This document transmits Revision 1 of Non-Modification Service Bulletin

TAY-72-A1821.

NOTE: If the Initial Issue of this Non-Modification Service Bulletin is already

incorporated, no further Operator action is required with this Revision.

Document History

Non-Modification Service Bulletin Revision Status

Initial Issue Jan. 6/15

Non-Modification Service Bulletin Revision 1

Remove Incorporate Reason for change

All Pages of the

Non-Modification

Service Bulletin.

Pages 1 to 16 of the

Non-Modification

Service Bulletin.

To clarify the

requirements for the

re-calculation of the

consumed cyclic life of

the High Pressure (HP)

turbine stage 1 disc

with the P/N JR32013.

Printed in Great Britain

Mar.26/15

TAY SERIES PROPULSION SYSTEM SERVICE BULLETIN

ALERT TAY−72−A1821

Transmittal - Page 1 of 1

ALERT

1. Planning Information

A. Effectivity

(1) Fokker 100.

Tay 650-15 and Tay 650-15/10 Engines.

All engines which do not have the Service Bulletin TAY-72-1241 standard

incorporated.

Modules M04300AA and M04301AA (Combustion and HP Turbine Module Modules).

(2) Boeing 727.

Tay 651-54 Engines.

All engines which do not have the Service Bulletin TAY-72-1241 standard

incorporated.

Modules M04300AA and M04301AA (Combustion and HP Turbine Module Modules).

B. Concurrent Requirements

None.

C. Reason

The safe cyclic lives of critical parts of the High Pressure (HP) turbine

stage 1 disc have been reviewed, which has resulted in the identification of a

potentially reduced cyclic life limit for the HP turbine stage 1 discs with

the P/N JR32013 (Vapour blasted HP turbine stage 1 disc of pre Service

Bulletin TAY-72-1241 standard).

Operation of critical parts beyond these reduced cyclic life limits could lead

to part failure and consequent release of high-energy debris, possibly

resulting in damage to the airplane and/or injury to the occupants.

Review of operation and overhaul data indicates that it is unlikely that this

standard of disc is still in service, since it has been superseded by a newer

standard of disc in 1991. However, to finally ensure no parts are left in

service and for the reasons described above, this Non-Modification Service

Bulletin instructs replacement of those discs that have already exceeded the

reduced cyclic life limit and replacement of all other affected discs before

the reduced life limit is exceeded.

ENGINE - HIGH PRESSURE (HP) TURBINE ROTOR - HP TURBINE STAGE 1 DISC - CHECK FOR AND

REMOVAL OF VAPOUR BLASTED DISCS - NON-MODIFICATION SERVICE BULLETIN

Printed in Great Britain

TAY−72−A1821

Page 1 of 16

Jan. 6/15

Mar.26/15 Revision 1
Revision 1 of this Non-Modification Service Bulletin has been issued to

clarify the requirements for the re-calculation of the consumed cyclic life of

the High Pressure (HP) turbine stage 1 disc with the P/N JR32013.

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R D. Description

R The safety intent of this Non-Modification Service Bulletin is SAFETY INTENT:

to communicate the new cyclic life limit of the HP turbine

stage 1 disc with the P/N JR32013 (Vapour HP turbine stage 1

disc of pre Service Bulletin TAY-72-1241 standard) given in

paragraph 1.E.Compliance of this Non-Modification Service

Bulletin. Depending on the service history of the HP turbine

stage 1 disc with the P/N JR32013 a re-calculation of the

consumed cyclic life is necessary. Where the new cyclic life

limit is exceeded, replacement of the HP turbine stage 1 disc

is required within 100 flight cycles after receipt of this

Non-Modification Service Bulletin.

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This Non-Modification Service Bulletin is divided into two PARTs as follows:

 - Verification of the engine log book to determine if the High PART A

Pressure (HP) turbine stage 1 disc with the P/N JR32013 is

installed.

NOTE: The Accomplishment Instruction for PART A of this

Non-Modification Service Bulletin is divided into two

INSTRUCTIONs as follows:

 Applicable for engines "In Service". INSTRUCTION I -

 Applicable for engines "At Overhaul/Shop INSTRUCTION II -

Visit".

