reject
Contact frettage to a depth greater than 0.2 mm (0.008 in.) in any other area is evident Reject

NOTE : Take particular care to inspect the entire exposed surface of the tube. A mirror can be used in areas where direct line of sight access is difficult. (d) Repeat steps 3.A.(2)(a) to 3.A.(2)(c) for the clips CP2607 and CP2427. Refer to Fig.4 and Fig.5.**Printed in Great Britain**



# RB.211−73−AH522 Page 11 Sep.20/13 Jul.18/14 R(3) Inspect all FOHE mounts and associated hardware for signs of obvious damage and excessive wear. Refer to Fig.6, Fig.7, Fig.8, Fig.9 and Fig.10.
NOTE : It is not necessary to remove the FOHE from the engine or disconnect the oil and fuel tubes. It is acceptable to inspect the FOHE mounts and associated hardware whist the FOHE is installed on the engine.
NOTE : The FOHE mounts/links/brackets can be removed, inspected and replaced one at a time.
NOTE : The purpose of this inspection is to identify noticeable play in the spherical bearings of the FOHE mounts. In most cases this can be done without removing hardware, by manipulating the FOHE and mounts. If wear is suspected then remove the bolt at one end of the link/strut for more detailed assessment. (a) Inspect the following FOHE mounts and associated hardware one at a time. If required remove the bolt at one end of the link/strut for assessment in accordance with Aircraft Maintenance Manual 79-21-41 and examine by manipulation and visual inspection in accordance with the criteria as specified in step 3.A.(3)(b). EIPC Ref Part No. Description 79-21-11, 01-280 FK10141 Bracket, assy of FCOC support strut 79-21-11, 01-300 FK19290 Strut, assy FOHE support - Front 79-21-11, 01-350 FK10129 Bracket, assy of FCOC mounting - Upper 79-21-11, 01-400 FK19924 Plate, assy FCOC support 79-21-11, 01-500 FK19264 Strut, assy FOHE support - Lower 79-21-11, 01-560 FK19265 Link, assy FOHE support - Lower 79-21-11, 01-580 FK19266 Link, assy FOHE - Upper 72-34-15, 02-330 FK11165 Bracket, assy FCOC forward mounting 72-34-15, 02-340 FK11164 Bracket, assy FCOC brace mounting 72-35-16, 05-480 FK10140 Bracket, assy FCOC brace mounting

NOTE : If replacement of damaged parts is not possible during inspection then they can be replaced within 800 flight hours. (b) FOHE mounting hardware acceptance and rejection criteria:**Printed in Great Britain**



# RB.211−73−AH522 Page 12 Sep.20/13 Jul.18/14 RBearing tight but not seized Accept Low friction but no play in bearings Accept
Minor scratches/score marks Accept Play in spherical bearings Replace within 800 flight hours Spherical bearings seized Replace within 800 flight hours Bent or twisted Replace within 800 flight hours (4) If fancase mounting brackets P/N FK10140, P/N FK11165 or P/N FK11164 is found to be unserviceable, remove and replace in accordance with the following instructions. Refer to Fig.8 and Fig.10. (a) Remove and install the bracket (P/N FK10140). Refer to Fig.8. (i) Remove the three bolts (P/N AS48518), the four washers (P/N AS12944) and the three nuts (P/N AS20625) that attach the bracket to flange FC. (ii) Remove the bracket (P/N FK10140). (iii) Attach the new bracket to bracket (P/N FK14374) and the flange FC. Use the three bolts (P/N AS48518), the four washers (P/N AS12944) and the three nuts (P/N AS20625). (iv) Torque the nuts (72-35-16, 05-502) to 11.5 Nm (100 lbfin). (b) Remove and install the bracket (P/N FK11165). Refer to Fig.10. (i) Remove the two bolts (P/N BLT5512) and the two washers (P/N AS12945) that attach the bracket to flange FB. (ii) Remove the bracket (P/N FK11165). (iii) Locally clean bracket fitment area and new bracket mating faces using an OMat 2/101 lint-free cloth moistened with either OMat 135 Methyl Ethyl Ketone, OMat 150 Acetone, OMat 1/40 Isopropyl alcohol or OMat 1/257 cleaning solvent. (iv) Apply jointing compound MSRR 9055 (Hylomar Grade L) to the mating face of bracket (P/N FK11165). (v) Attach the new bracket to flange FB. Use the two bolts (P/N BLT5512) and the two washers (P/N AS12945). (vi) Torque the bolts (P/N BLT5512) to 24 Nm (210 lbfin).**Printed in Great Britain**



