All pages of Appendix 1 Page 1 of Appendix 1 To revise 3. Accomplishment Instructions, 1.F. Manpower, 1.G. Material Price and Availability, 1.H. Tooling Price and Availability. Updated 1.B. Reason, 1.E. Approval. Minor non-technical changes also made.**Printed in Great Britain**



# RB.211−72−AG971 Transmittal - Page 2LIST 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 Sep.27/13 R 2 1 Sep.27/13 R 3 1 Sep.27/13 R 4 1 Sep.27/13 R 5 1 Sep.27/13 R 6 1 Sep.27/13 R 7 1 Sep.27/13 R 8 1 Sep.27/13 R 9 1 Sep.27/13 R 10 1 Sep.27/13 R 11 1 Sep.27/13 R 12 1 Sep.27/13 R 13 1 Sep.27/13 R 14 1 Sep.27/13 R 15 1 Sep.27/13 R 16 1 Sep.27/13 R 17 1 Sep.27/13 R 18 1 Sep.27/13 R 19 1 Sep.27/13 Appendix 1 R 1 1 Sep.27/13**Printed in Great Britain**



# RB.211−72−AG971 Transmittal - Page 31. Planning Information A. Effectivity Airbus A380 All RB211 TRENT 900 Engines
B. Reason Problem Re-analysis of Tail Bearing Housing (TBH) structural features R has shown that the TBH does not R have full limit load capability in the fail safe condition. To confirm intact capability, an on-wing R and in-shop inspection regime has been defined for the Trent 900 TBH. The structural features to be inspected are the TBH mount lug run-outs and Top Core Vanes (TCV). In addition, the life of the TBH is to be limited to 17200 cycles to make sure it does not enter in fail safe mode. R R R Additionally, historical inspections of the TBH to initial issue of Non-Modification Service Bulletin (NMSB) 72-AG971 identified issues which required additional inspection criteria as part of a revised containment strategy. This has been addressed independently through NMSB 72-AH154. R R R R Revision 1 of this NMSB is issued to provide additional clarity for some of the materials, tooling and cleaning tasks associated with inspections. It also revises the acceptance criteria for the on-wing inspections (section 3.A.(2)) and introduces the inspection of the fail safe catcher in-shop to inform root cause understanding for the issues addressed in NMSB 72-AH154. R R R R R C. Description This Non-Modification Service Bulletin (NMSB) instructs the following: (1) On-wing or R in-shop TBH mount lug run-out inspections which are required on all engines across the Trent 900 fleet every 2200 cycles. (2) The in-shop inspection of TBH top core vanes which are required on all engines across the Trent 900 fleet every 3800 cycles. (3) Adherence to the above inspection intervals until the TBH Life of 17200 Cycles is reached. The Time Limits Manual is to be updated to instruct that the life of the TBH is 17200 cycles. TRENT 900 LP TURBINE EXHAUST CASE AND SUPPORT ASSEMBLY (TAIL BEARING HOUSING) MOUNT LUG RUN-OUT AND TOP CORE VANE INSPECTIONS - NON-MODIFICATION SERVICE BULLETIN - NON - MOD.72-AG971**Printed in Great Britain**



# RB.211−72−AG971 Page 1 of 19 Sep 20/12 Sep.27/13 ROn-wing a specified area on the mount lug run-outs is to be crack tested using a Fluorescent Penetrant Inspection (FPI) method, see Fig.1. In shop, the mount lug run-outs can either be inspected using a local FPI or through a full FPI of the TBH. In shop the top core vanes are to be inspected by a full FPI of the TBH. This NMSB applies to all the below TBH part numbers: FW27718 FW35923 FW51434 Results of the Inspections are to be returned to Rolls-Royce. 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. Rolls-Royce recommends that the following action is undertaken to maintain continued airworthiness. This NMSB applies to both on-wing and in-shop activities. (1) On-wing - Localised Mount Lug Run-Outs Inspection: R Accomplish the first inspection in accordance with section 3.A. Accomplish the first inspection within 2200 cycles for the TBH mount lug run-outs if it is not to be done in-shop. Subsequent inspections whether in-shop or on-wing should be within 2200 cycles of previous inspection. Any TBH mount lug run-outs that were inspected to TV124801 or TV124851 prior to initial R issue of this NMSB are deemed as compliant with the NMSB. Repeat R this inspection regime until the TBH life of 17200 cycles is reached. The Time Limits Manual is to be updated to instruct that the life of the TBH is 17200 cycles.**Printed in Great Britain**



