This document transmits the Initial Issue of Service Bulletin RB211-72-H311

Bulletin Initial Issue

Remove Incorporate Reason for change

Pages 1 to 41 of the

Service Bulletin

Initial Issue

Pages 1 to 6 of

Appendix 1

Initial Issue

Page 1 of Appendix 2 Initial Issue

Page 1 of Appendix 3 Initial Issue

Page 1 and 2 of

Appendix 4

Initial Issue

Pages 1, 3 to 5, 7

and 9 to 14 of

Appendix 5

Initial Issue

Printed in Great Britain

Mar. 8/13

RB211 TRENT 700 SERIES PROPULSION SYSTEMS NON-MODIFICATION SERVICE BULLETIN

RB.211−72−H311

Transmittal - Page 1 of 3

Signed Date
LIST OF EFFECTIVE PAGES

The effective pages to this Service Bulletin are as follows:

Page Revision Number Revision Date

Bulletin

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Appendix 1

1 Mar.8/13

2 Mar.8/13

Printed in Great Britain

RB.211−72−H311

Transmittal - Page 2
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4 Mar.8/13

5 Mar.8/13

6 Mar.8/13

Appendix 2

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Appendix 3

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Appendix 4

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2 Mar.8/13

Appendix 5

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4 Mar.8/13

5 Mar.8/13

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Printed in Great Britain

RB.211−72−H311

Transmittal - Page 3
1. Planning Information

A. Effectivity

Airbus A330

RB211 TRENT768-60, TRENT768-60/15, TRENT768-60/16 Engines which have an LP

compressor blade(s) with a Serial No. given in Appendix 1.

RB211 TRENT772-60, TRENT772-60/15, TRENT772-60/16 Engines which have an LP

compressor blade(s) with a Serial No. given in Appendix 1.

RB211 TRENT772B-60, TRENT772B-60/15, TRENT772B-60/16 Engines which have an LP

compressor blade(s) with a Serial No. given in Appendix 1.

RB211 TRENT772C-60/16 Engines which have an LP compressor blade(s) with a

Serial No. given in Appendix 1.

B. Reason

Problem

Non-Modification Service Bulletin (NMSB) 72-G872 introduced an in-service

ultrasonic inspection of LP Compressor (LPC) blades to mitigate against release

events. It has been established that a number of LP Compressor blades, with

serial numbers listed in Appendix 1, previously inspected in accordance with

NMSB 72-G872 were undertaken incorrectly and therefore require re-inspection.

This NMSB is issued to identify the LP compressor blades by serial number and

to instruct the re-inspection.

C. Description

(1) This Non-Modification Service Bulletin (NMSB) is issued to instruct an

ultrasonic inspection of LP compressor blades aerofoil as listed in

Appendix 1.

(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-H311

Printed in Great Britain

RB.211−72−H311

Page 1 of 41

Mar. 8/13

Mar. 8/13
(2) The Accomplishment Instructions for ultrasonic inspection of 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.

(f) Accomplishment Instructions for phased array inspection of LP

compressor blades removed from an engine on-wing. Refer to Section

3.H.

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 blades given in Appendix 1, with a life greater than

3,000 cycles since new or since last C-scan inspection on 30th June 2013.

E. Approval

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

under the authority of Design Organisation Approval EASA.21J.035 on Mar.8/13.

F. Manpower

On-wing:

(1) Time to remove LP compressor blades:

3 hours per LP compressor blade set (2 persons)

Printed in Great Britain

RB.211−72−H311

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Mar. 8/13
(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)

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.

Additionally, all inspection personnel utilising this technique

must have received specific training and approval by the

Rolls-Royce NDE Laboratory.

(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:

Tool No. Description Qty

RR1024167 Single head ultrasonic

immersion system

1 off

QC6808 Single head calibration

blade

1 off

M403T Triple head ultrasonic

immersion system

1 off

Printed in Great Britain

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Page 3

Mar. 8/13

Mar. 8/13
HU82364 Triple head calibration

blade

1 off

RRT076133 Phased array inspection

kit

1 off

RRT076135 Fan blade holder 1 off

(2) Consumable Materials:

Consumable No. Description

OMat 655 Ultrasonic Couplant

I. References

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

72-G872

Engine - LP Compressor - Inspection of LP Compressor Blades

(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 of the LP Compressor Blades

