This document transmits the Initial Issue of Service Bulletin RB211-72-G702 Bulletin Initial Issue Remove Incorporate Reason for change Pages 1 to 11 of the Service Bulletin Initial issue Pages 1 to 17 of Appendix 1 Initial issue Page 1 of Appendix 2 Initial issuePrinted in Great Britain May.23/11

RB211 TRENT 700 SERIES PROPULSION SYSTEMS NON-MODIFICATION SERVICE BULLETIN



# RB.211−72−G702 Transmittal - Page 1 of 2 Signed DateLIST OF EFFECTIVE PAGES The effective pages to this Service Bulletin are as follows: Page Revision Number Revision Date

Bulletin 1 May 23/11 2 May 23/11 3 May 23/11 4 May 23/11 5 May 23/11 6 May 23/11 7 May 23/11 8 May 23/11 9 May 23/11 10 May 23/11 11 May 23/11 Appendix 1 1 May 23/11 2 May 23/11 3 May 23/11 4 May 23/11 5 May 23/11 6 May 23/11 7 May 23/11 8 May 23/11 9 May 23/11 10 May 23/11 11 May 23/11 12 May 23/11 13 May 23/11 14 May 23/11 15 May 23/11 16 May 23/11 17 May 23/11 Appendix 2 1 May 23/11Printed in Great Britain



# RB.211−72−G702 Transmittal - Page 21. Planning Information A. Effectivity Airbus A330 RB211 TRENT768-60, TRENT768-60/15, TRENT768-60/16, TRENT772-60, TRENT772-60/15, TRENT772-60/16, TRENT772B-60, TRENT772B-60/15, TRENT772B-60/16, TRENT772B-60/16, TRENT772C-60/16 Engines which have an LP compressor blade(s) with a Serial No. given in Appendix 1.
B. Reason Following LP Compressor (LPC) blade events in service, an inspection technique, Single Head C-scan, has been adapted for Trent 700 LPC blades. This inspection is already in place for RB211 and V2500 LPC blades. The C-scan inspection is capable of detecting sub-surface anomalies in the LPC blade aerofoil. This Non-Modification Service Bulletin (NMSB) has been issued to understand the condition of a sample of operator blades in advance of the introduction of regular C-scan inspections at every shop visit instructed in the Engine Manual. This NMSB will be applicable only to the LPC blades listed in APPENDIX 1. These blades are part of a high life fleet and are the most suitable for sampling. Operators affected by this NMSB have been individually informed. From the 10th June 2011 Single Head C-scan inspection will be included in the Engine Manual. C. Description This NMSB instructs the Single Head C-scan inspection of LP Compressor blades listed in APPENDIX 1. Accomplishment of this NMSB must be recorded in the engine/module log book. Inform your assigned Rolls-Royce Service Representative of NMSB accomplishment. D. Compliance Recommended Rolls-Royce recommends a one time only inspection of the LPC blades listed in APPENDIX 1 by the 31st December 2011. ENGINE - LP COMPRESSOR - INSPECTION OF LP COMPRESSOR BLADES - NON-MODIFICATION SERVICE BULLETIN - NON - MOD.72-G702Printed in Great Britain



# RB.211−72−G702 Page 1 of 11 May.23/11 May.23/11The inspection requirements are defined in accordance with 3.A Accomplishment Instructions for engines on-wing and 3.B. and 3.C. Accomplishment Instructions for engines in the shop. Rolls-Royce recommends that the following action is undertaken to maintain reliability. E. Approval The technical content of this Non-Modification Service Bulletin was approved under the authority of Design Organisation Approval EASA.21J.035 on May.23/11. F. Manpower (1) In Service (a) Time to remove LPC blades 2 persons - 6 hours per LPC blade set. (b) Time to inspect LPC blades in the shop 1 person - 52 hours per LPC blade set. (c) Time to install LPC blades 2 persons - 6 hours per LPC blade set.
NOTE : A vibration ground run will be required. (2) Shop visit (Overhaul) (a) Time to inspect LPC blades in the shop 1 person - 30 hours per LPC blade set. G. Material Price and Availability Please contact your local Rolls-Royce field service office for availability. H. Tooling Price and Availability Tooling for LPC blade inspection: RR1024167 - Ultrasonic immersion system - 1 off. QC6808 - Calibration blade - 1 off.Printed in Great Britain