# RB.211−73−AH522 Page 13 Sep.20/13 Jul.18/14 R(vii) Remove excess jointing compound. (c) Remove and install the brackets (P/N FK11164) and (P/N FK20859). Refer to Fig.10. (i) Remove the two bolts (P/N BLT5512) and the two washers (P/N AS12945) that attach the bracket to flange FB. (ii) Remove the brackets (P/N FK11164) and (P/N FK20859). (iii) Locally clean bracket fitment area and new bracket mating faces using an OMat 2/101 lint-free cloth moistened with either OMat 135 Methyl Ethyl Ketone, OMat 150 Acetone, OMat 1/40 Isopropyl alcohol or OMat 1/257 cleaning solvent. (iv) Apply jointing compound MSRR 9055 (Hylomar Grade L) to the mating face of bracket (P/N FK11165). (v) Attach the new brackets (P/N FK11164) and (P/N FK20859) to flange FB. Use the two bolts (P/N BLT5512) and the two washers (P/N AS12945). (vi) Torque the bolts (P/N BLT5512) to 24 Nm (210 lbfin). (vii) Remove excess jointing compound. (5) Re-assemble the FOHE mounts and links in accordance with Aircraft Maintenance Manual, 79-21-41. R (6) Close the fan cowl doors; refer to Aircraft Maintenance Manual (AMM) Task 71-13-00. (a) For 4030EM1 (POWERPLANT-DEMOUNTABLE, ENG1): 415AL 416AL (b) For 4030EM2 (POWERPLANT-DEMOUNTABLE, ENG2): 425AL 426AR (7) Remove the access platform. (8) If any fuel tube was replaced then do a fuel and oil leak test in accordance with Aircraft Maintenance Manual, 71-00-00, Test No.2, The Fuel and Oil Leak Test. (9) If any abnormal findings or damage was noted, complete Proforma (Appendix 2) and return to Rolls-Royce FSO. B. At shop visit - Inspect the fuel tubes (Part numbers FW26589, FW36335, FW26587 and FW53576, FW53577), P-clips and FOHE mounting hardware for**Printed in Great Britain**



# RB.211−73−AH522 Page 14 Sep.20/13 Jul.18/14 Rwear/damage/frettage. Refer to Fig.1 to Fig.17.

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. (1) Visually inspect the LP fuel tubes (EIPC 73-11-47 Fig/Item No.05-100, 05-500, 04-100, 04-300 and 04-500) and the relevant clipstacks for damage/wear. Refer to Fig.1 to Fig.5 and Fig.11 to Fig.17.
NOTE : If it is not planned to remove the tubes as part of the existing shop visit, the clips should be removed and replaced with new, one at a time to prevent pre-loading of the clip position. (a) Visually inspect all the clips for obvious evidence of wear that may have damaged the fuel tubes (for example, significant wear to rubber and/or dust/debris at location of clip). (i) Remove any obviously damaged clip(s) first and inspect fuel tube(s) in accordance with the criteria as specified in 3.B.(1)(e). (ii) If fuel tubes are found unserviceable, remove and replace in accordance with Accomplishment Instructions 3.B.(1)(f). (iii) Do not refit any used clips, replace with new at each inspection. (b) Remove and inspect each remaining clip one at a time (positions specified in 3.B.(1)(b)(i) and 3.B.(1)(b)(ii)) and inspect fuel tube(s) in accordance with the criteria as specified in 3.B.(1)(e). Start from either the top or the bottom of the tube run. (i) Clipping positions CP2433, CP2729, CP2556, CP2430, CP2664, CP2946 and CP2428 are located on the fuel tubes FW26587, FW36335, FW26589 (LP outlet to FOHE inlet tube run). Refer to Fig.11, Fig.13 to Fig.17. (ii) Clipping positions CP4881, CP2607 and CP2427 are located on the fuel tubes FW53576, FW53577 (FOHE outlet to HP inlet tube run). Refer to Fig.1, Fig.3, Fig.4, Fig.5.
NOTE : Inspection of the clips must be done one at a time to prevent alteration to the system alignment and stressing of the tube and clips.**Printed in Great Britain**



