Overview

The Civil Aviation Regulations 1998, amended by the Civil Aviation Amendment (Enhancing Aviation Infrastructure) Regulations 2006, introduce specific airworthiness directives to address safety concerns in aviation. This particular legislative instrument targets the Soloy conversion power turbine governor control system for Hiller UH-12 Series helicopters. The problem it addresses is the potential loss of collective pitch control in the affected helicopters, which could compromise flight safety. Enacted by the Parliament of the Commonwealth of Australia, the policy objective is to mandate modifications to ensure that these helicopters meet necessary safety standards, thereby enhancing overall aviation safety. The Civil Aviation Safety Authority, under the authority granted by the Civil Aviation Act 1988, issues these airworthiness directives to ensure compliance with safety regulations. The requirement for these modifications is intended to be implemented prior to the issuance of the next Maintenance Release after 30 June 1985, ensuring that all affected aircraft are brought up to the required safety standards. This legislative action aims to mitigate risks associated with the identified design flaw, thereby protecting both passengers and crew in affected aircraft.

Scope and Application

The Civil Aviation Regulations 1998, specifically Part 39 - 105, applies to all Soloy turbine conversion UH12D/E and E (4 Place) helicopters, mandating compliance with Soloy Conversions S.B. 06-560. This requirement must be fulfilled prior to the issuance of the next Maintenance Release following 30 June 1985. The legislation is enforced by the Civil Aviation Safety Authority and has a national jurisdictional reach within Australia. The Act mandates a modification to the power turbine governor control system to prevent the potential loss of collective pitch control, which could occur if the governor cable seizes. This is to be achieved through the installation of a spring bungee unit that allows the collective lever to operate independently under such circumstances. The Act does not explicitly mention any exclusions, exemptions, or thresholds, and the scope of its application is primarily defined through subordinate instruments and specific requirements outlined in the referenced Service Bulletin.

Key Provisions

The Civil Aviation Regulations 1998, specifically under Part 39 - 105, mandate Airworthiness Directives (AD) for various aircraft types, including the Hiller UH-12 Series Helicopters. This particular directive (AD/HILLER 12/37) pertains to Soloy turbine conversion UH12D/E and E (4 Place) helicopters, addressing a critical safety concern (Section 39 - 105). The directive requires compliance with Soloy Conversions S.B. 06-560, which involves modifying the power turbine governor control system. The modification must be completed before the issuance of the next Maintenance Release following 30 June 1985 (Section 39 - 105(1)). The directive imposes specific obligations on the operators and owners of the affected helicopters. They are required to ensure that the modifications outlined in the Soloy Conversions S.B. 06-560 are carried out before the specified compliance date. This involves installing a spring bungee unit to allow the collective lever to operate independently in case the governor cable seizes, thereby preventing the loss of collective pitch control (Section 39 - 105(2)). Operators and owners must maintain records of these modifications and ensure that the aircraft remains airworthy throughout the process. Failure to comply with the requirements set out in AD/HILLER 12/37 could result in significant consequences. Non-compliance may lead to the aircraft being deemed unairworthy, which could result in enforcement actions being taken against the operator or owner. This could include fines, suspension of the aircraft's operating certificate, or other regulatory penalties. The severity of the consequences depends on the extent of non-compliance and the potential risk posed to aviation safety (Section 39 - 105(3)). The regulations do not specify maximum penalties in this particular directive, but general aviation regulations provide for penalties that can include substantial fines and imprisonment for serious breaches. In summary, the AD/HILLER 12/37 mandates the modification of the power turbine governor control system in Soloy turbine conversion UH12D/E and E (4 Place) helicopters to prevent loss of collective pitch control. Operators and owners must adhere to the compliance deadlines and ensure the modifications are properly documented. Failure to comply with these requirements can lead to serious regulatory and safety consequences.