COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
SCHEDULE OF AIRWORTHINESS DIRECTIVES
Piper PA-44 (Seminole) Series Aeroplanes
AD/PA-44/12 Engine Mount Frame 10/90
Applicability: All models.
Requirement: Inspect the engine mount ring in accordance with Piper Service Bulletin No 937, dated 2 April 1990.
Note: Reinforcement of the mount ring in accordance with Part II of the Requirement document constitutes terminating action for the inspection requirements of this Directive.
Compliance: Prior to accumulating 100 hours time in service after 1 November 1990 and thereafter at intervals not to exceed 100 hours time in service.
Background: This inspection is required following reports of fatigue cracks in the upper left hand portion of the engine mount near the dynafocal mount ring. Uncorrected, such cracks may affect the structural integrity of the engine mount.
Overview
The Civil Aviation Regulations 1998 (Cth), administered by the Civil Aviation Safety Authority (CASA), provide a comprehensive framework for ensuring the safety of civil aviation operations in Australia. Part 39, in particular, contains specific directives aimed at maintaining the airworthiness of aircraft. One such directive is AD/PA-44/12, which applies to Piper PA-44 (Seminole) series aeroplanes and was enacted to address the identified issue of potential fatigue cracks in the engine mount ring. This directive was introduced in response to reports of structural concerns that could compromise the safety of these aircraft if left unaddressed. The policy objective of this directive is to mandate regular inspections of the engine mount ring to prevent the progression of fatigue cracks, thereby ensuring the continued airworthiness and safety of the aircraft in question. Compliance with this directive is crucial for maintaining the integrity of the engine mount and preventing potential in-flight failures.
Scope and Application
The Civil Aviation Regulations 1998, under Part 39 - 105, mandate the Civil Aviation Safety Authority (CASA) to issue Airworthiness Directives (AD) to ensure the ongoing safety of aircraft. Specifically, AD/PA-44/12 pertains to all models of Piper PA-44 (Seminole) Series aeroplanes and mandates an inspection of the engine mount ring in line with Piper Service Bulletin No 937 dated 2 April 1990. This requirement is pivotal as it addresses the potential issue of fatigue cracks in the upper left-hand portion of the engine mount near the dynafocal mount ring, which, if unaddressed, could compromise the structural integrity of the engine mount. The reinforcement of the mount ring, as outlined in Part II of the Requirement document, serves as the terminating action for the inspection stipulations of this Directive. Compliance with this directive is necessary before the aircraft accumulates 100 hours of time in service following 1 November 1990, and subsequently at intervals not exceeding 100 hours of time in service.
Key Provisions
The Civil Aviation Regulations 1998, under Part 39 - 105, specifically in the Schedule of Airworthiness Directives for Piper PA-44 (Seminole) series aeroplanes, includes AD/PA-44/12 concerning the engine mount frame (10/90). This directive applies to all models of the Piper PA-44 (Seminole) series aeroplanes. According to section 10/90, operators are required to inspect the engine mount ring in line with Piper Service Bulletin No 937, dated 2 April 1990. This inspection is crucial to ensure the airworthiness and safety of the aircraft. The reinforcement of the mount ring, as detailed in Part II of the Requirement document, serves as the terminating action for the inspection requirements outlined in this directive.
Operators of Piper PA-44 (Seminole) series aeroplanes are obligated to conduct the specified inspection before the aircraft accumulates 100 hours of time in service after 1 November 1990. This inspection must be repeated at intervals not exceeding 100 hours of time in service thereafter. The directive aims to prevent potential fatigue cracks that have been reported in the upper left-hand portion of the engine mount near the dynafocal mount ring. Such cracks, if left uncorrected, may compromise the structural integrity of the engine mount, posing a significant risk to flight safety.
Failure to comply with the requirements set forth in AD/PA-44/12 may result in serious safety implications, including the potential for structural failure of the engine mount during flight. The regulations do not explicitly state specific offences, penalties, or civil/criminal consequences for non-compliance within the provided text. However, non-compliance with airworthiness directives generally results in the aircraft being deemed non-airworthy, which could lead to grounding of the aircraft and potential enforcement actions by the Civil Aviation Safety Authority. The consequences could include substantial fines and other regulatory penalties for the operators. The exact penalties are subject to the broader provisions of the Civil Aviation Act 1988 and associated regulations.