# Rolls-Royce Non-Modification Service Bulletin 72-K132: No revision named

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- Document: [Rolls-Royce Non-Modification Service Bulletin 72-K132](https://openairdocs.org/service-documents/rolls-royce/72-k132.md)
- Title as filed: RB_72-K132_0_2018-10-22_08-20-01
- Pages: 51
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- Page: https://openairdocs.org/service-documents/rolls-royce/72-k132/file/e715fd71ffd3

## Text

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### Page 1

This document transmits the Initial Issue of Service Bulletin TRENT1000-72-K132
Bulletin Initial Issue
Remove Incorporate Reason for change
Pages 1 to 40 of the
Service Bulletin
Initial Issue
Page 1 and 2 of
Appendix 1
Initial Issue
Page 1 and 2 of
Appendix 2
Initial Issue
Page 1 and 2 of
Appendix 3
Initial Issue
Page 1 and 2 of
Appendix 4
Initial Issue
Printed in Great Britain
Jun.29/18
TRENT 1000 SERIES PROPULSION SYSTEMS NON-MODIFICATION SERVICE BULLETIN
TRENT 1000 72−K132
Transmittal - Page 1 of 3
Date

### Page 2

LIST OF EFFECTIVE PAGES
The effective pages to this Service Bulletin are as follows:
Page Revision Number Revision Date
Bulletin
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2 Jun.29/18
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Appendix 1
1 Jun.29/18
2 Jun.29/18
Printed in Great Britain
TRENT 1000 72−K132
Transmittal - Page 2

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Appendix 2
1 Jun.29/18
2 Jun.29/18
Appendix 3
1 Jun.29/18
2 Jun.29/18
Appendix 4
1 Jun.29/18
2 Jun.29/18
Printed in Great Britain
TRENT 1000 72−K132
Transmittal - Page 3

### Page 4

1. Planning Information
A. Effectivity
Boeing 787
TRENT1000-A/01 All Engines
TRENT1000-A/01A All Engines
TRENT1000-AE All Engines
TRENT1000-AE/01A All Engines
TRENT1000-C/01 All Engines
TRENT1000-C/01A All Engines
TRENT1000-CE All Engines
TRENT1000-CE/01A All Engines
TRENT1000-D/01 All Engines
TRENT1000-D/01A All Engines
TRENT1000-E/01 All Engines
TRENT1000-E/01A All Engines
TRENT1000-G/01 All Engines
TRENT1000-G/01A All Engines
TRENT1000-H/01 All Engines
TRENT1000-H/01A All Engines
Trent1000 IP Compressor Modules
B. Reason
It has been identified that there is a requirement to replace Intermediate
Pressure (IP) compressor stage 1 rotor blades (FW61601 or KH16052) and/or stage
2 rotor blades (FW61602 or KH16053) and/or the IP compressor drum (FW75680) on
the Trent 1000 Package B engines using a cost-effective method.
ENGINE COMPONENT - REPLACEMENT OF THE IP COMPRESSOR ROTOR STAGE 1 BLADES AND/OR
STAGE 2 BLADES AND/OR IPC ROTOR - NON-MODIFICATION SERVICE BULLETIN - NON -
MOD.72-K132
Printed in Great Britain
TRENT 1000 72−K132
Page 1 of 40
Jun.29/18
Jun.29/18
TRENT 1000 SERIES
SERVICE BULLETIN

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C. Description
This Non-Modification Service Bulletin (NMSB) instructs the restoration to a
serviceable condition of engines or modules which require IP compressor stage 1
rotor and/or IP compressor stage 2 rotor blades to be replaced. Engines/IPC
modules embodied with NMSB 72-K132 will be subjected to inspection requirements
as detailed in NMSB 72-AK130.
The Initial Issue of this NMSB will only cover the accomplishment of 2
workscope options:
Part B - The replacement of up to a maximum of 6 IP compressor stage 1
rotor blades and/or up to 6 IP compressor stage 2 rotor blades with new or
serviceable used material (SUM) with the 02 module removed from the core
engine.
Part C - To replace all IP compressor stage 1 rotor blades and all IP
compressor stage 2 rotor blades with new.
Subsequent revisions to this NMSB will include additional blade replacement
workscopes including replacing the IP Compressor Rotor Shaft.
D. Compliance
The on-wing inspection requirements as detailed in NMSB 72-AK130 is anticipated
to be the subject of an Airworthiness Directive. Therefore, when recording
compliance to NMSB 72-K132 in the engine/module log book the Revision Number of
this NMSB must be recorded along with which Part of this NMSB was accomplished.
(1) ON-WING
Not Applicable
(2) IN-SHOP
OPTIONAL
(a) To replace up to a maximum of 6 IP compressor stage 1 rotor blades
and/or up to 6 IP compressor stage 2 rotor blades with new or SUM with
the 02 module removed from the core engine, carry out accomplishment
instructions in accordance with 3.B. Accomplishment Instructions.
(b) To replace all IP compressor stage 1 rotor blades and all IP
compressor stage 2 rotor blades with new, carry out accomplishment
instructions in accordance with 3.C. Accomplishment Instructions.
E. Approval
The technical content of this Non-Modification Service Bulletin was approved
under the authority of Design Organisation Approval EASA.21J.035 on Jun.28/18.
Printed in Great Britain
TRENT 1000 72−K132
Page 2
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F. Manpower
(1) On-wing
Not applicable
(2) In-shop
Accomplishment Instructions
(a) 3.A. Accomplishment Instructions - Reserved for Future Use
(b) 3.B Accomplishment Instructions
(i) Time to gain access:
5 Days (4 persons)
(ii) Time to inspect and refurbish parts:
8 Days (2 persons)
(iii) Time to restore to a serviceable condition:
5 Days (4 persons)
(c) 3.C Accomplishment Instructions
(i) Time to gain access:
5 Days (4 persons)
(ii) Time to inspect and refurbish parts:
5 Days (2 persons)
(iii) Time to restore to a serviceable condition:
10 Days (4 persons)
(d) 3.D Accomplishment Instructions - Reserved for future use.
(e) 3.E Accomplishment Instructions - Reserved for future use.
(f) 3.F Accomplishment Instructions - Reserved for future use.
NOTE: The parts affected by this Non-Modification Service Bulletin are
accessible in-shop only.
Printed in Great Britain
TRENT 1000 72−K132
Page 3
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Jun.29/18
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SERVICE BULLETIN

### Page 7

G. Material Price and Availability
Prices are available on request.
H. Tooling Price and Availability
Special tools are not required
I. References
(1) Repeat Technical Variances
(a) RTV180888 - ADVANCE ISSUE OF RMR128586
(b) RTV183155 - Install the IP Compressor Module (Gantry Method TTL
Tooling Series)
(c) RTV183187 - Install the LP Compressor Module and LP Compressor
Retention Shaft (Gantry Method TTL Tooling Series).
(2) Engine Manual (EM):
(a) EM Task, 72-32-00-020-802, Remove the Air/Oil Seal Tube from the IP
Compressor Module
(b) EM Task, 72-32-00-030-801, Disassemble the IP Compressor Module
(c) EM Task, 72-32-00-420-801, Install the Air and Oil Guide Tubes in the
IP Compressor Module
(d) EM Task, 72-32-20-030-801, Case and Rotor Disassembly
(e) EM Task, 72-32-30-040-801, Disassemble the IP Compressor Rotor
Assembly
(f) EM Task, 72-32-30-440-801, Assemble the IP Compressor Rotor Assembly
(g) EM Task, 75-31-11-050-801, Remove the VSV Actuators from the IP
Compressor Module
(3) Source Controlled Repairs:
(a) Clean, Inspection and Repair Manual, 72-32-32-300-032, Intermediate
Pressure (IP) Compressor Stage 1 Blades - Re-Shot Peen the Blade Root
(FRSB775).
(b) Engine Manual, 72-32-32-300-033, Intermediate Pressure (IP) Compressor
Stage 2 Blades - Re-Shot Peen the Blade Root (FRSB776).
(c) Check and Rectify Manual, 72-32-00-300-003, Intermediate Pressure (IP)
Compressor Stage 1 and Stage 2 Blades - Machine the Blades (FRSB777).
Printed in Great Britain
TRENT 1000 72−K132
Page 4
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SERVICE BULLETIN

### Page 8

(4) Non-Source Controlled Repairs:
(a) Clean, Inspection and Repair Manual, 72-32-32-300-001, Intermediate
Pressure (IP) Compressor Blades Stages 1 to 6 - Re-apply the Dry Film
Lubricant (FRSB368).
(5) Clean, Inspection and Repair (CIR) Manual:
(a) CIR Task, 72-32-32, Clean, Inspect and Repair the Compressor Blades.
(b) CIR Task, 72-32-32-100-801, Clean the Stage 1 Rotor Blade
(c) CIR Task, 72-32-32-100-802, Clean the Stage 2 thru Stage 6 Rotor
Blades
(d) CIR Task, 72-32-32-200-801, Examine the Stage 1 Rotor Blade
(e) CIR Task, 72-32-32-200-802, Examine the Stage 2 to Stage 6 Rotor
Blades
(6) Check and Rectify Manual (CRM):
(a) CRM Task, 72-32-00-200-801, Examine the IP Compressor Cases, Rotor
Assembly and Front Bearing Housing
(7) Overhaul Process Manual TSD594-J:
(a) Task, 70-00-00-100-108, Overhaul Process 108 - Stripping of Silicone
Rubbers
(b) Task, 70-00-00-100-148, Overhaul Process 148 - Swab Etch
(c) Task, 70-00-00-200-210, Overhaul Process 210 - Fluorescent Penetrant
Inspection
(d) Task, 70-00-00-200-224, Overhaul Process 224 - Assessment of Surface
Features using Rubber Replica Material
(e) Task, 70-00-00-300-363, Overhaul Process 363 - Marking Methods
(8) Standard Practices Manual (SPM):
(a) Task, 70-31-00-200-000, Inspection of Parts
(9) TSD7019, Authorised Repair Vendor Directory
(10) Rolls-Royce Non Modification Service Bulletin (NMSB):
(a) NMSB 72-AK130 - IP Compressor Stage 1 Blades, Stage 2 Blades and IPC
Shaft Stage 2 Dovetailposts - Inspection Interval Definition
Printed in Great Britain
TRENT 1000 72−K132
Page 5
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SERVICE BULLETIN

