P.O. Box 31, DERBY 

DE24 8BJ, UK 

Telephone: 44 (0) 1332 242424 

Fax: 44 (0) 1332 249936 - Rolls-Royce 

TRANSMITTA 

The technical information contained in this document has been approved under the authority 

of - See Planning Information, Approval. 

Signed Date Jan. 26/10 

N. J. Wright 

RB211 TRENT 800 SERIES PROPULSION SYSTEMS NON-MODIFICATION SERVICE BULLETIN 

ALERT 

This document transmits Revision 1 to Service Bulletin RB211-72-AG244 

Document History 

Service Bulletin Revision Status 

Initial Issue Aug. 7/09 

Bulletin Revision 1 

Remove 

Pages 1 to 9 of the 

Service Bulletin 

Page 1 and 2 of 

Appendix 1 

Supplement Revision Status 

Incorporate 

Pages 1 to 10 of the 

Service Bulletin 

Pages 1 to 8 of 

Appendix 1 

ALERT 

Reason for change 

Compliance statement 

expanded. Appendices 

reformatted and graphics 

resequenced to improve 

readability without 

technical changes. 

Compliance statement 

expanded. Appendices 

reformatted and graphics 

resequenced to improve 

readability without 

technical changes. 

Transmittal - Page 1 of 4 

CHECK THAT ALL PREVIOUS TRANSMITTALS HAVE BEEN INCORPORATED 

If any have not been received please advise Customer Data Services, Rolls-Royce plc, Derby, England 

O Rolls-Royce plc (date as above) Printed in Great Britain 
Page 1 and 2 of

Appendix 2

Pages 1 to 26 of

Appendix 2

Compliance statement

expanded. Appendices

reformatted and graphics

resequenced to improve

readability without

technical changes.

All pages of

Appendix 3

Compliance statement

expanded. Appendices

reformatted and graphics

resequenced to improve

readability without

technical changes.

Printed in Great Britain

RB.211−72−AG244

Transmittal - Page 2
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 Jan.26/10

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Appendix 1

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Transmittal - Page 4
1. Planning Information

A. Effectivity

Boeing 777 aircraft

RB211 TRENT875-17 Engines incorporating SB72-D672 standard LP compressor blades

RB211 TRENT877-17 Engines incorporating SB72-D672 standard LP compressor blades

RB211 TRENT884-17 Engines incorporating SB72-D672 standard LP compressor blades

RB211 TRENT884B-17 Engines incorporating SB72-D672 standard LP compressor

blades

RB211 TRENT892-17 Engines incorporating SB72-D672 standard LP compressor blades

RB211 TRENT892B-17 Engines incorporating SB72-D672 standard LP compressor

blades

RB211 TRENT895-17 Engines incorporating SB72-D672 standard LP compressor blades

B. Reason

A Trent 895 powered Boeing 777-200 aircraft experienced release of an LP

compressor blade in January 2009. The released blade was to Service Bulletin

(SB) 72-D672, Introduction of Laser Shock Peening (LSP) with an undercut root

standard. The blade life was 33,499 hours 4657 cycles since new. The blade

release was due to cracking within the undercut feature on the convex side of

the root section with a primary origin to the rear of the shear key slot.

The current standard of LP compressor blade root lubrication system uses a

metal spray coating applied to the blade root bedding flanks, onto which is

applied a Dry Film Lubricant (DFL). Some LP compressor blades to SB 72-D672

standard have previously been run with an earlier root coating system that did

not use this metal spray coating. Investigation has revealed that the

effectiveness of the current coating system may be reduced as a result of

previous running without the metal spray coating being present, leading to

increased blade root stress levels.

ENGINE - LP COMPRESSOR BLADES - INSPECTION OF LP COMPRESSOR BLADE ROOTS

NON-MODIFICATION SERVICE BULLETIN - NON - MOD.72-AG244

Printed in Great Britain

RB.211−72−AG244

Page 1 of 10

Aug 7/09

R Jan.26/10
In the specific case of the released blade, a review of its in-service

modification history shows that it operated for a significant number of cycles

prior to embodiment of LSP and the root metal spray coating. A review of the

Engine Health Monitoring data has also identified it operated at high N1 speeds

compared to the Trent 800 fleet average N1 speeds. The combination of operation

at high N1 speed, plus a period of operation without LSP, plus a period of

operation without the blade root metal spray coating resulted in increased

fatigue life usage. This is considered to have led to crack initiation and

propagation prior to reaching the blades declared life limit.

