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

Bulletin 1 Sep.3/10 2 Sep.3/10 3 Sep.3/10 4 Sep.3/10 5 Sep.3/10 6 Sep.3/10 7 Sep.3/10 8 Sep.3/10 9 Sep.3/10 10 Sep.3/10 Appendix 1 1 Sep.3/10Printed in Great Britain



# RB.211−71−AG416 Transmittal - Page 21. Planning Information A. Effectivity Airbus A330 RB211 TRENT 768-60, TRENT 768-60/15, TRENT 768-60/16, TRENT 768-60/17 Propulsion Systems. RB211 TRENT 772-60, TRENT 772-60/15, TRENT 772-60/16, TRENT 772-60/17 Propulsion Systems. RB211 TRENT 772B-60, TRENT 772B-60/15, TRENT 772B-60/16, TRENT 772B-60/17 Propulsion Systems. RB211 TRENT 772C-60, TRENT 772C-60/15, TRENT 772C-60/16 Propulsion Systems.
B. Reason A number of Trent 700 air intake cowl, primary assembly structures (refer to Bombardier Aerospace-Shorts NMSB RB211-71-015, Figure 2), were found with cracks in the forward bulkhead web, web stiffeners, boundary angles and to a lesser extent on the Thermal Anti Ice (TAI) spray ring during shop visit. Analysis of the effects of cracking on these structures identified a need to inspect the primary assembly and to rectify the damage found. This Non-Modification Service Bulletin (NMSB) instructs an inspection of the forward bulkhead assembly, the TAI spray ring and its associated attachment links. The intent of this inspection is to identify and rectify damage. Operators are also requested to provide details of the findings to aid problem understanding. These findings will also help define the most effective way of managing the issue in-service. Permitted damage limits are provided to help operators with managing their fleet (refer to Fig.1 and Table 1). If any component is found to have damage more than these limits, it must be repaired before the air intake is returned to service. C. Description This NMSB instructs a borescope inspection of the forward bulkhead, TAI spray ring assembly and attachment brackets. Advise Bombardier Aerospace-Shorts and your local Rolls-Royce Field Service Office (FSO) of NMSB accomplishment and inspection results in accordance with Bombardier Aerospace-Shorts NMSB RB211-NAC-71-015. Refer to Appendix 1. POWERPLANT - AIR INTAKE COWL - INSPECTION OF THE FORWARD BULKHEAD, THERMAL ANTI ICE (TAI) SPRAY RING ASSEMBLY AND ATTACHMENT BRACKETS (BOMBARDIER AEROSPACE-SHORTS NON-MODIFICATION SERVICE BULLETIN RB211-NAC-71-015) NON-MODIFICATION SERVICE BULLETIN - NON - MOD.71-AG416Printed in Great Britain



# RB.211−71−AG416 Page 1 of 10 Sep. 3/10 Sep. 3/10D. Compliance
ALERT This NMSB is anticipated to be the subject of an EASA Airworthiness Directive. Rolls-Royce recommends that the procedures contained within Bombardier Aerospace-Shorts NMSB RB211-71-015 and 3. Accomplishment Instructions are done at the following opportunities given the age of the air intakes since new or life since replacement of the air intake primary assembly.
NOTE : A flow chart is provided (refer to Fig.1) to assist with the planning of the various inspection procedures.
NOTE : When the complete component life history is available, inspect the air intake cowl in accordance with Compliance (1.D.).
NOTE : When the history of an air intake is partial or unknown, prior to inspection of the air intake cowl in accordance with Compliance (1.D.), apply one of the following methods to estimate the accumulated life of the air intake cowl: (1) If it can be proven that an air intake cowl has been in continued use with one particular operator from its entry into service until the date the NMSB is accomplished the aircraft life from that operators fleet leader must be adopted. (2) If it cannot be proven that the air intake cowl has been in continued use with a particular operator from entry into service until the date the NMSB is accomplished, the Yearly Fleet Leader method is to be applied. Refer to Accomplishment Instructions (3.C.).
NOTE : It is imperative that operators continue to maintain an accurate record of the air intake cowl lives to avoid the need to repeat the Yearly Fleet Leader life calculations in the future. (1) For air intakes with a life less than 5000 cycles since new accomplish the initial inspection of the primary assembly in accordance with step D.(1)(a) or step D.(1)(b), whichever is greater. (a) When the air intake cowl has accumulated 5000 cycles since new (b) Within 24 months from the issue of this NMSB (2) For air intakes with a life greater than 5000 cycles since new accomplish the initial inspection of the primary assembly within 24 months from issue of this NMSB.Printed in Great Britain



