COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
SCHEDULE OF AIRWORTHINESS DIRECTIVES
Schweizer (Hughes) 269 Series Helicopters
AD/HU 269/92 Centre Frame Aft Cluster Fittings 6/88
DM
Applicability: All models and Serial Numbers listed in the Requirement documents. Requirement: Action in accordance with Schweizer SIN N-217, SIN N-220 and SIN N-221.
Compliance: Initial actions to be carried out within 25 hours time in service after 30 March 1988, or prior to 31 May 1988 whichever is sooner. Thereafter, inspect in accordance with the Requirement Documents.
Background: Boom support structure cluster fittings that are either misidentified, have stress raisers or are excessively hardened may have been fitted in new production or sold as spares. Failure of a cluster fitting may cause boom separation.
Overview
The Civil Aviation Regulations 1998, enacted by the Parliament of the Commonwealth of Australia, are designed to ensure the safety and efficiency of civil aviation within Australia. These regulations, particularly Part 39 - 105, aim to provide detailed directives to ensure the airworthiness of aircraft, addressing gaps and problems that might otherwise compromise flight safety. This legislative instrument, F2006B10650, specifically targets Schweizer (Hughes) 269 Series Helicopters through Airworthiness Directives, focusing on critical components such as the Centre Frame Aft Cluster Fittings. The policy objective behind these directives is to mandate actions and inspections that prevent potential failures in the boom support structure, which could lead to catastrophic outcomes such as boom separation. The requirement for compliance was set to be completed within a specific timeframe following the directive's issuance, ensuring that the safety concerns are addressed promptly and effectively.
Scope and Application
The Civil Aviation Regulations 1998, specifically Part 39 - 105, pertains to the Civil Aviation Safety Authority's Schedule of Airworthiness Directives, focusing on the Schweizer (Hughes) 269 Series Helicopters. This legislation applies to all models and serial numbers of these helicopters, as listed in the specific requirement documents, mandating compliance with Schweizer Service Instructions N-217, N-220, and N-221. The directive is necessitated by the potential failure of centre frame aft cluster fittings, which could be misidentified, contain stress raisers, or be excessively hardened, potentially leading to boom separation. The requirement stipulates that initial actions must be undertaken within 25 hours of time in service after 30 March 1988, or by 31 May 1988, whichever is sooner, with subsequent inspections to be conducted in accordance with the outlined requirement documents. The regulations are applicable nationally, covering all entities operating Schweizer (Hughes) 269 Series Helicopters within Australia, ensuring adherence to safety standards and maintaining airworthiness.
Key Provisions
The Civil Aviation Regulations 1998, specifically Part 39, Section 105, mandate the safety directives for Schweizer (Hughes) 269 Series Helicopters. The key operative sections of this legislation include AD/HU 269/92, which pertains to the Centre Frame Aft Cluster Fittings, dated 6/88DM. This directive applies to all models and serial numbers listed in the requirement documents (Section 105). The directive requires compliance with Schweizer Service Information Notices (SIN) N-217, N-220, and N-221. These notices detail specific actions to be taken regarding the centre frame aft cluster fittings, which are critical for the structural integrity of the helicopter.
Operators and owners of Schweizer (Hughes) 269 Series Helicopters are obligated to follow the requirements set out in the directive. This includes performing initial actions within 25 hours of time in service after 30 March 1988, or prior to 31 May 1988, whichever is sooner. After this initial period, operators must adhere to the inspection schedule outlined in the requirement documents. The directive highlights a significant safety concern related to boom support structure cluster fittings, which may be misidentified, have stress raisers, or be excessively hardened. Such defects can lead to failure of the cluster fittings, potentially resulting in boom separation, which poses a serious risk to the aircraft’s airworthiness.
Failure to comply with the Civil Aviation Regulations 1998, particularly with the provisions set out in Section 105, can result in serious consequences. Non-compliance may be considered a breach of the regulations, potentially leading to civil or criminal penalties. The specific penalties for breaches are not detailed in the provided text, but generally, such violations can result in fines, enforcement actions, or even grounding of the aircraft until the required actions are taken. It is crucial for operators and owners to adhere strictly to these directives to ensure the safety and airworthiness of their aircraft.