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 2
LIST 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

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Transmittal - Page 3
R 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 4
1. 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

R Aug.28/15
Failure 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

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R Aug.28/15
D. 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

R Aug.28/15
(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,

R Jun. 5/15, Jul.20/15 and again on Aug.27/15.

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

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(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

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2. Material Information

None

Printed in Great Britain

RB.211−72−AH972

Page 6

May 22/15

R Aug.28/15
3. 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

R Aug.28/15
After 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

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Page 8

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(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

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Logic for On-wing Accomplishment Instructions

Fig.1

Printed in Great Britain

RB.211−72−AH972

Page 10

May 22/15

R Aug.28/15
Logic for In-shop Accomplishment Instructions

Fig.2

Printed in Great Britain

RB.211−72−AH972

Page 11

May 22/15

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Recording 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

R Aug.28/15
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 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

R Aug.28/15
Group 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

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Appendix 2 - Page 1 of 8

May 22/15

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72-31-20, 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

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Appendix 2 - Page 2

May 22/15

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72-51-63, 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

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May 22/15

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72-51-61, 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

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72-51-61, 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

R Aug.28/15
8. 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

R Aug.28/15
72-51-31, 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

R Aug.28/15
72-41-31, 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

R Aug.28/15
Group 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

R Aug.28/15
72-31-11, 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

R Aug.28/15
72-31-11, 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

R Aug.28/15
72-31-11, 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

R Aug.28/15
The 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

R Aug.28/15
List 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

RB.211−72−AH972

Appendix 4 - Page 1 of 29

May 22/15

R Aug.28/15
Printed in Great Britain

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Appendix 4 - Page 2

May 22/15

R Aug.28/15
Printed in Great Britain

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Appendix 4 - Page 3

May 22/15

R Aug.28/15
Printed in Great Britain

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Appendix 4 - Page 4

May 22/15

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Printed in Great Britain

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Appendix 4 - Page 5

May 22/15

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Printed in Great Britain

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Appendix 4 - Page 6

May 22/15

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Printed in Great Britain

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Appendix 4 - Page 7

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deh0014785

PART NAME PART SERIAL

NUMBER

PART

NUMBER

30629 DISK, LPT STAGE 2 UL29029 SETM22360 NONE 303

30629 SHAFT, COMPRESSOR ROTOR REAR HP UL18114 MW0246408 NONE 365

30629 DISK, HP TURBINE UL39767 LDRCZ16898 NONE 465

30629 DISK, COMPRESSOR, HP 1ST & 2ND STAGE UL11678 MW0246733 NONE 510

30630 DISK, HP TURBINE UL27681 LDRCZ12259 NONE 2175

30640 DISK, COMPRESSOR, HP 1ST & 2ND STAGE UL11678 MW0011407 NONE 1853

30640 DISK, HP TURBINE UL27681 LDRCZ12887 NONE 2117

30643 SHAFT, COMPRESSOR FRONT IP UL16758 DN35520 NONE 2107

30643 DISK, HP TURBINE UL27681 LDRCZ12036 904 FC, OR BY

30660 DISK, HP TURBINE UL39767 LDRCZ16622 NONE 2297

30670 DISK, LPT STAGE 2 FW16686 SEBH5141 904 FC, OR BY

30676 SHAFT, COMPRESSOR ROTOR REAR HP UL18114 DN60412 REMOVE WITHIN

30687 SHAFT, COMPRESSOR FRONT IP UL16758 DN40586 NONE 601

30694 SHAFT, COMPRESSOR ROTOR REAR HP UL18114 DN65734 NONE 956

30712 SHAFT, COMPRESSOR ROTOR REAR HP UL18114 RRDCDDMW NONE 676