 - Instruction for the removal of the High Pressure (HP) turbine stage PART B

1 discs with the P/N JR32013 from service.

NOTE: The Accomplishment Instruction of PART B of this

Non-Modification Service Bulletin is applicable for engines

"At Overhaul/Shop Visit" only.

Printed in Great Britain

TAY−72−A1821

Page 2 of 16

Jan. 6/15

Mar.26/15 Revision 1
E. Compliance

PART A

ALERT

PART A of this Non-Modification Service Bulletin must be accomplished on all

engines within 30 days after receipt of this Non-Modification Service

Bulletin.

PART B

ALERT

If it is found in PART A of this Non-Modification Service Bulletin that a HP

turbine stage 1 disc with the P/N JR32013 is installed, PART B of this

Non-Modification Service Bulletin must be accomplished on all engines before

the accumulated cyclic life exceeds the removal live given in the table below

or within 100 flight cycles after receipt of this Non-Modification Service

Bulletin, whichever comes later.

FLIGHT PLAN CYCLIC LIFE LIMIT

Tay 650-15

engine flight

plan A

18900 flight cycles

Tay 650-15

engine flight

plan B

15500 flight cycles

Tay 650-15

engine flight

plan C

11500 flight cycles

Tay 650-15

engine flight

plan D

9300 flight cycles

Tay 651-54

engine

operation

10873 flight cycles

F. Approval

The technical content of this document is approved under the authority of EASA

Design Organisation Approval No. EASA.21J.065.

Printed in Great Britain

TAY−72−A1821

Page 3 of 16

Jan. 6/15

Mar.26/15 Revision 1
G. Manpower

Estimated Man-hours:

PART A

(1) In Service

30 minutes.

(2) At Overhaul/Shop Visit

Applicable (Hours not affected).

PART B

(1) In Service

Not applicable.

(2) At Overhaul/Shop Visit

Applicable (Hours not affected).

H. Material Price and Availability

Not applicable.

I. Tooling Price and Availability

New tools are not required.

J. Industry Support Information

None.

K. Weight and Balance

(1) Weight Change

None.

(2) Moment Arm

No effect.

(3) Datum

ES2540 (PPS100).

Printed in Great Britain

TAY−72−A1821

Page 4 of 16

Jan. 6/15

Mar.26/15 Revision 1
L. Electrical Load Data

The aircraft electrical load is not affected by this Non-Modification Service

Bulletin.

M. Software Accomplishment Summary

Not applicable.

N. References

For Tay 650-15 and Tay 650-15/10 Engines:

(1) Aircraft Maintenance Manual, Chapter 71-00-00.

(2) Engine Manual - E-TAY-3RR, Chapters 72-00-41 and 72-41-30.

(3) Power Plant Build-up Manual - R-R TAY 650-15 - TAY 650-15/10, Chapters

71-00-01, 71-00-02, 71-00-03 and 71-00-04.

(4) Service Bulletin TAY-72-1241

ENGINE - H.P. TURBINE ROTOR DISCS AND BLADES - H.P.1 and H.P.2 TURBINE

DISCS WITH SHOT-PEENED SURFACES

R (5) Time Limits Manual - T-TAY-3RR, Chapter 05-10-01.

For Tay 651-54 Engines:

(1) Aircraft Maintenance Manual, Chapter 71-00-01.

(2) Engine Manual - E-TAY-5RR, Chapters 72-00-41 and 72-41-30.

(3) Service Bulletin TAY-72-1241

ENGINE - H.P. TURBINE ROTOR DISCS AND BLADES - H.P.1 and H.P.2 TURBINE

DISCS WITH SHOT-PEENED SURFACES

R (4) Time Limits Manual - T-TAY-5RR, Chapter 05-10-01.

O. Other Publications Affected

None.

P. Interchangeability of Parts

Not affected.

Printed in Great Britain

TAY−72−A1821

Page 5 of 16

Jan. 6/15

Mar.26/15 Revision 1
2. Material Information

A. Parts to be Replaced

IPC

Fig/Item

No.

New

Part

No.

Unit Price

(US

Dollars)

Qty

Per

Eng.

Key Word Old

Part

No.