# RB.211−72−AG971 Page 2 Sep 20/12 Sep.27/13 R(2) In-shop - Localised Mount Lug Run-outs Inspection: Accomplish the first inspection in accordance with section 3.B. Accomplish the first inspection within 2200 cycles for the TBH mount lug run-outs if it is not to be done on-wing or in-shop through full FPI of the TBH. Subsequent inspections whether in-shop or on-wing should be within 2200 cycles of previous inspection. Any TBH mount lug run-outs that were inspected to TV124801 or TV124851 prior to initial R issue of this NMSB are deemed as compliant with the NMSB. Repeat R this inspection regime until the TBH life of 17200 cycles is reached. The Time Limits Manual is to be updated to instruct that the life of the TBH is 17200 cycles. (3) In-shop - Top Core Vanes and Mount Lug Run-outs Inspection through full FPI of the TBH: Accomplish the first inspection of the Top Core Vanes in accordance with section 3.C. Accomplish the first inspection within 3800 cycles for the TBH top core vanes. Subsequent inspections should be within 3800 cycles of previous inspection. Inspection of the mount lug run-outs can also be accomplished in accordance with section 3.C. Accomplish the first inspection within 2200 cycles for the TBH mount lug run-outs if it is not to be done on-wing or through a localised in-shop inspection. Subsequent inspections whether in-shop or on-wing should be within 2200 cycles of previous inspection. Repeat R this inspection regime until the TBH life of 17200 cycles is reached. The Time Limits Manual is to be updated to instruct that the life of the TBH is 17200 cycles. 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.4/12 and was re-approved on Sep.13/13. R R The inspection procedures described in this SB are reviewed and technically accepted by Airbus Design Office to apply to the Airbus fleet affected. This SB does not contain any change information that revises the equipment definition covered by Airbus approved modifications.**Printed in Great Britain**



# RB.211−72−AG971 Page 3 Sep 20/12 Sep.27/13 RF. Manpower (1) On-wing: (a) Time to gain access 1 hour (1 person) (b) Time to inspect TBH Mount Lug Run-outs 3 hours (2 persons) (c) Time to restore to serviceable condition 1 hour (1 person) (2) In-shop: (a) Time to locally inspect TBH Mount Lug Run-outs 2 hours (2 persons) (b) Inspection of TBH through full FPI Level 2 workscope The FPI defined in this Technical Instruction shall only be performed by personnel qualified to FPI level 2 or higher and in possession of an up to date eyesight record in accordance with EN4179/NAS410 or alternative standards/guidelines accepted by the applicable National Aviation Authority. G. Material Price and Availability

Material/Compounds Description OMat 651 (Aerosol) R Aerosol R penetrant - Commercially available OMat 617 (Aerosol) R Aerosol R Developer - Commercially available OMat 150 Acetone OMat 2/101 Lint-Free Cloth OMat 677 Penetrant Test Panel H. Tooling Price and Availability

Material/Compounds R Description Dark Non-reflective cover R R To darken the area for inspection - Commercially available**Printed in Great Britain**



