PRATT & WHITNEY CANADA

SERVICE BULLETIN
P&WC S.B. No. 13002R20

BULLETIN INDEX LOCATOR

TURBOPROP ENGINE
ROTOR COMPONENTS - SERVICE LIFE

MODEL APPLICATION
PT6A-52, PT6A-60A, PT6A-61, PT6A-62, PT6A-65AR, PT6A-65B, PT6A-65R

Compliance: Refer to Para. 1.E. in the Service Bulletin

Summary: 1. This service bulletin (SB) provides the service life limits for the rotor component
parts which are authorized for use in the above Pratt & Whitney Canada (P&WC)
Inc. engine models, as required by the Canadian Department of Transport
regulations.
2. Compliance with the Accomplishment Instructions in step 3 is necessary to
maintain conformity with the approval type design and the validity of the
airworthiness certification.
3. The Low Cycle Fatigue (LCF) counting process is described in detail, including
the formula to use, refer to the ‘‘Remaining Life’’ section, to calculate the total
accumulated cycles for the various rotor components.

Oct 02/1982 PT6A-72-13002

Revision No. 20: Nov 07/2023 Cover Sheet

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 WARNING - PROPRIETARY RIGHTS & EXPORT CONTROLS NOTICE

This bulletin contains proprietary information of Pratt & Whitney Canada Corp. (″P&WC″), which
P&WC provides in confidence and solely for the purposes of supporting engine certification and
providing applicable information regarding the proper use, maintenance, inspection, repair, servicing
and parts application of P&WC products and services, as directed therein. Neither this bulletin nor
any information in it may be disclosed to others, or used for any other purpose, including, without
limitation, to design, create, develop, reproduce, manufacture or derive any design, part, product,
material, process, modification, configuration change or repair, or obtain FAA or other government
approval to do so. Possession and use of this bulletin is also subject to the restrictions set out in
P&WC’s Technical Data Agreement (a copy of which may be obtained by contacting P&WC Technical
Publications). The contents of this bulletin may be subject to export control laws. Unauthorized export
or re-export of the bulletin, or parts thereof, is prohibited. By accepting and possessing this bulletin,
you agree to be bound by the foregoing terms.

If a Government agency or department intends to disclose any information, written notice should be
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 Pratt & Whitney Canada Corp.
1000, Marie-Victorin
Longueuil, Québec, Canada J4G 1A1
Tél. 450-677-9411

07 November 2023

P&WC S.B. No. 13002R20

REVISION TRANSMITTAL SHEET

TURBOPROP ENGINE MODEL PT6A

SUBJECT: Pratt & Whitney Canada Service Bulletin No. PT6A-72-13002, Rev. No. 20, dated Nov
07/2023 (P&WC S.B. No. 13002R20) ROTOR COMPONENTS - SERVICE LIFE

Replace your existing copy of this service bulletin with the attached revised bulletin. Destroy the
superseded copy.

Please retain this Revision Transmittal Sheet with the revised bulletin.

SUMMARY: This service bulletin is revised to:

v add PT6A-62 BS1320.

EFFECT OF REVISION ON PRIOR ACCOMPLISHMENT:

None.

NOTE: A black bar in the left margin indicates a change in that line of text or figure.

REVISION HISTORY:
Original Issue: Oct 02/1982 Revision No. 14: Aug 02/2007
Revision No. 1: Mar 24/1983 Revision No. 15: Jan 03/2008
Revision No. 2: Dec 23/1983 Revision No. 16: Mar 04/2010
Revision No. 3: Oct 25/1984 Revision No. 17: Dec 08/2019
Revision No. 4: Feb 28/1985 Revision No. 18: Jun 24/2020
Revision No. 5: Oct 02/1985 Revision No. 19: Aug 02/2021
Revision No. 6: Oct 14/1986 Revision No. 20: Nov 07/2023
Revision No. 7: Oct 26/1988
Revision No. 8: Nov 15/1989
Revision No. 9: Apr 16/1991
Revision No. 10: TBA
Revision No. 11: Sep 22/1993
Revision No. 12: May 11/1999
Revision No. 13: Dec 23/1999

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 PRATT & WHITNEY CANADA

SERVICE BULLETIN
P&WC S.B. No. 13002R20
TURBOPROP ENGINE
ROTOR COMPONENTS - SERVICE LIFE

1. Planning Information

A. Effectivity
PT6A-52, PT6A-60A, PT6A-61, PT6A-62, PT6A-65AR, PT6A-65B and PT6A-65R
Engines
B. Concurrent Requirements

None.
C. Reason

(1) To provide initial rotor components service life in accordance with D.O.T. regulation.

