# Rolls-Royce Non-Modification Service Bulletin RB.211-72-G872

## Copies (2)

Copies the FAA filed in AD dockets on regulations.gov, newest revision first. A newer revision may exist.

- Revision 2 ("U.S. DOT/FAA - Service Bulletin - RB.211-72-G872 R2"), 61 pages: PDF https://openairdocs.org/files/sha256/31/12/3112596a0b5d615673dde91412bbd767794c0bb3e9c7fd4b069c5e916f21f443; text https://openairdocs.org/service-documents/rolls-royce/rb211-72-g872/file/3112596a0b5d.md. Rights: © Rolls-Royce plc. Filed by the FAA in regulations.gov docket FAA-2012-1327; AD 2013-12-01 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication.
- U.S. DOT/FAA - Service Information - 2 ("U.S. DOT/FAA - Service Information - 2"), 22 pages: PDF https://openairdocs.org/files/sha256/9b/f7/9bf7abef2499bced498b1405ebf0db79000b49e05260fe824baeb9f9bdc7799c; text https://openairdocs.org/service-documents/rolls-royce/rb211-72-g872/file/9bf7abef2499.md. Rights: © Rolls-Royce plc. Filed by the FAA in regulations.gov docket FAA-2012-1327; AD 2013-12-01 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication.

## Details

- Manufacturer: [Rolls-Royce](https://openairdocs.org/service-documents/rolls-royce.md)
- Type: Service bulletin (Non-Modification Service Bulletin)
- Number: RB.211-72-G872
- Latest revision known: RB.211-72-G872, Revision 2, dated March 8, 2013 (OpenAirDocs)
- Page: https://openairdocs.org/service-documents/rolls-royce/rb211-72-g872

## ADs that cite it (4) (OpenAirDocs)

Newest first, with the revision each names, as OpenAirDocs read it from the AD's text.

- [AD 2020-06-16](https://openairdocs.org/ad/2020-06-16.md), effective May 5, 2020: Revision 2
- [AD 2017-03-02](https://openairdocs.org/ad/2017-03-02.md), effective Mar 22, 2017: Revision 2
- [AD 2014-16-10](https://openairdocs.org/ad/2014-16-10.md), effective Sep 23, 2014: Revision 2
- [AD 2013-12-01](https://openairdocs.org/ad/2013-12-01.md), effective Jul 29, 2013: Revisions 1 and 2

Also cited in [2 proposed ADs](https://openairdocs.org/service-documents/rolls-royce/rb211-72-g872/proposed.md).

## Text (61 pages)

Revision 2, the newest copy. Rights: © Rolls-Royce plc. Filed by the FAA in regulations.gov docket FAA-2012-1327; AD 2013-12-01 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication. Some pages are OCR from a scan. OCR can misread letters and numbers. Each page's text from the PDF; open the PDF at a page with #page=N.

### Page 1

This document transmits Revision 2 to Service Bulletin RB211-72-G872
Document History
Service Bulletin Revision Status Supplement Revision Status
Initial Issue Apr.3/12
Revision 1 Jul.2/12
Bulletin Revision 2
Remove Incorporate Reason for change
Pages 1 to 19 of the
Service Bulletin
Pages 1 to 41 of the
Service Bulletin
To add an alternative
ultrasonic inspection as
sections 3.G. and 3.H.
Accomplishment
Instructions. Added
Appendices 2 thru 9 and
added Figures 5 thru 20.
Updated sections 1.B.
Reason, 1.C. Description,
1.D. Compliance, 1.E.
Approval, 1.H. Tooling
Price and Availability.
Minor editorial changes
also made.
Printed in Great Britain
Mar. 8/13
RB211 TRENT 700 SERIES PROPULSION SYSTEMS NON-MODIFICATION SERVICE BULLETIN
RB.211−72−G872
Transmittal - Page 1 of 5
Signed
 Date

### Page 2

All pages of
Appendix 1
Page 1 of Appendix 1 To add an alternative
ultrasonic inspection as
sections 3.G. and 3.H.
Accomplishment
Instructions. Added
Appendices 2 thru 9 and
added Figures 5 thru 20.
Updated sections 1.B.
Reason, 1.C. Description,
1.D. Compliance, 1.E.
Approval, 1.H. Tooling
Price and Availability.
Minor editorial changes
also made.
Page 1 of Appendix 2 To add an alternative
ultrasonic inspection as
sections 3.G. and 3.H.
Accomplishment
Instructions. Added
Appendices 2 thru 9 and
added Figures 5 thru 20.
Updated sections 1.B.
Reason, 1.C. Description,
1.D. Compliance, 1.E.
Approval, 1.H. Tooling
Price and Availability.
Minor editorial changes
also made.
Page 1 and 2 of
Appendix 3
To add an alternative
ultrasonic inspection as
sections 3.G. and 3.H.
Accomplishment
Instructions. Added
Appendices 2 thru 9 and
added Figures 5 thru 20.
Updated sections 1.B.
Reason, 1.C. Description,
1.D. Compliance, 1.E.
Approval, 1.H. Tooling
Price and Availability.
Minor editorial changes
also made.
Printed in Great Britain
RB.211−72−G872
Transmittal - Page 2

### Page 3

Page 1 of Appendix 4 To add an alternative
ultrasonic inspection as
sections 3.G. and 3.H.
Accomplishment
Instructions. Added
Appendices 2 thru 9 and
added Figures 5 thru 20.
Updated sections 1.B.
Reason, 1.C. Description,
1.D. Compliance, 1.E.
Approval, 1.H. Tooling
Price and Availability.
Minor editorial changes
also made.
Pages 1 to 3, 5 and
7 to 12 of Appendix
5
To add an alternative
ultrasonic inspection as
sections 3.G. and 3.H.
Accomplishment
Instructions. Added
Appendices 2 thru 9 and
added Figures 5 thru 20.
Updated sections 1.B.
Reason, 1.C. Description,
1.D. Compliance, 1.E.
Approval, 1.H. Tooling
Price and Availability.
Minor editorial changes
also made.
Printed in Great Britain
RB.211−72−G872
Transmittal - Page 3

### Page 4

LIST OF EFFECTIVE PAGES
The effective pages to this Service Bulletin following incorporation of Revision
2 are as follows:
Page Revision Number Revision Date
Bulletin
R     1 2 Mar.8/13
R     2 2 Mar.8/13
R     3 2 Mar.8/13
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R    37 2 Mar.8/13
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R    39 2 Mar.8/13
R    40 2 Mar.8/13
R    41 2 Mar.8/13
Appendix 1
R     1 2 Mar.8/13
Printed in Great Britain
RB.211−72−G872
Transmittal - Page 4

### Page 5

Appendix 2
R     1 2 Mar.8/13
Appendix 3
R     1 2 Mar.8/13
R     2 2 Mar.8/13
Appendix 4
R     1 2 Mar.8/13
Appendix 5
R     1 2 Mar.8/13
R     2 2 Mar.8/13
R     3 2 Mar.8/13
R     5 2 Mar.8/13
R     7 2 Mar.8/13
R     8 2 Mar.8/13
R     9 2 Mar.8/13
R    10 2 Mar.8/13
R    11 2 Mar.8/13
R    12 2 Mar.8/13
Printed in Great Britain
RB.211−72−G872
Transmittal - Page 5

### Page 6

1. Planning Information
A. Effectivity
Airbus A330
RB211 TRENT768-60, TRENT768-60/15, TRENT768-60/16 Engines
RB211 TRENT772-60, TRENT772-60/15, TRENT772-60/16 Engines
RB211 TRENT772B-60, TRENT772B-60/15, TRENT772B-60/16 Engines
RB211 TRENT772C-60/16 Engines
B. Reason
Problem
Following in-service Low Pressure (LP) compressor blade release events it is
recommended that an in-service inspection (ultrasonic)R is undertaken to
mitigate against release events. The ultrasonicR inspection is capable of
detecting sub-surface anomalies in the LP compressor blade aerofoil. AnR
inspection is already in place for Trent 700 LP compressor blades at every shop
visit but the intervals between shop visits is too large to only use shop visit
opportunities.
Revision 1 of this Non-Modification Service Bulletin (NMSB) wasR issued to add
an additional section into the Accomplishment Instructions for C-scan
inspection of LP compressor blades, removed from am engine on-wing undertaken
in an overhaul facility where serviceability restoration wasR required. In
addition, Section 1.D. Compliance wasR updated to clearly define what LP
compressor blades wereR affected by this NMSB and which inspections were to be
claimed.
Revision 2 of this NMSB is to add an alternative ultrasonic inspection
technique, phased array. Two additional sections have been added into 3.
Accomplishment Instructions for the phased array inspection of LP compressor
blades, one for LP compressor blades installed on an engine, the other for LP
compressor blades removed from an engine on-wing.
R
R
R
R
R
C. Description
(1) This Non-Modification Service Bulletin (NMSB) isR issued to instruct an
ultrasonic
R
R inspection of LP compressor blades aerofoil.
(a) Accomplishment of this NMSB must be recorded against the individual
blades.
ENGINE - LP COMPRESSOR - INSPECTION OF LP COMPRESSOR BLADES - NON-MODIFICATION
SERVICE BULLETIN - NON - MOD.72-G872
Printed in Great Britain
RB.211−72−G872
Page 1 of 41
Apr. 3/12
Mar. 8/13R