A fleet-wide review of all in-service Trent 800 LP compressor blades to SB

72-D672 standard has identified a specific number of blades that carry an

increased susceptibility to cracking, as a result of a combination of operation

at high N1 speed and a period of operation without LSP and the root metal spray

coating. A once-around-the-fleet ultrasonic inspection instructed by

Non-Modification Service Bulletin (NMSB) 72-E175 Revision 5 has been completed

and has not identified any cracks present in any of the identified blades.

This NMSB introduces an ultrasonic inspection of specific LP compressor blades

to SB 72-D672 standard, to detect root cracks in the undercut radius. The first

inspection must be carried out when the blades reach a specified life, which

differs from blade to blade as a result of differences in operating history.

The inspection must then be repeated at intervals not exceeding 100 cycles.

Appendix 3 specifies the affected LP compressor blades, and the life at which

the first inspection must be accomplished for each blade.

Revision 1 of this NMSB is issued to clarify the inspection requirements in

1.D. Compliance. In addition, Appendix 1 and 2 have been reformatted and

resequenced to improve readability without any technical changes.

R

R

R

C. Description

This NMSB instructs repeat ultrasonic inspection of LP compressor blade roots

for a sub-population of SB 72-D672 standard LP compressor blades in order to

maintain serviceability. The affected LP compressor blades are listed in

R through Appendix 3F of this NMSB. Appendix 3A

Advise your Rolls-Royce service representative of any rejected LP compressor

blades following the inspection in accordance with NMSB. Refer to Table 1.

D. Compliance

ALERT

R LP compressor blades to SB 72-D672 standard as listed in Appendix 3A through

R Appendix 3F.

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Carry out an inspection, using the procedure defined in Accomplishment

Instructions (3.A. or 3.B.). For those LP compressor blades listed in Appendix

R the initial inspection must be carried out within 120 flight cycles from 3A,

initial issue of this NMSB. For those LP compressor blades listed in Appendix

R through 3F, the initial inspection must be carried out on or before the 3B

R Appendices. dates stated in the

The inspection must be repeated at intervals not exceeding 100 flight cycles.

NOTE: The intent of this NMSB is for the LP compressor blades to receive the

first inspection at a convenient time that is close to but not later

than the appropriate date stated in Appendix 3B through 3F, such that

the first of the repeat inspections occurs after the stated date.

R

R

R

R

If a set of LP compressor blades is removed from an engine and fitted to

another and the blades are currently being inspected at 100 cycle repeat

intervals or are due to start the first inspection within 100 cycles or less,

then

R

R

R the LP compressor blades must be inspected prior to installation and at

100 cycles repeat intervals thereafter.

R

R

A record of accomplishment is required for each inspection.

R subject of an Airworthiness It is anticipated that this NMSB will be the

Directive.

E. Approval

The technical content of this Non-Modification Service Bulletin was approved

under the authority of Design Organisation Approval EASA.21J.035 on Aug.7/09

and was re-approved on Jan.25/10.

R

R

F. Manpower

Estimated man-hours (in service and at overhaul):

(1) 3 hours per engine (blades not removed)

(2) 8 hours per engine (blades removed)

NOTE: Personnel engaged in the execution of NDT procedures contained in

this NMSB should be approved in accordance with the necessary

requirements of the national controlling regulatory authority.

Minimum qualification level should be ASNT level 2 or equivalent.

G. Tooling

(1) Equipment - Ultrasonic inspection to Appendix 1 procedure.

(a) Ultrasonic flaw detector capable of operating in the 10MHz range.

(b) HU81567 Kit comprising:

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Part Number Description

HU81566 10 MHz twin crystal probe

QC6890 Test piece

NOTE: Item (1)(b) is supplied by Rolls-Royce.

