AD/PA-38/17 Amdt 2 - Rudder Upper Hinge - Inspection and Replacement

Overview

The Civil Aviation Regulations 1998 (Cth), as amended, address the regulation of civil aviation within Australia and include provisions for ensuring the airworthiness of aircraft. This particular regulation, introduced by the Civil Aviation Safety Authority (CASA), targets the Piper PA-38 (Tomahawk) Series Aeroplanes to mitigate flight hazards associated with potential cracks in the rudder upper hinge fitting. The regulation was enacted to enhance flight safety by mandating specific inspections, replacements, and modifications to the rudder upper hinge components to prevent structural failure. The policy objective is to ensure that aircraft maintain their airworthiness and continue to operate safely by addressing known issues with specific aircraft models.

Scope and Application

The Civil Aviation Regulations 1998, specifically PART 39 - 105, addresses the safety and operational standards for civil aircraft within Australia. This legislation applies to all operators of aircraft, particularly focusing on the Piper PA-38 (Tomahawk) Series Aeroplanes as outlined in AD/PA-38/17 Amendment 2. The regulation mandates specific maintenance and inspection procedures for identified models of the Piper PA-38 series, which includes aeroplanes with serial numbers ranging from 38-78A0001 to 38-80A0099, 38-80A0113, 38-80A0120, and 38-80A0123 to 38-80A0165. The directive is designed to mitigate potential flight hazards due to cracks in the rudder upper hinge fitting, and it sets out clear requirements for inspection, replacement, and re-installation procedures. Compliance with these directives is crucial for maintaining the airworthiness of the specified aircraft, and the regulations stipulate precise timelines for the inspection and replacement tasks. These regulations extend across the Commonwealth of Australia and are enforced by the Civil Aviation Safety Authority, ensuring that all operators adhere to the specified safety standards.

Key Provisions

The Civil Aviation Regulations 1998, specifically Part 39 - 105, includes detailed provisions regarding airworthiness directives, which are mandatory safety instructions issued by the Civil Aviation Safety Authority (CASA) for specific aircraft types. One such directive, AD/PA-38/17 Amendment 2, pertains to the Piper PA-38 (Tomahawk) series aeroplanes and addresses issues with the rudder upper hinge (section 2/81). The directive applies to all models PA-38-112 with specific serial numbers, from 38-78A0001 to 38-80A0099, 38-80A0113, 38-80A0120, and 38-80A0123 to 38-80A0165. The main requirement of this directive is to mitigate potential flight hazards associated with cracks in the rudder upper hinge fitting. To do this, operators must follow a series of steps that involve inspecting and replacing the components in question. To comply with the directive, operators must first remove the rudder upper hinge pin and displace the rudder aft to expose the surfaces of both rudder upper hinge brackets (P/N 77610-02). A visual inspection must then be conducted using at least a 10X lens or an approved dye penetrant technique to check for cracks in the hinge surfaces, specifically in the area from the hinge pin hole to the forward edge of the hinge. Upon re-installation of the upper hinge bolt, it is imperative to torque the nut to between 50 and 70 inch pounds, but not to exceed the maximum figure. Additionally, the directive mandates that the hinge brackets be replaced with steel brackets (P/N 77610-03) in accordance with Piper Service Bulletin No. 686. It is also required to retire the steel hinge brackets (P/N 77610-03) from service, although installation of these brackets negates the need for inspections as per paragraphs 1 and 2. The directive imposes several obligations on operators. For paragraphs 1, 2, and 3, the initial inspection must be completed within 10 hours of time in service after 6 June 1980, and subsequent inspections must occur at intervals not exceeding 50 hours of time in service until modifications are made according to Piper Service Bulletin No. 686. For paragraph 4, the replacement of the hinge brackets must be done within 300 hours of time in service after 4 July 1980. Finally, for paragraph 5, the retirement of the steel hinge brackets must occur prior to the accumulation of 5000 hours of component time in service. Failure to comply with these obligations can lead to serious consequences. Failure to adhere to the provisions outlined in AD/PA-38/17 Amendment 2 can result in significant penalties and consequences. The regulations do not explicitly state the penalties for non-compliance, but violations of Civil Aviation Regulations generally can result in substantial fines, imprisonment, or both. In the context of airworthiness directives, non-compliance could lead to the grounding of the affected aircraft until the required inspections and repairs are performed. Additionally, CASA may impose administrative penalties, including fines up to $27,500 per infringement, or in the case of a corporation, up to $1.375 million per infringement. For repeat offenders, the fines can be even higher. In severe cases, CASA may also suspend or revoke the aircraft’s certificate of airworthiness, which could result in the aircraft being permanently grounded.