### Page 7

(b) Inform your assigned Rolls-Royce Service Representative of NMSB
accomplishment.
(2) The Accomplishment Instructions for ultrasonicR inspection of removed LP
compressor blades is dependent on where the inspection is undertaken as
follows:
(a) Accomplishment instructions for C-scan inspection of LP compressor
blades, removed from an engine on-wing, undertaken by the operator
locally, refer to Section 3. C.
(b) Accomplishment instructions for C-scan inspection of LP compressor
blades, removed from an engine on-wing, undertaken in an overhaul
facility, refer to Section 3. D.
(c) Accomplishment instructions for C-scan inspection of LP compressor
blades, removed from an engine in-shop, refer to Section 3. E.
(d) Accomplishment Instructions for C-scan inspection of LP compressor
blades, removed from an engine on-wing undertaken in an overhaul
facility where serviceability restoration is required, refer to
Section 3.F.
(e) Accomplishment Instructions for phased array inspection of LP
compressor blades installed on an engine. Refer to Section 3.G.
R
R
(f) Accomplishment Instructions for phased array inspection of LP
compressor blades removed from an engine on-wing. Refer to Section
3.H.
R
R
R
D. Compliance
RECOMMENDED
Rolls-Royce recommends that the following action is undertaken to maintain
reliability.
This Non-Modification Service Bulletin should be accomplished by 30th June
2013, on all LP compressor blade standards with a life greater than 3,000
cycles since new or since last C-scan inspection on 30th June 2013.
NOTE: If an operator finds it convenient to inspect LP compressor blades
earlier than 3,000 cycles, then inspection in accordance with this
Non-Modification Service Bulletin can be accredited provided the life of
the LP compressor blades are at least 2,000 cycles from new.
NOTE: LP compressor blades previously inspected in-shop in accordance with
Engine Manual or to NMSB 72-G702 can be accredited against this
Non-Modification Service Bulletin at any life of LP compressor blade.
Printed in Great Britain
RB.211−72−G872
Page 2
Apr. 3/12
Mar. 8/13R

### Page 8

E. Approval
The technical content of this Non-Modification Service Bulletin was approved
under the authority of Design Organisation Approval EASA.21J.035 on Apr.2/12,
Jul.2/12
R
R and was re-approved on Mar.8/13.
F. Manpower
On-wing:
(1) Time to remove LP compressor blades:
3 hours per LP compressor blade set (2 persons)
(2) Time to inspect LP compressor blades:
(a) Visual inspection - 4 hours per LP compressor blade set (1 person)
(b) C-scan inspection - 28 hours per LP compressor blade set (1 person)
(c) Phased array inspection - 12 hours per LP compressor blade set (1
person)
R
R
NOTE: The Phased Array ultrasonic inspection defined in Section 3.
Accomplishment Instructions must be performed by personnel
qualified to ultrasonic inspection level 2 or higher in
accordance with EN4179/NAS-410 or alternative
standard/guidelines accepted by the applicable National
Aviation Authority.
R
R
R
R
R
R
Additionally, all inspection personnel utilising this technique
must have received specific training and approval by the
Rolls-Royce NDE Laboratory.
R
R
R
(3) Time to install LP compressor blades:
3 hours per LP compressor blade set (2 persons)
NOTE: A vibration ground run will be required.
G. Material Price and Availability
None.
Printed in Great Britain
RB.211−72−G872
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Apr. 3/12
Mar. 8/13R

### Page 9

H. Tooling Price and Availability
(1) Tooling for LP compressor blade inspection:
Tool No.R DescriptionR QtyR
RR1024167R Single head ultrasonic
immersion system
R
R
1 offR
QC6808R Single head calibration
blade
R
R
1 offR
M403TR Triple head ultrasonic
immersion system
R
R
1 offR
HU82364R Triple head calibration
blade
R
R
1 offR
RRT076133R Phased array inspection
kit
R
R
1 offR
RRT076135R Fan blade holderR 1 offR
(2) Consumable Materials:R
Consumable No.R DescriptionR
OMat 655R Ultrasonic CouplantR
I. References
(1) Rolls-Royce RB211 Non-Modification Service Bulletin:
72-G702
Engine - LP Compressor - Inspection of LP Compressor Blades -
Non-Modification Service Bulletin
Printed in Great Britain
RB.211−72−G872
Page 4
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Mar. 8/13R

### Page 10

(2) Aircraft Maintenance Manual (AMM):
(a) 72-00-00, Test No.11 The Engine Vibration Survey
(b) Task 70-20-01-100-802, Non-Aqueous Liquid Degreasing - Maintenance
Process 101
(c) 72-31-41, Removal/Installation of LP Compressor Blades and Dampers
(d) Task 72-31-41-200-801, Inspection/Check
(e) 72-31-41, LP Compressor Rotor Blade - Re-apply the Dry Film Lubricant
(FRSA031)
(f) 72-31-51, LP Compressor Disc - Re-apply the Dry Film Lubricant
(FRSA017)
(3) Engine Manual (EM):
(a) Task 70-00-00-100-102, Overhaul Process 102, Primary Cleaning -
Aqueous (TSD594J)
(b) Task 72-31-11-100-801, Clean the Low Pressure (LP) Compressor Blades
(c) Task 72-31-11-200-806, C-Scan Inspection of the Low Pressure (LP)
Compressor Blades for Sub-Surface Cracks
Printed in Great Britain
RB.211−72−G872
Page 5
Apr. 3/12
Mar. 8/13R

### Page 11

2. Material Information
A. None
Printed in Great Britain
RB.211−72−G872
Page 6
Apr. 3/12
Mar. 8/13R

### Page 12

3. Accomplishment Instructions
A. Identify recipient engine for ultrasonicR inspected LP Compressor blades to make
sure blades do not continue in-service greater than 6000 cycles before
refurbishment. See Fig.1.
B. Accomplishment Instructions for Removal and Installation of LP Compressor
Blades.
CAUTION: IN ORDER TO REDUCE THE POTENTIAL FOR MULTIPLE ENGINE IN FLIGHT SHUTDOWN,
POWER LOSS OR OTHER ANOMALIES  DUE TO MAINTENANCE ERROR, ROLLS-ROYCE
RECOMMENDS THAT OPERATORS AVOID PERFORMING MAINTENANCE ON MULTIPLE
ENGINES INSTALLED ON THE SAME AIRCRAFT AT THE SAME TIME. IF IT IS NOT
POSSIBLE TO AVOID MAINTENANCE ON MORE THAN ONE ENGINE AT THE SAME TIME,
ROLLS-ROYCE RECOMMENDS THAT ADDITIONAL CONTROLS ARE APPLIED IN ORDER TO
ENSURE THAT MAINTENANCE TASKS HAVE BEEN COMPLETED AS DEFINED.
MAINTENANCE GUIDELINES SHOULD BE REVISED, WHERE POSSIBLE, TO PROMOTE
THIS RECOMMENDATION.
(1) Remove LP Compressor blades:
(a) Remove the applicable LP compressor blades in accordance with AMM
72-31-41, Removal/Installation.
(2) Visually inspect the LP compressor blades in accordance with AMM Task
72-31-41-200-801, Inspection/Check.
(3) Send removed LP compressor blades for ultrasonicR inspection.
(4) Re-apply the dry film lubricant to the replacement LP compressor blade
roots in accordance with AMM Task 72-31-41-300-802 (FRSA031).
(5) Re-apply the dry film lubricant to the LP compressor disc in accordance
with AMM Task 72-31-51-300-801 (FRSA017).
(6) Install the replacement LP compressor blades in accordance with AMM
72-31-41, Removal/installation.
(7) Restore the engine to serviceable condition in accordance with AMM
72-31-41, Removal/Installation.
Printed in Great Britain
RB.211−72−G872
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### Page 13

