COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
SCHEDULE OF AIRWORTHINESS DIRECTIVES
Piper PA-32 (Cherokee Six) Series Aeroplanes
AD/PA-32/42
Amdt 1
Wing Structural Fatigue Life Limitation 13/96
Applicability: All PA-32 series aircraft, all models. Requirement: 1. Retire from service:
1.1. The wing main spar assembly; and
1.2. The bottom cap of the wing main spar box (carry through). OR
2. Inspect the lower wing joint for fatigue cracks in accordance with an inspection program approved through a District Office of the Authority.
Note 1: For Requirement 1, replace retired components in accordance with approved maintenance data; Regulations 42V and 2A refer.
Note 2: For Requirement 2, acceptable standards for the inspection program are CAO 101.22.3.61 (3) and FAR 23.573.
Compliance: For Requirement 1: Retire before 11000 hours component time in service.
For Requirement 2: Inspect before 11000 hours component time in service, and thereafter at the intervals specified in the approved inspection program.
This Amendment becomes effective on 5 December 1996.
Background: Fatigue analysis predicts the possibility of cracking in the lower wing joint after 11000 hours. Such cracking caused a fatal accident to a similar model with the same style of wing joint.
Amendment 1 re-affirms that all PA-32 series models are subject to the same life limit, even those released after the original issue of this Directive.
Amendment 1 minimises the structure to be retired by limiting it to the components which comprise the lower wing joint. However the Authority has not investigated whether or not it is more practical to replace these components separately instead of replacing the complete wing and carry-through.
Amendment 1 refers to the possibility of inspection as an alternative to retirement.
The original issue of this Airworthiness Directive became effective on 29 October 1976.