# RB.211−72−G702 Page 2 May.23/11 May.23/11I. References (1) Aircraft Maintenance Manual (AMM) Task 72-31-41, Removal/Installation of the Low Pressure (LP) Compressor Blades and Dampers. Task 72-31-51, Local repair of the Dry Film Lubricant on the Low Pressure (LP) Compressor Fan Disc (FRSA017). Task 72-00-00, Test No.11 The Engine Vibration Survey. (2) Engine Manual (EM) Task 72-31-11, Removal and Installation the Low Pressure (LP) Compressor Blades and Dampers. Task 72-31-11, Clean the Low Pressure (LP) Compressor Blades. Task 70-00-00, Overhaul Process 102, Primary Cleaning - Aqueous (TSD594J). Task 72-31-11, General data for the Inspection/Check of the Low Pressure (LP) Compressor Blades and Fillers (Inspection/Check 00). Task SPM 70-42-11, Dress Group A Components to only remove indication of damage (Depth x1) (FRS6625). Task 72-31-11, Low Pressure (LP) Compressor Fan Blade - Repair Damage by Dressing, Scalloping and/or Cropping (FRSA024). Task 72-31-11, Low Pressure (LP) Compressor Rotor Blade Assembly - Dress Aerofoil Surface Damage (FRSA025). Task 72-31-11, Low Pressure (LP) Compressor Rotor Blade Assembly - Restore the Aerofoil Surface Finish (FRSA026). Task 72-00-00, Low Pressure (LP) Compressor Fan Blades - Re-apply the Dry Film Lubricant (DFL) (FRSA202). Task 72-00-00, Low Pressure (LP) Compressor Fan Disc - Re-apply the Dry Film Lubricant (DFL) (FRSA203). (3) Technical Variance (TV) TV112799, Introduction of C-scan Crack Detection Technique.Printed in Great Britain



# RB.211−72−G702 Page 3 May.23/11 May.23/112. Material Information
A. None.Printed in Great Britain



# RB.211−72−G702 Page 4 May.23/11 May.23/113. Accomplishment Instructions A. On-wing (1) Remove LP Compressor blades
CAUTION : IN ORDER TO REDUCE THE POTENTIAL FOR MULTIPLE ENGINE IN-FLIGHT SHUT DOWN, POWER LOSS, OR OTHER ANOMALY 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, WERE POSSIBLE, TO PROMOTE THIS RECOMMENDATION. (a) Remove the applicable LP Compressor blades in accordance with Aircraft Maintenance Manual, 72-31-41, Removal/Installation. (2) Send the removed LP Compressor blades to the overhaul shop. (3) Clean the LP Compressor Blades. (a) Clean the LPC blades in accordance with Engine Manual, 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 a presence of Dry Film Lubricant (DFL) in the LPC blade aerofoil, mask the LPC blade root and clean in accordance with Engine Manual, Task 72-31-11-100-801, Subtask 72-31-11-110-008-002, Dry plastic blast, OP TASK 70-00-00-100-104, Subtask 70-00-00-120-104-005. (4) Visual Inspection of LP Compressor Blades (a) The following procedure needs to be carried out in the overhaul shop: (b) Refer to Engine Manual, Task 72-31-11-200-801, Fig. 72-31-11-990-003 and Fig. 72-31-11-990-264. (c) Aerofoil Surface at location 1 (convex) and 2 (concave) above annulus filler line. (i) Nicked or Scored in Area A. (1) Up to 0,20mm (0.008in.) in depth - Accept.Printed in Great Britain



