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Caravan SERVICE LETTERCAL-71-12

TITLEPOWER PLANT - TRANSMITTAL OF P&WC S.I.L. NO. PT6A-196R1, S.I.L. NO. GEN-123R2, S.I.L. NO.GEN-134, PT6A SPB NO. 185, PT6A SPB NO. 186, S.B. NO. 1002R29, S.B. NO. 1455R3, S.B. NO. 1521R5,S.B. NO. 1568R7, S.B. NO. 1588R2, S.B. NO. 1731, S.B. NO. 1733

EFFECTIVITY208 and 208B Airplanes

REASONTo transmit the 12 Pratt & Whitney Canada (P&WC) service documents that follow:

• Service Information Letter S.I.L NO. PT6A-196R1, Removal of HTS oils from the approved listingof lubricating oils

• Service Information Letter S.I.L NO. GEN-123R2, Qualified Engine Oil Analysis Laboratory List• Service Information Letter S.I.L NO. GEN-134, Technical Publication Revision Status• Spare Parts Bulletin PT6A SPB No. 185, TURBOPROP ENGINE FUEL FILTER REPLACEMENT PARTS

KIT - REPLACEMENT OF• Spare Parts Bulletin PT6A SPB No. 186, TURBOPROP ENGINE METAL SHIPPING CONTAINER -

INTRODUCTION OF• Service Bulletin P&WC S.B. No. 1002R29, TURBOPROP ENGINE ROTOR COMPONENTS - SERVICE

LIFE• Service Bulletin P&WC S.B. No. 1455R3, TURBOPROP ENGINE COMPRESSOR TURBINE BLADE -

REPLACEMENT OF• Service Bulletin P&WC S.B. No. 1521R5, TURBOPROP ENGINE COMPRESSOR TURBINE DISK

BALANCING ASSEMBLY AND BLADES - REPLACEMENT/MODIFICATION OF• Service Bulletin P&WC S.B. No. 1568R7, TURBOPROP ENGINE FUEL CONTROL UNIT -

MODIFICATION/REPLACEMENT OF• Service Bulletin P&WC S.B. No. 1588R2, TURBOPROP ENGINE COMPRESSOR BLEED OFF VALVE -

REPLACEMENT OF• Service Bulletin P&WC S.B. No. 1731, TURBOPROP ENGINE ACCESSORY GEARBOX (AGB)

HOUSING ASSEMBLY - REPLACEMENT OF• Service Bulletin P&WC S.B. No. 1733, TURBOPROP ENGINE TORQUE LIMITER - INSPECTION OF.

DESCRIPTIONCessna Aircraft Company wishes to transmit these 12 P&WC service documents as information formodel 208/208B airplane owners.

COMPLIANCEINFORMATIONAL. This service letter is for informational purposes only.

LABOR HOURSNot applicable

MATERIAL AVAILABILITYNot applicable

REFERENCESRefer to the 12 P&WC service documents that are attached to this service letter.

CAL-71-12March 26, 2014 of 1

Cessna Aircraft Company, Cessna Customer Service, P.O. Box 7706, Wichita, KS 67277, U.S.A. 1-316-517-5800

This document contains technical data and is subject to U.S. export regulations. This information has been exported from the United Statesin accordance with export administration regulations. Diversion contrary to U.S. law is prohibited. ECCN: 9E991

COPYRIGHT © 2014

S.I.L NO. PT6A-196 R1

SERVICE INFORMATION LETTER

This Service Information Letter is valid until superseded by revision or cancellation.

EXPORT CONTROL CLASSIFICATION: This document does not contain technical data

ISSUED: July 11th 2012 Revised: December 10th 2013 Page 1 of 1

PRATT & WHITNEY CANADA CORP. MARIE-VICTORIN, LONGUEUIL

QUEBEC, CANADA J4G 1A1 PRINTED IN CANADA

Subject: Removal of HTS oils from the approved listing of lubricating oils. Applicability: All PT6A engines This Service Information Letter (SIL) is issued to notify operators that effective March 20

th, 2014, HTS

oils will no longer be approved for use in PT6A engines. A lead time of three months is provided in order to give a time period to operators for conversion of oil type, if applicable, in their engines.

Analysis has indicated that long term interaction of HTS oils with the fluorocarbon-based elastomeric material AMS7276 (Viton A) at higher oil temperatures may increase the rate of seal degradation, which can result in oil leakage. It is based on this determination that HTS oils use is no longer recommended, and therefore, conversion to another oil type is required. Customer who would experience AGB lip seal degradation due to prior use of HTS oils will be covered by P&WC warranty.

The recommended oil change procedure is by attrition (oil top up method) as described in the

applicable turboprop engine approved listing of lubricating oils Service Bulletins.

Yours truly, PRATT & WHITNEY CANADA Corp.

David Meisels Manager, PT6A Customer Engineering Customer Service

S.I.L NO. GEN-123R2


This Service Information Letter is valid until cancelled or superseded by revision.

EXPORT CONTROL CLASSIFICATION: This document does not contain technical data.ISSUED: Jan 21/2013REVISION: Dec 09/2013 Page 1 of 5

PRATT & WHITNEY CANADA CORP.MARIE-VICTORIN, LONGUEUIL

QUEBEC, CANADA J4G 1A1PRINTED IN CANADA

Subject : Qualified Engine Oil Analysis Laboratory List

Applicability : All Engine Models

Pratt & Whitney Canada Corp. (P&WC) wishes to provide operators and maintainers of P&WCengines the following list of qualified laboratories for purposes of engine oil sample analyses.

Region : Americas

Analysts, Inc.3385 Martin Farm Road, Suwanee,GA 30024Atlanta, Georgia, USATEL 800-241-6315 | 470-238-4000FAX 470-238-4019WEBSITE: www.analystsinc.com

Aviation Laboratories Inc.Corporate Headquarters5401 Mitchelldale #B6HoustonTX 77092USA1-800-256-6876TEL: (713) 864-6677FAX: (713) 864-6990WEBSITE: www.avlab.com

Aviation Laboratories Inc.New Orleans International Airport910 Maria StreetKenner, LA 70062USATEL: (504) 469-6751FAX: (504) 469-6886E-mail 1: [email protected] 2:[email protected]: www.avlab.com

Jet-Care International Inc.3 Saddle RoadCedar KnollsNJ 07927-902USATEL: 877 JET-CARETEL: (973) 292-9597FAX: (973) 292-3030WEBSITE: www.jet-care.com

PRATT & WHITNEY CANADASERVICE INFORMATION LETTER

PWC: SIL GEN-123R2


Region : Americas (Continued)

Martel Laboratories JDS Inc.Petroleum Laboratory Services1025 Cromwell Bridge RoadBaltimore, MD 21286USATEL: (410) 825-7790FAX: (410) 821-1054E-mail: [email protected]: www.martellabs.com

Martel Laboratories JDS Inc.Petroleum Laboratory Services1438 E Samgamon Ave.Springfield, IL 62702USATEL: (217) 522-0009FAX: (217) 522-2119WEBSITE: www.matelabs.com

Martel Laboratory Services Inc.Aero Services BuildingCapital AirportSpring field, IL 62707USATEL: (217) 522-0009FAX: (217) 544-2034WEBSITE: www.martellabs.com

Metro Tech Systems Ltd.Bay 1125621-11th Street N.ECalgary. AlbertaT2E 7G9, CanadaTEL: (403) 295-8803FAX: (403) 295-3848E-mail: [email protected]: www.metrotechsystems.ca

Predictive Maintenance Corporation8330 Décarie Boulevard,Montréal, Quebec,CanadaH4P 2P5TOLL FREE 1.800.461.TEST (8378)WEBSITE:www.tribologik.com

WearCheck Canada Inc.C8-1175 Appleby LineBurlington, ONL7L 5H9CanadaTEL: +1 (905)569-8600FAX: +1 (905)569-8605E-mail: [email protected]: www.wearcheck.com

SkywatchService of Analysts, Inc.3075 Cornors North Court NWNorcross, GA 30071USATEL: (770) 448-5235FAX: (404) 448-5918


PWC: SIL GEN-123R2


Region: Asia & Australia

All Nippon Airways Co., Ltd3-6-7 Haneda AirportOta-kuTokyo 144-0041JapanTEL: +81-3-6428-2144FAX: +81-3-6428-2141

Det Norske Veritas Pte. Ltd10 Science Park DriveDNV Technology CenterSingapore 118224TEL: 65-6779-6363FAX: 65-6779-5239E-mail: [email protected]: www.dnv.com.sq

Qantas NDT SectionQantas EngineeringMelbourne Maintenance BaseOperations RoadTullamarineVictoria 3043AustraliaTEL: 61-3-92807265FAX: 61-3-92807064WEBSITE: www.qantas.com.au

Xi’an Aero Engine Corp.Physic and Chemical Testing CentreXujiawan BeijiaoP.O Box 13-88, Xi’an 710021Peoples Republic of ChinaTEL: 86-29-86152501FAX: 86-29-86153145WEBSITE: www.xaec.com

Aviation Safety Institute Technology Lab.(Center of Aviation Safety Technology)General Civil Aviation Administration of ChinaBuilding 24 Jia, Xibahe Beili,Chaoyang District, Beijing 100028 P.R.ChinaTEL: 86-10-64473571, 86-10-64473559FAX: 86-10-64473569, 86-10-64473548E-mail 1: [email protected] 2: [email protected]: www.castc.org.cn/lab

Materials Research LaboratoriesIndustrial Technology Research Institute321 Kuang Fu RoadSection 2. HsinchuTaiwanTEL: (886) 03-573-2677FAX: (886) 03-573-2348E-mail: [email protected]: www.mrl.itri.org.tw

Setsco Services Pte, Ltd.18 Teban Gardens CresentSingapore 608925TEL: 65-6566-7777FAX: 65-6566-7718E-mail: [email protected]: www.setsco.com

Xi’an High-Tech Physical Chemical Co. LtdTesting Center8 Guangde RoadXi’an High Tech Development Zone, 710075Peoples Republic of ChinaTEL: 86-29-88452776 & 86-29-88453188FAX: 86-29-88452779E-mail: [email protected]: www.xagklh.com


PWC: SIL GEN-123R2


Region: Asia & Australia (Continued)

Japan Airlines Co., Ltd.Dept: Marketing & Sales Department, Engineering& MaintenanceM1 Bldg. 3-5-1 Haneda Airport, Ota-ku, Tokyo144-0041JapanTel : +81-3-5756-2242Fax : +81-3-5756-2209E-Mail: [email protected]

Region: Europe

AVIO Spa Laboratory80038, Pomigliano D’ArcoNapoli, ItalyTEL: 39-081-3163215FAX: 39-081-3163463E-mail: [email protected]: www.avio.it

PCAS (Produits Chimiques Auxiliaires etSyntheses)Zone Industrielle de la vigne aux Loups23 Rue Bosselet91-161 Long-JumeauFranceTEL: 33-1-69-74-81-00FAX: 33-1-69-09-49-74E-mail: [email protected]: www.pcaschem.com

SN BrusselsBuilding 12-012International AirportBrussels, 1930 ZaventemBelgiumTEL: (32) 2 723 4958FAX: (32) 2 723 5995WEBSITE: http://www.sabena.com

Lufthansa Technik AGWeg Beim JaegerDept: HAM/TQ/MWR123D-22313 HamburgGermanyTEL: (49) 0 40 5070 2233FAX: (48) 0 40 5070 1411

ITS Testing Sevices (UK) LtdIntertek FarnboroughCody technology ParkFuels and Lubricants centreRoom 1068 Bldg A7Cody Technology ParkFarnborough GU14 0LXDirect: +44 (0) 1252 397469Mob: +44 (0) 7771808541E mail: [email protected]

Spectro Oil Analysis Company Ltd.Palace GateHigh StreetOdiham, Hampshire RG29 1NPUnited KingdomTEL: 44-0-1256-704000FAX: 44-0-1256-704006AOG: +44 (0) 1256 393500 (24 Hours)E-mail: [email protected]: www.spectro-oil.com


PWC: SIL GEN-123R2


Region: Europe (Continued)

Vernolab ENGEOILZone Industrielle des Cents Sillone Tobias Barreto Street No. 150Rue Lavoisier BP 813 New Neighbourhood Suissa27130 Verneuil Sr Avre CEP: 30421-028-Bello HorizoneteFrance Minas Gerais, BrazilTEL: 33-232606500 TEL: 55-31-3371-3322FAX: 16-232601646 Contact person: Geraldo Mota Abranches BaptistE [email protected] Technical DirectorWEBSITE: www.vernolab.com WEBSITE: http://www.engeoil.com.br/home/

Following the issue of this SIL (Service Information Letter), the Oil analysis laboratories list will nolonger appear in the P& WC Engine Maintenance manuals.

