This document transmits Revision 1 to Service Bulletin RB211-72-G872 Document History Service Bulletin Revision Status Supplement Revision Status Initial Issue Apr.3/12 Bulletin Revision 1 Remove Incorporate Reason for change Pages 1 to 12 of the Service Bulletin Pages 1 to 19 of the Service Bulletin To add Fig.2, Fig.3, Fig.4 and an additional section 3.F. to Accomplishment Instructions. Revised 1.D. Compliance. Updated 1.B. Reason and 1.E. Approval. All pages of Appendix 1 Page 1 of Appendix 1 To add Fig.2, Fig.3, Fig.4 and an additional section 3.F. to Accomplishment Instructions. Revised 1.D. Compliance. Updated 1.B. Reason and 1.E. Approval.**Printed in Great Britain** Jul. 2/12

RB211 TRENT 700 SERIES PROPULSION SYSTEMS NON-MODIFICATION SERVICE BULLETIN



# RB.211−72−G872 Transmittal - Page 1 of 2 Signed DateLIST OF EFFECTIVE PAGES The effective pages to this Service Bulletin following incorporation of Revision 1 are as follows: Page Revision Number Revision Date

Bulletin R 1 1 Jul.2/12 R 2 1 Jul.2/12 R 3 1 Jul.2/12 R 4 1 Jul.2/12 R 5 1 Jul.2/12 R 6 1 Jul.2/12 R 7 1 Jul.2/12 R 8 1 Jul.2/12 R 9 1 Jul.2/12 R 10 1 Jul.2/12 R 11 1 Jul.2/12 R 12 1 Jul.2/12 R 13 1 Jul.2/12 R 14 1 Jul.2/12 R 15 1 Jul.2/12 R 16 1 Jul.2/12 R 17 1 Jul.2/12 R 18 1 Jul.2/12 R 19 1 Jul.2/12 Appendix 1 R 1 1 Jul.2/12**Printed in Great Britain**



# RB.211−72−G872 Transmittal - Page 21. Planning Information A. Effectivity Airbus A330 RB211 TRENT768-60, TRENT768-60/15, TRENT768-60/16 Engines RB211 TRENT772-60, TRENT772-60/15, TRENT772-60/16 Engines RB211 TRENT772B-60, TRENT772B-60/15, TRENT772B-60/16 Engines RB211 TRENT772C-60/16 Engines
B. Reason Problem Following in-service Low Pressure (LP) compressor blade release events it is recommended that an in-service inspection (C-scan) is undertaken to mitigate against release events. The C-scan inspection is capable of detecting sub-surface anomalies in the LP compressor blade aerofoil. This inspection is already in place for Trent 700 LP compressor blades at every shop visit but the intervals between shop visits is too large to only use shop visit opportunities. Revision 1 of this Non-Modification Service Bulletin (NMSB) is being issued to add an additional section into the Accomplishment Instructions for C-scan inspection of LP compressor blades, removed from am engine on-wing undertaken in an overhaul facility where serviceability restoration is required. In addition, Section 1.D. Compliance has been updated to clearly define what LP compressor blades are affected by this NMSB and which inspections can be claimed. R R R R R R R C. Description (1) This Non-Modification Service Bulletin (NMSB) has been issued to instruct C-scan inspection of LP compressor blades. (a) Accomplishment of this NMSB must be recorded against the individual blades. (b) Inform your assigned Rolls-Royce Service Representative of NMSB accomplishment. ENGINE - LP COMPRESSOR - INSPECTION OF LP COMPRESSOR BLADES - NON-MODIFICATION SERVICE BULLETIN - NON - MOD.72-G872**Printed in Great Britain**