# RB.211−72−AG971 Page 4 Sep 20/12 Sep.27/13 RUltra Violet (UV) light source R R 2 alternatives R Capable of providing a minimum UV radiation intensity of 1200 micro W/sq.cm at the inspection surface. R R Alternatively, Spectroline Tritan 365 UV/White LED Inspection Lamp, Portable, Battery Operated Version, Part Number - TRI-365MH/FB Kit R R R Unit Price - Approximately £ 1200, Supplier - RSL NDT Ltd. R I. References (1) Aircraft Maintenance Manual (AMM) (a) 71-13-00, Maintenance Practices, Opening of Fan Cowl Doors (b) 78-26-00, Maintenance Practices, Opening/Closing of the Fan Exhaust Cowl or Thrust Reverser (c) 78-30-00, Deactivation/Reactivation, Make the Thrust Reverser Unserviceable for Maintenance (d) 70-20-02, Maintenance Processes - Inspection - Maintenance Practices, Fluorescent Penetrant Inspection (2) Engine Manual (EM) (a) 70-00-00, Overhaul Process 102, Primary Cleaning Aqueous, Overhaul Process 121, Alkaline Derusting and Descaling, Overhaul Process 134, Acidic Descalers, Overhaul Process R R R 210, Fluorescent Penetrant Inspection. R (b) 72-52-00-030-802, Engine Data Task, Disassemble the LP Turbine (c) 72-52-51-200-801, Cleaning/Inspection and Repair Data Task, Examine the LP Turbine Exhaust Case**Printed in Great Britain**



# RB.211−72−AG971 Page 5 Sep 20/12 Sep.27/13 R2. Material Information
A. None**Printed in Great Britain**



# RB.211−72−AG971 Page 6 Sep 20/12 Sep.27/13 R3. Accomplishment Instructions A. On-wing - Localised R Mount Lug Run-outs Inspection

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 SHUTDOWN, POWER LOSS OR OTHER ANOMALIES 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. R R R R R R R R R (1) To get access to the Tail Bearing Housing (TBH) mount lug run-outs: (a) Open the fan cowl doors in accordance with AMM Task 71-13-00, Maintenance Practices to get access (b) Make the thrust reverser unserviceable for maintenance in accordance with AMM 78-30-00, Deactivation/Activation.
WARNING : YOU MUST MAKE THE THRUST REVERSER UNSERVICEABLE (INSTALL AND SAFETY THE INHIBITION DEVICE) BEFORE YOU DO WORK ON OR AROUND THE THRUST REVERSER. IF YOU DO NOT INSTALL AND SAFETY THE INHIBITION DEVICE, THERE IS A RISK THAT THE THRUST REVERSER CAN OPERATE ACCIDENTALLY. THIS CAN CAUSE INJURY TO PERSON AND/OR DAMAGE TO THE EQUIPMENT. (c) Open the fan exhaust cowls in accordance with the AMM, 78-26-00. (d) Use appropriate staging to gain access to the TBH. (2) Carry out the inspection on the mount lug run-outs:
WARNING : PROTECTIVE GLOVES AND SAFETY GLASSES MUST BE WORN AT ALL TIMES DURING THE INSPECTION. IF YOU GET AN INJURY, SEEK MEDICAL AID IMMEDIATELY (a) This inspection must be performed in accordance with the requirements of AMM 70-20-02, Maintenance Processes - Inspection - Maintenance Practices, Fluorescent Penetrant Inspection.**Printed in Great Britain**