P & WC Customer service Centre24- HOUR GLOBAL SERVICE

E-MAIL: [email protected] : (+Canada) (450) 647-8000USA & CANADA : 1-800-268-8000INTERNATIONAL : (+1AC*) 8000-268-8000FAX : (+Canada) (450) 647-2888WEBSITE : www.pwc.ca

Yours truly,PRATT & WHITNEY CANADA COPR.

Narcisa JivanService EngineeringRegional Turboprop Program

S.I.L NO. GEN-134


This Service Information Letter is valid for one year from date of issue.

EXPORT CONTROL CLASSIFICATION: This document does not contain technical data. ISSUED: Nov 12/2013 Page 1 of 2

PRATT & WHITNEY CANADA CORP. MARIE-VICTORIN, LONGUEUIL

QUEBEC, CANADA J4G 1A1 PRINTED IN CANADA

Subject Technical Publication Revision Status Applicability All P&WC Engine Series This SIL is issued to remind Publication Services subscribers of the need to regularly check for the revision status of Technical Publications and Bulletins on P&WC site. Ideally, this verification should be conducted every time documentation is accessed. According to our records some operators do not appear to be accessing the system, hence the reminder. This is increasingly important as P&WC continues to improve the frequency of revisions to its Manuals and updates can only be accessed by licensed users who are registered on the P&WC customer portal -- eportal.pwc.ca. Recent Changes to P&WC Technical Publications Services The deployment of Manuals to the customer portal gradually took place between May 2011 and June 2013 and CD-ROMs are no longer distributed by mail. Similarly, Temporary Revisions (TRs) and Bulletins are no longer mailed out as all active subscribers were upgraded to the new online service. (Note that mail out of Revisions, TRs and Bulletins is maintained for subscribers of the Printed Manuals service only.) The online Publications Service is designed for ease of use and peace of mind. Revisions and Bulletins are instantly posted on the Technical Publications application on the Customer Portal. The “My Publications” workspace in the application displays all the newest documentation applicable to your engine model in one, convenient location. The content on this page is always current; there is no need to check for status before use. Users can view online or download and save an offline backup copy of Manuals and Bulletins. Email notification can also be requested by individual users to ensure they remain current with updates for Manuals, Bulletins or Ground Base Software (as applicable). It is important to know that individual users at your location must be assigned a “license” before they can view or download any documentation from the Technical Publications online application. Your subscription to P&WC Technical Publications entitles you to five licenses that must be assigned or revoked by the Technical Publications Administrator in your company. If you have difficulty identifying your Administrator or accessing your Publications, please refer to tutorials on the “Get Started” page on the site or contact us at [email protected]. You can also provide us your feedback through this email address.

PRATT & WHITNEY CANADA SERVICE INFORMATION LETTER

PWC: S.I.L. NO. GEN-134

EXPORT CONTROL CLASSIFICATION: This document does not contain technical data. ISSUED: Nov 12/2013 Page 2 of 2

Revision Status Report and Bulletin Index Checks The revision date for your Manuals, and the latest releases of Service Bulletins or Service Information Letters, can be checked at any time for free on our corporate website: www.pwc.ca. Once on the site, click on “Service & Support,” then select “Technical Publications” from the menu bar, or use this direct link -- http://www.pwc.ca/en/service-support/technical-publications. Alternatively on the customer portal, any Manual or Bulletin posted under “My Publications” will display the date of issue and the revision number, applicable to the engine model selected. To ensure you have access to the latest Technical Publications, it is your responsibility to check for status before using an offline backup copy of any Manual or Bulletin downloaded from the “My Publication” section of the application. The same applies if you subscribe to the Printed Manuals service. Exception to the above is direct viewing of Manuals and Bulletins online which saves you from checking for status, browsing bulletin indexes or repeatedly downloading and handling files. For your productivity and peace of mind, what you see on the online application is always current. P&WC is committed to online services and we continue to invest in service improvements. As always, your feedback is important. Do not hesitate to contact us at [email protected] if you have any suggestion or question. PRATT & WHITNEY CANADA CORP

Jean-Francois Arcand Manager, Service Information Management

1. Model

PT6A-140 Engines.

2. Reason

To ease procurement and for standardization purposes, replace the fuel filter replacementparts kit with one that has a fuel filter Interchangeability Control (IC) option.

3. Description

Replace the fuel filter replacement parts kit with the new one.

4. Approval

D.O.T./D.A.A. approved

5. Publications Affected

Illustrated Parts Catalog P/N 3075744 (PT6A-140)

6. Material - Cost and Availability

You can get the procurable parts listed in Para. 7., from any Pratt & Whitney Canada PartsDistribution Center.

P&WC No. E6995K

PRATT & WHITNEY CANADA

SPARE PARTS BULLETINPT6A SPB No. 185

WARNING - PROPRIETARY RIGHTS & EXPORT CONTROLS NOTICE

This bulletin contains proprietary information of Pratt & Whitney Canada Corp. (″P&WC″), which P&WC provides in confidenceand 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 thisbulletin 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 changeor repair, or obtain FAA or other government approval to do so. Possession and use of this bulletin is also subject to the restrictionsset out in P&WC’s Technical Data Agreement (a copy of which may be obtained by contacting P&WC Technical Publications). Thecontents of this bulletin may be subject to export control laws. Unauthorized export or re-export of the bulletin, or parts thereof, isprohibited. 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 given to:VP - Legal Services, Pratt & Whitney Canada Corp., 1000 Marie-Victorin (01BE5), Longueuil, Quebec J4G 1A1.

Export Control Classification

*Data is subject to the jurisdiction of the Export and ImportControls Bureau of the Department of Foreign Affairs andInternational Trade of Canada, Department of Commerceof the United States and/or Department of State of theUnited States.

** Data is not subject to the jurisdiction of the Departmentof Commerce of the United States or Department of Stateof the United States but would become subject if exposedto any US involvement.

Regulation ClassificationNumber

Canadian ECL(s)*

ECCN(s)*

P-ECCN(s)** 9E991

USML (ITAR)*

P-USML**

Dec 16/2013 PT6A SPB No. 185Page 1 of 2© 2013 Pratt & Whitney Canada Corp.

PRINTED IN CANADA

TURBOPROP ENGINEFUEL FILTER REPLACEMENT PARTS KIT - REPLACEMENT OF

6. Material - Cost and Availability (Cont’d)

The estimated total cost of new parts needed to replace old parts is $Quote (US, 2013).

The new parts are available.

7. Material Information

The quantity of materials listed in this section is on a per Engine basis.

New P/N Keyword Old P/N Qty

Est. UnitList Price

($US,2013)

InstructionsDisposition

3079314-01 Parts Kit, FilterReplacement, FOHE

3078194-01 1 Quote (A)(B)

Ê Filter Element, Fuel, NonCleanable

3059778-01 1 (C)

3059779-01 Ê Filter Element Option (IC) 1 48.76

3070220-01 Ê Ê Element Filter, FuelPump

Ref.

3059778-01 Ê Ê Filter Element, Fuel, NonCleanable

Ref. (C)

(A) TWO WAY INTERCHANGEABLE - (ATA 200 Explanation Code 02)The old or the new part can replace the old or the new part.

(B) The kit can be procured from any Pratt & Whitney Canada Distribution Center.

(C) Change in part hierarchy from old configuration to new configuration.



P&WC Proprietary Information. Subject to the restrictions on the first page.

The export control classification with respect to this document is contained on the first page.Dec 16/2013 PT6A SPB No. 185Page 2 of 2

TURBOPROP ENGINEFUEL FILTER REPLACEMENT PARTS KIT - REPLACEMENT OF

1. Model

PT6A-140 Engines.

2. Reason

For service engines only, allow the use of a reusable metal shipping container withcorresponding shipping instructions.

3. Description

4. Approval

D.O.T./D.A.A. approved

5. Publications Affected

Illustrated Parts Catalog P/N 3075744 (PT6A-140)

6. Material - Cost and Availability

You can get the procurable parts listed in Para. 7., from any Pratt & Whitney Canada PartsDistribution Center.

P&WC No. E7602A




This bulletin contains proprietary information of Pratt & Whitney Canada Corp. (″P&WC″), which P&WC provides in confidenceand 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 thisbulletin 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 changeor repair, or obtain FAA or other government approval to do so. Possession and use of this bulletin is also subject to the restrictionsset out in P&WC’s Technical Data Agreement (a copy of which may be obtained by contacting P&WC Technical Publications). Thecontents of this bulletin may be subject to export control laws. Unauthorized export or re-export of the bulletin, or parts thereof, isprohibited. 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 given to:VP - Legal Services, Pratt & Whitney Canada Corp., 1000 Marie-Victorin (01BE5), Longueuil, Quebec J4G 1A1.





Canadian ECL(s)*

ECCN(s)*

P-ECCN(s)** 9E991

USML (ITAR)*

P-USML**

Dec 13/2013 PT6A SPB No. 186Page 1 of 7© 2013 Pratt & Whitney Canada Corp.

PRINTED IN CANADA

TURBOPROP ENGINEMETAL SHIPPING CONTAINER - INTRODUCTION OF

6. Material - Cost and Availability (Cont’d)

The estimated total cost of new parts needed to replace old parts is $TBA (US, 2013).





Est. UnitList Price

($US,2013)


3079331-01 Container Assy-Comp EngMetal Ship

Ref

PK242 Ê Cover-Shipping,Oil Vent 1 9.31

PK245 Ê Plug-Shipping,.4375-20Thd

2 3.71

PK3608 Ê Cap-Shipping,.5625-18Thd

2 9.45

PK1301 Ê Cap-Prot Dust Seal,.375-24 Thd

1 2.78

PK251 Ê Cover-Shipping,StarterGenerator

1 65.77

PK255 Ê Cover,Shipping-TachoMount

2 11.60

PK4471 Ê Cover-Shipping, PropellerShaft

1 14.15

PK3654-07 Ê Cap-Protective,.720 X.500

3 9.32

PK1178 Ê Cap-Protective,InternalScrew Thd

2 7.67

PK3611 Ê Cap-Shipping,1.0625-12Thd

2 7.35

MS9532-04 Ê Bolt-Mach,.375-24J X.625,Dr Hex

8 13.28

MS35338-46 Ê Washer-Lock,.375X.683X.094

8 0.42






7. Material Information (Cont’d)


Est. UnitList Price

($US,2013)



1 13.20

MS3367-1-4 Ê Strap-Tiedown,Adjustable A/R 0.57

PK3655-08 Ê Plug-Protective,Tapered 2 11.19


1 8.35


1 8.74

PK423 Ê Desiccant 8 Unit Bagged 8 14.47

PK5732 Ê Container-Shipping,Metal,ReusabAsyo

1 175000.00

PK751 Ê Ê Plate-Identification,ShipCont

1 216.50

AN535-4-4 Ê Ê Screw-Drive,RoundHead,.114 X .250

4 Quote

PK342 Ê Ê Indicator-Humidity,Shipping Cntnr

1 208.30

PK1626 Ê Ê Window-Observtn-ShippCont

2 287.40

PK748 Ê Ê Plate-Data,ShipContainer

1 Quote


4 Quote

PK1624 Ê Ê Valve-Breather,ShippingContainer

1 1846.10

PK335 Ê Ê Valve-Air Fill,Serv Recp(Scd)

1 30.22

PK751 Ê Ê Plate-Identification,ShipCont

1 216.50








Est. UnitList Price

($US,2013)



4 Quote

MS20913-6 Ê Ê Plug-Pipe,.750Npt,Square

1 99.22

PK3799 Ê Ê Skid-Shipping Container 4 Quote

PK345 Ê Ê Packing-Preformed,5.975X.275

1 58.82

PK333 Ê Ê Receptacle-Service ShpgCntr

1 Quote

PK343 Ê Ê Cover-RecordRecept.Ship.Contain

1 Quote

PK346 Ê Ê Cover-Service ReceptShip.Cont.