# RB.211−72−G872 Page 1 of 19 Apr 3/12 Jul. 2/12 R(2) The Accomplishment Instructions for C-scan inspection of removed LP compressor blades is dependent on where the inspection is undertaken as follows: (a) Accomplishment instructions for C-scan inspection of LP compressor blades, removed from an engine on-wing, undertaken by the operator locally, refer to Section 3. C. (b) Accomplishment instructions for C-scan inspection of LP compressor blades, removed from an engine on-wing, undertaken in an overhaul facility, refer to Section 3. D. (c) Accomplishment instructions for C-scan inspection of LP compressor blades, removed from an engine in-shop, refer to Section 3. E. (d) Accomplishment Instructions for C-scan inspection of LP compressor blades, removed from an engine on-wing undertaken in an overhaul facility where serviceability restoration is required, refer to Section 3.F. R R R R D. Compliance
RECOMMENDED Rolls-Royce recommends that the following action is undertaken to maintain reliability. This Non-Modification Service Bulletin should be accomplished by 30th June 2013, R R on all LP compressor blade standards with a life greater than 3,000 cycles since new or since last C-scan inspection on R 30th June 2013.
NOTE : If an operator finds it convenient to inspect R LP compressor blades earlier than 3,000 cycles, then inspection R in accordance with this Non-Modification Service Bulletin R can be accredited provided the life of the LP compressor blades are at least 2,000 cycles from new. R R
NOTE : LP compressor blades previously inspected in-shop in accordance with Engine Manual or to NMSB 72-G702 can be accredited against this Non-Modification Service Bulletin at any life of LP compressor blade. R R R E. Approval The technical content of this Non-Modification Service Bulletin was approved under the authority of Design Organisation Approval EASA.21J.035 on Apr.2/12 and was re-approved on Jul.2/12. R R F. Manpower On-wing:**Printed in Great Britain**



# RB.211−72−G872 Page 2 Apr 3/12 Jul. 2/12 R(1) Time to remove LP compressor blades: 3 hours per LP compressor blade set (2 persons) (2) Time to inspect LP compressor blades: (a) Visual inspection - 4 hours per LP compressor blade set (1 person) (b) C-scan inspection - 28 hours per LP compressor blade set (1 person) (3) Time to install LP compressor blades: 3 hours per LP compressor blade set (2 persons)
NOTE : A vibration ground run will be required. G. Material Price and Availability
None. H. Tooling Price and Availability (1) Tooling for LP compressor blade inspection:

RR1024167 Ultrasonic immersion system 1 off

QC6808 Calibration blade 1 off

I. References (1) Rolls-Royce RB211 Non-Modification Service Bulletin: 72-G702 Engine - LP Compressor - Inspection of LP Compressor Blades - Non-Modification Service Bulletin (2) Aircraft Maintenance Manual (AMM): (a) 72-00-00, Test No.11 The Engine Vibration Survey (b) Task 70-20-01-100-802, Non-Aqueous Liquid Degreasing - Maintenance Process 101 (c) 72-31-41, Removal/Installation of LP Compressor Blades and Dampers (d) Task 72-31-41-200-801, Inspection/Check**Printed in Great Britain**



# RB.211−72−G872 Page 3 Apr 3/12 Jul. 2/12 R(e) 72-31-41, LP Compressor Rotor Blade - Re-apply the Dry Film Lubricant (FRSA031) (f) 72-31-51, LP Compressor Disc - Re-apply the Dry Film Lubricant (FRSA017) (3) Engine Manual (EM): (a) Task 70-00-00-100-102, Overhaul Process 102, Primary Cleaning - Aqueous (TSD594J) (b) Task 72-31-11-100-801, Clean the Low Pressure (LP) Compressor Blades (c) Task 72-31-11-200-806, C-Scan Inspection of the Low Pressure (LP) Compressor Blades for Sub-Surface Cracks**Printed in Great Britain**



# RB.211−72−G872 Page 4 Apr 3/12 Jul. 2/12 R2. Material Information
A. None**Printed in Great Britain**



# RB.211−72−G872 Page 5 Apr 3/12 Jul. 2/12 R3. Accomplishment Instructions A. Identify recipient engine for C-scan inspected LP Compressor blades to make sure blades do not continue in-service greater than 6000 cycles before refurbishment. See Fig.1.
B. Accomplishment Instructions for Removal and Installation of LP Compressor Blades.

