Transport Transports Canada Canada TP 7245E



# AIRWORTHINESS DIRECTIVE

The following airworthiness directive (AD) may be applicable to an aircraft which our records indicate is registered in your na me. ADs are issued pursuant to Canadian Aviation Regulation (CAR) 521 Division X . Pursuant to CAR 605.84 and the further details of CAR Standard 625, Appendix H , the continuing airworthiness of a Canadian registered aircraft is contingent upon compliance with all applicable ADs. Failure to comply with the requirements of an AD may invalidate the flight authorization of the aircraft. Alternative means of compliance shall be applied for in accordance with CAR 605.84 and the above-referenced Standard

. This AD has been issued b y the Continuin g Airworthiness Division ( AARDG ) , National Aircraft Certification Branch, Trans p ort Canada, Ottawa, tele p hone 613 952-4357.

Pursuant to CAR 202.51 the registered owner of a Canadian aircraft shall, within seven days, notify the Minister in writing of any change of his or her name or address. To request a change of address, contact the Civil Aviation Communicat ions Centre (AARC) at Place de Ville, Ottawa, Ontario K1A 0N8 , or 1-800-305-2059
, or www.tc.gc.ca/civilaviation/communications/centre/ address.asp

2 4-0022 ( 01-2005 ) 1/2 No

. CF-2013-21
Issue Date 1 August 2013

Number: CF-2013-21
Subject: Compressor Turbine (CT) Blade Failures
Effective: 15 August 2013
Applicability: Pratt & Whitney Canada model PT6A-114 and PT6A-114A engines, with Pre-SB 1669 Configuration CT Blades Installation.
Compliance: As indicated below, unless already accomplished.
Background: There have been a number of reported incident s where Compressor Turbine (CT) blades failures have caused power loss on PT6-114 & PT 6A-114A engines, resulting in in-flight shutdown (IFSD). Investigation by engine m anufacturer Pratt & Whitney Canada (P&WC) has determined that when operated at high power and high temperature settings, the subject CT blades are prone to crack/fracture as result of creep and/or sulfidation.
P&WC issued Service Bulletin (SB) 1669 t hat introduces a newly designed CT blade which has proven to be far less affected by the blade “Creep” phenomenon. A dditionally, to help prevent IFSD by identifying pending Creep induced blade failure of the pre-SB 1669 configuration blades, P&WC has revised the SB 1669 to include specific inspection/maintenance requirements for engi nes with pre-SB 1669 configuration CT blade installation.
An engine power loss or IFSD on a single engine powered aeroplane such as Cessna 208 could result in an unsafe condition. This AD is issued to mandate the compliance with SB 1669R9 requirements to inspect and replac e the existing CT blades on PT6A-114 & PT6A-114A engines with new type of post SB 1669 configuration CT bl a des.

Corrective Actions: Part I - For Engines With 500 or More Hours Air Time Since New That Have Not Been Previously Inspected Or Have Accumulated More Than 500 Hours Air Time Since Last Inspection, Per The MM 72-00-00, Table 601 Requirements:

Within 150 hours of air time from the effe ctive date of this AD, perform a borescope inspection of the CT blades in accordanc e with Accomplishment Instructions in paragraph 3.A of the P&WC SB 1669R9 dated 28 June 2013 or later revisions approved by the Chief, Continuing Airworthiness, Transport Canada.

Part II - For Engines That Have Been Previously Inspected Per MM 72-00-00, Table 601 Requirements:

At intervals not to exceed 500 hours air time since the last inspection, perform a borescope inspection of the CT blades in accordance with the Accomplishment Instructions in paragraph 3.A of the P&WC SB 1669R9 dated 28 June 2013 or later revisions approved by the Chief, Cont inuing Airworthiness, Transport Canada.No. N ° CF-2013-21 2/2

Part III - For All Affected Engines: During the next engine Hot Section Inspection (H SI) as of the effective date of this A D; submit a two-CT blade sample in accordanc e with Accomplishment Instructions in paragraph 3.B of the P&WC SB 1669R9, to P&WC approved overhaul facility for metallurgical evaluation. If the eval uation results are not satisfactory, replace the complete set of CT blades with Post-SB1669 blades in accordance with paragraph 3.C of the P&WC SB 1669R9 dated 28 June 2013 or later revisions approved by the Chief, Continuing Airworthiness, Transport Canada. Part IV - For All Affected Engines:

Within 36 months as of the effective date of this AD, replace all existing CT blades with new CT blades P/N 3072791-01 and/or replace the Compressor Turbine Disk Balancing Assembly with new P/N 3072801-01, as requir ed, in accordance with Accomplishment Instructions in paragraph 3.C of the P&WC SB 1669R9 dated 28 June 2013 or later revisions approved by the Chief Cont inuing Airworthiness, Transport Canada.
Compliance with Part IV of this AD constitutes terminating action of this AD.
Compliance with earlier versions of SB 1669 prio r to the effective date of this AD also meets the Part IV requirements of this AD and constitutes terminating action of this AD.

Authorization: For the Minister of Transport,

ORIGINAL SIGNED BY

Robin Lau Acting Chief, Continuing Airworthiness

Contact: A K Durrani, Continuing Airworthiness, Ottawa, telephone 613-952-4357, facsimile 613-996-9178 or e-mail AD-CN@tc.gc.ca or any Transport Canada Centre.