(8) Carry out vibration survey in accordance with AMM, 71-00-00, Test No.11,
The Engine Vibration Survey.
NOTE: If an engine trim balance is undertaken, then the post balance
vibration survey may be waived provided the trim balance have been
accomplished using Rolls-Royce balancing software VX77 and no more
than 6 trim balance bolts have been added/removed. If further
engine running is not undertaken then engine LP vibration should be
monitored for the next 10 days.
(9) If replacement LP compressor blades have been ultrasonically inspected by
C-scan or phased array then accomplishment of NMSB 72-G872 must be
recorded against the individual blades and compliance, blade serial
numbers and associated lives (TSN/CSN) logged with the local FSO.
R
R
R
R
C. Accomplishment Instructions for C-scan inspection of LP Compressor Blades,
removed from an Engine On-Wing, undertaken by the Operator locally.
(1) Clean the LP compressor blades.
(a) Clean the LP compressor blades in accordance with AMM Task
70-20-01-100-802 (Non-Aqueous Liquid Degreasing (Maintenance Process
101))
(b) If there is the presence of Dry Film Lubricant (DFL) in the LP
compressor blade aerofoil, mask the LP compressor blade root and clean
as follows:
CAUTION: TO MAINTAIN THE CLEANLINESS OF THE WIPING SOLVENT, YOU
MUST POUR THE SOLVENT ONTO THE WIPING CLOTH. THE CLOTH
MUST NOT BE DIPPED INTO THE SOLVENT CONTAINER.
(i) Apply the solvent to the area to be cleaned using an OMat 2/101
lint-free cloth moistened with either OMat 150 Acetone, OMat
1/40 Isopropyl alcohol. Discard the soiled cloth after use.
(ii) Repeat the swabbing using fresh cloth and solvent until the
area is clean and free of DFL.
(iii) Allow the parts to dry. Drying may be assisted by removing
excess solvent using a clean dry lint-free cloth (Material No.
OMat 2/101) or a clean oil-free air blast to help dry the part.
(iv) Remove masks from the LP compressor blade root.
(2) Option 1: Carry out C-scan inspection of LP compressor blades - Single
head C-Scan equipment
R
R
(a) Special Tools:
Printed in Great Britain
RB.211−72−G872
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### Page 14

RR1024167 Single head ultrasonic
immersion system
R
R
1 off
QC6808 Single head
calibration blade
R
R
1 off
NOTE: The tools specified are the minimum standard for this Task.
(b) Calibrate the C-Scan Equipment:
(i) Switch the equipment on and allow the system to warm up for 30
minutes.
(ii) Enter operator details and log on to the system.
(iii) Check the probe is aligned:
(1) Place a ruler on the front face of the probe holder.
(2) Check the ruler is parallel to the end of the tank.
(3) If the ruler is not parallel to the end of the tank, loosen
the grub screw on the holder and align the holder; tighten
the grub screw.
CAUTION: YOU MUST DO THE OPERATION THAT FOLLOWS WITH THE PROBE
PUT FULLY INTO THE LIQUID IN THE TANK
(iv) Remove the probe from the probe holder and carefully wipe the
face of the probe to remove any air bubbles, install the probe
to the probe holder again.
(v) Select the CALIBRATE icon on the control screen.
(vi) Install the QC6808 calibration blade 1 off.
(vii) Scan the calibration blade.
NOTE: The system will scan the calibration blade and self analyse
the C-scan. The system then corrects the reject level to
adjust for any change in the system sensitivity.
(viii) Set the BLADE TYPE box on the control screen to 'Calibrate
Blade' and type test in the SERIAL NUMBER box.
Printed in Great Britain
RB.211−72−G872
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Mar. 8/13R

### Page 15

(ix) Re-scan the calibration blade.
(1) The threshold values will be displayed on screen. Make a
written record in a historical log.
NOTE: The calibration blade will be rejected by the second
scan. Do not archive the calibration scan results.
(x) Use the scan results to find the action necessary from the
table that follows:
NUMBER OF DEFECTS CHECK ACTION
More than four N/A Do steps (v) to (ix)
again. Inspect again
any blade which
failed since the
last calibration
check
Two at the top of
the panel and two at
the bottom
If the WEIGHTING of
one of the two
smallest defects is
seven or more
Do steps (v) to (ix)
again. Inspect again
any blade which
failed since the
last calibration
check
Two at the top of
the panel and two at
the bottom
If the WEIGHTING of
one of the two
smallest defects are
both less than seven
Continue the
procedure
Two at the top of
the panel and one at
the bottom
N/A Continue the
procedure
One at the top of
the panel and two at
the bottom
N/A Continue the
procedure
Printed in Great Britain
RB.211−72−G872
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### Page 16

One at the top of
the panel and one at
the bottom
N/A Continue the
procedure
None of the above N/A Do steps (v) to (ix)
again. Inspect again
all the work since
the last calibration
check
(xi) At 4 hour intervals, install the calibration blade and do steps
(viii) to (x) to make sure the equipment is in the calibration
limits.
(c) Focus Inspect the LP compressor blades:
(i) Set the BLADE TYPE box on the control screen to 'Trent 700
full'.
(ii) Record the details of the blade to be scanned, PART NUMBER,
SERIAL NUMBER, ENGINE/MODULE NUMBER, HOURS and CYCLES on the
control screen.
(iii) Install the LP compressor blade to be scanned.
(iv) Scan the LP compressor blade.
NOTE: When the scan is complete, the system will automatically
accept or reject the blade. Scan results from any blade
rejected by the system must be archived as given on the
control screen.
(v) Do steps (i) to (iv) for the remaining blades.
(vi) When the inspection is completed, install the QC6808
calibration blade 1 off and do steps (b)(viii) to (x) again.
(d) Data retrieval
(i) The inspection system records the inspection records in a text
file named scanlog.txt. This file gives the PART NUMBER, SERIAL
NUMBER, ENGINE/MODULE NUMBER, DATE INSPECTED and INSPECTION
RESULT.
Printed in Great Britain
RB.211−72−G872
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### Page 17

(ii) If a blade is rejected, the system prompts the archive of a
blade C-Scan data to an archive directory, where it is stored
with the blade serial number as the file name. Inspection and
blade data should be entered on the LP compressor blade
rejection proforma (Appendix 1) and returned to Rolls-Royce
with a copy of the archived scan data.
(3) Option 2: Carry out C-scan inspection of LP compressor blades - Triple
head C-Scan equipment
R
R
(a) Special Tools:R
M403TR Triple head ultrasonic
immersion system
R
R
1 offR
HU82364R Triple head
calibration blade
R
R
1 offR
NOTE: The tools specified are the minimum standard for this Task.R
(b) Calibrate the C-Scan Equipment:R
(i) Switch on the system and allow to warm up for 10 minutes.R
(ii) Enter operator details and log on to the system.R
(iii) Check that the front face of the probe holder is parallel to
the end of the tank by placing a ruler on the front face of the
holder and comparing to the end of the tank. If it is not
parallel, loosen the grub screw and re-position the holder to
correct the error.
R
R
R
R
R
(iv) Check for air bubbles on the probe faces by wiping the probe
faces with a soft brush whilst the probes are immersed.
R
R
(v) Select the calibrate icon from the presented menu. The system
will prompt the user to load the calibration blade.
R
R
(vi) Load the calibration blade HU82364.R
(vii) Click OK and the system will scan the calibration blade
(HU82364) and analyse the result. The sytem will then
automatically correct the threshold readings to compensate for
any variation in sensitivity. Record the thresholds in a
historical log.
R
R
R
R
R
(viii) Type TEST in the blade serial number box and select TRENT
CALIBRATION BLADE.from the blade type drop down menu.
R
R
Printed in Great Britain
RB.211−72−G872
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Apr. 3/12
Mar. 8/13R

### Page 18

(ix) Scan the calibration blade again. The system will then reject
the calibration blade.
R
R
NOTE: Do not archive this scan result.R
(x) Check the results of the calibration scan meet the following
criteria:
R
R
(1) Make sure that the results for each probe (Near, Middle and
Far) reveal one indication below fifty percent scan height
and atleast one indication above fifty percent scan height.
R
R
R
(2) Individual indications below fifty percent scan height shall
be in the range of 5 to 15 inclusive.
R
R
(3) If more than one indication per channel exists above fifty
percent scan height then the largest indication shall be
regarded as the primary indication and this primary
indication shall be in the range of 5 to 15 inclusive.
R
R
R
R
(4) If the above criteria are not fulfilled then repat steps 3 to
10 inclusive.
R
R
(5) Record the results in a historical log:R
NOTE: The calibration standard HU82364 is only corrosion
resistant. After use make sure that the calibration
blade is thoroughly dried to prevent pitting. Do not
leave the calibration blade in the tank for periods of
more than one hour.
R
R
R
R
R
(xi) Every eight hours repeat steps (vii) to (ix) inclusive to make
sure the system has not drifted. Failure to meet the
requirements of step (ix) will necessitate rescanning of all
blades scanned since the last satisfactory check.
R
R
R
R
(c) Focus inspect the LP compressor blades:R
(i) Select the fan blade standard to be inspected from the drop
down menu.
R
R
NOTE: The correct scan program for Trent blades is always
suffixed by the letter A e.g. T700A.
R
R
(ii) Enter details of the blade to be inspected: SERIAL NUMBER, PART
NUMBER, ENGINE NUMBER, HOURS and CYCLES.
R
R
(iii) Click SCAN and the screen will prompt the operator to load the
blade. This action also disengages the motors to allow for easy
blade loading.
R
R
R
Printed in Great Britain
RB.211−72−G872
Page 13
Apr. 3/12
Mar. 8/13R