CAUTION : IN ORDER TO REDUCE THE POTENTIAL FOR MULTIPLE ENGINE IN FLIGHT SHUTDOWN, POWER LOSS OR OTHER ANOMALIES DUE TO MAINTENANCE ERROR, ROLLS-ROYCE RECOMMENDS THAT OPERATORS AVOID PERFORMING MAINTENANCE ON MULTIPLE ENGINES INSTALLED ON THE SAME AIRCRAFT AT THE SAME TIME. IF IT IS NOT POSSIBLE TO AVOID MAINTENANCE ON MORE THAN ONE ENGINE AT THE SAME TIME, ROLLS-ROYCE RECOMMENDS THAT ADDITIONAL CONTROLS ARE APPLIED IN ORDER TO ENSURE THAT MAINTENANCE TASKS HAVE BEEN COMPLETED AS DEFINED. MAINTENANCE GUIDELINES SHOULD BE REVISED, WHERE POSSIBLE, TO PROMOTE THIS RECOMMENDATION. (1) Remove LP Compressor blades: (a) Remove the applicable LP compressor blades in accordance with AMM 72-31-41, Removal/Installation. (2) Visually inspect the LP compressor blades in accordance with AMM Task 72-31-41-200-801, Inspection/Check. (3) Send removed LP compressor blades for C-scan inspection. (4) Re-apply the dry film lubricant to the replacement LP compressor blade roots in accordance with AMM Task 72-31-41-300-802 (FRSA031). (5) Re-apply the dry film lubricant to the LP compressor disc in accordance with AMM Task 72-31-51-300-801 (FRSA017). (6) Install the replacement LP compressor blades in accordance with AMM 72-31-41, Removal/installation. (7) Restore the engine to serviceable condition in accordance with AMM 72-31-41, Removal/Installation.**Printed in Great Britain**



# RB.211−72−G872 Page 6 Apr 3/12 Jul. 2/12 R(8) Carry out vibration survey in accordance with AMM, 71-00-00, Test No.11, The Engine Vibration Survey.
NOTE : If an engine trim balance is undertaken, then the post balance vibration survey may be waived provided the trim balance have been accomplished using Rolls-Royce balancing software VX77 and no more than 6 trim balance bolts have been added/removed. If further engine running is not undertaken then engine LP vibration should be monitored for the next 10 days. (9) If replacement LP compressor blades have been C-scanned then accomplishment of NMSB 72-G872 must be recorded against the individual blades and compliance logged with local FSO. C. Accomplishment Instructions for C-scan inspection of LP Compressor Blades, removed from an Engine On-Wing, undertaken by the Operator locally. (1) Clean the LP compressor blades. (a) Clean the LP compressor blades in accordance with AMM Task 70-20-01-100-802 (Non-Aqueous Liquid Degreasing (Maintenance Process 101)) (b) If there is the presence of Dry Film Lubricant (DFL) in the LP compressor blade aerofoil, mask the LP compressor blade root and clean as follows:
CAUTION : TO MAINTAIN THE CLEANLINESS OF THE WIPING SOLVENT, YOU MUST POUR THE SOLVENT ONTO THE WIPING CLOTH. THE CLOTH MUST NOT BE DIPPED INTO THE SOLVENT CONTAINER. (i) Apply the solvent to the area to be cleaned using an OMat 2/101 lint-free cloth moistened with either OMat 150 Acetone, OMat 1/40 Isopropyl alcohol. Discard the soiled cloth after use. (ii) Repeat the swabbing using fresh cloth and solvent until the area is clean and free of DFL. (iii) Allow the parts to dry. Drying may be assisted by removing excess solvent using a clean dry lint-free cloth (Material No. OMat 2/101) or a clean oil-free air blast to help dry the part. (iv) Remove masks from the LP compressor blade root.**Printed in Great Britain**



# RB.211−72−G872 Page 7 Apr 3/12 Jul. 2/12 R(2) Carry out C-scan inspection of LP compressor blades (a) Special Tools:

RR1024167 Ultrasonic immersion system 1 off

QC6808 Calibration blade 1 off

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



# RB.211−72−G872 Page 8 Apr 3/12 Jul. 2/12 R(viii) Set the BLADE TYPE box on the control screen to 'Calibrate Blade' and type test in the SERIAL NUMBER box. (ix) Re-scan the calibration blade. (1) The threshold values will be displayed on screen. Make a written record in a historical log.
NOTE : The calibration blade will be rejected by the second scan. Do not archive the calibration scan results. (x) Use the scan results to find the action necessary from the table that follows:

