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 Sep.11/12 R 2 1 Sep.11/12 R 3 1 Sep.11/12 R 4 1 Sep.11/12 R 5 1 Sep.11/12 R 6 1 Sep.11/12 R 7 1 Sep.11/12 R 8 1 Sep.11/12 R 9 1 Sep.11/12 R 10 1 Sep.11/12 R 11 1 Sep.11/12 R 12 1 Sep.11/12 R 13 1 Sep.11/12 R 14 1 Sep.11/12 R 15 1 Sep.11/12 R 16 1 Sep.11/12 R 17 1 Sep.11/12 R 18 1 Sep.11/12 R 19 1 Sep.11/12 R 20 1 Sep.11/12**Printed in Great Britain**



# RB.211−72−AH051 Transmittal - Page 21. Planning Information A. Effectivity Airbus A380 RB211 TRENT 970-84 and TRENT 972-84 Engine Serial Numbers 91021, 91024, 91025, 91066, 91070, 91094, 91095, 91107, 91115, 91119, 91131, 91144, 91160, 91165, 91167, 91182, 91190, 91197, 91198, 91199, 91201, 91206, 91211, 91212, 91214 ,91221, 91227, 91270, 91280 and 91287
B. Reason (1) Problem Engineering investigation following an in service event has determined that omission at original engine build of a spherical seat EIPC Ref. 72-55-11, 01-148 (P/N CU38971) caused fracture of the oil transfer tube 72-55-11, 01-151 (P/N FK14432) leading to reduced oil flow and subsequent damage to the LP and IP bearings. Contributing factors to the most likely cause of incorrect assembly have been determined and corrective actions have been taken. A subsequent review has determined that the Trent 900 engines listed in 1.A. Effectivity may have been exposed to similar omission of the spherical seat during original assembly. C. Description This Non-Modification Service Bulletin (NMSB) is issued to identify potentially affected engines by serial number and to instruct a means to confirm by visual inspection that the spherical seat is installed correctly. A flexible borescope technique is utilised to view the oil transfer tube and spherical seat inside the LPT bearing housing via an oil scavenge tube connection. This NMSB supersedes on expiration Technical Variance (TV) 125436 which was raised to cover initial inspections to the intent of this NMSB. Therefore, accomplishment of TV 125436 satisfies the requirements of this NMSB. Revision 1 issued to correct part number reference in paragraphs 3.A.(7) and 3.B.(9)(b). R R Inform your Rolls-Royce Service Representative of Non-Modification Service Bulletin accomplishment. R ENGINE - LP TURBINE SHAFT AND BEARING HOUSING END COVER - INSPECTION TO CONFIRM THAT THE SPHERICAL SEAT IS FITTED - NON-MODIFICATION SERVICE BULLETIN - NON - MOD.72-AH051**Printed in Great Britain**



# RB.211−72−AH051 Page 1 of 20 Aug 3/12 Sep.11/12 RD. Compliance
ALERT This NMSB is anticipated to be the subject of an EASA Airworthiness Directive. (1) On-wing Carry out visual inspection in accordance with 3. Accomplishment Instructions Part A or Part B within 20 engine cycles effective from date of issue of this NMSB. (2) In-shop Carry out visual inspection in accordance with 3. Accomplishment Instructions Part C prior to engine dispatch. Accomplishment of TV 125436 can be accepted as an alternative means of compliance to the action stated in step (1) or (2) above. E. Approval The technical content of this Non-Modification Service Bulletin was approved under the authority of Design Organisation Approval EASA.21J.035 on Aug.3/12 and was re-approved on Sep.10/12. R R F. Manpower (1) Time to gain access 0.5 man hours (1 person) (2) Time to inspect 0.5 man hours (1 person) (3) Time to restore to serviceable condition 0.5 man hours (1 person)
NOTE : Low power engine running (idle) will be required as part of the Fuel and Oil Leak Test G. Material Price and Availability The following expendable parts may be required.