### Page 19

(iv) Click OK and the system will automatically scan and sentence
the blade as accept or reject.
R
R
NOTE: When the scan is complete, the system will automatically
accept or reject the blade. Scan results from any blade
rejected by the system must be ARCHIVED as given on the
control screen.
R
R
R
R
(v) If the blade is accepted then continue as per steps (ii) to
(iv).
R
R
(vi) If the blade is rejected then the scan must be ARCHIVED as
prompted.
R
R
(d) Data retrievalR
(i) The inspection system records the inspection records in a text
file named scanlog.txt. This file gives the PART NUMBER, SERIAL
NUMBER, ENGINE/MODULE NUMBER, DATE INSPECTED and INSPECTION
RESULT.
R
R
R
R
(ii) If a blade is rejected, the system prompts the archive of a
blade C-Scan data to an archive directory, where it is stored
with the blade serial number as the file name. Inspection and
blade data should be entered on the LP compressor blade
rejection proforma (Appendix 1) and returned to Rolls-Royce
with a copy of the archived scan data.
R
R
R
R
R
R
(4) Let the LP compressor blades become dry:
(a) Use a clean dry lint-free cloth (Material No. OMat 2/101) or a clean
oil-free air blast to help dry the part.
(5) Accomplishment of NMSB 72-G872 must be recorded against the individual
blades and compliance, blade serial numbers and associated lives (TSN/CSN)
logged with the local FSO.
R
R
R
D. Accomplishment Instructions for C-scan inspection of LP Compressor Blades,
removed from an Engine On-Wing, undertaken in an Overhaul Facility.
(1) Clean the LP compressor blades:
(a) Clean the LP compressor blades in accordance with EM Task
72-31-11-100-801, Subtask 72-31-11-110-006-001 (non-aqueous vapour and
liquid degreasing OP Task 70-00-00-100-101) or Subtask
72-31-11-110-006-002 (primary clean OP Task 70-00-00-100-102, Subtask
70-00-00-110-102-001).
Printed in Great Britain
RB.211−72−G872
Page 14
Apr. 3/12
Mar. 8/13R

### Page 20

(b) If there is the presence of Dry Film Lubricant (DFL) in the LP
compressor blade aerofoil, mask the LP compressor blade root and clean
as follows:
CAUTION: TO MAINTAIN THE CLEANLINESS OF THE WIPING SOLVENT, YOU
MUST POUR THE SOLVENT ONTO THE WIPING CLOTH. THE CLOTH
MUST NOT BE DIPPED INTO THE SOLVENT CONTAINER.
(i) Apply the solvent to the area to be cleaned using an OMat 2/101
lint free cloth moistened with either OMat 150 Acetone, OMat
1/40 Isopropyl alcohol. Discard the soiled cloth after use.
(ii) Repeat the swabbing using fresh cloth and solvent until the
area is clean and free of DFL.
(iii) Allow the parts to dry. Drying may be assisted by removing
excess solvent using a clean dry lint-free cloth (Material No.
OMat 2/101) or a clean oil-free air blast to help dry the part.
(iv) Remove masks from the LP compressor blade root.
(2) Carry out C-scan inspection of LP compressor blades.
(a) Carry out C-scan inspection of LP compressor blades in accordance with
EM Task 72-31-11-200-806.
(b) If a blade is rejected by the C-scan inspection, inspection and blade
data should be entered on the LP compressor blade rejection proforma
(Appendix 1) and returned to Rolls-Royce with a copy of the archived
scan data.
(3) Dry LP compressor blades.
(a) Dry LP compressor blades in accordance with EM Task 70-00-00-100-102,
Subtask 70-00-00-110-102-007.
(4) Accomplishment of NMSB 72-G872 must be recorded against the individual
blades and compliance, blade serial numbers and associated lives (TSN/CSN)
logged with the local FSO.
R
R
R
E. Accomplishment Instructions for C-scan inspection of LP Compressor Blades,
removed from an Engine In-Shop.
(1) C-scan inspection is required on all LP compressor blades installed on an
engine subject to a shop visit in accordance with EM Task
72-31-11-200-806.
(2) Accomplishment of NMSB 72-G872 must be recorded against the individual
blades and compliance, blade serial numbers and associated lives (TSN/CSN)
logged with the local FSO.
R
R
R
Printed in Great Britain
RB.211−72−G872
Page 15
Apr. 3/12
Mar. 8/13R

### Page 21

F. Accomplishment Instructions for C-scan inspection of LP Compressor Blades,
removed from an Engine On-Wing, undertaken in an Overhaul Facility where
serviceability restoration is required.
(1) Clean the LP compressor blades:
(a) Clean the LP compressor blades in accordance with EM Task
72-31-11-100-801, Subtask 72-31-11-110-006-001 (non-aqueous vapour and
liquid degreasing OP Task 70-00-00-100-101) or Subtask
72-31-11-110-006-002 (primary clean OP Task 70-00-00-100-102, Subtask
70-00-00-110-102-001).
(b) If there is the presence of Dry Film Lubricant (DFL) in the LP
compressor blade aerofoil, mask the LP compressor blade root and clean
as follows:
CAUTION: TO MAINTAIN THE CLEANLINESS OF THE WIPING SOLVENT, YOU
MUST POUR THE SOLVENT ONTO THE WIPING CLOTH. THE CLOTH
MUST NOT BE DIPPED INTO THE SOLVENT CONTAINER.
(i) Apply the solvent to the area to be cleaned using an OMat 2/101
lint free cloth moistened with either OMat 150 Acetone, OMat
1/40 Isopropyl alcohol. Discard the soiled cloth after use.
(ii) Repeat the swabbing using fresh cloth and solvent until the
area is clean and free of DFL.
(iii) Allow the parts to dry. Drying may be assisted by removing
excess solvent using a clean dry lint-free cloth (Material No.
OMat 2/101) or a clean oil-free air blast to help dry the part.
(iv) Remove masks from the LP compressor blade root.
(2) Visually inspect LP compressor blades. Refer to Fig.2, Fig.3 and Fig.4 for
details.
NOTE: It is normal to see the panel lines on the airfoil surfaces near
the tip of the LP compressor fan blades. This is not an indication
of rippling caused by LP compressor fan blade damage.
(a) Examine the blade aerofoil for rippling:
(i) If the blade has ripples up to 0.16 mm (0.006 in.) in depth
(minor ripples within the manufacturing specification) - Accept
the blade.
(ii) If the blade has one or more ripples of any length with a form
more than in step above - Reject the blade.
Printed in Great Britain
RB.211−72−G872
Page 16
Apr. 3/12
Mar. 8/13R

### Page 22

(b) Examine the blade airfoil surfaces for cracks:
(i) If the blade is cracked - Reject the blade.
(c) Examine the blade tips and the airfoil surfaces for blueing or heat
discoloration.
(i) If there is blueing or heat discoloration on the blade tips and
on the airfoil surfaces up to 0.26 in. (6.5 mm) from the blade
tip - Accept the blade.
(d) If there is blueing or heat discoloration more than limit given above
- Reject the blade.
(e) Examine the blade surfaces for arc-burns.
(i) If the blade shows signs of arc-burns - Reject the blade.
(f) Examine the blades concave and convex airfoil surfaces for nicks.
(i) If the blade has nicks in the airfoil surfaces above the
annulus line and up to 0.008 in. (0.2 mm) in depth - Accept the
blade.
(ii) If the blade has nicks in the airfoil surfaces above the
annulus line more than the limit given above - Reject the
blade.
(iii) If the blade has nicks in the airfoil surfaces below the
annulus line - Reject the blade.
(g) Examine the blade forward edge for nicks from 4.75 in. (120.65 mm)
radially away from the annulus filler outer profile to the blade tip.
(i) If the blade has nicks up to 0.025 in. (0.64 mm) in depth -
Accept the blade.
(ii) If the blade has nicks more than the limit given above - Reject
the blade.
(h) Examine the blade root and forward edge for nicks up to 4.75 in.
(120.65 mm) radially away from the annulus filler outer profile.
(i) If the blade has nicks up to 0.008 in. (0.2 mm) in depth -
Accept the blade.
(ii) If the blade has nicks more than the limit given above - Reject
the blade.
Printed in Great Britain
RB.211−72−G872
Page 17
Apr. 3/12
Mar. 8/13R

