This document transmits the Initial Issue of Service Bulletin RB211-72-J024 and

the Initial Issue of the Supplement

Bulletin Initial Issue

Remove Incorporate Reason for change

Pages 1 to 22 of the

Service Bulletin

Initial Issue

Supplement Initial Issue

Remove Incorporate Reason for change

Page 1 Initial Issue

Printed in Great Britain

Mar. 1/16

RB211 TRENT 900 SERIES PROPULSION SYSTEMS SERVICE BULLETIN

RB.211−72−J024

Transmittal - Page 1 of 2

Date
LIST OF EFFECTIVE PAGES

The effective pages to this Service Bulletin are as follows:

Page Revision Number Revision Date

Bulletin

1 Mar.1/16

2 Mar.1/16

3 Mar.1/16

4 Mar.1/16

5 Mar.1/16

6 Mar.1/16

7 Mar.1/16

8 Mar.1/16

9 Mar.1/16

10 Mar.1/16

11 Mar.1/16

12 Mar.1/16

13 Mar.1/16

14 Mar.1/16

15 Mar.1/16

16 Mar.1/16

17 Mar.1/16

18 Mar.1/16

19 Mar.1/16

20 Mar.1/16

21 Mar.1/16

22 Mar.1/16

Supplement

1 Mar.1/16

Printed in Great Britain

RB.211−72−J024

Transmittal - Page 2
1. Planning Information

A. Effectivity

Airbus A380

RB211 TRENT970-84 Engines

RB211 TRENT972-84 Engines

RB211 SE100006, SE100444, SE100560, SE100562, SE100563, SE100577, SE100578,

SE100767, SE100768, SE100802, SE100803, SE100804, SE100828, SE100829, SE100830,

SE100831, SE100832, SE100885, SE100886, SE100887, SE100888, SE100889, SE100897,

SE100898, SE100899, SE100900, SE100904, SE100905, SE100906, SE100907, SE100909,

SE100910, SE100924, SE100925 Core Engines

RB211 M08100014, M08100443, M08100911 Modules 52 (08)

B. Concurrent Requirements

None.

C. Reason

(1) Problem and Evidence

Premature fatigue cracking, on a number of LP Turbine Exhaust Case and

Support Assemblies at vanes 1 and 14 leading edge fillets, have been

observed during in-service fluorescent penetrant inspections.

This is attributed to high thermal peak stress at initial ramps during the

flight cycle.

(2) Substantiation

The changes introduced by this Service Bulletin have been the subject of

satisfactory engineering evaluation, including stress and thermal

analysis.

(3) Objective

Incorporation of this Service Bulletin (Modification) is designed to

maintain reliability.

ENGINE - EXHAUST CASE - INTRODUCTION OF LP TURBINE EXHAUST CASE AND SUPPORT

ASSEMBLIES ACCOMPLISHED BY REWORK OF EXISTING ASSEMBLIES - MOD.72-J024

Printed in Great Britain

RB.211−72−J024

Page 1 of 22

Mar. 1/16

Mar. 1/16
(4) Effect of Bulletin on:

(a) Operation

Not affected

(b) Maintenance

Not affected

(c) Overhaul

Not affected

(d) Repair Schemes

Affected (Repairs will be revised to include the part(s) introduced by

this Service Bulletin)

(e) Interchangeability

Not affected

D. Description

(1) The changes are:

(a) Revised LP Turbine Exhaust Case and Support Assemblies are introduced

similar to the existing items except they are produced by reworking

existing assemblies by machining scallops at the leading edge fillets

of vanes 1 and 14.

(2) This Service Bulletin is in three parts as follows:

(a) Part 1

Rework of LP turbine exhaust case and support assembly to Service

Bulletin 72-F250 standard.

(b) Part 2

Rework of LP turbine exhaust case and support assembly to Service

Bulletin 72-E439 standard.

(c) Part 3

Rework of LP turbine exhaust case and support assembly to pre-Service

Bulletin 72-F250 standard.

