AD/PA-20/16 Amdt 1 - Fuselage Door Frame Tube Corrosion

Overview

The Civil Aviation Regulations 1998, amended through the legislative instrument F2006B05407, address a significant safety concern related to the Piper PA-20 (Pacer) series aeroplanes. This legislation was introduced to mitigate the risk of structural failure due to corrosion in the fuselage door frame tube. The Civil Aviation Safety Authority (CASA) issued this directive to ensure the airworthiness of these aircraft by mandating specific inspections and maintenance actions. The overarching policy objective is to enhance the safety standards of civil aviation by addressing corrosion issues that could compromise the integrity of the aircraft structure. This directive provides operators with options for compliance, including adherence to Piper Service Bulletin No 819 or undergoing a radiographic inspection approved by the Secretary, thus ensuring the continued safe operation of the affected aircraft models. The Civil Aviation Regulations 1998, enacted by the Parliament of the Commonwealth of Australia, provide a comprehensive framework for the regulation of civil aviation safety. The specific legislative instrument F2006B05407, pertaining to the Piper PA-20 (Pacer) series aeroplanes, was designed to tackle the problem of excessive corrosion in critical structural components. By requiring either the implementation of the manufacturer's service bulletin or a radiographic inspection, the regulations aim to ensure that the identified corrosion issues are effectively managed, thereby preventing potential in-flight structural failures and ensuring the continued safety and airworthiness of these aircraft.

Scope and Application

The Civil Aviation Regulations 1998, specifically Part 39, Subpart 105, governs the airworthiness directives for aircraft operating in Australia, with the AD/PA-20/16 Amendment 1 being pertinent to the Piper PA-20 (Pacer) series aeroplanes. This directive applies to all model PA-20 aeroplanes with serial numbers ranging from 20-01 to 20-1121. The legislation mandates compliance with either the action specified in Piper Service Bulletin No 819 or a radiographic inspection of designated areas, as outlined in the same service bulletin, to a scheme approved by the Secretary. The requirement for compliance must be fulfilled either before 30 November 1986 if not previously done, or if already completed, then at intervals not exceeding three years thereafter. Notably, a radiographic technique approved by Gippsland Aeronautics, ANTDS.86.4, is recognised as an acceptable method for complying with this directive. This legislation extends throughout the Commonwealth of Australia and is overseen by the Civil Aviation Safety Authority. There are no exclusions or exemptions specified within the directive itself, but the application and enforcement of this regulation are subject to the broader scope of the Civil Aviation Regulations 1998.

Key Provisions

The Civil Aviation Regulations 1998, specifically Part 39 - 105, under the Civil Aviation Safety Authority's Schedule of Airworthiness Directives for Piper PA-20 (Pacer) Series Aeroplanes, outlines the requirements for addressing corrosion issues in the fuselage door frame tube (Section AD/PA-20/16). According to this directive, owners or operators of the specified model range (S/Nos 20-01 to 20-1121) must comply with Piper Service Bulletin No 819, which provides instructions on the necessary action to address corrosion, or alternatively, they must conduct a radiographic inspection of the affected areas. This inspection must follow a scheme approved by the Secretary and can be done using a method such as the radiographic technique No ANTDS.86.4 by Gippsland Aeronautics, which has been deemed acceptable for compliance purposes. The obligations imposed by this directive are clear and specific. Aircraft owners or operators must ensure that either the action outlined in the Piper Service Bulletin No 819 is carried out, or a radiographic inspection is performed in accordance with an approved scheme. The directive mandates that this action or inspection must be completed before 30 November 1986 if it has not already been done, and subsequently, the inspection must be repeated at intervals not exceeding three years. The objective is to maintain the structural integrity of the aircraft by mitigating the risk of excessive corrosion in the specified areas of the fuselage. Failure to comply with the requirements of this directive can result in serious consequences. The regulations do not explicitly state the penalties for non-compliance within the text provided, but typically, non-compliance with airworthiness directives can lead to enforcement actions by the Civil Aviation Safety Authority. These actions may include fines, penalties, and potentially grounding the aircraft until the required actions are completed. The severity of the penalties can vary based on the circumstances and the impact of the non-compliance on aviation safety. It is crucial for aircraft owners and operators to adhere strictly to the outlined directives to avoid these potential repercussions.