Overview

The Civil Aviation Regulations 1998 (CAR 1998) were enacted by the Commonwealth of Australia to ensure the safety of civil aviation in the country. The CAR 1998 is a comprehensive set of regulations that governs various aspects of civil aviation, including airworthiness, licensing, and operations. One specific instrument under this regulation is the Airworthiness Directive (AD) issued by the Civil Aviation Safety Authority (CASA). ADs are issued to address identified safety issues and ensure that corrective actions are taken to mitigate any risks. In the case of AD/F406/5, it was introduced to address the problem of fatigue cracks and elongated bolt holes found in the horizontal stabiliser rear attach structure and the vertical fin rear spar attach structure of Reims Aviation F406 Series Aeroplanes. The policy objective of the AD is to ensure the continued airworthiness of the affected aircraft by requiring inspections and repairs as necessary to prevent structural failure.

Scope and Application

The Airworthiness Directive AD/F406/5 issued under the Civil Aviation Regulations 1998 pertains specifically to the Reims Aviation F406 Series Aeroplanes with serial numbers ranging from F406-0001 to F406-0089. This directive mandates the inspection of the horizontal stabiliser rear attach structure in accordance with Reims Aviation Service Bulletin CAB01-5, dated 12 March 2001. If any cracks or elongated bolt holes are identified, the affected parts must be repaired or replaced before further flight. The initial inspection must be conducted upon the aircraft accumulating 2,500 hours of total time in service, or at the next scheduled Phase 6 (600 hour) inspection if this occurs after 2,500 hours, and for aircraft that have already accumulated more than 2,500 hours at the directive's effective date, the inspection must occur at the next scheduled Phase 6 inspection after 9 August 2001. Subsequent inspections must then be carried out at intervals not exceeding 2,400 hours of time in service following the initial inspection. This directive becomes effective on 9 August 2001 and is applicable within the national jurisdiction of the Commonwealth of Australia.

Key Provisions

The Airworthiness Directive AD/F406/5 issued by the Civil Aviation Safety Authority (CASA) applies specifically to Reims Aviation F406 Series Aeroplanes with serial numbers ranging from F406-0001 to F406-0089. According to section 1 of the AD, the directive mandates inspections and, if necessary, repairs or replacements of the horizontal stabiliser rear attach structure. This requirement is detailed in section 2, which specifies that the inspection must be carried out in accordance with Reims Aviation Service Bulletin CAB01-5, dated 12 March 2001. If any cracks or elongated bolt holes are discovered during this inspection, the affected parts must be repaired or replaced before further flight. The initial inspection must occur at the next scheduled Phase 6 inspection, which is a 600-hour inspection, once the aircraft has accumulated 2,500 hours of total time in service. For aircraft that have already exceeded 2,500 hours of total time in service as of the effective date of this directive, the inspection should be conducted at the next scheduled Phase 6 inspection after 9 August 2001. Subsequent inspections are to be carried out at intervals not exceeding 2,400 hours of time in service following the initial inspection. The obligations imposed on the parties governed by this AD include conducting thorough inspections of the specified aircraft models and ensuring compliance with the instructions outlined in the directive. The responsibility for carrying out these inspections and any necessary repairs falls on the aircraft operator or owner. Furthermore, operators must ensure that the inspections and any corrective actions are documented and logged appropriately to maintain an accurate record of compliance. Section 3 of the AD provides the compliance timeline and specifies the intervals at which repeat inspections must be conducted. Failure to adhere to these requirements can compromise the airworthiness of the aircraft and potentially lead to serious safety issues. Failure to comply with the AD/F406/5 may result in severe consequences. The AD highlights that undetected cracking in the horizontal stabiliser rear attach structure could lead to structural failure of the empennage, posing a significant risk to flight safety. Section 4 of the AD notes that the directive was issued due to reports of fatigue cracks and elongated bolt holes in the specified structures. Regulatory enforcement of this AD is likely to include penalties for non-compliance, though the specific penalties are not detailed within the AD itself. However, general provisions under the Civil Aviation Regulations 1998, which govern CASA’s authority, could impose fines or other sanctions for violations of airworthiness directives. Non-compliance with airworthiness requirements can also result in the grounding of affected aircraft until the necessary repairs are made, further impacting operational readiness and potentially incurring additional costs for the operator.