NUMBER OF DEFECTS CHECK ACTION

More than four N/A Do steps (v) to (ix) again. Inspect again any blade which failed since the last calibration check
Two at the top of the panel and two at the bottom If the WEIGHTING of one of the two smallest defects is seven or more Do steps (v) to (ix) again. Inspect again any blade which failed since the last calibration check
Two at the top of the panel and two at the bottom If the WEIGHTING of one of the two smallest defects are both less than seven Continue the procedure

Two at the top of the panel and one at the bottom N/A Continue the procedure

One at the top of the panel and two at the bottom N/A Continue the procedure**Printed in Great Britain**



# RB.211−72−G872 Page 9 Apr 3/12 Jul. 2/12 ROne at the top of the panel and one at the bottom N/A Continue the procedure

None of the above N/A Do steps (v) to (ix) again. Inspect again

all the work since the last calibration check
(xi) At 4 hour intervals, install the calibration blade and do steps (viii) to (x) to make sure the equipment is in the calibration limits. (c) Focus Inspect the LP compressor blades: (i) Set the BLADE TYPE box on the control screen to 'Trent 700 full'. (ii) Record the details of the blade to be scanned, PART NUMBER, SERIAL NUMBER, ENGINE/MODULE NUMBER, HOURS and CYCLES on the control screen. (iii) Install the LP compressor blade to be scanned. (iv) Scan the LP compressor blade.
NOTE : When the scan is complete, the system will automatically accept or reject the blade. Scan results from any blade rejected by the system must be archived as given on the control screen. (v) Do steps (i) to (iv) for the remaining blades. (vi) When the inspection is completed, install the QC6808 calibration blade 1 off and do steps (b)(viii) to (x) again. (d) Data retrieval (i) The inspection system records the inspection records in a text file named scanlog.txt. This file gives the PART NUMBER, SERIAL NUMBER, ENGINE/MODULE NUMBER, DATE INSPECTED and INSPECTION RESULT.**Printed in Great Britain**



# RB.211−72−G872 Page 10 Apr 3/12 Jul. 2/12 R(ii) If a blade is rejected, the system prompts the archive of a blade C-Scan data to an archive directory, where it is stored with the blade serial number as the file name. Inspection and blade data should be entered on the LP compressor blade rejection proforma (Appendix 1) and returned to Rolls-Royce with a copy of the archived scan data. (3) Let the LP compressor blades become dry: (a) Use a clean dry lint-free cloth (Material No. OMat 2/101) or a clean oil-free air blast to help dry the part. (4) Accomplishment of NMSB 72-G872 must be recorded against the individual blades and compliance logged with local FSO. D. Accomplishment Instructions for C-scan inspection of LP Compressor Blades, removed from an Engine On-Wing, undertaken in an Overhaul Facility. (1) Clean the LP compressor blades: (a) Clean the LP compressor blades in accordance with EM Task 72-31-11-100-801, Subtask 72-31-11-110-006-001 (non-aqueous vapour and liquid degreasing OP Task 70-00-00-100-101) or Subtask 72-31-11-110-006-002 (primary clean OP Task 70-00-00-100-102, Subtask 70-00-00-110-102-001). (b) If there is the presence of Dry Film Lubricant (DFL) in the LP compressor blade aerofoil, mask the LP compressor blade root and clean as follows:
CAUTION : TO MAINTAIN THE CLEANLINESS OF THE WIPING SOLVENT, YOU MUST POUR THE SOLVENT ONTO THE WIPING CLOTH. THE CLOTH MUST NOT BE DIPPED INTO THE SOLVENT CONTAINER. (i) Apply the solvent to the area to be cleaned using an OMat 2/101 lint free cloth moistened with either OMat 150 Acetone, OMat 1/40 Isopropyl alcohol. Discard the soiled cloth after use. (ii) Repeat the swabbing using fresh cloth and solvent until the area is clean and free of DFL. (iii) Allow the parts to dry. Drying may be assisted by removing excess solvent using a clean dry lint-free cloth (Material No. OMat 2/101) or a clean oil-free air blast to help dry the part. (iv) Remove masks from the LP compressor blade root. (2) Carry out C-scan inspection of LP compressor blades. (a) Carry out C-scan inspection of LP compressor blades in accordance with EM Task 72-31-11-200-806.**Printed in Great Britain**