### Page 23

(i) Examine the blade forward and rear edges for bends:
(i) Blade bends - General.
(1) The maximum number of bent blades in the LPC rotor assembly
must not be more than three.
(2) If there are more than one bend in a blade - Reject the
blade.
(3) If a bend in a blade is not smooth or has kinks, creases,
tears, cracks or nicks - Reject the blade.
(4) If there is blade untwist - Reject the blade.
(ii) Accept bends with a circumferential deflection (X) not more
than a maximum of 0.197 in. (5 mm) but only if:
(1) The axial bend, dimension (Y) is more than eight times the
circumferential bend, dimension (X). If the axial bend,
dimension (Y) is less than eight times the circumferential
bend, dimension (X) - Reject the blade.
(2) The radial bend, dimension (Z) is more than 15 times the
circumferential bend, dimension (X). If the radial bend,
dimension (Z) is less than 15 times the circumferential bend,
dimension (X) - Reject the blade.
(3) The bend does not extend into the panel area. If the bend
extends into the panel area - Reject the blade.
(iii) If the circumferential deflection (X) is more than 0.197 in. (5
mm), but not more than 0.492 in. (12.5 mm), accept the blade
but only if:
(1) The axial bend, dimension (Y) is more than eight times the
circumferential bend, dimension (X). If the axial bend,
dimension (Y) is less than eight times the circumferential
bend, dimension (X) - Reject the blade.
(2) The radial bend, dimension (Z) is more than 15 times the
circumferential bend, dimension (X). If the radial bend,
dimension (Z) is less than 15 times the circumferential bend,
dimension (X) - Reject the blade.
(iv) If the bend is more than the limits given above - Reject the
blade.
Printed in Great Britain
RB.211−72−G872
Page 18
Apr. 3/12
Mar. 8/13R

### Page 24

(j) Examine the blade airfoil for wear from the annulus filler seal:
(i) If the blade has galling up to 0.005 in. (0.13 mm) deep on the
convex side caused by the annulus filler seal - Accept the
blade.
(ii) If the blade has galling more than the limit given above -
Reject the blade.
(3) Carry out C-scan inspection of LP compressor blades.
(a) Carry out C-scan inspection of LP compressor blades in accordance with
EM Task 72-31-11-200-806.
(b) If a blade is rejected by the C-scan inspection, inspection and blade
data should be entered on the LP compressor blade rejection proforma
(Appendix 1) and returned to Rolls-Royce with a copy of the archived
scan data.
(4) Dry LP compressor blades.
(a) Dry LP compressor blades in accordance with EM Task 70-00-00-100-102,
Subtask 70-00-00-110-102-007.
(5) Accomplishment of NMSB 72-G872 must be recorded against the individual
blades and compliance, blade serial numbers and associated lives (TSN/CSN)
logged with the local FSO.
R
R
R
G. Accomplishment Instructions for phased array inspection of LP Compressor Blades
installed on an Engine.
R
R
CAUTION: IT IS THE RESPONSIBILITY OF THE OPERATOR /USER TO OBTAIN DETAILED HEALTH
AND SAFETY DATA FOR THE MATERIALS IN USE AND TO REFER TO LOCAL
REGULATIONS TO ENSURE SAFE WORKING PRACTICE.
R
R
R
(1) Visually inspect LP compressor blades in accordance with AMM Task
72-31-41-200-801, Inspection/Check.
R
R
(2) Remove LP compressor annulus fillers:R
(a) Remove the LP compressor annulus fillers in accordance with AMM
72-31-41, Removal/Installation.
R
R
(3) Prepare ultrasonic array and OmniScan as per Appendix 2.R
(4) Check the system as per Appendix 3.R
(5) Calibrate the probe as per Appendix 4.R
Printed in Great Britain
RB.211−72−G872
Page 19
Apr. 3/12
Mar. 8/13R

### Page 25

(6) Attach the scanning frame to the first LP compressor blade to be
inspected.
R
R
(a) Rotate the fan so that the blade is in appropriate position to be
inspected. It is recommended that the fan blade is at the 3 o'clock
position to inspect the suction (convex) side or in the 9 'clock
position for the pressure (concave) side when viewed from the front.
R
R
R
R
(b) Secure the fan blade using the blade immobiliser HU44525, as shown in
Fig.5.
R
R
(c) Make sure the fan blade surface is clean and is free of any loose
dust, dirt or grease.
R
R
(d) Position the fan blade holder so the axial locating rod touches the
fan liner, as shown in Fig.6.
R
R
(e) Align the root-end and tip-end clamps so the blocks are against the
leading-edge of the fan blade, as shown in Fig.7 and Fig.8.
R
R
(f) Squeeze the clamps shut. Make sure the blocks are still against the
leading-edge.
R
R
(g) To release the clamps, pull the middle lever.R
(7) Inspect both sides of the LP compressor blade as per the procedure in
Appendix 5.
R
R
(8) Repeat steps (6) and (7) for the remaining LP compressor blades.R
(9) Restore the engine to a serviceable condition in accordance with AMM
72-31-41, Removal/Installation.
R
R
(10) Accomplishment of NMSB 72-G872 must be recorded against the individual
blades and compliance, blade serial numbers and associated lives (TSN/CSN)
logged with the local FSO.
R
R
R
H. Accomplishment Instructions for phased array inspection of LP Compressor Blades
removed from an Engine - On-wing.
R
R
CAUTION: IT IS THE RESPONSIBILITY OF THE OPERATOR /USER TO OBTAIN DETAILED HEALTH
AND SAFETY DATA FOR THE MATERIALS IN USE AND TO REFER TO LOCAL
REGULATIONS TO ENSURE SAFE WORKING PRACTICE.
R
R
R
(1) Prepare ultrasonic array and OmniScan as per Appendix 2.R
(2) Check the system as per Appendix 3.R
(3) Calibrate the probe as per Appendix 4.R
Printed in Great Britain
RB.211−72−G872
Page 20
Apr. 3/12
Mar. 8/13R

### Page 26

(4) Attach the scanning frame to the first LP compressor blade to be
inspected.
R
R
(a) Place the fan blade holder on a steady bench with a non-slip top. Make
sure that the holder is positioned so that the leading edge of the fan
blade will be closest to you.
R
R
R
(b) Place the fan blade on the holder suction (convex) side up, as shown
in Fig.9.
R
R
NOTE: Make sure the fan blade's retaining straps and shear keys are
removed before placing in the holder.
R
R
(c) When the fan blade is positioned pressure (concave) side up, make sure
the clamp on the holder securely fastens the blade in place, as shown
in Fig.10.
R
R
R
(d) Make sure the fan blade surface is clean and is free of any loose
dust, dirt or grease.
R
R
(e) Position the fan blade holder so the axial locating rod is touching
the holder support as shown in Fig.11.
R
R
(f) Align the root-end and tip-end clamps so the blocks are against the
leading-edge of the fan blade, as shown in Fig.7 and Fig.8.
R
R
(g) Squeeze the clamps shut. Make sure the blocks are still against the
leading-edge.
R
R
(h) To release the clamps, pull on the middle lever.R
NOTE: Once the scanning frame is correctly attached to the blade,
either surface of the fan blade can be inspected without having
to reposition the frame.
R
R
R
(5) Inspect both sides of the LP compressor blade as per the procedure in
Appendix 5.
R
R
(6) Repeat steps (4) and (5) for the remaining LP compressor blades.R
(7) Accomplishment of NMSB 72-G872 must be recorded against the individual
blades and compliance, blade serial numbers and associated lives (TSN/CSN)
logged with the local FSO.
R
R
R
Printed in Great Britain
RB.211−72−G872
Page 21
Apr. 3/12
Mar. 8/13R

### Page 27 (OCR)

RB211  SYSTEM  PROPULSION
SERVICE
ROYCE  BULLETIN
Check cycles of  Printed in Great Britain
fan blades since
refurbishment
Choose a  Check cycles since
different  refurbishment of
recipient engine  recipient engine
Are fan blades
Add fan blade cycles to  cycles > cycles
Refurbish  refurbishment of recipient  Yes  since  No
fan blades  engine or refurbishment  refurbishment
of fan blades  of recipient
engine?
Refit fan blade  Yes  Is total  No  Set can be
set to any engine  ≥ 6000  refitted to
cycles?  planned engine
L  def0016009a
R  Flowchart
Fig-'
Apr. 3/12  RB.211-72-G872
R Mar. 8/13  Page 22
© Rolls-Royce p/c

### Page 28 (OCR)

RB211  PROPULSION
SYSTEM
SERVICE
BULLETIN
LEADING EDGE
Printed in Great Britain
70%  511mm (20.10 in)  ZONE C
100%
20%  146mm (5.75 in)  ZONE B
ANNULUS FILLER OUTER
PROFILE AT LEADING EDGE
10%  76 mm (3.00 in)  ZONE A
121 mm (4.75 in)
64 mm (2.52 in)
REF
L  def0016234
Acceptance Zone Dimensions
Fig.2
Apr. 3/12  RB.211-72-G872
R Mar. 8/13  Page 23
© Rolls-Royce p/c