### Page 9

(b) NMSB 72-J871 - Replacement of the IP Compressor Rotor Stage 1 Blades
and/or Stage 2 Blades and/or IPC Rotor.
Printed in Great Britain
TRENT 1000 72−K132
Page 6
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Jun.29/18
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SERVICE BULLETIN

### Page 10

2. Material Information
A. The parts required to accomplish this Non-Modification Service Bulletin:
Consumable Materials
OMat PART NO. DESCRIPTION
OMat 1/286 Remover - Cured Polysulphide and
Silicone Rubber
OMat 261 Temporary Marker
OMat 262 Temporary marker felt/fibre tip
OMat 283 Masking tape
OMat 606 Developer, Powder
OMat 652 Fluorescent penetrant Ultra high
sensitivity post-emulsified
Printed in Great Britain
TRENT 1000 72−K132
Page 7
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3. Accomplishment Instructions
Only carry out a visual check on modules, mini modules, sub-assemblies and parts
that are removed solely to gain access to parts that require repair or
modification, do not carry out any additional disassembly for the purpose of
visual inspection. Refer to SPM TASK 70-31-00-200-000 Inspection of Parts and
report any findings to Rolls-Royce.
NOTE: A visual inspection is the examination of a part for obvious damage,
only inspect exposed areas. This evaluation is to be carried out with
white light, without magnification, and does not require dimensional
measurements.
Unless the engine requires an in-shop engine test, or if required for access to
complete the defined workscope, any covers or blanks that are installed on the
engine are not to be removed.
A. Part A - Reserved for Future Use
B. Part B - To replace no more than 6 Intermediate Pressure (IP) Compressor Stage
1 rotor blades and/or up to 6 IP Compressor Stage 2 rotor blades only with new
or SUM with the 02 module removed from the core engine.
If more than 6 blades from either stage 1 or 2 require replacing, do Part C. of
the Accomplishment Instructions, instead.
NOTE: The following Accomplishment Instructions define how blades from both
stage 1 and 2 should be removed, inspected, and installed.
NOTE: The following is to be accomplished at an Overhaul Facility with the IP
compressor module removed and partially disassembled. This is to reduce
the workscope to a minimum.
(1) Use currently published EM procedures to gain access to the IP compressor
blades.
(a) When removing the LP and IP Compressor Modules there are 4 alternative
procedures published in the EM Vertical Build, Engine Build Stand,
Gantry Method ROT and Gantry Method TTL Tooling series.
If stripping the engine using the Gantry Method TTL Tooling Series,
Refer to RTV180888 until Dec.31/18.
Printed in Great Britain
TRENT 1000 72−K132
Page 8
Jun.29/18
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SERVICE BULLETIN

### Page 12

(b) Prior to removing the IP Compressor Module, temporarily mark one of
the 4-off location pins (72-33-21, 01-325) on the IP compressor rear
stub shaft (72-33-21, 01-250) and the correlating location pin hole on
the IP compressor rotor curvic cone (72-32-31, 01-125). Use OMat 261
or OMat 262.
NOTE: The temporary mark created on the IP compressor rear stub shaft
location pin and IP compressor rotor curvic cone is important
for avoiding an increase in vibration when the IP compressor
module is reinstalled to the intermediate casing module.
(c) Remove the air/oil seal tube from the IP compressor module in
accordance with current overhaul procedures (EM Task 72-32-00-020-802,
Remove the Air/Oil Seal Tube from the IP Compressor Module).
(d) Disassemble the IP Compressor Module in accordance with current
overhaul procedures (EM TASK 72-32-00-030-801, Disassemble the IP
Compressor Module and EM TASK 72-32-20-030-801 IP Compressor Case and
Rotor Group Assembly).
When disassembling the IP Compressor Module:
(i) Do not perform SUBTASK 72-32-00-030-028, Remove the Two
Variable Stator Vane (VSV) Actuators.
(ii) Do not perform SUBTASK 72-32-00-030-029, Remove the IP
Compressor Variable Inlet Guide Vanes (VIGV) and VSV Actuating
Mechanism unless there are obvious visible signs of damage.
(iii) Do not perform SUBTASK 72-32-00-030-030, Disassemble the
Actuating Mechanism Control Rods, unless there are obvious
visible signs of damage.
(iv) If there are no obvious visible signs of damage, remove the VSV
and VIGV Actuation Mechanism Assembly. Do steps 1.to 7. below:
(1) Refer to Engine Manual TASK 72-32-00-030-801 -
Fig.72-32-00-990-322-001, Fig.72-32-00-990-322-002,
Fig.72-32-00-990-322-003, Fig.72-32-00-990-323-001,
Fig.72-32-00-990-323-002, Fig.72-32-00-990-323-003,
Fig.72-32-00-990-324, and Fig. 1 from this NMSB. Refer to
Engine Manual TASK 75-31-11-050-801, Fig. 75-31-11-990-011
and Fig. 75-31-11-990-014.
(2) For the removal of the Left VIGV Control Rod, remove the
Cotter Split Pin (72-32-42, 02-175), release the Nuts
(72-32-42, 02-180), Washer (72-32-42, 02-190) and the Bolts
(72-32-12, 01-150). Release the VIGV Control Rod (72-32-42,
02-200) from the Bridge Plate (72-32-12, 01-510). Repeat for
the Right VIGV control rod.
Printed in Great Britain
TRENT 1000 72−K132
Page 9
Jun.29/18
Jun.29/18
TRENT 1000 SERIES
SERVICE BULLETIN

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(3) For the removal of the Left VSV Stage 1 Control Rod, remove
the Cotter Split Pin (72-32-42, 02-375), release the Nuts
(72-32-42, 02-380), Washer (72-32-42, 02-390) and Bolts
(72-32-42, 03-150). Release the VSV Stage 1 Control Rods
(72-32-42, 02-400) from the Bridge Plate (72-32-12, 03-250).
Repeat for the Right VSV stage 1 control rod.
(4) For the removal of the Left VSV Stage 2 Control Rod, remove
the Cotter Split Pin (72-32-42, 02-575), release the Nuts
(72-32-42, 02-580), Washer (72-32-42, 02-590) and Bolts
(72-32-42, 04-150). Release the VSV Stage 2 Control Rods
(72-32-42, 02-400) from the Bridge Plate (72-32-12, 04-250).
Repeat for the Right VSV stage 2 control rod.
(5) For the removal of the Right VSV actuator, release the 2 off
Nuts (75-31-11, 01-270) and the 2 off Washer (75-31-11,
01-265) to remove the 2 off Bolts (75-31-11, 01-260).
Disassemble the Right VSV Actuator (75-31-11, 01-250) from
the Rear Mounting Bracket (75-31-11, 01-285).
(6) For the removal of the Left VSV actuator release the 2 off
Nuts (75-31-11, 02-270) and the 2 off Washer (75-31-11,
02-265) to remove the 2 off Bolts (75-31-11, 02-260).
Disassemble the Left VSV Actuator (75-31-11, 02-250) from the
Rear Mounting Bracket (75-31-11, 02-285).
(7) The complete assembly of the Upper VSV Bracket (72-32-42,
01-200) and the Lower VSV Bracket (72-32-42, 01-850) can be
removed as a complete set by releasing the 4 off Nuts
(72-32-00, 01-220) and the 4 off Washer (72-32-00, 01-210).
Remove the 4 off Bolts (72-32-00, 01-200) and the 4 off
Hollow Pins (72-32-00, 01-160) to separate the complete
assembly of the Upper VSV Bracket (72-32-42, 01-200) and the
Lower VSV Bracket (72-32-42, 01-850) from the Rear Flange
Housing Assembly (72-32-11, 01-250).
(e) Examine the front air guide tube seal ring (72-32-31, 01-290). Remove
the seal ring if it is not held in a compressed condition in the
groove in accordance with EM Task 72-32-00-420-801, Install the Air
and Oil Guide Tubes in the IP Compressor Module.
(i) Refer to Subtask 72-32-00-420-042-A00 step 13.F.(1) for engines
pre Service Bulletin 72-G222.
(ii) Refer to Subtask 72-32-00-420-042-B00 step 14.F.(1) thru (4)
for engines that have embodied Service Bulletin 72-G222.
(iii) Refer to Subtask 72-32-00-420-042-B00 step 14.G.(1) thru (4)
for engines that have embodied Service Bulletin 72-H364.
Printed in Great Britain
TRENT 1000 72−K132
Page 10
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Jun.29/18
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### Page 14