(2) To provide information covering method of marking.

D. Description

(1) Engine rotating parts listed under Paragraph 3.D. and 3.E. are subject to LCF due
to cyclic operation of the engine. As a result, these parts must be replaced when
the cycle limit is reached.

(2) Operators must record all flights, starts and accumulated total cycles (which must
be calculated using the formula Ref. 3.H) in the applicable document for each
component (i.e. logbook, LCF component card, etc.).

(3) The following is additional information for the Accumulated Total Cycle calculation:

v A start is defined as an engine start followed by one or more flights.

v Aircraft operation often includes abbreviated engine cycles. The definition of an
abbreviated cycle is: idle - takeoff - flight - landing - idle. A normal or full cycle
includes the foregoing plus an engine start and shutdown (i.e. abbreviated cycles
are equivalent to the number of flights minus the number of starts). The limits
specified in Paragraph 3. are in terms of full cycles. Accumulated abbreviated
cycles are summated in terms of full cycles by means of a formula and tabulated
factors.
v A full cycle is defined as an engine start followed by one flight then shutdown.
v An abbreviated cycle is less severe than a full cycle. To benefit from this, an
Abbreviated Cycle Factor (ACF) is listed in the le below, and used in the
formula which determines accumulated total cycles;
v A Flight Count Factor (FCF) is a multiplying factor that can be used to credit or
debit life to the components listed in the Life Service to reflect the aircraft
application of the engine. This factor can also be specific to an operator that
diverges from the standards as missions.

P&WC No. 27832, 27906, 28910, 31338, 31368, 33304, 70070B, 80245, 80305, 81921A, 83278,
85794, 96298A, 96181A, D8527C, D8527D, D2736A, D5439D, EC-0008320, CO-0006793,
CO-0012219
Oct 02/1982 P&WC Proprietary Information. Subject to the restrictions on the back of the locator PT6A-72-13002
Revision No. 20: Nov 07/2023 © 1982 Pratt & Whitney Canada Corp. Page 1 of 11
PRINTED IN CANADA

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 PRATT & WHITNEY CANADA

SERVICE BULLETIN
P&WC S.B. No. 13002R20
TURBOPROP ENGINE
ROTOR COMPONENTS - SERVICE LIFE

1. Planning Information (Cont’d)

v When abbreviated cycles are not recorded, each flight is considered to have been
preceded by one start, i.e., each flight is equivalent to a full cycle.

(4) The LCF life limits listed in the below are incorporated in the Type Approval as
issued by Transport Canada. Transport Canada must approve changes to rotor
component cyclic lives.

(5) The specified cyclic lives apply to engines, modules and components that contain
parts listed in the approved parts list, as shown in the applicable Illustrated Parts
Catalog (IPC) and SB. Operators requesting approval to incorporate parts not listed
in the applicable IPC and SBs will be required to substantiate the cyclic lives of
these parts to their local Airworthiness Authority.

(6) Operators having missions which include many touch-and-go flights, or a frequency
of scheduled in-flight shutdowns (such as used within training missions) or which
include more than 10 flights per hour, must submit their mission profiles to P&WC Inc.
for life cycle analysis.

(7) Operators making scheduled or frequent use of the engine’s highest allowable rated
power must submit their mission profile(s) to P&WC for analysis.

(8) The same component (e.g. disk, Hub, Impeller, etc.) may be installed in different
models, providing the part number is authorized to be installed in the specific
engine models (Ref. applicable SB). Operators transferring rotating components
between engine models governed by different SBs must adhere to the lower of the
LCF life limits published in the applicable SBs.

NOTE: 1. This applies to all PT6A engines and exclude all ST6 (industrial and
marine) engines.

NOTE: 2. It is not permitted to use parts which were installed on ST6 engines for
PT6 engines.

E. Compliance

The service lives quoted in the Accomplishment Instructions are incorporated by

reference in the type approval as issued by the Canadian Department of Transport.
Compliance with these instructions is therefore necessary to maintain conformity with the
approval type design and the validity of the airworthiness certification.