# RB.211−71−AG416 Page 2 Sep. 3/10 Sep. 3/10(3) If it can be shown that the previous repair of the air intake introduced a new complete primary assembly (including TAI spray ring and installation), then the initial inspection can be delayed and performed after 5000 cycles of service has accumulated since the repair was accomplished. (4) If no damage is found after the initial inspection, do repeat inspections of the air intake primary assembly as follows: (a) TAI spray ring and attachment links every 2500 cycles. (b) Inner and outer boundary angles and bulkhead every 5000 cycles. (5) If damage is found repeat inspections in accordance with the limits and intervals provided in Fig.1 and Table 1. (6) If multiple engines on a given aircraft are found to have broken TAI spray ring attachment links, depair engines as instructed in Fig.1. Depair - replace one air intake cowl with a serviceable unit to reduce the risk of having two air intake cowls with broken TAI spray ring attachment links (more than permitted limit) on one aircraft. E. Approval The technical content of this Non-Modification Service Bulletin was approved under the authority of Design Organisation Approval EASA.21J.031 on Aug.26/10. F. Manpower Refer to Bombardier Aerospace-Shorts NMSB RB211-NAC-71-015. G. Material Price and Availability Refer to Bombardier Aerospace-Shorts NMSB RB211-NAC-71-015. H. Tooling Price and Availability Refer to Bombardier Aerospace-Shorts NMSB RB211-NAC-71-015. I. References (1) Engine Manual, 71-61-00, Removal and Installation. (2) Airbus A330 Aircraft Maintenance Manual, 71-61-41, Maintenance Practices (3) Bombardier Aerospace-Shorts NMSB RB211-NAC-71-015 (4) Airbus aircraft Service Bulletin A330-71-3025Printed in Great Britain



# RB.211−71−AG416 Page 3 Sep. 3/10 Sep. 3/102. Material Information Refer to Bombardier Aerospace-Shorts NMSB RB211-NAC-71-015.Printed in Great Britain



# RB.211−71−AG416 Page 4 Sep. 3/10 Sep. 3/103. Accomplishment Instructions A. The procedure contained in Bombardier Aerospace-Shorts NMSB RB211-NAC-71-015, 3.Accomplishment Instructions has been developed to allow inspection to be completed with the air intake cowl installed on-wing. It is permitted for the inspection to be accomplished with the air intake cowl removed.

CAUTION : IN ORDER TO REDUCE THE POTENTIAL FOR MULTIPLE-ENGINE IN-FLIGHT SHUTDOWN, 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 MAKE SURE THAT MAINTENANCE TASKS HAVE BEEN COMPLETED AS DEFINED. MAINTENANCE GUIDELINES SHOULD BE REVISED, WHERE POSSIBLE, TO PROMOTE THIS RECOMMENDATION. (1) If necessary remove air intake cowl in accordance with current overhaul or maintenance procedures (Engine Manual, 71-61-00, Removal and Installation or Aircraft Maintenance Manual, 71-61-41, Maintenance Practices). (2) Inspect the air intake cowl in accordance with Bombardier Aerospace -Shorts NMSB RB211-NAC-71-015 and 3.Accomplishment Instructions. (3) If applicable, fit the air intake cowl, or a replacement, to the engine in accordance with current overhaul or maintenance procedures (Engine Manual, 71-61-00, Removal and Installation or Aircraft Maintenance Manual, 71-61-41, Maintenance Practices). B. Permitted damage limits and repeat inspection intervals

Outer Boundary Angle (OBA) Forward Bulkhead Length of Crack(s) Found millimeters (inches) - Largest Crack on Unit Repeat Inspection Interval (Cycles) Step (1) Length of Crack(s) Found millimeters (inches) - Largest Crack on Unit Repeat Inspection Interval (Cycles) Step (1) None 5000 None 5000 25,4 (1.00) 5000 25,4 (1.00) 3225 50,8 (2.00) 5000 50,8 (2.00) 2825 76,2 (3.00) 5000 76,2 (3.00) 2425 101,6 (4.00) 5000 101,6 (4.00) 2025 127,0 (5.00) 4600 127,0 (5.00) 1600 152,4 (6.00) 4125 152,4 (6.00) 1200 177,8 (7.00) 3650 177,8 (7.00) 800 203,2 (8.00) 3200 203,2 (8.00) 400 228,6 (9.00) 2750 228,6 (9.00) Reject See Step (3)Printed in Great Britain



# RB.211−71−AG416 Page 5 Sep. 3/10 Sep. 3/10Outer Boundary Angle (OBA) Forward Bulkhead Length of Crack(s) Found millimeters (inches) - Largest Crack on Unit Repeat Inspection Interval (Cycles) Step (1) Length of Crack(s) Found millimeters (inches) - Largest Crack on Unit Repeat Inspection Interval (Cycles) Step (1) 254,0 (10.00) 2300 279,4 (11.00) 1825 304,8 (12.00) 1375 330,2 (13.00) 900 355,6 (14.00) 450 381,0 (15.00) Reject See Step (2) Table 1 (1) Get the Repeat inspection interval from the longest crack found on a unit. There is no limit to the number of cracks but there must be a minimum distance between the cracks (centre to centre) of 3 times the length of the longest crack. Reject units found to have cracking more than this limit. (2) Crack in OBA: (a) Between 381,0 mm and 558.8 mm (15.00 in. and 22.00 in.) long, remove the intake cowl before 100 flight cycles. (b) Greater than 558,8 mm (22.00 in.) long, remove intake cowl before next flight. (3) Crack in forward bulkhead: (a) Between 228,6 mm and 330,2 mm (9.00 in. and 13.00 in. ) long, remove intake cowl before 100 flight cycles. (b) Greater than 330,2 mm (13.00 in.) long, remove intake cowl before next flight. C. Trent 700 air intake cowl - life calculation - Yearly Fleet Leader method (1) When the complete component life history is available, inspect the air intake cowl in accordance with Compliance (1.D.).Printed in Great Britain



