AD/FU24/58 Amdt 1 - Wing Structural Fatigue Limitation (Cth)

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

Airparts (NZ) Ltd. FU 24 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/FU24/58 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/FU24/58 Amdt 1

Wing Structural Fatigue Limitation 6/2000

Applicability: All model FU24-950, FU24A-950, FU24-954 and FU24A-954 series aeroplanes which are or have been used in agricultural operations.

Requirement: Retire the wing main spar lower cap from service.

Compliance: Upon or prior to achieving 11000 hours time in service in agricultural operations.

This Amendment becomes effective on 15 June 2000.

Background: The wing spar safe fatigue life of 11000 hours in agricultural operations was established on the basis of the manufacturer's fatigue substantiation in accordance with Australian certification requirements, and with due allowance for Australian requirements and operating conditions.

The safe fatigue life estimate for Normal Category operations is approximately 130000 hours. This amendment clarifies that the life limitation relates to flight time accumulated in agricultural operations only.