(2) Equipment - Ultrasonic inspection to Appendix 2 procedure

(a) Ultrasonic flaw detector capable of operating in the 3 to 8 MHz range.

(b) HU81574 Kit comprising:

Part Number Description

HU81573 5 MHz, 45 degree, single crystal

shear wave probe

HU81576 Probe guide

QC6895 Test piece

NOTE: Item (2)(b) is supplied by Rolls-Royce.

(3) Consumable materials

Material Description

OMat 655 Ultrasonic couplant

OMat 150 Acetone

OMat 2-101 Lint-Free Cloth

OMat 582 Scotchbrite pad

H. References

(1) Rolls-Royce Service Bulletins:

(a) NMSB 72-D347

Engine - LP Compressor Blades - Re-application of Dry Film Lubricant

to LP Compressor Blade Roots and LP Compressor Disc Dovetail Slots.

(b) SB 72-D672

Engine - Compressor Blades - Introduction of Laser Shock Peening to

Blade Roots.

(c) NMSB 72-E175

Engine - LP Compressor Blades - Inspection of Fan Blade Roots.

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(2) Trent 800 Engine Manual

(a) 72-31-11-000-801, Remove the Low Pressure (LP) Compressor Blades and

Dampers

(b) 72-31-11-420-801, Install the Low Pressure (LP) Compressor Blades and

Dampers

(c) 72-31-15-000-801, Disassemble the Low Pressure (LP) Compressor Rear

Spinner

(d) 72-31-15-400-801, Assemble the Low Pressure (LP) Compressor Rear

Spinner

(e) 72-35-11-000-801, Remove the Air Intake Fairing/Spinner

(f) 72-35-11-400-801, Install the Air Intake Fairing/Spinner

(g) 72-31-11-300-001, Low Pressure (LP) Compressor Rotor Blades - Apply

Dry Film Lubricant (FRSA028)

(3) Aircraft Maintenance Manual

(a) 72-31-11-000-801-R00, LP Compressor Rotor Blades -

Removal/Installation

(b) 72-31-11-400-801-R00, LP Compressor Rotor (Individual) Blade

Installation

(c) 72-35-11-000-801-R00, Air Intake Fairing/Spinner -

Removal/Installation

(d) 72-35-11-400-801-R00, Air Intake Fairing/Spinner Installation

(e) 72-31-12-000-801-R00, LP Compressor (Fan) Annulus Fillers -

Removal/Installation

(f) 72-31-12-400-801-R00, LP Compressor (Fan) Annulus Fillers Installation

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2. Material Information

None.

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3. Accomplishment Instructions.

A. Inspect LP compressor blades - Blades removed from the engine.

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

MAKE SURE THAT MAINTENANCE TASKS HAVE BEEN COMPLETED AS DEFINED.

MAINTENANCE GUIDELINES SHOULD BE REVISED, WHERE POSSIBLE, TO PROMOTE

THIS RECOMMENDATION.

WARNING: BE CAREFUL TO AVOID INJURY WHEN YOU MOVE THE LP COMPRESSOR BLADE, SINCE

IT WEIGHS 24 POUNDS (11 KG). USE APPLICABLE GLOVES ON YOUR HANDS WHEN

YOU HOLD THE LP COMPRESSOR BLADE. THE LEADING EDGE OF THE LP COMPRESSOR

BLADE CAN CAUSE AN INJURY IF ERODED AND SHARP.

NOTE: This procedure assumes that the task is being accomplished on an

installed engine. Where inspection is being carried out in an Airmotive

environment, the corresponding EM tasks have been quoted in parentheses.

(1) Remove all LP compressor blades in accordance with AMM Task

72-31-11-000-801-R00 (or EM Task 72-31-11-000-801), make sure that the

position of all annulus fillers and blades are temporarily marked on the

components to aid reinstallation.

(2) Ultrasonically inspect the blades.

(a) Calibrate the probe and flaw detector in accordance with Appendix 1.

(b) Remove the LP compressor blade rubber strap by pulling over the pins

and remove the shear key, see Fig.1.

(c) Ultrasonically inspect the blades in accordance with Appendix 1.

(d) Reject any blades with unacceptable indications in accordance with

Appendix 1.

