AD/PA-32/19 Amdt 3 - Stabilator Balance Weight Tube Assembly

Overview

The Civil Aviation Regulations 1998, which were enacted by the Parliament of Australia, aim to ensure the safety of civil aviation operations within the country. These regulations were introduced to address the need for comprehensive and enforceable safety standards in the aviation industry. A specific legislative instrument, F2006B05812, pertains to Part 39 - 105 of the Civil Aviation Regulations, focusing on airworthiness directives for particular aircraft models. This instrument amends the stabilator balance weight tube assembly inspection requirements for Piper PA-32 (Cherokee Six) series aeroplanes, aiming to enhance the structural integrity and safety of these aircraft. The policy objective is to mitigate risks associated with potential cracking and wear in critical components, ensuring that aircraft maintain their airworthiness and comply with safety standards. The amendment to the stabilator balance weight tube assembly inspection directive, effective from 13 October 1994, targets specific models of the Piper PA-32 series. It mandates inspections using magnetic particle or dye penetrant methods, along with visual inspections of mounting fittings and stabilator mounting points. This legislative measure responds to manufacturer reports of cracking and aims to standardise the inspection intervals to not exceed 200 hours of service time, thereby enhancing overall aviation safety and compliance with airworthiness directives.

Scope and Application

The Civil Aviation Regulations 1998, as amended, under the jurisdiction of the Civil Aviation Safety Authority, specifically pertain to the maintenance and safety of aircraft, including the Piper PA-32 (Cherokee Six) Series Aeroplanes. This regulation, AD/PA-32/19 Amendment 3, applies to aircraft models PA-32-260 with serial numbers 32-01 and onward, and PA-32-300, PA-32-300S with serial numbers 32-40000 and onward, excluding those with tube assembly part number 69624-02V installed. The directive mandates that inspections of the stabilator balance weight tube assembly for cracks, particularly around control cable lugs and tube attachment bolt holes, must be conducted using a magnetic particle or dye penetrant method, with a preference for magnetic particle inspection if the surface has been mechanically treated or sandblasted. Additionally, the stabilator/tube mounting fittings must be visually inspected for wear, cracking, and loose rivets, and any stabilator side movement must be corrected by installing appropriate washers to centre the assembly. Compliance with these requirements must occur at intervals not exceeding 200 hours of flight time. This directive is effective as of 13 October 1994 and applies on a national level within Australia, overseen by the Civil Aviation Safety Authority.

Key Provisions

The Civil Aviation Regulations 1998, specifically Part 39 - 105, outlines the requirements for maintaining the airworthiness of certain Piper PA-32 (Cherokee Six) Series aeroplanes through Airworthiness Directives (AD). One such directive, AD/PA-32/19 Amendment 3, concerns the stabilator balance weight tube assembly (sections 1-3). This directive applies to Piper PA-32-260 models with serial numbers starting from 32-01 and PA-32-300 and PA-32-300S models with serial numbers starting from 32-40000, excluding those already equipped with tube assembly part number 69624-02V. The directive mandates a comprehensive inspection process to ensure safety and compliance with airworthiness standards. The main operative sections of this directive (section 1) require an inspection using a magnetic particle or dye penetrant method to check for cracks around the control cable lugs and tube attachment bolt holes. In cases where mechanical means or sand blasting has been used to remove surface protective treatment, a magnetic particle inspection method is mandatory. Section 2 further requires a visual inspection of the stabilator/tube mounting fittings, specifically P/N 63567-03, for signs of wear, cracking, and loose rivets. Additionally, section 3 involves inspecting the stabilator mounting points for any side movement, with a requirement to install specific washers if side movement is detected, as referenced in Piper SB 327. The obligations imposed by the directive (sections 1-3) mandate regular and detailed inspections to be conducted at intervals not exceeding 200 hours of service time. This ensures that any potential issues with the stabilator balance weight tube assembly are identified and rectified promptly. Failure to comply with these inspection intervals or to identify and address any defects could result in serious safety risks, potentially leading to in-flight failures. Should an operator or entity fail to comply with the requirements outlined in this Airworthiness Directive, there could be significant civil or criminal consequences. While the specific penalties are not detailed in the directive itself, general provisions under the Civil Aviation Act 1988 could apply, potentially including fines and other regulatory actions. The severity of the penalties would depend on the specific circumstances of the breach and the impact on aviation safety.