AD/PA-42/17 - Main Landing Gear Actuator Attachment Bolt

Overview

The Civil Aviation Regulations 1998, as amended by the Legislative Instrument F2006B05983, address safety concerns associated with the main landing gear actuator attachment bolt of the Piper PA-42 (Cheyenne III) Series aeroplanes. Enacted by the Australian Government through the Civil Aviation Safety Authority (CASA), this regulation was introduced to mitigate the risk of bolt failure, which could potentially lead to the inability to retract or extend the main landing gear, thereby compromising aircraft safety. The policy objective of this directive is to ensure the airworthiness of the specified aircraft models by mandating compliance with manufacturer service bulletins to address identified structural vulnerabilities. This legislative instrument targets Piper PA-42 aeroplanes with specific serial numbers, requiring adherence to Piper Service Bulletin 885 concerning the main landing gear actuator attachment bolt. The regulation stipulates that aircraft with over 500 hours of total time in service as of 11 August 1988 must comply with the directive before the next inspection for maintenance release and thereafter every 500 hours of service. Conversely, aircraft with less than 500 hours of total time in service as of the same date must comply before achieving 500 hours and then every 500 hours of service. This approach ensures that all affected aircraft are systematically inspected and maintained to prevent potential safety incidents arising from bolt failure.

Scope and Application

The Civil Aviation Regulations 1998, under Part 39 - 105, govern the application of Airworthiness Directives within Australia. Specifically, AD/PA42/17 pertains to the Piper PA-42 (Cheyenne III) Series aeroplanes and mandates specific actions to address issues with the main landing gear actuator attachment bolt. This legislation applies to Piper PA-42-1000 series aircraft with serial numbers 42-5527001 and subsequent. The directive is concerned with ensuring that the specified bolt is maintained in accordance with Piper Service Bulletin 885 to prevent potential failures that could compromise the aircraft’s landing gear functionality. The requirement for compliance is contingent upon the total time in service of the aircraft, with actions necessary for those exceeding 500 hours as of 11 August 1988 before the next maintenance release inspection and thereafter every 500 hours. For aircraft with less than 500 hours of service by that date, compliance must occur before reaching 500 hours and subsequently every 500 hours. This directive underscores the necessity for regular and rigorous maintenance checks to ensure air safety, reflecting the Civil Aviation Safety Authority's commitment to stringent oversight and safety standards.

Key Provisions

The Civil Aviation Regulations 1998, specifically Part 39 - 105, includes Airworthiness Directives (AD) for various aircraft. One such AD is AD/PA42/17 concerning the Piper PA-42 (Cheyenne III) Series Aeroplanes, particularly focusing on the Main Landing Gear (MLG) Actuator Attachment Bolt. The directive applies to PA42-1000 series aeroplanes with serial numbers 42-5527001 and subsequent (section 1). The requirement is for the action to be taken in accordance with Piper Service Bulletin (SB) 885. The compliance requirement is divided based on the total time in service of the aircraft as of 11 August 1988. For aircraft that have accrued more than 500 hours of total time in service as of that date, the action must be taken prior to the next inspection for Maintenance Release issue after 11 August 1988 and thereafter every 500 hours of time in service (section 1(1)). For aircraft with less than 500 hours of total time in service as of 11 August 1988, the action must be taken prior to achieving 500 hours of total time in service and thereafter every 500 hours of time in service (section 1(2)). The obligations imposed by this AD are clear: operators of PA42-1000 series aeroplanes must ensure that the MLG actuator attachment bolt is inspected and addressed in accordance with the specified timelines. This involves adhering to the manufacturer's Service Bulletin 885, which likely includes detailed instructions on inspecting, replacing, or repairing the bolt as necessary. Operators must maintain accurate records of the aircraft's time in service to determine when these inspections and actions are due. These obligations are essential for ensuring the continued airworthiness of the aircraft and maintaining safety standards. Failure to comply with the requirements set out in AD/PA42/17 may result in serious safety concerns, as the background information indicates that bolt failure could lead to an inability to retract or extend the affected MLG. This could potentially result in severe operational issues and compromise the safety of the flight. Although the specific penalties for non-compliance are not detailed in the text provided, the overarching framework of the Civil Aviation Regulations 1998 typically includes both civil and criminal penalties for non-compliance with airworthiness directives. Civil penalties may include fines, and in severe cases, criminal penalties could apply, including imprisonment. The exact penalties would be determined based on the specific breach and its impact on aviation safety.