(e) Install the shear key and fit the rubber strap over the securing pins

on all blades deemed acceptable.

(f) Repeat steps (b) to (e) for all blades.

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(3) Install all blades which are considered acceptable, in their original

positions in accordance with AMM Task 72-31-11-400-801-R00 (or EM Task

72-31-11-420-801). Make sure that dry film lubricant is reapplied to all

blades in accordance with NMSB 72-D347.

NOTE: Where blade inspection is being carried out in an Airmotive

environment, it is recommended that the dry film lubricant should

be re-applied in accordance with the Engine Manual, 72-31-11,

Repair 001 (FRSA028).

(4) Install annulus fillers in accordance with AMM Task 72-31-12-400-801-R00

(or EM Task 72-31-11-420-801).

(5) Install air intake fairing/spinner and spinner extension, AMM Task

72-35-11-400-801-R00 (or EM Task 72-35-11-400-801 and 72-31-15-400-801)

and put the airplane back to its usual condition.

(6) Record accomplishment of NMSB 72-AG244. Make sure that the engine cycles

since new are stated. A copy of the Form 1 for the inspection should be

filed in the certificate section at the front of the engine logbook.

B. Inspect LP compressor blades - Blades not removed from engine.

(1) Remove air intake fairing/spinner and spinner extension in accordance with

AMM Task 72-35-11-000-801-R00 (or EM Task 72-35-11-000-801 and

72-31-15-000-801).

(2) Remove annulus fillers, in accordance with AMM Task 72-31-12-000-801-R00

(or EM Task 72-31-11-000-801), make sure that the position of all annulus

fillers are temporarily marked to aid reinstallation.

(3) Ultrasonically inspect the blades

(a) Calibrate the probe and flaw detector in accordance with Appendix 2.

(b) Rotate LP compressor to position blade to be inspected at

approximately 10 o' clock position and immobilise.

(c) Ultrasonically inspect the blades in accordance with Appendix 2.

(d) Reject any blade with unacceptable indications in accordance with

Appendix 2.

(e) Remove immobiliser.

(f) Repeat steps (b) to (e) for all blades in turn.

(4) Install annulus fillers in accordance with AMM Task 72-31-12-400-801-R00

(or EM Task 72-31-11-420-801).

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(5) Install air intake fairing/spinner and spinner extension in accordance

with AMM Task 72-35-11-400-801-R00 (or EM Tasks 72-35-11-400-801 and

72-31-15-400-801) and put the Airplane back to its usual condition.

(6) Record accomplishment of NMSB 72-AG244. Make sure that the engine cycles

since new are stated. A copy of the Form 1 for the inspection should be

filed in the certificate section at the front of the engine logbook.

Printed in Great Britain

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R

R LP Compressor Blade reject details

R Table 1

Printed in Great Britain

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BLADE ROOT ULTRASONIC INSPECTION - BLADES REMOVED

1. Calibration

A. Make sure flaw detector is set for twin crystal operation.

B. Connect probe HU81566 to the flaw detector.

C. Apply couplant to test piece QC6890 on the convex angled face, see Fig.1.

D. Using zero delay and a time base range of approximately 40mm for a velocity

of 6150M/S, place probe on test piece as shown in Fig.1, opposite large

slot 6,35mm (0.25in.) marked A. The signal from the slot will appear behind

a signal that is generated by the undercut geometry, see Fig.2.

E. Identify the large signal from this slot and position the signal at the 5

divisions mark on the time base. Adjust this to 50 percent screen height

and then increase gain by 20dB.

F. Slide the probe towards the 0,5mm (0.020in.) deep slot marked B.

G. The signal reflected from slot B should appear at position, 5, on the time

base. Identify this signal and adjust the gain to bring the signal to 40

percent screen height.

H. If a monitor gate is available position this as close to the undercut

signal as possible, without the undercut triggering the gate and over the

signal from slot B, (at this stage the delay can be increased and the range

reduced to aid accuracy of settings). Monitor gate width should be 1.2

divisions approximately, see Fig.2. Adjust any audible or visual alarms to

trigger at 50 percent screen height.

