All pages of Appendix 3 Pages 1 to 5 of Appendix 3 To Revise the contents in Appendix 4 based upon additional data provided by Operators. All pages of Appendix 4 Pages 1 to 29 of Appendix 4 To Revise the contents in Appendix 4 based upon additional data provided by Operators. All pages of Appendix 5 Pages 1 to 5 of Appendix 5 To Revise the contents in Appendix 4 based upon additional data provided by Operators. All pages of Appendix 6 Pages 1 to 13 of Appendix 6 To Revise the contents in Appendix 4 based upon additional data provided by Operators.**Printed in Great Britain**



# RB.211−72−AH972 Transmittal - Page 2LIST OF EFFECTIVE PAGES The effective pages to this Service Bulletin following incorporation of Revision 3 are as follows: Page Revision Number Revision Date

Bulletin R 1 3 Aug.28/15 R 2 3 Aug.28/15 R 3 3 Aug.28/15 R 4 3 Aug.28/15 R 5 3 Aug.28/15 R 6 3 Aug.28/15 R 7 3 Aug.28/15 R 8 3 Aug.28/15 R 9 3 Aug.28/15 R 10 3 Aug.28/15 R 11 3 Aug.28/15 Appendix 1 R 1 3 Aug.28/15 R 2 3 Aug.28/15 Appendix 2 R 1 3 Aug.28/15 R 2 3 Aug.28/15 R 3 3 Aug.28/15 R 4 3 Aug.28/15 R 5 3 Aug.28/15 R 6 3 Aug.28/15 R 7 3 Aug.28/15 R 8 3 Aug.28/15 Appendix 3 R 1 3 Aug.28/15 R 2 3 Aug.28/15 R 3 3 Aug.28/15 R 4 3 Aug.28/15 R 5 3 Aug.28/15 Appendix 4 R 1 3 Aug.28/15 R 2 3 Aug.28/15 R 3 3 Aug.28/15 R 4 3 Aug.28/15 R 5 3 Aug.28/15 R 6 3 Aug.28/15 R 7 3 Aug.28/15 R 8 3 Aug.28/15 R 9 3 Aug.28/15 R 10 3 Aug.28/15**Printed in Great Britain**



# RB.211−72−AH972 Transmittal - Page 3R 11 3 Aug.28/15 R 12 3 Aug.28/15 R 13 3 Aug.28/15 R 14 3 Aug.28/15 R 15 3 Aug.28/15 R 16 3 Aug.28/15 R 17 3 Aug.28/15 R 18 3 Aug.28/15 R 19 3 Aug.28/15 R 20 3 Aug.28/15 R 21 3 Aug.28/15 R 22 3 Aug.28/15 R 23 3 Aug.28/15 R 24 3 Aug.28/15 R 25 3 Aug.28/15 R 26 3 Aug.28/15 R 27 3 Aug.28/15 R 28 3 Aug.28/15 R 29 3 Aug.28/15 Appendix 5 R 1 3 Aug.28/15 R 2 3 Aug.28/15 R 3 3 Aug.28/15 R 4 3 Aug.28/15 R 5 3 Aug.28/15 Appendix 6 R 1 3 Aug.28/15 R 2 3 Aug.28/15 R 3 3 Aug.28/15 R 4 3 Aug.28/15 R 5 3 Aug.28/15 R 6 3 Aug.28/15 R 7 3 Aug.28/15 R 8 3 Aug.28/15 R 9 3 Aug.28/15 R 10 3 Aug.28/15 R 11 3 Aug.28/15 R 12 3 Aug.28/15 R 13 3 Aug.28/15**Printed in Great Britain**



# RB.211−72−AH972 Transmittal - Page 41. Planning Information A. Effectivity Boeing 757 (1) RB211-535E4-37, 535E4-37/10, 535E4-37/11, 535E4-37/12, 535E4-37/14, 535E4-37/16, 535E4-37/17, 535E4-37/19, 535E4-37/20, 535E4-37/23, 535E4-37/24, 535E4-37/25, 535E4-37/39, 535E4-37/43, 535E4-37/44 Engines (2) RB211-535E4-B-37, 535E4-B-37/15, 535E4-B-37/19, 535E4-B-37/20, 535E4-B-37/21, 535E4-B-37/25, 535E4-B-37/35, 535E4-B-37/39, 535E4-B-37/41, 535E4-B-37/44 Engines (3) RB211-535E4-C-37, 535E4-C-37/43 Engines B. Reason Problem Due to operation of some RB211-535E4 engines in excess of the currently published flight profiles (Flight Profile 'A' and 'B') shaft speed limits during take-off and climb, a new flight profile (Flight Profile 'G') with associated Provisional Group A part lives has been developed for the 535E4 engine which encompasses the higher shaft speeds. For a summary of all flight profiles on the RB211-535E4 series of engine, including the new flight profile (Flight Profile 'G') introduced by this NMSB, refer to the table in Appendix 1. The new flight profile will be published in the Aircraft Maintenance Manual (AMM). Once instructed in the AMM, affected operators of the E4 engine should declare operation to this new flight profile (refer to Appendix 1). The Time Limits Manual (TLM) will also be updated to include approved Group A Part Declared Safe Cyclic Life (DSCL) limits for the new flight profile. Analysis of RB211-535E4 engines which have operated in excess of the currently published flight profiles (Flight Profile 'A' and 'B') shaft speeds during take-off and climb has identified that ownership of some of these engines and/or components installed in these engines have been transferred to other operators or leasing companies. In order to manage the risk of Group A parts exceeding their Declared Safe Cyclic Life (DSCL), this NMSB has been introduced to artificially age affected Group A parts and manage the removal of these parts from service. The TLM will be updated by 31st March 2018 The AMM will be updated by 31st March 2018 CHANGES TO TIME LIMITS MANUAL AND AIRCRAFT MAINTENANCE MANUAL RESULTING FROM CHANGES TO THE RB211-535E4 FLIGHT PROFILE - NON-MODIFICATION SERVICE BULLETIN - NON - MOD.72-AH972**Printed in Great Britain**



# RB.211−72−AH972 Page 1 of 11 May 22/15 Aug.28/15 RFailure to comply with this Non-Modification Service Bulletin (NMSB) will introduce a risk of exceeding the Group A life limits and thus premature component failure. This NMSB is related to Worldwide Communication WW/11196/1/01 May 15. Revision 1 to this NMSB 72-AH972 was issued to remove UL39765 and UL39766 from Appendix 2 and to correct Part Numbers UL12375 to UL12379 and UL12529 to FW12375 to FW12379 and FW12529 respectively in Appendix 3. Revision 2 to this NMSB 72-AH972 was issued to: (1) Appendix 2 - Correct the maximum approved lives: LP Turbine Shaft from 16,200 to 16,270. LP Turbine Disc Stage 2, subject to Mandatory NMSB 72-D181 from 14,400 to 13,300. LP Turbine Disc Stage 2 reworked in accordance with SB 72-D365 from 22,700 to 20,900. (2) Appendix 3 - Revise the list of LP Compressor (Fan) Blades: Remove the LP Compressor (Fan) Blade part number FW12378. Include the following LP Compressor (Fan) Blade part numbers, UL21345, UL22286, UL23122, UL24528, UL24530, UL24532, UL24534, UL27992, UL28601, UL28602 and UL29511. (3) Appendix 4 - Update Part S/N (where previously stated 'Contact RR') with either a Compliance Time or an Additional Life Consumed if Operating in FP 'A'. (4) To include minor typographical changes that do not affect the technical content of this NMSB. Revision 3 to this NMSB has been issued to update the contents in Appendix 4 based upon additional data provided by Operators. R R C. Description This NMSB introduces a new flight profile Flight Profile 'G' and their associated Provisional Group A and Group B part lives for the RB211-535E4 engine. This NMSB provides the instructions to artificially age Group A parts which have operated in excess of the currently published flight profiles (Flight Profile 'A' and 'B') shaft speeds during take-off and climb and remove from service Group A parts which will exceed their DSCL within the effective period covered by this NMSB.**Printed in Great Britain**



# RB.211−72−AH972 Page 2 May 22/15 Aug.28/15 RD. Compliance (1) ALERT Rolls-Royce recommends that within six weeks of the initial issue date of this NMSB, the following actions should be undertaken on Group A parts for planning purposes only, after this, NMSB 72-AH972 goes live. The provisional lives defined in NMSB 72-AH972 must be used in conjunction with the TLM until the TLM is updated with component lives for the new flight profile, Flight Profile 'G' on 31st March 2018. (a) Refer to Appendix 4 to establish if you have Group A part(s) with Part Serial Number(s) listed. NOTE : The Part Serial Numbers are listed against the last known Engine Serial Number (ESN) they were fitted to. This may not be the ESN they are currently fitted to. (b) If you do have Group A part(s) with Part Serial Number(s) listed in Appendix 4, then the accomplishment instructions in section 3 of this NMSB should be followed. This Non-Modification Service Bulletin, and in particular the life limits given in Appendix 2, is anticipated to be the subject of EASA and FAA Airworthiness Directives (AD). (c) Refer to Appendix 6 to establish if any engine sub-fleet is currently operating above the RB211-535E4 Flight Profile 'B' but within Flight Profile 'G' limits. (d) If any engine sub-fleet is currently operating above the RB211-535E4 Flight Profile 'B' but within Flight Profile 'G' limits, then follow the instructions in 3. Accomplishment Instructions. (e) If any engine sub-fleet is currently operating above the RB211-535E4 Flight Profile 'G' then you must contact Rolls-Royce. (f) If neither (b), (d) or (e) apply, then no further action is required. (2) RECOMMENDED Rolls-Royce recommends that within six weeks of the initial issue date of this NMSB, the following actions should be undertaken on Group B parts for planning purposes only, after this, NMSB 72-AH972 goes live. The provisional lives defined in NMSB 72-AH972 must be used in conjunction with the TLM until the TLM is updated with component lives for the new flight profile, Flight Profile 'G' on 31st March 2018. (a) Refer to Appendix 6 to establish if any engine sub-fleet is currently operating above the RB211-535E4 Flight Profile 'B' but within Flight Profile 'G' limits.**Printed in Great Britain**



# RB.211−72−AH972 Page 3 May 22/15 Aug.28/15 R(b) If any engine sub-fleet is currently operating above the RB211-535E4 Flight Profile 'B' but within Flight Profile 'G' limits, then follow the instructions in 3. Accomplishment Instructions. (c) If any engine sub-fleet is currently operating above the RB211-535E4 Flight Profile 'G' then you must contact Rolls-Royce. (d) If neither (b) or (c) apply, then no further action is required. 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.21/15, Jun. 5/15, Jul.20/15 and again on Aug.27/15. R F. Manpower Not applicable G. Material Price and Availability Not applicable H. Tooling Price and Availability Special tools are not required I. References (1) Rolls-Royce RB211 Service Bulletins: (a) 72-8717 Engine - LP Compressor - Wide Chord Fan Blade (WCFB) Annulus Filler to Air Seal with Improved Bonding Features (b) 72-9434 Engine - HP Compressor - Stage 3 Rotor Disc Corrosion Removal and Re-Protection using Sermetals (c) 72-9700 Engine - LP Compressor - Introduction of revised Annulus Fillers (d) 72-B106 Engine - LP Compressor Blades and Dampers - Introduction of Trimmed Annulus Filler Seals**Printed in Great Britain**