1 142.30

PK5730 Ê Ê Stud-Collar,Hex.375-16X2.030Long

2 Quote

PK344 Ê Ê Packing-Preformed,4.225X.210

1 80.35

PK341 Ê Ê Packing-Extruded,.475X.194

1 473.30

PK2631 Ê Ê Gasket-Side EngineMount

2 19.12

PK488 Ê Ê Bracket-Eng Mount,Rear 1 291.70

PK2630 Ê Ê Gasket-Rear EngineMount

1 11.15

PK383 Ê Ê Pin-Straight,Headed,.375X1.266

1 Quote

PK495 Ê Ê Mount-Swivel,Rear,Asyo 1 246.10

MS24665-372 Ê Ê Pin-Cotter(Split) 1,250 1 Quote

NAS1149C1063R Ê Ê Washer-Flat,.640X1.188X.063

1 Quote








Est. UnitList Price

($US,2013)


MS20392-9P43 Ê Ê Pin-Straight,Headed,.625X1.500,Flat

1 Quote

PK487 Ê Ê Bracket-Eng Mount,Front 2 523.30

AN121817 Ê Ê Pin-Straight Hd,.372X1.719,Flat Dr

2 Quote

MS27183-14 Ê Ê Washer-Flat,.406X.812X.065

3 1.22

MS24665-285 Ê Ê Pin-Cotter,.094 X 1.000 3 0.40

PK5731 Ê Ê Cradle-Mount,ShippingContainer

1 Quote

PK3651 Ê Ê Pin-Loc,Thd .375-16Unc-2A,2.500 L

2 Quote

MS51967-8 Ê Ê Nut-Plain,Hex,.3750-16X.3285

2 Quote

MS35338-46 Ê Ê Washer-Lock,.375X.683X.094

2 0.42

PK749 Ê Ê Bracket-Mtg,ShipContainer

4 276.90

PK338 Ê Ê Mount-Shear,ShippingContainer(Scd)

4 Quote

3032923 Ê Ê Decal-CompanyInsignia,Eng Cntnr

2 164.10

MS9244-01 Ê Ê Decal-Rubber AssemblyDate

1 28.67

PK2070 Ê Cover-Shipping,ExhaustDuct

1 101.30

MS9519-07 Ê Bolt-Mach,.250-28J X.562,Hex

6 9.89

MS9320-10 Ê Washer-Flat,.276 X .500 X.062

6 3.57








Est. UnitList Price

($US,2013)


MS9881-10 Ê Nut-Plain Hex,.250-28X.219

6 9.43

MS35338-44 Ê Washer-Lock,.250X.489X.062

3 0.98

MS9519-10 Ê Bolt-Mach,.250-28J X.750,Hex

3 Quote

3079330 Ê Shipping ContainerInstructions

1 Quote

PK3199 Ê Cover-Shipping,Air Inlet 1 48.65


1 8.74

PK1219 Ê Plug-Shipping,.375-24 Thd 2 2.25

PK3654-065 Ê Cap-Protective, .680 X.500

1 2.35


1 2.35

PK1599 Ê Plug-Shipping,.875-14 Thd 1 10.22

PK268 Ê Desiccant-4 Unit Bagged 1 4.31

PK268 Ê Desiccant-4 Unit Bagged 1 4.31


1 8.30


1 13.83


2 3.71

PK3609 Ê Cap-Shipping,.500-20 Thd 1 9.94


1 13.83

PK2261 Ê Cover-Shipping,CenterEngine Mount

1 19.11








Est. UnitList Price

($US,2013)



1 2.35


1 3.71


1 9.32


1 3.71

PK5192 Ê Cap-Protective 1 Quote


1 3.71






BULLETIN INDEX LOCATORTURBOPROP ENGINE

ROTOR COMPONENTS - SERVICE LIFE

MODEL APPLICATION

PT6A-6, PT6A-6A, PT6A-6B, PT6A-6/C20, PT6A-20, PT6A-20A, PT6A-20B, PT6A-21, PT6A-27,PT6A-28, PT6A-34, PT6A-35, PT6A-34B, PT6A-36, PT6A-114, PT6A-114A, PT6A-135,

PT6A-135AModel(s) deleted this revision: PT6A-140

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

Summary: 1. This service bulletin provides the service life limits for the rotor component partswhich are authorized for use in the above Pratt & Whitney Canada Inc. enginemodels, as required by the Canadian Department of Transport regulations.

2. Compliance with the Accomplishment Instructions in step 3. of this servicebulletin is necessary to maintain conformity with the approval type design and thevalidity of the airworthiness certification.

3. The Low Cycle Fatigue (LCF) counting process is described in detail, includingthe formula to use, refer to the ‘‘Remaining Life’’ section below, to calculate thetotal accumulated cycles for the various rotor components.


SERVICE BULLETINP&WC S.B. No. 1002R29

Dec 01/1973 PT6A-72-1002Revision No. 29: Dec 05/2013 Cover Sheet

24-Hour Global Service USA & CANADA........................ 1-800-268-8000 Other .......................................... 1-450-647-8000

CFIRST CENTRE International .................... (IAC*)+8000-268-8000 Fax ............................................. 1-450-647-2888

Toll free where available (SIL GEN-027) * International Access Code Web Site .................................. www.pwc.ca


This bulletin contains proprietary information of Pratt & Whitney Canada Corp. (″P&WC″), whichP&WC provides in confidence and solely for the purposes of supporting engine certification andproviding applicable information regarding the proper use, maintenance, inspection, repair, servicingand parts application of P&WC products and services, as directed therein. Neither this bulletin norany information in it may be disclosed to others, or used for any other purpose, including, withoutlimitation, to design, create, develop, reproduce, manufacture or derive any design, part, product,material, process, modification, configuration change or repair, or obtain FAA or other governmentapproval to do so. Possession and use of this bulletin is also subject to the restrictions set out inP&WC’s Technical Data Agreement (a copy of which may be obtained by contacting P&WC TechnicalPublications). The contents of this bulletin may be subject to export control laws. Unauthorized exportor 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 begiven to:VP - Legal Services, Pratt & Whitney Canada Corp., 1000 Marie-Victorin (01BE5), Longueuil,Quebec J4G 1A1.





Canadian ECL(s)*

ECCN(s)*

P-ECCN(s)** 9E991

USML (ITAR)*

P-USML**

REVISION TRANSMITTAL SHEETTURBOPROP ENGINE MODEL PT6A

SUBJECT: Pratt & Whitney Canada Service Bulletin No. PT6A-72-1002, Rev. No. 29, dated Dec05/2013 (P&WC S.B. No. 1002R29) ROTOR COMPONENTS - SERVICE LIFE

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

Please retain this Revision Transmittal Sheet with the revised bulletin.

SUMMARY: This revision is issued to:

v remove the PT6A-140 engine since the life items are part of the AWL section of theMaintenance Manual.

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: Dec 01/1973Revision No. 1: Aug 26/1974Revision No. 2: Jan 28/1975Revision No. 3: Nov 10/1975Revision No. 4: Apr 01/1976Revision No. 5: Apr 25/1976Revision No. 6: Oct 20/1976Revision No. 7: Mar 30/1977Revision No. 8: Dec 15/1977Revision No. 9: Jun 16/1978Revision No. 10: Jun 22/1979Revision No. 11: Apr 22/1980Revision No. 12: Feb 09/1982

Revision No. 13: Aug 16/1982Revision No. 14: Aug 29/1983Revision No. 15: Jun 01/1984Revision No. 16: Feb 05/1985Revision No. 17: Oct 02/1985Revision No. 18: Oct 08/1986Revision No. 19: Aug 08/1989Revision No. 20: Jun 04/1990Revision No. 21: Dec 05/1998Revision No. 22: Apr 17/2000Revision No. 23: Apr 12/2002Revision No. 24: Sep 29/2004Revision No. 25: Dec 19/2007

Revision No. 26: Jun 13/2012Revision No. 27: Jun 15/2012Revision No. 28: Oct 23/2012Revision No. 29: Dec 05/2013

Pratt & Whitney Canada Corp.1000, Marie-VictorinLongueuil, Québec, Canada J4G 1A1Tél. 450-677-9411

05 December 2013

P&WC S.B. No. 1002R29

1. Planning Information

A. Effectivity

PT6A-6, PT6A-6A, PT6A-6B, PT6A-6/C20, PT6A-20, PT6A-20A, PT6A-20B, PT6A-21,PT6A-27, PT6A-28, PT6A-34, PT6A-34B, PT6A-35, PT6A-36, PT6A-114,PT6A-114A, PT6A-135, PT6A-135A 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 components listed in the table below are subject to LCF due tocyclic operation of the engine. As a result, these parts must be replaced whentheir respective accumulated total cycle limit is reached.

(2) Operators must record all flights, starts and accumulated total cycles (which mustbe calculated using the formula Ref. 3.E.) in the applicable document for eachcomponent (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 anabbreviated cycle is: idle - takeoff - flight - landing - idle. A normal or full cycleincludes the foregoing plus an engine start and shutdown (i.e. abbreviated cyclesare equivalent to the number of flights minus the number of starts). The limitsspecified in Paragraph 3. (Ref. Table 1) are in terms of full cycles. Accumulatedabbreviated cycles are summated in terms of full cycles by means of a formula andtabulated 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, anAbbreviated Cycle Factor (ACF) is listed in the le below, and used in theformula which determines accumulated total cycles;

v A Flight Count Factor (FCF) is a multiplying factor that can be used to credit ordebit life to the components listed in the Life Service to reflect the aircraftapplication of the engine. This factor can also be specific to an operator thatdiverges from the standards as missions.

P&WC No. 36484, 31427, B6344A, D0998A, D0998B, D2849A, D2849C, DCR20432



P&WC Proprietary Information. Subject to the restrictions on the back of the locator

The export control classification with respect to this document is contained on the back of the locator.Dec 01/1973 PT6A-72-1002Revision No. 29: Dec 05/2013 Page 1 of 10© 1973 Pratt & Whitney Canada Corp.

PRINTED IN CANADA

TURBOPROP ENGINEROTOR COMPONENTS - SERVICE LIFE

1. Planning Information (Cont’d)

v When abbreviated cycles are not recorded, each flight is considered to have beenpreceded 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 asissued by Transport Canada. Transport Canada must approve changes to rotorcomponent cyclic lives.

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

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

(7) Operators making scheduled or frequent use of the engine’s highest allowable ratedpower 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 differentmodels, providing the part number is authorized to be installed in the specificengine models (Ref. applicable Service Bulletin). Operators transferring rotatingcomponents between engine models governed by different SBs must adhere to thelower of the LCF life limits published in the applicable SBs.

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

NOTE: 2. It is not permitted to use parts which were installed on ST6 engines forPT6 engines.

E. Compliance

The service lives quoted in the Accomplishment Instructions are incorporated byreference in the type approval as issued by the Canadian Department of Transport.Compliance with these instructions is therefore necessary to maintain conformity with theapproval type design and the validity of the airworthiness certification.




The export control classification with respect to this document is contained on the back of the locator.Dec 01/1973 PT6A-72-1002Revision No. 29: Dec 05/2013 Page 2 of 10



F. Approval

Transport Canada has reviewed and approved the technical contents of this ServiceBulletin.

NOTE: This Service Bulletin is incorporated by reference in one or more TransportCanada, Aircraft Engine Type Approvals and the service lives thereby constitutelimits applicable to the corresponding engines, modules and componentswhich embody only parts listed in the Transport Canada approved parts list, aspromulgated in the applicable Illustrated Parts Catalog and Service Bulletins.Operators requiring approval for incorporation of parts not listed will be requiredto substantiate to their local Airworthiness Authority the applicability of thelives 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 ManualsP&WC S.B. No. 1094, 1113, 1164 and 1302

L. Publications Affected

Applicable PT6A Technical Manuals

M. Interchangeability and Intermixability of Parts

Not applicable.