Oct 02/1982 P&WC Proprietary Information. Subject to the restrictions on the back of the locator PT6A-72-13002
Revision No. 20: Nov 07/2023 Page 2 of 11

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 PRATT & WHITNEY CANADA

SERVICE BULLETIN
P&WC S.B. No. 13002R20
TURBOPROP ENGINE
ROTOR COMPONENTS - SERVICE LIFE

1. Planning Information (Cont’d)

F. Approval

Transport Canada has reviewed and approved the technical contents of this Service
Bulletin.
NOTE: This SB is incorporated by reference in one or more Transport Canada, Aircraft
Engine Type Approvals and the service lives thereby constitute limits applicable
to the corresponding engines, modules and components which embody only
parts listed in the Transport Canada approved parts list, as promulgated in the
applicable IPC and SBs. Operators requiring approval for incorporation of
parts not listed will be required to substantiate to their local Airworthiness
Authority the applicability of the lives of the substitute parts and associated parts
and assemblies.
G. Manpower

Not applicable.
H. Weight and Balance

None.
I. Electrical Load Data

Not changed.
J. Software Accomplishment Summary

Not applicable.
K. References
Applicable PT6A Technical Manuals
P&WC S.B. No. 13188, 13229, 13240, 13257, 13269, 13434, 13441 and 13508
L. Publications Affected
Applicable PT6A Technical Manuals
M. Interchangeability and Intermixability of Parts

Not applicable.
2. Material Information

A. Industry Support Information

Not applicable.

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 PRATT & WHITNEY CANADA

SERVICE BULLETIN
P&WC S.B. No. 13002R20
TURBOPROP ENGINE
ROTOR COMPONENTS - SERVICE LIFE

2. Material Information (Cont’d)

B. Material - Cost and Availability

Not applicable.

C. Material Necessary for Each Engine

Not applicable.

D. Reidentified Parts

None.

E. Tooling - Price and Availability

Not applicable.

3. Accomplishment Instructions

A. Accumulated total cycles and all flights and starts must be recorded in the appropriate
engine log book.

B. Turbine disk assemblies removed for repair must be tagged, stating the total number of
flights, engine starts and/or the calculated total cycles, per Paragraph 3.D.

C. Components with accumulated total cycles or hours, as applicable, greater than the
limits shown in Tables 1, 2 or 3 or components not supported with proper
documentation, are to be removed from service.

NOTE: The practice of marking life limited parts with the accumulated cycle count is no
longer required. The accumulated cycle count previously marked on parts alone
is not considered sufficient supporting documentation.

D. The following limits shown in Table 1 in terms of number of cycles apply to, PT6A-60A,
PT6A-61 and PT6A-62 engines only.

TABLE 1, Rotor Components - Service Life Limits

Abbr’d Flight Life Limits

Detail Part Cycle Count No. Of
Description No. Engine Model Factor Factor Cycles
Hub, Compressor 3036211 PT6A-60A, -61 3 1 7,500
(1st Stage)
3036011 PT6A-60A, -61 3 1 10,000
3037311 PT6A-60A, -61 3 1 8,000

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 PRATT & WHITNEY CANADA

SERVICE BULLETIN
P&WC S.B. No. 13002R20
TURBOPROP ENGINE
ROTOR COMPONENTS - SERVICE LIFE

3. Accomplishment Instructions (Cont’d)

TABLE 1, Rotor Components - Service Life Limits (Cont’d)

Abbr’d Flight Life Limits

Detail Part Cycle Count No. Of
Description No. Engine Model Factor Factor Cycles
Rotor, Compressor 3033801 PT6A-60A, -61, -62 3 1 15,000
(1st Stage)
3035701 PT6A-60A, -61, -62 3 1 15,000
3037701 PT6A-60A, -61 3 1 15,000
3036001 PT6A-60A, -61 3 1 15,000
3038401 PT6A-60A, -61 3 1 15,000
3038801 PT6A-60A, -61, -62 3 1 15,000
3041401 PT6A-60A, -61, -62 3 1 15,000
3041301 PT6A-60A, -61, -62 3 1 15,000
3040781 PT6A-60A, -61 3 1 15,000
3041271 PT6A-60A, -61, -62 3 1 15,000
Disk, Compressor 3034312 PT6A-60A, -61, -62 3 1 20,000
(2nd Stage)
3134865 PT6A-60A, -61, -62 3 1 20,000
Disk, Compressor 3034313 PT6A-60A, -61, -62 3 1 20,000
(3rd Stage)
3134866 PT6A-60A, -61, -62 3 1 20,000
Impeller, Centrifugal 3017463 PT6A-60A, -61, -62 3 1 20,000
3035635 PT6A-60A, -61, -62 3 1 20,000
3036098 PT6A-60A, -61, -62 3 1 20,000
3036793 PT6A-60A, -61, -62 3 1 24,000

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 PRATT & WHITNEY CANADA

SERVICE BULLETIN
P&WC S.B. No. 13002R20
TURBOPROP ENGINE
ROTOR COMPONENTS - SERVICE LIFE

3. Accomplishment Instructions (Cont’d)

TABLE 1, Rotor Components - Service Life Limits (Cont’d)