(2) Disassemble the IP Compressor Rotor Assembly sufficiently to remove the IP
Compressor Stage 1 and Stage 2 Blades
CAUTION: EXTREME CARE IS TO BE TAKEN TO NOT DAMAGE THE IP COMPRESSOR
DRUM AND THE STAGE 1 TO 2 AND STAGE 2 TO 3 SEAL FINS DURING
THE DISASSEMBLY PROCEDURE.  DAMAGING CAN LEAD TO REJECTION
OF THE IP COMPRESSOR DRUM ASSEMBLY.
CAUTION: RATHER THAN LEAVING THE IP COMPRESSOR STUB SHAFT (72-32-31,
01-350) INSTALLED (WHICH IS THE PREFERRED METHOD), IT IS
ACCEPTABLE TO INSTALL THE DUMMY STUB SHAFT (RRT026842).
HOWEVER, INSTALLING THE DUMMY STUB SHAFT WILL RESULT IN AN
INCREASE IN TIME TO COMPLETE THIS PART OF THIS NMSB
(a) Refer to EM TASK 72-32-30-040-801, Disassemble the IP Compressor Rotor
Assembly.
(b) Installing the dummy stub shaft (RRT026842) is optional. To install
the dummy stub shaft, complete the following subtasks in accordance
with current overhaul procedures (EM TASK 72-32-30-040-801,
Disassemble the IP Compressor Rotor Assembly).
(i) SUBTASK 72-32-30-040-105, Remove the IP Stub Shaft from the IP
Compressor Rotor Shaft.
(ii) SUBTASK 72-32-30-040-106-A00, and 72-32-30-040-106-B00.
(iii) SUBTASK 72-32-30-040-107, Install the Lift Tools to the Dummy
Shaft.
(iv) SUBTASK 72-32-30-040-108, Install the Dummy Shaft.
(c) Do not perform EM TASK 72-32-30-040-801, SUBTASK 72-32-030-040-117-A00
or B00, Measure the Blade Tip Radius of the Stage 1 thru Stage 8
Blades
(d) Do not perform EM TASK 72-32-30-040-801, SUBTASK 72-32-30-040-118,
Measure the Diameters of the Rotor Seal Fins.
(e) Where the Stage 1 Seal Fin Protector (RRT065987) is not available,
attach a suitable protective cover of sheet rubber cut to size, with a
thickness of 5,00mm or greater. Use masking taps OMat 283 to secure
the sheet rubber and protect the Stage 1 Rotor Disc Seal Fins.
(f) Remove the IP Compressor Stage 1 Blades (72-32-32, 01-250).
(i) You must correlate and make a record of the weight and position
of the IP compressor stage 1 rotor blades (72-32-32, 01-250)
against their positions on the rotor.
Printed in Great Britain
TRENT 1000 72−K132
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### Page 15

(ii) Find the mark to show the No.1 dovetail slot of the stage 1
rotor disc. The mark is on the face of the outer diameter of
the rotor disc adjacent to the dovetail slot.
(iii) Identify the position of the blades (1 thru 34) before removal
relative to the No.1 dovetail. Record the positions from which
the blade is removed on Appendix 1: IP Compressor Stage 1 Blade
Movement Tracking Form.
(iv) When you remove the stage 1 retaining ring (72-32-32, 01-200)
record the position of the gap in the retaining ring against
the corresponding disc slot.
(v) On removal of the blade you must record the serial number of
each blade in relation to their installed position on the stage
1 rotor disc as each blade is removed. Record the positions on
Appendix 1.
NOTE: This correlation is required as matched IP compressor stage
1 rotor blades (72-32-32, 01-250) must be re-installed in
the position from which they were removed.
(vi) Visually inspect the blade roots for cracks. Measure any cracks
using an applicable metal ruler and record the results in
Appendix 3 - IP Compressor Stage 1 Blade Crack Recording Form.
Provide Appendix 3 to Rolls-Royce (U9505173@Rolls-Royce.com)
through your local Rolls-Royce Overhaul Support Team.
(vii) Remove and do not reuse the 25 off straps (72-32-32, 01-275),
all the nominal straps (72-32-32, 01-285), and all the balance
straps (72-32-32, 01-295).
(1) You must correlate and make a record of the weight and type
of strap along with their positions on the stage 1 rotor
disc.
(2) Record the type of strap removed and the weight of the
balance straps using Appendix 1.
NOTE: This correlation is required when installing
replacement balance straps and for rotor balancing.
(g) Remove the IP Compressor Stage 2 Blades (72-32-32, 02-250).
(i) You must correlate and make a record of the weight and position
of the IP compressor stage 2 rotor blades (72-32-32, 01-250)
against their positions on the rotor.
(ii) When you remove the stage 2 retaining ring (72-32-32, 02-200)
record the position of the gap in the retaining ring against
the corresponding disc slot.
Printed in Great Britain
TRENT 1000 72−K132
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### Page 16

