Overview

The Civil Aviation Regulations 1998 (Cth) were enacted to ensure the safety of aviation operations in Australia. The particular legislative instrument in focus, F2006B06875, pertains to the Schedule of Airworthiness Directives under Part 39 - 105 of these regulations. This specific Airworthiness Directive, AD/SD3-60/30, addresses the critical issue of potential fatigue cracks in the stub wing and outer wing strut attachment fittings of Short Series SD3-60 aeroplanes, specifically those with serial numbers ranging from SH301 to SH3642. The problem it aims to resolve is the risk of undetected fatigue cracks in these fittings, which could compromise the structural integrity of the wing, leading to potentially catastrophic outcomes. The policy objective is to mandate inspections and ensure ongoing airworthiness through specified intervals to mitigate this risk, with the ultimate goal of maintaining the highest safety standards in civil aviation as overseen by the Civil Aviation Safety Authority. This Airworthiness Directive was issued by the Civil Aviation Safety Authority, reflecting the Commonwealth Government’s commitment to ensuring that all civil aviation activities are conducted safely. Compliance with AD/SD3-60/30 is mandatory for the specified aircraft models, requiring inspections before the accumulation of 9600 flight hours or by 29 November 1990, whichever is later, and subsequently at intervals not exceeding 600 hours. This directive is aligned with the UK Civil Aviation Authority’s classification of the action as mandatory, underscoring the international collaboration in addressing aviation safety concerns. The directive aims to safeguard against the structural failure of the wing fittings through rigorous and regular inspections, pending the development of a permanent modification by the manufacturer.

Scope and Application

The Civil Aviation Regulations 1998, specifically Part 39 - 105, mandates the Civil Aviation Safety Authority to issue Airworthiness Directives (ADs) that are applicable to all aircraft models within the specified serial numbers. The particular directive AD/SD3-60/30 pertains to the stub wing and outer wing strut attachment fittings of Shorts SD3-60 series aeroplanes, serial numbers SH301 to SH3642 inclusive, requiring inspections in accordance with the manufacturer's service bulletin. The directive applies to all entities or individuals operating these aircraft within the Commonwealth of Australia, ensuring compliance with both the Civil Aviation Regulations and the UK Civil Aviation Authority's (CAA) classification of the action as mandatory. The inspections must be conducted prior to the accumulation of 9600 flight hours or by 29 November 1990, whichever is later, and thereafter at intervals not exceeding 600 hours of component time in service. The directive is designed to address the potential risk of undetected fatigue cracks in the wing strut attachment fittings, which could compromise the structural integrity of the aircraft. The compliance with this directive is essential to maintain the airworthiness of the affected aircraft, as the manufacturer works on a modification to eliminate the need for repetitive inspections.

Key Provisions

The Civil Aviation Regulations 1998, specifically under Part 39 - 105, detail the Civil Aviation Safety Authority (CASA) Schedule of Airworthiness Directives (ADs). One such directive, AD/SD3-60/30, pertains to the inspection of stub wing and outer wing strut attachment fittings on Short SD3-60 series aeroplanes. This directive applies to all models with serial numbers ranging from SH301 to SH3642 (Section 11/90). The requirement is to inspect these fittings in accordance with Shorts SD3-60 Service Bulletin SD360-57-12, as stated in the legislation. These inspections must be carried out prior to the aircraft accumulating 9600 flight hours or before 29 November 1990, whichever is later. Following this initial inspection, the inspections must be repeated at intervals not exceeding 600 hours of component time in service. This stringent inspection regime is necessitated by the damage tolerance evaluation of the SD3-30 type fittings, which has indicated that the maximum safe inspection interval is 600 hours. Undetected fatigue cracks in these fittings could potentially result in a loss of structural integrity of the wing. The manufacturer is also in the process of developing a modification to eliminate the need for repetitive inspections. The obligations imposed by this directive are clear and specific. Aircraft operators must ensure that the inspections are conducted by qualified personnel in accordance with the specified bulletin and within the stipulated timeframes. The directive also mandates that any modifications as outlined in Service Bulletin SD360-57-03 will be considered as terminating action for the purposes of this AD. Failure to comply with these requirements could result in serious safety implications, given the potential for structural failure due to undetected fatigue cracks. For breaches of this directive, the consequences can be severe. The legislation does not explicitly detail the penalties for non-compliance; however, under the Civil Aviation Act 1988, CASA has the authority to enforce compliance through various measures, including fines and potentially grounding the aircraft. The specific penalties for non-compliance with ADs are typically detailed in other sections of the Civil Aviation Regulations, but the overarching objective is to ensure the highest safety standards are maintained in civil aviation operations.