### Page 29 (OCR)

ROLLS  RB211 PRSPULSION
SYSTEM
SERVICE
ROYCE  BULLETIN
Printed in Great Britain
X - CIRCUMFERENTIAL BEND-DIMENSION
Y - AXIAL BEND-DIMENSION
Z - RADIAL BEND-DIMENSION
def0016233
LP Compressor Blades - Bends
Fig.3
Apr. 3/12  RB.211-72-G872
R Mar. 8/13  Page 24
© Rolls-Royce plc

### Page 30 (OCR)

RB211  PROPULSION  SYSTEM
SERVICE
ROYCE  BULLETIN
10 mm
Printed in Great Britain  (0.39 in)
14 mm
(0.55 in)
39 mm
LEADING EDGE
(1.53 in)
~ 13 mm  (0.51 in) TRAILING EDGE
PANEL LINE -
- PANEL AREA
45 mm
(1.77 in)
32 mm
(1.26 in)
70 mm
- (2.75 in)
72 mm
(2.83 in)
ANNULUS LINE
L  def0016232
LP Compressor Blades - Inspection Areas
Fig.4
Apr. 3/12  RB.211-72-G872
R Mar. 8/13  Page 25
© Rolls-Royce p/c

### Page 31

R
LP Compressor Blade ImmobiliserR
Fig.5R
Printed in Great Britain
RB.211−72−G872
Page 26
Apr. 3/12
Mar. 8/13R

### Page 32

R
Axial Position of the Scanning Frame on the LP Compressor BladeR
Fig.6R
Printed in Great Britain
RB.211−72−G872
Page 27
Apr. 3/12
Mar. 8/13R

### Page 33

R
Correct Position of the Clamps on the LP Compressor Blade for the Root EndR
Fig.7R
Printed in Great Britain
RB.211−72−G872
Page 28
Apr. 3/12
Mar. 8/13R

### Page 34

R
Correct Position of the Clamps on the LP Compressor Blade for the Tip EndR
Fig.8R
Printed in Great Britain
RB.211−72−G872
Page 29
Apr. 3/12
Mar. 8/13R

### Page 35

R
LP Compressor Blade Suction (Convex) Side Up in the HolderR
Fig.9R
Printed in Great Britain
RB.211−72−G872
Page 30
Apr. 3/12
Mar. 8/13R

### Page 36

R
LP Compressor Blade Pressure (Concave) Side Up on the Holder with Holder Clamp in
PlaceR
Fig.10R
Printed in Great Britain
RB.211−72−G872
Page 31
Apr. 3/12
Mar. 8/13R

### Page 37

R
Axial Position of the Scanning Frame on the LP Compressor BladeR
Fig.11R
Printed in Great Britain
RB.211−72−G872
Page 32
Apr. 3/12
Mar. 8/13R

### Page 38 (OCR)

RB211 PASPUN SION  SYSTEM
SERVICE
ROYCE  BULLETIN
Printed in Great Britain
1mm LONG X 0.5mm DEEP EDM NOTCHES
5.5mm
120mm  STEP
R
6mm  5mm  4mm  3mm  2mm  1mm
200mm
L  def0016580
R  Schematic Diagram of the Bottom-Side of the Working Standard
R  Fig.12
Apr. 3/12  RB.211-72-G872
R Mar. 8/13  Page 33
© Rolls-Royce p/c

### Page 39 (OCR)

ROLLS  RB211 PEsTULSion
SYSTEM
SERVICE
ROYCE  BULLETIN
Printed in Great Britain
R
6mm  5mm  4mm  3mm  2mm  1mm  5.5mm STEP
def0016581
Schematic Diagram of the Working Standard Cross-Section showing the 5.5 mm step
Fig.13
Apr. 3/12  RB.211-72-G872
R Mar. 8/13  Page 34
© Rolls-Royce p/c

### Page 40 (OCR)

RB211 PRSPULSION  SYSTEM
SERVICE
BULLETIN
Printed in Great Britain
R
6mm  5mm  4mm  3mm  2mm  1mm  5.5mm STEP
def0016582
Schematic Diagram of the Working Standard Cross-Section showing the Probe Inspecting
R
the Notch at the Material Depth of 6 mm
R  Fig.14
Apr. 3/12  RB.211-72-G872
R Mar. 8/13  Page 35
© Rolls-Royce p/c

### Page 41

R
Image showing the Correct Position of the Scan Arm HolderR
Fig.15R
Printed in Great Britain
RB.211−72−G872
Page 36
Apr. 3/12
Mar. 8/13R

### Page 42

R
Scan Arm Positioned to the First Index positionR
Fig.16R
Printed in Great Britain
RB.211−72−G872
Page 37
Apr. 3/12
Mar. 8/13R

### Page 43 (OCR)

OLLS  RB211  PROPULSION
SYSTEM
SERVICE
ROYCE  BULLETIN
r:1 A:0.00 Sk:090 L:020 S:0.00 mm 1:11  S-Scan Gr: 1 A:0.00 Sk:090 L:020 S:0.00 mm 1:11.79 mm  Printed in Great Britain
VPA 20
Fan blade surface signal
Interface
gate extent y
R
Iz0  120  I25
R Screen Shot of the OmniScan Showing that the LP Compressor Blade Surface Signal is
within the Interface Gate Extent
R  Fig.17
Apr. 3/12  RB.211-72-G872
R Mar. 8/13  Page 38
© Rolls-Royce plc

### Page 44 (OCR)

RB211  PROPULSION
SYSTEM
SERVICE
BULLETIN
Printed in Great Britain  A-Scan Gr: 1 A:0.00 Sk:090 L:041 S:201.50 mm 1:24.48 mm  S-Scan Gr: 1 A:0.00 Sk:090 L:041 S:201.50 mm 1:24.48 mm
VPA 41
150  11 65
Uncorrected C-scan A% Gr: 1 A:0.00 Sk:090 L:041 S:201.50 mm 1:24.48 mm
Lines of
missed data
Screen Shot of the OmniScan Showing Lines of Data that were not Recorded because the
R
Probe was Scanned too Quickly
R  Fig. 18
Apr. 3/12  RB.211-72-G872
R Mar. 8/13  Page 39
© Rolls-Royce plc

### Page 45 (OCR)

OLLS  RB211  _ PROPULSION
SYSTEM
SERVICE
ROYCE  BULLETIN
A-Scan Gr:1 A:0.00 Sk:090 L:013 S:46.00 mm I:7.56 mm  S-Scan Gr:1 A:0.00 Sk:090 L:013 S:46.00 mm 1:7.56 mm  Printed in Great Britain
VPA 13
09
110
Uncorrected C-scan A% Gr:1 A:0.00 Sk:090 L:013 5:46.00 mm 1:7.56 mm
Screen Shot of the OmniScan Showing a 5 mm Long by 0.5 mm Deep Notch in a LP
R
Compressor Blade
R  Fig.19
Apr. 3/12  RB.211-72-G872
R Mar. 8/13  Page 40
© Rolls-Royce p/c

### Page 46 (OCR)

RB211 PRSPULSION  SYSTEM
SERVICE
BULLETIN
Printed in Great Britain
*XXXXXXXXX
Achievable inspection area due to on-wing geometry
def0016613
R Diagram Showing the Achievable Scanning Area due to On-wing Geometry Limitations
Fig.20
Apr. 3/12  RB.211-72-G872
R Mar. 8/13  Page 41
© Rolls-Royce p/c

### Page 47

LP Compressor Blade C-scan Rejection Proforma
Results to be sent to Rolls-Royce via your Service Representative.
Blade Rejection Date:
Blade Part Number: Blade Serial Number:
Blade Time Since New (Hrs/Cycles):
Engine Number: Module Number:
Airline:
C-Scan Results:
1st Indication 2nd Indication 3rd Indication
Percentage of Height
Weighting
Blade Side (A/B)*
(*) A = Convex side
B = Concave side
APPENDIX 1
Printed in Great Britain
RB.211−72−G872
Appendix 1 - Page 1 of 1
Apr. 3/12
Mar. 8/13R