# RB.211−72−AG971 Page 7 Sep 20/12 Sep.27/13 R(b) Clean R the inspection areas (see Fig.1) with a clean OMat 2/101 lint-free cloth moistened with OMat 150 acetone. R R (c) Discard the soiled cloth after use. R (d) Repeat the swabbing using fresh OMat 150 acetone and a fresh OMat 2/101 lint-free cloth until R R all deposits have been removed.
NOTE : The inspection surface, must be clean, dry and free from soils, oil, grease, paint, coatings, corrosion products, scale, smeared metal, welding flux, chemical residues or any other material that could prevent penetrant from entering a discontinuity, affect process performance or produce an unacceptable background. (e) Allow five R minutes for the area to completely dry prior to penetrant application. (f) Penetrant application - Apply OMat 651 R penetrant to the inspection areas (Fig.1) by brush or sponge applicator. The penetrant must be dispensed from a sealed aerosol can and any unused penetrant must go to waste. (g) Make sure that the inspection area is fully covered with penetrant with the aid of a UV lamp. (h) Apply OMat 651 R penetrant to the OMat 677 penetrant test panel. (i) Leave the penetrant in contact with the components for 30 minutes.
NOTE : The penetrant contact time must not exceed one hour. If it does, the penetrant must be re-applied and 5 minutes contact time allowed. (j) Penetrant Removal - After the 30 minutes contact time, remove the excess penetrant from the inspection surface and the OMat 677 penetrant test panel by wiping thoroughly with a clean OMat 2/101 lint-free cloth. (k) Whilst illuminating with UV light, wipe off the penetrant with a clean OMat 2/101 lint-free cloth moistened with OMat 150 acetone. Use the minimum application necessary to achieve acceptable background fluorescence and make sure that acetone is not allowed to flow on the inspection surface. (l) Make sure that all traces of the OMat 150 acetone have been completely removed. (m) Develop - Apply a light, even coating of OMat 617 non-aqueous wet developer from a sealed aerosol can to the inspection area and the OMat 677 penetrant test panel.**Printed in Great Britain**



# RB.211−72−AG971 Page 8 Sep 20/12 Sep.27/13 R(n) Allow 10 minutes contact time for the developer prior to inspection. R (o) Cover the region of the engine with a dark non-reflective cover in order to reduce the white light levels. (p) Make sure there are no white light sources or fluorescent items (including clothing) within the inspection area or the inspector's field of vision. (q) Do not wear darkened or light sensitive glasses. (r) Allow one minute for eye adaptation to the darkened area. (s) Illuminate the OMat 677 penetrant test panel in the darkened area R with one of the allowed R UV light sources listed in 1.H. Tooling Price and Availability. R R (t) Inspect the OMat 677 penetrant test panel and check that the four R largest indications are visible and match the control photograph for that individual panel. (u) Illuminate the inspection surface with the same R UV light in the darkened area. (v) Inspect the mount lug run-outs for crack indications. (w) The Wipe Off technique can be used to aid the evaluation of any indications: R (i) Dampen a cotton swab with acetone. R (ii) Wipe once across the indication. R (iii) Allow the acetone to evaporate and inspect immediately. R (iv) If the indication reappears then record it is a crack. If the indications does not reappear then apply a light, even coating of OMat 617 non-aqueous wet developer from a sealed aerosol can to the area. R R R R (v) Allow the solvent in the developer to evaporate and inspect immediately. R R (vi) If the indication reappears then record it as a crack. If the indication does not reappear then allow 10 minutes contact time for the developer. R R R (vii) If the indication reappears after the 10 minutes contact time then record it as a crack. If the indication does not reappear then that area is acceptable. R R R**Printed in Great Britain**



# RB.211−72−AG971 Page 9 Sep 20/12 Sep.27/13 R(x) The cause of all indications must be evaluated under white light using visual aids, such as magnification, as appropriate. (y) Photograph R any suspected crack indications and record them in Appendix 1. (z) No cracks detected - Accept Any cracks less than or equal to 2mm length R - Remove engine within 10 flight cycles R Any cracks greater than 2mm length - Remove engine or refer to Rolls-Royce R R
NOTE : Any findings outside the above limits can be referred to Rolls-Royce to determine if up to 10 flight cycles additional fly on can be granted in order to facilitate engine removal. R R R (aa) Post Clean - Once all indications have been evaluated and recorded, remove the penetrant processing materials from the inspection surface by wiping with a clean OMat 2/101, lint-free cloth moistened with OMat 150 acetone. (ab) Restore the OMat 677 penetrant test panel to a completely clean condition and make sure there is no residual fluorescence. R R (3) Close access to the tail bearing housing: (a) Make sure the work area is clean and clear of tools and other items. (b) Close the fan exhaust cowls in accordance with AMM 78-26-00, Maintenance Practices. (c) Make the thrust reverser serviceable after maintenance in accordance with AMM 78-30-00, Deactivation/Activation as necessary. (d) Close the fan exhaust cowls in accordance with AMM 71-13-00, Maintenance Practices. (4) Accomplishment of this Non-Modification Service Bulletin should be recorded in accordance with local SB tracking system procedures.**Printed in Great Britain**



