AD/BEECH 55/61 Amdt 2 - Wing Fatigue Life Limitation (Cth)

AIRWORTHINESS DIRECTIVE For the reasons set out in the background section, the CASA delegate whose signature appears below revokes Airworthiness Directive (AD) AD/BEECH 55/61 Amdt 1 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 55, 58 & 95-55 (Baron) Series Aeroplanes

AD/BEECH 55/61 Amdt 2

Wing Fatigue Life Limitation 3/2003

Applicability: All models 58, 58A, 58TC, 58P and 58PA series.

Requirement: Retire the wing spar and wing centre section spar low cap (and associated structural fittings) together with the wing rear spar upper and lower attachment fitting assemblies.

The model 58TC and 58P life limitation assumes an average mean cruise weight of 2490kg and one landing every 40 minutes. Should the mean cruise weight be greater than 2540kg or should the landings occur at a greater frequency than one landing every 30 minutes the Authority must be advised as it will be necessary to reassess the life limitation.

Note 1: The wing rear spar attachment fitting assembly includes both fuselage and wing fitting components.

Note 2: On the basis of currently available fatigue substantiating data, only one spar cap replacement is permitted. This will allow a single lifetime extension from spar cap replacement.

Note 3: For aircraft which have had winglets fitted subsequent to manufacture, the retirement life, in hours, is to be calculated using the formula;