This document transmits Revision 1 to Service Bulletin RB211-72-G872

Document History

Service Bulletin Revision Status Supplement Revision Status

Initial Issue Apr.3/12

Bulletin Revision 1

Remove Incorporate Reason for change

Pages 1 to 12 of the

Service Bulletin

Pages 1 to 19 of the

Service Bulletin

To add Fig.2, Fig.3, Fig.4

and an additional section

3.F. to Accomplishment

Instructions. Revised 1.D.

Compliance. Updated 1.B.

Reason and 1.E. Approval.

All pages of

Appendix 1

Page 1 of Appendix 1 To add Fig.2, Fig.3, Fig.4

and an additional section

3.F. to Accomplishment

Instructions. Revised 1.D.

Compliance. Updated 1.B.

Reason and 1.E. Approval.

Printed in Great Britain

Jul. 2/12

RB211 TRENT 700 SERIES PROPULSION SYSTEMS NON-MODIFICATION SERVICE BULLETIN

RB.211−72−G872

Transmittal - Page 1 of 2

Signed Date
LIST OF EFFECTIVE PAGES

The effective pages to this Service Bulletin following incorporation of Revision

1 are as follows:

Page Revision Number Revision Date

Bulletin

R 1 1 Jul.2/12

R 2 1 Jul.2/12

R 3 1 Jul.2/12

R 4 1 Jul.2/12

R 5 1 Jul.2/12

R 6 1 Jul.2/12

R 7 1 Jul.2/12

R 8 1 Jul.2/12

R 9 1 Jul.2/12

R 10 1 Jul.2/12

R 11 1 Jul.2/12

R 12 1 Jul.2/12

R 13 1 Jul.2/12

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R 15 1 Jul.2/12

R 16 1 Jul.2/12

R 17 1 Jul.2/12

R 18 1 Jul.2/12

R 19 1 Jul.2/12

Appendix 1

R 1 1 Jul.2/12

Printed in Great Britain

RB.211−72−G872

Transmittal - Page 2
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 (C-scan) is undertaken to mitigate

against release events. The C-scan inspection is capable of detecting

sub-surface anomalies in the LP compressor blade aerofoil. This 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) is being 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 is required. In

addition, Section 1.D. Compliance has been updated to clearly define what LP

compressor blades are affected by this NMSB and which inspections can be

claimed.

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C. Description

(1) This Non-Modification Service Bulletin (NMSB) has been issued to instruct

C-scan inspection of LP compressor blades.

(a) Accomplishment of this NMSB must be recorded against the individual

blades.

(b) Inform your assigned Rolls-Royce Service Representative of NMSB

accomplishment.

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 19

Apr 3/12

R Jul. 2/12
(2) The Accomplishment Instructions for C-scan 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.

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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,

R

R on all LP compressor blade standards with a life greater than 3,000

R cycles since new or since last C-scan inspection on 30th June 2013.

R NOTE: If an operator finds it convenient to inspect LP compressor blades

R earlier than 3,000 cycles, then inspection in accordance with this

R can be accredited provided the life of Non-Modification Service Bulletin

the LP compressor blades are at least 2,000 cycles from new.

R

R

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.

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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

and was re-approved on Jul.2/12.

R

R

F. Manpower

On-wing:

Printed in Great Britain

RB.211−72−G872

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(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)

(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.

H. Tooling Price and Availability

(1) Tooling for LP compressor blade inspection:

RR1024167 Ultrasonic immersion

system

1 off

QC6808 Calibration blade 1 off

I. References

(1) Rolls-Royce RB211 Non-Modification Service Bulletin:

72-G702

Engine - LP Compressor - Inspection of LP Compressor Blades -

Non-Modification Service Bulletin

(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

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(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

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2. Material Information

A. None

Printed in Great Britain

RB.211−72−G872

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3. Accomplishment Instructions

A. Identify recipient engine for C-scan 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 C-scan 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.

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(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 C-scanned then

accomplishment of NMSB 72-G872 must be recorded against the individual

blades and compliance logged with local FSO.

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.

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(2) Carry out C-scan inspection of LP compressor blades

(a) Special Tools:

RR1024167 Ultrasonic immersion

system

1 off

QC6808 Calibration blade 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.

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(viii) Set the BLADE TYPE box on the control screen to 'Calibrate

Blade' and type test in the SERIAL NUMBER box.

(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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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.

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(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) 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.

(4) Accomplishment of NMSB 72-G872 must be recorded against the individual

blades and compliance logged with local FSO.

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).

(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.

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(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 logged with local FSO.

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 logged with local FSO.

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.

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R (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).

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(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:

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R

R

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.

R

R

R

(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.

R

R

R

(ii) Repeat the swabbing using fresh cloth and solvent until the

area is clean and free of DFL.

R

R

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(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.

R

R

R

R (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.

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R

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.

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R

R (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.

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R

R

(ii) If the blade has one or more ripples of any length with a form

more than in step above - Reject the blade.

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R

R (b) Examine the blade airfoil surfaces for cracks:

R (i) If the blade is cracked - Reject the blade.

(c) Examine the blade tips and the airfoil surfaces for blueing or heat

discoloration.

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R

(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.

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R

R

(d) If there is blueing or heat discoloration more than limit given above

- Reject the blade.

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R (e) Examine the blade surfaces for arc-burns.

R (i) If the blade shows signs of arc-burns - Reject the blade.

R (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.

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R

R

(ii) If the blade has nicks in the airfoil surfaces above the

annulus line more than the limit given above - Reject the

blade.

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R

R

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(iii) If the blade has nicks in the airfoil surfaces below the

annulus line - Reject the blade.

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R

(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.

R

R

(i) If the blade has nicks up to 0.025 in. (0.64 mm) in depth -

Accept the blade.

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R

(ii) If the blade has nicks more than the limit given above - Reject

the blade.

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R

(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.

R

R

(i) If the blade has nicks up to 0.008 in. (0.2 mm) in depth -

Accept the blade.

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R

(ii) If the blade has nicks more than the limit given above - Reject

the blade.

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R

R (i) Examine the blade forward and rear edges for bends:

R (i) Blade bends - General.

(1) The maximum number of bent blades in the LPC rotor assembly

must not be more than three.

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R

(2) If there are more than one bend in a blade - Reject the

blade.

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R

(3) If a bend in a blade is not smooth or has kinks, creases,

tears, cracks or nicks - Reject the blade.

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R

R (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:

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R

(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.

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R

R

R

(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.

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R

R

R

(3) The bend does not extend into the panel area. If the bend

extends into the panel area - Reject the blade.

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R

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(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:

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R

R

(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.

R

R

R

R

(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.

R

R

R

R

(iv) If the bend is more than the limits given above - Reject the

blade.

R

R

R (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.

R

R

R

(ii) If the blade has galling more than the limit given above -

Reject the blade.

R

R

R (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.

R

R

(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.

R

R

R

R

R (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.

R

R

(5) Accomplishment of NMSB 72-G872 must be recorded against the individual

blades and compliance logged with local FSO.

R

R

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R

R Fig.1

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R

R Acceptance Zone Dimensions

R Fig.2

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R

R LP Compressor Blades - Bends

R Fig.3

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R

R LP Compressor Blades - Inspection Areas

R Fig.4

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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

R Jul. 2/12