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 2
1. 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

R Bulletin accomplishment.

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

R Sep.11/12
D. 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

R Sep.11/12
72-55-11, 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

R Sep.11/12
(3) Technical Variance, 125436

Printed in Great Britain

RB.211−72−AH051

Page 4

Aug 3/12

R Sep.11/12
2. Material Information

A. None

Printed in Great Britain

RB.211−72−AH051

Page 5

Aug 3/12

R Sep.11/12
3. 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

R Sep.11/12
(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

R is attached to the LPT bearing where the oil transfer tube (P/N FK14432)

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

R Sep.11/12
(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

R Sep.11/12
(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

R Sep.11/12
(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

R Sep.11/12
(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).

R (b) Install the new sealing ring (P/N AS43013-019) 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

R Sep.11/12
(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

R Sep.11/12
(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

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(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

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deh0013077

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

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AS48425

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

R Sep.11/12
deh0013079

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

R Sep.11/12
LP Turbine Bearing Cover Plate Arrangement

Fig.3

Printed in Great Britain

RB.211−72−AH051

Page 18

Aug 3/12

R Sep.11/12
Spherical Seat Installed Arrangement

Fig.4

Printed in Great Britain

RB.211−72−AH051

Page 19

Aug 3/12

R Sep.11/12
deh0013084

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

R Sep.11/12