I. The probe and flaw detector are now calibrated.

2. Inspection

A. Remove any loose/flaking dry film lubricant from the blade root using

acetone (OMat 150) and a lint-free cloth (OMat 2-101).

B. Apply couplant to the root convex angled face 40 mm (1.575in.) either side

of the shear key slot position, see Fig.3.

APPENDIX 1

Printed in Great Britain

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Appendix 1 - Page 1 of 8

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C. Inspect the LP compressor blade 40mm (1.575in.) either side of the shear

key slot. Due to cracks initiating at or near the corner of the shear key

it is necessary to pay particular attention to the root adjacent to the

shear key slot. Inspect to the very edge, until the probe drops off the

corner. Crack signals will appear at the same time base position as the

calibration slots (5 division mark).

NOTE: Crack signals in the undercut radius are expected to fall in the

gated area of the time base. If the crack initiates closer to the

re-entrant angle of the undercut it will have the effect of markedly

increasing the size of the undercut signal, see Fig.4. Cracks which

are in the re-entrant angled corner of the undercut may appear

either as tight handover signals or distinct signals before or after

the reflected signal from the undercut feature, (see Fig.5 and

Fig.6). Visual observation of the screen is necessary to detect

this. Only inspect within the area specified. Spurious signals from

the blade material are possible in the area outside the inspection

requirement.

CAUTION: YOU MUST USE ONLY ACETONE AND A LINT-FREE CLOTH TO CLEAN THE BEDDING

FLANK (ZONE B). DO NOT USE ABRASIVE MEDIA ON THE BEDDING FLANK AS THIS

CAN CAUSE WEAR AND CRACKING IN THE LP COMPRESSOR BLADE ROOT.

NOTE: False signals can sometimes be generated by patchy dry film

lubricant in the undercut (zone A Fig.3) and also on the convex

angled face (zone C Fig.3) where the probe runs along. To aid

interpretation of any signals found it is recommended to remove the

dry film lubricant from the undercut and convex angled face using

scotchbrite (OMat 582) as shown in Fig.3. Do not dress the bedding

flank area (zone B Fig.3). When dressed test the blade.

D. Wipe off excess couplant from blade using a lint-free cloth (OMat 2-101).

3. Acceptance/Rejection criteria

A. Accept LP compressor blades that do not produce signals that trigger the

monitor gate and where there is no sudden increase in the amplitude of the

undercut signal.

B. Reject blades with signals greater than 50 percent screen height that

trigger the monitor gate, or blades where there has been a sudden

unexplained increase in the size of the undercut signal, see notes above.

C. Replace any rejected blades in accordance with Aircraft Maintenance Manual,

Task 72-31-11-400-801-R00.

D. Advise Rolls-Royce plc of reject findings as a result of this NMSB, please

complete reject details in Table 1 of this NMSB and send to your local

Rolls-Royce representative and the Technical Help Desk.

Printed in Great Britain

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Appendix 1 - Page 2

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R

R Inspection - Calibration

R Fig.1

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R

Showing Monitor Gate Positioned Just behind the Undercut Signal and Over the

Calibration Slot Signal R

R Fig.2

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Appendix 1 - Page 4

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R

R Inspection of LP Compressor Blade Root

R Fig.3

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Appendix 1 - Page 5

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R

R Expected Screen Display from Crack Close to Re-entrant Angle on Undercut

R Fig.4

Printed in Great Britain

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Appendix 1 - Page 6

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R

R Screen Display Showing Genuine Crack Signal Close to Undercut

R Fig.5

Printed in Great Britain

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Appendix 1 - Page 7

Aug 7/09

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R

Screen Display Showing Genuine Crack in the Re-entrant Corner of the Undercut

Appearing Before the Undercut signal R

R Fig.6

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Appendix 1 - Page 8

Aug 7/09

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BLADE ROOT ULTRASONIC INSPECTION - BLADES NOT REMOVED

1. Calibration

A. Make sure flaw detector is set for single crystal operation; velocity

should be set at approximately 3353 meters per second (132,000 inches per

second) and the range at 75mm (3in.).