(iii) Find the mark to show the No.1 dovetail slot of the stage 2
rotor disc. The mark is on the face of the outer diameter of
the rotor disc adjacent to the dovetail slot.
(iv) Identify the position of the blades (1 thru 49) before removal
relative to the No.1 dovetail. Record the position from which
the blade is removed in Appendix 2 - Blade Movement Tracking
Form.
NOTE: This correlation is required as matched IP compressor stage
2 rotor blades (72-32-32, 02-250) must be re-installed in
the positions from which they were removed.
(v) Visually inspect the blade roots for cracks. Measure any cracks
using an applicable metal ruler and record the results in
Appendix 4 - IP Compressor Stage 2 Blade Crack Recording Form.
Provide Appendix 4 to Rolls-Royce (U9505173@Rolls-Royce.com)
through your local Rolls-Royce Overhaul Support Team.
(3) Carry Out Inspections of Specific IP Compressor Components
(a) Only carry out a visual inspection on a part unless it is listed
below. No cleaning of a part is required unless stated below.
NOTE: It is acceptable to do the cleaning and inspection of the
components specified in this NMSB in any reasonable sequence to
aid production.
(b) Clean and Inspect the Stage 1 retaining ring (72-32-32, 01-200) in
accordance with published Clean, Inspect and Repair Tasks.
(c) Clean and Inspect the Stage 2 retaining ring (72-32-32, 01-200) in
accordance with published Clean, Inspect and Repair Tasks.
(d) Clean and inspect the exposed surfaces of the stage 1 and 2 rotor
shaft.
(i) Refer to Fig.2.
(ii) Clean the stage 1 of the IP compressor rotor shaft (72-32-31,
01-450) of any residual silicone compound from the locations
where the stage 1 rotor blades (72-32-32, 01-250) have been
removed in accordance with current overhaul procedures (OP Task
70-00-00-100-108, Stripping of Silicone Rubbers, Subtask
70-00-00-110-108-002).
The use of OMat 1/286 can be negated if the IP compressor shaft
can be cleaned sufficiently with the plastic scraper.
(iii) Perform visual check inspection of exposed surfaces. Refer to
the definition of a visual check.
Printed in Great Britain
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(iv) Carry out a local Fluorescent Penetrant Inspection (FPI) of the
IP compressor rotor shaft (72-32-31, 01-450) stage 1 and 2
dovetail post front and rear faces at Zones B and E.
(1) Carry out the inspection in accordance with current overhaul
procedures (OP Task 70-00-00-200-210, Subtask
70-00-00-230-210-002) using OMat 652 Fluorescent Penetrant.
(2) Report any cracks found to Rolls-Royce. If crack free then
accept the disc.
(v) Inspect the dovetail slots of the stage 1 rotor disc.
(1) Identify the stage 1 rotor disc dovetail slot where the stage
1 blade with the largest visible crack was found and measure
depth of galling in Zone A only using an approved Overhaul
Shop Process such as Replicast (OP TASK 70-00-00-200-224).
(2) Identify one other stage 1 rotor disc slot which did not
contain a visibly cracked stage 1 rotor blade. Measure depth
of galling in Zone A only using an approved Overhaul Shop
Process such as Replicast (OP TASK 70-00-00-200-224).
(3) Accept galling in Zone A up to 0,15 mm (0.006 in.) in depth.
(4) For any other defect contact Rolls-Royce and send the
replicasts to the Rolls-Royce Critical Parts and Lifing team.
(vi) Inspect the dovetail slots of the stage 2 rotor disc.
(1) Identify the stage 2 rotor disc dovetail slot where the stage
2 blade with the largest visible crack was found and measure
depth of galling in Zone A only using an approved Overhaul
Shop Process such as Replicast (OP TASK 70-00-00-200-224).
(2) Identify one other stage 2 rotor disc slot which did not
contain a visibly cracked stage 2 rotor blade.  Measure depth
of galling in Zone A only using an approved Overhaul Shop
Process such as Replicast (OP TASK 70-00-00-200-224).
(3) Accept galling in Zone A up to 0,15 mm (0.006 in.) in depth.
(4) For any other defect contact Rolls-Royce and send the
replicasts to the Rolls-Royce Critical Parts and Lifing team.
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(e) Inspect the IP compressor case linings.
(i) Examine the stage 1 to 4 case (72-32-41, 01-250) and stage 5 to
8 case (72-32-46, 01-250) linings in accordance with current
overhaul procedures (CRM Task 72-32-00-200-801, Examine the IP
Compressor Cases, Rotor Assembly and Front Bearing Housing,
Subtask 72-32-00-220-046).
(ii) For any IP Compressor case linings that are outside of those
limits published in the applicable manual tasks following these
inspections, the casing must be repaired in accordance with the
published repair manuals.
(4) Clean, Inspect and Repair the IP compressor stage 1 rotor blades
(72-32-32, 01-250) and stage 2 rotor blades (72-32-32, 02-250):
(a) IP compressor stage 1 rotor blades (72-32-32, 01-250) and stage 2
rotor blades (72-32-32, 02-250) that have already been identified as
needing to be replaced do not require cleaning and inspection.
It is acceptable to use SUM blades to replace the cracked blades if
new blades are unavailable. The SUM blades must have been inspected to
Part 3.B.(4) of this NMSB; match the blade weight and tip height
requirements (using FRSB777 if required); and have been repaired using
FRSB775 for Stage 1 blades and FRSB776 for Stage 2 blades.
(b) Clean the IP compressor stage 1 rotor blades (72-32-32, 01-250) that
remain in accordance with current overhaul procedures (CIR Task
72-32-32-100-801).
(c) Clean the IP compressor stage 2 rotor blades (72-32-32, 02-250) that
remain in accordance with current overhaul procedures (CIR Task
72-32-32-100-802).
(d) Visually inspect the IP compressor stage 1 rotor blades (72-32-32,
01-250) for damage.
NOTE: Refer to the definition of a visual check.
(i) Refer to CIR Task 72-32-32-200-801 for acceptance criteria for
visually observed damage.
(ii) You must only examine the IP compressor stage 1 rotor blades
(72-32-32, 01-250) further in the Zone(s) where damage has been
identified outside of the defined visual check limit.
(iii) The damage limit for galling is to be defined by a measure of
surface area roughness in accordance with Step 3.B.(4)(l)(iv)
of these Accomplishment Instructions.
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(iv) If an IP compressor stage 1 rotor blade (72-32-32, 01-250) is
found outside of damaged limits, update the records in the
Appendix 1: IP Compressor Stage 1 Blade Movement Tracking Form
to identify that it requires to be replaced.
(e) Visually inspect the IP compressor stage 2 rotor blades (72-32-32,
02-250) for damage.
NOTE: Refer to the definition of a visual check.
(i) Refer to CIR Task 72-32-32-200-802 for acceptance criteria for
visually observed damage.
(ii) You must only examine the IP compressor stage 2 rotor blades
(72-32-32, 02-250) further in the Zone(s) where damage has been
identified outside of the defined visual check limit.
(iii) The damage limit for galling is to be defined by a measure of
surface area roughness in accordance with Step 3.B.(4)(m)(iv)
of these Accomplishment Instructions.
(iv) If an IP compressor stage 2 rotor blade (72-32-32, 02-250) is
found damaged outside of limits, update the records in Appendix
2 - IP Compressor Stage 2 Blade Movement Tracking Form to
identify that it requires to be replaced.
(f) Swab-etch the IP compressor stage 1 rotor blade root edge of bedding
(72-32-32, 01-250) and IP compressor stage 2 rotor blade root edge of
bedding (72-32-32-02-250) surfaces to prepare for inspection in
accordance with current overhaul procedures (OP Task
70-00-00-100-148).
(g) Locally degrease the IP compressor stage 1 rotor blade (72-32-32,
01-250) and IP compressor stage 2 rotor blade (72-32-32, 02-250) in
accordance with current overhaul procedures (CIR Task 72-32-32-100-801
and 72-32-32-100-802).
(h) Carry out a Fluorescent Penetrant Inspection (FPI) crack test on each
blade root using OMat 652 Ultra-sensitivity Penetrant in accordance
with current overhaul procedures (OP Task 70-00-00-200-210, Overhaul
Processes 210 - Fluorescent Penetrant Inspection).
If an IP compressor stage 1 rotor blade (72-32-32, 01-250) or IP
compressor stage 2 rotor blade (72-32-32, 02-250) is found to be
cracked during inspection, update the records in Appendices 1 and 2 -
Blade Movement Tracking Form to identify which blade(s) require to be
replaced.
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(i) Locally degrease the IP compressor stage 1 rotor blade (72-32-32,
01-250) and IP compressor stage 2 rotor blade (72-32-32, 02-250) in
accordance with current overhaul procedures (CIR Task 72-32-32-100-801
and 72-32-32-100-802). If the second FPI crack test can be completed
on all the blades within 3 hours of applying the OMat 606 developer
applied in the previous step, then this cleaning step can be omitted.
CAUTION: AN INDEPENDENT INSPECTOR MUST BE USED TO COMPLETE THIS STEP
3.B.(4)(J) FROM THE INSPECTOR THAT COMPLETED STEP 3.B.(4)(H).
(j) Carry out an additional FPI crack test on each IP compressor stage 1
rotor blade root (72-32-32, 01-250) and IP compressor stage 2 rotor
blade root (72-32-32, 02-250) using OMat 652 Ultra-Sensitive Penetrant
in accordance with current overhaul procedures (OP Task
70-00-00-200-210 Overhaul Process 210 - Fluorescent Penetrant
Inspection).
If the second FPI crack test can be completed on all the blades in
this set within 3 hours of applying the OMat 606 developer in the
first FPI crack test, then the application of additional OMat 652
fluid in this step can be omitted.
If an IP compressor stage 1 rotor blade (72-32-32, 01-250) or IP
compressor stage 2 rotor blade (72-32-32, 02-250) is found to be
cracked during inspections, update the records in Appendices 1 and 2 -
Blade Movement Tracking Form, to identify which blade(s) require to be
replaced.
(k) Locally degrease the IP compressor stage 1 rotor blades (72-32-32,
01-250) and IP compressor stage 2 rotor blades (72-32-32, 02-250) in
accordance with current overhaul procedures (CIR Task 72-32-32-100-801
and 72-32-32-100-802).
(l) Inspect the IP compressor stage 1 rotor blade (72-32-32, 01-250) root
flank surface for galling.
NOTE: The root flank surface is contained within dovetail root Zone
D, refer to Fig.3.
(i) Visually examine the IP compressor stage 1 blade (72-32-32,
01-250) root flank surface for galling, refer to Fig.3.
(ii) Select any two crack free IP compressor stage 1 rotor blades
(72-32-32, 01-250) from the set. New replacement blades are
excluded.
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(iii) Measure surface roughness (Ra) (positions to include the area
where galling is evident) using Alicona, Mitutoyo SJ-410 or
equivalent:
(1) Take three readings, at set points, from the concave side of
the IP compressor stage 1 rotor blade (72-32-32, 01-250), in
accordance with repair vendor process.
(2) Take three readings, at set points, from the convex side of
the IP compressor stage 1 rotor blade (72-32-32, 01-250), in
accordance with repair vendor process.
(3) Record all measurements against each IP compressor stage 1
blade (72-32-32, 01-250) serial number.
(iv) Surface Roughness:
(1) Not more than 2,50 micrometers (Ra or Sa) or 2,5 microns -
Accept.
(2) More than in (1) - contact Rolls-Royce.
(v) Any other damage beyond galling in this area contact
Rolls-Royce.
(m) Inspect the IP compressor stage 2 rotor blade (72-32-32, 02-250) root
flank surfaces for galling.
NOTE: The root flank surface is identified as Face 9A and Face 9B,
refer to Fig.4.
(i) Visually examine the IP compressor stage 2 blade (72-32-32,
02-250) root flank surfaces for galling, refer to Fig.4.
(ii) Select any two crack free IP compressor stage 2 rotor blades
(72-32-32, 02-250) from the set. New replacement blades are
excluded.
(iii) Measure roughness (Ra) (positions to include the area where
galling is evident) using Alicona, Mitutoya SJ-410 or
equivalent:
(1) Take three readings, at set points, on Face 9A of the IP
compressor stage 2 rotor blade (72-32-32, 02-250), in
accordance with repair vendor process.
(2) Take three readings, at set points, on Face 9B of the IP
compressor stage 2 rotor blade (72-32-32, 02-250), in
accordance with repair vendor process.
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(3) Record all measurements against each IP compressor stage 2
blade (72-32-32, 02-250) serial number.
(iv) Surface Roughness:
(1) Not more than 2,50 micrometers (Ra or Sa) or 2,5 microns -
Accept.
(2) More than in (1) - contact Rolls-Royce.
(v) Any other damage beyond galling in this area contact
Rolls-Royce.
(n) Weigh each of the IP compressor stage 1 rotor blades (72-32-32,
01-250) and record their weight.
(i) Weigh all of the IP compressor stage 1 rotor blades (72-32-32,
01-250) that were removed and record their weight using
Appendix 1: IP Compressor Stage 1 Blade Movement Tracking Form.
(ii) If all the balance strap (72-32-32, 01-295) weights have not
already been recorded on Appendix 1 - Blade Movement Tracking
Form, weigh the balance straps (72-32-32, 01-295) and record
their weight on Appendix 1: IP Compressor Stage 1 Blade
Movement Tracking Form.
(o) Select new or SUM IP compressor stage 1 rotor blades (72-32-32,
01-250) to replace the IP compressor stage 1 rotor blades that have
been identified as requiring replacement. If SUM blades are used then
the SUM blades must have been inspected to Part 3.B.(4) of this NMSB;
match the blade weight and tip height requirements (using FRSB777) if
required); and have been repaired using FRSB775.
Using the weight data recorded on Appendix 1: IP Compressor Stage 1
Blade Movement Tracking Form, choose blades closest to the original
weight.
CAUTION: THE TOTAL WEIGHT OF THE STAGE 1 ROTOR BLADES CANNOT BE
MORE THAN 15142,9 G (534.14 OZ) EXCEEDING THIS WEIGHT
MAY PUT EXCESSIVE STRESS ON THE ROTOR AND SUPPORT
STRUCTURE.
(i) If more than 6 stage 1 blades need replacing, do not continue
Part 3.B. of this NMSB. Inform the overhaul facility that Part
3.C of this NMSB must be performed, instead.
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(ii) The total weight of all replacement IP compressor stage 1 rotor
blades (72-32-32, 01-250) after cropping must be within plus or
minus 6,00 g of the total weight of all blades being replaced.
This is to be achieved in accordance with the following
conditions:
(1) If no more than 3 IP compressor stage 1 blades are to be
replaced - each replacement blade after cropping must be
within plus or minus 2,00 g of the blade being replaced.
(2) If 4 IP compressor stage 1 rotor blades are to be replaced -
Each replacement blade after cropping must be within plus or
minus 1,50 g of the blade being replaced.
(3) If more than 4 but no more than 6 IP compressor stage 1 rotor
blades are to be replaced - each replacement blade after
cropping must be within plus or minus 1,00 g of the blade
being replaced.
(iii) If it is not possible to replace a blade in accordance with the
requirements above, then do the following:
(1) Identify the blade diametrically opposite the blade to be
replaced.
(2) Replace both blades with new or SUM blades. There should be
no more than 1,00 g difference between the changes in blade
weights of the diametrically opposite blades.
(iv) Calculate the total weight imbalance of the replaced blades:
NOTE: The following procedures may be automated in a spreadsheet
for ease and consistency of calculation.
NOTE: This method and formulae used are identical to those used
in NMSB 72-J871 Part B.
(1) Refer to Fig.5.
(2) For each blade being replaced, calculate the difference in
weight between the old and the new blades. Subtract the
weight of the new blade from the weight of the old blade.
Make a note of whether the weight difference is positive or
negative.
(3) For each blade being replaced, if the difference in blade
weight calculated in Step 3.B.(4)(o)(iv)(2) of these
Accomplishment Instructions is negative, do the following:
A From this point forward, use the absolute value for blade
weight difference by removing the negative sign.
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B If the blade to be replaced is located at blade position
1 thru 17, add 17 to the blade position number. If the
blade to be replaced is located at blade position 18 thru
34, subtract 17 from the blade position number. This
calculation is performed to identify the blade position
opposite the blade being replaced.
C Use the new values for blade weight difference and blade
position in the following calculations.
(4) Determine the angle of each replaced blade in relation to
blade number 1. There are 34 IP compressor stage 1 rotor
blades. Therefore the angle in degrees between blade 1 and
the blade to be replaced is calculated as:
(360 ÷ 34) x (Blade Number - 1)
Ensure that the new blade position calculated in Step
3.B.(4)(o)(iv)(3) B of these Accomplishment Instructions is
used if the difference in blade weight calculated in Step
3.B.(4)(o)(iv)(2) of these Accomplishment Instructions was
negative.
(5) Resolve the calculated weight difference into the x and
y-plane for each blade. The y-plane is in the orientation of
blade number 1. The x-plane is at 90 degrees to the y-plane.
A A To calculate the weight difference in the x-plane,
multiply the weight difference by the Sine of the angle
calculated in Step 3.B.(4)(o)(iv)(4) of these
Accomplishment Instructions.
B To calculate the weight difference in the y-plane,
multiply the weight difference by the Cosine of the angle
calculated in Step 3.B.(4)(o)(iv)(4) of these
Accomplishment Instructions.
(6) Sum together the x-plane weight of each blade. You must take
into account the direction of the weight by using the
positive and negative denotations calculated in Step
3.B.(4)(o)(iv)(5) of these Accomplishment Instructions. Do
not convert the weights to absolute values.
(7) Sum together the y-plane weight of each blade. You must take
into account the direction of the weight by using the
positive and negative denotations calculated in Step
3.B.(4)(o)(iv)(5) of these Accomplishment Instructions. Do
not convert the weights to absolute values.
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(8) Calculate the combined vector sum weight to provide the total
weight imbalance.
A Calculate the square of the x-plane weight calculated in
Step 3.B.(4)(o)(iv)(6) of these Accomplishment
Instructions.
B Calculate the square of the y-plane weight calculated in
Step 3.B.(4)(o)(iv)(7) of these Accomplishment
Instructions.
C Sum the values calculated in Step 3.B.(4)(p)(iv)(8) A and
Step 3.B.(4)(o)(iv)(8) B of these Accomplishment
Instructions.
D Calculate the square root of the values calculated in
step 3.B.(4)(o)(iv)(8) C of these Accomplishment
Instructions.
(v) If the vector sum of the replaced blades calculated in Step
3.B.(4)(o)(iv)(8) D of these Accomplishment Instructions
produces an imbalance of 4,00 grams or more, do the following:
NOTE: The following procedure may be automated in a spreadsheet
for ease and consistency of calculation.
NOTE: This method and formulae used are identical to those used
in NMSB 72-J871 Part B.
(1) Calculate the angle at which the imbalance acts in relation
to blade number 1.
A If the weight in the x-plane (calculated in Step
3.B.(4)(o)(iv)(6) of these Accomplishment Instructions)
is positive and the weight in the y-plane (calculated in
Step 3.B.(4)(o)(iv)(7) of these Accomplishment
Instructions) is positive, do the following calculation.
Ensure that the calculation is performed in Radians and
not degrees.
(INVTAN (X-Plane weight ÷ Y-Plane weight))
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B If the weight in the x-plane (calculated in Step
3.B.(4)(o)(iv)(6) of these Accomplishment Instructions)
is positive and the weight in the y-plane (calculated in
Step 3.B.(4)(o)(iv)(7) of these Accomplishment
Instructions) is negative, do the following calculation.
Use the absolute values for the weights (remove the
negative sign from the y-plane weight). Ensure that the
calculation is performed in Radians and not degrees.
(INVTAN (Y-Plane weight ÷ X-Plane weight)) + (0.5 x PI)
C If the weight in the x-plane (calculated in Step
3.B.(4)(o)(iv)(6) of these Accomplishment Instructions)
is negative and the weight in the y-plane (calculated in
Step 3.B.(4)(o)(iv)(7) of these Accomplishment
Instructions is negative, do the following calculation.
Use the absolute values for the weights (remove the
negative signs from the x-plane weight and y-plane
weight). Ensure that the calculation is performed in
Radians and not degrees.
((INVTAN (X-Plane weight ÷ Y-Plane weight)) + PI
D If the weight in the x-plane (calculated in Step
3.B.(4)(o)(iv)(6) of these Accomplishment Instructions)
is negative and the weight in the y-plane (calculated in
step 3.B.(4)(o)(iv)(7) of these Accomplishment
Instructions) is positive, do the following calculation.
Use the absolute values for the weights (remove the
negative sign from the x-plane weight). Ensure that the
calculation is performed in Radians and not degrees.
((INVTAN (Y-Plane weight ÷ X-Plane weight)) + (1.5 x PI)
(2) Convert the calculated angle to a blade position.
A Divide the angle calculated in Step 3.B.(4)(o)(v)(1) of
these Accomplishment Instructions by 2 x PI.
B Multiply the answer from Step 3.B.(4)(o)(v)(2) A of these
Accomplishment Instructions by 34 (the number of IP
compressor stage 1 rotor blades). Add 1 to this answer
and round to the nearest whole number to define the blade
position.
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(3) Replace the blade opposite the blade identified in Step
3.B.(4)(o)(v)(2) of these Accomplishment Instructions with a
new blade that is less than the old blade by between 2,00 g
and 4,00 g. If the old blade has already been identified for
replacement, change the new blade for one which is between
2,00 g and 4,00 g less than the previously selected blade.
If this is not possible, replace the blade identified in Step
3.B.(4)(o)(v)(2) of these Accomplishment Instructions with a
new blade that is more than the old blade by between 2,00 g
and 4,00 g. If the old blade has already been identified for
replacement, change the new blade for one which is between
2,00 g and 4,00 g more than the previously selected new
blade.
(4) Repeat Step 3.B.(4)(o)(iv) of these Accomplishment
Instructions to check that the imbalance is less than 4,00
grams. If it is not, contact Rolls-Royce.
(p) Machine the replacement blades in accordance with FRSB777. (Refer to
Check and Rectify Manual Task 72-32-00-300-003). The replacement IP
compressor stage 1 root blade (72-32-32, 01-250) length must be as
follows:
(i) Shorter IP compressor stage 1 rotor blades (72-32-32, 01-250):
Airfoil tip leading edge permitted to be shorter than that of the
original blade by 0,25 mm, no more than two undersized blades
adjacent, any pair of undersized blades must be separated from the
next undersized blade by at least two normal blades.
(ii) Longer IP compressor stage 1 rotor blades (72-32-32, 01-250):
Airfoil tip leading edge of the blade permitted to be no longer
than 0,1 mm of the blade they replace.
(iii) Cropping the IP compressor stage 1 rotor blade (72-32-32,
01-250) by 0,5 mm will remove approximately 0,5 g of material.
When selecting a replacement blade make sure that it has
sufficient weight to allow removal of material to achieve the
target blade weight.
(iv) If it is not possible to accurately measure the length of the
blade to be replaced because of blade cracking, measure the
length of the blades either side of the blade to be replaced.
Machine the new blade to the average length of the two measured
blades.
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(q) Shot peen the roots of the IP compressor stage 1 rotor blades
(72-32-32, 01-250) that have not been replaced in accordance with
FRSB775 (CIR Task 72-32-32-300-032). Do not apply FRSB775 to new
blades.
NOTE: FRSB775 includes FRSB368 reapplication of Dry Film Lubricant
(DFL).
(r) Identify the IP compressor stage 1 rotor blades (72-32-32, 01-250),
refer to OP Task 70-00-00-300-363. Mark 160 within a triangle on the
same surface as the part number on all blades that have been subject
to FRSB775.
(s) Send the IP compressor stage 1 rotor blade (72-32-32, 01-250) set
weight details to the overhaul facility for balancing configuration.
(t) Weigh each of the IP compressor stage 2 rotor blades (72-32-32,
02-250) and record their weight using Appendix 2 - IP Compressor Stage
2 Blade Movement Tracking Form.
(u) Select new or SUM IP compressor stage 2 rotor blades (72-32-32,
02-250) to replace the IP compressor stage 2 rotor blades that have
been identified as requiring replacement. If SUM blades are used then
the SUM blades must have been inspected to Part 3.A Para (4) of this
NMSB; match the blade weight and tip height requirements (using
FRSB777 if required); and have been repaired using FRSB776. Using the
weight data recorded on Appendix 2 - IP Compressor Stage 2 Blade
Movement Tracking Form, choose blades closest to the original blade
weight.
CAUTION: THE TOTAL WEIGHT OF THE STAGE 2 ROTOR BLADES CANNOT BE
MORE THAN 6748,6 G (238.05 OZ). EXCEEDING THIS WEIGHT
MAY PUT EXCESSIVE STRESS ON THE ROTOR AND SUPPORT
STRUCTURE.
(i) If more than 6 IP Compressor stage 2 rotor blades need
replacing, do not continue Part 3.B. of this NMSB. Inform the
overhaul facility that Part 3.C. of this NMSB must be performed
instead.
(ii) The total weight of all replacement IP compressor stage 2 rotor
blades (72-32-32, 02-250) after cropping must be within plus or
minus 6,00 g of the total weight of all blades being replaced.
This is to be achieved in accordance with the following
conditions:
(1) If no more than 3 off IP compressor stage 2 rotor blades are
to be replaced - each replacement blade after cropping must
be within plus or minus 2,00 g of the blade being replaced.
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(2) If 4 off IP compressor stage 2 blades are to be replaced
each replacement blade after cropping must be within plus or
minus 1,50 g of the blade being replaced.
(3) If more than 4 off but not more than 6 off IP compressor
stage 2 rotor blades are to be replaced - each replacement
blade after cropping must be within plus or minus 1,00 g of
the blade being replaced.
(iii) If it is not possible to replace a blade in accordance with the
requirements above, then do the following:
(1) Identify the blade diametrically opposite the blade to be
replaced.
(2) Replace both blades with either new or SUM blades.  There
should be no more than 1,00 g difference between the changes
in blade weights of the diametrically opposite blades.
(iv) Calculate the total weight imbalance of the replaced blades:
NOTE: The following procedures may be automated in a spreadsheet
for ease and consistency of calculation.
NOTE: This method and formulae used are identical to those used
in NMSB 72-J871 Part B.
(1) Refer to Fig.5.
(2) For each blade being replaced, calculate the difference in
weight between the old and the new blades. Subtract the
weight of the new blade from the weight of the old blade.
Make a note of whether the weight difference is positive or
negative.
(3) For each blade being replaced, if the difference in blade
weight calculated in Step 3.B.(4)(u)(iv)(2) of these
Accomplishment Instructions is negative, do the following:
A From this point forward, use the absolute value for blade
weight difference by removing the negative sign.
B If the blade to be replaced is located at blade position
1 thru 24, add 24 to the blade position number. If the
blade to be replaced is located at blade position 25 thru
49, subtract 24 from the blade position number. This
calculation is performed to identify the blade position
opposite the blade being replaced.
C Use these new values for blade weight difference and
blade position in the following calculations.
Printed in Great Britain
TRENT 1000 72−K132
Page 26
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### Page 30