Instructions/

Dispositions

PART B

72-41-32

 JR33838 $ 123370.00 R 1 High Pressure (HP) 02-010

turbine stage 1

disc

JR32013 (1)(2)

B. Expendable Parts

Refer to the related Manual tasks given in the Accomplishment Instruction of

this Non-Modification Service Bulletin.

C. Instruction/Disposition Codes

(1) It is necessary to replace the used part with a replacement part during

the accomplishment of PART B of this Non-Modification Service Bulletin.

(2) The High Pressure (HP) turbine stage 1 disc, P/N JR32013 can be replaced

by the High Pressure (HP) turbine stage 1 disc, P/N JR33838 by

incorporation of PART 1 of Service Bulletin TAY-72-1241.

Printed in Great Britain

TAY−72−A1821

Page 6 of 16

Jan. 6/15

Mar.26/15 Revision 1
3. Accomplishment Instruction

INSTRUCTION I - APPLICABLE FOR ENGINES "IN SERVICE"

 - Verification of the engine log book to determine if the High PART A

Pressure (HP) turbine stage 1 disc with the P/N JR32013 is

installed.

A. Verify the engine log book to determine if a High Pressure (HP) turbine stage

1 disc (72-41-32, 02-010), P/N JR32013 (Vapour blasted HP turbine stage 1 disc

of pre Service Bulletin TAY-72-1241 standard) is installed on the engine

(1) Tick the applicable box in the Accomplishment Form on page 16 to record

that a HP turbine stage 1 disc (72-41-32, 02-010), P/N JR32013 is

installed on the engine or not

(a) If no HP turbine stage 1 disc (72-41-32, 02-010), P/N JR32013 is

installed on the engine continue with step D.

CAUTION: SEVERAL OF THE GROUP A PARTS ARE COMMON TO DIFFERENT MARKS OF

THE TAY ENGINE. THE CHANGE OF THE TURBINE STAGE 1 DISC

(72-41-32, 02-010) BETWEEN THE 650-15 AND 651-54 MARKS OF THE

TAY IS PERMISSIBLE. HOWEVER, THE REMAINING SERVICE LIFE OF THAT

PART WILL BE THE LIFE RELATED WITH THE LOWEST DECLARED LIFE OF

THAT PART ON EITHER ENGINE MARK. IT IS THE OPERATORS

RESPONSIBILITY TO MAKE SURE THAT THE LIFE REMAINING, AS

RECORDED IN THE ENGINE LOG BOOK, IS THAT RELATED WITH THE

LOWEST LIFE DECLARED FOR EITHER ENGINE MARK.

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(b) If a HP turbine stage 1 disc (72-41-32, 02-010), P/N JR32013 is

installed on the engine, determine if the HP turbine stage 1 disc

(72-41-32, 02-010), P/N JR32013 has been operated on a different

engine mark (Tay 650-15 or Tay 651-54) and/or a different flight

plan (Tay 650-15)

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R

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[1] If a HP turbine stage 1 disc (72-41-32, 02-010), P/N JR32013

has not previously been operated on a different engine mark

(Tay 650-15 or Tay 651-54) and has not previously been operated

to flight plans that are different to the currently operated

flight plan (Tay 650-15), the consumed cyclic life must be

tracked against the new cyclic life limit as given in paragraph

1.E.Compliance of this Non-Modification Service Bulletin.

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Printed in Great Britain

TAY−72−A1821

Page 7 of 16

Jan. 6/15

Mar.26/15 Revision 1
[2] If a HP turbine stage 1 disc (72-41-32, 02-010), P/N JR32013

has not previously been operated on a different engine mark

(Tay 650-15 or Tay 651-54) but has previously been operated to

flight plans that are different to the currently operated

flight plan (Tay 650-15), the consumed cyclic life must be

re-calculated using the pro-rata calculation given in the Time

Limits Manual (Refer to the Time Limits Manual, Chapter

05-10-01, Task 05-10-01-800-000). Use the new cyclic life limit

given in paragraph 1.E.Compliance of this Non-Modification

Service Bulletin.