B. Connect probe HU81573 leads to flaw detector.

C. Apply couplant to test piece QC6895. On the concave aerofoil surface,

locate the front edge of the probe on the scribed line, see Fig.7. A large

signal should be observed at approximately 8 divisions on the screen as

shown in Fig.9; this signal is generated from the bottom of the root.

Accurately adjust range to position this signal at 8 divisions on the

timebase.

D. Slide the probe along the scribed line on the concave side, until opposite

the large slot marked A on the convex side of the test piece as shown in

Fig.7 and Fig.8.

E. Identify the signal from this slot that should appear at position 6.2

divisions on the timebase. Adjust this to 50 percent screen height and then

increase gain by 12dB.

F. Slide the probe along the scribed line until opposite the position of the

smaller slot marked B (see Fig.8), which is on the convex side of the

testpiece.

G. The signal reflected from slot B should appear at the same position, on the

timebase. Identify this signal and adjust the gain to bring the signal to

50 percent screen height.

H. If a monitor gate is available position this to start at timebase position

5.6 divisions and to finish at timebase position 6.6 divisions. Adjust any

audible or visual alarms to trigger at 50 percent screen height. The screen

display is shown as Fig.9.

I. Slide the probe along the scribed line until opposite the slot marked C on

the convex side of the test piece (this slot is difficult to see, as it is

in the tight radius closest to the root end face). Observe that the signal

from this slot, which is of the lower amplitude, falls within the gated

range.

J. The probe and flaw detector are now calibrated.

APPENDIX 2

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Appendix 2 - Page 1 of 8

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2. Inspection

A. Fit the probe guide to the LP compressor disc as shown in Fig.10. Apply the

couplant to the concave aerofoil just above the probe guide, the inspection

zone is approximately 40mm (1.6in.) either side of the shear key slot

position, see Fig.10.

B. Slide the probe along the LP compressor blade (see Fig.11), make sure

correct coupling by observing that the large signal from the bottom of the

convex root positioned at the 8 divisions mark on the timebase is always

present. Inspect the blade approximately 40mm (1.6in.) either side of the

shear key slot. Due to cracks initiating at or near the corner of the shear

key it is necessary to pay particular attention to the root adjacent to the

shear key slot. Inspect to the very edge, until the signal from the root

disappears.

NOTE: If there is a genuine crack indication, this will effectively mask

the bottom of the blade and result in a much reduced signal from

this feature at division 8 on the timebase, see Fig.12.

3. Acceptance/Rejection criteria

A. Accept LP compressor blades that do not produce signals that trigger the

monitor gate.

B. Reject blades with signals greater than 50 percent screen height that

trigger the monitor gate.

C. Check rejected blades utilising the blade out procedure, Appendix 1.

D. Replace any rejected blades in accordance with Aircraft Maintenance Manual,

Task 72-31-11-400-801-R00.

E. Advise Rolls-Royce plc of reject findings as a result of this NMSB, please

complete reject details in Table 1 of this NMSB and send your local

Rolls-Royce representative and the Technical Help Desk.

Printed in Great Britain

RB.211−72−AG244

Appendix 2 - Page 2

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R

R Probe on Test Piece QC6895

R Fig.7

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R

R Calibration Slots on Test Piece QC6895

R Fig.8

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Appendix 2 - Page 4

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R

Monitor Gate Positioned over the Calibration Slot Signal set to 50 per cent and

signal generated by bottom of blade root R

R Fig.9

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R

Showing Probe Guide in Position and Area either side of Shear Key Slot to be

Inspected R

R Fig.10

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R

R Showing Probe and Probe Guide Fitted to the Disc

R Fig.11

Printed in Great Britain

RB.211−72−AG244

Appendix 2 - Page 7

Aug 7/09

R Jan.26/10
R

R Screen Display Showing Crack Signal. Note Loss of Signal from Bottom of Blade

R Fig.12

Printed in Great Britain

RB.211−72−AG244

Appendix 2 - Page 8

Aug 7/09

R Jan.26/10
The LP compressor blades listed below are subject to inspection in accordance with

section 1.D. Compliance of this NMSB.

NOTE: The ESN data is provided for information only. If an engine has had a recent

shop visit, the ESN data may not be correct.