# RB.211−72−AH972 Page 4 May 22/15 Aug.28/15 R(e) 72-C901 Engine - LP Compressor Blades and Dampers, LP Compressor Annulus Fillers - Introduction of Thickened Top Flange (f) 72-D365 Engine - LP Turbine Stage 2 Disc - Introduction of Rework to Maintain Cyclic Life (g) 72-G017 Engine - LP Compressor Blades - Introduction of Revised Fan Blade Annulus Filler Assemblies with Reduced Weight (2) Rolls-Royce RB211 Non-Modification Service Bulletins: (a) 72-9661 Engine - HP Compressor - Stage 3 Disc revised Lives for Rework (b) 72-D181 Engine - LP Turbine Rotor - Stage 2 Turbine Disc Reduced Cyclic Life - Engine Management and On-wing Inspection - Non-Modification Service Bulletin (c) 72-E087 Engine - LP Compressor Blade Annulus Filler Inspections - Cancellation of Non-Modification Service Bulletin (d) 72-AG875 Engine - Changes to the Time Limits Manual and Aircraft Maintenance Manual Resulting from changes to the RB211-535E4-B Flight Profile (e) 72-AH029 Engine - Low Pressure (LP) Turbine Stage 2 Disc - Life Reduction - Non-Modification Service Bulletin (3) Aircraft Maintenance Manual (AMM), 70-01-10 (4) Time Limits Manual (TLM), 05-00-01, 05-10-01, 05-10-02**Printed in Great Britain**



# RB.211−72−AH972 Page 5 May 22/15 Aug.28/15 R2. Material Information None**Printed in Great Britain**



# RB.211−72−AH972 Page 6 May 22/15 Aug.28/15 R3. Accomplishment Instructions A. The procedures and life limits detailed in Appendices 1, 2 and 3 are to be utilised by the affected Operators prior to their incorporation into the AMM and TLM on the date detailed in Section 1.D. Compliance. For planning purposes, calculate the Total Life Consumed for each Part Serial Number listed in the table in Appendix 4. Record the Total Life Consumed using local operating procedures. CAUTION: IF THE FLIGHT PROFILE OF ANY OF YOUR FLEETS OR SUB-FLEETS HAVE CHANGED BETWEEN OCTOBER 2014 AND THE PUBLICATION DATE OF THIS NMSB, INFORM ROLLS-ROYCE AS THE LIFE DEBT FOR THE AFFECTED PARTS LISTED IN APPENDIX 4 WILL NEED TO BE RE-CALCULATED. NOTE: Each Part Serial Number in the table in Appendix 4 is listed against the last known Engine Serial Number (ESN) it was fitted to. This may not be the ESN they are currently fitted to. NOTE: For guidance on how to calculate the Total Life Consumed refer to Appendix 5. NOTE: The table in Appendix 4 provides a recommended format for recording the Total Life Consumed. (1) On-wing Post release of this NMSB, operators with Group 'A' Part Serial Numbers listed in the table in Appendix 4 and fitted to an engine 'on-wing', should follow the instructions in Fig.1. NOTE: Flight Cycle (FC) limit is from the initial issue date of this NMSB. NOTE: Appendix 5, Examples 1 to 4 illustrate calculations for components with serial numbers listed in Appendix 4. For RB211-535E4 aircraft with engines installed which have operated in excess of the currently published flight profile (Flight Profile 'A' and 'B') shaft speeds during take-off and climb, the provisional lives defined in Appendix 2 of this NMSB must be used in conjunction with the TLM until the TLM is updated with component lives for the new flight profile 'Flight Profile 'G' by the 31st of March 2018. NOTE: Appendix 5, Example 5 illustrates a calculation for a component with a serial number not listed in Appendix 4, but which are subject to updated lives for the new profile Flight Profile 'G'.**Printed in Great Britain**



# RB.211−72−AH972 Page 7 May 22/15 Aug.28/15 RAfter release of this NMSB, should 'on-wing' engines be removed for a shop visit, then refer to 3.A.(2). NOTE: A shop visit refers to refurbishment where discs are de-bladed and where shafts are reduced to shaft assembly piece part level or separation of a major flange with the exception of the gearbox. (2) In-shop Group 'A' Serial Numbers listed in the table in Appendix 4 should follow the instructions defined in Fig.2. Appendix 5, Examples 1 to 4 illustrate calculations for components with serial numbers listed in Appendix 4. NOTE: In-shop refers to refurbishment where discs are de-bladed and where shafts are reduced to shaft assembly piece part level or separation of a major flange with exception of the gearbox and/or discs and shafts which are currently held as either Service Usable Material (SUM) or Held Out Of Service (HOOS). NOTE: If it has been established that there has been movement from one flight profile to a different flight profile during the history of the engine/component (e.g. Flight Profile 'A' to Flight Profile 'B') then a pro-rata life calculation will be necessary to establish the equivalent CSN in the engine/components current flight profile. Guidance on when these calculations might be necessary and how to complete these calculations is described in steps (3) and (4) below and the Time Limits Manual 05-00-01 with further guidance and examples contained in Appendix 5. NOTE: For LP turbine stage 2 discs that have previously embodied the mid-life rework defined in SB 72-D365, it is necessary to review the life history and retrospectively apply the provisional re-work threshold life. As defined in SB 72-D365, if the disc life at re-work is found to be above the provisional re-work threshold then the accrued life post re-work is unchanged. If the disc life at re-work is found to be below the provisional re-work threshold then the disc should be artificially aged in accordance with the provisional re-work threshold and the accrued life should be re-calculated. Further guidance is given in AMM and also in NMSB 72-AH029. (3) If an RB211-535E4 engine fleet or sub-fleet is currently operating in excess of the currently published profiles (Flight Profile 'A' and 'B') i.e. in profile Flight Profile 'G' then the remaining life of the Group 'A' components in the new profile should be calculated using the provisional part lives in Appendix 2. It may be necessary to perform a pro-rata life calculation if the component has historically operated in more than one flight profile.**Printed in Great Britain**



# RB.211−72−AH972 Page 8 May 22/15 Aug.28/15 R(4) All guidance surrounding shaft speed data capture and flight profile monitoring, as given in the AMM 70-01-10, still apply. B. In Shop:

If an RB211-535E4 engine fleet or sub-fleet is currently operating in excess of the currently published profiles (Flight Profile 'A' and 'B') i.e. in profile Flight Profile 'G' then the remaining Group 'B' part lives should be calculated when the engine comes in for a shop visit using the provisional part lives in Appendix 3. It may be necessary to perform a pro-rata life calculation if the component has historically operated in more than one flight profile. Appendix 5, Example 5 illustrates a calculation for a Group 'B' component operating in the new profile Flight Profile 'G'.**Printed in Great Britain**



# RB.211−72−AH972 Page 9 May 22/15 Aug.28/15 RLogic for On-wing Accomplishment Instructions Fig.1**Printed in Great Britain**



# RB.211−72−AH972 Page 10 May 22/15 Aug.28/15 RLogic for In-shop Accomplishment Instructions Fig.2**Printed in Great Britain**



# RB.211−72−AH972 Page 11 May 22/15 Aug.28/15 RRecording and Control of the Lives of Parts: Time Limits Manual 05-00-01-800-000 The following section of TLM Task 05-00-01-800-000 in the Time Limits Manual, will be updated to include reference to the new E4 flight profiles. All other sections of TLM Task 05-00-01-800-000 remain unchanged and should be followed as normal. 1. Intermixing of Group A and Group B Parts between Flight Profiles A. Where the engine configuration allows, Group A and Group B parts may be moved between any combination of 535E4-37 Flight Profile 'A', 535E4-37 Flight Profile 'B', 535E4-37 Flight Profile 'G', 535E4-B-37 Flight Profile 'C', 535E4-B-37 Flight Profile 'D', 535E4-B-37 Flight Profile 'E' and 535E4-C-37 Flight Profile 'F' operation. B. The published Declared Life of Group A and Group B parts may be different from one flight profile to another. The Time Limits Manual contains seven sets of Declared Cyclic lives applicable to Group 'A' (05-10-01) and Group 'B' (05-10-02) parts: Engine Flight profile Reference New Flight profile Reference Aircraft Type

535E4 E4 Flight Profile 'A' Flight Profile 'A' 757-200
E4 Flight Profile 'B' Flight Profile 'B' 757-200

N/A Flight Profile 'G' 757-200

535E4-B E4-B Flight Profile Flight Profile 'C' 757-200 and 757-300
E4-B 757-200 Heavy Flight Profile 'D' Typically 757-200

E4-B 757-300 Heavy Flight Profile 'E' Typically 757-300 APPENDIX 1**Printed in Great Britain**



# RB.211−72−AH972 Appendix 1 - Page 1 of 2 May 22/15 Aug.28/15 R535E4-C E4-C Flight Profile Flight Profile 'F' 757-200 and 757-300
NOTE : The flight profiles given in the above sequence from Flight Profile 'A' to Flight Profile 'G' are not in any particular hierarchy or order in relation to shaft speed limits or nature of operation. The aircraft type associated with each flight profile has been included for guidance purposes only and is reflective of the fleet at the date of issue of this NMSB. New operators of the 535E4 engine rating should assume Flight Profile 'G' by default until a full 12 months worth of shaft speed data shows compliance to Flight Profile 'A' or Flight Profile 'B'. C. The flight profiles applicable to 535E4-37 Flight profiles 'A', 'B' and 'G', the 535E4-B-37 Flight Profile 'C', 535E4-B-37 Flight Profile 'D', 535E4-B-37 Flight Profile 'E' and the 535E4-C-37 Flight Profile 'F' will be published in the Aircraft Maintenance Manual, 70-01-10.**Printed in Great Britain**