A. Industry Support Information

Not applicable.







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 appropriateengine log book.

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

C. Deleted

D. Rotor components with lives greater than the limits shown in Table 1 or rotor componentsnot supported with proper documentation, are to be removed from service.

TABLE 1, Rotor Components - Service Life Limits

DescriptionDetail PartNo. Engine Model

Abbr’dCycleFactor

FlightCountFactor

Life LimitsNo. OfCycles

Hub, Compressor(1st Stage)

3006911 PT6A-6, -6A, -6B,-6/C20, -20, -20B

1 1 5000

3011420 PT6A-6, -6A, -6B,-6/C20, -20, -20B

1 1 5000

3011711 PT6A-27 1 1 12000

3012811 PT6A-6, -6A, -6B,-6/C20, -20, -20B

1 1 6000






3. Accomplishment Instructions (Cont’d)

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


Abbr’dCycleFactor

FlightCountFactor


3013111 PT6A-6, -6A, -6B,-6/C20, -20, -20A,-20B, -21, -27, -28,-34, -35, -34B, -36,-114, -114A, -135,-135A

2 1 19000

3013611 PT6A-6, -6A, -6B,-6/C20, -20, -20B

2 1 23000

3014111 PT6A-27 1 1 19000

Stub ShaftCompressor Rotor

3055000-01 Deleted

Rotor Compressor 3076420-01 Deleted

Disk, Compressor(2nd Stage)

3006912 PT6A-6, -6A, -6B,-6/C20, -20, -20B

2 1 20000

3013712 PT6A-6, -6A, -6B,-6/C20, -20, -20A,-20B, -21, -27, -28,-34, -35, -34B, -36,-114, -114A, -135,-135A

2 1 24000

3040312 Deleted

Disk, Compressor(3rd Stage)

3006913 PT6A-6, -6A, -6B,-6/C20, -20, -20B

2 1 20000

3011713 PT6A-6, -6A, -6B,-6/C20, -20, -20A,-20B, -21, -27, -28,-34, -34B, -35, -36,-114, -114A, -135,-135A

2 1 25000

3040213 Deleted

Impeller 3008176 PT6A-6, -6A, -6B 1 1 2600









Abbr’dCycleFactor

FlightCountFactor


3009576 PT6A-6, -6A, -6B,-6/C20, -20, -20B

1 1 33000

3010676 PT6A-6, -6A, -6B 1 1 2600

3011376 PT6A-6, -6A, -6B,-6/C20, -20, -20B

2 1 33000

3011476 PT6A-6, -6A, -6B 1 1 2600

3013176 PT6A-21, -27, -28,-34, -34B, -36, -114,-135

2 1 19000

3013676 PT6A-6, -6A, -6B,-6/C20, -20, -20A,-20B

2 1 33000

3032249 PT6A-21, -27, -28,-34, -34B, -36, -135

2 1 19000

3033292 PT6A-21, -27, -28,-34,-34B, -36, -135

2 1 19000

3027798 PT6A-35, -114A,-135, -135A,

2 1 19000

3027798 Deleted

3035883 PT6A-135, -135A 2 1 19000

Disk, CompressorTurbine

3007111* PT6A-6, -6A, -6B,-6/C20, -20, -20B

20 1 18000

3010311* PT6A-6, -6A, -6B,-6/C20, -20, -20B

20 1 18000

3013411 PT6A-21, -27, -28,-34, -36

4 1 16000

3013411 PT6A-114, -114A 5 1 16000

3013411 PT6A-34B 20 1.35 16000









Abbr’dCycleFactor

FlightCountFactor


3013511* PT6A-6, -6A, -6B,-6/C20, -20, -20A,-20B

20 1 18000

3013711 PT6A-27 3.5 1 18000

3024211 PT6A-135, -135A 10 1 16000

3024211 PT6A-35 1.5 3.2 16000

3076856-01 Deleted

Disk, Power Turbine 3006412 PT6A-6, -6A, -6B,-20

1 1 2300

3010312 PT6A-6, -6A, -6B,-6/C20, -20, -20B

3 1 18000

3010712 PT6A-27 3.5 1 20000

3012712 PT6A-6, -6A, -6B,-6/C20, -20, -20A,-20B

3 1 18000

3012812 PT6A-27, -28, -34 3.5 1 20000

3016712 PT6A-27, -28 3.5 1 20000

3019712 PT6A-34 4 1 20000

3022412 PT6A-20, -20A, -20B,-21, -27, -28, -34

3.5 1 20000

3022512 PT6A-6, -6A, -6B,-6/C20, -20, -20A,-20B

3 1 18000

3122658-01 PT6A-6, -6A, -6B 3 1 18000

3026812 PT6A-20, -20A, -20B 3.5 1 20000

3026812 PT6A-34, -36 4 1 20000

3026812 PT6A-114, -114A 5 1 20000

3026812 PT6A-34B 20 1 20000









Abbr’dCycleFactor

FlightCountFactor


3026812 PT6A-21, -27, -28 3.5 1 20000

3022312 PT6A-135, -135A 10 1 30000

3022312 PT6A-35 10 2 30000

3076855-01 Deleted

E. Life Determination/Calculation

(1) Remaining component life is determined by subtracting the calculated accumulatedtotal cycles from the accumulated total cycle limits shown in the table above.

(2) The accumulated total cycles are calculated as follows, using the factors providedin the table above. Two examples are provided below using the following formula,to illustrate the difference in calculation of accumulated total cycles between anengine operated with full cycles versus an engine operated using a combinationof full and abbreviated cycles.

(3) At repair and overhaul, component life is calculated in accordance with thefollowing formula:

AccumulatedTotal Cycles = [ No. of

Starts + ( No. of Flights - No. of Starts ) ] X Flight Count FactorAbbreviated Cycle Factor







(4) Example No. 1 (Full cycles only - includes flights where starts are not recorded):

EXAMPLE:

Engine Model PT6A-27Part No. 3013111 (Hub, Compressor 1st Stage)Abbreviated Cycle Factor 2No. of Starts 9000No. of Flights 9000Flight Count Factor 1

AccumulatedTotal Cycles = [ 9000 + ( 9000 - 9000 ) ] X 1

2

= [9000 + 0] X 1

= 9000







(5) Example No. 2 (Full and abbreviated cycles):

EXAMPLE:

Engine Model PT6A-27Part No. 3013111 (Hub, Compressor 1st Stage)Abbreviated Cycle Factor 2No. of Starts 3000No. of Flights 9000Flight Count Factor 1

AccumulatedTotal Cycles = [ 3000 + ( 9000 - 3000 ) ] X 1

2

= [3000 + 3000] X 1

= 6000

F. Engine rotating components subject to LCF limits may be modified (i.e. reworked). Themodified component is introduced by an SB, which allows rework of pre-SB componentsto the post-SB configuration. When a component is modified and reidentified with anew part number due to rework action, both pre-SB and post-SB cyclic lives must be takeninto consideration when calculating the total accumulated cycles, as follows:

Total Accumulated Cycles = Pre-SB accumulated total cycles + Post-SB accumulatedtotal cycles.

NOTE: The post-SB accumulated total cycle limit is to be used to determine theremaining LCF life of the modified component.

G. Accumulated total cycles must be marked using a CY prefix, as follows:

(1) The accumulated total cycles between each shop visit, rounded to the nearest 100cycles, must be marked with the last two digits dropped and followed by a dash (-).

(2) A part having LCF cycles of 525, 1,819, and 1,972, at shop visits, would be markedas CY5-18-20- which equals approximately 4,300 accumulated total cycles.

4. Appendix

Not applicable.







COMPRESSOR TURBINE BLADE - REPLACEMENT OF

MODEL APPLICATION

PT6A-21, PT6A-25, PT6A-25A, PT6A-25C, PT6A-27, PT6A-28, PT6A-34, PT6A-34AG, PT6A-34B,PT6A-36, PT6A-114, PT6A-114A

Compliance: CATEGORY 10

Summary: The intent of this Service Bulletin is cancelled. The content of the Service Bulletin isprovided for information only.



Apr 12/1991 PT6A-72-1455Revision No. 3: Oct 17/2013 Cover Sheet











Canadian ECL(s)*

ECCN(s)*

P-ECCN(s)** 9E991

USML (ITAR)*

P-USML**


SUBJECT: Pratt & Whitney Canada Service Bulletin No. PT6A-72-1455, Rev. No. 3, dated Oct17/2013 (P&WC S.B. No. 1455R3) COMPRESSOR TURBINE BLADE - REPLACEMENTOF




v update the superseding statement in Para. 1.B., Concurrent Requirements.

v change the compliance code from ‘‘8’’ to ‘‘10’’.


None.


REVISION HISTORY:

Original Issue: Apr 12/1991Revision No. 1: Sep 04/1992Revision No. 2: Dec 06/1999Revision No. 3: Oct 17/2013


17 October 2013

P&WC S.B. No. 1455R3


A. Effectivity

PT6A-21 Engines.PT6A-25 Engines.PT6A-25A Engines.PT6A-25C Engines.PT6A-27 Engines.PT6A-28 Engines.PT6A-34 Engines.PT6A-34AG Engines.PT6A-34B Engines.PT6A-36 Engines.PT6A-114 Engines.PT6A-114A Engines.


P&WC S.B. No. 1455 is superseded by P&WC S.B. No. 1669.

C. Reason

To introduce an optional compressor turbine blade having a protective coating withimproved resistance to sulfidation.

D. Description

The compressor turbine blades are removed and replaced with similar new bladeshaving an alternative protective coating.

NOTE: Incorporation of this service bulletin does not diminish the requirement toperform compressor washes, as recommended in the engine maintenancemanual, to reduce sulfidation attack.

E. Compliance

CATEGORY 10 - This Service Bulletin is provided for information only.

F. Approval

D.O.T./D.A.A. approved.

G. Manpower

No more man-hours are necessary to include this service bulletin at overhaul.


None.

P&WC No. 82996, 82996A, 82996B, 86407




The export control classification with respect to this document is contained on the back of the locator.Apr 12/1991 PT6A-72-1455Revision No. 3: Oct 17/2013 Page 1 of 4© 1991 Pratt & Whitney Canada Corp.

PRINTED IN CANADA

TURBOPROP ENGINECOMPRESSOR TURBINE BLADE - REPLACEMENT OF



Not changed.


Not applicable.

K. References

Illustrated Parts Catalog P/N 3013244 (PT6A-21, PT6A-27, PT6A-28)Illustrated Parts Catalog P/N 3027544 (PT6A-25, PT6A-25A)Illustrated Parts Catalog P/N 3032144 (PT6A-25C)Illustrated Parts Catalog P/N 3021244 (PT6A-34, PT6A-34AG, PT6A-34B, PT6A-36)Illustrated Parts Catalog P/N 3043514 (PT6A-114, PT6A-114A, PT6A-135, PT6A-135A)Maintenance Manual P/N 3013242 (PT6A-21, PT6A-27, PT6A-28)Maintenance Manual P/N 3027542 (PT6A-25, PT6A-25A)Maintenance Manual P/N 3032142 (PT6A-25C)Maintenance Manual P/N 3021242 (PT6A-34, PT6A-34AG, PT6A-34B, PT6A-36)Maintenance Manual P/N 3043512 (PT6A-114, PT6A-114A, PT6A-135, PT6A-135A)Overhaul Manual P/N 3013243 (PT6A-21, PT6A-27, PT6A-28)Overhaul Manual P/N 3027543 (PT6A-25, PT6A-25A)Overhaul Manual P/N 3032143 (PT6A-25C)Overhaul Manual P/N 3021243 (PT6A-34, PT6A-34AG, PT6A-34B, PT6A-35, PT6A-36,

PT6A-114, PT6A-114A, PT6A-135, PT6A-135A)P&WC S.B. No. 1669


Illustrated Parts Catalog P/N 3013244 (PT6A-21, PT6A-27, PT6A-28)Illustrated Parts Catalog P/N 3027544 (PT6A-25, PT6A-25A)Illustrated Parts Catalog P/N 3032144 (PT6A-25C)Illustrated Parts Catalog P/N 3021244 (PT6A-34, PT6A-34AG, PT6A-34B, PT6A-36)Illustrated Parts Catalog P/N 3043514 (PT6A-114, PT6A-114A, PT6A-135, PT6A-135A)


Interchangeability - Refer to Para. 2.C.