30712 DISK, HP TURBINE UL39767 LDRCZ19337 NONE 860

30712 DISK, LPT STAGE 2 UL29029 SETM24314 NONE 897

30712 DISK, COMPRESSOR, HP 1ST & 2ND STAGE UL11678 MW0441132 NONE 944

30712 SHAFT, COMPRESSOR FRONT IP UL30176 MW0148568 NONE 1383

30713 SHAFT, COMPRESSOR FRONT IP UL30176 MW0233720 NONE 1124

30713 DISK, LPT STAGE 2 UL29029 SETM22154 NONE 1918

30713 SHAFT, COMPRESSOR ROTOR REAR HP UL18114 MW0235188 NONE 2316

30713 DISK, HP TURBINE UL39767 LDRCZ16792 NONE 2947

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

RB.211−72−AH972

Appendix 4 - Page 8

May 22/15

R Aug.28/15
Printed in Great Britain

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Appendix 4 - Page 9

May 22/15

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Printed in Great Britain

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Appendix 4 - Page 10

May 22/15

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Printed in Great Britain

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Appendix 4 - Page 11

May 22/15

R Aug.28/15
Printed in Great Britain

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Appendix 4 - Page 12

May 22/15

R Aug.28/15
Printed in Great Britain

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Appendix 4 - Page 13

May 22/15

R Aug.28/15
Printed in Great Britain

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Appendix 4 - Page 14

May 22/15

R Aug.28/15
Printed in Great Britain

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Appendix 4 - Page 15

May 22/15

R Aug.28/15
Printed in Great Britain

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Appendix 4 - Page 16

May 22/15

R Aug.28/15
Printed in Great Britain

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Appendix 4 - Page 17

May 22/15

R Aug.28/15
Printed in Great Britain

RB.211−72−AH972

Appendix 4 - Page 18

May 22/15

R Aug.28/15
Printed in Great Britain

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Appendix 4 - Page 19

May 22/15

R Aug.28/15
Printed in Great Britain

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Appendix 4 - Page 20

May 22/15

R Aug.28/15
Printed in Great Britain

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Appendix 4 - Page 21

May 22/15

R Aug.28/15
Printed in Great Britain

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Appendix 4 - Page 22

May 22/15

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Printed in Great Britain

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Appendix 4 - Page 23

May 22/15

R Aug.28/15
Printed in Great Britain

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Appendix 4 - Page 24

May 22/15

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Printed in Great Britain

RB.211−72−AH972

Appendix 4 - Page 25

May 22/15

R Aug.28/15
deh0014786

PART NAME PART SERIAL

NUMBER

PART

NUMBER

UNKNOWN DISK, COMPRESSOR, HP 1ST & 2ND STAGE UL11678 DN36555 NONE

UNKNOWN DISK, COMPRESSOR, HP 1ST & 2ND STAGE UL11678 DN60981

UNKNOWN DISK, HP TURBINE UL27681 LDRCZ10176

UNKNOWN DISK, LPT STAGE 2 FW16687 SETM05754

30906 SHAFT, COMPRESSOR FRONT IP UL30176 DN59361 NONE

UNKNOWN SHAFT, COMPRESSOR ROTOR REAR HP UL18114 DN61028

31677 SHAFT, COMPRESSOR ROTOR REAR HP UL18114 MW0016950 NONE

UNKNOWN DISK, HP TURBINE UL27680 CQDY6502

SPARE DISK, COMPRESSOR, HP 1ST & 2ND STAGE UL11678 DN62390

UNKNOWN SHAFT, COMPRESSOR ROTOR REAR HP UL18114 DN36917

SPARE DISK, HP TURBINE UL27681 LDRCZ11442 NONE

UNKNOWN DISK, LPT STAGE 2 UL11508 SEBH5100

31105 DISK, COMPRESSOR, HP 1ST & 2ND STAGE UL11678 MW0096376 NONE

30517 DISK, LPT STAGE 2 UL29029 SETM13563

31081 SHAFT, COMPRESSOR ROTOR REAR HP UL18114 MW0078829 NONE

UNKNOWN DISK, COMPRESSOR, HP 1ST & 2ND STAGE UL11678 MW0003373 NONE

UNKNOWN DISK, LPT STAGE 2 UL37352 SEBH5135

UNKNOWN SHAFT, COMPRESSOR FRONT IP UL16758 DN35301 NONE

UNKNOWN DISK, COMPRESSOR, HP 1ST & 2ND STAGE UL11678 DN61976

UNKNOWN DISK, HP TURBINE UL39767 LDRCZ10975

31282 DISK, COMPRESSOR, HP 1ST & 2ND STAGE UL11678 DN61972 NONE

DISK, LPT STAGE 2 UL29029 SETM15229 NONE

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

R Aug.28/15
deh0014787

PART NAME PART SERIAL

NUMBER

PART

NUMBER

UNKNOWN DISK, COMPRESSOR, HP 1ST & 2ND STAGE UL11678 DN41401

UNKNOWN DISK, LPT STAGE 2 UL29029 SETM1710 NONE

UNKNOWN DISK, LPT STAGE 2 UL37352 SEBH5124

UNKNOWN DISK, COMPRESSOR, HP 1ST & 2ND STAGE UL11678 DN42706

UNKNOWN SHAFT, COMPRESSOR FRONT IP UL16758 DN42484

UNKNOWN DISK, COMPRESSOR, HP 1ST & 2ND STAGE UL11678 DN42712

UNKNOWN DISK, LPT STAGE 2 UL18947 SETM2345

UNKNOWN DISK, HP TURBINE UL27681 LDRCZ10086

UNKNOWN SHAFT, COMPRESSOR ROTOR REAR HP UL18114 DN58832

UNKNOWN DISK, LPT STAGE 2 FW16687 SETM05760 NONE

UNKNOWN SHAFT, COMPRESSOR FRONT IP UL30176 DN59386

UNKNOWN DISK, COMPRESSOR, HP 1ST & 2ND STAGE UL11678 DN66953

UNKNOWN DISK, HP TURBINE UL27681 LDRCZ10606

30631 SHAFT, COMPRESSOR ROTOR REAR HP UL18114 DN61134

UNKNOWN DISK, LPT STAGE 2 FW16687 SETM07546

UNKNOWN DISK, COMPRESSOR, HP 1ST & 2ND STAGE UL11678 DN60848

UNKNOWN DISK, COMPRESSOR, HP 1ST & 2ND STAGE UL11678 DN61859

UNKNOWN DISK, LPT STAGE 2 FW16687 SETM06288

UNKNOWN SHAFT, COMPRESSOR ROTOR REAR HP UL18114 DN61818