EIPC Ref. Part Number Part Name Qty**Printed in Great Britain**



# RB.211−72−AH051 Page 2 Aug 3/12 Sep.11/12 R72-55-11, 01-103 AS43013-172 Sealing ring 1 off
72-55-11, 01-109 AS43013-019 Sealing ring 1 off
H. Tooling Price and Availability Flexible borescope (4mm) I. References (1) Aircraft Maintenance Manual: (a) 24-41-00-861-801, Energize the Aircraft Electrical Circuits (b) 24-71-00-860-801, Get Access to the Power Distribution Control Management Pages and to the Mechanical Circuit Breakers (c) 71-00-00-700-822-A, Conduct Fuel and Oil Leak Test (d) 71-13-00-010-801, Opening of the Fan Cowl Doors (e) 71-13-00-410-801, Closing of the Fan Cowl Doors (f) 78-11-42-400-803-A, Installation of the Forward Exhaust Plug (g) 78-11-42-000-803-A, Removal of the Forward Exhaust Plug (h) 78-11-42-400-804-A, Installation of the Aft Exhaust Plug (i) 78-11-42-000-804-A, Removal of the Aft Exhaust Plug (j) 78-26-00-010-801, Opening of the Fan Exhaust Cowl or Thrust Reverser (k) 78-26-00-010-801, Closing of the Fan Exhaust Cowl or Thrust Reverser (l) 78-30-00-040-801, Make the Thrust Reverser Unserviceable for Maintenance (2) Engine Manual: (a) 72-00-13-800-803, Clip Position Data (CP-210200 to CP-210299) (b) 72-55-11, LP Turbine Shaft and Bearing Housing End Cover (c) 72-55-11-040-801, Remove the LP Turbine Bearing Housing End Cover (d) 72-55-11-440-801, Install the LP Turbine Bearing Housing End Cover**Printed in Great Britain**



# RB.211−72−AH051 Page 3 Aug 3/12 Sep.11/12 R(3) Technical Variance, 125436**Printed in Great Britain**



# RB.211−72−AH051 Page 4 Aug 3/12 Sep.11/12 R2. Material Information
A. None**Printed in Great Britain**



# RB.211−72−AH051 Page 5 Aug 3/12 Sep.11/12 R3. Accomplishment Instructions A. On-wing - Procedure for Borescope Inspection of the Spherical Retaining Seat (P/N CU38971).

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.
CAUTION : DO NOT START THE BORESCOPE INSPECTION UNTIL THE ENGINE HAS COOLED TO WITHIN THE BORESCOPE MANUFACTURERS RECOMMENDATIONS. THE ENGINE IS HOT IMMEDIATELY AFTER THE ENGINE IS STOPPED AND CAN CAUSE BURNS AND DAMAGE TO BORESCOPE INSPECTION EQUIPMENT. (1) Energise the aircraft electrical circuits in accordance with AMM Task 24-41-00, Maintenance Practices. (2) On the OMS home page, select Power Distribution Control or C/B Management in accordance with AMM Task 24-71-00, Maintenance Practices. (3) Open, safety/lock and tag the below circuit breaker(s):
PANEL DESIGNATION FIN LOCATION For FIN 4000 EM1 (Engine-1) SEPDC2 FADEC B ENG1 802KS1 SSPC 2500VU FADEC A ENG1 12KS1 0961 For FIN 4000 EM2 (Engine-2) SEPDC1 FADEC B ENG2 803KS1 SSPC 2500VU FADEC A ENG2 12KS2 1063 For FIN 4000 EM3 (Engine-3) SEPDC2 FADEC B ENG3 802KS2 SSPC 2500VU FADEC A ENG3 12KS2 SSPC For FIN 4000 EM4 (Engine-4) SEPDC1 FADEC B ENG4 803KS2 SSPC 2500VU FADEC A ENG4 12KS4 0962**Printed in Great Britain**