Intermixability - The old blades P/N 3102401-01 are intermixable with the new bladesP/N 3039901.



Not applicable.




The export control classification with respect to this document is contained on the back of the locator.Apr 12/1991 PT6A-72-1455Revision No. 3: Oct 17/2013 Page 2 of 4




You can get the procurable parts listed in Para. 2.C. from any Pratt & Whitney CanadaParts Distribution Center.

The estimated total cost of new parts needed to replace old partsis $18,873.20 (US, 1999).





Est. UnitList Price

($US,1999)


For information only:

3039901 Blade, Compressor Turbine 3102401-01 58 325.40 (A)(B)(C)

(A) TWO WAY INTERCHANGEABLE - (ATA 200 Explanation Code 02):The old or the new part can replace the old or the new part.

(B) Discard the part if it is unserviceable. Return a serviceable part to stock.

(C) Old blades 3102401-01 and new blades 3039901 are intermixable.


None.


Not applicable.


NOTE: The accomplishment instructions that follows are for information only.

A. Remove the parts listed under Old P/N in Para. 2.C., Material Information, per theapplicable overhaul manual instructions.

B. Install the parts listed under New P/N in Para. 2.C., Material Information, per theapplicable maintenance or overhaul manual instructions.







C. Write accomplishment of P&WC S.B. No. 1455 in the applicable engine module logbook.

4. Appendix

Not applicable.






BULLETIN INDEX LOCATOR72-50-02

TURBOPROP ENGINECOMPRESSOR TURBINE DISK BALANCING ASSEMBLY AND BLADES -

REPLACEMENT/MODIFICATION OF

MODEL APPLICATION

PT6A-21, PT6A-25, PT6A-25A, PT6A-25C, PT6A-27, PT6A-28, PT6A-34, PT6A-34AG, PT6A-34B,PT6A-36, PT6A-114, PT6A-114A, PT6D-114A


Summary: Under adverse environmental operating conditions, the coating (CPW333) used onthe compressor turbine blades does not have sufficient resistance to sulphidation.Introduce an alternative compressor turbine blade with an improved coating (CPW 550)which provides increased resistance to sulphidation.



Aug 19/1997 PT6A-72-1521Revision No. 5: Nov 25/2013 Cover Sheet











Canadian ECL(s)*

ECCN(s)*

P-ECCN(s)** 9E991

USML (ITAR)*

P-USML**


SUBJECT: Pratt & Whitney Canada Service Bulletin No. PT6A-72-1521, Rev. No. 5, dated Nov25/2013 (P&WC S.B. No. 1521R5) COMPRESSOR TURBINE DISK BALANCINGASSEMBLY AND BLADES - REPLACEMENT/MODIFICATION OF




v Reinstate the SB for PT6A-21, PT6A-25, PT6A-25A, PT6A-25C, PT6A-27, PT6A-28


None.


REVISION HISTORY:

Original Issue: Aug 19/1997Revision No. 1: May 28/1998Revision No. 2: Jan 22/1999Revision No. 3: Jan 11/2000Revision No. 4: Oct 17/2013Revision No. 5: Nov 25/2013


25 November 2013



A. Effectivity

All PT6A-21, -25, -25A, -25C EnginesAll PT6A-27 Engines and all engines converted to Engine Model PT6A-27 (Ref. engine

conversion SB1214)All PT6A-28 Engines and all engines converted to Engine Model PT6A-28 (Ref. engine

conversion SB1120)All PT6A-34 Engines and all engines converted to Engine Model PT6A-34 (Ref. engine

conversion SB1499)All PT6A-34AG Engines and all engines converted to Engine Model PT6A-34AG (Ref.

engine conversion SB1252)All PT6A-34B EnginesAll PT6A-36 Engines and all engines converted to Engine Model PT6A-36 (Ref. engine

conversion SB1405)PT6A-114 Engines which are before and include Serial No. PCE-17497PT6A-114 Engines which are before and include Serial No. PCE-PB0517PT6A-114A Engines which are before and include Serial No. PCE-19423 and all engines

converted to Engine Model PT6A-114A (Ref. engine conversion SB1453)PT6A-114A Engines which are before and include Serial No. PCE-PC0507 and all

engines converted to Engine Model PT6A-114A (Ref. engine conversion SB1453)All PT6D-114A Engines


For the PT6A-114, PT6A-114A P&WC S.B. No. 1521 is superseded by P&WC S.B.No. 1669.

For the PT6A-34, PT6A-34AG, PT6A-34B, PT6A-36 P&WC S.B. No. 1521 is supersededby P&WC S.B. No. 1690.

C. Reason

(1) Problem

Field operators are requesting that the coating used on compressor turbine bladesbe changed.

(2) Cause

Current coating (CPW333) used on compressor turbine blades does not havesufficient resistance to sulphidation under adverse environmental operatingconditions.

(3) Solution

Introduce an alternative compressor turbine blade with a coating (CPW550) whichprovides increased resistance to sulphidation.

P&WC No. B8888A, B8888B, B8888C, B8888D




The export control classification with respect to this document is contained on the back of the locator.Aug 19/1997 PT6A-72-1521Revision No. 5: Nov 25/2013 Page 1 of 5© 1997 Pratt & Whitney Canada Corp.

PRINTED IN CANADA




D. Description

Replace the compressor turbine blades with similar compressor turbine bladesincorporating a coating (CPW550) which provides improved resistance to sulphidation.

NOTE: Incorporation of this service bulletin does not diminish the requirement to performcompressor washes, as recommended in the engine maintenance manual, toreduce sulphidation attack.

E. Compliance

CATEGORY 8 - This service bulletin is optional and can be done at the discretion ofthe operator.

F. Approval


G. Manpower



None.


Not changed.


Not applicable.

K. References

Illustrated Parts Catalog P/N 3013244 (PT6A-21, PT6A-27, PT6A-28)Illustrated Parts Catalog P/N 3027544 (PT6A-25, PT6A-25A)Illustrated Parts Catalog P/N 3032144 (PT6A-25C)Illustrated Parts Catalog P/N 3021244 (PT6A-34, PT6A-34AG, PT6A-34B, PT6A-36)Illustrated Parts Catalog P/N 3043514 (PT6A-114, PT6A-114A, PT6A-135, PT6A-135A)Maintenance Manual P/N 3013242 (PT6A-21, PT6A-27, PT6A-28)Maintenance Manual P/N 3027542 (PT6A-25, PT6A-25A)Maintenance Manual P/N 3032142 (PT6A-25C)Maintenance Manual P/N 3021242 (PT6A-34, PT6A-34AG, PT6A-34B, PT6A-36)




The export control classification with respect to this document is contained on the back of the locator.Aug 19/1997 PT6A-72-1521Revision No. 5: Nov 25/2013 Page 2 of 5




Maintenance Manual P/N 3043512 (PT6A-114, PT6A-114A, PT6A-135, PT6A-135A)Overhaul Manual P/N 3013243 (PT6A-21, PT6A-27, PT6A-28)Overhaul Manual P/N 3027543 (PT6A-25, PT6A-25A)Overhaul Manual P/N 3032143 (PT6A-25C)Overhaul Manual P/N 3021243 (PT6A-34, PT6A-34AG, PT6A-34B, PT6A-35, PT6A-36,

PT6A-114, PT6A-114A, PT6A-135, PT6A-135A)P&WC S.B. No. 1453, SB1268, SB1267, SB1206, SB1214, SB1120, SB1499, SB1252,

SB1405 (Conversion Bulletin)PWA Overhaul Standard Practices Manual P/N 585005P&WC S.B. No. 1669




Not applicable.



Not applicable.



CT Disk Balancing Assembly

The estimated total cost of new parts needed to replace old parts is $57237.25 (US, 1997).


CT Blades replacement

The estimated total cost of new parts needed to replace old parts is $31165.14 (US, 1997).











Est. UnitList Price

($US,1997)


PT6A-21, PT6A-25, PT6A-25A, PT6A-25C, PT6A-27, PT6A-28, PT6A-34, PT6A-34AG,PT6A-34B, PT6A-36 engine models:

3045741-01 Blade - Turbine 3102401-01 58 534.00 (A)

Consumable Materials Required:

3018240 Rivet - Tubular, 0.0805 x0.745 Countersunk

58 3.33


For PT6A-114, PT6A-114A and PT6D-114A engine models:

3045761-01 Disk Balancing Assembly -Compressor Turbine

3102421-01 1 57237.25 (A)(B)

3045741-01 Ê Blade - Turbine 3102401-01 58 534.00 (A)


(B) To get the new part it is possible to make a modification to the old part, or you can get thenew part from any Pratt & Whitney Canada Distribution Center.


The following list of parts can be reworked:

OLD P/N NEW P/N

3102421-01 3045761-01


Not applicable.


A. Refer to the overhaul manual for instructions:

(1) For all engine models (excluding PT6A-34, PT6A-34AG, PT6A-34B, PT6A-36,PT6A-114, -114A and PT6D-114A):








(a) Remove 58 rivets P/N 3018240.

(b) Remove 58 compressor turbine blades P/N 3102401-01.

(c) Install 58 new compressor turbine blades P/N 3045741-01 with 58 new rivetsP/N 3018240.

(d) Write ‘‘P&WC S.B. No. 1521 Incorporated’’ in the engine log book.

NOTE: Engines incorporating less than the full set of the compressor turbineblades P/N 3045741-01, write in the engine log book the number ofthe new blades installed.

4. Appendix

Not applicable.








FUEL CONTROL UNIT - MODIFICATION/REPLACEMENT OF

MODEL APPLICATION

PT6A-6, PT6A-6A, PT6A-6B, PT6A-20, PT6A-20A, PT6A-20B, PT6A-21, PT6A-25, PT6A-25A,PT6A-25C, PT6A-27, PT6A-28, PT6A-34, PT6A-34B, PT6A-34AG, PT6A-36, PT6A-114,

PT6A-114A, PT6A-135, PT6A-135A


Summary: The supplier of the Fuel Control Unit (FCU) can no longer provide the unit ascurrently defined. The current design of the unit’s P3 bellows assembly has beendiscontinued. Introduce a new FCU which has a new P3 bellows assembly.



Apr 19/1999 PT6A-72-1568Revision No. 7: Oct 24/2013 Cover Sheet











Canadian ECL(s)*

ECCN(s)*

P-ECCN(s)** 9E991

USML (ITAR)*

P-USML**


SUBJECT: Pratt & Whitney Canada Service Bulletin No. PT6A-72-1568, Rev. No. 7, dated Oct24/2013 (P&WC S.B. No. 1568R7) FUEL CONTROL UNIT - MODIFICATION/REPLACEMENT OF



SUMMARY: This service bulletin is revised to correct the engine serial numbers in Para. 1.A.,Planning Information.


None.


REVISION HISTORY:

Original Issue: Apr 19/1999Revision No. 1: Aug 08/2000Revision No. 2: Sep 07/2001Revision No. 3: Feb 28/2005Revision No. 4: May 06/2005Revision No. 5: Oct 31/2007Revision No. 6: Nov 16/2007Revision No. 7: Oct 24/2013


24 October 2013



A. Effectivity

PT6A-6 Engines.PT6A-6A Engines.PT6A-6B Engines.PT6A-20 Engines.PT6A-20A Engines.PT6A-20B Engines.PT6A-21 Engines which are before and include Serial No. PCE-PE0193 and Serial No.

PCE-24301 thru PCE-25931.PT6A-25 Engines which are before and include Serial No. PCE-58412.PT6A-25A Engines which are before and include Serial No. PCE-48757PT6A-25C Engines which are before and include Serial No. PCE-PF0043 and Serial No.

PCE-26001 thru PCE-26441.PT6A-27 Engines which are before and include Serial No. PCE-PG0069 and Serial No.