# RB.211−71−AG416 Page 6 Sep. 3/10 Sep. 3/10(2) To estimate the accumulated life of the air intake cowl when the history is partial or unknown, apply the following methodology.
NOTE : This methodology is based on the Yearly Fleet Leader and allows the calculation of conservative values to cover periods during which the accumulation of flight cycles is unknown. It can be applied to calculate the life from new or to cover only certain periods of the component history. (a) For periods where no history is available the Yearly Fleet Leader accumulated flight cycles for the Airbus A330 (Trent 700 engine) aircraft must be considered. The actual fleet leader lives from 1995 to 2009 have been provided in Table 2. (b) Yearly fleet leader lives from Jan.01/10 onwards can be obtained from Airbus. (c) Calculations must include the accumulated Airbus A330 (Trent 700 engine) aircraft flight cycles from the date of the air intake cowls initial entry into service until the date when this NMSB is accomplished. (d) If an operator does not have a record of the entry into service date of the air intake cowl (it is not included on the air intake cowl plate or aircraft log book) operators must contact Bombardier Aerospace-Shorts to get the date of manufacture for each serialised unit. (e) If the initial entry into service date cannot be established then the conservative start date of Apr.01/95 must be used. (f) Each year of service must be divided into twelve equal periods (one per month), except for the year 1995, which must be divided into nine equal periods. (g) The start date and end date of each period during which the history of life accumulation is unknown must be rounded up to consider complete months only. (3) Calculation example An operator needs to calculate the life of an air intake cowl from Apr.17/02 (air intake cowl first flight). The operator wants to know the parts life on Nov.30/09. For periods where no history is available the Yearly Fleet Leader accumulated Flight Cycles (FC) must be considered Refer to Table 2.Printed in Great Britain



# RB.211−71−AG416 Page 7 Sep. 3/10 Sep. 3/10(4) The calculation parameters are: (a) Date of first flight - Apr.17/02. Actual, recorded , life accumulated between Apr.17/02 to Jun.16/03 = +723FC No history is available for the following period Jun.16/03 to Dec.11/06. Actual, recorded, life accumulated between Dec.11/06 to Nov.30/09 = +2100FC (5) Calculation of life history (a) Actual, recorded, life accumulated between Apr.17/02 to Jun.16/03 = +723 FC (b) Conservative life (calculated using Yearly Fleet Leader data) for the period from Jun.16/03 to Dec.11/06: To cover period from Jun.16/03 to Dec.31/03: +7x(1404/12)= +819 FC To cover year 2004 = +1557 FC To cover year 2005 = +1558 FC To cover year 2006 = +1655 FC Total = +5589 FC
NOTE : This period of conservative life is rounded up to complete months. Actual, recorded, life accumulated between Dec.11/06 and Nov.30/09 = +2100 FC Total Life = +723 FC + 5589 FC + 2100 FC = 8412 FC As a result on Nov.30/09, the subject component has a life of 8412 FC.
NOTE : This calculation will remain valid as long as the operator maintains traceability for this component until the end of the parts life. If the operator loses an additional part of the component history, a new calculation will need to be performed with updated parameters. It is imperative that the operators continue to maintain an accurate record of the air intake cowl lives to avoid the need to repeat the Yearly Fleet Leader calculations in the future.Printed in Great Britain



# RB.211−71−AG416 Page 8 Sep. 3/10 Sep. 3/10Year Yearly Fleet Leader Life (FC) 1994 333 1995 938 1996 1178 1997 1270 1998 1327 1999 1269 2000 1415 2001 1413 2002 1465 2003 1404 2004 1557 2005 1558 2006 1665 2007 1733 2008 1619 2009 1674 Trent 700 A330 Yearly Fleet Leader Lives 1995 to 2009 Table 2 D. Accomplishment of this NMSB should be recorded in the engine logbook or in accordance with the local SB tracking system procedures.Printed in Great Britain



# RB.211−71−AG416 Page 9 Sep. 3/10 Sep. 3/10Inspection Process Flow Chart Fig.1Printed in Great Britain



# RB.211−71−AG416 Page 10 Sep. 3/10 Sep. 3/10Non-Modification Service Bulletin 71-AG416

1. Record accomplishment of this Non-Modification Service Bulletin in accordance with local Service Bulletin tracking system procedures. 2. Advise Bombardier Aerospace-Shorts and your local Rolls-Royce FSO of NMSB accomplishment and inspection results regardless of findings. Refer to Bombardier Aerospace-Shorts NMSB RB211-NAC-71-015. APPENDIX 1Printed in Great Britain



# RB.211−71−AG416 Appendix 1 - Page 1 of 1 Sep. 3/10 Sep. 3/10