# RB.211−72−G872 Page 11 Apr 3/12 Jul. 2/12 R(b) If a blade is rejected by the C-scan inspection, inspection and blade data should be entered on the LP compressor blade rejection proforma (Appendix 1) and returned to Rolls-Royce with a copy of the archived scan data. (3) Dry LP compressor blades. (a) Dry LP compressor blades in accordance with EM Task 70-00-00-100-102, Subtask 70-00-00-110-102-007. (4) Accomplishment of NMSB 72-G872 must be recorded against the individual blades and compliance logged with local FSO. E. Accomplishment Instructions for C-scan inspection of LP Compressor Blades, removed from an Engine In-Shop. (1) C-scan inspection is required on all LP compressor blades installed on an engine subject to a shop visit in accordance with EM Task 72-31-11-200-806. (2) Accomplishment of NMSB 72-G872 must be recorded against the individual blades and compliance logged with local FSO. F. Accomplishment Instructions for C-scan inspection of LP Compressor Blades, removed from an Engine On-Wing, undertaken in an Overhaul Facility where serviceability restoration is required. R R R (1) Clean the LP compressor blades: R (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). R R R R R (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: R R R
CAUTION : TO MAINTAIN THE CLEANLINESS OF THE WIPING SOLVENT, YOU MUST POUR THE SOLVENT ONTO THE WIPING CLOTH. THE CLOTH MUST NOT BE DIPPED INTO THE SOLVENT CONTAINER. R R R (i) Apply the solvent to the area to be cleaned using an OMat 2/101 lint free cloth moistened with either OMat 150 Acetone, OMat 1/40 Isopropyl alcohol. Discard the soiled cloth after use. R R R (ii) Repeat the swabbing using fresh cloth and solvent until the area is clean and free of DFL. R R**Printed in Great Britain**



# RB.211−72−G872 Page 12 Apr 3/12 Jul. 2/12 R(iii) Allow the parts to dry. Drying may be assisted by removing excess solvent using a clean dry lint-free cloth (Material No. OMat 2/101) or a clean oil-free air blast to help dry the part. R R R (iv) Remove masks from the LP compressor blade root. R (2) Visually inspect LP compressor blades. Refer to Fig.2, Fig.3 and Fig.4 for details. R R
NOTE : It is normal to see the panel lines on the airfoil surfaces near the tip of the LP compressor fan blades. This is not an indication of rippling caused by LP compressor fan blade damage. R R R (a) Examine the blade aerofoil for rippling: R (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. R R R (ii) If the blade has one or more ripples of any length with a form more than in step above - Reject the blade. R R (b) Examine the blade airfoil surfaces for cracks: R (i) If the blade is cracked - Reject the blade. R (c) Examine the blade tips and the airfoil surfaces for blueing or heat discoloration. R R (i) If there is blueing or heat discoloration on the blade tips and on the airfoil surfaces up to 0.26 in. (6.5 mm) from the blade tip - Accept the blade. R R R (d) If there is blueing or heat discoloration more than limit given above - Reject the blade. R R (e) Examine the blade surfaces for arc-burns. R (i) If the blade shows signs of arc-burns - Reject the blade. R (f) Examine the blades concave and convex airfoil surfaces for nicks. R (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. R R R (ii) If the blade has nicks in the airfoil surfaces above the annulus line more than the limit given above - Reject the blade. R R R**Printed in Great Britain**



