# Rolls-Royce Service Bulletin RB 72-J024: No revision named

- Rights: © Rolls-Royce plc. Filed by the FAA in regulations.gov docket FAA-2013-1015, the docket of AD 2014-05-25, 2017-01-01, 2017-08-10. Not covered by OpenAirDocs’ CC0 dedication.
- Document: [Rolls-Royce Service Bulletin RB 72-J024](https://openairdocs.org/service-documents/rolls-royce/rb72-j024.md)
- Title as filed: RB_72-J024_0
- Pages: 25
- PDF: https://openairdocs.org/files/sha256/65/92/6592aad4f03f5e468030b7aa8de1062c01bd824cd5dcb2a6e85fe0d910ed8132
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## Text

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### Page 1

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

### Page 2

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

### Page 3

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

### Page 4

(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

### Page 5

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
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Mar. 1/16

### Page 6

(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
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### Page 7

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
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Mar. 1/16

### Page 8

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
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### Page 9

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

### Page 10

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
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Mar. 1/16

### Page 11

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

### Page 12

(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

### Page 13

(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

### Page 14

(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

### Page 15

(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

### Page 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

### Page 17

(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

### Page 18

(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

### Page 19

(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

### Page 20

(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

### Page 21

(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

### Page 22 (OCR)

RB211  PROPULSION
SYSTEM
SERVICE
ROYCE  BULLETIN
(13°45'50.4')  AA  - (11°57)  c)  Printed in Great Britain
VANE 14  - VANE 1
AẦ™
AB
THE VERTICAL
ENGINE CENTERLINE
VIEW ON THE TAIL BEARING HOUSING
SUPPORT STRUCTURE ASSEMBLY
LOOKING FORWARDS
MIS SPECIFIED BY THE CYLINDRICAL AREA OF THE OUTER FLOWPATH
B IS SPECIFIED BY POINT AE AND PERPENDICULAR TO A FOR EACH OF
THE VANES 1 AND 14
C IS SPECIFIED THROUGH THE AXIS OF LA  AND AT A DISTANCE FROM
POINT AG FOR EACH OF THE VANES 1 AND 14
DIMENSIONS ARE IN MILLIMETERS (INCHES)
HE SURFACE TEXTURE VALUES ARE IN MICROMETERS (MICROINCHES
ГНЕ SURFACE TEXTURE TO BE 3,2 (125) UNLESS SPECIFIÈD DIFFERENTL
GEOMETRIC SYMBOLS ARE GIVEN IN THE ISO MANUAL R1101
dem0002568  REMOVE SHARP EDGES MINIMUM 0,80 (0.031)
MACHINE WHERE SHOWN V
REWORK OF THE TAIL BEARING HOUSING SUPPORT STRUCTURE ASSEMBLY
Rework details
Figure 1
Mar. 1/16  RB.211-72-J024
Mar. 1/16  Page 20
© Rolls-Royce p/c

### Page 23 (OCR)

RB211  PROPULSION
SYSTEM
SERVICE
ROYCE  BULLETIN
2,00 (0.079) A BC
Printed in Great Britain  GAGE  \ 0,80 (0.031)
17,17 (0.676)  APPLIES ONLY
TO RADIUS
POINT AF
FROM POINT AF  R10,00 (0.394)  AC
1,38/0.054
0,38 (0.015)
GAGE  AH/
49,11 (1.933)
70°  (POINT AE-
AD'  PAD
AC
- 3,00 (0.118) ABC
OVER AREA AH
LEADING EDGE
\ SILHOUETTE  9,50 (0.374)
OVER THE RADIUS
SECTION AA (VANE 1)
THE SAME FOR
SECTION AB (VANE 14)
I dem0002569  REWORK OF THE TAIL BEARING HOUSING SUPPORT STRUCTURE ASSEMBLY
Rework details
Figure 2
Mar. 1/16  RB.211-72-J024
Mar. 1/16  Page 21
© Rolls-Royce p/c

### Page 24 (OCR)

OLLS  RB211  PROPULSION
SYSTEM
SERVICE
ROYCE  BULLETIN
(VANE 8)  (VANE 7)  Printed in Great Britain
(OUTER SHEET)
IDENTITY MARKS HERE
TO THE INSTRUCTIONS
BOTTOM DEAD
CENTER
SECTION AC
POINT AE
20,38 (0.802)
GAGE  - POINT AG
26,74 (1.053)
SECTION AD
Idem0002570  REWORK OF THE TAIL BEARING HOUSING SUPPORT STRUCTURE ASSEMBLY
Rework details
Figure 3
Mar. 1/16  RB.211-72-J024
Mar. 1/16  Page 22
© Rolls-Royce p/c

### Page 25

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

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