Printed in Great Britain

RB.211−72−J024

Page 2

Mar. 1/16

Mar. 1/16
E. Compliance

(1) ON-WING

Not applicable

(2) IN-SHOP

OPTIONAL

This Service Bulletin introduces alternative and fully interchangeable

parts.

F. Approval

The technical content of Service Bulletin 72-J024 was approved by a

representative of the European Aviation Safety Agency (EASA) on Jul.2/15, EASA

certificate No.10053525.

The technical content under the JAR 25 regulation of this document is approved

under the authority of DOA ref. EASA.21J.031.

G. Manpower

(1) On-wing

Not applicable

(2) In-shop

12 hours

NOTE: The parts affected by this Service Bulletin are accessible on-wing

and in-shop.

H. Material Price and Availability

Modification kit not required; parts supplied as single line items.

For prices and availability of future spares see supplement to this bulletin.

I. Tooling Price and Availability

Special tools are not required.

J. Weight and Balance

(1) Weight change

None.

Printed in Great Britain

RB.211−72−J024

Page 3

Mar. 1/16

Mar. 1/16
(2) Moment arm

No effect.

(3) Datum

Power Plant Station (PPS) 100.

K. References

(1) This Service Bulletin is subject to aircraft Modification No 75499 T85479

(classified minor).

(2) Rolls-Royce Service Bulletins:

(a) 72-E439

Engine - Exhaust Case - Introduction of a revised tail bearing support

structure to flight test standard.

(b) 72-F250

Engine - Exhaust Case - Introduction of an LP turbine exhaust case and

support assembly with revised manufacturing methods.

(3) Rolls-Royce Non-Modification Service Bulletins:

72-AH154

Engine - LP Turbine Exhaust Case and Support Assembly (Tail Bearing

Housing) Mount Lug Forging Leading Edge Inspections - Non-Modification

Service Bulletin

(4) Engine Manual, 72-52-00, 72-52-50, Disassembly and Assembly

L. Other Publications Affected

For effect on Engine Illustrated Parts Catalogue (EIPC) refer to 2. Material

Information.

M. Interchangeability of Parts

Not affected.

Printed in Great Britain

RB.211−72−J024

Page 4

Mar. 1/16

Mar. 1/16
2. Material Information

A. The kit required consists of the following parts:

None.

B. Parts to be reworked:

All Engines, Core Engines and Modules

72-52-51

Part 1 of SB

FIG

ITEM

NO.

NEW

PART

NO.

QTY PART TITLE MAT OLD

PART

NO.

INSTR

DISP

03300 KH46678 1 Case, & support

assy of -

LP turbine exhaust

- FW51434 (1)

Part 2 of SB

FIG

ITEM

NO.

NEW

PART

NO.

QTY PART TITLE MAT OLD

PART

NO.

INSTR

DISP

03300 KH45090 1 Case, & support

assy of -

LP turbine exhaust

- FW27718 (1)

Part 3 of SB

FIG

ITEM

NO.

NEW

PART

NO.

QTY PART TITLE MAT OLD

PART

NO.

INSTR

DISP

03300 KH46677 1 Case, & support

assy of -

LP turbine exhaust

- FW35923 (1)

C. New production parts:

The following parts will be made available as future spares in addition to

those listed under B:

None.

Printed in Great Britain

RB.211−72−J024

Page 5

Mar. 1/16

Mar. 1/16
D. Instruction disposition codes:

(1) Two-Way Interchangeable. Old and new parts are fully interchangeable.

Printed in Great Britain

RB.211−72−J024

Page 6

Mar. 1/16

Mar. 1/16
3. Accomplishment Instructions

A. The revised LP turbine exhaust case and support assemblies introduced by this

Service Bulletin are interchangeable with the existing items (see 1.M.

Interchangeability of Parts). Remove and install in accordance with current

overhaul procedures (Engine Manual, 72-52-00, 72-52-50, Disassembly and

Assembly). Rework the LP turbine exhaust case and support assemblies in

accordance with Part B thru Part D of these Accomplishment Instructions.

B. This TASK gives the procedure to rework the Low Pressure (LP) Turbine Bearing

and Support Exhaust Case by machining the Vane Leading Edge at Vanes 1 and 14.