# RB.211−72−AH972 Appendix 1 - Page 2 May 22/15 Aug.28/15 RGroup A Parts Lives for E4 Flight Profile 'G': Time Limits Manual 05-10-01-800-000 1. Maximum Approved Lives of LP Compressor Rotor Disc
IPC FIG/ITEM PART NO. FLIGHT PROFILE 'G' PROVISIONAL LIVES (FLIGHT CYCLES) 72-31-12, 01-210 UL16174 22,600 72-31-12, 01-210 UL16194 22,600 72-31-12, 01-210 UL21343 22,600 72-31-12, 01-210 UL24536 22,600 2. Maximum Approved Lives of LP Compressor Shaft
IPC FIG/ITEM PART NO. FLIGHT PROFILE 'G' PROVISIONAL LIVES (FLIGHT CYCLES) 72-31-20, 01-100 UL16140 (Assy) 14,230 72-31-20, 01-100 UL16217 (Assy) 14,230 72-31-20, 01-100 UL24100 (Assy) 14,230 72-31-20, 01-100 UL16211 (Assy) 14,230 72-31-20, 01-100 UL27910 (Assy) 14,230 72-31-20, 01-100 UL28351 (Assy) 14,230 72-31-20, 01-150 UL16141 (Assy) 14,230 APPENDIX 2**Printed in Great Britain**



# RB.211−72−AH972 Appendix 2 - Page 1 of 8 May 22/15 Aug.28/15 R72-31-20, 01-150 UL16218 (Assy) 14,230 72-31-20, 01-150 UL24101 (Assy) 14,230 72-31-20, 01-150 UL16212 (Assy) 14,230 72-31-20, 01-150 UL27911 (Assy) 14,230 72-31-20, 01-170 UL16142 14,230 72-31-20, 01-170 UL16219 14,230 72-31-20, 01-170 UL24102 14,230 3. Maximum Approved Lives of LP Turbine Shaft
IPC FIG/ITEM PART NO. FLIGHT PROFILE 'G' PROVISIONAL LIVES (FLIGHT CYCLES) 72-51-63, 01-200 UL17734 (Assy) 16,270 72-51-63, 01-200 UL19434 (Assy) 16,270 72-51-63, 01-200 UL20331 (Assy) 16,270 72-51-63, 01-200 UL37584 (Assy) 16,270 72-51-63, 01-200 UL37761 (Assy) 16,270 72-51-63, 01-200 FW30429 (Assy) 16,270 72-51-63, 01-200 FW30430 (Assy) 16,270**Printed in Great Britain**



# RB.211−72−AH972 Appendix 2 - Page 2 May 22/15 Aug.28/15 R72-51-63, 01-200 FW30431 (Assy) 16,270 72-51-63, 01-200 FW30432 (Assy) 16,270 72-51-63, 01-200 FW30433 (Assy) 16,270 72-51-63, 01-200 FW30434 (Assy) 16,270 72-51-63, 01-214 UL14859 16,270 72-51-63, 01-214 UL19435 16,270 72-51-63, 01-214 UL20332 16,270 72-51-63, 01-214 UL37585 16,270 72-51-63, 01-214 UL37762 16,270 4. Maximum Approved Lives of LP Turbine Disc Stage 1
IPC FIG/ITEM PART NO. FLIGHT PROFILE 'G' PROVISIONAL LIVES (FLIGHT CYCLES) 72-51-61, 01-300 UL10175 27,650 72-51-61, 01-300 UL17724 27,650 72-51-61, 01-300 UL18946 27,650 72-51-61, 01-300 UL29028 27,650 72-51-61, 01-300 UL37342 27,650**Printed in Great Britain**



# RB.211−72−AH972 Appendix 2 - Page 3 May 22/15 Aug.28/15 R72-51-61, 01-300 UL38584 27,650 5. Maximum Approved Lives of LP Turbine Disc Stage 2 A. The life of the following components can be extended by rework and artificial ageing as defined in and by the incorporation of SB 72-D365. NOTE : Until the TLM is updated the pre-rework provisional life will act as the threshold life. It is permissible to rework a disc that had a greater cyclic life than the threshold for Flight Profile 'G' in accordance with SB 72-D365. SB 72-D365 instructs that where a part with a cyclic life greater than its threshold has been reworked, the part retains its existing life. B. The following lives are subject to mandatory NMSB 72-D181.
IPC FIG/ITEM PART NO. FLIGHT PROFILE 'G' PROVISIONAL LIVES

(FLIGHT CYCLES) 72-51-61, 01-350 UL11508 13,300 72-51-61, 01-350 UL17141 13,300 72-51-61, 01-350 UL18947 13,300 72-51-61, 01-350 UL29029 13,300 72-51-61, 01-350 UL37352 13,300 C. The life (Flight Cycles) of the following parts have been reworked in accordance with SB 72-D365.
IPC FIG/ITEM PART NO. FLIGHT PROFILE 'G' PROVISIONAL LIVES

(FLIGHT CYCLES) 72-51-61, 01-350 FW16685 20,900**Printed in Great Britain**



# RB.211−72−AH972 Appendix 2 - Page 4 May 22/15 Aug.28/15 R72-51-61, 01-350 FW16686 20,900 72-51-61, 01-350 FW16687 20,900 72-51-61, 01-350 FW16688 20,900 72-51-61, 01-350 FW16689 20,900 6. Maximum Approved Lives of LP Turbine Disc Stage 3.
IPC FIG/ITEM PART NO. FLIGHT PROFILE 'G' PROVISIONAL LIVES (FLIGHT CYCLES) 72-51-61, 01-470 UL11578 25,630 72-51-61, 01-470 UL18954 25,630 72-51-61, 01-470 UL29031 25,630 72-51-61, 01-470 UL37349 25,630 7. Maximum Approved Lives of IP Compressor Rotor Shaft (Stage 1 to 6).
IPC FIG/ITEM PART NO. FLIGHT PROFILE 'G' PROVISIONAL LIVES (FLIGHT CYCLES) 72-32-31, 01-080 UL16758 22,700 72-32-31, 01-080 UL30176 22,700**Printed in Great Britain**



# RB.211−72−AH972 Appendix 2 - Page 5 May 22/15 Aug.28/15 R8. Maximum Approved Lives of IP Compressor Rotor Rear Stub Shaft.
IPC FIG/ITEM PART NO. FLIGHT PROFILE 'G' PROVISIONAL LIVES (FLIGHT CYCLES) 72-33-21, 01-260 UL14081 26,500 72-33-21, 01-260 UL18796 26,500 72-33-21, 01-260 UL20016 26,500 9. Maximum Approved Lives of IP Turbine Shaft.
IPC FIG/ITEM PART NO. FLIGHT PROFILE 'G' PROVISIONAL LIVES (FLIGHT CYCLES) 72-51-33, 01-185 UL14860 26,500 72-51-33, 01-185 UL19437 26,500 72-51-33, 01-185 UL20005 26,500 72-51-33, 01-185 UL37571 26,500 72-51-33, 01-185 UL37760 26,500 10. Maximum Approved Lives of IP Turbine Disc.
IPC FIG/ITEM PART NO. FLIGHT PROFILE 'G' PROVISIONAL LIVES (FLIGHT CYCLES) 72-51-31, 01-150 UL17774 26,500**Printed in Great Britain**



# RB.211−72−AH972 Appendix 2 - Page 6 May 22/15 Aug.28/15 R72-51-31, 01-150 UL19818 26,500 72-51-31, 01-150 UL27940 26,500 11. Maximum Approved Lives of HP Compressor Rotor Disc Stage 1 and 2.
IPC FIG/ITEM PART NO. FLIGHT PROFILE 'G' PROVISIONAL LIVES (FLIGHT CYCLES) 72-41-31, 01-170 UL11678 12,600 72-41-31, 01-170 UL24024 12,600 12. Maximum Approved Lives of HP Compressor Rotor Disc Stage 3. A. The life (Flight Cycles) of the following components may be extended by incorporation of SB 72-9434 and reference to NMSB 72-9661.
IPC FIG/ITEM PART NO. FLIGHT PROFILE 'G' PROVISIONAL LIVES

(FLIGHT CYCLES) 72-41-31, 01-240 UL11706 15,000 72-41-31, 01-240 UL15358 15,000 72-41-31, 01-240 UL24738 15,000 72-41-31, 01-240 UL22578 15,000 B. The life (Flight Cycles) of the following part numbers are as listed in table below:
IPC FIG/ITEM PART NO. FLIGHT PROFILE 'G' PROVISIONAL LIVES

(FLIGHT CYCLES)**Printed in Great Britain**



# RB.211−72−AH972 Appendix 2 - Page 7 May 22/15 Aug.28/15 R72-41-31, 01-240 UL29347 25,100 72-41-31, 01-240 UL29349 25,100 13. Maximum Approved Lives of HP Compressor Rear Rotor Shaft Assembly.
IPC FIG/ITEM PART NO. FLIGHT PROFILE 'G' PROVISIONAL LIVES (FLIGHT CYCLES) 72-41-31, 01-370 UL16994 15,000 72-41-31, 01-370 UL18095 15,000 72-41-31, 01-370 UL18096 15,000 72-41-31, 01-370 UL18114 15,000 72-41-31, 01-370 UL26989 15,000 14. Maximum Approved Lives of HP Turbine Disc.
IPC FIG/ITEM PART NO. FLIGHT PROFILE 'G' PROVISIONAL LIVES (FLIGHT CYCLES) 72-41-51, 01-350 UL10323 11,400 72-41-51, 01-350 UL27680 14,000 72-41-51, 01-350 UL27681 14,000 72-41-51, 01-350 UL39767 14,000**Printed in Great Britain**



# RB.211−72−AH972 Appendix 2 - Page 8 May 22/15 Aug.28/15 RGroup B Parts Lives for E4 Flight Profile 'G'. Time Limits Manual 05-10-02-800-001 Not all Group B part lives are affected for the new Flight profile - Flight Profile 'G' when compared to Flight Profile 'B'. For completeness the lives for rotating parts only have been given below. Static parts are not affected. 1. Maximum Approved Lives of LP Compressor (Fan) Blades
IPC FIG/ITEM PART NO. FLIGHT PROFILE 'G' PROVISIONAL LIVES (FLIGHT CYCLES) 72-31-11, 01-280 FW12308 17,600 72-31-11, 01-280 FW12309 17,600 72-31-11, 01-280 FW12366 17,600 72-31-11, 01-280 FW12367 17,600 72-31-11, 01-280 FW12368 17,600 72-31-11, 01-280 FW12369 17,600 72-31-11, 01-280 FW12371 17,600 72-31-11, 01-280 FW12372 17,600 72-31-11, 01-280 FW12373 17,600 72-31-11, 01-280 FW12374 17,600 72-31-11, 01-280 FW12375 17,600 72-31-11, 01-280 FW12376 17,600 APPENDIX 3**Printed in Great Britain**



# RB.211−72−AH972 Appendix 3 - Page 1 of 5 May 22/15 Aug.28/15 R72-31-11, 01-280 FW12377 17,600 72-31-11, 01-280 FW12379 17,600 72-31-11, 01-280 FW12529 17,600 72-31-11, 01-280 UL16135 17,600 72-31-11, 01-280 UL16171 17,600 72-31-11, 01-280 UL16182 17,600 72-31-11, 01-280 UL19643 17,600 72-31-11, 01-280 UL20044 17,600 72-31-11, 01-280 UL20132 17,600 72-31-11, 01-280 UL20616 17,600 72-31-11, 01-280 UL21345 17,600 72-31-11, 01-280 UL22286 17,600 72-31-11, 01-280 UL23122 17,600 72-31-11, 01-280 UL24525 17,600 72-31-11, 01-280 UL24528 17,600 72-31-11, 01-280 UL24530 17,600 72-31-11, 01-280 UL24532 17,600**Printed in Great Britain**