# RB.211−72−G872 Page 13 Apr 3/12 Jul. 2/12 R(iii) If the blade has nicks in the airfoil surfaces below the annulus line - Reject the blade. R R (g) Examine the blade forward edge for nicks from 4.75 in. (120.65 mm) radially away from the annulus filler outer profile to the blade tip. R R (i) If the blade has nicks up to 0.025 in. (0.64 mm) in depth - Accept the blade. R R (ii) If the blade has nicks more than the limit given above - Reject the blade. R R (h) Examine the blade root and forward edge for nicks up to 4.75 in. (120.65 mm) radially away from the annulus filler outer profile. R R (i) If the blade has nicks up to 0.008 in. (0.2 mm) in depth - Accept the blade. R R (ii) If the blade has nicks more than the limit given above - Reject the blade. R R (i) Examine the blade forward and rear edges for bends: R (i) Blade bends - General. R (1) The maximum number of bent blades in the LPC rotor assembly must not be more than three. R R (2) If there are more than one bend in a blade - Reject the blade. R R (3) If a bend in a blade is not smooth or has kinks, creases, tears, cracks or nicks - Reject the blade. R R (4) If there is blade untwist - Reject the blade. R (ii) Accept bends with a circumferential deflection (X) not more than a maximum of 0.197 in. (5 mm) but only if: R R (1) The axial bend, dimension (Y) is more than eight times the circumferential bend, dimension (X). If the axial bend, dimension (Y) is less than eight times the circumferential bend, dimension (X) - Reject the blade. R R R R (2) The radial bend, dimension (Z) is more than 15 times the circumferential bend, dimension (X). If the radial bend, dimension (Z) is less than 15 times the circumferential bend, dimension (X) - Reject the blade. R R R R (3) The bend does not extend into the panel area. If the bend extends into the panel area - Reject the blade. R R**Printed in Great Britain**



# RB.211−72−G872 Page 14 Apr 3/12 Jul. 2/12 R(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: R R R (1) The axial bend, dimension (Y) is more than eight times the circumferential bend, dimension (X). If the axial bend, dimension (Y) is less than eight times the circumferential bend, dimension (X) - Reject the blade. R R R R (2) The radial bend, dimension (Z) is more than 15 times the circumferential bend, dimension (X). If the radial bend, dimension (Z) is less than 15 times the circumferential bend, dimension (X) - Reject the blade. R R R R (iv) If the bend is more than the limits given above - Reject the blade. R R (j) Examine the blade airfoil for wear from the annulus filler seal: R (i) If the blade has galling up to 0.005 in. (0.13 mm) deep on the convex side caused by the annulus filler seal - Accept the blade. R R R (ii) If the blade has galling more than the limit given above - Reject the blade. R R (3) Carry out C-scan inspection of LP compressor blades. R (a) Carry out C-scan inspection of LP compressor blades in accordance with EM Task 72-31-11-200-806. R R (b) If a blade is rejected by the C-scan inspection, inspection and blade data should be entered on the LP compressor blade rejection proforma (Appendix 1) and returned to Rolls-Royce with a copy of the archived scan data. R R R R (4) Dry LP compressor blades. R (a) Dry LP compressor blades in accordance with EM Task 70-00-00-100-102, Subtask 70-00-00-110-102-007. R R (5) Accomplishment of NMSB 72-G872 must be recorded against the individual blades and compliance logged with local FSO. R R**Printed in Great Britain**



# RB.211−72−G872 Page 15 Apr 3/12 Jul. 2/12 RR

Fig.1 R**Printed in Great Britain**



# RB.211−72−G872 Page 16 Apr 3/12 Jul. 2/12 RR

Acceptance Zone Dimensions R Fig.2 R**Printed in Great Britain**



# RB.211−72−G872 Page 17 Apr 3/12 Jul. 2/12 RR

LP Compressor Blades - Bends R Fig.3 R**Printed in Great Britain**



# RB.211−72−G872 Page 18 Apr 3/12 Jul. 2/12 RR

LP Compressor Blades - Inspection Areas R Fig.4 R**Printed in Great Britain**



# RB.211−72−G872 Page 19 Apr 3/12 Jul. 2/12 RLP Compressor Blade C-scan Rejection Proforma Results to be sent to Rolls-Royce via your Service Representative.
Blade Rejection Date:

Blade Part Number: Blade Serial Number:
Blade Time Since New (Hrs/Cycles):
Engine Number: Module Number:

Airline:

C-Scan Results:

1st Indication 2nd Indication 3rd Indication
Percentage of Height
Weighting

Blade Side (A/B)*

(*) A = Convex side B = Concave side APPENDIX 1**Printed in Great Britain**



# RB.211−72−G872 Appendix 1 - Page 1 of 1 Apr 3/12 Jul. 2/12 R