# RB.211−72−AG971 Page 10 Sep 20/12 Sep.27/13 RB. In-shop - Localised Mount Lug Run-outs Inspection (1) Carry out the inspection on the mount lug run-outs (local inspection only)
WARNING : PROTECTIVE GLOVES AND SAFETY GLASSES MUST BE WORN AT ALL TIMES DURING THE INSPECTION. IF YOU GET AN INJURY, SEEK MEDICAL AID IMMEDIATELY (a) This inspection must be performed in accordance with the requirements of 70-00-00 Overhaul Process 210, Fluorescent Penetrant Inspection. (b) Clean the inspection areas (see Fig.1) with a clean OMat 2/101 lint-free cloth moistened with OMat 150 acetone. R R (c) Discard the soiled cloth after use. R (d) Repeat the swabbing using fresh OMat 150 acetone and a fresh OMat 2/101 lint-free cloth until all deposits have been removed. R R
NOTE : The inspection surface, must be clean, dry and free from soils, oil, grease, paint, coatings, corrosion products, scale, smeared metal, welding flux, chemical residues or any other material that could prevent penetrant from entering a discontinuity, affect process performance or produce an unacceptable background. (e) Allow five R minutes for the area to completely dry prior to penetrant application. (f) Penetrant application - Apply OMat 651 R penetrant to the inspection areas (see Fig.1) by brush or sponge applicator. The penetrant must be dispensed from a sealed aerosol can and any unused penetrant must go to waste. (g) Make sure that the inspection area is fully covered with penetrant with the aid of a UV lamp. (h) Apply OMat 651 R penetrant to the OMat 677 penetrant test panel. (i) Leave the penetrant in contact with the components for 30 minutes.
NOTE : The penetrant contact time must not exceed one hour. If it does, the penetrant must be re-applied and 5 minutes contact time allowed. (j) Penetrant Removal - After the 30 minutes contact time, remove the excess penetrant from the inspection surface and the OMat 677 penetrant test panel by wiping thoroughly with a clean OMat 2/101 lint-free cloth.**Printed in Great Britain**



# RB.211−72−AG971 Page 11 Sep 20/12 Sep.27/13 R(k) Whilst illuminating with UV light, wipe off the penetrant with a clean OMat 2/101 lint-free cloth moistened with OMat 150 acetone. Use the minimum application necessary to achieve acceptable background fluorescence and make sure that acetone is not allowed to flow on the inspection surface. (l) Make sure that all traces of the OMat 150 acetone have been completely removed. (m) Develop - Apply a light, even coating of OMat 617 non-aqueous wet developer from a sealed aerosol can to the inspection area and the OMat 677 penetrant test panel. (n) Allow 10 minutes contact time for the developer prior to inspection. R (o) Cover the region of the engine with a dark non-reflective cover in order to reduce the white light levels. (p) Make sure there are no white light sources or fluorescent items (including clothing) within the inspection area or the inspector's field of vision. (q) Do not wear darkened or light sensitive glasses. (r) Allow one R minute for eye adaptation to the darkened area. (s) Illuminate the OMat 677 penetrant test panel in the darkened area R with one of the allowed R UV light sources listed in 1.H. Tooling Price and Availability. R R (t) Inspect the OMat 677 penetrant test panel and check that the four R largest indications are visible and match the control photograph for that individual panel. (u) Illuminate the inspection surface with the same R UV light in the darkened area. (v) Inspect the mount lug run-outs for crack indications. (w) The Wipe Off technique can be used to aid the evaluation of any indications: R (i) Dampen a cotton swab with acetone. R (ii) Wipe once across the indication. R (iii) Allow the acetone to evaporate and inspect immediately. R**Printed in Great Britain**