# RB.211−72−AH972 Appendix 3 - Page 2 May 22/15 Aug.28/15 R72-31-11, 01-280 UL24534 17,600 72-31-11, 01-280 UL27992 17,600 72-31-11, 01-280 UL28601 17,600 72-31-11, 01-280 UL28602 17,600 72-31-11, 01-280 UL29511 17,600 72-31-11, 01-280 UL29556 17,600 72-31-11, 01-280 UL30817 17,600 72-31-11, 01-280 UL30819 17,600 72-31-11, 01-280 UL30933 17,600 72-31-11, 01-280 UL30935 17,600 72-31-11, 01-280 UL33707 17,600 72-31-11, 01-280 UL33709 17,600 72-31-11, 01-280 UL37090 17,600 72-31-11, 01-280 UL38029 17,600 72-31-11, 01-280 UL38032 17,600 72-31-11, 01-280 UL38373 17,600 72-31-11, 01-280 UL38375 17,600**Printed in Great Britain**



# RB.211−72−AH972 Appendix 3 - Page 3 May 22/15 Aug.28/15 R72-31-11, 01-280 UL38377 17,600 72-31-11, 01-280 UL38379 17,600 The declared life for the following blade serial numbers is limited to 10,000 cycles: GB51119, GB51554, GB53544, GB80870, GB81315, GB83871, GB87679, GB87705, GB87805, GB88227, GB88894, GB89740, RGH13261, RGH27905 2. Maximum Approved Lives of LP Compressor Annulus Filler A. The life (Flight Cycles) of the following part numbers are as listed. B. SB 72-E087 introduces new lives which are detailed in the table below:
IPC FIG/ITEM PART NO. FLIGHT PROFILE 'G' PROVISIONAL LIVES

(FLIGHT CYCLES) 72-31-11, 01-350 UL16208 12,000 The following part number has been introduced by the incorporation of SB 72-8717:
IPC FIG/ITEM PART NO. FLIGHT PROFILE 'G' PROVISIONAL LIVES

(FLIGHT CYCLES) 72-31-11, 01-350 UL16160 12,000 The following part number has been introduced by the incorporation of SB 72-9700:
IPC FIG/ITEM PART NO. FLIGHT PROFILE 'G' PROVISIONAL LIVES

(FLIGHT CYCLES) 72-31-11, 01-350 UL35848 8,000**Printed in Great Britain**



# RB.211−72−AH972 Appendix 3 - Page 4 May 22/15 Aug.28/15 RThe following part number have been introduced by the incorporation of SB 72-B106:
IPC FIG/ITEM PART NO. FLIGHT PROFILE 'G' PROVISIONAL LIVES

(FLIGHT CYCLES) 72-31-11, 01-350 UL38852 12,000 72-31-11, 01-350 UL38855 8,000 The following part number have been introduced by the incorporation of SB 72-C901:
IPC FIG/ITEM PART NO. FLIGHT PROFILE 'G' PROVISIONAL LIVES

(FLIGHT CYCLES) 72-31-11, 01-350 UL39738 3,500 The following part number have been introduced by the incorporation of SB 72-G017:
IPC FIG/ITEM PART NO. FLIGHT PROFILE 'G' PROVISIONAL LIVES

(FLIGHT CYCLES) 72-31-11, 01-350 FW61408 10,000**Printed in Great Britain**



# RB.211−72−AH972 Appendix 3 - Page 5 May 22/15 Aug.28/15 RList of Affected Group 'A' Part Serial Numbers Glossary: 1. Last Known ESN: The last known ESN the Group 'A' part was fitted to - if the Group 'A' part is not fitted to the corresponding ESN listed in the table the operator must still carry out the accomplishment instructions. 2. Part Name: Description of Group 'A' Part 3. Part Number: Affected Group 'A' Part Number 4. Part Serial Number: Affected Group 'A' Part Serial Number 5. Compliance Time (FC or Calendar date, whichever occurs first): The Flight Cycle (FC) limit (from initial issue date of this NMSB) and removal date (whichever occurs first) by which an engine should come in for a shop visit. The compliance time has been agreed with the airworthiness authorities for continued safe operation of the engine.

CAUTION: IF THE FLIGHT PROFILE OF ANY OF YOUR FLEETS OR SUB-FLEETS HAVE CHANGED BETWEEN OCTOBER 2014 AND THE PUBLICATION DATE OF THIS NMSB, INFORM ROLLS-ROYCE AS THE LIFE DEBT FOR THE AFFECTED PARTS LISTED IN APPENDIX 4 WILL NEED TO BE RE-CALCULATED. NOTE : Where it states 'NONE' the operator should calculate the Total Life Consumed for each Part Serial Number and plan a shop visit before the DSCL is exceeded. NOTE: Where it states 'No Residual Life' the Operator has confirmed the part as being scrapped. 6. Additional Life Consumed if Operating FP 'A': The number of additional flight cycles, calculated by Rolls-Royce, which should be added to the CSN of the Part Serial Number as a result of historical operation in excess of Flight Profile 'B'.

NOTE : This assumes current operation is within Flight Profile (FP) 'A' through to Mar.31/15. Refer to Appendix 5 for guidance on calculating the number of additional cycles if current operation is in another Flight Profile e.g. Flight Profile 'B'. Where it states 'Remove within Compliance Time' the engine should come in for a shop visit within the Compliance Time (FC OR Calender Date, whichever occurs first) stated. NOTE: Flight Cycle (FC) limit is from the initial issue date of this NMSB. 7. Total Life Consumed: This column is provided for operators to record the calculation of Total Life Consumed. Refer to Appendix 5 for guidance on calculating this value. APPENDIX 4**Printed in Great Britain**



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# RB.211−72−AH972 Appendix 4 - Page 7 May 22/15 Aug.28/15 Rdeh0014785 PART NAME PART SERIAL NUMBER PART NUMBER
30629 DISK, LPT STAGE 2 SETM22360 NONE 303 UL29029
30629 SHAFT, COMPRESSOR ROTOR REAR HP MW0246408 NONE 365 UL18114
30629 DISK, HP TURBINE LDRCZ16898 NONE 465 UL39767
30629 DISK, COMPRESSOR, HP 1ST & 2ND STAGE MW0246733 NONE 510 UL11678
30630 DISK, HP TURBINE LDRCZ12259 NONE 2175 UL27681
30640 DISK, COMPRESSOR, HP 1ST & 2ND STAGE MW0011407 NONE 1853 UL11678
30640 DISK, HP TURBINE LDRCZ12887 NONE 2117 UL27681
30643 SHAFT, COMPRESSOR FRONT IP DN35520 NONE 2107 UL16758
30643 DISK, HP TURBINE LDRCZ12036 904 FC, OR BY UL27681
30660 DISK, HP TURBINE LDRCZ16622 NONE 2297 UL39767
30670 DISK, LPT STAGE 2 SEBH5141 904 FC, OR BY FW16686
30676 SHAFT, COMPRESSOR ROTOR REAR HP DN60412 REMOVE WITHIN UL18114
30687 SHAFT, COMPRESSOR FRONT IP DN40586 NONE 601 UL16758
30694 SHAFT, COMPRESSOR ROTOR REAR HP DN65734 NONE 956 UL18114
30712 SHAFT, COMPRESSOR ROTOR REAR HP RRDCDDMW NONE 676 UL18114
30712 DISK, HP TURBINE LDRCZ19337 NONE 860 UL39767
30712 DISK, LPT STAGE 2 SETM24314 NONE 897 UL29029
30712 DISK, COMPRESSOR, HP 1ST & 2ND STAGE MW0441132 NONE 944 UL11678
30712 SHAFT, COMPRESSOR FRONT IP MW0148568 NONE 1383 UL30176
30713 SHAFT, COMPRESSOR FRONT IP MW0233720 NONE 1124 UL30176
30713 DISK, LPT STAGE 2 SETM22154 NONE 1918 UL29029
30713 SHAFT, COMPRESSOR ROTOR REAR HP MW0235188 NONE 2316 UL18114
30713 DISK, HP TURBINE LDRCZ16792 NONE 2947 UL39767 COMPLIANCE TIME (FC OR CALENDAR DATE, WHICHEVER

OCCURS FIRST) TOTAL LIFE CONSUMED

FLIGHT CYCLES (FC) LAST KNOWN

ESN ADDITIONAL LIFE CONSUMED IF OPERATING IN FP ’A’ FLIGHT CYCLES (FC)

30/06/2016 REMOVE WITHIN COMPLIANCE TIME

30/06/2016 REMOVE WITHIN COMPLIANCE TIME 371 FC, OR BY

31/10/2015 COMPLIANCE TIME

0451517 R**Printed in Great Britain**



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# RB.211−72−AH972 Appendix 4 - Page 25 May 22/15 Aug.28/15 Rdeh0014786 PART NAME PART SERIAL NUMBER PART NUMBER UNKNOWN DISK, COMPRESSOR, HP 1ST & 2ND STAGE DN36555 NONE UL11678 UNKNOWN DISK, COMPRESSOR, HP 1ST & 2ND STAGE DN60981 UL11678 UNKNOWN DISK, HP TURBINE LDRCZ10176 UL27681 UNKNOWN DISK, LPT STAGE 2 SETM05754 FW16687
30906 SHAFT, COMPRESSOR FRONT IP DN59361 NONE UL30176 UNKNOWN SHAFT, COMPRESSOR ROTOR REAR HP DN61028 UL18114
31677 SHAFT, COMPRESSOR ROTOR REAR HP MW0016950 NONE UL18114 UNKNOWN DISK, HP TURBINE CQDY6502 UL27680 SPARE DISK, COMPRESSOR, HP 1ST & 2ND STAGE DN62390 UL11678
UNKNOWN SHAFT, COMPRESSOR ROTOR REAR HP DN36917 UL18114 SPARE DISK, HP TURBINE LDRCZ11442 NONE UL27681 UNKNOWN DISK, LPT STAGE 2 SEBH5100 UL11508
31105 DISK, COMPRESSOR, HP 1ST & 2ND STAGE MW0096376 NONE UL11678
30517 DISK, LPT STAGE 2 SETM13563 UL29029
31081 SHAFT, COMPRESSOR ROTOR REAR HP MW0078829 NONE UL18114 UNKNOWN DISK, COMPRESSOR, HP 1ST & 2ND STAGE MW0003373 NONE UL11678 UNKNOWN DISK, LPT STAGE 2 SEBH5135 UL37352 UNKNOWN SHAFT, COMPRESSOR FRONT IP DN35301 NONE UL16758 UNKNOWN DISK, COMPRESSOR, HP 1ST & 2ND STAGE DN61976 UL11678 UNKNOWN DISK, HP TURBINE LDRCZ10975 UL39767
31282 DISK, COMPRESSOR, HP 1ST & 2ND STAGE DN61972 NONE UL11678 DISK, LPT STAGE 2 SETM15229 NONE UL29029 COMPLIANCE TIME (FC OR CALENDAR DATE, WHICHEVER