(4) Determine the angle of each replacement blade in relation to
blade number 1. There are 49 IP compressor stage 2 rotor
blades. Therefore the angle in degrees between blade 1 and
the blade to be replaced is calculated as:
(360 ÷ 49) x (Blade Number - 1)
Ensure that the new blade position calculated in Step
3.B.(4)(u)(iv)(3)B of these Accomplishment Instructions is
used if the difference in blade weight calculated in Step
3.B.(4)(u)(iv)(2) of these Accomplishment Instructions was
negative.
(5) Resolve the calculated weight difference into the x and
y-plane for each blade. The y-plane is in the orientation of
blade number 1. The x-plane is at 90 degrees to the y-plane.
A To calculate the weight difference in the x-plane,
multiply the weight difference by the Sine of the angle
calculated in Step 3.B.(4)(u)(iv)(4) of these
Accomplishment Instructions.
B To calculate the weight difference in the y-plane,
multiply the weight difference by the Cosine of the angle
calculated in Step 3.B.(4)(u)(iv)(4) of these
Accomplishment Instructions.
(6) Sum together the x-plane weight of each blade. You must take
into account the direction of the weight by using the
positive and negative denotations calculated in Step
3.B.(4)(u)(iv)(5) of these Accomplishment Instructions. Do
not convert the weights to absolute values.
(7) Sum together the y-plane weight of each blade. You must take
into account the direction of the weight by using the
positive and negative denotations calculated in Step
3.B.(4)(u)(iv)(5) of these Accomplishment Instructions. Do
not convert the weights to absolute values.
(8) Calculate the combined vector sum weight to provide the total
weight imbalance.
A Calculate the square of the x-plane weight calculated in
Step 3.B.(4)(u)(iv)(6) of these Accomplishment
Instructions.
B Calculate the square of the y-plane weight calculated in
Step 3.B.(4)(u)(iv)(7) of these Accomplishment
Instructions.
Printed in Great Britain
TRENT 1000 72−K132
Page 27
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### Page 31