The reworked Low Pressure (LP) Turbine Bearing and Support Exhaust Case

introduced by this Service Bulletin is interchangeable with existing.

This TASK can be accomplished in the following circumstances:

A) When the engine is removed from the airframe but assembled and is located on

an engine build stand, or on a all purpose stand, or on a multi purpose stand or

on a gantry, accomplish in accordance with paragraph 3.C of these accomplishment

instructions.

B) When the component is at a piece part level and is located vertically in a

suitable stand with the engine mount lugs located at top dead centre, accomplish

in accordance with paragraph 3.D of these accomplishment instructions.

General Data

Source demonstration is necessary for this rework modification. Only those

personnel who hold Certificates of Competence and Valid Approval Documentation

from Rolls-Royce plc are authorised to do this rework modification. This source

controlled rework modification is classified as a fixed process document and must

be controlled as specified in RRES90000.

Material of components

PART IDENTIFICATION SYMBOL MATERIAL

Low Pressure (LP) Turbine Bearing

and Support Exhaust Case

RGB IN718

TASKS identified by OP TASK are in the Overhaul Processes Manual (TSD594-J).

TASKS identified by SPM TASK are in the Standard Practices Manual.

This TASK can only be applied one time on the Vane 1 and one time on the Vane 14.

This TASK is controlled by RPR52361.

Printed in Great Britain

RB.211−72−J024

Page 7

Mar. 1/16

Mar. 1/16
EQUIPMENT AND MATERIALS

Standard Equipment

degreasing equipment

hand tools

inspection equipment

penetrant crack test equipment

suction equipment

swab etch equipment

vibration peen equipment

Consumable Material

REFERENCE NAME

OMat 1249 polyethylene sheet

OMat 262 temporary marker

OMat 283B polyester masking tape

OMat 670 marker pen

OMat 632 fluorescent penetrant, high sensitivity

water washable

To identify the consumable materials refer to the Overhaul Materials Manual

(OMat)

Other necessary consumable materials are referred to in the OP TASKS in these

accomplishment instructions.

Special Tools

TOOL NUMBER TOOL DESCRIPTION QTY

HU45506 T900 TBH vane scallop kit 1 Off

This kit contains:

HU45500 T900 TBH vane inspection kit 1 Off

HU45501 T900 TBH vane polishing kit 1 Off

HU45502 T900 TBH vane machining kit 1 Off

HU45507 T900 TBH vane primary fixture kit 1 Off

Expendable Parts

FIG/ITEM PART NO PART IDENT QTY

None.

Re-work Parts

FIG/ITEM PART NO PART IDENT QTY

None.

Printed in Great Britain

RB.211−72−J024

Page 8

Mar. 1/16

Mar. 1/16
C. OFF-WING. Rework the Low Pressure (LP) Turbine Bearing and Support Exhaust Case

when the engine is removed from the airframe but is assembled.

(1) Clean the part. Locally clean the repair area. Refer

to OP TASK 70-00-00-100-101. Use swab

method.

Use degreasing equipment.

(2) Fluorescent Penetrant Inspect. Do a penetrant crack test on the Low

Pressure (LP) Turbine Bearing and

Support Exhaust Case vanes 1 and 14

in accordance with NMSB 72-AH154.

Refer to OP TASK 70-00-00-200-210.

If cracked refer to FRSH741.

If crack is not in the limits of

FRSH741 then refer to NMSB72-AH154

for acceptance criteria. Do not

complete this rework modification.

(3) Mask the Part Refer to Figure 1, Figure 2 and

Figure 3.

Mask the repair area between vane

number 11 and vane number 3 and the

rear edge of the LP turbine stage 5

blades. Use OMat 1249 polyethylene

sheet and OMat 283B polyester masking

tape.

(4) Set up the machining equipment. Refer to Figure 1, Figure 2 and

Figure 3.

Assemble the Tooling

Refer to HU45506 OMSD. Assemble

HU45507 and HU45502 to Vane 1 on the

Low Pressure (LP) Turbine Bearing and

Support Exhaust Case. Assemble the

flexible drive to Vane 13 and 14.