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[3] If a HP turbine stage 1 disc (72-41-32, 02-010), P/N JR32013

has previously been operated on a different engine mark (Tay

650-15 or Tay 651-54) and has not previously been operated to

flight plans that are different to the currently operated

flight plan (Tay 650-15), the consumed cyclic life must be

tracked against the new cyclic life limit as given in paragraph

1.E.Compliance of this Non-Modification Service Bulletin using

the consideration of the lowest declared cyclic life limit at

engine mark changes given in the Time Limits Manual (Refer to

the Time Limits Manual, Chapter 05-10-01, Task

05-10-01-800-000).

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NOTE: Examples for the consideration of the lowest declared

cyclic life limit at engine mark changes are given in

the Tay 650-15 Time Limits Manual (Refer to the Time

Limits Manual, Chapter 05-10-01, Task 05-10-01-800-000).

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Printed in Great Britain

TAY−72−A1821

Page 8 of 16

Jan. 6/15

Mar.26/15 Revision 1
[4] If a HP turbine stage 1 disc (72-41-32, 02-010), P/N JR32013

has previously been operated on a different engine mark and has

previously been operated to flight plans that are different to

the currently operated flight plan it must be differentiated

between the current engine applications:

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[a] The current application is a Tay 650-15 or Tay 650-15/10

Engine:

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If a HP turbine stage 1 disc (72-41-32, 02-010), P/N

JR32013 has been operated on a different engine mark (Tay

651-54) and has previously been operated to flight plans

that are different to the currently operated flight plan

(Tay 650-15), the consumed cyclic life must be

re-calculated using the combination of the consideration

of the lowest declared cyclic life limit at engine mark

changes and the pro-rata calculation given in the Time

Limits Manual (Refer to the Time Limits Manual, Chapter

05-10-01, Task 05-10-01-800-000). Use the new cyclic life

limit given in paragraph 1.E.Compliance of this

Non-Modification Service Bulletin.

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NOTE: Examples for the combination of the consideration

of the lowest declared cyclic life limit at engine

mark changes and the pro-rata calculation are given

in the Tay 650-15 Time Limits Manual (Refer to the

Time Limits Manual, Chapter 05-10-01, Task

05-10-01-800-000).

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NOTE: Depending on how often the flight plan of a HP

turbine stage 1 disc has been changed, the achieved

cyclic life may have to be calculated more than

once.

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R

Printed in Great Britain

TAY−72−A1821

Page 9 of 16

Jan. 6/15

Mar.26/15 Revision 1
R [b] The current application is a Tay 651-54 Engine:

If a HP turbine stage 1 disc (72-41-32, 02-010), P/N

JR32013 has been operated on a different engine mark (Tay

650-15) and has previously been operated to various flight

plans of the different engine mark (Tay 650-15), the

consumed cyclic life must be re-calculated using the

combination of the consideration of the lowest declared

cyclic life limit at engine mark changes and the pro-rata

calculation given in the Time Limits Manual (Refer to the

Time Limits Manual, Chapter 05-10-01, Task

05-10-01-800-000). Use the new cyclic life limit given in

paragraph 1.E.Compliance of this Non-Modification Service

Bulletin.

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NOTE: Examples for the combination of the consideration

of the lowest declared cyclic life limit at engine

mark changes and the pro-rata calculation are given

in the Tay 650-15 Time Limits Manual (Refer to the

Time Limits Manual, Chapter 05-10-01, Task

05-10-01-800-000).

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NOTE: Depending on how often the flight plan of a HP

turbine stage 1 disc has been changed, the achieved

cyclic life may have to be calculated more than

once.

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(c) If the new cyclic life limit of the HP turbine stage 1 disc

(72-41-32, 02-010), P/N JR32013 has not been exceeded, record the

serial number, the hours and the new calculated cycles in the

Accomplishment Form on page 16, continue with Step D.

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(d) If the new cyclic life limit of the HP turbine stage 1 disc

(72-41-32, 02-010), P/N JR32013 has been exceeded, record the serial

number, the hours and the new calculated cycles in the

Accomplishment Form on page 16, continue with step B.

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B. Replace the engine within 100 flight cycles after receipt of this

Non-Modification Service Bulletin

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(1) For Tay 650-15 and Tay 650-15/10 Engines:

Refer to the Aircraft Maintenance Manual, Chapter 71-00-00 and to the

Power Plant Build-up Manual, Chapters 71-00-01, 71-00-02, 71-00-03 and

71-00-04.

