AD/PT6A/15 - Reversing Linkage Front End Clevis - Incorporation of Inspection Hole

Overview

The Civil Aviation Regulations 1998, enacted by the Parliament of the Commonwealth of Australia, were established to ensure the safety and efficiency of civil aviation within Australia. A specific aspect of these regulations is contained within Part 39 - 106, which pertains to the Civil Aviation Safety Authority's (CASA) Schedule of Airworthiness Directives. This particular legislative instrument, F2006B06356, targets Pratt and Whitney Canada's PT6A series turbine engines, specifically addressing issues with the reversing linkage front end clevis. The objective of this directive is to incorporate an inspection hole to enhance the safety of these engines, thereby mitigating potential risks associated with their operation. The directive applies to PT6A-27 and -28 engines that include a solid link propeller reversing option and were manufactured prior to a specific serial number, with certain exceptions noted. Compliance with these regulations is mandatory within 100 hours of the engine's time in service after a specified date, underscoring CASA's commitment to maintaining high safety standards in civil aviation.

Scope and Application

The Civil Aviation Regulations 1998, under Part 39 - 106, governs the airworthiness directives applicable to Pratt and Whitney Canada PT6A series turbine engines, specifically concerning the reversing linkage front end clevis. This legislation applies to PT6A-27 and -28 engines that have the solid link propeller reversing option and were manufactured before engine serial number PC-E40168, with the exception of serial numbers PC-E40153 and 40162. The directive is designed to ensure that these engines meet specific safety standards, and compliance is mandated within 100 hours of time in service after 31 October 1974. The geographic and jurisdictional reach of this legislation is national, as it is a Commonwealth regulation under the Civil Aviation Act 1988. The legislation applies to operators and maintenance personnel within Australia, thereby impacting the aviation industry nationwide. There are no stated exclusions or exemptions in this specific directive, and it extends its application through the references provided in UACL Service Bulletins and other relevant administrative documents.

Key Provisions

The Civil Aviation Regulations 1998, particularly Part 39, contains various Airworthiness Directives (ADs) aimed at ensuring the safety of aircraft and their operations. One such AD is AD/PT6A/15 (Reversing Linkage Front End Clevis - Incorporation of Inspection Hole), which pertains to Pratt and Whitney Canada's PT6A Series turbine engines. Section 106 of the regulations specifically governs the applicability of this AD (Section 1). The AD is applicable to PT6A-27 and -28 engines that have a solid link propeller reversing option and were manufactured before a certain serial number, excluding specific serial numbers (Section 1). The AD requires compliance through certain service bulletins and directives, namely UACL SB No. 166, UACL SB No. 1119, or AD/UAC-T/21 (Section 2). Compliance must be achieved within 100 hours of time in service after a specified date, in this case, 31 October 1974 (Section 2). The AD sets out the necessary steps and checks that must be performed on the reversing linkage front end clevis to incorporate an inspection hole, ensuring the integrity and safety of the engine (Section 2). Entities governed by these regulations must ensure that their aircraft and engines comply with the ADs outlined. This includes adhering to the specified timeframes and utilising the appropriate service bulletins and directives to make the necessary modifications. Compliance involves inspecting the reversing linkage front end clevis, incorporating the inspection hole, and ensuring that all work is documented and certified by an authorised person (Section 3). Failure to comply with these directives can result in significant safety risks and may lead to further regulatory action. Breaches of these requirements can result in severe consequences, both civil and criminal. Under the Civil Aviation Act 1988, non-compliance with an AD can lead to fines and potential grounding of the aircraft until the deficiencies are rectified. Additionally, if the non-compliance results in an incident or accident, it could lead to criminal charges against the responsible parties, including individuals and corporations (Section 4). The maximum penalties for breaches can include substantial fines and imprisonment, reflecting the serious nature of ensuring aviation safety (Section 4).