### Page 48

Ultrasonic Array and OmniScan PreparationR
1. Ultrasonic Array and OmniScan PreparationR
A. Check the flexible wedge is free from defects. There should be no bubbles
in the volume of the wedge and the probe/wedge interface and wedge/blade
interface should have no scratches or gouges. Replace the wedge if defects
are present.
R
R
R
R
B. Check that the feet of the wedge housing do not exhibit significant wear.
If either of the two front feet are less than 18 mm in height or the rear
foot is less than 10 mm in height replace the wedge housing.
R
R
R
C. If it is not already, insert the flexible wedge into the wedge housing.R
D. Apply sufficient couplant to cover the wedge/array interface.R
E. Attach the wedge housing to the array using the four screws. Make sure the
screws are done up tightly.
R
R
NOTE: It does not fundamentally matter which way around the array probe is
attached to the wedge housing. All that this will change is how the
defect indication moves on the OmniScan display relative to a
sideways movement of the probe.
R
R
R
R
F. Check that the probe/wedge interface is free from bubbles. Remove any
bubbles in the couplant between the array and wedge by pressing down on the
front face of the wedge.
R
R
R
G. Connect the array to the OmniScan using the OmniScan connector. Make sure
the connector is screwed into the OmniScan tightly.
R
R
H. Make sure the Secure Digital High Capacity (SDHC) memory card is in the
OmniScan memory card slot.
R
R
NOTE: If the switch on the side of the memory card is set to Lock, the
OmniScan will not boot up correctly.
R
R
I. Turn on the OmniScan by pressing the Power Button for one second.R
J. If the boot up screen appears press MXU 3.2.R
K. Make sure the OmniScan is charging or the battery has sufficient charge for
the required inspection.
R
R
APPENDIX 2
Printed in Great Britain
RB.211−72−G872
Appendix 2 - Page 1 of 1
Apr. 3/12
Mar. 8/13R

### Page 49

System CheckR
NOTE: The system check uses the working standard to make sure the probe has a
consistent sensitivity for all the 64 elements in the array. The working
standard is a 200x120x6.5mm section of titanium alloy plate, as shown in
Fig.12. It contains six milled slots which have a depth ranging from 6mm to
1mm in 1mm increments. To clarify, the slot labelled 1mm has a material
thickness of 1mm. Likewise the slot labelled 6mm has a material thickness of
6mm. In each of the milled slots is a 1mm long by 0.5mm deep EDM notch. These
notches are later used for the calibration procedure.
R
R
R
R
R
R
R
R
NOTE: Between the 6.5mm plate and the 1mm thick milled slot is a 5.5mm step, as
shown in Fig.13. The system check uses the pulse-echo signal from this 5.5mm
step and every element in the array to make sure there is consistent
sensitivity.
R
R
R
R
NOTE: The system check should be performed as a minimum at the start of each
inspection shift. The system check must be performed after the array, wedge
or housing has been replaced or if the probe cannot be calibrated as per
Appendix 4.
R
R
R
R
1. Perform the system check:R
A. Load the RR_T700FB_Probe_Check.ops file. To do this press File - Setup -
Open, select RR_T700FB_Probe_Check.ops and press Open.
R
R
B. Apply couplant to the front-face of the wedge.R
C. Place the probe on the working standard and position the wedge over the
5.5mm step. The front of the wedging housing should be approximately 70mm
from the end of the plate and the centre line of the probe should be
approximately 60mm from the edge of the plate.
R
R
R
R
D. Check for dead elements. A dead element will show as a line of zero signal.
If adjacent elements appear dead check that the probe is connected
correctly with the OmniScan and both screws are tight.
R
R
R
E. If any dead elements are still present, replace the array and send the
broken array for repair.
R
R
F. Perform an element sensitivity check. To do this press Wizard -
Calibration. Select Type (Ultrasound), Mode (Sensitivity), apply to all
VPA. Press Select Calibration Start.
R
R
R
G. Apply a firm pressure to the probe so that all three feet of the wedge
housing are touching the surface of the working standard and position the
probe so a flat straight line from the 5.5mm step appears across all
elements of the array and maximise the signal.
R
R
R
R
APPENDIX 3
Printed in Great Britain
RB.211−72−G872
Appendix 3 - Page 1 of 2
Apr. 3/12
Mar. 8/13R

### Page 50

H. Adjust the gain so that the average signal from all the elements is
approximately 50 per cent screen height. The gain should be approximately
23dB.
R
R
R
I. Make sure all signals are within the 40 per cent tolerance bars.R
J. If the signals cannot be made to lie within the 40 per cent tolerance bars,
check the coupling between the probe and wedge and between the wedge and
the working standard.
R
R
R
K. Exit the Calibration Wizard by pressing the Cancel key.R
NOTE: If at any point the OmniScan pop-up message says: 'The set up has
been modified. Would you like to save the setup?' select 'No' by
pressing the Cancel key.
R
R
R
L. If the setup is accidentally saved, load the
Master_RR_T700FB_Probe_Check.ops. Check the settings are the same as in
Appendix 8. Save this setup as RR_T700FB_Probe_Check.ops.
R
R
R
Printed in Great Britain
RB.211−72−G872
Appendix 3 - Page 2
Apr. 3/12
Mar. 8/13R

### Page 51

Calibration ProcedureR
NOTE: The sensitivity of the probe is set using the 1.0 mm long by 0.5mm deep notch
positioned in the working standard plate at the material depth of 6mm, as
shown in Fig.14.
R
R
R
1. Perform the Calibration:R
A. Load the RR_T700FB_Frame_Scan.ops file. To do this press File - Setup -
Open, select RR_T700FB_Frame_Scan.ops and press Open.
R
R
B. Position the probe over the 6mm deep 1.0x0.5mm notch. The front of the
wedge housing should be approximately 60mm from the end of the plate and
the centre line of the probe should be approximately 40mm from the edge of
the plate.
R
R
R
R
C. Maximise the signal from the notch.R
D. Change the gain setting to set the maximised signal to 100 per cent screen
height. The gain should be around 27dB.
R
R
E. Add 3dB of gain. This operation is done so the Interface gate is triggered
correctly. The gain setting should be a minimum of 30dB and a maximum of
33dB.
R
R
R
F. Run the probe over the five remaining notches in the milled slots. Make
sure all notches give a signal of atleast 120 per cent screen height. If
any of the notches give a signal of less than 120 per cent screen height
check the coupling between the wedge and the working standard. If required
increase the gain to a maximum of 33dB.
R
R
R
R
R
G. At the edge of each milled slot is a 1mm step, as shown in Fig.14. When the
probe passes over each 1mm step, make sure that a consistent signal is
given across the S-Scan. If any of the signals from the 1mm steps are
inconsistent across the S-Scan, check the coupling and re-do the system
check as per Appendix 3.
R
R
R
R
R
APPENDIX 4
Printed in Great Britain
RB.211−72−G872
Appendix 4 - Page 1 of 1
Apr. 3/12
Mar. 8/13R

### Page 52

Inspection ProcedureR
1. Inspection ProcedureR
A. Attach the ultrasonic probe to the scan arm using the two hex screws in the
probe holder.
R
R
B. Connect the encoder to the OmniScan using the scanner interface.R
C. Make sure the correct polarity of the encoder has been set. For the suction
(convex) side this is 'Inverse' for the pressure (concave) side this is
'Normal'.
R
R
R
D. Connect the string encoder clip to the correct carriage arm.R
E. Cover the area of the blade that is to be scanned with couplant.R
CAUTION: MAKE SURE THERE IS ADEQUATE COUPLANT BETWEEN THE PROBE AND AEROFOIL
SURFACE AT ALL TIMES TO PREVENT DEFECTS BEING MISSED
R
R
F. Put couplant on the wedge surface and make sure the probe flows easily over
the blade surface.
R
R
G. Place the scan arm holder into the rail carriage and make sure the
spring-loaded pins are closed and the arm holder is secure. The scan arm
holder must be attached using the middle positioning holes and with index
pin facing upwards and away from the leading edge of the blade, as shown in
Fig.15.
R
R
R
R
R
H. Make sure the correct side of the scan arm is uppermost. For example, if
the suction (convex) side is being inspected, the scan arm should be
positioned so that the 'Convex' label is upright.
R
R
R
I. Set the scan arm to the first index position and make sure the
spring-loaded pin has dropped firmly into the index hole, as shown in
Fig.16.
R
R
R
J. Move the scan arm and probe to the start position. For suction (convex)
side this is where the carriage is as close to the tip-end as possible. For
the pressure (concave) side this is where the carriage is as close to the
root-end as possible.
R
R
R
R
K. Apply a firm pressure to the probe to make sure the three housing feet are
always in contact with the blade surface.
R
R
NOTE: At every position on the blade scan, the fan blade surface signal
should lie entirely within the Interface gate extent, as shown in
Fig.17. If this is not achieved, check all three feet of the wedge
housing are in contact with the fan blade surface.
R
R
R
R
APPENDIX 5
Printed in Great Britain
RB.211−72−G872
Appendix 5 - Page 1 of 3
Apr. 3/12
Mar. 8/13R

