AD/F406/1 - Canted Rib Upper Cap

Overview

The Civil Aviation Regulations 1998, specifically PART 39 - 105, addresses safety concerns related to aircraft airworthiness through the Civil Aviation Safety Authority’s schedule of airworthiness directives. One such directive, AD/F406/1, pertains to Reims Aviation F406 Series Aeroplanes and was enacted to address the issue of cracks found in the canted ribs upper cap in the centre wing carry-through area. This problem was identified after several instances of structural failures which prompted the need for stringent inspection and modification protocols to ensure the continued safety of these aircraft in operation. The directive aims to prevent potential in-flight structural failures by requiring regular inspections and necessary modifications based on the findings. The Civil Aviation Regulations 1998 were enacted by the Australian Parliament and are administered by the Civil Aviation Safety Authority, which operates under the Department of Infrastructure, Transport, Regional Development, and Communications. The policy objective of AD/F406/1 is to ensure the safety and reliability of Reims Aviation F406 Series Aeroplanes by mandating specific inspection and modification procedures to mitigate the risk of in-flight structural failure. This directive became effective on 12 May 1999, and compliance is mandatory for all F406 aircraft within the specified serial number range.

Scope and Application

The Civil Aviation Regulations 1998, specifically PART 39 - 105, issued by the Civil Aviation Safety Authority, apply to the Reims Aviation F406 Series Aeroplanes, including all aircraft with serial numbers ranging from F406-0001 to F406-0083. This legislation mandates that operators of these aircraft must inspect the canted ribs upper cap in the centre wing carry-through area for cracks, as per Reims / Cessna Service Bulletin CAB 98-16. This directive applies to all aircraft of the specified model and serial numbers within the Commonwealth of Australia and ensures adherence to safety standards set forth by the Civil Aviation Safety Authority. Compliance with the Airworthiness Directive AD/F406/1 requires an initial inspection before further flight after the effective date of 12 May 1999, with modifications to be installed based on the inspection results, not later than 600 hours of operation or 12 months after the directive becomes effective, whichever is sooner. Repetitive inspections must be carried out at intervals not exceeding 200 hours in service or 12 months after the initial inspection, continuing until the aircraft is modified according to the requirements specified in the directive.

Key Provisions

The Civil Aviation Regulations 1998, specifically Part 39 - 105, mandate the issuance of airworthiness directives for various aircraft models to ensure safety. One such directive is AD/F406/1, which applies to Reims Aviation F406 Series Aeroplanes with serial numbers F406-0001 through F406-0083 (s. 1). This directive requires an inspection of the canted ribs upper cap in the centre wing carry-through area for cracks in accordance with Reims / Cessna Service Bulletin CAB 98-16 (s. 2). For compliance, an initial inspection must be performed before further flight after 12 May 1999 (s. 3(1)). If necessary, a modification must be installed based on the inspection results but no later than 600 hours of operation or 12 months after the directive is effective, whichever comes first (s. 3(2)). Repetitive inspections are required at intervals not exceeding 200 hours time in service or 12 months after the initial inspection, or until the aircraft is modified as specified (s. 3(3)). The obligations under this directive include conducting a thorough inspection of the canted ribs upper cap to detect any cracks that may compromise the structural integrity of the aircraft. Operators of the affected Reims F406 aircraft must ensure that the initial inspection is completed before any further flight after the directive's effective date. Additionally, if the inspection reveals any issues, a modification must be installed within the specified timeframe to rectify the problem. Furthermore, subsequent inspections must be performed at regular intervals to ensure ongoing compliance with the directive. Failure to comply with the requirements set forth in AD/F406/1 can lead to significant consequences. The primary risk is the potential for structural failure during flight, which could result in serious injury or loss of life. Civil Aviation Regulations 1998 impose strict penalties for non-compliance with airworthiness directives. The maximum penalty for a serious breach can include substantial fines and imprisonment, reflecting the critical nature of adhering to safety regulations. Additionally, non-compliance can result in the grounding of the aircraft, leading to operational disruptions and financial losses for the operator. Ensuring adherence to this directive is paramount to maintaining the safety standards required by Australian aviation authorities.