COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
SCHEDULE OF AIRWORTHINESS DIRECTIVES
Piper PA-46 (Malibu) Series Aeroplanes
AIRWORTHINESS DIRECTIVE
For the reasons set out in the background section, the CASA delegate whose signature appears below revokes Airworthiness Directive (AD) AD/PA-46/19 and issues the following AD under subregulation 39.1 (1) of CAR 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.
AD/PA-46/19
Amdt 1
Wing and Fuselage Structural Fatigue Limitations
11/2000
Applicability: All models.
Requirement: Retire from service the wing main spar lower cap and the fuselage pressure hull.
Note: On the basis of the currently available fatigue substantiation for the aircraft, only one spar cap replacement is permitted. Any proposal for a further extension in life incorporating a second spar cap replacement must be supported by a substantiation covering all the remaining primary structure including the empennage, control surface hinge arms, etc. The substantiation must incorporate a safe life assessment, or a sufficiently rigorous inspection schedule to ensure that any fatigue cracking which could occur in service will be detected before the aircraft is endangered.
Compliance: 1. For the pressure fuselage – prior to exceeding 9200 pressurised flights.
2. For the wing main spar lower cap:
– Model PA-46-310P – prior to exceeding 15600 hours component total time in service.
– Model PA-46-350P – prior to exceeding 10100 hours component total time in service.
This Amendment becomes effective on 2 November 2000.
Background: Fatigue life limitations for the pressure cabin and for the wing spar were determined by the manufacturer in accordance with FAA type certification requirements. The fuselage and wing primary structures are identical in both models, however the -350P wing stress levels are higher than for the -310P, primarily because of the increased aircraft mass. The spar life for the -350P, which in the original issue was stated as “to be determined”, has now been determined on the basis of the higher stress, and following discussions with the manufacturer.
COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
SCHEDULE OF AIRWORTHINESS DIRECTIVES
The original issue of this Airworthiness Directive became effective on 11 July 1991.
David Alan Villiers
Delegate of the Civil Aviation Safety Authority 13 September 2000
The above AD is notified in the Commonwealth of Australia Gazette on 4 October 2000.