# RB.211−72−G702 Page 5 May.23/11 May.23/11(2) More than in (1) but not more than 0,38mm (0.015in.) - Repair, FRS6625 SPM Task 70-42-11-300-004-001 and Repair, FRSA026 Task 72-31-11-300-007. (3) More than in (2) - Reject. (ii) Nicked or Scored in Area B. (1) Up to 0,20mm (0.008in.) in depth - Accept. (2) More than in (1) but not more than 0,38mm (0.015in.) - Repair, FRSA025 Task 72-31-11-300-037 and Repair, FRSA026 Task 72-31-11-300-007. (3) More than in (2) - Reject. (iii) Rippling.
NOTE : It is possible to see the panel line on the aerofoil surface, especially near the blade tip. This is normal and must not be confused with ripples caused by blade damage. (1) Up to 0,16mm (0.0063in.) in height (minor ripples are within manufacturing specification) - Accept. (2) One or more ripple(s) with a form more than in (1) and of any length - Reject. (d) Aerofoil surface at location 1 (convex) and 2 (concave) along the line of the annulus filler or below annulus filler line. (i) Worn, as a result of annulus filler sealing strip rub - Accept. (ii) Surface protection missing as a result of annulus filler sealing strip rub - Accept. (iii) Galled, along the line of the annulus filler. (1) Up to 0,10mm (0.004in.) in depth - Accept. (2) More than in (1) - Reject. (iv) Nicks or scored (1) Up to 0,08mm (0.003in.) in depth - Accept. (2) More than in (1) but not more than 0,38mm (0.015in.) - Repair, FRSA025 Task 72-31-11-300-037 and Repair, FRSA026 Task 72-31-11-300-007. (3) More than in (2) - Reject.Printed in Great Britain



# RB.211−72−G702 Page 6 May.23/11 May.23/11(e) Blade leading edge from 191,65mm (7.545in.) radially away from the blade root base to the tip. (i) Nicked or scored. (1) Up to 0,64mm (0.025in.) in depth - Accept. (2) More than (1) - Repair, FRSA024 Task 72-31-11-300-012. (f) Blade leading edge up to 191,65mm (7.545in.) radially away from the blade root base. (i) Nicked or Scored - Repair, FRSA024 Task 72-31-11-300-012. (g) Blade or leading edge and trailing edges. (i) Blade bends - General
NOTE : The maximum number of bent blades in the Low Pressure Compressor (LPC) rotor assembly must not be more than three. (1) If there is more than one bend in a blade - Do the following Task 72-31-11-200-800 Inspection/Check. (2) If a bend in a blade is not smooth or has kinks, creases, tears, cracks or nicks - Do the following Task 72-31-11-200-800 Inspection/Check. (ii) Blade bends - Dimensions Bends with a circumferential deflection, dimension (X), not more than a maximum of 5,00mm (0.197in.) Refer to Fig.1 - Accept, but only if in the limits in the steps below: (1) The axial bend, dimension (Y) is more than eight times the circumferential bend, dimension (X). (2) The radial bend, dimension (Z) is more than 15 times the circumferential bend, dimension (X). (3) The bend does not extend into the panel area. (4) More than in the steps (1), (2) or (3) above - Do the following Task 72-31-11-200-800 Inspection/Check.Printed in Great Britain



# RB.211−72−G702 Page 7 May.23/11 May.23/11(h) Blade root (limit for OMat 328 metal spray anti-fretttage coating condition for engines with SB72-C974 or SB72-D379 blades).
NOTE : SB72-C974 or SB72-D739 blades can be identified by a blue triangle chemically etched to the suction surface of the blade, adjacent to the leading edge tip. The metal spray anti-frettage coating is situated on the bedding flanks of the fan blade root, See Fig. 72-00-00-991-370 in Engine Manual, Task 72-00-00-280-850-A01 (SP50). The coating is gold in colour and is only exposed in areas where loss, wear or damage of dry film lubricant has occurred. (i) Chipped. (1) Up to a maximum of 5 isolated chips in the edge of the coating. If the chips are not more than 1,50mm (0.060in.) in length and are not less than 25,00mm (1.000in.) from the shear key slot - Accept. (2) More than in (1) - Do the following Task 72-31-11-200-800 Inspection/Check. (ii) Loss of coating. (1) Up to 5 per cent of total surface area, if not less than 25,00mm (1.000in.) from the shear key slot - Accept. (2) In the radius of the shear key slot, if not extended onto the work flank - Accept. (3) More than in (1) or (2) - Do the following Task 72-31-11-200-800 Inspection/Check. (i) Blade shear keys and retaining straps. (i) Damaged, loose or torn - Do the following Task 72-31-11-200-800 Inspection/Check. (5) Carry out C-scan Inspection of the LPC blades (a) The following procedure needs to be carried out in the shop (b) Carry out C-scan inspection of the LPC blades in accordance with TV112799. (c) If the blade is rejected by the C-scan inspection, inspection and blade data should be entered on the LPC blade rejection proforma (Appendix 2) and returned to Rolls-Royce.Printed in Great Britain