# RB.211−72−AH051 Page 6 Aug 3/12 Sep.11/12 R(4) Get access: (a) Put an access platform in position:
WARNING : YOU MUST DEACTIVATE THE THRUST REVERSER BEFORE YOU DO WORK ON OR AROUND IT. IF YOU DO NOT, THE THRUST REVERSER CAN OPERATE ACCIDENTALLY AND CAUSE AN INJURY AND/OR DAMAGE. (b) If you do the procedure on an inboard engine, do the deactivation of the thrust reverser. Refer to AMM 78-30-00, Deactivation/Activation. (c) Open the fan cowl doors in accordance with AMM 71-13-00, Maintenance Practices. (d) Open the fan exhaust cowls in accordance with AMM 78-26-00, Maintenance Practices. (5) Identify and remove the clip position 210250 on the LP turbine exhaust case and retain the parts. Refer to Fig.1. (6) Remove oil tube (P/N FW30495). Refer to Fig.1
CAUTION : YOU MUST HOLD THE TUBE(S) WHEN YOU LOOSEN/TIGHTEN THE CONNECTIONS. MAKE SURE THAT THE TUBE(S) CANNOT TWIST. DAMAGE TO THE TUBE(S) CAN OCCUR IF THEY DO TWIST. (7) Insert a flexible borescope (4mm) through the 0,5 in.(12.7mm) diameter oil tube on the LPT exhaust case and into the cavity to view the position where the oil transfer tube (P/N FK14432) R is attached to the LPT bearing housing end cover (P/N FW22780), see Fig.2 and Fig.3. Confirm through visual inspection that the spherical seat (P/N CU38971) is fitted between the oil transfer tube and the end cover secured by the four bolts (P/N AS48513)) and four washers (P/N AS12944), see Fig.3 and Fig.4. (8) Accept / Reject Criteria (a) If the assembly conforms to the detail in Fig.4 and the spherical seat (P/N CU38971) is fitted then no further work is necessary. Record findings and proceed from step (9). (b) If the assembly does not conform to the detail in Fig.4 or spherical seat (P/N CU38971) cannot be confirmed as fitted then remove the LP turbine bearing housing end cover (P/N FW22780) for inspection in accordance with Section 3.B. (9) Remove the borescope equipment from the engine.**Printed in Great Britain**



# RB.211−72−AH051 Page 7 Aug 3/12 Sep.11/12 R(10) Refit the oil tube (P/N FW30495). Refer to Fig.1
CAUTION : YOU MUST HOLD THE TUBE(S) WHEN YOU LOOSEN OR TIGHTEN THE CONNECTIONS. MAKE SURE THE TUBE(S) CANNOT TWIST. DAMAGE CAN OCCUR IF THE TUBE(S) DO TWIST. (a) Reinstall the tube to the LP turbine exhaust case. (b) Refit the clip position 210250. (c) Torque the clip point bolt to 4,5 Nm (40 lbfin) (d) Re-install the connections of tube (P/N FW30495). (e) Torque the nut on the tube (P/N FW30495) that connects the LP turbine exhaust case to 43,0 Nm (380 lbfin). (f) Torque the nut on the tube (P/N FW30495) that connects the two way adapter union to 43,0 Nm (380 lbfin). (11) Close access: (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 Task 78-26-00, Maintenance Practices (c) Close the fan cowl doors in accordance with AMM Task 71-13-00, Maintenance Practices (d) Remove all the fixtures, tools, test and support equipment used during this procedure. (12) Remove the tag(s) and/or the safety clip-circuit breaker and close/unlock these circuit breaker(s):
PANEL DESIGNATION FIN LOCATION For FIN 4000 EM1 (Engine-1) SEPDC2 FADEC B ENG1 802KS1 SSPC 2500VU FADEC A ENG1 12KS1 0961 For FIN 4000 EM2 (Engine-2) SEPDC1 FADEC B ENG2 803KS1 SSPC 2500VU FADEC A ENG2 12KS2 1063 For FIN 4000 EM3 (Engine-3) SEPDC2 FADEC B ENG3 802KS2 SSPC 2500VU FADEC A ENG3 12KS2 SSPC For FIN 4000 EM4 (Engine-4) SEPDC1 FADEC B ENG4 803KS2 SSPC 2500VU FADEC A ENG4 12KS4 0962**Printed in Great Britain**



# RB.211−72−AH051 Page 8 Aug 3/12 Sep.11/12 R(13) Conduct Fuel and Oil Leak Test in accordance with AMM Task 71-00-00-700-822-A. (14) Accomplishment of this Non-Modification Service Bulletin should be recorded in accordance with local SB tracking system procedures B. On-wing - Removal and Installation of the LPT Bearing Housing End Cover

NOTE : Use this procedure as an alternative to the borescope inspection detailed in Section 3.A or where inspection in accordance with Section 3.A has been unable to confirm that the spherical seat (P/N CU38971) is fitted. The following expendable parts are required to be fitted.

