Overview

The Civil Aviation Regulations 1998, enacted by the Parliament of the Commonwealth of Australia, are a comprehensive set of regulations designed to ensure the safety of civil aviation within Australia. One specific directive under this regulation, AD/CESSNA 320/23, addresses the inspection requirements for the main landing gear attachment of Cessna 320 series aeroplanes, aiming to identify and mitigate potential safety hazards associated with the landing gear. The policy objective of this directive is to ensure the airworthiness of these aircraft by mandating regular inspections of critical components such as the “U” bolts and attaching shafts for any signs of cracks, thereby maintaining the structural integrity and safety of the aeroplanes. The directive stipulates that the inspection must be conducted with the aeroplane on jacks, requiring the removal of the main landing gear attaching “U” bolts and shafts. Inspectors are to visually examine the “U” bolts and attaching shafts, specifically focusing on the thread root ends and the area around the roll pin hole, using a 10X magnifying glass to detect any cracks. The frequency of these inspections varies depending on the total time in service of the aeroplane, with more stringent requirements placed on components that have achieved certain thresholds of operational hours. This proactive approach is intended to prevent potential failures and ensure the continued compliance with safety standards set forth by the Civil Aviation Safety Authority.

Scope and Application

The Civil Aviation Regulations 1998, under Part 39 - 105 and the Civil Aviation Safety Authority’s Schedule of Airworthiness Directives, apply specifically to all models of the Cessna 320 series aeroplanes, ranging from 320 to 320D inclusive. This legislation mandates particular inspection procedures for the main landing gear attachment components. The requirement involves removing the main landing gear attaching “U” bolts and shafts while the aeroplane is on jacks, followed by a detailed visual inspection of these components. The inspection must be carried out using a 10X magnifying glass to detect any cracks in the area of the thread root ends of the “U” bolts and in the area of the roll pin hole of the attaching shafts. Compliance with these regulations necessitates inspections at specific intervals depending on the accumulated flight hours of the aeroplane. For main landing gear attachment shafts and “U” bolts that have reached 2500 hours at the specified date, inspections must occur within 100 hours and then at intervals not exceeding 200 hours. For other components, inspections must be conducted before they reach 2500 hours and subsequently at intervals not exceeding 200 hours. The legislation is enforced at a national level and applies to all operators and owners of the specified Cessna models within Australian jurisdiction.

Key Provisions

The Civil Aviation Regulations 1998, under Part 39 - 105, contain specific directives concerning the airworthiness of certain aircraft types, including the Cessna 320 series aeroplanes. One such directive, AD/CESSNA 320/23, focuses on the inspection of the main landing gear attachment components (section 1). This directive applies to all models within the 320 series, from 320 to 320D inclusive. The primary requirement outlined in the directive is to visually inspect the main landing gear attaching “U” bolts and shafts for any signs of cracks, using a 10X magnifying glass for clarity (section 2). This inspection must be conducted when the aeroplane is jacked up, ensuring a thorough examination of the thread root ends of the “U” bolts and the area around the roll pin hole of the attaching shafts (section 3). In terms of obligations, operators of Cessna 320 series aeroplanes must adhere to specific timelines and intervals for conducting these inspections (section 1). For main landing gear attachment shafts and “U” bolts that have accumulated 2500 hours of service by 12 August 1975, the first inspection must occur within 100 hours of that date and subsequent inspections should be conducted at intervals not exceeding 200 hours. For all other main landing gear attachment shafts and “U” bolts, inspections must be performed before reaching 2500 hours of service and then at intervals not exceeding 200 hours thereafter (section 1). This ensures that any potential issues are identified and addressed promptly to maintain the airworthiness of the aircraft. Failure to comply with these inspection requirements can result in serious consequences. Although the Civil Aviation Regulations do not explicitly outline specific offences, penalties, or consequences for non-compliance within this particular directive, general provisions under civil aviation law may apply. Non-compliance with airworthiness directives can lead to enforcement actions by the Civil Aviation Safety Authority (CASA), which may include fines, suspension or revocation of an aircraft’s airworthiness certificate, and other regulatory measures. These actions are designed to ensure that aircraft remain safe and compliant with all applicable regulations, ultimately safeguarding the public and maintaining the integrity of the aviation system.