### Page 53

L. Scan the probe along the blade. For the suction (convex) side this is from
tip to root. For the pressure (concave) this is from root to tip. The probe
should not be scanned with a speed greater than 90mm/s. If the probe is
scanned too quickly, black lines will appear in the C-Scan showing lines of
data that were not recorded, as shown in Fig.18. If this occurs, re-scan
the required area.
R
R
R
R
R
R
CAUTION: MAKE SURE S-SCAN DISPLAY IS VIEWED CONTINUOUSLY DURING SCANNING TO
PREVENT DEFECTS BEING MISSED
R
R
M. Whilst scanning the Probe along the blade, view the S-Scan display for
potential defect indications.
R
R
N. The finish point of the scan is when the carriage reaches the end of the
rail.
R
R
O. Once a scan line is finished press the Freeze key to freeze the scan. View
the C-Scan for potential defect indications.
R
R
P. If a defect indication greater than 30 per cent screen height appears on
the C-Scan, un-freeze the OmniScan and move the probe to the indication.
Maximise the signal by moving the probe up and down the blade and from side
to side, releasing the locking screw on the carriage if required.
R
R
R
R
Q. Once the signal is maximised, Freeze the OmniScan. Measure the maximum
signal height of the indication by moving the data selector lines (the
vertical line and horizontal line on the C-Scan) over the indication, as
shown in Fig.19. this can be done by either double tapping the touch screen
display on the C-Scan or by pressing the Data Selection key then the Enter
key then moving the data selector line using the Scroll Knob.
R
R
R
R
R
R
R. Reject any indication greater than 60 per cent screen height.R
S. Record the details of indications greater than 60 per cent screen height
using the appropriate sheets in Appendix 7.
R
R
T. Save the data of the indication. To do this press the Freeze key to freeze
the data. Click File - Data Settings, click File Name twice and type in the
file name in format 'RGF [blade number] [SS/PS] [Reference Label]'. For
example the file name for blade RGF 12345 with an indication on the suction
(convex) side with a Reference Label 'A' will have the file name 'RGF 12345
SS A'. Press the Accept key to accept the file name. Finally click Data
then Save. Click the Freeze key again to un-freeze.
R
R
R
R
R
R
R
U. Extend the scan arm 20mm to the next scan index position and repeat steps
J. to T. until the final scan index has been scanned.
R
R
NOTE: Due to the on-wing geometry of the fan blades the last three scans
on the pressure (concave) side cannot be started at the normal
starting position. For these scans, start with the carriage behind
the start line marked on the rail. See Fig.20 for details on
achievable scanning area.
R
R
R
R
R
Printed in Great Britain
RB.211−72−G872
Appendix 5 - Page 2
Apr. 3/12
Mar. 8/13R

### Page 54

V. After scanning each blade remove any grit that has collected on the probe,
specifically on the wedge feet, as this could potentially mark the blade
surface.
R
R
R
W. After scanning the blade surface, use the working standard to make sure the
probe is still calibrated i.e. the signal heights from all the notches must
be atleast 120 per cent screen height and the signals from the 1mm steps
are consistent across the S-Scan. If not, check the coupling, re-calibrate
and re-scan the entire blade surface.
R
R
R
R
R
X. Record the inspection result of the blade on the sheet in Appendix 6. If
any indications are present record the details on the appropriate sheets in
Appendix 7.
R
R
R
Y. Once the fan blade surface has been inspected, remove the couplant from the
blade surface.
R
R
NOTE: If at any point the OmniScan pop-up message says: 'The set-up has
been modified. Would you like to save the set-up?' select 'No' by
pressing the Cancel key.
R
R
R
Z. If the setup is accidentally saved, load the
Master_RR_T700FB_Frame_Scan.ops. Check the settings are the same as in
Appendix 9. Save this setup as RR_T700FB_Frame_Scan.ops.
R
R
R
Printed in Great Britain
RB.211−72−G872
Appendix 5 - Page 3
Apr. 3/12
Mar. 8/13R

### Page 55

Ultrasonic Array Trent 700 Fan Blade Results SheetR
Blade NumberR Results
(Pass/Fail)
R
R
Gain
(dB)
R
R
Blade NumberR Results
(Pass/Fail)
R
R
Gain
(dB)
R
R
SSR SSR
PSR PSR
SSR SSR
PSR PSR
SSR SSR
PSR PSR
SSR SSR
PSR PSR
SSR SSR
PSR PSR
SSR SSR
PSR PSR
SSR SSR
PSR PSR
SSR SSR
PSR PSR
SSR SSR
PSR PSR
SSR SSR
PSR PSR
SSR SSR
PSR PSR
SSR SSR
PSR PSR
SSR SSR
PSR PSR
Inspectors:....................................................R
Date:...............................R
Probe S/N:....................................................R
Omni-Scan S/N:...............................R
Operator:.....................R
ESN:.................R
APPENDIX 6
Printed in Great Britain
RB.211−72−G872
Appendix 6 - Page 1 of 1
Apr. 3/12
Mar. 8/13R

### Page 56

Ultrasonic Array Trent 700 fan Blade Indication SheetR
For any indications over 60 per cent screen height:R
- Measure the location of the indication.R
- Mark an 'X' on the appropriate diagram below showing its approximate locationR
- Label the indication with a reference (i.e.'A')R
- Fill in the table below with the details of the indicationR
Reference
label
R
R
A-Scan Signal
(% SH)
R
R
Gain Setting
(dB)
R
R
Distance from
Blade Root
(mm)
R
R
R
Distance from
Leading Edge
(mm)
R
R
R
Image File
Name
R
R
Inspectors:....................................................R
Date:...............................R
Probe S/N:....................................................R
Omni-Scan S/N:...............................R
Operator:.....................R
ESN:.................R
APPENDIX 7
Printed in Great Britain
RB.211−72−G872
Appendix 7 - Page 1 of 2
Apr. 3/12
Mar. 8/13R

### Page 57 (OCR)

OLLS  RB211 PRSPULSION
SYSTEM
SERVICE
ROYCE  BULLETIN
BLADE TIP  BLADE TIP  Printed in Great Britain
LEADING  LEADING
EDGE  EDGE
SUCTION/CONVEX  PRESSURE/CONCAVE
R  SIDE  SIDE
TRAILING  TRAILING
EDGE  EDGE
BLADE ROOT  BLADE ROOT
def0016579
Apr. 3/12  RB.211-72-G872
R Mar. 8/13  Appendix 7 - Page 2
© Rolls-Royce p/c

### Page 58

Settings for Master RR ProbeCheck.opsR
To check the settings: click File - Report - Preview then check the settings match
those below:
R
R
1. SetupR
- Beam delay - 0.0 micro secondR
- Start - 40.01 mmR
- Range - 20.00 mmR
- Video Filter - OnR
- Rectification - FWR
- Filter - None 0.9 - 17.7 MHzR
- Voltage - 115 (High)R
- Gain - 23 dBR
- Sound Velocity - 3100 m/sR
- Pulse Width - 50.00 nsR
A. Gate AR
(1)Start - 52.03 mmR
(2)Width - 10.0 mmR
(3)Threshold - 10.0 per centR
(4)Synchro - PulseR
(5)Peak - Selection - Max. PeakR
2. CalculatorR
- Element Qty. Used - 1R
- First Element - 1R
- Last Element - 64R
- Resolution - 1.0R
- Wave Type - ShearR
APPENDIX 8
Printed in Great Britain
RB.211−72−G872
Appendix 8 - Page 1 of 2
Apr. 3/12
Mar. 8/13R

### Page 59

- Material Velocity - 3100 m/sR
- Start Angle - 0.00 degreesR
- Focal Depth - 5.00 mmR
- Law Configuration - LinearR
NOTE: Make sure only one group is in operationR
Printed in Great Britain
RB.211−72−G872
Appendix 8 - Page 2
Apr. 3/12
Mar. 8/13R

### Page 60

Settings for Master RR T700FB Frame Scan.opsR
To check the settings: click File - Report - Preview then check the settings match
those below:
R
R
1. SetupR
- Beam delay - 0.0 micro secondR
- Start - 35.00 mmR
- Range - 29.99 mmR
- Video Filter - OnR
- Rectification - FWR
- Filter - None 0.53 - 17.7 MHzR
- Voltage - 115 (High)R
- Gain - 30 dBR
- Sound Velocity - 3100 m/sR
- Pulse Width - 50.00 nsR
- Sum Gain - 18.1 dBR
A. Gate IR
(1)Start - 39.80 mmR
(2)Width - 15.21 mmR
(3)Threshold - 3.00 per centR
(4)Synchro - PulseR
(5)Peak - Selection - Max. PeakR
B. Gate AR
(1)Start - 5.01 mmR
(2)Width - 12.00 mmR
(3)Threshold - 30.00 per centR
(4)Synchro - I-edgeR
APPENDIX 9
Printed in Great Britain
RB.211−72−G872
Appendix 9 - Page 1 of 2
Apr. 3/12
Mar. 8/13R

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