EIPC Ref. Part Number Part Name Qty
72-55-11, 01-103 AS43013-172 Sealing ring 1 off
72-55-11, 01-109 AS43013-019 Sealing ring 1 off

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. (1) Energise the aircraft electrical circuits in accordance with AMM Task 24-41-00, Maintenance Practices. (2) On the OMS home page, select Power Distribution Control or C/B Management in accordance with AMM Task 24-71-00, Maintenance Practices.**Printed in Great Britain**



# RB.211−72−AH051 Page 9 Aug 3/12 Sep.11/12 R(3) Open, safety/lock and tag the below circuit breaker(s):
PANEL DESIGNATION FIN LOCATION For FIN 4000 EM1 (Engine-1) SEPDC2 FADEC B ENG1 802KS1 SSPC 2500VU FADEC A ENG1 12KS1 0961 For FIN 4000 EM2 (Engine-2) SEPDC1 FADEC B ENG2 803KS1 SSPC 2500VU FADEC A ENG2 12KS2 1063 For FIN 4000 EM3 (Engine-3) SEPDC2 FADEC B ENG3 802KS2 SSPC 2500VU FADEC A ENG3 12KS2 SSPC For FIN 4000 EM4 (Engine-4) SEPDC1 FADEC B ENG4 803KS2 SSPC 2500VU FADEC A ENG4 12KS4 0962 (4) Get access: (a) Put an access platform in position:
WARNING : YOU MUST DEACTIVATE THE THRUST REVERSER BEFORE YOU DO WORK ON OR AROUND IT. IF YOU DO NOT, THE THRUST REVERSER CAN OPERATE ACCIDENTALLY AND CAUSE AN INJURY AND/OR DAMAGE. (b) If you do the procedure on an inboard engine, do the deactivation of the thrust reverser. Refer to AMM 78-30-00, Deactivation/Activation. (c) Remove the aft exhaust plug in accordance with AMM Task 78-11-42-000-804-A. (d) Remove the forward exhaust plug in accordance with AMM Task 78-11-42-000-803-A. (5) Remove the end cover thermal insulating blanket (P/N FW30195) (retain for re-installation) Refer to Fig.5. (a) Remove the lockwire from the lacing tags that attach the end cover thermal insulating blanket (P/N FW30195) to the insulating blanket (P/N FW25645), LH lower insulating blanket (P/N FW25646) and the RH lower insulating blanket (P/N FW25644). (b) Remove the end cover thermal insulating blanket (P/N FW30195). (6) Remove the end cover (P/N FW22780), see Fig.3. (a) Remove the nine bolts (P/N AS48510) that attach the rear cover (P/N FW22780) to the LP turbine bearing support hub. (b) Remove the end cover (P/N FW22780) from the LP turbine bearing support hub.**Printed in Great Britain**



# RB.211−72−AH051 Page 10 Aug 3/12 Sep.11/12 R(c) Remove and discard the sealing rings (P/N AS43013-172) and (P/N AS43013-019) from the rear cover. (7) Visually inspect where the oil transfer tube (P/N FK14432) is attached to the LPT bearing housing end cover. Confirm through visual inspection that the spherical seat (P/N CU38971) is fitted between the oil transfer tube and the end cover secured by the four bolts (P/N AS48513) and four washers (P/N AS12944), see Fig.3 and Fig.4. (8) Accept/Reject Criteria (a) If the assembly conforms to the detail in Fig.4 and the spherical seat (P/N CU38971) is fitted then no further work is necessary. Record findings and proceed from step (9). (b) If the assembly does not conform to the detail in Fig.4 or spherical seat (P/N CU38971) cannot be confirmed as fitted then the whole LP turbine bearing housing end cover assembly (P/N FW22780 and P/N FK14432) must be replaced. Make sure that replacement parts meet the criteria of step (7). (9) Install the rear cover (P/N FW22780), spherical seat component (P/N CU38971) and the oil transfer tube (P/N FK14432) as an assembly, see Fig.4. (a) Install the new sealing ring (P/N AS43013-172) on the rear cover (P/N FW22780). (b) Install the new sealing ring (P/N AS43013-019) R on the rear cover (P/N FW22780).
CAUTION : CARE NEEDS TO BE TAKEN WHEN INSTALLING THE REAR COVER THAT THE SEALING RINGS ARE NOT PINCHED ON ASSEMBLY (c) Attach the rear cover to the LP turbine bearing support hub with nine bolts (P/N AS48510). Make sure that the shouldered pin (P/N AS44800) is aligned. (d) Torque the nine bolts (P/N AS48510) to 11,5 Nm (100 lbfin). (10) Install the end cover, thermal insulating blanket (P/N FW30195), see Fig.5. (a) Install the end cover thermal insulating blanket (P/N FW30195) on the rear cover (P/N FW22780). (i) Put the end cover thermal insulating blanket in position on the rear cover. Make sure the lacing tags of the end cover thermal insulating blanket align with the lacing tags of the other insulating blankets.**Printed in Great Britain**



