Overview

The Civil Aviation Regulations 1998, specifically Part 39 - 105, addresses the safety concerns associated with the Cessna 400 series aeroplanes, excluding models 404 and 441, by issuing Airworthiness Directives (ADs) to ensure the continued airworthiness of these aircraft. This legislative instrument was enacted to mitigate the risk of fatigue and stress corrosion cracking in the wing front spar lower attachment fittings, which have been identified as potential safety hazards. The policy objective behind this directive is to enhance the safety of civil aviation by mandating regular inspections of the specified fittings to prevent catastrophic failures due to undetected cracks. Compliance with these directives is mandatory for all operators of the applicable aircraft models, requiring inspections to be conducted prior to exceeding 5000 hours of component time in service or before the next scheduled maintenance release, whichever is later. This directive was established by the Civil Aviation Safety Authority (CASA) under the authority granted by the Civil Aviation Act 1988. The regulatory approach aims to proactively address potential safety issues before they can result in significant operational risks. The requirement to visually inspect the wing fittings for signs of fatigue and stress corrosion cracks is intended to ensure that any developing issues are detected and addressed in a timely manner, thereby maintaining the overall airworthiness of the aircraft fleet.

Scope and Application

The Civil Aviation Regulations 1998, specifically Part 39 - 105 concerning Airworthiness Directives, mandates that all Cessna 400 series aircraft, excluding models 404 and 441, must adhere to specific maintenance and inspection procedures to ensure their airworthiness. This legislation applies to all operators of these aircraft, requiring them to perform a visual inspection of the wing front spar lower attachment fittings, identified by part number 0822550, for signs of fatigue and stress corrosion cracks. The inspection must be conducted either before the aircraft component reaches 5000 hours of service or before the next scheduled maintenance release, whichever comes later, and then at every subsequent scheduled inspection. The directive is intended to mitigate the risk of structural failure due to undetected cracks in the wing fittings, as evidenced by previous incidents in similar aircraft. This regulation ensures that all relevant aircraft maintain a high standard of safety and reliability, overseen by the Civil Aviation Safety Authority.

Key Provisions

The Civil Aviation Regulations 1998, specifically Part 39 - 105, mandate the issue of an Airworthiness Directive (AD) aimed at addressing identified safety issues in Cessna 400 series aeroplanes. AD/CESSNA 400/92 Amendment 1 focuses on the wing front spar lower attachment fittings, which are prone to fatigue and stress corrosion cracking. This directive applies to all 400 series aircraft except for models 404 and 441 (Section 1). Operators must ensure the fairing between the wing and carry-thru is removed to access the specified fittings (P/N 0822550) for inspection. The inspection process includes visually examining the upper and lower edges of the lug for fatigue cracks and inspecting visible fittings for stress corrosion cracks and surface pitting from inside the wheel well (Section 2). The directive specifies that these inspections should occur before the component time in service reaches 5000 hours or before the next Maintenance Release after 22 March 1989, whichever is later, and subsequently at each scheduled inspection (Section 3). Compliance with AD/CESSNA 400/92 Amendment 1 is mandatory for all applicable aircraft operators. These operators must conduct the specified visual inspections on the wing front spar lower attachment fittings to ensure the aircraft meet airworthiness standards. The directive stipulates that the inspections should be performed without removing the primer, which simplifies the process and ensures that the inspection does not alter the condition of the fittings (Section 4). Operators must document the inspection findings and maintain records of compliance to demonstrate adherence to the regulatory requirements. Failure to comply with the provisions of AD/CESSNA 400/92 Amendment 1 can result in serious safety implications, including potential structural failure of the wing fittings. Such non-compliance may lead to enforcement actions by the Civil Aviation Safety Authority (CASA). In cases of non-compliance, CASA can impose penalties, including fines, suspension or revocation of the aircraft's airworthiness certificate, and other administrative actions. The severity of the penalties depends on the extent and nature of the non-compliance and whether it results in actual harm or potential danger to flight safety.