UNKNOWN SHAFT, COMPRESSOR ROTOR REAR HP UL18114 MW0007872 NONE

31559 DISK, HP TURBINE UL27681 LDRCZ13503 NONE

UNKNOWN DISK, COMPRESSOR, HP 1ST & 2ND STAGE UL24024 DN40358

SHAFT, COMPRESSOR ROTOR REAR HP UL18114 DN40549 NONE

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

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Appendix 4 - Page 27

May 22/15

R Aug.28/15
deh0014788

PART NAME PART SERIAL

NUMBER

PART

NUMBER

31638 DISK, HP TURBINE UL27681 LDRCZ11710

UNKNOWN DISK, LPT STAGE 2 UL11508 SEBH5140

UNKNOWN DISK, COMPRESSOR, HP 1ST & 2ND STAGE UL24024 DN62973

30687 SHAFT, COMPRESSOR ROTOR REAR HP UL18114 DN63595

SPARE DISK, HP TURBINE UL10323 CQDY6374 NONE

UNKNOWN DISK, LPT STAGE 2 UL11508 SEBH5142

31559 DISK, COMPRESSOR, HP 1ST & 2ND STAGE UL11678 DN66262 NONE

31559 SHAFT, COMPRESSOR ROTOR REAR HP UL18114 MW0002261

31559 DISK, HP TURBINE UL27681 LDRCZ13902

30946 DISK, COMPRESSOR, HP 1ST & 2ND STAGE UL11678 DN66611 NONE

30946 SHAFT, COMPRESSOR ROTOR REAR HP UL18114 DN66474 NONE

30946 DISK, HP TURBINE UL27681 LDRCZ13171 NONE

UNKNOWN DISK, LPT STAGE 2 UL11508 SEBH5019

UNKNOWN SHAFT, COMPRESSOR FRONT IP UL16758 DN35650

UNKNOWN DISK, COMPRESSOR, HP 1ST & 2ND STAGE UL11678 DN35709

UNKNOWN DISK, LPT STAGE 2 UL11508 SEBH5060

UNKNOWN DISK, LPT STAGE 2 UL29029 SETM735

UNKNOWN DISK, HP TURBINE UL10323 CQDY6065 NONE

UNKNOWN DISK, COMPRESSOR, HP 1ST & 2ND STAGE UL11678 DN40347

UNKNOWN DISK, COMPRESSOR, HP 1ST & 2ND STAGE UL24024 DN39140

UNKNOWN DISK, HP TURBINE UL27681 LDRCZ10691

UNKNOWN DISK, HP TURBINE UL27681 LDRCZ10138

SHAFT, COMPRESSOR ROTOR REAR HP UL18114 DN59531

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

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COMPLIANCE TIME

NONE 2079

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31/08/2015

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COMPLIANCE TIME

100 FC, OR BY

31/08/2015

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COMPLIANCE TIME

100 FC, OR BY

31/08/2015

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COMPLIANCE TIME

100 FC, OR BY

31/08/2015

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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

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Appendix 4 - Page 28

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R

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Appendix 4 - Page 29

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For 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

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Appendix 5 - Page 1 of 5

May 22/15

R Aug.28/15
The 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

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D. 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

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Appendix 5 - Page 3

May 22/15

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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 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

R Aug.28/15
The 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

R Aug.28/15
Revised 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

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Appendix 6 - Page 1 of 13

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(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

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Appendix 6 - Page 2

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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

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

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Appendix 6 - Page 3

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(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

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Appendix 6 - Page 4

May 22/15

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(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

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Appendix 6 - Page 5

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D. 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

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Appendix 6 - Page 6

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F. 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

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LP (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

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Appendix 6 - Page 8

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6. 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

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(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.

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(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.

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(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.

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(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).

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