# RB.211−73−AH522 Page 15 Sep.20/13 Jul.18/14 R(iii) Do not refit any used clips, replace with new at each inspection. (c) Inspect the fuel tube around the area which the clip was fitted in accordance with criteria as specified in 3.B.(1)(e). (i) If fuel tube is found to be serviceable, reinstall tube and replace clips in accordance with Engine Manual 72-00-34. Refer to Fig.3, Fig.4, Fig.5, Fig.13 or Fig.17 for specific tube and clipping point details. (ii) If any tubes are found to be unserviceable, replace in accordance with Accomplishment Instructions 3.B.(1)(f). (d) Ensure clip is replaced and the tube is back to a serviceable condition before moving to the next clipping point.
NOTE : During removal of the clips look for any significant relaxation of 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 minimise any strain in the system. Make a note on the proforma (Appendix 2) or similar if alignment issues are seen. (e) Fuel tube acceptance and rejection criteria Contact frettage to a depth greater than 0.1 mm (0.004 in.) on the outer surface of a bend on the tube Reject
Contact frettage to a depth greater than 0.2 mm (0.008 in.) in any other area of the tube Reject
(f) If the fuel tube is rejected, remove and replace it in accordance with Engine Manual 72-00-34. Refer to Fig.3, Fig.4, Fig.5, Fig.13 to Fig.17 for specific tube and clipping point details.
NOTE : Take particular care to inspect the entire exposed surface of the tube. A mirror can be used in areas where direct line of sight access is difficult.**Printed in Great Britain**



# RB.211−73−AH522 Page 16 Sep.20/13 Jul.18/14 R(2) Inspect all FOHE mounts and associated hardware for signs of obvious damage and excessive wear. Refer to Fig.6, Fig.7, Fig.8, Fig.9 and Fig.10.
NOTE : It is not necessary to remove the FOHE from the engine or disconnect the oil and fuel tubes. It is acceptable to inspect the FOHE mounts and associated hardware whist the FOHE is installed on the engine.
NOTE : The FOHE mounts/links/brackets can be removed, inspected and replaced one at a time.
NOTE : The purpose of this inspection is to identify noticeable play in the spherical bearings of the FOHE mounts. In most cases this can be done without removing hardware, by manipulating the FOHE and mounts. If wear is suspected then remove the bolt at one end of the link/strut for more detailed assessment. (a) Inspect the following FOHE mounts and associated hardware one at a time. If required remove the bolt at one end of the link/strut for assessment in accordance with Engine Manual 72-00-34 and examine by manipulation and visual inspection in accordance with the criteria as specified in step 3.A.(2)(b). EIPC Ref Part No. Description 79-21-11, 01-280 FK10141 Bracket, assy of FCOC support strut 79-21-11, 01-300 FK19290 Strut, assy FOHE support - Front 79-21-11, 01-350 FK10129 Bracket, assy of FCOC mounting - Upper 79-21-11, 01-400 FK19924 Plate, assy FCOC support 79-21-11, 01-500 FK19264 Strut, assy FOHE support - Lower 79-21-11, 01-560 FK19265 Link, assy FOHE support - Lower 79-21-11, 01-580 FK19266 Link, assy FOHE - Upper 72-34-15, 02-330 FK11165 Bracket, assy FCOC forward mounting 72-34-15, 02-340 FK11164 Bracket, assy FCOC brace mounting 72-35-16, 05-480 FK10140 Bracket, assy FCOC brace mounting
(b) FOHE mounting hardware acceptance and rejection criteria: Bearing tight but not seized Accept**Printed in Great Britain**



# RB.211−73−AH522 Page 17 Sep.20/13 Jul.18/14 RLow friction but no play in bearings Accept
Minor scratches/score marks Accept Play in spherical bearings Reject Spherical bearings seized Reject Bent or twisted Reject (3) If fancase mounting bracket, 72-35-16, 05-480, 72-34-15, 02-330 or 02-340 is found to be unserviceable, remove and replace in accordance with the following instructions. Refer to Fig.8 and Fig.10. (a) Remove and install the bracket (72-35-16, 05-480). Refer to Fig.8. (i) Remove the three bolts, the four washers and the three nuts that attach the bracket to flange FC. (ii) Remove the bracket. (iii) Attach the new bracket to bracket (73-35-16, 05-500) and the flange FC. Use the three bolts (72-35-16, 05-505), the four washers (72-35-16, 05-504) and the three nuts (72-35-16, 05-502). (iv) Torque the nuts (72-35-16, 05-502) to 11.5 Nm (100 lbfin). (b) Remove and install the bracket (72-34-15, 02-330). Refer to Fig.10. (i) Remove the two bolts and the two washers that attach the bracket to flange FB. (ii) Remove the bracket. (iii) Locally clean bracket fitment area and new bracket mating faces using an OMat 2/101 lint-free cloth moistened with either OMat 135 Methyl Ethyl Ketone, OMat 150 Acetone, OMat 1/40 Isopropyl alcohol or OMat 1/257 cleaning solvent. (iv) Apply jointing compound MSRR 9055 (Hylomar Grade L) to the mating face of bracket (72-34-15, 02-330). (v) Attach the new bracket to flange FB. Use the two bolts (72-34-15, 04-321) and the two washers (72-34-15, 04-330). (vi) Torque the bolts (72-34-15, 04-321) to 24 Nm (210 lbfin). (vii) Remove excess jointing compound.**Printed in Great Britain**



