AD/PA-24/41 Amdt 2 - Wing Inspection for Fatigue Cracking (Cth)

COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY SCHEDULE OF AIRWORTHINESS DIRECTIVES

Piper PA-24 (Comanche) Series Aeroplanes

AD/PA-24/41 Amdt 2

Wing Inspection for Fatigue Cracking 12/91

Applicability: All model PA-24 Model PA-24-250 S/N 24-1 and subsequent Model PA-24-260 S/N 24-3642, 24-4000 and subsequent Model PA-24-400 S/N 26-1 and subsequent.

Requirement: Modify the wing skin and visually inspect the left and right wing lower main spar caps and upper main spar attachment plate, in accordance with the Technical Requirements of FAA Emergency Airworthiness Directive 82-19-01 Piper dated 3 September 1982.

Note: The FAA rescinded AD 82-19-01 on 27 April 1988 and no longer supplies copies . A copy of this document is available, free of charge from Manager, Airworthiness and Operations Branch, Civil Aviation Authority, GPO Box 367,CANBERRA ACT 2601.

Compliance: At intervals not exceeding 100 hours time in service. This Directive was originally issued in June 1984. This amendment, which is issued for clarification only and does not affect compliance times, is effective from 12 December 1991.

Background: This requirement is based upon a FAA Directive issued to prevent the possibility of catastrophic wing failure associated with fatigue damage. Amendment 1 to this Directive clarified that the inspection is repetitive. Amendment 2 clarifies that the inspections must be continued for Australian registered aircraft (even though AD 82- 19-01 has been withdrawn by the FAA), because the possibility of fatigue cracking still exists.