# RB.211−72−AG971 Page 12 Sep 20/12 Sep.27/13 R(iv) If the indication reappears then record it is a crack. If the indications does not reappear then apply a light, even coating of OMat 617 non-aqueous wet developer from a sealed aerosol can to the area. R R R R (v) Allow the solvent in the developer to evaporate and inspect immediately. R R (vi) If the indication reappears then record it as a crack. If the indication does not reappear then allow 10 minutes contact time for the developer. R R R (vii) If the indication reappears after the 10 minutes contact time then record it as a crack. If the indication does not reappear then that area is acceptable. R R R (x) The cause of all indications must be evaluated under white light using visual aids, such as magnification, as appropriate. (y) Photograph any suspected crack indications and record them in Appendix 1. R R (z) No cracks detected - Accept Any cracks detected - Reject (aa) Post Clean - Once all indications have been evaluated and recorded, remove the penetrant processing materials from the inspection surface by wiping with a clean OMat 2/101, lint-free cloth moistened with OMat 150 acetone. (ab) Restore the OMat 677 penetrant test panels to a completely clean condition and make sure there is no residual fluorescence. R R (2) Inspect the fail safe catcher for signs of contact. R (a) Visually inspect the LE face of the fail safe catcher (see Fig.3.). R (b) Inspect in accordance with CIR: 72-52-51-200-801, Examine the LP Turbine Exhaust, Subtask, 72-52-51-210-110, Examine the LP Turbine Mounting Lug at location 10. R R R**Printed in Great Britain**



# RB.211−72−AG971 Page 13 Sep 20/12 Sep.27/13 R(c) If Scored, galled, fretted or dented on the center lug (fail safe lug) front surface: R R (i) Not more than 8,00 mm in width and 1,00 mm in depth, if the minimum cross section area (Area A, See Fig.4.) of the mount lug is more than 1155 sqmm after repair. R R R R R R R REPAIR, FRS3253 R

(ii) More than in (i) R REJECT R (d) Photograph any damage and note location of the damage on the fail safe catcher. See Fig.3. for an example of typical damage. R R (3) Accomplishment of this Non-Modification Service Bulletin should be recorded in the engine log book. C. In-shop - Top Core Vanes and Mount Lug Run-outs Inspection through Full FPI of the TBH (1) Carry out the inspection on the Top Core Vanes (TCV) and mount lug run-outs. (a) Remove the tail bearing housing in accordance with Engine Data Task 72-52-00-030-802, Disassemble the LP Turbine. (b) Disassemble the TBH in accordance with Engine Data Task 72-52-50-040-801, Disassemble the LP Turbine Bearing Housing (TBH) Support and Exhaust Case. R R R (c) Clean the TBH in accordance with Overhaul Process 134, Acidic Descalers, Subtask 70-00-00-110-134-002: R R (i) In accordance with Subtask 70-00-00-110-134-002, Degrease the part in accordance with Overhaul Process 102, Primary Cleaning Aqueous. R R R (ii) In accordance with Subtask 70-00-00-110-134-002, perform the optional Alkali Derust in accordance with Overhaul Process 121, Alkaline Derusting and Descaling, Subtask 70-00-00-110-121-001. R R R (iii) In accordance with remainder of Subtask 70-00-00-110-134-002, perform the Acidic Descale (step 1), Scale Condition Acidic Descale (step 2). R R R (d) Carry out a full FPI crack test in line with Cleaning/Inspection and Repair Data Task 72-52-51-200-801, Subtask 72-52-51-230-023. Use a high sensitivity penetrant as R R the minimum sensitivity.**Printed in Great Britain**