(2) For Tay 651-54 Engines:

Refer to the Aircraft Maintenance Manual, Chapter 71-00-01.

Printed in Great Britain

TAY−72−A1821

Page 10 of 16

Jan. 6/15

Mar.26/15 Revision 1
(3) Send the removed engine to a Rolls-Royce approved overhaul facility for

replacement of the HP turbine stage 1 disc (72-41-32, 02-010), P/N

JR32013 in accordance with PART B of this Non-Modification Service

Bulletin.

(4) Continue with step C.

C. Make sure that the work area is clean and clear of tools, equipment and other

unwanted materials.

D. Complete the Accomplishment Form on page 16 and send it to Rolls-Royce

Deutschland, Service Engineering.

R

E. A record of accomplishment is required. Rolls-Royce Deutschland suggests to

put an entry into the engine log book.

Printed in Great Britain

TAY−72−A1821

Page 11 of 16

Jan. 6/15

Mar.26/15 Revision 1
INSTRUCTION II - APPLICABLE FOR ENGINES "AT OVERHAUL/SHOP VISIT"

 - Verification of the engine log book to determine if the High PART A

Pressure (HP) turbine stage 1 disc with the P/N JR32013 is

installed.

F. Verify the engine log book to determine if a High Pressure (HP) turbine stage

1 disc (72-41-32, 02-010), P/N JR32013 (Vapour blasted HP turbine stage 1 disc

of pre Service Bulletin TAY-72-1241 standard) is installed on the engine

(1) Tick the applicable box in the Accomplishment Form on page 16 to record

that a HP turbine stage 1 disc (72-41-32, 02-010), P/N JR32013 is

installed on the engine or not

(a) If no HP turbine stage 1 disc (72-41-32, 02-010), P/N JR32013 is

installed on the engine continue with step H.

CAUTION: SEVERAL OF THE GROUP A PARTS ARE COMMON TO DIFFERENT MARKS OF

THE TAY ENGINE. THE CHANGE OF THE HP TURBINE STAGE 1 DISC

(72-41-32, 02-010) BETWEEN THE 650-15 AND 651-54 MARKS OF THE

TAY IS PERMISSIBLE, HOWEVER, THE REMAINING SERVICE LIFE OF THAT

PART WILL BE THE LIFE RELATED WITH THE LOWEST DECLARED LIFE OF

THAT PART ON EITHER ENGINE MARK. IT IS THE REPAIR FACILITIES

RESPONSIBILITY TO MAKE SURE THAT THE LIFE REMAINING, AS

RECORDED IN THE ENGINE LOG BOOK, IS THAT RELATED WITH THE

LOWEST LIFE DECLARED FOR EITHER ENGINE MARK.

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(b) If a HP turbine stage 1 disc (72-41-32, 02-010), P/N JR32013 is

installed on the engine, determine if the HP turbine stage 1 disc

(72-41-32, 02-010), P/N JR32013 has been operated on a different

engine mark (Tay 650-15 or Tay 651-54) and/or a different flight

plan (Tay 650-15)

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R

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[1] If a HP turbine stage 1 disc (72-41-32, 02-010), P/N JR32013

has not previously been operated on a different engine mark

(Tay 650-15 or Tay 651-54) and has not previously been operated

to flight plans that are different to the currently operated

flight plan (Tay 650-15), the consumed cyclic life must be

tracked against the new cyclic life limit as given in paragraph

1.E.Compliance of this Non-Modification Service Bulletin.

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[2] If a HP turbine stage 1 disc (72-41-32, 02-010), P/N JR32013

has not previously been operated on a different engine mark

(Tay 650-15 or Tay 651-54) but has previously been operated to

flight plans that are different to the currently operated

flight plan (Tay 650-15), the consumed cyclic life must be

re-calculated using the pro-rata calculation given in the Time

Limits Manual (Refer to the Time Limits Manual, Chapter

05-10-01, Task 05-10-01-800-000). Use the new cyclic life limit

given in paragraph 1.E.Compliance of this Non-Modification

Service Bulletin.