PCE-40001 thru PCE-42771, PCE-47001 thru PCE-47015.PT6A-28 Engines which are before and include Serial No. PCE-52696.PT6A-34 Engines which are before and include Serial No. PCE-RB0045 and Serial No.

PCE-57001 thru PCE-57521.PT6A-34AG Engines which are before and include Serial No. PCE-PH0165, and Serial

No. PCE-57001 thru PCE-57528.PT6A-34B Engines which include Serial No. PCE-54001 thru PCE-54137.PT6A-36 Engines which are before and include Serial No. PCE-38215.PT6A-114 Engines which are before and include Serial No. PCE-PB0527 and Serial No.

PCE-17001 thru PCE-17497.PT6A-114A Engines which are before and include Serial No. PCE-PC0655 and Serial

No. PCE-19101 thru PCE-19423.PT6A-135 Engines which are before and include Serial No. PCE-RE0002 and Serial No.

PCE-92001 thru PCE-92772.PT6A-135A Engines which are before and include Serial No. PCE-PZ0023 and Serial

No. PCE-35001 thru PCE-35101.


None.

C. Reason

(1) Problem

The Fuel Control Unit (FCU) supplier can no longer provide the unit as currentlydefined.

(2) Cause

The supplier of the P3 bellows assembly has discontinued this bellows design.

P&WC No. C4379B, C4379C, C4379R, C4379T, C9985E, C9985C, C9985J, C9985N, DCR21029




The export control classification with respect to this document is contained on the back of the locator.Apr 19/1999 PT6A-72-1568Revision No. 7: Oct 24/2013 Page 1 of 35© 1999 Pratt & Whitney Canada Corp.

PRINTED IN CANADA

TURBOPROP ENGINEFUEL CONTROL UNIT - MODIFICATION/REPLACEMENT OF


(3) Solution

Introduce a new FCU which has a new P3 bellows assembly.

D. Description

Replace or modify the FCU.

E. Compliance

CATEGORY 7 - You can do this service bulletin when the supply of superseded partsis fully used.

F. Approval


G. Manpower

Once you have access to the part, an estimate of 2 man-hours is required to includethis service bulletin at maintenance.



None.


Not changed.


Not applicable.

K. References

Illustrated Parts Catalog P/N 3015444 (PT6A-6, PT6A-6A, PT6A-6B, PT6A-20,PT6A-20A, PT6A-20B)








For P/N 2524439-7

Honeywell Inc. SB No. 2524439-73-7Component Maintenance Manual P/N 73-20-28

For P/N 2524440-8


For P/N 3244745-4

Honeywell Inc. SB No. 3020586-73-5

For P/N 3244746-10


For P/N 3244775-7


For P/N 3244777-5


For P/N 3244786-7


For P/N 3244788-7


For P/N 3244789-3

Honeywell Inc. SB No. 3244789-73-3

For P/N 3244791-4








For P/N 3244809-8


For P/N 3244834-5


For P/N 3244872-3


For P/N 3244897-4



Illustrated Parts Catalog P/N 3015444 (PT6A-6, PT6A-6A, PT6A-6B, PT6A-20,PT6A-20A, PT6A-20B)




Intermixability - Not changed.



Not applicable.









The estimated total cost of new parts needed to replace old parts is $Quote (US, 2007).











Est. UnitList Price

($US,2007)


For Engines PT6A-6, PT6A-6A, PT6A-6B, PT6A-20, PT6A-20A, PT6A-20B:

Fuel Control, TurbopropSupplier (06848)P&WC P/N 3045119-01

2524439-6 1 (A)(B)

2524439-7 Fuel Control, TurbopropSupplier (06848)P&WC P/N 3045119-02

1 Quote (C)

For Engine PT6A-21:


3244745-3 1 (A)(B)

3244745-4 Fuel Control UnitSupplier (06848)(P&WC P/N 3049652-01)

1 43,307.00 (C)


3244775-6 1 (A)(B)


1 Quote (C)

For Engine PT6A-25 (BS734):


3244746-9 1 (A)(B)


1 Quote (C)







Est. UnitList Price

($US,2007)


For Engines PT6A-25, PT6A-25A:


3244745-3 1 (A)(B)


1 43,307.00 (C)


3244775-6 1 (A)(B)


1 Quote (C)

For Engine PT6A-25C:


3244789-2 1 (A)(B)


1 Quote (C)


3244809-7 1 (A)(B)


1 Quote (C)

For Engine PT6A-27:


2524440-7 1 (A)(B)


1 Quote (C)







Est. UnitList Price

($US,2007)



3244786-6 1 (A)(B)


1 Quote (C)


3244872-2 1 (A)(B)


1 51,979.00 (C)

For Engine PT6A-28:


2524440-7 1 (A)(B)


1 Quote (C)


3244786-6 1 (A)(B)


1 Quote (C)

For Engine PT6A-34:


3244777-4 1 (A)(B)


1 Quote (C)


3244789-2 1 (A)(B)







Est. UnitList Price

($US,2007)



1 Quote (C)


3244809-7 1 (A)(B)


1 49,176.00 (C)


3244834-4 1 (A)(B)


1 Quote (C)

For Engine PT6A-34B:


3244777-4 1 (A)(B)


1 Quote (C)

For Engine PT6A-34AG:


3244777-4 1 (A)(B)


1 Quote (C)


3244786-6 1 (A)(B)


1 Quote (C)







Est. UnitList Price

($US,2007)



3244789-2 1 (A)(B)


1 Quote (C)


3244872-2 1 (A)(B)


1 51,979.00 (C)


4138008-2 1 (A)(B)


1 Quote (C)

For Engine PT6A-36 (BS621):


3244791-3 1 (A)(B)


1 Quote (C)

For Engine PT6A-36:


3244777-4 1 (A)(B)


1 Quote (C)


3244786-6 1 (A)(B)







Est. UnitList Price

($US,2007)



1 Quote (C)


3244789-2 1 (A)(B)


1 Quote (C)


3244809-7 1 (A)(B)


1 Quote (C)

For Engine PT6A-114:


3244789-2 1 (A)(B)


1 Quote (C)


3244809-7 1 (A)(B)


1 Quote (C)

For Engine PT6A-114A:


3244789-2 1 (A)(B)


1 Quote (C)







Est. UnitList Price

($US,2007)


Fuel Control, TurbopropSupplier(06848)P&WC P/N 3122678-03

3244897-3 1 (A)(B)


1 Quote (C)


3244809-7 1 (A)(B)


1 Quote (C)

For Engine PT6A-135:


3244777-4 1 (A)(B)


1 Quote (C)


3244789-2 1 (A)(B)


1 Quote (C)


3244809-7 1 (A)(B)


1 49,176.00 (C)

For Engine PT6A-135A:


3244777-4 1 (A)(B)







Est. UnitList Price

($US,2007)



1 Quote (C)


3244789-2 1 (A)(B)


1 Quote (C)


3244809-7 1 (A)(B)


1 49,176.00 (C)

For Engines PT6A-135 and PT6A-135A:


3244788-6 1 (A)(B)


1 Quote (C)

For Engine PT6D-114A:


3244789-2 1 (A)(B)


1 Quote (C)


3244897-3 1 (A)(B)


1 48,870.00 (C)







Est. UnitList Price

($US,2007)



(B) Return the old part(s) to:An authorized accessory shop that can do the modification, or sendto:

Pratt & Whitney CanadaAccessories Services 333 rue d’Auvergne (Area 2K)Longueuil QuebecCanada J4H 3Y3

TEL: (450) 442-6837FAX: (450) 442-6810

(C) To get the new part it is possible to make a modification to the old part, or you can get thenew part from any Pratt & Whitney Canada Distribution Center.



OLD P/N NEW P/N

2524439-6 2524439-7(P&WC P/N 3045119-01) (P&WC P/N 3045119-02)2524440-7 2524440-8(P&WC P/N 3045120-01) (P&WC P/N3049625-01)3244745-3 3244745-4(P&WC P/N 3045123-01) (P&WC P/N3049652-01)3244746-9 3244746-10(P&WC P/N 3045127-01) (P&WC P/N3045127-02)3244775-6 3244775-7(P&WC P/N 3045131-01) (P&WC P/N3049633-01)3244777-4 3244777-5(P&WC P/N 3045132-01) (P&WC P/N3049634-01)3244786-6 3244786-7(P&WC P/N 3045133-01) (P&WC P/N3049635-01)3244788-6 3244788-7(P&WC P/N 3045135-01) (P&WC P/N3045135-02)3244789-2 3244789-3






OLD P/N NEW P/N

(P&WC P/N 3045137-01) (P&WC P/N 3045137-02)3244791-3 3244791-4(P&WC P/N 3045107-01) (P&WC P/N3049639-01)3244809-7 3244809-8(P&WC P/N 3122696-02) (P&WC P/N3122696-03)3244834-4 3244834-5(P&WC P/N 3045139-01) (P&WC P/N3049640-01)3244872-2 3244872-3(P&WC P/N 3049944-01) (P&WC P/N3049641-01)3244897-3 3244897-4(P&WC P/N 3122678-03) (P&WC P/N3122678-04)4138008-2 4138008-3(P&WC P/N 3048965-02) (P&WC P/N3048965-03)


Not applicable.


A. Remove the parts listed under old P/N in Para. 2.C., Material Information, per theapplicable maintenance manual instructions.

B. Install the parts listed under New P/N in Para. 2.C., Material Information, refer to theapplicable maintenance manual instructions.


4. Appendix

A. Refer to Figure 1 for the PT6A-6/6A/6B and PT6A-20/20A/20B FCU - Part Progression.

B. Refer to Figure 2 for the PT6A-21 FCU - Part Progression.

C. Refer to Figure 3 for the PT6A-25 (BS734) FCU - Part Progression.

D. Refer to Figure 4 for the PT6A-25/25A FCU - Part Progression.

E. Refer to Figure 5 for the PT6A-25C FCU - Part Progression.

F. Refer to Figure 6 for the PT6A-27/28 FCU - Part Progression.






4. Appendix (Cont’d)

G. Refer to Figure 7 for the PT6A-34/34B/34AG FCU - Part Progression.

H. Refer to Figure 8 for the PT6A-36 (BS621) FCU - Part Progression.

I. Refer to Figure 9 for the PT6A-36 FCU - Part Progression.

J. Refer to Figure 10 for the PT6A-114/114A FCU - Part Progression.

K. Refer to Figure 11 for the PT6A-135/135A FCU - Part Progression.






2524229(3009474)

2524316−7(3013505)PD273/727

2524439−1(3015525)

2524439−2(3015525A)

2524439−3(3015525B)

PD376

2524439−4(3015525C)

2524439−5(3015525D)

PD1430

2524196(3009174)

2524314−7(3013503)PD273/727

2524245(3010074)SB1071

2524259−7(3011874)

PD174

2524288(3009374)

2524315−7(3013504)PD273/727

2524439−6(3045119−01)

SB1561IMPROVED BEARINGS

CC6 PRC02

2524439−7(3045119−02)

SB1568NEW P3 BELLOWS

CC7 PRC02

C72961

PT6A-6/6A/6B, PT6A-20/20A/20B FCU - Part ProgressionFigure 1






3244775−5(3039071)

3244745−2(3027049A)

3244745−3(3045123−01)

SB1561Improved BearingCC 6 PRC 02

3244745−1(3027049)

3244745−4(3049652−01)

SB1568New P3 Bellows

CC 7 PRC 02

3244775−6(3045131−01)


3244775−7(3049633−01)


CC 7 PRC 02

C66761A

PT6A-21 FCU - Part ProgressionFigure 2






3244746−6(3031944)

3244746−7(3039072)SB1472

CC 5 PRC 02

3244746−8(3045199−01)

SB1547CC 8 PRC 02

3244746−9(3045127−01)

SB1561CC 6 PRC 02

3244746−10(3045127−02)

SB1568CC 7 PRC 02

C100056

PT6A-25 (BS734) FCU - Part ProgressionFigure 3






3244746−8(3045199−01)

SB1547CC 8 PRC 02

3244746−3(3027206D)

SB1317

3244746−2(3027206A)

