AIRWORTHINESS DIRECTIVE
For the reasons set out in the background section, the CASA delegate whose signature appears below revokes Airworthiness Directive (AD) AD/BEECH 76/12 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.
Beechcraft 76 (Duchess) Series Aeroplanes
AD/BEECH 76/12
Amdt 1
Wing Structural Inspections and Fatigue Life Limitation
13/2002
Applicability: All Models.
Requirement: 1. Carry out the Mandatory Inspections as detailed in Section 57-00-00 of the Beechcraft Duchess 76 Maintenance Manual.
When inspecting the Fuselage She ar Fittings P/N 105-420011-5 and -6, look for evidence of the following:
(i) Rivets working loose, sheared or missing.
(ii) Cracking in the bend radii of the Fuselage Shear Fitting.
(iii) Evidence of fretting products which will be generated if the fitting is loose and is moving relative to the fuselage skin.
2. Retire the wing and carry through structure as detailed in Section 4-00-00 of the Beechcraft Duchess 76 Maintenance Manual.
Compliance: For Requirement 1 - At the Initial Inspection and Subsequent Inspection times as detailed in the Mandatory Inspection Schedule, Chart 1, Section 57-00-00 of the Beechcraft Duchess 76 Maintenance Manual.
For Requirement 2 - Upon or prior to achieving 20000 hours’ time in service.
The Compliance times of the original issue of this Airworthiness Directive are not changed by this amendment.
This Amendment becomes effective on 26th December 2002.
Background: The mandatory wing inspections and fatigue life limitation are as determined by the manufacturer from the results of full scale fatigue tests.
Beechcraft 76 (Duchess) Series Aeroplanes
AD/BEECH 76/12 Amdt 1 (continued)
Amendment 1 provides additional guidance for inspection of the Fuselage Shear Fittings. This is the result of several recent events where the fitting has been found cracked or with loose or missing rivets.
The consequences of a cracked or loose Fuselage Shear Fitting may be the loss of wing to fuselage attachment and subsequent damage to the wing and fuselage structure.
The original issue of this AD became effective on 31st March 1983.
David Alan Villiers
Delegate of the Civil Aviation Safety Authority 14 November 2002
The above AD is notified in the Commonwealth of Australia Gazette on 4 December 2002.