Make sure that the debris removal

system is installed.

Test the tooling. Refer to the OMSD.

Make sure the debris removal,

electric motor, cooling and tool

movement systems all function

correctly.

Printed in Great Britain

RB.211−72−J024

Page 9

Mar. 1/16

Mar. 1/16
(5) Machine Vane 1 Refer to Figure 1, Figure 2 and

Figure 3.

Machine the part.

Refer to vendor data cards. Run the

electric motor at 3000 rpm +/- 250

rpm. Cut for 3 sec +/- 1 sec per

contact of the cutting tool to the

Tail Bearing Housing. Machine vane 1

to the dimensions specified. Make

sure that the cutting tool is

supplied with adequate water coolant.

Make sure the cutting tool has a rest

period to remove debris using suction

equipment and cool the cutting tool

between contact periods with the

part.

(6) Remove the machining equipment. Refer to Figure 1, Figure 2 and

Figure 3.

Remove the Tooling

Refer to HU45506 OMSD. Remove HU45502

from Vane 1 on the Low Pressure (LP)

Turbine Bearing and Support Exhaust

Case. Remove the flexible drive from

Vane 13 and 14. Make sure that the

debris removal system is removed.

(7) Clean the part. Locally clean the repair area. Refer

to OP TASK 70-00-00-100-101. Use swab

method.

Use degreasing equipment.

(8) Break Sharp Edges on Vane 1 Refer to Figure 1, Figure 2 and

Figure 3.

Remove the sharp edges from the vane

machining.

Refer to vendor data cards. Use

HU45501 T900 TBH Vane Polishing Kit.

Break the sharp edges by using 120

grit Policap for 20 seconds per side

at 11000 rpm +/- 500rpm.

Printed in Great Britain

RB.211−72−J024

Page 10

Mar. 1/16

Mar. 1/16
(9) Polish Vane 1 Refer to Figure 1, Figure 2 and

Figure 3.

Polish Vane 1.

Refer to vendor data cards. Polish

vane 1 to create the surface finish

specified. Use HU45434 T900 TBH Vane

Polishing Kit. Polish the machined

surfaces by using 2 off 120 grit

Poliroll for 60 seconds each at 11000

rpm +/- 500rpm.

(10) Inspect Vane 1 Refer to Figure 1, Figure 2 and

Figure 3.

Inspect the part.

Refer to vendor data cards. Refer to

HU45506 OMSD for installation and

removal instructions. Inspect vane 1.

Use HU45500 T900 TBH vane inspection

kit and inspection equipment. If not

in the limits then contact

Rolls-Royce.

(11) Set up the machining equipment. Refer to Figure 1, Figure 2 and

Figure 3.

Assemble the Tooling

Refer to HU45506 OMSD. Assemble

HU45507 and HU45502 to Vane 14 on the

Low Pressure (LP) Turbine Bearing and

Support Exhaust Case. Assemble the

flexible drive to Vane 12 and 13.

Make sure that the debris removal

system is installed.

Test the tooling. Refer to the OMSD.

Make sure the debris removal,

electric motor, cooling and tool

movement systems all function

correctly.

Printed in Great Britain

RB.211−72−J024

Page 11

Mar. 1/16

Mar. 1/16
(12) Machine Vane 14 Refer to Figure 1, Figure 2 and

Figure 3.

Machine the part.

Refer to vendor data cards. Run the

electric motor at 3000 rpm +/- 250

rpm. Cut for 3 sec +/- 1 sec per

contact of the cutting tool to the

Tail Bearing Housing. Machine vane 14

to the dimensions specified. Make

sure that the cutting tool is

supplied with adequate water coolant.

Make sure the cutting tool has a rest

period to remove debris using suction

equipment and cool the cutting tool

between contact periods with the

part.

(13) Remove the machining equipment. Refer to Figure 1, Figure 2 and

Figure 3.

Remove the Tooling

Refer to HU45506 OMSD. Remove HU45502

from Vane 14 on the Low Pressure (LP)

Turbine Bearing and Support Exhaust

Case. Remove the flexible drive from

Vane 12 and 13. Make sure that the

debris removal system is removed.