# RB.211−73−AH522 Page 18 Sep.20/13 Jul.18/14 R(c) Remove and install the brackets (72-34-15, 02-340) and (72-34-15, 02-775). Refer to Fig.10. (i) Remove the two bolts and the two washers that attach the bracket to flange FB. (ii) Remove the brackets (72-34-15, 02-340) and (72-34-15, 02-775). (iii) Locally clean bracket fitment area and new bracket mating faces using an OMat 2/101 lint-free cloth moistened with either OMat 135 Methyl Ethyl Ketone, OMat 150 Acetone, OMat 1/40 Isopropyl alcohol or OMat 1/257 cleaning solvent. (iv) Apply jointing compound MSRR 9055 (Hylomar Grade L) to the mating face of bracket (72-34-15, 02-330). (v) Attach the new brackets (72-34-15, 02-340) and (72-34-15, 02-775) to flange FB. Use the two bolts (72-34-15, 04-321) and the two washers (72-34-15, 04-330). (vi) Torque the bolts (72-34-15, 04-321) to 24 Nm (210 lbfin). (vii) Remove excess jointing compound. (4) Re-assemble the FOHE mounts and links in accordance with Engine Manual, 72-00-34 and 72-34-00. (5) If any abnormal findings or damage was noted, complete Proforma (Appendix 2) and return to Rolls-Royce FSO. C. A record of accomplishment is required, refer to Appendix 1.**Printed in Great Britain**



# RB.211−73−AH522 Page 19 Sep.20/13 Jul.18/14 RGeneral Fuel Tube Arrangement Fig.1**Printed in Great Britain**



# RB.211−73−AH522 Page 20 Sep.20/13 Jul.18/14 RArrangement of Fuel Tubes FW53577 and FW53576 Fig.2**Printed in Great Britain**



# RB.211−73−AH522 Page 21 Sep.20/13 Jul.18/14 RArrangement of Clip Position CP4881 Fig.3**Printed in Great Britain**



# RB.211−73−AH522 Page 22 Sep.20/13 Jul.18/14 RArrangement of Clip Position CP2427 Fig.4**Printed in Great Britain**



# RB.211−73−AH522 Page 23 Sep.20/13 Jul.18/14 RArrangement of Clip Position CP2607 Fig.5**Printed in Great Britain**



# RB.211−73−AH522 Page 24 Sep.20/13 Jul.18/14 RGeneral Arrangement of FOHE Mounting Hardware Fig.6**Printed in Great Britain**



# RB.211−73−AH522 Page 25 Sep.20/13 Jul.18/14 RArrangement of FOHE Upper Mounting Bracket (P/N FK10129) and Upper Front Strut (P/N FK19290)

Fig.7**Printed in Great Britain**



# RB.211−73−AH522 Page 26 Sep.20/13 Jul.18/14 RArrangement for Brackets (FK10140 and FK14347) Fig.8**Printed in Great Britain**



# RB.211−73−AH522 Page 27 Sep.20/13 Jul.18/14 RR

Arrangement of FOHE Lower Mounting Brackets, Struts and Links R Fig.9 R**Printed in Great Britain**



# RB.211−73−AH522 Page 28 Sep.20/13 Jul.18/14 RArrangement for Brackets (FK11164 and FK11165) Fig.10**Printed in Great Britain**



# RB.211−73−AH522 Page 29 Sep.20/13 Jul.18/14 RGeneral Fuel Tube Arrangement Fig.11**Printed in Great Britain**



# RB.211−73−AH522 Page 30 Sep.20/13 Jul.18/14 RArrangement of Fuel Tubes FW26587, FW36335 and FW26589 Fig.12**Printed in Great Britain**



# RB.211−73−AH522 Page 31 Sep.20/13 Jul.18/14 RArrangement of Clip Positions CP2430 and CP2433 Fig.13**Printed in Great Britain**



# RB.211−73−AH522 Page 32 Sep.20/13 Jul.18/14 RArrangement of Clip Position CP2428 Fig.14**Printed in Great Britain**



# RB.211−73−AH522 Page 33 Sep.20/13 Jul.18/14 RArrangement of Clip Position CP2556 Fig.15**Printed in Great Britain**



# RB.211−73−AH522 Page 34 Sep.20/13 Jul.18/14 RArrangement of Clip Positions CP2664 and CP2729 Fig.16**Printed in Great Britain**