OCCURS FIRST) TOTAL LIFE CONSUMED

FLIGHT CYCLES (FC) LAST KNOWN

ESN ADDITIONAL LIFE CONSUMED IF OPERATING IN FP ’A’ FLIGHT CYCLES (FC)

NONE

NONE

UNKNOWN 7522

2857

1700

0 (ZERO)

1951

1570
1762

3002

1132
1463 0 (ZERO)

1325 100 FC, OR BY

31/08/2015 REMOVE WITHIN COMPLIANCE TIME

REMOVE WITHIN COMPLIANCE TIME

REMOVE WITHIN COMPLIANCE TIME

REMOVE WITHIN COMPLIANCE TIME

REMOVE WITHIN COMPLIANCE TIME

REMOVE WITHIN COMPLIANCE TIME

REMOVE WITHIN COMPLIANCE TIME

REMOVE WITHIN COMPLIANCE TIME

REMOVE WITHIN COMPLIANCE TIME

REMOVE WITHIN COMPLIANCE TIME 100 FC, OR BY

31/08/2015 100 FC, OR BY

31/08/2015

100 FC, OR BY

31/08/2015

100 FC, OR BY

31/08/2015

100 FC, OR BY

31/08/2015

100 FC, OR BY

31/08/2015

100 FC, OR BY

31/08/2015

100 FC, OR BY

31/08/2015 100 FC, OR BY

31/08/2015 R**Printed in Great Britain**



# RB.211−72−AH972 Appendix 4 - Page 26 May 22/15 Aug.28/15 Rdeh0014787 PART NAME PART SERIAL NUMBER PART NUMBER UNKNOWN DISK, COMPRESSOR, HP 1ST & 2ND STAGE DN41401 UL11678 UNKNOWN DISK, LPT STAGE 2 SETM1710 NONE UL29029 UNKNOWN DISK, LPT STAGE 2 SEBH5124 UL37352 UNKNOWN DISK, COMPRESSOR, HP 1ST & 2ND STAGE DN42706 UL11678 UNKNOWN SHAFT, COMPRESSOR FRONT IP DN42484 UL16758 UNKNOWN DISK, COMPRESSOR, HP 1ST & 2ND STAGE DN42712 UL11678 UNKNOWN DISK, LPT STAGE 2 SETM2345 UL18947 UNKNOWN DISK, HP TURBINE LDRCZ10086 UL27681 UNKNOWN SHAFT, COMPRESSOR ROTOR REAR HP DN58832 UL18114
UNKNOWN DISK, LPT STAGE 2 SETM05760 NONE FW16687 UNKNOWN SHAFT, COMPRESSOR FRONT IP DN59386 UL30176 UNKNOWN DISK, COMPRESSOR, HP 1ST & 2ND STAGE DN66953 UL11678 UNKNOWN DISK, HP TURBINE LDRCZ10606 UL27681
30631 SHAFT, COMPRESSOR ROTOR REAR HP DN61134 UL18114 UNKNOWN DISK, LPT STAGE 2 SETM07546 FW16687 UNKNOWN DISK, COMPRESSOR, HP 1ST & 2ND STAGE DN60848 UL11678 UNKNOWN DISK, COMPRESSOR, HP 1ST & 2ND STAGE DN61859 UL11678 UNKNOWN DISK, LPT STAGE 2 SETM06288 FW16687 UNKNOWN SHAFT, COMPRESSOR ROTOR REAR HP DN61818 UL18114 UNKNOWN SHAFT, COMPRESSOR ROTOR REAR HP MW0007872 NONE UL18114
31559 DISK, HP TURBINE LDRCZ13503 NONE UL27681 UNKNOWN DISK, COMPRESSOR, HP 1ST & 2ND STAGE DN40358 UL24024 SHAFT, COMPRESSOR ROTOR REAR HP DN40549 NONE UL18114 COMPLIANCE TIME (FC OR CALENDAR DATE, WHICHEVER

OCCURS FIRST) TOTAL LIFE CONSUMED

FLIGHT CYCLES (FC) LAST KNOWN

ESN ADDITIONAL LIFE CONSUMED IF OPERATING IN FP ’A’ FLIGHT CYCLES (FC)

31744 573

5000

3306
1668

984 100 FC, OR BY

31/08/2015 REMOVE WITHIN COMPLIANCE TIME

100 FC, OR BY

31/08/2015 REMOVE WITHIN COMPLIANCE TIME 100 FC, OR BY

31/08/2015 REMOVE WITHIN COMPLIANCE TIME 100 FC, OR BY

31/08/2015 REMOVE WITHIN COMPLIANCE TIME 100 FC, OR BY

31/08/2015 REMOVE WITHIN COMPLIANCE TIME 100 FC, OR BY

31/08/2015 REMOVE WITHIN COMPLIANCE TIME 100 FC, OR BY

31/08/2015 REMOVE WITHIN COMPLIANCE TIME 100 FC, OR BY

31/08/2015 REMOVE WITHIN COMPLIANCE TIME

100 FC, OR BY

31/08/2015 REMOVE WITHIN COMPLIANCE TIME 100 FC, OR BY

31/08/2015 REMOVE WITHIN COMPLIANCE TIME 100 FC, OR BY

31/08/2015 REMOVE WITHIN COMPLIANCE TIME NONE 1010 100 FC, OR BY

31/08/2015 REMOVE WITHIN COMPLIANCE TIME 100 FC, OR BY

31/08/2015 REMOVE WITHIN COMPLIANCE TIME 100 FC, OR BY

31/08/2015 REMOVE WITHIN COMPLIANCE TIME 100 FC, OR BY

31/08/2015 REMOVE WITHIN COMPLIANCE TIME 100 FC, OR BY

31/08/2015 REMOVE WITHIN COMPLIANCE TIME

100 FC, OR BY

31/08/2015 REMOVE WITHIN COMPLIANCE TIME R**Printed in Great Britain**



# RB.211−72−AH972 Appendix 4 - Page 27 May 22/15 Aug.28/15 Rdeh0014788 PART NAME PART SERIAL NUMBER PART NUMBER
31638 DISK, HP TURBINE LDRCZ11710 UL27681 UNKNOWN DISK, LPT STAGE 2 SEBH5140 UL11508 UNKNOWN DISK, COMPRESSOR, HP 1ST & 2ND STAGE DN62973 UL24024
30687 SHAFT, COMPRESSOR ROTOR REAR HP DN63595 UL18114 SPARE DISK, HP TURBINE CQDY6374 NONE UL10323 UNKNOWN DISK, LPT STAGE 2 SEBH5142 UL11508
31559 DISK, COMPRESSOR, HP 1ST & 2ND STAGE DN66262 NONE UL11678
31559 SHAFT, COMPRESSOR ROTOR REAR HP MW0002261 UL18114
31559 DISK, HP TURBINE LDRCZ13902 UL27681
30946 DISK, COMPRESSOR, HP 1ST & 2ND STAGE DN66611 NONE UL11678
30946 SHAFT, COMPRESSOR ROTOR REAR HP DN66474 NONE UL18114
30946 DISK, HP TURBINE LDRCZ13171 NONE UL27681 UNKNOWN DISK, LPT STAGE 2 SEBH5019 UL11508 UNKNOWN SHAFT, COMPRESSOR FRONT IP DN35650 UL16758 UNKNOWN DISK, COMPRESSOR, HP 1ST & 2ND STAGE DN35709 UL11678 UNKNOWN DISK, LPT STAGE 2 SEBH5060 UL11508 UNKNOWN DISK, LPT STAGE 2 SETM735 UL29029 UNKNOWN DISK, HP TURBINE CQDY6065 NONE UL10323 UNKNOWN DISK, COMPRESSOR, HP 1ST & 2ND STAGE DN40347 UL11678 UNKNOWN DISK, COMPRESSOR, HP 1ST & 2ND STAGE DN39140 UL24024 UNKNOWN DISK, HP TURBINE LDRCZ10691 UL27681 UNKNOWN DISK, HP TURBINE LDRCZ10138 UL27681 SHAFT, COMPRESSOR ROTOR REAR HP DN59531 UL18114 COMPLIANCE TIME (FC OR CALENDAR DATE, WHICHEVER

OCCURS FIRST) TOTAL LIFE CONSUMED

FLIGHT CYCLES (FC) LAST KNOWN

ESN ADDITIONAL LIFE CONSUMED IF OPERATING IN FP ’A’ FLIGHT CYCLES (FC)

NONE NONE

UNKNOWN 0 (ZERO)

2547

2383
1707
2173

4023 1825
2322 NONE 2597 100 FC, OR BY

31/08/2015 REMOVE WITHIN COMPLIANCE TIME 100 FC, OR BY

31/08/2015 REMOVE WITHIN COMPLIANCE TIME NONE 2079

100 FC, OR BY

31/08/2015 REMOVE WITHIN COMPLIANCE TIME

100 FC, OR BY

31/08/2015 REMOVE WITHIN COMPLIANCE TIME 100 FC, OR BY

31/08/2015 REMOVE WITHIN COMPLIANCE TIME 100 FC, OR BY

31/08/2015 REMOVE WITHIN COMPLIANCE TIME 100 FC, OR BY

31/08/2015 REMOVE WITHIN COMPLIANCE TIME 100 FC, OR BY

31/08/2015 REMOVE WITHIN COMPLIANCE TIME

100 FC, OR BY

31/08/2015 REMOVE WITHIN COMPLIANCE TIME 100 FC, OR BY

31/08/2015 REMOVE WITHIN COMPLIANCE TIME 100 FC, OR BY

31/08/2015 REMOVE WITHIN COMPLIANCE TIME 100 FC, OR BY

31/08/2015 REMOVE WITHIN COMPLIANCE TIME 100 FC, OR BY

31/08/2015 REMOVE WITHIN COMPLIANCE TIME R**Printed in Great Britain**



# RB.211−72−AH972 Appendix 4 - Page 28 May 22/15 Aug.28/15 RR**Printed in Great Britain**



# RB.211−72−AH972 Appendix 4 - Page 29 May 22/15 Aug.28/15 RFor Planning Purposes Only: Working Examples of Total Life Consumed
NOTE: The table in Appendix 4 lists each Group A part Serial Number against the last known ESN it was fitted to (according to Rolls-Royce records). With reference to section 1.D. Compliance operators of Group 'A' part serial numbers listed in Appendix 4 should follow the accomplishment instruction in section 3 and if required calculate the Total Life Consumed as defined in EQN 1. Total life consumed = CSN + Additional life consumed in current Flight Profile
EQN 1 NOTE: If current operations is in Flight Profile 'A' then the additional life consumed in the current Flight Profile is the same as the value recorded in the column 'Additional life consumed if operating in Flight Profile 'A'. If operation is in another flight profile e.g. Flight Profile 'B' then the following calculation in EQN 2 should be used (to at least 1 decimal place): Additional Life Consumed

in current

FP Additional Life Consumed if operating in FPA* ----------------------------------------------X DSCL in Current FP** DSCL in FP 'A'¬