# RB.211−72−AH051 Page 11 Aug 3/12 Sep.11/12 R(ii) Use OMat 238 lockwire to attach the end cover thermal insulating blanket to the insulating blanket (P/N FW25645), the LH lower insulating blanket (P/N FW25646) and the RH lower insulating blanket (P/N FW25644). (iii) Safety the folded ends of the lockwire below the lacing tags. (11) Close access: (a) Make sure the work area is clean and clear of tools and other items. (b) Refit the forward exhaust plug in accordance with AMM Task 78-11-42-400-803-A. (c) Refit the aft exhaust plug in accordance with AMM Task 78-11-42-400-804-A. (12) Remove the tag(s) and/or the safety clip-circuit breaker and close/unlock these circuit breaker(s):
PANEL DESIGNATION FIN LOCATION For FIN 4000 EM1 (Engine-1) SEPDC2 FADEC B ENG1 802KS1 SSPC 2500VU FADEC A ENG1 12KS1 0961 For FIN 4000 EM2 (Engine-2) SEPDC1 FADEC B ENG2 803KS1 SSPC 2500VU FADEC A ENG2 12KS2 1063 For FIN 4000 EM3 (Engine-3) SEPDC2 FADEC B ENG3 802KS2 SSPC 2500VU FADEC A ENG3 12KS2 SSPC For FIN 4000 EM4 (Engine-4) SEPDC1 FADEC B ENG4 803KS2 SSPC 2500VU FADEC A ENG4 12KS4 0962 (13) Conduct Fuel and Oil Leak Test in accordance with AMM Task 71-00-00-700-822-A. (14) Accomplishment of this Non-Modification Service Bulletin should be recorded in accordance with local SB tracking system procedures. C. In-shop - Procedure for Inspection of the Spherical Seat (EIPC Ref. 72-55-11, 01-148).

NOTE : This procedure provides instructions to confirm by visual inspection on an assembled engine utilising borescope equipment that the spherical seat (EIPC Ref. 72-55-11, 01-148) is fitted correctly. Any alternative visual inspection by component disassembly is an acceptable alternative to this procedure.**Printed in Great Britain**



# RB.211−72−AH051 Page 12 Aug 3/12 Sep.11/12 R(1) Remove oil scavenge tube (EIPC Ref. 79-22-49, 05-500). Refer to Fig.1
CAUTION : YOU MUST HOLD THE TUBE(S) WHEN YOU LOOSEN/TIGHTEN THE CONNECTIONS. MAKE SURE THAT THE TUBE(S) CANNOT TWIST. DAMAGE TO THE TUBE(S) CAN OCCUR IF THEY DO TWIST. (a) Disassemble the clip position 210250. Refer to Fig.1. (b) Release the tube nut that attaches the tube to the LP turbine exhaust case (EIPC Ref. 72-52-51, 03-300). (c) Remove the oil scavenge tube. (2) Insert a flexible borescope (4mm) through the 0,5 in.(12.7mm) diameter oil tube on the LPT exhaust case and into the cavity to view the position where the oil transfer tube (EIPC Ref. 72-55-11, 01-151) is attached to the LPT bearing housing end cover (EIPC Ref. 72-55-11, 01-100), see Fig.2 and Fig.3. Confirm through visual inspection that the spherical seat (EIPC Ref. 72-55-11, 01-148) is fitted between the oil transfer tube and the end cover secured by the four bolts (EIPC Ref. 72-55-11, 01-149) and four washers (EIPC Ref. 72-55-11, 01-150), see Fig.3 and Fig.4. (3) Accept / Reject Criteria (a) If the assembly conforms to the detail in Fig.4 and the spherical seat (EIPC Ref. 72-55-11, 01-148) is fitted then no further work is necessary. Record findings and proceed from step (4). (b) If the assembly does not conform to the detail in Fig.4 or spherical seat (EIPC Ref. 72-55-11, 01-148) cannot be confirmed as fitted then remove the LP turbine bearing housing end cover for inspection in accordance with Engine Manual Task 72-55-11-040-801. (i) Remove the end cover thermal insulating blanket in accordance with Engine Manual Task 72-55-11-020-022. (ii) Remove the rear cover in accordance with Engine Manual Task 72-55-11-020-023. (iii) At this stage visually inspect where the oil transfer tube is attached to the LPT bearing housing end cover. Confirm that the spherical seat (EIPC Ref. 72-55-11, 01-148) is fitted between the oil transfer tube and the end cover, see Fig.3 and Fig.4. (iv) If the assembly conforms to the detail in Fig.4 and the spherical seat (EIPC Ref. 72-55-11, 01-148) is fitted then no further work is necessary. Record findings and proceed from step (4).**Printed in Great Britain**