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Printed in Great Britain

TAY−72−A1821

Page 12 of 16

Jan. 6/15

Mar.26/15 Revision 1
[3] If a HP turbine stage 1 disc (72-41-32, 02-010), P/N JR32013

has previously been operated on a different engine mark (Tay

650-15 or Tay 651-54) and has not previously been operated to

flight plans that are different to the currently operated

flight plan (Tay 650-15), the consumed cyclic life must be

tracked against the new cyclic life limit as given in paragraph

1.E.Compliance of this Non-Modification Service Bulletin using

the consideration of the lowest declared cyclic life limit at

engine mark changes given in the Time Limits Manual (Refer to

the Time Limits Manual, Chapter 05-10-01, Task

05-10-01-800-000).

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NOTE: Examples for the consideration of the lowest declared

cyclic life limit at engine mark changes are given in

the Tay 650-15 Time Limits Manual (Refer to the Time

Limits Manual, Chapter 05-10-01, Task 05-10-01-800-000).

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[4] If a HP turbine stage 1 disc (72-41-32, 02-010), P/N JR32013

has previously been operated on a different engine mark and has

previously been operated to flight plans that are different to

the currently operated flight plan it must be differentiated

between the current engine applications:

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[a] The current application is a Tay 650-15 or Tay 650-15/10

Engine:

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R

If a HP turbine stage 1 disc (72-41-32, 02-010), P/N

JR32013 has been operated on a different engine mark (Tay

651-54) and has previously been operated to flight plans

that are different to the currently operated flight plan

(Tay 650-15), the consumed cyclic life must be

re-calculated using the combination of the consideration

of the lowest declared cyclic life limit at engine mark

changes and the pro-rata calculation given in the Time

Limits Manual (Refer to the Time Limits Manual, Chapter

05-10-01, Task 05-10-01-800-000). Use the new cyclic life

limit given in paragraph 1.E.Compliance of this

Non-Modification Service Bulletin.

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NOTE: Examples for the combination of the lowest declared

cyclic life limit at engine mark changes and the

pro-rata calculation are given in the Tay 650-15

Time Limits Manual (Refer to the Time Limits

Manual, Chapter 05-10-01, Task 05-10-01-800-000).

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NOTE: Depending on how often the flight plan of a HP

turbine stage 1 disc has been changed, the achieved

cyclic life may have to be calculated more than

once.

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Printed in Great Britain

TAY−72−A1821

Page 13 of 16

Jan. 6/15

Mar.26/15 Revision 1
R [b] If the current application is a Tay 651-54 Engine:

If a HP turbine stage 1 disc (72-41-32, 02-010), P/N

JR32013 has been operated on a different engine mark (Tay

650-15) and has previously been operated to various flight

plans of the different engine mark (Tay 650-15), the

consumed cyclic life must be re-calculated using the

combination of the consideration of the lowest declared

cyclic life limit at engine mark changes and the pro-rata

calculation given in the Time Limits Manual (Refer to the

Time Limits Manual, Chapter 05-10-01, Task

05-10-01-800-000). Use the new cyclic life limit given in

paragraph 1.E.Compliance of this Non-Modification Service

Bulletin.

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NOTE: Examples for the combination of the lowest declared

cyclic life limit at engine mark changes and the

pro-rata calculation are given in the Tay 650-15

Time Limits Manual (Refer to the Time Limits

Manual, Chapter 05-10-01, Task 05-10-01-800-000).

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NOTE: Depending on how often the flight plan of a HP

turbine stage 1 disc has been changed, the achieved

cyclic life may have to be calculated more than

once.

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(c) If the new cyclic life limit of the HP turbine stage 1 disc

(72-41-32, 02-010), P/N JR32013 has not been exceeded, record the

serial number, the hours and the new calculated cycles in the

Accomplishment Form on page 16, continue with Step H.

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(d) If the re-calculated cyclic life of the HP turbine stage 1 disc

(72-41-32, 02-010), P/N JR32013 does not meet the target built life,

record the serial number, the hours and the new calculated cycles in

the Accomplishment Form on page 16, continue with step G.

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(e) If the new cyclic life limit of the HP turbine stage 1 disc

(72-41-32, 02-010), P/N JR32013 has been exceeded, record the serial

number, the hours and the new calculated cycles in the

Accomplishment Form on page 16, continue with step G.