Abbr’d Flight Life Limits

Detail Part Cycle Count No. Of
Description No. Engine Model Factor Factor Cycles
Disk, Compressor 3031811 PT6A-60A, -61 10 1 15,000
Turbine
3036711 PT6A-60A, -61 10 1 15,000
3040311 PT6A-60A, -61 10 1 15,000
3031811 PT6A-62 10 2 15,000
3036711 PT6A-62 10 2 15,000
3040311 PT6A-62 10 2 15,000
3040311 PT6A-62 BS1320 1 15 15,000
Disk, Power Turbine 3029312 PT6A-60A 10 1.5 30,000
(1st Stage)
3029312 PT6A-61 10 1.5 30,000
3029312 PT6A-62 10 2.5 30,000
3029312 PT6A-62 BS1320 1 30 30,000
Disk, Power Turbine 3029313 PT6A-60A 10 1.5 30,000
(2nd Stage)
3029313 PT6A-61 10 1.5 30,000
3029313 PT6A-62 10 2.5 30,000
3029313 PT6A-62 BS1320 1 30 30,000

E. The following limits shown in Table 2 in terms of number of cycles apply to PT6A-65AR,
-65B and -65R engines only.

TABLE 2, Rotor Components - Service Life Limits

Abbr’d Flight Life Limits

Detail Part Cycle Count No. Of
Description No. Engine Model Factor Factor Cycles
Hub, Compressor *3033511 PT6A-65B, -65R 3 1 2,500
(1st Stage)
3036111 PT6A-65B, -65R 3 1 5,000

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 PRATT & WHITNEY CANADA

SERVICE BULLETIN
P&WC S.B. No. 13002R20
TURBOPROP ENGINE
ROTOR COMPONENTS - SERVICE LIFE

3. Accomplishment Instructions (Cont’d)

TABLE 2, Rotor Components - Service Life Limits (Cont’d)

Abbr’d Flight Life Limits

Detail Part Cycle Count No. Of
Description No. Engine Model Factor Factor Cycles
Rotor, Compressor 3033601 PT6A-65AR, -65B, 3 1 24,000
(1st Stage) -65R
3035901 PT6A-65AR, -65B, 3 1 24,000
-65R
3037101 PT6A-65AR, -65B, 3 1 24,000
-65R
3038901 PT6A-65AR, -65B, 3 1 24,000
-65R
3040791 PT6A-65AR, -65B, 3 1 24,000
-65R
3073211-01 PT6A-65AR, -65B, 3 1 24,000
-65R
Shaft, Compressor 3037277 PT6A-65AR, -65B, 3 1 15,000
Rotor -65R
3111903-01 PT6A-65AR, -65B, 3 1 15,000
-65R
3039799 PT6A-65AR, -65B, 3 1 24,000
-65R
3040925 PT6A-65AR, -65B, 3 1 24,000
-65R
3043092 PT6A-65AR, -65B, 3 1 24,000
-65R
Disk, Compressor 3033512 PT6A-65AR, -65B, 3 1 24,000
(2nd Stage) -65R
3036802 PT6A-65AR, -65B, 3 1 24,000
-65R
Disk, Compressor 3033513 PT6A-65AR, -65B, 3 1 24,000
(3rd Stage) -65R
3036803 PT6A-65AR, -65B, 3 1 24,000
-65R

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 PRATT & WHITNEY CANADA

SERVICE BULLETIN
P&WC S.B. No. 13002R20
TURBOPROP ENGINE
ROTOR COMPONENTS - SERVICE LIFE

3. Accomplishment Instructions (Cont’d)

TABLE 2, Rotor Components - Service Life Limits (Cont’d)

Abbr’d Flight Life Limits

Detail Part Cycle Count No. Of
Description No. Engine Model Factor Factor Cycles
Disk, Compressor 3033514 PT6A-65AR, -65B, 3 1 24,000
(4th Stage) -65R
3036804 PT6A-65AR, -65B, 3 1 24,000
-65R
Spacer, Compressor 3102018-01 PT6A-65AR, -65B, 3 1 24,000
(4th Stage) -65R
3105389-01 PT6A-65AR, -65B, 3 1 24,000
-65R
3107098-01 PT6A-65AR, -65B, 3 1 24,000
-65R
3114590-01 PT6A-65AR, -65B, 3 1 24,000
-65R
3075012-01 PT6A-65AR, -65B, 3 1 24,000
-65R
Impeller, Centrifugal 3032973 PT6A-65AR, -65B, 3 1 24,000
-65R
3036794 PT6A-65AR, -65B, 3 1 24,000
-65R
3035876 PT6A-65AR, -65B, 3 1 24,000
-65R
3036039 PT6A-65AR, -65B, 3 1 24,000
-65R
3036891 PT6A-65AR, -65B, 3 1 24,000
-65R
3036897 PT6A-65AR, -65B, 3 1 24,000
-65R
3037204 PT6A-65AR, -65B, 3 1 24,000
-65R