(14) Clean the part. Locally clean the repair area. Refer

to OP TASK 70-00-00-100-101. Use swab

method.

Use degreasing equipment.

(15) Break Sharp Edges on Vane 14 Refer to Figure 1, Figure 2 and

Figure 3.

Remove the sharp edges from the vane

machining.

Refer to vendor data cards. Use

HU45501 T900 TBH Vane Polishing Kit.

Break the sharp edges by using 120

grit Policap for 20 seconds per side

at 11000 rpm +/- 500rpm.

Printed in Great Britain

RB.211−72−J024

Page 12

Mar. 1/16

Mar. 1/16
(16) Polish Vane 14 Refer to Figure 1, Figure 2 and

Figure 3.

Polish the part.

Refer to vendor data cards. Polish

vane 14 to create the surface finish

specified. Use HU45434 T900 TBH Vane

Polishing Kit. Polish the machined

surfaces by using 2 off 120 grit

Poliroll for 60 seconds each at 11000

rpm +/- 500rpm.

(17) Inspect Vane 14 Refer to Figure 1, Figure 2 and

Figure 3.

Inspect the part.

Refer to vendor data cards. Refer to

HU45506 OMSD for installation and

removal instructions. Inspect vane

14. Use HU45500 T900 TBH vane

inspection kit and inspection

equipment. If not in the limits then

contact Rolls-Royce.

(18) Clean the part. Locally clean the repair area on vane

1 and vane 14. Refer to OP TASK

70-00-00-100-101. Use swab method.

Use degreasing equipment.

(19) Etch the part. Swab etch vane 1 and vane 14. Refer

to OP TASK 70-00-00-100-148 and use

the ferric chloride etch paste. Use

swab etch equipment.

(20) Fluorescent Penetrant Inspect. Do a local penetrant crack test on

the Low Pressure (LP) Turbine Bearing

and Support Exhaust Case vane 1 and

vane 14 in the machined area. Use

OMat 632 fluorescent penetrant, high

sensitivity water washable.

Refer to OP TASK 70-00-00-200-210.

Reject if cracked.

(21) Remove the Masking Refer to Figure 1, Figure 2 and

Figure 3.

Remove the masking in the repair area

between vane number 11 and vane

number 3 and the rear edge of the LP

turbine stage 5 blades.

Printed in Great Britain

RB.211−72−J024

Page 13

Mar. 1/16

Mar. 1/16
(22) Re-identify the Low Pressure (LP)

Turbine Bearing and Support Exhaust

Case.

Refer to Figure 1, Figure 2 and

Figure 3.

Strike out the part number and

vibration peen the new part number in

the position specified. Use vibration

peen equipment.

Existing Part

Number

New Part Number

FW27718 KH45090

FW35923 KH46677

FW51434 KH46678

Record the accomplishment of this

Service Bulletin in the engine log

book.

D. OFF-WING. Rework the Low Pressure (LP) Turbine Bearing and Support Exhaust Case

when it is at piece part level.

(1) Clean the part. Locally clean the repair area. Refer

to OP TASK 70-00-00-100-101. Use swab

method.

Use degreasing equipment.

(2) Fluorescent Penetrant Inspect. Do a penetrant crack test on the Low

Pressure (LP) Turbine Bearing and

Support Exhaust Case vanes 1 and 14

in accordance with NMSB 72-AH154.

Refer to OP TASK 70-00-00-200-210.

If cracked refer to FRSH741.

If crack is not in the limits of

FRSH741 then refer to NMSB72-AH154

for acceptance criteria. Do not

complete this rework modification.

Printed in Great Britain

RB.211−72−J024

Page 14

Mar. 1/16

Mar. 1/16
(3) Set up the machining equipment. Refer to Figure 1, Figure 2 and

Figure 3.

Assemble the Tooling

Refer to HU45506 OMSD. Assemble

HU45507 and HU45502 to Vane 1 on the

Low Pressure (LP) Turbine Bearing and

Support Exhaust Case. Assemble the

flexible drive to Vane 13 and 14.

Make sure that the debris removal

system is installed.