(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)

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(b) Task 72-31-11-100-801, Clean the Low Pressure (LP) Compressor Blades

(c) Task 72-31-11-200-800, General data for the Inspection/Check of the

Low Pressure (LP) Compressor Blades and Fillers

(d) 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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Mar. 8/13
2. Material Information

A. None

Printed in Great Britain

RB.211−72−H311

Page 6

Mar. 8/13

Mar. 8/13
3. Accomplishment Instructions

A. Identify recipient engine for ultrasonic 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 ultrasonic 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 (Repair 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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Mar. 8/13
(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-H311 must be

recorded against the individual blades and compliance, blade serial

numbers and associated lives (TSN/CSN) logged with the 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.

(2) Option 1: Carry out C-scan inspection of LP compressor blades - Single

head C-Scan equipment.

(a) Special Tools:

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Mar. 8/13
RR1024167 Single head ultrasonic

immersion system

1 off

QC6808 Single head

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.

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

Blade' and type 'test' in the SERIAL NUMBER box.

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(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

One at the top of

the panel and one at

the bottom

N/A Continue the

procedure

Printed in Great Britain

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Page 10

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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.

(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.

Printed in Great Britain

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(3) Option 2: Carry out C-scan inspection of LP compressor blades - Triple

head C-Scan equipment.

(a) Special Tools:

M403T Triple head ultrasonic

immersion system

1 off

HU82364 Triple head

calibration blade

1 off

NOTE: The tools specified are the minimum standard for this Task.

(b) Calibrate the C-Scan Equipment:

(i) Switch on the system and allow to warm up for 10 minutes.

(ii) Enter operator details and log on to the system.

(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.

(iv) Check for air bubbles on the probe faces by wiping the probe

faces with a soft brush whilst the probes are immersed.

(v) Select the calibrate icon from the presented menu. The system

will prompt the user to load the calibration blade.

(vi) Load the calibration blade HU82364.

(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.

(viii) Type TEST in the blade serial number box and select TRENT

CALIBRATION BLADE.from the blade type drop down menu.

(ix) Scan the calibration blade again. The system will then reject

the calibration blade.

NOTE: Do not archive this scan result.

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(x) Check the results of the calibration scan meet the following

criteria:

(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.

(2) Individual indications below fifty percent scan height shall

be in the range of 5 to 15 inclusive.

(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.

(4) If the above criteria are not fulfilled then repat steps 3 to

10 inclusive.

(5) Record the results in a historical log:

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.

(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.

(c) Focus inspect the LP compressor blades:

(i) Select the fan blade standard to be inspected from the drop

down menu.

NOTE: The correct scan program for Trent blades is always

suffixed by the letter A e.g. T700A.

(ii) Enter details of the blade to be inspected: SERIAL NUMBER, PART

NUMBER, ENGINE NUMBER, HOURS and CYCLES.

(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.

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(iv) Click OK and the system will automatically scan and sentence

the blade as accept or reject.

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) If the blade is accepted then continue as per steps (ii) to

(iv).

(vi) If the blade is rejected then the scan must be ARCHIVED as

prompted.

(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.

(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.

(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-H311 must be recorded against the individual

blades and compliance, blade serial numbers and associated lives (TSN/CSN)

logged with the 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).

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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:

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 2) 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-H311 must be recorded against the individual

blades and compliance, blade serial numbers and associated lives (TSN/CSN)

logged with the 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-H311 must be recorded against the individual

blades and compliance, blade serial numbers and associated lives (TSN/CSN)

logged with the local FSO.

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Mar. 8/13
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.

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(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−H311

Page 17

Mar. 8/13

Mar. 8/13
(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−H311

Page 18

Mar. 8/13

Mar. 8/13
(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 2) 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-H311 must be recorded against the individual

blades and compliance, blade serial numbers and associated lives (TSN/CSN)

logged with the local FSO.

G. Accomplishment Instructions for phased array inspection of LP Compressor Blades

installed on an Engine.

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.

(1) Visually inspect LP compressor blades in accordance with AMM Task

72-31-41-200-801, Inspection/Check.

(2) Remove LP compressor annulus fillers:

(a) Remove the LP compressor annulus fillers in accordance with AMM

72-31-41, Removal/Installation.

(3) Prepare ultrasonic array and OmniScan as per Appendix 3.

(4) Check the system as per Appendix 4.

(5) Calibrate the probe as per Appendix 5.

Printed in Great Britain

RB.211−72−H311

Page 19

Mar. 8/13

Mar. 8/13
(6) Attach the scanning frame to the first LP compressor blade to be

inspected.

(a) Rotate the fan so that the blade is in an 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.

(b) Secure the fan blade using the blade immobiliser HU44525, as shown in

Fig.5.

(c) Make sure the fan blade surface is clean and is free of any loose

dust, dirt or grease.

(d) Position the fan blade holder so the axial locating rod touches the

fan liner, as shown in Fig.6.

(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.

(f) Squeeze the clamps shut. Make sure the blocks are still against the

leading-edge.

(g) To release the clamps, pull the middle lever.

(7) Inspect both sides of the LP compressor blade as per the procedure in

Appendix 6.

(8) Repeat steps (6) and (7) for the remaining LP compressor blades.

(9) Restore the engine to a serviceable condition in accordance with AMM

72-31-41, Removal/Installation.

(10) Accomplishment of NMSB 72-H311 must be recorded against the individual

blades and compliance, blade serial numbers and associated lives (TSN/CSN)

logged with the local FSO.

H. Accomplishment Instructions for phased array inspection of LP Compressor Blades

removed from an Engine - On-wing.

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.

(1) Prepare ultrasonic array and OmniScan as per Appendix 3.

(2) Check the system as per Appendix 4.

(3) Calibrate the probe as per Appendix 5.

Printed in Great Britain

RB.211−72−H311

Page 20

Mar. 8/13

Mar. 8/13
(4) Attach the scanning frame to the first LP compressor blade to be

inspected.

(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.

(b) Place the fan blade on the holder suction (convex) side up, as shown

in Fig.9.

NOTE: Make sure the fan blade's retaining straps and shear keys are

removed before placing in the holder.

(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.

(d) Make sure the fan blade surface is clean and is free of any loose

dust, dirt or grease.

(e) Position the fan blade holder so the axial locating rod is touching

the holder support as shown in Fig.11.

(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.

(g) Squeeze the clamps shut. Make sure the blocks are still against the

leading-edge.

(h) To release the clamps, pull on the middle lever.

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.

(5) Inspect both sides of the LP compressor blade as per the procedure in

Appendix 6.

(6) Repeat steps (4) and (5) for the remaining LP compressor blades.

(7) Accomplishment of NMSB 72-H311 must be recorded against the individual

blades and compliance, blade serial numbers and associated lives (TSN/CSN)

logged with the local FSO.

Printed in Great Britain

RB.211−72−H311

Page 21

Mar. 8/13

Mar. 8/13
Flowchart

Fig.1

Printed in Great Britain

RB.211−72−H311

Page 22

Mar. 8/13

Mar. 8/13
Acceptance Zone Dimensions

Fig.2

Printed in Great Britain

RB.211−72−H311

Page 23

Mar. 8/13

Mar. 8/13
LP Compressor Blades - Bends

Fig.3

Printed in Great Britain

RB.211−72−H311

Page 24

Mar. 8/13

Mar. 8/13
LP Compressor Blades - Inspection Areas

Fig.4

Printed in Great Britain

RB.211−72−H311

Page 25

Mar. 8/13

Mar. 8/13
LP Compressor Blade Immobiliser

Fig.5

Printed in Great Britain

RB.211−72−H311

Page 26

Mar. 8/13

Mar. 8/13
Axial Position of the Scanning Frame on the LP Compressor Blade

Fig.6

Printed in Great Britain

RB.211−72−H311

Page 27

Mar. 8/13

Mar. 8/13
Correct Position of the Clamps on the LP Compressor Blade for the Root End

Fig.7

Printed in Great Britain

RB.211−72−H311

Page 28

Mar. 8/13

Mar. 8/13
Correct Position of the Clamps on the LP Compressor Blade for the Tip End

Fig.8

Printed in Great Britain

RB.211−72−H311

Page 29

Mar. 8/13

Mar. 8/13
LP Compressor Blade Suction (Convex) Side Up in the Holder

Fig.9

Printed in Great Britain

RB.211−72−H311

Page 30

Mar. 8/13

Mar. 8/13
LP Compressor Blade Pressure (Concave) Side Up on the Holder with Holder Clamp in

Place

Fig.10

Printed in Great Britain

RB.211−72−H311

Page 31

Mar. 8/13

Mar. 8/13
Axial Position of the Scanning Frame on the LP Compressor Blade

Fig.11

Printed in Great Britain

RB.211−72−H311

Page 32

Mar. 8/13

Mar. 8/13
Schematic Diagram of the Bottom-Side of the Working Standard

Fig.12

Printed in Great Britain

RB.211−72−H311

Page 33

Mar. 8/13

Mar. 8/13
Schematic Diagram of the Working Standard Cross-Section Showing the 5.5 mm step

Fig.13

Printed in Great Britain

RB.211−72−H311

Page 34

Mar. 8/13

Mar. 8/13
Schematic Diagram of the Working Standard Cross-Section Showing the Probe Inspecting

the Notch at the Material Depth of 6 mm

Fig.14

Printed in Great Britain

RB.211−72−H311

Page 35

Mar. 8/13

Mar. 8/13
Image Showing the Correct Position of the Scan Arm Holder

Fig.15

Printed in Great Britain

RB.211−72−H311

Page 36

Mar. 8/13

Mar. 8/13
Scan Arm Positioned to the First Index Positiom

Fig.16

Printed in Great Britain

RB.211−72−H311

Page 37

Mar. 8/13

Mar. 8/13
Screen Shot of the OmniScan that the LP Compressor Blade Surface Signal is within

the Interface Gate Extent

Fig.17

Printed in Great Britain

RB.211−72−H311

Page 38

Mar. 8/13

Mar. 8/13
Screen Shot of the OmniScan Showing Lines of Data that were not Recorded because the

Probe was Scanned too Quickly

Fig.18

Printed in Great Britain

RB.211−72−H311

Page 39

Mar. 8/13

Mar. 8/13
Screen Shot of the OmniScan Showing a 5mm Long by 0.5 mm Deep Notch in a LP

Compressor Blade

Fig.19

Printed in Great Britain

RB.211−72−H311

Page 40

Mar. 8/13

Mar. 8/13
Diagram Showing the Achievable Scanning Area due to On-wing Geometry Limitations

Fig.20

Printed in Great Britain

RB.211−72−H311

Page 41

Mar. 8/13

Mar. 8/13
LP Compressor Blade Serial Numbers

NOTE: The prefix marking of the blade serial numbers changed from RGF to RRWCFBRGF

in December 2012 and therefore may affect blades from RGF39000 onwards.

APPENDIX 1

Printed in Great Britain

RB.211−72−H311

Appendix 1 - Page 1 of 6

Mar. 8/13

Mar. 8/13
Printed in Great Britain

RB.211−72−H311

Appendix 1 - Page 2

Mar. 8/13

Mar. 8/13
Printed in Great Britain

RB.211−72−H311

Appendix 1 - Page 3

Mar. 8/13

Mar. 8/13
Printed in Great Britain

RB.211−72−H311

Appendix 1 - Page 4

Mar. 8/13

Mar. 8/13
Printed in Great Britain

RB.211−72−H311

Appendix 1 - Page 5

Mar. 8/13

Mar. 8/13
Printed in Great Britain

RB.211−72−H311

Appendix 1 - Page 6

Mar. 8/13

Mar. 8/13
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 2

Printed in Great Britain

RB.211−72−H311

Appendix 2 - Page 1 of 1

Mar. 8/13

Mar. 8/13
Ultrasonic Array and OmniScan Preparation

1. Ultrasonic Array and OmniScan Preparation

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.

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.

C. If it is not already, insert the flexible wedge into the wedge housing.

D. Apply sufficient couplant to cover the wedge/array interface.

E. Attach the wedge housing to the array using the four screws. Make sure the

screws are done up tightly.

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.

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.

G. Connect the array to the OmniScan using the OmniScan connector. Make sure

the connector is screwed into the OmniScan tightly.

H. Make sure the Secure Digital High Capacity (SDHC) memory card is in the

OmniScan memory card slot.

NOTE: If the switch on the side of the memory card is set to Lock, the

OmniScan will not boot up correctly.

I. Turn on the OmniScan by pressing the Power Button for one second.

J. If the boot up screen appears press MXU 3.2.

K. Make sure the OmniScan is charging or the battery has sufficient charge for

the required inspection.

APPENDIX 3

Printed in Great Britain

RB.211−72−H311

Appendix 3 - Page 1 of 1

Mar. 8/13

Mar. 8/13
System Check

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.

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.

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.

1. Perform the system check:

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.

B. Apply couplant to the front-face of the wedge.

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.

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.

E. If any dead elements are still present, replace the array and send the

broken array for repair.

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.

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.

APPENDIX 4

Printed in Great Britain

RB.211−72−H311

Appendix 4 - Page 1 of 2

Mar. 8/13

Mar. 8/13
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.

I. Make sure all signals are within the 40 per cent tolerance bars.

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.

K. Exit the Calibration Wizard by pressing the Cancel key.

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.

L. If the setup is accidentally saved, load the

Master_RR_T700FB_Probe_Check.ops. Check the settings are the same as in

Appendix 9. Save this setup as RR_T700FB_Probe_Check.ops.

Printed in Great Britain

RB.211−72−H311

Appendix 4 - Page 2

Mar. 8/13

Mar. 8/13
Calibration Procedure

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.

1. Perform the Calibration:

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.

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.

C. Maximise the signal from the notch.

D. Change the gain setting to set the maximised signal to 100 per cent screen

height. The gain should be around 27dB.

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.

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.

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 4.

APPENDIX 5

Printed in Great Britain

RB.211−72−H311

Appendix 5 - Page 1 of 1

Mar. 8/13

Mar. 8/13
Inspection Procedure

1. Inspection Procedure

A. Attach the ultrasonic probe to the scan arm using the two hex screws in the

probe holder.

B. Connect the encoder to the OmniScan using the scanner interface.

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'.

D. Connect the string encoder clip to the correct carriage arm.

E. Cover the area of the blade that is to be scanned with couplant.

CAUTION: MAKE SURE THERE IS ADEQUATE COUPLANT BETWEEN THE PROBE AND AEROFOIL

SURFACE AT ALL TIMES TO PREVENT DEFECTS BEING MISSED

F. Put couplant on the wedge surface and make sure the probe flows easily over

the blade surface.

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.

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.

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.

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.

K. Apply a firm pressure to the probe to make sure the three housing feet are

always in contact with the blade surface.

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.

APPENDIX 6

Printed in Great Britain

RB.211−72−H311

Appendix 6 - Page 1 of 3

Mar. 8/13

Mar. 8/13
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.

CAUTION: MAKE SURE S-SCAN DISPLAY IS VIEWED CONTINUOUSLY DURING SCANNING TO

PREVENT DEFECTS BEING MISSED

M. Whilst scanning the Probe along the blade, view the S-Scan display for

potential defect indications.

N. The finish point of the scan is when the carriage reaches the end of the

rail.

O. Once a scan line is finished press the Freeze key to freeze the scan. View

the C-Scan for potential defect indications.

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.

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. Reject any indication greater than 60 per cent screen height.

S. Record the details of indications greater than 60 per cent screen height

using the appropriate sheets in Appendix 7.

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.

U. Extended the scan arm 20mm to the next scan index position and repeat steps

J. to T. until the final scan index has been scanned.

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.

Printed in Great Britain

RB.211−72−H311

Appendix 6 - Page 2

Mar. 8/13

Mar. 8/13
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.

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.

X. Record the inspection result of the blade on the sheet in Appendix 7. If

any indications are present record the details on the appropriate sheets in

Appendix 8.

Y. Once the fan blade surface has been inspected, remove the couplant from the

blade surface.

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.

Z. If the setup is accidentally saved, load the

Master_RR_T700FB_Frame_Scan.ops. Check the settings are the same as in

Appendix 10. Save this setup as RR_T700FB_Frame_Scan.ops.

Printed in Great Britain

RB.211−72−H311

Appendix 6 - Page 3

Mar. 8/13

Mar. 8/13
Ultrasonic Array Trent 700 Fan Blade Results Sheet

Blade Number Results

(Pass/Fail)

Gain

(dB)

Blade Number Results

(Pass/Fail)

Gain

(dB)

SS SS

PS PS

SS SS

PS PS

SS SS

PS PS

SS SS

PS PS

SS SS

PS PS

SS SS

PS PS

SS SS

PS PS

SS SS

PS PS

SS SS

PS PS

SS SS

PS PS

SS SS

PS PS

SS SS

PS PS

SS SS

PS PS

Inspectors:.................................