# RB.211−72−AG971 Page 14 Sep 20/12 Sep.27/13 R(e) Inspect the entire TBH for crack indications, including the R areas for the mount lug run-outs highlighted in Fig.1 and the areas of the TCV R highlighted in Fig.2. R (f) Record inspection results and any crack indications in Appendix 1. (g) No cracks detected - Accept Any cracks detected - Reject (2) Inspect the fail safe catcher for signs of contact. R (a) Visually inspect the LE face of the fail safe catcher (see Fig.3.). R (b) Inspect in accordance with CIR: 72-52-51-200-801, Examine the LP Turbine Exhaust, Subtask, 72-52-51-210-110, Examine the LP Turbine Mounting Lug at location 10. R R R (c) If Scored, galled, fretted or dented on the center lug (fail safe lug) front surface: R R (i) Not more than 8,00 mm in width and 1,00 mm in depth, if the minimum cross section area (Area A, See Fig.4.) of the mount lug is more than 1155 sqmm after repair. R R R R R R R REPAIR, FRS3253 R

(ii) More than in (i) R REJECT R (d) Photograph any damage and note location of the damage on the fail safe catcher. See Fig.3. for an example of typical damage. R R (3) Accomplishment of this Non-Modification Service Bulletin should be recorded in the engine log book.**Printed in Great Britain**



# RB.211−72−AG971 Page 15 Sep 20/12 Sep.27/13 Rdeh0013070 

## A



## A **B**

**B C** 

5.0 mm (0.20 in) 

## B 250.0 mm (9.80 in) INSPECTION AREAS THE CURVED FACES IN THESE TWO POSITIONS ON EACH SIDE OF THE ENGINE MUST BE INSPECTED IN ADDITION APPROXIMATELY

5.0mm (0.20 in) COVERAGE

IS REQUIRED AROUND THE CORNERS

Mount Lug Run Outs - Inspection Areas Fig.1**Printed in Great Britain**



# RB.211−72−AG971 Page 16 Sep 20/12 Sep.27/13 Rdeh001307 1 TOP CORE VANES



## C REQUIRING INSPECTION

Top Core Vanes Requiring Inspection Fig.2**Printed in Great Britain**



# RB.211−72−AG971 Page 17 Sep 20/12 Sep.27/13 R

## A

deh0014279 

## A **B**

30.0 mm

FAIL SAFE CATCHER DAMAGE FAIL SAFE CATCHER DAMAGE 

## B INSPECT LE FACE OF FAIL SAFE CATCHER

(1.181 in) 30.0 mm (1.181 in) R

In-shop Fail Safe Catcher Inspection Locations R Fig.3 R**Printed in Great Britain**



# RB.211−72−AG971 Page 18 Sep 20/12 Sep.27/13 RR

Repair Acceptance Criteria R Fig.4 R**Printed in Great Britain**



# RB.211−72−AG971 Page 19 Sep 20/12 Sep.27/13 RThis form (or similar) is to be completed for every component. Results and photographs R R to be sent to Rolls-Royce via your Service Representative.

Feedback Sheet NMSB 72-AG971 Overhaul Base Operator Engine Mark Date of Inspection Engine Serial Number Engine Hours Since New Engine Cycles Since New 08 Module Serial Number

08 Module Hours Since new

08 Module Cycles Since New Component Part Number / Component R Serial Number Component Hours Since New / Component Cycles Since New R R Inspection Result and Comments On-wing Inspection of Mount Lug Run-outs (if applicable)

In-shop Inspection of Mount Lug Run-outs (if applicable)

In-shop Inspection of Top Core Vanes (if applicable)

In-shop Inspection of Fail Safe Catcher (if applicable) R R

Any other finding during In-shop Inspection (Full FPI) R R APPENDIX 1**Printed in Great Britain**



# RB.211−72−AG971 Appendix 1 - Page 1 of 1 Sep 20/12 Sep.27/13 R