Test the tooling. Refer to the OMSD.

Make sure the debris removal,

electric motor, cooling and tool

movement systems all function

correctly.

(4) Machine Vane 1 Refer to Figure 1, Figure 2 and

Figure 3.

Machine the part.

Refer to vendor data cards. Run the

electric motor at 3000 rpm +/- 250

rpm. Cut for 3 sec +/- 1 sec per

contact of the cutting tool to the

Tail Bearing Housing. Machine vane 1

to the dimensions specified. Make

sure that the cutting tool is

supplied with adequate water coolant.

Make sure the cutting tool has a rest

period to remove debris using suction

equipment and cool the cutting tool

between contact periods with the

part.

(5) Remove the machining equipment. Refer to Figure 1, Figure 2 and

Figure 3.

Remove the Tooling

Refer to HU45506 OMSD. Remove HU45502

from Vane 1 on the Low Pressure (LP)

Turbine Bearing and Support Exhaust

Case. Remove the flexible drive from

Vane 13 and 14. Make sure that the

debris removal system is removed.

(6) Clean the part. Locally clean the repair area. Refer

to OP TASK 70-00-00-100-101. Use swab

method.

Use degreasing equipment.

Printed in Great Britain

RB.211−72−J024

Page 15

Mar. 1/16

Mar. 1/16
(7) Break Sharp Edges on Vane 1 Refer to Figure 1, Figure 2 and

Figure 3.

Remove the sharp edges from the vane

machining.

Refer to vendor data cards. Use

HU45501 T900 TBH Vane Polishing Kit.

Break the sharp edges by using 120

grit Policap for 20 seconds per side

at 11000 rpm +/- 500rpm.

(8) Polish Vane 1 Refer to Figure 1, Figure 2 and

Figure 3.

Polish Vane 1.

Refer to vendor data cards. Polish

vane 1 to create the surface finish

specified. Use HU45434 T900 TBH Vane

Polishing Kit. Polish the machined

surfaces by using 2 off 120 grit

Poliroll for 60 seconds each at 11000

rpm +/- 500rpm.

(9) Inspect Vane 1 Refer to Figure 1, Figure 2 and

Figure 3.

Inspect the part.

Refer to vendor data cards. Refer to

HU45506 OMSD for installation and

removal instructions. Inspect vane 1.

Use HU45500 T900 TBH vane inspection

kit and inspection equipment. If not

in the limits then contact

Rolls-Royce.

(10) Set up the machining equipment. Refer to Figure 1, Figure 2 and

Figure 3.

Assemble the Tooling

Refer to HU45506 OMSD. Assemble

HU45507 and HU45502 to Vane 14 on the

Low Pressure (LP) Turbine Bearing and

Support Exhaust Case. Assemble the

flexible drive to Vane 12 and 13.

Make sure that the debris removal

system is installed.

Test the tooling. Refer to the OMSD.

Make sure the debris removal,

electric motor, cooling and tool

movement systems all function

correctly.

Printed in Great Britain

RB.211−72−J024

Page 16

Mar. 1/16

Mar. 1/16
(11) Machine Vane 14 Refer to Figure 1, Figure 2 and

Figure 3.

Machine the part.

Refer to vendor data cards. Run the

electric motor at 3000 rpm +/- 250

rpm. Cut for 3 sec +/- 1 sec per

contact of the cutting tool to the

Tail Bearing Housing. Machine vane 14

to the dimensions specified. Make

sure that the cutting tool is

supplied with adequate water coolant.

Make sure the cutting tool has a rest

period to remove debris using suction

equipment and cool the cutting tool

between contact periods with the

part.

(12) Remove the machining equipment. Refer to Figure 1, Figure 2 and

Figure 3.

Remove the Tooling

Refer to HU45506 OMSD. Remove HU45502

from Vane 14 on the Low Pressure (LP)

Turbine Bearing and Support Exhaust

Case. Remove the flexible drive from

Vane 12 and 13. Make sure that the

debris removal system is removed.

(13) Clean the part. Locally clean the repair area. Refer

to OP TASK 70-00-00-100-101. Use swab

method.