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G. Replace the HP turbine stage 1 disc (72-41-32, 02-010), P/N JR32013 in

accordance with PART B of this Non-Modification Service Bulletin.

H. Complete the Accomplishment Form on page 16 and send it to Rolls-Royce

Deutschland, Service Engineering.

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I. A record of accomplishment is required. Rolls-Royce Deutschland suggests to

put an entry into the engine log book.

Printed in Great Britain

TAY−72−A1821

Page 14 of 16

Jan. 6/15

Mar.26/15 Revision 1
APPLICABLE FOR ENGINES "AT OVERHAUL/SHOP VISIT"

 - Instruction for removal of the High Pressure (HP) turbine stage 1 PART B

discs with the P/N JR32013 from service.

J. General

(1) Obey all the WARNINGS and CAUTIONS in the procedures that are referred

to.

(2) Consumable Materials

(a) Refer to the related Manual tasks given in this instruction.

(3) Tools and Equipment

(a) Refer to the related Manual tasks given in this instruction.

K. Remove the combustion and High Pressure (HP) turbine module from the engine

and disassemble (Refer to the Engine Manual, Chapter 72-00-41, TASK

72-00-41-000-000).

L. Disassemble the HP turbine rotor discs and shaft (Refer to the Engine Manual,

Chapter 72-41-30, TASK 72-41-30-000-000)

(1) Remove the used HP turbine stage 1 disc (72-41-32, 02-010), P/N JR32013

in accordance with PART 1 of Service Bulletin TAY-72-1241.

M. Assemble the HP turbine rotor discs and shaft (Refer to the Engine Manual,

Chapter 72-41-30, TASK 72-41-30-400-000)

(1) Install a replacement HP turbine stage 1 disc (72-41-32, 02-010), P/N

JR33838 in accordance with PART 1 of Service Bulletin TAY-72-1241.

N. Assemble the combustion and HP turbine module and install on the engine (Refer

to the Engine Manual, Chapter 72-00-41, TASK 72-00-41-400-000).

O. Make sure that the work area is clean and clear of tools, equipment and other

unwanted materials.

P. A record of accomplishment is required. Rolls-Royce Deutschland suggests to

put an entry into the engine log book.

Printed in Great Britain

TAY−72−A1821

Page 15 of 16

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Mar.26/15 Revision 1
R

R Accomplishment Form

Printed in Great Britain

TAY−72−A1821

Page 16 of 16

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Mar.26/15 Revision 1
 

 SERVICE BULLETIN FEEDBACK FORM

Mar.26/15

Revision 1

© Rolls-Royce Deutschland Ltd & Co KG

TAY-72-A1821

Page 1 of 1

Printed in Great Britain

Please use this form to give feedback on the quality of this Service Bulletin. The input you provide will be used to 

analyse areas of improvement and to take action to further improve the quality of our Service Bulletins.

We thank you for the time you spent in completing this form.

Please rate on a scale of 1 to 5, with 5 being the highest score:

- General quality rating of this Service Bulletin  1  2  3  4  5

- Quality rating of the Accomplishment Instructions  1  2  3  4  5

- Quality rating of the Illustration  1  2  3  4  5

- Is this Service Bulletin easy to understand ?  Yes  No 

If you have had difficulties to perform this Service Bulletin please quote below the area(s) and give a short 

description of the issue:

Operator: Overhaul Site:

Name/Title: Date:

Please send the completed Service Bulletin Feedback Form to Rolls-Royce Deutschland, Service Bulletin Group.

Email: mailto:RRD.SERVICE.BULLETINS@ROLLS-ROYCE.COM 

Planning Information

Section:

Material Information

Section:

Accomplishment Instruction

Section:

  1.A.  1.I.  2.A.  General

  1.B.  1.J.  2.B.  Get Access

  1.C.  1.K.  2.C.  Removal/Installation

  1.D.  1.L.  2.D.  Inspection

  1.E.  1.M.  2.E.  Test

  1.F.  1.N.  2.F.  Close the Access

  1.G.  1.O.  Log Book Entry

  1.H  1.P. 

Explanatory notes: