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 DateLIST OF EFFECTIVE PAGES The effective pages to this Service Bulletin are as follows: Page Revision Number Revision Date

Bulletin 1 Mar.8/13 2 Mar.8/13 3 Mar.8/13 4 Mar.8/13 5 Mar.8/13 6 Mar.8/13 7 Mar.8/13 8 Mar.8/13 9 Mar.8/13 10 Mar.8/13 11 Mar.8/13 12 Mar.8/13 13 Mar.8/13 14 Mar.8/13 15 Mar.8/13 16 Mar.8/13 17 Mar.8/13 18 Mar.8/13 19 Mar.8/13 20 Mar.8/13 21 Mar.8/13 22 Mar.8/13 23 Mar.8/13 24 Mar.8/13 25 Mar.8/13 26 Mar.8/13 27 Mar.8/13 28 Mar.8/13 29 Mar.8/13 30 Mar.8/13 31 Mar.8/13 32 Mar.8/13 33 Mar.8/13 34 Mar.8/13 35 Mar.8/13 36 Mar.8/13 37 Mar.8/13 38 Mar.8/13 39 Mar.8/13 40 Mar.8/13 41 Mar.8/13 Appendix 1 1 Mar.8/13 2 Mar.8/13**Printed in Great Britain**



# RB.211−72−H311 Transmittal - Page 23 Mar.8/13 4 Mar.8/13 5 Mar.8/13 6 Mar.8/13 Appendix 2 1 Mar.8/13 Appendix 3 1 Mar.8/13 Appendix 4 1 Mar.8/13 2 Mar.8/13 Appendix 5 1 Mar.8/13 3 Mar.8/13 4 Mar.8/13 5 Mar.8/13 7 Mar.8/13 9 Mar.8/13 10 Mar.8/13 11 Mar.8/13 12 Mar.8/13 13 Mar.8/13 14 Mar.8/13**Printed in Great Britain**



# RB.211−72−H311 Transmittal - Page 31. 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 Page 2 Mar. 8/13 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**



# RB.211−72−H311 Page 3 Mar. 8/13 Mar. 8/13HU82364 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)**Printed in Great Britain**



# RB.211−72−H311 Page 4 Mar. 8/13 Mar. 8/13(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**



# RB.211−72−H311 Page 5 Mar. 8/13 Mar. 8/132. Material Information
A. None**Printed in Great Britain**



# RB.211−72−H311 Page 6 Mar. 8/13 Mar. 8/133. 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.**Printed in Great Britain**



# RB.211−72−H311 Page 7 Mar. 8/13 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:**Printed in Great Britain**



# RB.211−72−H311 Page 8 Mar. 8/13 Mar. 8/13RR1024167 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.**Printed in Great Britain**



# RB.211−72−H311 Page 9 Mar. 8/13 Mar. 8/13(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**



# RB.211−72−H311 Page 10 Mar. 8/13 Mar. 8/13None 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**



# RB.211−72−H311 Page 11 Mar. 8/13 Mar. 8/13(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.**Printed in Great Britain**



# RB.211−72−H311 Page 12 Mar. 8/13 Mar. 8/13(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.**Printed in Great Britain**



# RB.211−72−H311 Page 13 Mar. 8/13 Mar. 8/13(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).**Printed in Great Britain**



# RB.211−72−H311 Page 14 Mar. 8/13 Mar. 8/13(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.**Printed in Great Britain**



# RB.211−72−H311 Page 15 Mar. 8/13 Mar. 8/13F. Accomplishment Instructions for C-scan inspection of LP Compressor Blades, removed from an Engine On-Wing, undertaken in an Overhaul Facility where serviceability restoration is required. (1) Clean the LP compressor blades: (a) Clean the LP compressor blades in accordance with EM Task 72-31-11-100-801, Subtask 72-31-11-110-006-001 (non-aqueous vapour and liquid degreasing OP Task 70-00-00-100-101) or Subtask 72-31-11-110-006-002 (primary clean OP Task 70-00-00-100-102, Subtask 70-00-00-110-102-001). (b) If there is the presence of Dry Film Lubricant (DFL) in the LP compressor blade aerofoil, mask the LP compressor blade root and clean as follows:
CAUTION : TO MAINTAIN THE CLEANLINESS OF THE WIPING SOLVENT, YOU MUST POUR THE SOLVENT ONTO THE WIPING CLOTH. THE CLOTH MUST NOT BE DIPPED INTO THE SOLVENT CONTAINER. (i) Apply the solvent to the area to be cleaned using an OMat 2/101 lint free cloth moistened with either OMat 150 Acetone, OMat 1/40 Isopropyl alcohol. Discard the soiled cloth after use. (ii) Repeat the swabbing using fresh cloth and solvent until the area is clean and free of DFL. (iii) Allow the parts to dry. Drying may be assisted by removing excess solvent using a clean dry lint-free cloth (Material No. OMat 2/101) or a clean oil-free air blast to help dry the part. (iv) Remove masks from the LP compressor blade root. (2) Visually inspect LP compressor blades. Refer to Fig.2, Fig.3 and Fig.4 for details.
NOTE : It is normal to see the panel lines on the airfoil surfaces near the tip of the LP compressor fan blades. This is not an indication of rippling caused by LP compressor fan blade damage. (a) Examine the blade aerofoil for rippling: (i) If the blade has ripples up to 0.16 mm (0.006 in.) in depth (minor ripples within the manufacturing specification) - Accept the blade. (ii) If the blade has one or more ripples of any length with a form more than in step above - Reject the blade.**Printed in Great Britain**



# RB.211−72−H311 Page 16 Mar. 8/13 Mar. 8/13(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. 8/13Flowchart Fig.1**Printed in Great Britain**



# RB.211−72−H311 Page 22 Mar. 8/13 Mar. 8/13Acceptance Zone Dimensions Fig.2**Printed in Great Britain**



# RB.211−72−H311 Page 23 Mar. 8/13 Mar. 8/13LP Compressor Blades - Bends Fig.3**Printed in Great Britain**



# RB.211−72−H311 Page 24 Mar. 8/13 Mar. 8/13LP Compressor Blades - Inspection Areas Fig.4**Printed in Great Britain**



# RB.211−72−H311 Page 25 Mar. 8/13 Mar. 8/13LP Compressor Blade Immobiliser Fig.5**Printed in Great Britain**



# RB.211−72−H311 Page 26 Mar. 8/13 Mar. 8/13Axial 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. 8/13Correct 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. 8/13Correct 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. 8/13LP 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. 8/13LP 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. 8/13Axial 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. 8/13Schematic 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. 8/13Schematic 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. 8/13Schematic 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. 8/13Image 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. 8/13Scan Arm Positioned to the First Index Positiom Fig.16**Printed in Great Britain**



# RB.211−72−H311 Page 37 Mar. 8/13 Mar. 8/13Screen 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. 8/13Screen 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. 8/13Screen 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. 8/13Diagram 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. 8/13LP 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. 8/13LP 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. 8/13Ultrasonic 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. 8/13System 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. 8/13H. 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. 8/13Calibration 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. 8/13Inspection 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. 8/13L. 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. 8/13V. 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. 8/13Ultrasonic 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. 8/13Ultrasonic 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. 8/13Settings 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. 8/13Settings 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