# RB.211−72−G702 Page 8 May.23/11 May.23/11(6) Dry the LP Compressor blades (a) Dry the LPC blades in accordance with Engine Manual, Task 70-00-00-100-102, Subtask 70-00-00-110-102-007. (7) Re apply the Dry Film Lubricant (rapid relube) (a) Re-apply the Dry Film Lubricant in accordance with Engine Manual, Task 72-00-00-300-010 (Repair FRSA202). (8) Return the Low Pressure (LP) Compressor blades to the operator for installation. (9) Repair the Low Pressure (LP) Compressor disc slots dry film lubricant in accordance with Aircraft Maintenance Manual, Task 72-31-51, (Repair FRSA017). (10) Install the Low Pressure (LP) Compressor blades in accordance with Aircraft Maintenance Manual, Task 72-31-41, Removal/Installation. (11) Restore the engine to a serviceable condition in accordance with Aircraft Maintenance Manual, Task 72-31-41, Removal/Installation. (12) Carry out a vibration survey in accordance with Aircraft Maintenance Manual, Task 71-00-00, Test No.11 The Engine Vibration Survey. (13) Accomplishment of NMSB 72-G702 must be recorded in the engine logbook. B. At Overhaul - Check and Repair, Level 2. (1) Remove the Low Pressure (LP) Compressor blades in accordance with Engine Manual, Task 72-31-11-000-801. (2) Clean the Low Pressure (LP) Compressor Blades. (a) Clean the LPC blades in accordance with Engine Manual, 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 a presence of Dry Film Lubricant (DFL) in the LPC blade aerofoil, mask the LPC blade root and clean in accordance with Engine Manual, Task 72-31-11-100-801, Subtask 72-31-11-110-008-002, Dry plastic blast, OP Task 70-00-00-100-104, Subtask 70-00-00-120-104-005. (3) Inspect the LP Compressor blades in accordance with Engine Manual, Task 72-00-00-280-850-A01 (SP50).Printed in Great Britain



# RB.211−72−G702 Page 9 May.23/11 May.23/11(4) Carry out C-scan Inspection of the LP Compressor Blades (a) Carry out a C-scan inspection of the LPC blades in accordance with TV112799. (b) If the blade is rejected by the C-scan inspection, inspection and blade data should be entered on the LPC blade rejection proforma (Appendix 2) and returned to Rolls-Royce. (5) Dry the LP Compressor blades. (a) Dry the LPC blades in accordance with Engine Manual, Task 70-00-00-100-102, Subtask 70-00-00-110-102-007. (6) Re-apply the Dry Film Lubricant to the LPC blade roots in accordance with Engine Manual, Task 72-00-00-300-010 (Repair FRSA202). (7) Re-apply the Dry Film Lubricant to the LPC disc slots in accordance with Engine Manual, Task 72-00-00-300-011 (Repair FRSA203). (8) Install the LPC blades in accordance with Engine Manual Task, 72-31-11-420-801. (9) Accomplishment of NMSB 72-G702 must be recorded in the engine logbook. C. At Overhaul (Engine refurbishment or Overhaul, Level 3 or 4). (1) In addition to standard overhaul procedures in accordance with Engine Manual, Task 72-31-11, carry out a C-scan inspection on the LP Compressor blades in accordance with TV112799. (a) If the blade is rejected by the C-scan inspection, inspection and blade data should be entered on the LPC blade rejection proforma (Appendix 2) and returned to Rolls-Royce. (2) Accomplishment of NMSB 72-G702 must be recorded in the engine logbook.Printed in Great Britain



# RB.211−72−G702 Page 10 May.23/11 May.23/11Forward or Rear Edge Bend Fig.1Printed in Great Britain



# RB.211−72−G702 Page 11 May.23/11 May.23/11Blade Serial Numbers APPENDIX 1Printed in Great Britain



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# RB.211−72−G702 Appendix 1 - Page 17 May.23/11 May.23/11LP Compressor C-scan Rejection Proforma
Blade Rejection Date:

Blade Part No: Blade Serial No:

Blade Time Since New (HRS/CYCLES):

Engine No: Module No:

Airline:

C-Scan Results: 1st Indication 2nd Indication 3rd Indication % Height

Weighting

Blade Side (A/B)*

(*) A=convex side B=concave side APPENDIX 2Printed in Great Britain



# RB.211−72−G702 Appendix 2 - Page 1 of 1 May.23/11 May.23/11