AD/P68/43 Amdt 5 Wing and Airframe Fatigue Life Limit (Cth)
AIRWORTHINESS DIRECTIVE
On the effective date specified below, and for the reasons set out in the background section, the CASA delegate whose signature appears below revokes Airworthiness Directive (AD) AD/P68/43 Amdt 4 and issues the following AD under subregulation 39.001(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.
Partenavia P68 Series Aeroplanes
| AD/P68/43 Amdt 5 | Wing and Airframe - Fatigue Life Limit | 6/2008 |
Applicability: | All Model P68 series aircraft, all serial numbers. |
Requirement: | Implement the Safe Fatigue Limits (SFL) into the aircraft maintenance program in accordance with the instructions contained in Vulcanair Service Bulletin No. 120 original issue, or Revision 1, or later EASA approved revision. Note 1: EASA AD 2007-0027 refers. Note 2: If your aircraft has a repair or modification that prevents you from fully complying with the above Requirement, you may need an Exclusion to use an alternative method to correct the unsafe condition (See CASR 39.004). |
Compliance: | Before the accumulation of 8,500 flight hours since new or within 500 flight hours after the effective date of this Directive, whichever occurs later. If the Requirement affects a recently-fitted part on your aircraft, you may time the Requirement for that part only by the time on that part. |
| This Amendment becomes effective on 5 June 2008. | |
Background: | To manage structural fatigue of Partenavia P68 airframe, the previous issue of this Directive mandated either retirement, or implementation of a validated structural inspection program for the wing and associated structure, and either inspection or retirement at a safe service life limit for the remaining airframe structure. Amendment 1, effective 15 June 2000, changed the method of control for the wing by implementing a repetitive inspection program, which was prescribed by the RAI, the Italian airworthiness authority. The inspections now include the stabilator. Amendment 2, effective 20 February 2003, added contact details of the Italian Authority, for the reporting of any cracking detected during inspections called out by this Directive. The technical content and compliance times were not changed. Amendment 3, effective 2 October 2003, expanded applicability to all aircraft, and introduced a new Vulcanair service bulletin as the Requirement document for the wing and stabilator structures inspection. |
| Amendment 4 corrected the Requirement 1 repeat inspection interval for aircraft with more than 8,500 total flight hours. Amendment 5 is issued in response to a new EASA AD which, while retaining requirements of superseded ENAC AD 2003-177, allows the implementation of Vulcanair Service Bulletin No. 120 Revision 1. The Safe Fatigue Limits (SFL) of the wing structure have been redefined from the current 8,500 flight hours to a new value to be calculated up to a maximum of 17,500 flight hours. Also, this amendment deletes the Requirement 2 of the previous issue of this Directive. The Authority is discussing, with EASA, how best to manage fatigue in the airframe not covered by Requirement 1 of this Directive. The new Safe Fatigue Limits depend upon: Status of the modification (reinforcement) of the wing structure itself (Partenavia Service Bulletin No. 65 refers); and, Aircraft Flight Hours accumulated before the modification (reinforcement) was implemented. The original issue of this Airworthiness Directive became effective on |
David Villiers
Delegate of the Civil Aviation Safety Authority
15 April 2008
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