EQN 2 * - Appendix 1 ** - For FP 'A', 'B', 'C' & 'F' refer to TLM 05-10-01-800-01 for FP 'D' & 'E' refer to NMSB 72-AG875

¬ - Time Limits Manual 05-10-01-800-01 1. Worked Examples. A. Example 1: RB211-535E4 aircraft operating ESN 30555 within FP 'A' - HPC Stage 1-2 (UL11678, MW0182624) has a CSN of 3,500 cycles. The HPC stage 1-2 (MW0182624) is listed in Appendix 4 with an additional life consumed in FP A of 2,161 cycles. As ESN 30555 is currently operating in FP 'A' then the calculation for the HPC Stage 1-2 would be: Total Life Consumed = 3,500 + 2,161 = 5,661 cycles APPENDIX 5**Printed in Great Britain**



# RB.211−72−AH972 Appendix 5 - Page 1 of 5 May 22/15 Aug.28/15 RThe HPC stage 1-2 would now fly onto the FP 'A' DSCL of 18,030 cycles and would have 12,369 cycles remaining. B. Example 2: RB211-535E4 aircraft operating ESN 30555 within FP 'B' - HPC Stage 1-2 (UL11678, MW0182624) has a CSN of 3,500 cycles The HPC stage 1-2 (MW0182624) is listed in Appendix 4 with an additional life consumed in FP A of 2,161 cycles. As ESN 30555 is currently operating in FP 'B' we need to use EQN 2 to calculate the additional life consumed in current FP. The calculation for the HPC Stage 1-2 would be:
Additional Life Consumed in current FP 2,161 ------- X 12,600 = 1510.18 Cycles 18,030
NOTE : The Additional Life Consumed in current Flight Profile should be rounded up to the next whole number - in this case 1,511 cycles. Total Life Consumed = 3,500 + 1,511 = 5,011 cycles The HPC stage 1-2 would now fly onto the FP 'B' DSCL of 12,600 cycles and would have 7,589 cycles remaining. C. Example 3: RB211-535E4-B aircraft operating ESN 30555 within FP 'E' - HPC Stage 1-2 (UL11678, MW0182624) has a CSN of 3,500 cycles The HPC stage 1-2 (MW0182624) is listed in Appendix 4 with an additional life consumed in FP 'A' of 2,161 cycles. As ESN 30555 is currently operating in FP 'E' we need to use EQN 2 to calculate the additional life consumed. The calculation for the HPC Stage 1-2 would be:
Additional Life Consumed in current FP 2,161 ------- X 15,700 = 1,881.74 Cycles 18,030
NOTE : The Additional Life Consumed in Current Flight Profile should be rounded up to the next whole number - in this case 1,882 cycles. Total Life Consumed = 3,500 + 1,882 = 5,382 cycles The HPC stage 1-2 would now fly onto the FP 'E' DSCL of 15,700 cycles and would have 10,318 cycles remaining.**Printed in Great Britain**



# RB.211−72−AH972 Appendix 5 - Page 2 May 22/15 Aug.28/15 RD. Example 4: RB211-535E4 aircraft operating ESN 30555 outside of FP 'B' (previously assumed to be operating in FP 'A') - HPC stage 1-2 (UL11678, MW0182624) has a CSN of 3,500 cycles. The HPC stage 1-2 (MW0182624) is listed in Appendix 4 with an additional life consumed in FP 'A' of 2,161 cycles. Flight Profile 'G' has been introduced to allow RB11-535E4 operation outside of currently published Flight Profiles e.g. FP 'A' or 'B'. Operators must first calculate the Total Life Consumed in the previously assumed Flight Profile before any conversion to Flight Profile 'G' lives are applied. The calculation for the HPC Stage 1-2 would be the same as in example 1: Total Life Consumed = 3,500 + 2,161 = 5,661 cycles Operators should then refer to Appendix 6 to determine whether their operation is within Flight Profile 'G' shaft speed limits defined in Appendix 6, Table 1. If operation is within the FP 'G' shaft speed limits they should carry out pro-rata calculations using the FP 'G' lives given in Appendix 2. In this example the calculation would be:
Total Life Consumed in current FP 'G' 5,661 ------- X 12,600 = 3,956.11 Cycles 18,030
NOTE : The Total Life Consumed in current FP 'G' should be rounded upto the next whole number - in this case 3,957 cycles. The HPC stage 1-2 would now fly onto the FP 'G' DSCL of 12,600 cycles and would have 8,643 cycles remaining. NOTE : If the operation is outside of FP 'G' shaft speed limits, the operator must contact RR. E. Example 5: RB211-535E4 aircraft operating ESN 30503 outside of FP 'B' (previously assumed to be operating in FP 'A') - LPC shaft (UL27910, PATH3990) has a CSN of 11,000 cycles on the issue date of NMSB 72-AH972. The LPC shaft (PATH3990) is not listed in Appendix 4 and therefore there is no requirement to calculate the Total life consumed. However, the DSCL of the LPC shaft is less in FP'G' than in the currently assumed FP 'A'.**Printed in Great Britain**



# RB.211−72−AH972 Appendix 5 - Page 3 May 22/15 Aug.28/15 ROperators should therefore refer to Appendix 6 to determine whether their operation is within FP 'G' shaft speed limits provided in Appendix 6, Table 1. If operation is within the FP 'G' shaft speed limits they should carry out pro-rata calculations using the FP 'G' lives given in Appendix 2. In this example the calculation would be:
Total Life Consumed in current FP 'G' 11,000 ------- X 14,230 = 5,744.22 Cycles 27,250
NOTE : The Total Life Consumed in current FP 'G' should be rounded upto the next whole number - in this case 5,745 cycles. NOTE : The LPC shaft would now fly onto the FP 'G' DSCL of 14,230 cycles and would have 8,485 cycles remaining. NOTE : If the operation is outside of FP 'G' shaft speed limits, the operator must contact RR. F. Example 6: RB211-535E4 aircraft operating ESN 30503 outside of FP 'B' (previously assumed to be operating in FP 'A') - Fan blades (FW12308) have a CSN of 5,000 cycles on the date the engine comes into shop. Fan blades are not listed in Appendix 4 and therefore there is no requirement to calculate the Total life consumed. However, the life limit for fan blades is less in FP'G' than in the currently assumed FP 'A'. Operators should therefore refer to Appendix 6 to determine whether their operation is within FP'G' shaft speed limits provided in Appendix 6, Table 1. If operation is within the FP 'G' shaft speed limits they should carry out pro-rata calculations using the FP 'G' lives given in Appendix 3. In this example the calculation would be:
Total Life Consumed in current FP 'G' 5,000 ------- X 17,600 = 3,580.15 Cycles 24,580
NOTE : The Total Life Consumed in current FP 'G' should be rounded upto the next whole number - in this case 3,581 cycles.**Printed in Great Britain**



# RB.211−72−AH972 Appendix 5 - Page 4 May 22/15 Aug.28/15 RThe fan blades would now fly onto the FP 'G' life limits of 17,600 cycles and would have 14,019 cycles remaining. NOTE : If the operation is outside of FP 'G' shaft speed limits, the operator must contact RR.**Printed in Great Britain**



# RB.211−72−AH972 Appendix 5 - Page 5 May 22/15 Aug.28/15 RRevised 535E4 Profile Flight Profile 'G'. The following contents will be instructed in the Aircraft Maintenance Manual under Temporary Revision. NOTE: Only Flight Profile speeds for the existing E4 flight profiles (Flight Profile 'A' and Flight Profile 'B'), the new flight profile (Flight Profiles 'G') have been included in this section of the document. All other 535E4 flight profiles remain unchanged. 1. Prepare for the Flight Profiles and Operational Monitoring Datum Flight Profiles, refer to Table 1. A. Engine operation must be monitored. The 12 month average shaft speeds are required to be less than or equal to the shaft speeds given in the datum Flight Profile. If the 12 month average shaft speeds exceed the shaft speeds given in the datum Flight Profile for the engine, operators must contact Rolls-Royce. This applies to all RB211-535 engine marks. B. For RB211-535C-37 Engines; refer to RB211-535C-37 Engine datum flight profile. C. For RB211-535E4-37 Engines; refer to Flight Profile 'A', Flight Profile 'B' and Flight Profile 'G'. You must have Airworthiness Authority approval in the country in which the operation is registered to use the life limits given in Flight Profile 'A' or Flight Profile 'B' as described in the Rolls-Royce Time Limits Manual (Chapter 05-10-01). There are three modes of operation for the 535E4-37. The three modes are Flight Profile 'A', Flight Profile 'B' and Flight Profile 'G'. (1)Flight Profile 'A' When the average maximum HP (N3), IP (N2) and LP (N1) speeds at takeoff and during climb are less than or equal to the limits of 535E4-37 Flight Profile 'A', the operator can use Flight Profile 'A'. The lives of the Group 'A' parts for these engines are as given in the Rolls-Royce Time Limits Manual for Flight Profile 'A' (Chapter 05-10-01). (2)Flight Profile 'B' When the average maximum HP (N3), IP (N2) and LP (N1) speeds at takeoff and during climb are more than the limits of 535E4-37 Flight Profile 'A', but are less than or equal to the limits of 535E4-37 Flight Profile 'B', the operator can use Flight Profile 'B'. The lives of the Group A parts for these engines are as given in the Rolls-Royce Time Limits Manual for Flight Profile 'B' (Chapter 05-10-01). APPENDIX 6**Printed in Great Britain**



