Overview

The Civil Aviation Regulations 1998, specifically Part 39, which deals with the Civil Aviation Safety Authority (CASA) Schedule of Airworthiness Directives, includes AD/CF6/23 concerning General Electric Turbine Engines of the CF6 series. This legislation was enacted to address the problem of potential uncontained separations in the high-pressure turbine rotor stage 1 disc/shaft of the CF6-80A series, following reports of such incidents. The policy objective is to ensure the safety of air travel by enforcing rigorous inspection and maintenance protocols for these engines. Compliance with this directive requires adherence to the technical specifications outlined in the Federal Aviation Administration's AD 92-04-08, effective from 17 September 1992, and references GE Service Bulletin 72-605. The directive mandates the removal from service of any CF6-80A engines with identified surface damage in the bore area and necessitates a one-time eddy current and fluorescent penetration inspection of other discs/shafts to ensure airworthiness.

Scope and Application

The Civil Aviation Regulations 1998, specifically PART 39 - 106, applies to the Civil Aviation Safety Authority’s Schedule of Airworthiness Directives concerning General Electric Turbine Engines of the CF6 Series. This legislation mandates the inspection and removal from service of the High Pressure Turbine Rotor Stage 1 Disc/Shaft for the CF6-80A Series engines, in compliance with the technical requirements of the Federal Aviation Administration's Airworthiness Directive AD 92-04-08. The directive applies to entities and industries operating aircraft equipped with these engines, necessitating adherence to the specified compliance actions to ensure aviation safety. The geographic and jurisdictional reach of this regulation is national, as it pertains to the Commonwealth of Australia and must be observed by all relevant parties operating within Australian airspace. While the Act provides a clear mandate, there are no stated exclusions or exemptions in the provided text, indicating a broad application intended to mitigate safety risks associated with the identified engine components. The application of this directive may be further extended or specified through subordinate instruments issued by the Civil Aviation Safety Authority.

Key Provisions

The Civil Aviation Regulations 1998, specifically Part 39 - 106, under the Civil Aviation Safety Authority Schedule of Airworthiness Directives, mandates particular actions concerning the CF6 Series of General Electric turbine engines, particularly the CF6-80A Series (106). The regulation requires that action be taken in accordance with the technical requirements outlined in FAA AD 92-04-08, which includes detailed procedures for the inspection and, if necessary, the removal from service of the high pressure turbine rotor stage 1 disc/shaft (106). This directive is grounded on a report of an uncontained separation of a CF6-80A high pressure turbine rotor stage 1 disk/shaft, leading to a requirement for a one-time eddy current and fluorescent penetration inspection of other discs/shafts, as well as the removal from service of those that show surface damage in the bore area (106). These obligations are stringent and aimed at ensuring the safety and reliability of the CF6-80A turbine engines. Operators of these engines must strictly follow the outlined procedures as specified in the Requirement Document with an effective date of 17 September 1992 (106). This involves conducting thorough inspections and adhering to the removal from service criteria to prevent potential catastrophic failures. The adherence to the FAA AD 92-04-08 and the referenced GE Service Bulletin 72-605 is imperative for compliance with these regulations (106). Non-compliance with the provisions of this directive can lead to serious consequences. If an operator fails to inspect or remove from service the affected turbine rotor stage 1 disc/shafts as required, they may face penalties. These can include fines, enforcement actions, and potential grounding of the affected aircraft until compliance is achieved. The severity of the penalties reflects the critical nature of the directive in maintaining aviation safety standards (106). Operators must therefore ensure that all actions are meticulously carried out to avoid any legal repercussions.