SEE SHEET 2

3244746−4(3027206E)

PD1989

3244746−5(3031944)SB1353

CC 5 PRC 02

3244746−6(3031944B)

3244746−7(3039072)SB1472

CC 5 PRC 02

C66770B

PT6A-25/25A FCU - Part ProgressionFigure 4 (Sheet 1 of 2)






3244745−2(3027049)PD1416

SEE SHEET 1

3244775−5(3039071)SB1472

CC 5 PRC 02

3244775−2(3033280)SB1373

3244775−3(3033366)PD2258

3244775−4(3033366B)

3244775−6(3045131−01)


3244745−3(3045123−01)


3244745−4(3049652−01)


CC 7 PRC 02

3244775−7(3049633−01)

SB1568

CC 7 PRC 02New P3 Bellows

C66771A

PT6A-25/25A FCU - Part ProgressionFigure 4 (Sheet 2)






3244809−7(3122696−02)

SB1561

CC 6 PRC 02

3244809−8(3122696−03)


CC 7 PRC 02

Improved Bearing

3244809−3(3034361C)

SPB39

3244809−1(3034361)

3244809−4(3039066)SB1472

CC 5 PRC 02

3244809−2(3034361B)

SB1469CC 6 PRC 02

3244789−1(3033013)SB1368

3244771−1(3031910A)

3244789−2(3045137−01)

SB1561

CC 6 PRC 02

3244789−3(3045137−02)


CC 7 PRC 02

Improved Bearing

C66773B

PT6A-25C FCU - Part ProgressionFigure 5






PD727

SEE SHEET 2

2524440−6(3040402)SB1475

CC 8 PRC 01

2524440−5(3015526E)

2524281−1(3011502)

2524440−4(3015526C)

2524440−7(3045120−01)


(3049625−01)SB1568

New P3 BellowsCC 7 PRC 02

2524440−8

3244872−1(3040059)

(JET CRUZER)

3244872−2(3049944−01)


3244872−3(3049641−01)


CC 7 PRC 02

C66762B

PT6A-27/28 FCU - Part ProgressionFigure 6 (Sheet 1 of 2)






3244786−3(3033367A)

3244786−5(3040397)SB1472

CC 5 PRC 02

3244786−6(3045133−01)


3244786−7(3049635−01)


CC 7 PRC 02

3244786−4(3039070)

3244786−2(3033367)SB1469

CC 6 PRC 02

SEE SHEET 1

C66766B

PT6A-27/28 FCU - Part ProgressionFigure 6 (Sheet 2)






2524440−4(3015526C)

3244777−2(3033009)SB1374

FCU RecalibrationCC 6 PRC 02

2524440−5(3015526E)

3244777−3(3040399)SB1475

New Roller CamCC 8 PRC 01

PD1995Basic A34B/A34AG

Basic A34

3244777−1(3032580)SB1374

3244834−1(3036343)SB1428

SEE SHEET 3

3244777−4(3045132−01)


3244777−5(3049634−01)


CC 7 PRC 02

SEE SHEET 2

C66785C

PT6A-34/34B/34AG FCU - Part ProgressionFigure 7 (Sheet 1 of 4)






3244834−2(3036344)

3244834−4(3045139−01)

SB1561

CC 6 PRC 02

SB1428

SEE SHEET 1

3244834−5(3049640−01)


CC 7 PRC 02

3244834−3(3037721)

3244867−1(3038936)SB1461SB1461CSU264

Improved Bearing

C66786B

PT6A-34/34B/34AG FCU - Part ProgressionFigure 7 (Sheet 2)






(3049635−1)SB1568


3244786−7

(3033367A)

SEE SHEET 1

3244786−2(3033367)SB1469

FCU with Manual OverrideCC 6 PRC 02

3244786−5(3040397)SB1472

Additional SpringCC 5 PRC 02

3244786−3

3244872−1(3040059)SB1557

New BS970

CC 8 PRC 07Single Line

4138008−1(3048965−01)

SB1566Additional Bracket

4138008−2(3048965−02)

SB1566Additional Bracketand Meldin BearingCC 6 PRC 01CC 6 PRC 01

3244786−6(3045133−01)


3244872−2(3049944−01)


(3049641−01)SB1568


3244872−3(3048965−03)


CC 7 PRC 02

4138008−3

C66787B







3244809−3(3034361C)

3244809−7(3122696−02)

SB1561

CC 6 PRC 02

PB39

BS952/BS1009

3244809−8(3122696−03)


CC 7 PRC 02

3244809−2(3034361B)

Improved Bearing

3244809−1(3034361)

3244809−4(3039066)

3244789−1(3033013)SB1368

3244771−1(3031910)

3244789−2(3045137−01)

SB1561

CC 6 PRC 02

3244789−3(3045137−02)


CC 7 PRC 02

Improved Bearing

C66788B







3244791−1(3033349)

3244791−2(3033473)PD2227

CC 6 PRC 02

3244791−3(3045107−1)

SB1561CC 6 PRC 02

3244791−4(3049639−1)

SB1568CC 7 PRC 02

C100057

PT6A-36 (BS621) FCU - Part ProgressionFigure 8






2524440−5(3015526E)

Basic

3244777−1(3032580)SB1374

3244771−1(3031910)

3244789−1(3033013)SB1368

SEE SHEET 23244791−1(3033349)SB1366

3244791−2(3033473)SB1371

3244777−2(3033009)SB1374

FCU RecalibrationCC 6 PRC 02

SEE SHEET 33244777−3(3040399)SB1475

New Roller CamCC 8 PRC 01

3244777−4(3045132−01)


3244777−5(3049634−01)


CC 7 PRC 02

3244789−2(3045137−01)

SB1561

CC 6 PRC 02

3244789−3(3045137−02)


CC 7 PRC 02

Improved Bearing

C66791C

PT6A-36 FCU - Part ProgressionFigure 9 (Sheet 1 of 3)






SEE SHEET 1

(3034361C)SPB39

3244809−1(3034361)

3244809−7(3122696−02)


3244809−2(3034361B)

3244809−3

(3039066)3244809−4

3244809−8(3122696−03)


CC 7 PRC 02

C66793A

PT6A-36 FCU - Part ProgressionFigure 9 (Sheet 2)






SEE SHEET 1

(3040397)

3244786−2(3033367)

3244786−6(3045133−01)


3244786−3(3033367A)

3244786−5

3244786−7(3049635−01)


CC 7 PRC 02

C66798B

PT6A-36 FCU - Part ProgressionFigure 9 (Sheet 3)






SEE SHEET 2

(3034361C)SPB39

3244809−1(3034361)

3244809−5(3122678−01)

SB1525

CC 8 PRC 02

3244809−2(3034361B)

3244809−3

(3039066)3244809−4

SPB1472

(0IR3034361)SB1525

3244809−5−4

A−114A Only

A−114A Only

3244789−2(3045137−01)

SB1561

CC 6 PRC 02

3244789−3(3045137−02)


CC 7 PRC 02

Improved Bearing

3244789−1(3033013)

3244809−7(3122696−02)

SB1561

CC 6 PRC 02

Improved Bearing

3244809−8(3122696−03)

SB1568R5

CC 7 PRC 02

New P3 Bellows

C73919D

PT6A-114/114A FCU - Part ProgressionFigure 10 (Sheet 1 of 2)






SEE SHEET 1

3244897−1(3122678−01A)

SB1529

CC 8 PRC 02

3244897−2(3122678−02)

SB1535

CC 7 PRC 02

3244897−3(3122678−03)

SB1561

CC 6 PRC 02

3244897−4(3122678−04)

SB1568

CC 7 PRC 02

Improved Bearings

New P3 Bellows

PT6A−114A Only

PT6A−114A Only

PT6A−114A Only

PT6A−114A Only

C66767B

PT6A-114/114A FCU - Part ProgressionFigure 10 (Sheet 2)






3244789−1(3033013)

3244809−1(3034361)PD2407

3244809−2(3034361B)

3244809−3(3034361C)

SPB39CC 9 PRC 02

3244809−4(3039066)

SB1472/1546CC 5 PRC 02

3244809−7(3122696−02)

SB1561CC 6 PRC 02

3244809−8(3122696−03)

SB1568CC 7 PRC 02

3244788−3(3033368C)

3244788−4(3039069)SB1472

CC 5 PRC 02

3244788−5(3040398)SB1475

CC 8 PRC 01

3244788−6(3045135−01)

SB1561CC 6 PRC 02

3244788−7(3045135−02)

SB1568CC 7 PRC 02

3244777−2(3033009)SB1364

3244777−3(3040399)SB1475

CC 8 PRC 01

3244777−4(3045132−01)

SB1561

CC 6 PRC 02

3244777−5(3049634−01)

SB1568

CC 7 PRC 02

Improved Bearings

New P3 Bellows

3244777−1(3032589)SB1347

2524440−5(3015526E)

PD1995

2524440−4(3015526C)

3244789−2(3045137−01)

SB1561

CC 6 PRC 02

3244789−3(3045137−02)


CC 7 PRC 02

Improved Bearing

C73918A

PT6A-135/135A FCU - Part ProgressionFigure 11







TURBOPROP ENGINECOMPRESSOR BLEED OFF VALVE - REPLACEMENT OF

MODEL APPLICATION

PT6A-114A

Commercial Support Program No: A99013


Summary: The compressor bleed valve requires further refinement of the orifice pack, becausethe adjustment of the orifice pack is not fully linear. A new compressor bleed valveincorporating an improved orifice pack is introduced.



Feb 18/2000 PT6A-72-1588Revision No. 2: Oct 24/2013 Cover Sheet











Canadian ECL(s)*

ECCN(s)*

P-ECCN(s)** 9E991

USML (ITAR)*

P-USML**


SUBJECT: Pratt & Whitney Canada Service Bulletin No. PT6A-72-1588, Rev. No. 2, dated Oct24/2013 (P&WC S.B. No. 1588R2) COMPRESSOR BLEED OFF VALVE -REPLACEMENT OF



SUMMARY: This service bulletin is revised to change the torque value of self locking screw inPara. 3.E., Accomplishment Instructions.


None.


REVISION HISTORY:

Original Issue: Feb 18/2000Revision No. 1: Jan 31/2001Revision No. 2: Oct 24/2013


24 October 2013



A. Effectivity

PT6A-114A Engines that incorporate P&WC S.B. No. 1510 which are before and includeSerial No. PCE-PC0771, Serial No. PCE-19101 thru PCE-19423 and all enginesconverted to Engine Model PT6A-114A (Ref. P&WC engine conversion SB1453) .


None.

C. Reason

(1) Problem

The compressor bleed valve requires further refinement of the orifice pack.

(2) Cause

The adjustment of the orifice pack is not fully linear.

(3) Solution

Introduce a new compressor bleed valve incorporating an improved orifice pack.

D. Description

Remove and replace the Bleed Off Valve (BOV) with a new one.

E. Compliance

CATEGORY 7 - You can do this service bulletin when the supply of superseded partsis fully used.

F. Approval


G. Manpower

Once you have access to the part, an estimate of 1.0 man-hours is required to includethis service bulletin at maintenance.



The engine weight will increase by 0.10 pounds (0.05 kgs).

P&WC No. C2814L, DCR21030




The export control classification with respect to this document is contained on the back of the locator.Feb 18/2000 PT6A-72-1588Revision No. 2: Oct 24/2013 Page 1 of 12© 2000 Pratt & Whitney Canada Corp.

PRINTED IN CANADA



The effect of weight change on the engine center of gravity is negligible.


Not changed.


Not applicable.

K. References

Illustrated Parts Catalog P/N 3043514 (PT6A-114, PT6A-114A, PT6A-135, PT6A-135A)Honeywell (Grimes Aerospace) SB 540-1407-75-SB02


Illustrated Parts Catalog P/N 3043514 (PT6A-114, PT6A-114A, PT6A-135, PT6A-135A)Honeywell (Grimes Aerospace) CMM 75-31-44






Please refer to Commercial Support Program Notification (CSPN) A99013



The estimated total cost of new parts needed to replace old parts is $7,821.80 (US, 2000).

The new parts are scheduled to be available in Mar 2000.