Date:.........................................

Probe S/N:.................................

Omni-Scan S/N:.........................

Operator:...................................

ESN:.........................................

APPENDIX 7

Printed in Great Britain

RB.211−72−H311

Appendix 7 - Page 1 of 1

Mar. 8/13

Mar. 8/13
Ultrasonic Array Trent 700 fan Blade Indication Sheet

For any indications over 60 per cent screen height:

- Measure the location of the indication.

- Mark an 'X' on the appropriate diagram below showing its approximate location

- Label the indication with a reference (i.e.'A')

- Fill in the table below with the details of the indication

Reference

label

A-Scan Signal

(% SH)

Gain Setting

(dB)

Distance from

Blade Root

(mm)

Distance from

Leading Edge

(mm)

Image File

Name

Inspectors:.................................

Date:.........................................

Probe S/N:.................................

Omni-Scan S/N:.........................

Operator:...................................

ESN:.........................................

APPENDIX 8

Printed in Great Britain

RB.211−72−H311

Appendix 8 - Page 1 of 2

Mar. 8/13

Mar. 8/13
Printed in Great Britain

RB.211−72−H311

Appendix 8 - Page 2

Mar. 8/13

Mar. 8/13
Settings for Master RR ProbeCheck.ops

To check the settings: click File - Report - Preview then check the settings match

those below:

1. Setup

- Beam delay - 0.0 micro second

- Start - 40.01 mm

- Range - 20.00 mm

- Video Filter - On

- Rectification - FW

- Filter - None 0.9 - 17.7 MHz

- Voltage - 115 (High)

- Gain - 23 dB

- Sound Velocity - 3100 m/s

- Pulse Width - 50.00 ns

A. Gate A

(1)Start - 52.03 mm

(2)Width - 10.0 mm

(3)Threshold - 10.0 per cent

(4)Synchro - Pulse

(5)Peak - Selection - Max. Peak

2. Calculator

- Element Qty. Used - 1

- First Element - 1

- Last Element - 64

- Resolution - 1.0

- Wave Type - Shear

APPENDIX 9

Printed in Great Britain

RB.211−72−H311

Appendix 9 - Page 1 of 2

Mar. 8/13

Mar. 8/13
- Material Velocity - 3100 m/s

- Start Angle - 0.00 degrees

- Focal Depth - 5.00 mm

- Law Configuration - Linear

NOTE: Make sure only one group is in operation

Printed in Great Britain

RB.211−72−H311

Appendix 9 - Page 2

Mar. 8/13

Mar. 8/13
Settings for Master RR T700FB Frame Scan.ops

To check the settings: click File - Report - Preview then check the settings match

those below:

1. Setup

- Beam delay - 0.0 micro second

- Start - 35.00 mm

- Range - 29.99 mm

- Video Filter - On

- Rectification - FW

- Filter - None 0.53 - 17.7 MHz

- Voltage - 115 (High)

- Gain - 30 dB

- Sound Velocity - 3100 m/s

- Pulse Width - 50.00 ns

- Sum Gain - 18.1 dB

A. Gate I

(1)Start - 39.80 mm

(2)Width - 15.21 mm

(3)Threshold - 3.00 per cent

(4)Synchro - Pulse

(5)Peak - Selection - Max. Peak

B. Gate A

(1)Start - 5.01 mm

(2)Width - 12.00 mm

(3)Threshold - 30.00 per cent

(4)Synchro - I-edge

APPENDIX 10

Printed in Great Britain

RB.211−72−H311

Appendix 10 - Page 1 of 2

Mar. 8/13

Mar. 8/13
(5)Peak - Selection - Max. Peak

2. Law

Law File Name - FB_8el_f5_64el.law

3. Scan Area

- Scan Start - 0.00mm

- Scan Length - 600.00mm

- Scan Resolution - 0.5mm

- Synchro - Encoder

- Axis - Scan

- Encoder - 1

- Encoder Type - Quadrature

- Encoder Resolution - 24.00 step/mm

- Polarity - Inverse

NOTE: Make sure only one group is in operation

Printed in Great Britain

RB.211−72−H311

Appendix 10 - Page 2

Mar. 8/13

Mar. 8/13