APPENDIX 3A

Printed in Great Britain

RB.211−72−AG244

Appendix 3A - Page 1 of 4

Aug 7/09

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Printed in Great Britain

RB.211−72−AG244

Appendix 3A - Page 2

Aug 7/09

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R Appendix 3A continued:

The LP compressor blades listed below are subject to inspection in accordance with

section 1.D. Compliance of this NMSB.

R

R

NOTE: The ESN data is provided for information only. If an engine has had a recent

shop visit, the ESN data may not be correct.

R

R

Printed in Great Britain

RB.211−72−AG244

Appendix 3A - Page 3

Aug 7/09

R Jan.26/10
R

Printed in Great Britain

RB.211−72−AG244

Appendix 3A - Page 4

Aug 7/09

R Jan.26/10
The following LP compressor blades listed are subject to inspection in accordance

with this NMSB from 1st January 2012.

NOTE: The ESN data is provided for information only. If an engine has had a recent

shop visit, the ESN data may not be correct.

APPENDIX 3B

Printed in Great Britain

RB.211−72−AG244

Appendix 3B - Page 1 of 2

Aug 7/09

R Jan.26/10
Printed in Great Britain

RB.211−72−AG244

Appendix 3B - Page 2

Aug 7/09

R Jan.26/10
The following LP compressor blades listed are subject to inspection in accordance

with this NMSB from 1st January 2013.

NOTE: The ESN data is provided for information only. If an engine has had a recent

shop visit, the ESN data may not be correct.

APPENDIX 3C

Printed in Great Britain

RB.211−72−AG244

Appendix 3C - Page 1 of 4

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Printed in Great Britain

RB.211−72−AG244

Appendix 3C - Page 2

Aug 7/09

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R Appendix 3C continued:

The following LP compressor blades listed are subject to inspection in accordance

with this NMSB from 1st January 2013.

R

R

NOTE: The ESN data is provided for information only. If an engine has had a recent

shop visit, the ESN data may not be correct.

R

R

Printed in Great Britain

RB.211−72−AG244

Appendix 3C - Page 3

Aug 7/09

R Jan.26/10
R

Printed in Great Britain

RB.211−72−AG244

Appendix 3C - Page 4

Aug 7/09

R Jan.26/10
The following LP compressor blades listed are subject to inspection in accordance

with this NMSB from 1st January 2014.

NOTE: The ESN data is provided for information only. If an engine has had a recent

shop visit, the ESN data may not be correct.

APPENDIX 3D

Printed in Great Britain

RB.211−72−AG244

Appendix 3D - Page 1 of 2

Aug 7/09

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Printed in Great Britain

RB.211−72−AG244

Appendix 3D - Page 2

Aug 7/09

R Jan.26/10
The following LP compressor blades listed are subject to inspection in accordance

with this NMSB from 1st January 2015.

NOTE: The ESN data is provided for information only. If an engine has had a recent

shop visit, the ESN data may not be correct.

APPENDIX 3E

Printed in Great Britain

RB.211−72−AG244

Appendix 3E - Page 1 of 2

Aug 7/09

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Printed in Great Britain

RB.211−72−AG244

Appendix 3E - Page 2

Aug 7/09

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The following LP compressor blades listed below are subject to inspection in

accordance with this NMSB from 1st January 2016.

NOTE: The ESN data is provided for information only. If an engine has had a recent

shop visit, the ESN data may not be correct.

APPENDIX 3F

Printed in Great Britain

RB.211−72−AG244

Appendix 3F - Page 1 of 4

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Printed in Great Britain

RB.211−72−AG244

Appendix 3F - Page 2

Aug 7/09

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R Appendix 3F continued:

The following LP compressor blades listed below are subject to inspection in

accordance with this NMSB from 1st January 2016.

R

R

NOTE: The ESN data is provided for information only. If an engine has had a recent

shop visit, the ESN data may not be correct.

R

R

Printed in Great Britain

RB.211−72−AG244

Appendix 3F - Page 3

Aug 7/09

R Jan.26/10
R

Printed in Great Britain

RB.211−72−AG244

Appendix 3F - Page 4

Aug 7/09

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