The export control classification with respect to this document is contained on the back of the locator.Feb 18/2000 PT6A-72-1588Revision No. 2: Oct 24/2013 Page 2 of 12





Est. UnitList Price

($US,2000)


Valve Assembly,Compressor BleedVendor (077L2)P&WC P/N 3049038-02

540-1407-3 1 (A)(B)(C)

540-1407-4 Valve Assembly,Compressor BleedVendor (077L2)P&WC P/N 3049038-03

1 7,821.80 (A)(B)


(B) To get the new part it is possible to make a modification to the old part, or you can get thenew part from any Pratt & Whitney Canada Distribution Center.

(C) Return the old part(s) to:

Honeywell Aerospatiale Inc.200 Marcel-Laurin Blv.Montreal QuebecCanada

TEL: 514-748-4415



OLD P/N NEW P/N

540-1407-3 540-1407-4P&WC P/N 3049038-02 P&WC P/N 3049038-03


Tool No. NomenclatureEst. Price

($US, 2000) Delivery

PWC50933-02 Thermocouple probeand extension cable

QUOTE






Tool No. NomenclatureEst. Price

($US, 2000) Delivery

PWC50933-04 Thermocouple probe QUOTE


CAUTION: THE BOV P/N 3049038-03 IS FOR USE ON PT6A-114A ENGINESINCORPORATING SB1510 ONLY.

NOTE: 1. BOV 3049038-03 is preset to a Px suitable for operation on PT6A-114A engineswith SB1510 incorporated.

NOTE: 2. Comply with the airframe manual requirements prior to running the engine.

A. Do an engine performance check per applicable maintenance manual instructions andacceleration check (Ref. 71-00-00) to verify engine baseline performance andacceleration.

B. Remove the BOV under old P/N in Para. 2.C Material Information, per the applicablemaintenance or overhaul manual instructions.

C. Install the BOV under New P/N in Para. 2.C Material Information, per the applicablemaintenance or overhaul manual instructions.

D. Do an engine performance check per applicable maintenance manual instructions andacceleration check (Ref. 71-00-00) and make sure no significant change in performanceor acceleration has occurred.

E. If the engine shows a significant shift in performance, acceleration or an engine surgeoccurs, verify the closing point of the BOV as follows:

CAUTION: BE CAREFUL TO ENSURE THAT THE BOV CAN OPERATE WITHOUTINTERFERENCE FROM THE PROBE.

(1) Install thermocouple P/N PWC 50933-02 or P/N PWC 50933-04 (Ref. Fig. 1) andextension cable on the BOV (Ref. Fig. 2).

NOTE: It is recommended to remove the ‘‘L’’ shaped bracket from the thermocoupleand to secure the thermocouple to the BOV using the clamp provided withP/N PWC50933-02 and P/N PWC50933-04.

(2) Connect the connector to a multimeter which has a 50 mV full scale deflection, orto a Fluke temperature readout or to a Barfield tester.

(3) Set the cabin bleed air switch to OFF.







(4) Start the engine and slowly increase power up to MAX.

NOTE: Ensure that the multimeter shows a reading, which gradually decreasesand becomes stable as full power is applied.

(5) Slowly reduce power until the multimeter or the temperature indicator just begins toindicate an increase in voltage or in temperature (BOV closing point). Record Ngand OAT at this point.

(6) Reduce power to IDLE and shut down the engine.

(7) Plot the value of Ng at measured OAT as recorded in Step (5), on Figure 3.

(8) Adjust the BOV closing point, as required and repeat steps (3) thru (7), in order thatNg at BOV closing point falls within the guide lines as shown on Figure 3.

NOTE: The closing point is adjusted by rotation of the adjustment screw (Ref.Fig. 4). A 60 degree clockwise rotation (i.e. one flat of the hexagonaladjustment screw) leads to an increase of Ng closing point of approximately2%. Lock the variable orifice by torquing the small self locking screw to17 to 20 lb.in. (size 3/32 in.).

(9) Remove the thermocouple P/N PWC 50933-02 or P/N PWC 50933-04 from theBOV.

F. Write accomplishment of P&WC S.B. No. 1588 in the applicable engine module logbook.

4. Appendix

A. Refer to Figure 5 for the PT6A-114A BOV part progression.

B. For shop calibration of the new BOV P/N 3049038-03, the closing point should beadjusted to obtain the Px as follows (Ref. Fig. 6):

(1) With a supply pressure of 70 Psia (P3) set adjustment to obtain a Px = 30.5 to 31.2Psia.

NOTE: The closing point is adjusted by rotation of the adjustment screw. A 60degree clockwise rotation (i.e. one flat of the hexagonal adjustment screw)leads to an approximate decrease Px/P3 = 0.02. Lock the variableorifice by torquing the small bolt to 17 to 20 lb.in..






C67577A

Tool P/N PWC50933-02 or P/N PWC50933-04Figure 1






C67573B

Thermocouple and BOV - Installation OfFigure 2 (Sheet 1 of 2)






FWD

C67574

Thermocouple and BOV - Installation OfFigure 2 (Sheet 2)






−20 0 20 40 60 80 100 120

84

86

88

90

92

94

96

98

100

OUTSIDE AIR TEMPERATURE (DEG. F)

Ng (%

)

82

WHEN ADJUSTING BOV, SET WITHIN THIS BAND

C69738

Compressor Bleed Valve Closing PointFigure 3






LOCKING SCREW

BOVADJUSTMENTSCREW

C69736

BOV AdjustmentFigure 4






3100829−07

3114735−01SB1453

Conversion A114 to A114ACC 8 PRC 02

3121248−03SB1510

New Metering PlugCC 5 PRC 07

540−1407−3

SB1579New Grimes BOV

CSU PRC 07

540−1407−3

SB1581New Grimes BOVCC 6 PRC 07

(3049038−03)SB1588

Improved Orifice

CC 7 PRC 02

540−1407−4

Pack

(3049038−02)(3049038−02)

C71587

PT6A-114A Part ProgressionFigure 5






Px DIAGNOSTICPORT

0−50 PSIA

P3INLETPORT

SHUT−OFFVALVE

FILTER

SHOP AIR

REGULATOR

DIFFUSER

FIXEDSECONDARYVENTURIA 10

ADJUSTABLEPRIMARYORIFICE A 20

0−75 PSIA

C69694

Compressor Bleed Valve Test Rig - SchematicFigure 6







TURBOPROP ENGINEACCESSORY GEARBOX (AGB) HOUSING ASSEMBLY - REPLACEMENT OF

MODEL APPLICATION

PT6A-140


Summary: As an interim configuration, replace the Accessory Gearbox (AGB) housing assemblywith one that has a different protective treatment from another supplier and thatincorporates a new chamfer on the AGB bracket mounting boss.


SERVICE BULLETINP&WC S.B. No. 1731

Dec 12/2013 PT6A-72-1731Cover Sheet











Canadian ECL(s)*

ECCN(s)*

P-ECCN(s)** 9E991

USML (ITAR)*

P-USML**


A. Effectivity

PT6A-140 Engines which are between and include Serial No. PCE-VA0090 toPCE-VA0093.


None.

C. Reason

(1) Problem

It can be difficult to procure the accessory gearbox housing assembly and to installthe nut and spacer on the stud at the Accessory Gearbox (AGB) housing flange.

(2) Cause

Longer lead time at the supplier’s facility and excess material at the AGB bracketmounting boss adjacent to the flange.

(3) Solution

Replace the accessory gearbox housing assembly with one that has a differentprotective treatment from another supplier and that incorporates a new chamfer onthe mounting boss.

D. Description

Replace the accessory gearbox housing assembly with the new one.

E. Compliance

CATEGORY 10 - This Service Bulletin is provided for information only.

F. Approval


G. Manpower



None.

P&WC No. E7466A




The export control classification with respect to this document is contained on the back of the locator.Dec 12/2013 PT6A-72-1731Page 1 of 3© 2013 Pratt & Whitney Canada Corp.

PRINTED IN CANADA




Not changed.


Not applicable.

K. References

Overhaul Manual P/N 3075743 (PT6A-140)Illustrated Parts Catalog P/N 3075744 (PT6A-140)


Overhaul Manual P/N 3075743 (PT6A-140)Illustrated Parts Catalog P/N 3075744 (PT6A-140)






Not applicable.


Not applicable.




Est. UnitList Price

($US,2013)



3078987-01 Housing Assy, AccessoryGearbox

3077525-01 1 (A)(C)




The export control classification with respect to this document is contained on the back of the locator.Dec 12/2013 PT6A-72-1731Page 2 of 3



Est. UnitList Price

($US,2013)


3079401-01 Ê Housing, AccessoryGearbox

3077524-01 1 (B)(C)


(B) NOT INTERCHANGEABLE - (ATA 200 Explanation Code 03):The old part must replace the old part; the new part must replace new part.

(C) Discard the part if it is unserviceable. Return a serviceable part to stock.


None.


Not applicable.


NOTE: The accomplishment instructions that follows are for information only.

A. Remove the parts listed under Old P/N in Para. 2.C., Material Information, in accordancewith the overhaul manual instructions as follows:

v Ref. OHM 72-00-00 ENGINE - DISASSEMBLY-3: MODULES AND MAJORSUB-ASSEMBLIES.

B. Install the parts listed under New P/N in Para. 2.C., Material Information, in accordancewith the overhaul manual instructions as follows:

v Ref. OHM 72-00-00 FINAL ASSEMBLY - 1: ENGINE ASSEMBLY.


4. Appendix

Not applicable.







TURBOPROP ENGINETORQUE LIMITER - INSPECTION OF

MODEL APPLICATION

PT6A-140


Summary: This service bulletin documents an inspection to be performed on the Torque Limiterthat are approaching 1,000 hours service time.



Dec 10/2013 PT6A-72-1733Cover Sheet











Canadian ECL(s)*

ECCN(s)*

P-ECCN(s)** 9E991

USML (ITAR)*

P-USML**


A. Effectivity

PT6A-140 with Torque limiter P/N 4138012-2 (P&WC P/N 3055738-01) installed havingSerial Number C79693 and prior.


None.

C. Reason

(1) Problem

An oil leak occurred on the torque limiter after 544 hours of service

(2) Cause

The torque limiter leakage was attributable to the pivot and spring assembly thatbecame loose due to a low torque condition of the retaining screws.

(3) Solution

Perform a one time in-situ inspection of the torque limiters that are approaching1000 hours of service time.

D. Description

Perform a one time in-situ inspection of the torque limiter

E. Compliance

CATEGORY 3 - P&WC recommends that this SB be performed at next scheduledmaintenance not to exceed 150 hrs or within 12 months, whichevercomes first, for torque limiters that have accumulated less than 800hours at time of issue of this SB.

F. Approval

D.A.A. approved

G. Manpower

Once you have access to the part, an estimate of 0.5 man-hours is required to includethis service bulletin at maintenance.


P&WC No. DCR25375




The export control classification with respect to this document is contained on the back of the locator.Dec 10/2013 PT6A-72-1733Page 1 of 4© 2013 Pratt & Whitney Canada Corp.

PRINTED IN CANADA




None.


Not changed.


Not applicable.

K. References

Maintenance Manual P/N 3075742 (PT6A-140)


None.


Not applicable.



Not applicable.


Not applicable.


Not applicable.


None.


Not applicable.







A. Gain access to the torque limiter and do a general visual inspection of torque limiterinstallation and hardware.

B. Do a detailed inspection on the torque limiter pivot spring installation (Ref. Fig. 1), byapplying finger pressure to pivot spring assembly and attempt to rotate spring pivothead clockwise and counterclockwise, and note for signs of movement.

(1) If no evidence of movement is found, no further action is required.

(2) If evidence of movement is detected, replace torque limiter per EMM chapter73-10-09, contact local P&WC FSR and send suspect unit to an authorized facility forrepair.


4. Appendix

Not applicable.






PIVOT SPRINGASSEMBLY

TRY TO ROTATE SPRING PIVOT HEAD IN A CLOCKWISE ANDCOUNTER CLOCKWISE DIRECTION AND LOOK FOR ANY SIGNS OF MOVEMENT

C219712

Torque Limiter InspectionFigure 1






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