Use degreasing equipment.

(14) Break Sharp Edges on Vane 14 Refer to Figure 1, Figure 2 and

Figure 3.

Remove the sharp edges from the vane

machining.

Refer to vendor data cards. Use

HU45501 T900 TBH Vane Polishing Kit.

Break the sharp edges by using 120

grit Policap for 20 seconds per side

at 11000 rpm +/- 500rpm.

Printed in Great Britain

RB.211−72−J024

Page 17

Mar. 1/16

Mar. 1/16
(15) Polish Vane 14 Refer to Figure 1, Figure 2 and

Figure 3.

Polish the part.

Refer to vendor data cards. Polish

vane 14 to create the surface finish

specified. Use HU45434 T900 TBH Vane

Polishing Kit. Polish the machined

surfaces by using 2 off 120 grit

Poliroll for 60 seconds each at 11000

rpm +/- 500rpm.

(16) Inspect Vane 14 Refer to Figure 1, Figure 2 and

Figure 3.

Inspect the part.

Refer to vendor data cards. Refer to

HU45506 OMSD for installation and

removal instructions. Inspect vane

14. Use HU45500 T900 TBH vane

inspection kit and inspection

equipment. If not in the limits then

contact Rolls-Royce.

(17) Clean the part. Locally clean the repair area on vane

1 and vane 14. Refer to OP TASK

70-00-00-100-101. Use swab method.

Use degreasing equipment.

(18) Etch the part. Swab etch vane 1 and vane 14. Refer

to OP TASK 70-00-00-100-148 and use

the ferric chloride etch paste. Use

swab etch equipment.

(19) Fluorescent Penetrant Inspect. Do a local penetrant crack test on

the Low Pressure (LP) Turbine Bearing

and Support Exhaust Case vane 1 and

vane 14 in the machined area. Use

OMat 632 fluorescent penetrant, high

sensitivity water washable.

Refer to OP TASK 70-00-00-200-210.

Reject if cracked.

Printed in Great Britain

RB.211−72−J024

Page 18

Mar. 1/16

Mar. 1/16
(20) Re-identify the Low Pressure (LP)

Turbine Bearing and Support Exhaust

Case.

Refer to Figure 1, Figure 2 and

Figure 3.

Strike out the part number and

vibration peen the new part number in

the position specified. Use vibration

peen equipment.

Existing Part

Number

New Part Number

FW27718 KH45090

FW35923 KH46677

FW51434 KH46678

Record the accomplishment of this

Service Bulletin in the engine log

book.

E. A record of accomplishment is required.

The Service Bulletin number and relevant Service Bulletin parts shall be recorded

in the engine log book when the Service Bulletin part is fitted in its entirety.

Printed in Great Britain

RB.211−72−J024

Page 19

Mar. 1/16

Mar. 1/16
Rework details

Figure 1

Printed in Great Britain

RB.211−72−J024

Page 20

Mar. 1/16

Mar. 1/16
Rework details

Figure 2

Printed in Great Britain

RB.211−72−J024

Page 21

Mar. 1/16

Mar. 1/16
Rework details

Figure 3

Printed in Great Britain

RB.211−72−J024

Page 22

Mar. 1/16

Mar. 1/16
SUPPLEMENT - PRICE AND AVAILABILITY

This is a technical document not a quotation; any prices and delivery given are in

good faith without engagement.

Alternative parts may be supplied instead of parts listed. See Material Information

disposition instructions.

1. Modification Kit

Not applicable. Parts supplied as single line items.

2. New production or rework parts:

Part No. Qty

Unit Price

US Dollars

KH45090 1 Price will be supplied on request

KH46677 1 Price will be supplied on request

KH46678 1 Price will be supplied on request

3. Tools

None.

ENGINE - EXHAUST CASE - INTRODUCTION OF LP TURBINE EXHAUST CASE AND SUPPORT

ASSEMBLIES ACCOMPLISHED BY REWORK OF EXISTING ASSEMBLIES - MOD.72-J024

Printed in Great Britain

RB.211−72−J024

Supplement Page 1 of 1

Mar. 1/16

Mar. 1/16