C Sum the values calculated in Step 3.B.(4)(u)(iv)(8) A and
Step 3.B.(4)(u)(iv)(8) B of these Accomplishment
Instructions.
D Calculate the square root of the values calculated in
step 3.B.(4)(u)(iv)(8) C of these Accomplishment
Instructions.
(v) If the vector sum of the replaced blades calculated in Step
3.B.(4)(u)(iv)(8) D of these Accomplishment Instructions
produces an imbalance of 4,00 grams or more, do the following:
NOTE: The following procedure may be automated in a spreadsheet
for ease and consistency of calculation.
(1) Calculate the angle at which the imbalance acts in relation
to blade number 1.
A If the weight in the x-plane (calculated in Step
3.B.(4)(u)(iv)(6) of these Accomplishment Instructions)
is positive and the weight in the y-plane (calculated in
Step 3.B.(4)(u)(iv)(7) of these Accomplishment
Instructions) is positive, do the following calculation.
Ensure that the calculation is performed in Radians and
not degrees.
(INVTAN (X-Plane weight ÷ Y-Plane weight))
B If the weight in the x-plane (calculated in Step
3.B.(4)(u)(iv)(6) of these Accomplishment Instructions)
is positive and the weight in the y-plane (calculated in
Step 3.B.(4)(u)(iv)(7) of these Accomplishment
Instructions) is negative, do the following calculation.
Use the absolute values for the weights (remove the
negative sign from the y-plane weight). Ensure that the
calculation is performed in Radians and not degrees.
(INVTAN (Y-Plane weight ÷ X-Plane weight)) + (0.5 x PI)
C If the weight in the x-plane (calculated in Step
3.B.(4)(u)(iv)(6) of these Accomplishment Instructions)
is negative and the weight in the y-plane (calculated in
Step 3.B.(4)(u)(iv)(7) of these Accomplishment
Instructions is negative, do the following calculation.
Use the absolute values for the weights (remove the
negative signs from the x-plane weight and y-plane
weight). Ensure that the calculation is performed in
Radians and not degrees.
((INVTAN (X-Plane weight ÷ Y-Plane weight)) + PI
Printed in Great Britain
TRENT 1000 72−K132
Page 28
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SERVICE BULLETIN

### Page 32

D If the weight in the x-plane (calculated in Step
3.B.(4)(u)(iv)(6) of these Accomplishment Instructions)
is negative and the weight in the y-plane (calculated in
step 3.B.(4)(u)(iv)(7) of these Accomplishment
Instructions) is positive, do the following calculation.
Use the absolute values for the weights (remove the
negative sign from the x-plane weight). Ensure that the
calculation is performed in Radians and not degrees.
((INVTAN (Y-plane weight ÷ X-Plane weight)) + (1.5 x PI)
(2) Convert the calculated angle to a blade position.
A Divide the angle calculated in Step 3.B.(4)(u)(v)(1) of
these Accomplishment Instructions by 2 x PI.
B Multiply the answer from Step 3.B.(4)(u)(v)(2) A of these
Accomplishment Instructions by 49 (the number of IP
compressor stage 2 rotor blades). Add 1 to this answer
and round to the nearest whole number to define the blade
position.
(3) Replace the blade opposite the blade identified in Step
3.B.(4)(u)(v)(2) of these Accomplishment Instructions with a
new blade that is less than the old blade by between 2,00 g
and 4,00 g. If the old blade has already been identified for
replacement, change the new blade for one which is between
2,00 g and 4,00 g less than the previously selected new
blade.
If this is not possible, replace the blade identified in Step
3.B.(4)(u)(v)(2) of these Accomplishment Instructions with a
new blade that is more than the old blade by between 2,00 g
and 4,00 g. If the old blade has already been identified for
replacement, change the new blade for one which is between
2,00 g and 4,00 g more than the previously selected new
blade.
(4) Repeat Step 3.B.(4)(u)(iv) of these Accomplishment
Instructions to check that the imbalance is less than 4,00
grams. If it is not, contact Rolls-Royce.
Printed in Great Britain
TRENT 1000 72−K132
Page 29
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### Page 33

(v) Machine the replacement blades in accordance with FRSB777 (Refer to
Check and Rectify Manual Task 72-32-00-300-003). The replacement IP
compressor stage 2 rotor blade (72-32-32, 02-250) length must be as
follows:
(i) Shorter IP compressor stage 2 rotor blade (72-32-32, 02-250):
Airfoil tip leading edge permitted to be shorter than that of the
original blade by 0,25 mm, no more than two undersized blades
adjacent, any pair of undersized blades must be separated from the
next undersized blade by at least two normal blades.
(ii) Longer IP compressor stage 2 rotor blades (72-32-32, 02-250):
Airfoil tip leading edge of the blade not permitted to be longer
than the blade they replace.
(iii) Cropping the IP compressor stage 2 rotor blades (72-32-32,
02-250) by 0,5 mm will remove approximately 0,135 g of
material. When selecting a replacement blade make sure that it
has sufficient weight to allow removal of material to achieve
the target weight.
(iv) If it is not possible to accurately measure the length of the
blade to be replaced because of blade cracking, measure the
length of the blades either side of the blade to be replaced.
Machine the new blade to the average length of the two measured
blades.
(w) Shot peen the roots of the IP compressor stage 2 rotor blades
(72-32-32, 02-250) that have not been replaced in accordance with
FRSB776 (CIR Task 72-32-32-300-033). Do not apply FRSB776 to new
blades.
NOTE: FRSB776 includes FRSB368 reapplication of DFL.
(x) Identify the IP compressor stage 2 rotor blade (72-32-32, 02-250).
Refer to OP Task 70-00-00-300-363. Mark 160 within a triangle on the
same surface as the part number on all blades that have been subject
to FRSB776.
(y) Send the IP compressor stage 2 rotor blade (72-32-32, 02-250) set
weight details to the overhaul facility for balancing configuration.
NOTE: The following work is to be completed at an Overhaul Facility:
(5) Install the 49 off stage 2 blades.
(a) Use currently published engine manual procedures to install the IP
Compressor Stage 2 Blades (72-32-32, 02-250).
Printed in Great Britain
TRENT 1000 72−K132
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### Page 34