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 PRATT & WHITNEY CANADA

SERVICE BULLETIN
P&WC S.B. No. 13002R20
TURBOPROP ENGINE
ROTOR COMPONENTS - SERVICE LIFE

3. Accomplishment Instructions (Cont’d)

TABLE 2, Rotor Components - Service Life Limits (Cont’d)

Abbr’d Flight Life Limits

Detail Part Cycle Count No. Of
Description No. Engine Model Factor Factor Cycles
Disk, Compressor 3031811 PT6A-65AR, -65B, 10 1 15,000
Turbine -65R
3036711 PT6A-65AR, -65B, 10 1 15,000
-65R
3040311 PT6A-65AR, -65B, 10 1 15,000
-65R
Disk, Power Turbine 3029312 PT6A-65AR, -65B, 10 1 30,000
(1st Stage) -65R
Disk, Power Turbine 3029313 PT6A-65AR, -65B, 10 1 30,000
(2nd Stage) -65R

* Ref. Para. G. (Tables 4 and 5)

F. The following limits shown in Table 3 in terms of number of cycles apply to PT6A-52
engines only.

TABLE 3, Rotor Components - Service Life Limits

Abbr’d Flight Life Limits

Detail Part Cycle Count No. Of
Description No. Engine Model Factor Factor Cycles
Rotor, Compressor 3041271 PT6A-52 3 1 15,000
(1st Stage)
Disk, Compressor 3034312 PT6A-52 3 1 20,000
(2nd Stage)
3134865 PT6A-52 3 1 20,000
Disk, Compressor 3034313 PT6A-52 3 1 20,000
(3rd Stage)
3134866 PT6A-52 3 1 20,000
Impeller, Centrifugal 3036793 PT6A-52 3 1 24,000
Disk, Compressor 3040311 PT6A-52 10 1 15,000
Turbine

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 PRATT & WHITNEY CANADA

SERVICE BULLETIN
P&WC S.B. No. 13002R20
TURBOPROP ENGINE
ROTOR COMPONENTS - SERVICE LIFE

3. Accomplishment Instructions (Cont’d)

TABLE 3, Rotor Components - Service Life Limits (Cont’d)

Abbr’d Flight Life Limits

Detail Part Cycle Count No. Of
Description No. Engine Model Factor Factor Cycles
Disk, Power Turbine 3029312 PT6A-52 10 1.5 30,000
(1st Stage)
Disk, Power Turbine 3029313 PT6A-52 10 1.5 30,000
(2nd Stage)

G. First stage compressor hub P/N 3033511 was installed on engines with the following
serial numbers and must be removed after accumulating 2500 total cycles.

TABLE 4, Compressor hub installed on PT6A-65B engines

Engine Serial No. Hub Serial No.

32001 5M123
32002 4M462
32003 5M128
32004 4M466
32005 7M858
32006 7M831

TABLE 5, Compressor hub installed on PT6A-65R engines

Engine Serial No. Hub Serial No.

97008 5M124
97009 4M464
97010 4M460
97011 5M127
97012 4M468
97013 5M119
97014 5M131
97016 5M125
97018 5M134

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SERVICE BULLETIN
P&WC S.B. No. 13002R20
TURBOPROP ENGINE
ROTOR COMPONENTS - SERVICE LIFE

3. Accomplishment Instructions (Cont’d)

TABLE 5, Compressor hub installed on PT6A-65R

engines (Cont’d)
Engine Serial No. Hub Serial No.

97019 5M122
97020 7M856
97023 9M312
97024 7M837
97026 7M830

H. At repair and overhaul, component life is calculated in accordance with the following
formula:

Accumulated No. of No. of Flights - No. of Starts

= [ + ( ) ] X Flight Count Factor
Total Cycles Starts Abbreviated Cycle Factor
EXAMPLE:

Part No. 3031811 (Disk)

Abbreviated Cycle Factor 10
No. of Starts 3000
No. of Flights 9000
Flight Count Factor 1

Accumulated 9000 - 3000

= [ 3000 + ( ) ] X 1
Total Cycles 10
= [3000 + 600] X 1

= 3600
4. Appendix

Not applicable.

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