# RB.211−73−AH522 Page 35 Sep.20/13 Jul.18/14 RArrangement of Clip Positions CP2946 Fig.17**Printed in Great Britain**



# RB.211−73−AH522 Page 36 Sep.20/13 Jul.18/14 R1. Fill in the Proforma in Appendix 2 for In-shop Inspections or Appendix 3 for On-wing Inspections. 2. Forward the inspection results and associated information to your Rolls-Royce FSO. 3. Accomplishment of this Non-Modification Service Bulletin should be in accordance with local SB tracking system procedures. APPENDIX 1**Printed in Great Britain**



# RB.211−73−AH522 Appendix 1 - Page 1 of 1 Sep.20/13 Jul.18/14 RFeedback Sheet NMSB 73-AH522 (In-shop Inspection) Date: Operator: Engine No. Aircraft: Hours Cycles Engine Life: Life Since Last Shop Visit: Life Since Embodiment of SB73-F343: Fuel Tubes Condition Observations (material transfer/fretted/dented/worn - please specify depth) Fig.No.

FW53576 Fig.1

FW53577 Fig.1

FW26587 Fig.11

FW36335 Fig.11

FW26589 Fig.11 Clips Condition Observations (material transfer/dust/worn/cracked/metal band exposed) Fig.No.

4881 Fig.3

2607 Fig.5

2427 Fig.4

2433 Fig.13

2729 Fig.16

2556 Fig.15

2430 Fig.13 APPENDIX 2**Printed in Great Britain**



# RB.211−73−AH522 Appendix 2 - Page 1 of 2 Sep.20/13 Jul.18/14 R2664 Fig.16

2946 Fig.17

2428 Fig.14
FOHE Mounts

Condition Observations (wear/cracked/fretted/dented/bent/twisted - Please specify depth) Fig./Part No.

Plate 01-400 Fig.9, FK19924 Link 01-580 Fig.9, FK19266 Link 01-560 Fig.9, FK19265 Strut 01-500 Fig.9, FK19264 Bracket 72-35-16, 05-480 Fig. 8/ Fig. 9/Fig.10,

FK10140 Strut 01-300 Fig.7, FK19290 Bracket 01-280 Fig.7, FK10141 Bracket 01-350 Fig.7, FK10129 Bracket 02-775 Fig.10, FK20859 Bracket 01-035 Fig.3, FK26692 Bracket 02-330 Fig. 7/Fig.10,

FK11165 Bracket 02-340 Fig. 7/Fig.10,

FK11164
Notes:**Printed in Great Britain**



# RB.211−73−AH522 Appendix 2 - Page 2 Sep.20/13 Jul.18/14 RFeedback Sheet NMSB 73-AH522 (On-wing Inspection) Date: Operator: Engine No. Aircraft: Hours Cycles Engine Life: Life Since Last Shop Visit: Life Since Embodiment of SB73-F343: Fuel Tubes Condition Observations (material transfer/fretted/dented/worn - please specify depth) Fig.No.

FW53576 Fig.1

FW53577 Fig.1 Clips Condition Observations (material transfer/dust/worn/cracked/metal band exposed) Fig.No.

4881 Fig.3

2607 Fig.5

2427 Fig.4
FOHE Mounts

Condition Observations (wear/cracked/fretted/dented/bent/twisted - Please specify depth) Fig./Part No.

Plate 01-400 Fig.9, FK19924 Link 01-580 Fig.9, FK19266 Link 01-560 Fig.9, FK19265 Strut 01-500 Fig.9, FK19264 Bracket 72-35-16, 05-480 Fig. 8/ Fig. 9/Fig.10,

FK10140 APPENDIX 3**Printed in Great Britain**



# RB.211−73−AH522 Appendix 3 - Page 1 of 2 Sep.20/13 Jul.18/14 RStrut 01-300 Fig.7, FK19290 Bracket 01-280 Fig.7, FK10141 Bracket 01-350 Fig.7, FK10129 Bracket 02-775 Fig.10, FK20859 Bracket 01-035 Fig.3, FK26692 Bracket 02-330 Fig. 7/Fig.10,

FK11165 Bracket 02-340 Fig. 7/Fig.10,

FK11164
Notes:**Printed in Great Britain**



# RB.211−73−AH522 Appendix 3 - Page 2 Sep.20/13 Jul.18/14 R