(b) The rotor slot and IP compressor stage 2 rotor blade serial numbers
are correlated. Use the blade correlation data recorded during blade
removal and recorded on Appendix 2 - IP Compressor Stage 2 Blade
Movement Tracking Form. They must be installed in these positions.
(c) Use the information recorded at disassembly to ensure the retaining
ring (72-32-32, 02-200) gap is positioned against the correct dovetail
slot.
(6) Install the 34 off stage 1 rotor blades (72-32-32, 01-250).
CAUTION: YOU MUST USE NEW STRAPS (EIPC 72-32-32, 01-275, 72-32-32,
01-285 OR 72-32-32, 01-0295) WHEN INSTALLING THE STAGE 1
BLADES OTHERWISE THE BLADES WILL NOT BE CORRECTLY INSTALLED.
CAUTION: YOU MUST USE A NON-METALIC DRIFT TO CLOSE THE GAP BETWEEN
THE STRAP AND THE RETAINING RING (72-32-32, 01-200) TO AVOID
DAMAGING THE IP COMPRESSOR ROTOR.
(a) Use currently published engine manual procedures to install the IP
Compressor Stage 1 rotor blades (72-32-32, 01-250).
(b) The rotor slot and IP compressor stage 1 rotor blade (72-32-32,
01-250) serial numbers are correlated. Use the blade correlation data
recorded during blade removal and recorded on Appendix 1: IP
Compressor Stage 1 Blade Movement Tracking Form. They must be
installed in these positions.
(c) The rotor slot and strap part numbers are correlated. Use the
correlated positions of the balance straps (72-32-32, 01-295) recorded
during IP compressor stage 1 rotor blade (72-32-32, 01-250) removal
and recorded in Appendix 1: IP Compressor Stage 1 Blade Movement
Tracking Form.
(d) Use the information recorded at disassembly to ensure the retaining
ring gap is positioned against the correct dovetail slot.
(7) Final Balance the IP Compressor Rotor Shaft
(a) Use currently published engine manual procedures to conduct a Final
Balance of the IP Compressor rotor shaft assembly.
(b) If the unbalance limit in plane FC cannot be achieved contact
Rolls-Royce.
(c) If the unbalance limit in plane RC limit cannot be achieved contact
Rolls-Royce.
Printed in Great Britain
TRENT 1000 72−K132
Page 31
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### Page 35

(8) Use currently published EM procedures to gain access to rebuild the
Engine.
CAUTION: YOU MUST ALIGN THE TEMPORARY CORRELATION MARK ON THE IP
COMPRESSOR ROTOR CURVIC CONE (72-32-31, 01-125) WITH THE
CORRESPONDING MARK ON THE IP COMPRESSOR REAR STUB SHAFT
(72-33-21, 01-250) LOCATION PIN (72-33-21, 01-325) OTHERWISE
THE ENGINE MAY SUFFER FROM EXCESSIVE IP VIBRATION AND BE
REJECTED WHEN TESTED.
(a) When installing the IP and LP Compressor Modules there are 4
alternative procedures published in the EM Vertical Build, Engine
Build Stand, Gantry Method ROT and Gantry Method TTL Tooling series.
(i) If installing the IP Compressor Module using the Gantry Method
TTL Tooling Series, Refer to RTV183155 until Dec.31/18.
(ii) If installing the LP Compressor Module and the LP Compressor
Retention Shaft using the Gantry Method TTL Tooling Series,
Refer to RTV183187 until Dec. 31/18.
(9) Record accomplishment of NMSB 72-K132 Part B at module level.
Using Appendix 1 and Appendix 2, record the IP compressor stage 1 rotor
blade (72-32-32, 01-250) and stage 2 rotor blade (72-32-32, 02-250) part
number, serial number and corresponding IP compressor drum dovetail slot
number and whether a new blade was fitted or whether a refurbished (in
accordance with the process in this NMSB) blade was installed in each disc
slot. Include Appendix 1 and Appendix 2 in the engine log book.
C. Part C - Replace all IP Compressor Stage 1 Rotor Blades and all Intermediate
Pressure (IP) Compressor Stage 2 rotor blades with new.
(1) Use currently published EM procedures to gain access to the IP Compressor
blades. Refer to Accomplishment Instructions Part 3.B.(1) of this NMSB.
Printed in Great Britain
TRENT 1000 72−K132
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### Page 36

(2) Disassemble the IP Compressor Rotor Assembly sufficiently to remove the IP
Compressor Stage 1 and Stage 2 Blades.
CAUTION: EXTREME CARE IS TO BE TAKEN TO NOT DAMAGE THE IP COMPRESSOR
DRUM AND THE STAGE 1 TO 2 AND STAGE 2 TO 3 SEAL FINS DURING
THE DISASSEMBLY PROCEDURE. DAMAGING CAN LEAD TO REJECTION OF
THE IP COMPRESSOR DRUM ASSEMBLY.
CAUTION: RATHER THAN LEAVING THE IP COMPRESSOR STUB SHAFT (72-32-31,
01-350) INSTALLED (WHICH IS THE PREFERRED METHOD), IT IS
ACCEPTABLE TO INSTALL THE DUMMY STUB SHAFT (RRT026842).
HOWEVER, INSTALLING THE DUMMY STUB SHAFT WILL RESULT IN AN
INCREASE IN TIME TO COMPLETE THIS PART OF THIS NMSB
(a) Use currently published EM procedures to remove the IP compressor
Stage 1 and Stage 2 Blades.
(b) When you remove the Stage 1 retaining ring (72-32-32, 01-200) record
the position of the gap in the retaining ring against the
corresponding disc slot.
(c) Remove and do not reuse the 25 off straps (72-32-32, 01-275) all the
nominal straps (72-32-32, 01-285) and all the balance straps
(72-32-32, 01-295).
(d) Visually inspect the Stage 1 blade roots for cracks. Measure any
cracks using an applicable metal ruler and record the results in
Appendix 3 - IP Compressor Stage 1 Blade Crack Recording Form.
Provide Appendix 3 to Rolls-Royce (U9505173@Rolls-Royce.com) through
your local Rolls-Royce Overhaul Support Team.
(e) When you remove the stage 2 retaining ring (72-32-32, 02-200) record
the position of the gap in the retaining ring against the
corresponding disc slot.
(f) Visually inspect the Stage 2 blade roots for cracks. Measure any
cracks using an applicable metal ruler and record the results in
Appendix 4 - IP Compressor Stage 2 Blade Crack Recording Form.
Provide Appendix 4 to Rolls-Royce (U9505173@Rolls-Royce.com) through
your local Rolls-Royce Overhaul Support Team.
(3) Carry Out Inspections of Specific IP Compressor Components. Refer to
Accomplishment Instructions Part 3.B.(3) of this NMSB.
(4) Find the installation sequence for the new sets of stage 1 IP compressor
rotor blades (72-32-32, 01-250) and stage 2 IP compressor rotor blades
(72-32-32, 02-250) that are to be installed in accordance with current
overhaul procedures (EM Task 72-32-30-440-801, Subtask
72-32-30-440-183-A00, for Pre SB72-H035; EM Task 72-32-30-440-801, Subtask
72-32-30-440-183-B00, Steps A thru C only, for Post SB72-H035).
Printed in Great Britain
TRENT 1000 72−K132
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### Page 37

(5) Install the IP compressor stage 1 and stage 2 rotor blades.
Install the 34 off stage 1 rotor blades in accordance with current
overhaul procedures. Use the information recorded at disassembly to ensure
the retaining ring gap is positioned against the correct dovetail slot.
CAUTION: YOU MUST USE NEW STRAPS (EIPC 72-32-32, 01-275, 72-32-32,
01-285 OR 72-32-32, 01-0295) WHEN INSTALLING THE STAGE 1
BLADES OTHERWISE THE BLADES WILL NOT BE CORRECTLY INSTALLED.
CAUTION: YOU MUST USE A NON-METALIC DRIFT TO CLOSE THE GAP BETWEEN
THE STRAP AND THE RETAINING RING (72-32-32, 01-200) TO AVOID
DAMAGING THE IP COMPRESSOR ROTOR.
(a) Use currently published engine manual procedures to install the IP
Compressor Stage 1 rotor blades (72-32-32, 01-250).
(b) Use the information recorded at disassembly to ensure the retaining
ring (72-32-32, 01-200) gap is positioned against the correct dovetail
slot.
(c) Use currently published engine manual procedures to install the IP
Compressor Stage 2 Blades (72-32-32, 02-250).
(d) Use the information recorded at disassembly to ensure the retaining
ring (72-32-32, 02-200) gap is positioned against the correct dovetail
slot.
(6) Use the currently published EM tasks to Balance the IP Compressor Rotor
group assembly and to perform the tip grinding operation on the stage 1
and stage 2 blades.
(7) Use currently published EM procedures to gain access to Rebuild the
Engine.
CAUTION: YOU MUST ALIGN THE TEMPORARY CORRELATION MARK ON THE IP
COMPRESSOR ROTOR CURVIC CONE (72-32-31, 01-125) WITH THE
CORRESPONDING MARK ON THE IP COMPRESSOR REAR STUB SHAFT
(72-33-21, 01-250) LOCATION PIN (72-33-21, 01-325) OTHERWISE
THE ENGINE MAY SUFFER FROM EXCESSIVE IP VIBRATION AND BE
REJECTED AT ENGINE TEST.
(a) When installing the IP and LP Compressor Modules there are 4
alternative procedures published in the EM Vertical Build, Engine
Build Stand, Gantry Method ROT and Gantry Method TTL Tooling series.
(i) If installing the IP Compressor Module using the Gantry Method
TTL Tooling Series, Refer to RTV183155 until Dec.31/18.
Printed in Great Britain
TRENT 1000 72−K132
Page 34
Jun.29/18
Jun.29/18
TRENT 1000 SERIES
SERVICE BULLETIN

