COMMONWEALTH OF AUSTRALIA (Civil Aviation Safety Regulations 1998), PART 39 - 106 CIVIL AVIATION SAFETY AUTHORITY
SCHEDULE OF AIRWORTHINESS DIRECTIVES
AIRWORTHINESS DIRECTIVE
For the reasons set out in the background section, the CASA delegate whose signature appears below issues the following Airworthiness Directive (AD) under subregulation 39.1 (1) of CASR 1998. The AD requires that the action set out in the requirement section (being action that the delegate considers necessary to correct the unsafe condition) be taken in relation to the aircraft or aeronautical product mentioned in the applicability section: (a) in the circumstances mentioned in the requirement section; and (b) in accordance with the instructions set out in the requirement section; and (c) at the time mentioned in the compliance section.
Pratt and Whitney Canada Turbine Engines - PT6A Series
AD/PT6A/33 Compressor Rear Hub - Life Limit Review 9/2003
DM
Applicability: All Pratt and Whitney Canada (P&WC) PT6B-36A, and PT6B-36B series engines.
Requirement: 1. Review and correct the critical part records for Compressor Rear Hub part number (P/N) 3018111 in accordance with P&WC Service Bulletin (SB) PT6B- 72-11002 Revision 8, dated 11 June 2003.
2. Remove from service any Compressor Rear Hub found, in compliance with Requirement 1, to have exceeded the published life limit contained in P&WC SB PT6B-72-11002 Revision 8, dated 11 June 2003.
Note: Transport Canada AD CF-2003-16 refers.
Compliance: For Requirement 1: Within 30 days or at next engine shop visit, whichever is the sooner, from the effective date of this Directive.
For Requirement 2: Before further flight. However, in the event that the part cannot be replaced due to the location of the aircraft, the aircraft may be operated to a facility where the part is to be replaced within 25 cycles or 25 flight hours, whichever occurs soonest, following compliance with Requirement 1.
This Airworthiness Directive becomes effective on 30 July 2003.
Background: A recent review of PW&C SB PT6B-72-11002 found an error in the Flight Count Factor (FAF) criteria used in calculating critical life limits of the Compressor Hub P/N 3018111. One engine was found to have exceeded the life limit using the corrected FAF. This Directive therefore requires a review to correct the critical parts record of Compressor Hub’s having P/N 3018111 and to remove them from service if it is calculated that they have exceeded the critical life limit using the amended FAF number.
Jim Coyne
Delegate of the Civil Aviation Safety Authority 24 July 2003
The above AD is notified in the Commonwealth of Australia Gazette on 30 July 2003.
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