# RB.211−72−AH972 Appendix 6 - Page 1 of 13 May 22/15 Aug.28/15 R(3)Flight Profile 'G' When the average maximum HP (N3), IP (N2) and LP (N1) speeds at takeoff and during climb are more than the limits of 535E4-37 Flight Profile 'B', but are less than or equal to the limits of 535E4-37 Flight Profile 'G', the operator must use Flight Profile 'G'. The lives of the Group A parts for these engines are as given in the Rolls-Royce Time Limits Manual for Flight Profile 'G' (Chapter 05-10-01). D. For RB211-535E4-B-37 Engines; refer to Flight Profile 'C', Flight Profile 'D' and Flight Profile 'E'. There are three flight profiles for the 535E4-B-37 engines. The three flight profiles are Flight Profile 'C', Flight Profile 'D' and Flight Profile 'E'. You must have Airworthiness Authority approval in the country in which the operation is registered to use the life limits given in Flight Profile 'C' as described in the Rolls-Royce Time Limits Manual (Chapter 05-10-01). (1)Flight Profile 'C'. When the average maximum HP (N3), IP (N2) and LP (N1) speeds at takeoff and during climb are less than or equal to the limits of 535E4-B-37 Flight Profile 'C' the operator can use Flight Profile 'C'. The lives of the Group A parts for these engines are as given in the Rolls-Royce Time Limits Manual for Flight Profile 'C' (Chapter 05-10-01). (2)Flight Profile 'D' When the average maximum HP (N3), IP (N2) and LP (N1) speeds at takeoff and during climb less than or equal to the limits of 535E4-B-37 Flight Profile 'D' the operator must use Flight Profile 'D'. The lives of the Group A parts for these engines are as given in the Rolls-Royce Time Limits Manual for Flight Profile 'D' (Chapter 05-10-01). (3)Flight Profile 'E' When the average maximum HP (N3), IP (N2) and LP (N1) speeds at takeoff and during climb less than or equal to the limits of 535E4-B-37 Flight Profile 'E' the operator must use Flight Profile 'E'. The lives of the Group A parts for these engines are as given in the Rolls-Royce Time Limits Manual for Flight Profile 'E' (Chapter 05-10-01). (4)For RB211-535E4-C-37 Engines, refer to Flight Profile 'F'. E. If operators are unable to establish historical operations, default to Flight Profile 'E' and contact Rolls-Royce. Summary Table of 535E4 Flight Profiles**Printed in Great Britain**



# RB.211−72−AH972 Appendix 6 - Page 2 May 22/15 Aug.28/15 REngine Flight Profile Reference New Flight Profile Reference Aircraft Type

535E4 E4 Flight Profile A Flight Profile A 757-200
E4 Flight Profile B Flight Profile B 757-200

N/A Flight Profile G 757-200
535E4-B E4-B Flight Profile Flight Profile C 757-200 and 757-300
E4-B 757-200 Heavy Flight Profile D Typically 757-200

E4-B 757-300 Heavy Flight Profile E Typically 757-300

535E4-C E4-C Flight Profile Flight Profile F 757-200 and 757-300
NOTE : The flight profiles given in the above sequence from Flight Profile 'A' to Flight Profile 'G' are not in any particular hierarchy or order in relation to shaft speed limits or nature of operation. The aircraft type associated with each flight profile has been included for guidance purposes only and is reflective of the fleet at the date of initial issue of this NMSB. 2. New Operators, or New Sub-fleets within an existing Operator, for Operational Flight Profiles, refer to Appendix 4 . A. For RB211-535C-37 and 535E4-C-37 Engines (Flight Profile 'F') do the steps that follow: (1)The new operators or sub-fleets must assume the operation to applicable datum flight profile for a minimum of the first 12 months of operation. This is to permit the consideration of seasonal variation.**Printed in Great Britain**



# RB.211−72−AH972 Appendix 6 - Page 3 May 22/15 Aug.28/15 R(2)After six months, if an operator thinks the operation of their fleet or any of their sub-fleets is more than the limits of the applicable flight profile, the operator must contact Rolls-Royce for advice and continue to monitor engine operation. (3)After 12 months, if an operator has data that shows the operation of their fleet or any of their sub-fleets is more than the limits of the applicable flight profile, the operator must contact Rolls-Royce for advice and continue to monitor engine operation. B. For RB211-535E4-37 Engines do the steps that follow: (1)The new operators or sub-fleets must assume the operation to 535E4-37 Flight Profile 'G' for a minimum of the first 12 months of operation. (2)The compliance with 5435E4-37 Flight profile 'A' or Flight Profile 'B' can only be considered after the collection of data for one full years operation. This is to permit the consideration of seasonal variations. (3)If this data shows that their operation is less than or equal to the limits of 535E4-37 Flight Profile 'A' or Flight Profile 'B', the operator must approach their Airworthiness Authority to apply for permission to account Group 'A' part life with the use of 535E4-37 Flight Profile 'A' or Flight Profile 'B'. (4)If this permission is given, 535E4-37 Flight Profile 'A' or Flight Profile 'B' can be taken from the entry into service of the operators new fleet or sub-fleet. (5)After six months, if an operator thinks the operation of their fleet or any of their sub-fleet is more than the limits of 535E4-37 Flight Profile 'G', the operator must contact Rolls-Royce for advice and continue to monitor engine operation. (6)After 12 months, if an operator has data that shows the operation of their fleet or any of their sub-fleets is more than the limits of 535E4-37 Flight Profile 'G', the operator must contact Rolls-Royce for advice and continue to monitor engine operation. C. For RB211-535E4-B-37 Engines do the steps that follow: (1)New operators or sub-fleets must assume operation to 535E4-B-37 Flight Profile 'E' for the first 12 months of operation. (2)The compliance with 535E4-B-37 Flight Profile 'C' or Flight Profile'D' can only be considered after the collection of data for one full years operation. This is to permit the consideration of seasonal variations.**Printed in Great Britain**



# RB.211−72−AH972 Appendix 6 - Page 4 May 22/15 Aug.28/15 R(3)If this data shows that their operation is less than or equal to the limits of 535E4-B-37 Flight Profile 'C' or Flight Profile 'D', the operator must approach their Airworthiness Authority to apply for permission to account Group A part life with the use of 535E4-B-37 Flight Profile 'C' or Flight Profile 'D'. (4)If this permission is given, 535E4-B-37 Flight Profile 'C' or Flight Profile 'D' can be taken from the entry into service of the operators new fleet or sub-fleet. (5)After six months, if an operator thinks the operation of their fleet or any of their sub-fleets is more than the limits of 535E4-B-37 Flight Profile 'E', the operator must contact Rolls-Royce for advice and continue to monitor engine operation. (6)After 12 months, if an operator has data that shows the operation of their fleet or any of their sub-fleets is more than the limits of 535E4-B-37 Flight Profile 'E', the operator must contact Rolls-Royce for advice and continue to monitor engine operation. 3. Construction of the Operational Flight Profile and Data - All RB211-535 Engine Marks A. It is very important for each operator to prepare and analyse their own operational flight profile and data. Differences between the operators data and the applicable datum flight profile can make it necessary to change the specified life limits for Group A parts. B. For flight profile monitoring, the operator must decide if their RB211-535 powered Boeing 757 aircraft must be treated as one fleet, or as two or more sub-fleets. This decision must be based on operators knowledge of their fleet specification and how they operate or utilize their engines. C. If a number of engines have been operated almost the same with respect to the aspects that follow, then those engines can be grouped together into the same fleet or sub-fleet: (1)Aircraft type or configuration (2)Installed engine rating (3)De-rate (4)Route structure (5)Usually interchangeable between route flown**Printed in Great Britain**



# RB.211−72−AH972 Appendix 6 - Page 5 May 22/15 Aug.28/15 RD. The operator must gather flight data for their fleet or each of their sub-fleets and use this to monitor the Operational Flight Profile flown by their fleet or sub-fleets. (1)The data is not necessary from every flight flown by every engine in a given fleet or sub-fleet. However, the data that is gathered must be of a minimum number of flights for the fleet or each sub-fleet as given in the table below.

NOTE: The data gathered from the minimum number of flights must contain data from both operating engines of each flight cycle. Number of Aircraft in the fleet or Sub-fleet Minimum Number of Flights to be Recorded Each Year 1 20 2 40 3 50 4-5 60 6-10 100 11-15 130 14-20 150 21-25 180 26-30 200 Over 30 220 (2)The data collected must be representative of the operation of their engine fleet or each of their engine sub-fleets as a whole, and must have the conditions that follow:

(1) Cover at least 12 months of operation, to permit the consideration of seasonal variations. (2) Be collected at different times of the day or night. (3) Include all months operated, with the ratio to the whole operation maintained. (4) Include all routes operated, with the ratio to the whole operation maintained. (5) Include all aircraft operated, with the ratio to the whole operation maintained. E. For example, if a quarter of all flights are on one route this must be reflected in the data collected. Similarly, if the majority of flights are made in the summer months, then this should also be reflected in the data collected. NOTE : Also refer to Chapter 05-00-01 of the Time Limits Manual. It is the responsibility of the operator to make sure that the data is representative of their operation.**Printed in Great Britain**



# RB.211−72−AH972 Appendix 6 - Page 6 May 22/15 Aug.28/15 RF. The average operational flight profile must be assembled from the points that follow: (1)Average maximum shaft speeds during take-off. (2)Average maximum shaft speeds during climb. 4. Measurement of the Data using Digital Flight Data Recording (DFDR) - All RB211-535 engine marks. A. Make arrangements to set the Digital Flight Data Recording (DFDR) equipment to record the maximum shaft speeds of the HP (N3), IP (N2), and LP (N1) during takeoff and climb. Record the data then find the averages of the HP, IP, and LP shaft speeds, after the airplane lands. B. Alternatively, after the airplane lands, remove the DFDR data from the airplane, then interrogate it to find the maximum shaft speeds of the HP (N3), IP (N2) and LP (N1) during takeoff and climb. Record the data then find the averages of the HP, IP, and LP shaft speeds and compare them to the datum profile speeds given in Table 1 below. Flight Profile TO N1 TO N2 TO N3 CL N1 CL N2 CL N3 A 95.5 93.0 91.5 99.0 90.9 91.2 B 101.4 93.0 94.9 100.7 90.9 91.2 C 98.4 93.0 92.7 99.0 90.9 91.2 D 95.3 91.9 93.0 100.0 91.6 92.3 E 98.2 93.5 94.8 99.9 92.5 92.8 F 101.5 93.2 94.0 98.9 90.9 90.3 G 101.4 94.7 94.9 100.7 92.5 92.8 Table 1: Summary of Flight Profile Speeds 5. Measurement of the data using Manual Data Capture - RB211-535E4-37, 535E4-B-37 and 535E4-C-37.

This is an alternative to the use of DFDR data.