### Page 38

(ii) If installing the LP Compressor Module and the LP Compressor
Retention Shaft using the Gantry Method TTL Tooling Series,
Refer to RTV183187 until Dec. 31/18.
(8) Record accomplishment of NMSB 72-K132 Part C at module level.
Using Appendix 1 and Appendix 2, record the IP compressor stage 1 rotor
blade (72-32-32, 01-250) and stage 2 rotor blade (72-32-32, 02-250) part
number, serial number and corresponding IP compressor drum dovetail slot
number and whether a new blade was fitted or whether a refurbished (in
accordance with the process in this NMSB) blade was installed in each disc
slot. Include Appendix 1 and Appendix 2 in the engine log book.
Printed in Great Britain
TRENT 1000 72−K132
Page 35
Jun.29/18
Jun.29/18
TRENT 1000 SERIES
SERVICE BULLETIN

### Page 39 (OCR)

Rolls-Royce  TRENT 1000 SERIES  SERVICE BULLETIN
7
Printed in Great Britain
dej0030973
VIGV and VSV Actuating Mechanism Assembly
Fig. 1
Jun. 29/18  TRENT 1000 72-K132
Jun.29/18  Page 36
© Rolls-Royce p/c

### Page 40

dej0030965
ZONE A
ZONE D
ZONE A
ZONE E
ZONE B
ZONE B
ZONE C
ZONE C
ZONE B
ZONE C
ZONE E
ZONE D
ZONE B
ZONE C
ZONE E
ZONE B
ZONE E
Disc dovetail inspection locations
Fig. 2
Printed in Great Britain
TRENT 1000 72−K132
Page 37
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SERVICE BULLETIN

### Page 41

dej0030966
NOTE:
All Chapter−Section−Subject and Fig−Item references
are quoted for the Engine IPC
CONCAVE AIRFOIL
SURFACE 3
ROOT RADIUS 4PLATFORM 6
GROOVE 5
TRAILING EDGE 8
AIRFOIL TIP 2
LEADING EDGE 1
CONVEX  AIRFOIL
SURFACE 7
A
DOVETAIL ROOT ZONE D
A
IP COMPRESSOR
STAGE 1 ROTOR BLADE
KH25729
72−32−32
01−250
IP Compressor Stage 1 Blade
Fig. 3
Printed in Great Britain
TRENT 1000 72−K132
Page 38
Jun.29/18
Jun.29/18
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SERVICE BULLETIN

### Page 42

dej0030967
A
A
LEADING EDGE 1
CONCAVE AIRFOIL
SURFACE 3
PLATFORM 6
FACE 9A
ROOT RADIUS 4
AIRFOIL TIP 2
FACE 9B
GROOVE 5
TRAILING
EDGE 8
CONVEX
AIRFOIL
SURFACE 7
IP Compressor Stage 2 blade inspection locations
Fig. 4
Printed in Great Britain
TRENT 1000 72−K132
Page 39
Jun.29/18
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### Page 43

dej0030968
BLADE No 1
BLADE POSITION ’A’
WEIGHT DIFFERENCE
IN THE Y−PLANE
BLADE POSITION ’A’
WEIGHT DIFFERENCE
IN THE X−PLANE
BLADE POSITION ’B’
WEIGHT DIFFERENCE
IN THE Y−PLANE
BLADE POSITION ’B’
WEIGHT DIFFERENCE
IN THE X−PLANE
BLADE POSITION ’C’
WEIGHT DIFFERENCE
IN THE Y−PLANE
BLADE POSITION ’C’
WEIGHT DIFFERENCE
IN THE X−PLANE
TOTAL WEIGHT DIFFERENCE IN THE Y−PLANE =
BLADE POSITION ’A’ WEIGHT DIFFERENCE
IN THE Y−PLANE + BLADE POSITION ’B’ WEIGHT
DIFFERENCE IN THE Y−PLANE + BLADE POSITION ’C’
WEIGHT DIFFERENCE IN THE Y−PLANE
TOTAL WEIGHT DIFFERENCE IN THE X−PLANE =
BLADE POSITION ’A’ WEIGHT DIFFERENCE
IN THE X−PLANE + BLADE POSITION ’B’ WEIGHT
DIFFERENCE IN THE X−PLANE + BLADE POSITION ’C’
WEIGHT DIFFERENCE IN THE X−PLANE
TOTAL WEIGHT IMBALANCE =
SQRT ((Total weight difference in the X−plane  )
+ (Total weight difference in the Y−plane  ))
Calculation of replacement blade imbalance
Fig. 5
Printed in Great Britain
TRENT 1000 72−K132
Page 40
Jun.29/18
Jun.29/18
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SERVICE BULLETIN

### Page 44

IP Compressor Stage 1 Blade Movement Tracking Form
APPENDIX 1
Printed in Great Britain
TRENT 1000 72−K132
Appendix 1 - Page 1 of 2
Jun.29/18
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SERVICE BULLETIN

### Page 45

dej0030969
BLADE
POSITION
BLADE PART
NUMBER
BLADE
SERIAL
NUMBER
REQUIRES
REPLACEMENT
WITH NEW.
ROOT FLANK
SURFACE
ROUGHNESS
(Micro metres)
BLADE
WEIGHT (g) LEADING
EDGE
CENTRE
POINT
TRAILING
EDGE
STRAP
TYPE
STRAP
WEIGHT (g)
BLADE HEIGHT (mm)
ESN: MODULE:
BLADES MOVEMENT FORM − REMOVED BLADES
1
2
3
4
5
6
7
8
9
10
11
12
13
14
15
16
17
18
19
20
21
22
23
24
25
26
27
28
29
30
31
32
33
34
ENTER NEW
SERIAL NUMBER
Printed in Great Britain
TRENT 1000 72−K132
Appendix 1 - Page 2
Jun.29/18
Jun.29/18
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SERVICE BULLETIN

### Page 46

IP Compressor Stage 2 Blade Movement Tracking Form
APPENDIX 2
Printed in Great Britain
TRENT 1000 72−K132
Appendix 2 - Page 1 of 2
Jun.29/18
Jun.29/18
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SERVICE BULLETIN

### Page 47

dej0030970
1
2
3
4
5
6
7
8
BLADE
POSITION
BLADE
PART
NUMBER
BLADE
SERIAL
NUMBER
REQIURES
REPLACEMENT
WITH NEW
SERIAL NUMBER
ROOT FLANK
SURFACE
ROUGHNESS
(Micro metres)
BLADE
WEIGHT (g) LEADING
EDGE
CENTRE
POINT
TRAILING
EDGE
BLADE HEIGHT (mm)
BLADE MOVEMENT FORM − REMOVED BLADES
ESN: MODULE:
9
10
11
12
13
14
15
16
17
18
19
20
21
22
23
24
25
26
27
28
29
30
31
32
33
34
35
36
37
38
39
40
41
42
43
44
45
46
47
48
49
Printed in Great Britain
TRENT 1000 72−K132
Appendix 2 - Page 2
Jun.29/18
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### Page 48

IP Compressor Stage 1 Blade Crack Recording Form
APPENDIX 3
Printed in Great Britain
TRENT 1000 72−K132
Appendix 3 - Page 1 of 2
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SERVICE BULLETIN

### Page 49

dej0030971
1
2
3
4
5
6
7
8
BLADE
POSITION
BLADE
PART
NUMBER
BLADE
SERIAL
NUMBER
BLADE ROOT
CRACK LENGTH
− FRONT FACE
BLADE CRACK RECORDING FORM
ESN: MODULE:
9
10
11
12
13
14
15
16
17
18
19
20
21
22
23
24
25
26
27
28
29
30
31
32
33
34
BLADE ROOT CRACK
LENGTH − FLANK
CONVEX AIRFOIL
SIDE (mm)
BLADE ROOT CRACK
LENGTH − FLANK
CONCAVE AIRFOIL
SIDE (mm)(mm)
BLADE ROOT
CRACK LENGTH
− REAR FACE
(mm)
Printed in Great Britain
TRENT 1000 72−K132
Appendix 3 - Page 2
Jun.29/18
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### Page 50

IP Compressor Stage 2 Blade Crack Recording Form
APPENDIX 4
Printed in Great Britain
TRENT 1000 72−K132
Appendix 4 - Page 1 of 2
Jun.29/18
Jun.29/18
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SERVICE BULLETIN

### Page 51

dej0030972
1
2
3
4
5
6
7
8
BLADE
POSITION
BLADE
PART
NUMBER
BLADE
SERIAL
NUMBER
BLADE ROOT
CRACK LENGTH
− FRONT FACE
BLADE CRACK RECORDING FORM
ESN: MODULE:
9
10
11
12
13
14
15
16
17
18
19
20
21
22
23
24
25
26
27
28
29
30
31
32
33
34
35
36
37
38
39
40
41
42
43
44
45
46
47
48
49
BLADE ROOT CRACK
LENGTH − FLANK
CONVEX AIRFOIL
SIDE (Face 9A) (mm)
BLADE ROOT CRACK
LENGTH − FLANK
CONCAVE AIRFOIL
SIDE (Face 9B) (mm)(mm)
BLADE ROOT
CRACK LENGTH
− REAR FACE
(mm)
Printed in Great Britain
TRENT 1000 72−K132
Appendix 4 - Page 2
Jun.29/18
Jun.29/18
TRENT 1000 SERIES
SERVICE BULLETIN

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