AD/BEECH 90/56 Amdt 3 - Fuselage Structural Fatigue (Cth)

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

Beechcraft 90 and 65-90 (King Air) 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/BEECH 90/56 Amdt 2 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/BEECH 90/56 Amdt 3

Fuselage Structural Fatigue 12/2000

Applicability: Models 65-90, 65-A90, B90, C90, C90A and E90.

Requirement: Inspect the fuselage structure, and retire the fuselage life-limited components, in accordance with Section 5-11-00, Fuselage and Associated Structure, in the Beech King Air 90 Maintenance Manual P/N 90-590012-13B7 as Revised July 30 1999.

Compliance: Not later than the times shown in the Beech King Air 90 Maintenance Manual.

Note: Compliance with previous issues of this Directive, satisfies the initial inspection requirements of this issue.

This Amendment becomes effective on 30 November 2000.

Background: The original issue of this AD promulgated a fatigue life limitation for the fuselage. It became effective on 31 March 1981.

Amendment 1 became effective on 7 October 1999 and allowed continued operation beyond the previous life limitation, based on an inspection program developed by the manufacturer and published in the maintenance Manual.