A. Make arrangement so that at takeoff, the necessary HP (N3), IP (N2) and LP (N1) shaft speeds are calculated from the flight log data. (1)Calculate the shaft speeds, use the Engine Pressure Ratio (EPR) and Outside Air Temperature (OAT) where A=EPR-1.4 and B=1.775+(1.0065 x OAT) as follows:**Printed in Great Britain**



# RB.211−72−AH972 Appendix 6 - Page 7 May 22/15 Aug.28/15 RLP (N1) speed= 75.7 + (65 x A) + (0.2333 x B) IP (N2) speed= 75.81 + (49.5 x A) + (0.1283 x B) HP (N3) speed= 81.41 + (27.75 x A) + (0.1133 x B) B. Record the calculated values, and then find the averages of the takeoff HP, IP and LP shaft speeds. C. Because the takeoff values are calculated values and not actual shaft speeds, the average of the calculated shaft speed must be compared with the limits that are given in the table below. The average of the calculated shaft speeds must be compared with Datum Flight Speed Profile. % Shaft Speed Engine LP (N1) Takeoff IP (N2) Takeoff HP (N3) Takeoff RB211-535E4-37 Flight Profile 'A' < or = 94.6 < or = 92.6 < or = 90.9 RB211-535E4-37 Flight Profile 'B' < or = 100.5 < or = 92.6 < or = 94.3 RB211-535E4-37 Flight Profile 'G' < or = 100.5 < or = 94.2 < or = 94.3 RB211-535E4-B-37 Flight Profile 'C' < or = 97.5 < or = 92.6 < or = 92.1

RB211-535E4-B-37 Flight Profile 'D' < or = 94.4 < or = 91.5 < or = 92.4

RB211-535E4-B-37 Flight Profile 'E' < or = 97.3 < or = 93.1 < or = 94.2

RB211-535E4-C-37 Flight Profile 'F' < or = 100.6 < or = 92.8 < or = 93.4 D. Arrangements must be made so that during climb, operation of the 'Manual Event' button records the HP (N3), IP (N2) and LP (N1) speeds. (1)The button must be operated during climb at 20,000 feet. (2)Download the data before the next flight. The values given are values of actual shaft speed.

NOTE: If you do not download the data, it will be written over on the next leg. E. Calculate the 12 month average of the recorded shaft speeds in climb and compare with the data in the Datum Flight Speed Profile for 'typical 20,000 feet' for the applicable engine rating.**Printed in Great Britain**



# RB.211−72−AH972 Appendix 6 - Page 8 May 22/15 Aug.28/15 R6. Monitoring of the Operational Flight Profile Data. A. For RB211-535-C-37 and 535E4-C-37 (Flight Profile 'F') engines do the steps that follow: (1)The operator must reassess their flight profile flown at regular intervals. A compliance report with supporting data must be sent to the operators Airworthiness Authority.

The interval recommended by Rolls-Royce is 12 months. This is to permit the consideration of seasonal variations. (2)If the operational flight profile shows that an operator fleet or any of their sub-fleets is more than the limits of the applicable datum flight profile, the operator must contact Rolls-Royce and continue to monitor their operational flight profile. B. For RB211-535E4-37 engines do the steps that follow: (1)The operator must reassess their flight profile flown at regular intervals. (2)A compliance report with supporting data must be sent to the operators Airworthiness Authority.

The interval recommended by Rolls-Royce is 12 months. This is to permit the consideration of seasonal variations. (3)For operators that already have agreement of compliance to the limits of 535E4-37 Flight Profile 'A' from their Airworthiness authority.

(1) If the operational flight profile shows that their fleet or applicable sub-fleet stays within the limits of 535E4-37 Flight Profile 'A', the operator must continue to use the Group A parts lives related to 535E4-37 Flight Profile 'A' for that sub fleet.**Printed in Great Britain**



# RB.211−72−AH972 Appendix 6 - Page 9 May 22/15 Aug.28/15 R(2) If the operational flight profile shows that their fleet or sub fleet is more than the limits of 535E4-37 Flight Profile 'A' the operator must take 535E4-37 Flight Profile 'B' or 'G' for that sub fleet, and the Group 'A' parts lives as given in the Time Limits Manual 05-10-01 for 535E4-37 Flight Profile 'B' or 'G'. The operator must inform their Airworthiness Authority of the change in flight profile allocation. The date of the change of flight profile must be taken as the start of the next 12 month operational flight profile period. Retrospective application of a flight profile for the previous 12 months is not required providing the following steps are complied with: 1. For the critical group A parts installed in the affected fleet or sub fleet that have 200 flight cycles remaining or less against the previous flight profile (Flight Profile 'A') declared lives. A pro-rata life calculation must be done in no more than two weeks to find the equivalent CSN in Flight Profile 'B' or 'G'. NOTE: Guidance on how to do the pro-rata life calculation is given in chapter 05-00-01 of the Time Limits Manual. 2. For the critical group A parts installed in the affected fleet or sub fleet that have more than 200 flight cycles remaining against the previous flight profile (Flight Profile 'A') declared lives. A pro-rata life calculation must be done in no more than four weeks to find the equivalent CSN in Flight Profile 'B' or 'G'. NOTE: Guidance on how to do the pro-rata life calculation is given in chapter 05-00-01 of the Time Limits Manual. (4)For operators that use the lives related to 535E4-37 Flight Profile 'B'. (1) If the operational flight profile shows that their fleet or applicable sub fleet stays within the limits of 535E4-37 Flight Profile 'B', the operator must continue to use the Group A parts lives related to 535E4-37 Flight Profile 'B' for that sub fleet.**Printed in Great Britain**



# RB.211−72−AH972 Appendix 6 - Page 10 May 22/15 Aug.28/15 R(2) If the operational flight profile shows that their fleet or applicable sub fleet is more than the limits of 535E4-37 Flight Profile 'B', the operator must take 535E4-37 Flight Profile 'G' and the Group A parts lives as given in the Time Limits Manual 05-10-01 for 535E4-37 Flight Profile 'G'. The operator must inform their Airworthiness Authority of the change in flight profile allocation. The date of change of flight profile must be taken as the start of the next 12 month operational flight profile period. Retrospective application of a flight profile for the previous 12 months is not required providing the following steps are complied with: 1. For the critical group A parts installed in the affected fleet or sub fleet that have 200 flight cycles remaining or less against the previous flight profile (Flight Profile 'A' or 'B') declared lives. A pro-rata life calculation must be done in no more than two weeks to find the equivalent CSN in Flight Profile 'G'. NOTE: Guidance on how to do the pro-rata life calculation is given in chapter 05-00-01 of the Time Limits Manual. 2. For the critical group A parts installed in the affected fleet or sub fleet that have more than 200 flight cycles remaining against the previous flight profile (Flight Profile 'A' or 'B') declared lives. A pro-rata life calculation must be done in no more than four weeks to find the equivalent CSN in Flight Profile 'G'. NOTE: Guidance on how to do the pro-rata life calculation is given in chapter 05-00-01 of the Time Limits Manual. C. For RB211-535E4-B-37 engines do the steps that follow: (1)The operator must reassess their flight profile flown at regular intervals. (2)A compliance report with supporting data must be sent to the operators Airworthiness Authority.

The interval recommended by Rolls-Royce is 12 months. This is to permit the consideration of seasonal variations. (3)For operators that already have agreement of compliance to the limits of 535E4-B-37 Flight Profile 'C' from their Airworthiness authority.

(1) If the operational flight profile shows that their fleet or applicable sub-fleet stays within the limits of 535E4-B-37 Flight Profile 'C', the operator must continue to use the Group A parts lives related to 535E4-B-37 Flight Profile 'C' for that sub fleet.**Printed in Great Britain**



# RB.211−72−AH972 Appendix 6 - Page 11 May 22/15 Aug.28/15 R(2) If the operational flight profile shows that their fleet or applicable sub fleet is more than the limits of 535E4-B-37 Flight Profile 'C', the operator must take 535E4-B-37 Flight Profile 'D' (757-200 operators) for that sub fleet and the Group A parts lives as given in the Time Limits Manual 05-10-01 for 535E4-37 Flight Profile 'D'. The operator must inform their Airworthiness Authority of the change in flight profile allocation. The date of change of flight profile must be taken as the start of the next 12 month operational flight profile period. Retrospective application of a flight profile for the previous 12 months is not required providing the following steps are complied with: 1. For the critical group A parts installed in the affected fleet or sub fleet that have 200 flight cycles remaining or less against the previous flight profile (Flight Profile 'C') declared lives. A pro-rata life calculation must be done in no more than two weeks to find the equivalent CSN in Flight Profile 'D'. NOTE: Guidance on how to do the pro-rata life calculation is given in chapter 05-00-01 of the Time Limits Manual. 2. For the critical group A parts installed in the affected fleet or sub fleet that have more than 200 flight cycles remaining against the previous flight profile (Flight Profile 'C') declared lives. A pro-rata life calculation must be done in no more than four weeks to find the equivalent CSN in Flight Profile 'D'. NOTE: Guidance on how to do the pro-rata life calculation is given in chapter 05-00-01 of the Time Limits Manual. (4)For operators that use the lives related to 535E4-B-37 Flight Profile 'D' (typically, but not limited to 757-200 operators).

(1) If the operational flight profile shows that their fleet or applicable sub fleet stays within the limits of 535E4-B-37 Flight Profile 'D', the operator must continue to use the Group A parts lives related to 535E4-B-37 Flight Profile 'D' for that sub fleet.**Printed in Great Britain**



# RB.211−72−AH972 Appendix 6 - Page 12 May 22/15 Aug.28/15 R(2) If the operational flight profile shows that their fleet or applicable sub fleet is more than the limits of 535E4-B-37 Flight Profile 'D', the operator must take 535E4-B-37 Flight Profile 'E' and the Group A parts lives as given in the Time Limits Manual 05-10-01 for 535E4-B-37 Flight Profile 'E'. the operator must inform their Airworthiness Authority of the change in flight profile allocation. The date of change of flight profile must be taken as the start of the next 12 month operational flight profile period. Retrospective application of a flight profile for the previous 12 months is not required providing the following steps are complied with: 1. For the critical group A parts installed in the affected fleet or sub fleet that have 200 flight cycles remaining or less against the previous flight profile (Flight Profile 'D') declared lives. A pro-rata life calculation must be done in no more than two weeks to find the equivalent CSN in Flight Profile 'E'. NOTE: Guidance on how to do the pro-rata life calculation is given in chapter 05-00-01 of the Time Limits Manual. 2. For the critical group A parts installed in the affected fleet or sub fleet that have more than 200 flight cycles remaining against the previous flight profile (Flight Profile 'D') declared lives. A pro-rata life calculation must be done in no more than four weeks to find the equivalent CSN in Flight Profile 'E'. NOTE: Guidance on how to do the pro-rata life calculation is given in chapter 05-00-01 of the Time Limits Manual. D. Intermixing between Engine Types. Refer to Rolls-Royce Time Limits Manual (Chapter 05-00-01). E. The Definition of a Flight Cycle - All RB211-535 engine marks. Normal flights - A normal take-off through to landing which agrees with the appropriate flight profile is specified as one flight cycle. Refer to Rolls-Royce Time Limits Manual (Chapter 05-00-01). NOTE : The data gathered from the minimum number of flights must contain data from both operating engines of each flight cycle. F. Pilot training flights - Refer to Rolls-Royce Time Limits Manual (Chapter 05-00-01).**Printed in Great Britain**



# RB.211−72−AH972 Appendix 6 - Page 13 May 22/15 Aug.28/15 R