# RB.211−72−AH051 Page 13 Aug 3/12 Sep.11/12 R(v) If the assembly does not conform to the detail in Fig.4 or spherical seat (EIPC Ref. 72-55-11, 01-148) is not fitted then replace the whole LP turbine bearing housing end cover assembly. Make sure replacement parts satisfy the requirements of step (3). (c) Install the LP turbine bearing housing end cover in accordance with Engine Manual 72-55-11-440-801. (i) Install the rear cover in accordance with Engine Manual 72-55-11-440-004. (ii) Install the end cover thermal insulating blanket in accordance with Engine Manual 72-55-11-440-005. (4) Remove the borescope equipment from the engine. (5) Refit the oil scavenge tube (EIPC Ref. 79-22-49, 05-500). Refer to Fig.1.
CAUTION : YOU MUST HOLD THE TUBE(S) WHEN YOU LOOSEN/TIGHTEN THE CONNECTIONS. MAKE SURE THAT THE TUBE(S) CANNOT TWIST. DAMAGE TO THE TUBE(S) CAN OCCUR IF THEY DO TWIST. (a) Attach the tube to the LP turbine exhaust case (EIPC Ref. 72-52-51, 03-300). (b) Assemble the clip position 210250 in accordance with the Engine Manual Task 72-00-13-800-803. (c) Torque the bolt to 4,5 Nm (40 lbfin). (6) 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−AH051 Page 14 Aug 3/12 Sep.11/12 Rdeh0013077 TUBE 

## A

**B** FW30495 79−22−49

05−500 210250

LP TURBINE EXHAUST CASE 

## B
TUBE FW30495 79−22−49

05−500 

## A

LP Turbine Exhaust Case and Oil Tube Removal for Access Fig.1 (sheet 1 of 2)**Printed in Great Britain**



# RB.211−72−AH051 Page 15 Aug 3/12 Sep.11/12 RAS48425 79−22−49

05−525

K8831 79−22−49

05−526

AS41104 79−22−49

05−532 CLIP POSITION 210250

deh0013078 UP10482 79−22−49

05−530

FW25454 72−52−00

02−210 UP12010 79−22−49

05−528 UP12010 26−12−17

02−168 904656−10 26−12−17

02−100

LK39520 26−12−17

05−612

FW30495 79−22−49

05−500 BOLT

WASHER

CLIP NUT SPACER

BRACKET CLIP CLIP TUBE

SLEEVE

TUBE

Clip Position 210250 Fig.1 (sheet 2 of 2)**Printed in Great Britain**



# RB.211−72−AH051 Page 16 Aug 3/12 Sep.11/12 Rdeh0013079 MODULE 52 

## A



## A BORESCOPE USING 4mm INTRASCOPE SPHERICAL SEAT CU38971 72−55−11

01−148 COMPONENT 

## B

LP Turbine Bearing Housing Arrangement Fig.2**Printed in Great Britain**



# RB.211−72−AH051 Page 17 Aug 3/12 Sep.11/12 RLP Turbine Bearing Cover Plate Arrangement Fig.3**Printed in Great Britain**



# RB.211−72−AH051 Page 18 Aug 3/12 Sep.11/12 RSpherical Seat Installed Arrangement Fig.4**Printed in Great Britain**



# RB.211−72−AH051 Page 19 Aug 3/12 Sep.11/12 Rdeh001308 4 

## B

B



## B LACING TAG 

## B

LH LOWER INSULATING

BLANKET FW25646 RH LOWER INSULATING

BLANKET FW25644 INSULATING

BLANKET FW25645

END COVER THERMAL FW30195 72−55−11

01−090 END COVER THERMAL INSULATING BLANKET FW30195 01−090

72−52−52 72−52−52

01−497 01−498 RH LOWER INSULATING

BLANKET FW25644 72−52−52

01−498 INSULATING BLANKET LH LOWER INSULATING

BLANKET FW25646 72−52−52

01−497 72−55−11 72−52−52

01−496

LP Turbine Cover Plate Insulation Blanket Arrangement Fig.5**Printed in Great Britain**



# RB.211−72−AH051 Page 20 Aug 3/12 Sep.11/12 R