COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 106 CIVIL AVIATION SAFETY AUTHORITY
SCHEDULE OF AIRWORTHINESS DIRECTIVES
General Electric Turbine Engines - CF6 Series
AD/CF6/29
Amdt 1
High Pressure Turbine - Stage 1 Disc Rim Bolt Holes and Stage 2 Disc Rim and Inner Bolt Holes
13/94
Applicability: General Electric CF6-45/50/-6 series engines.
Requirement: Action in accordance with the technical requirements of the September 1994 corrected issue of FAA AD 94-09-18.
Note: General Electric Service Bulletins 72-1002, 1003, 1057 and 1059 refer.
Compliance: As specified in the FAA AD with a revised effective date of 8 December 1994.
Background: The requirement arises from an uncontained high pressure turbine disc failure which resulted in an aborted take-off. This amendment incorporates changes to two sections but does not constitute a major change in the thrust of the overall AD document.
Overview
The Civil Aviation Regulations 1998, enacted by the Parliament of the Commonwealth of Australia, provide a comprehensive framework for ensuring the safety and regulation of civil aviation within Australia. Part 39, specifically, deals with the airworthiness of aircraft and associated directives, including the detailed regulation of engine airworthiness. One such directive, AD/CF6/29 Amendment 1, pertains to the high-pressure turbine stage 1 disc rim bolt holes and stage 2 disc rim and inner bolt holes for General Electric CF6 series engines, addressing a critical safety issue identified with these components. This directive was introduced to address a significant safety concern following an uncontained high-pressure turbine disc failure that led to an aborted take-off. The policy objective of this directive is to ensure that all affected engines comply with the technical requirements as specified in the FAA AD 94-09-18, thereby mitigating the risk of similar incidents in the future. The incorporation of the FAA directive, with a revised effective date, underscores the collaborative approach to maintaining aviation safety standards across jurisdictions.
Scope and Application
The Civil Aviation Regulations 1998, specifically Part 39 - 106, addresses the safety of civil aviation in Australia by setting forth stringent requirements for the maintenance and operation of aircraft and their components. Under this regulation, the Civil Aviation Safety Authority (CASA) mandates compliance with Airworthiness Directives (ADs) which ensure that aircraft remain safe and airworthy throughout their operational lifespan. AD/CF6/29 Amendment 1 pertains specifically to the General Electric CF6-45/50/-6 series engines, outlining actions required to rectify issues identified in high-pressure turbine components such as the Stage 1 disc rim bolt holes and Stage 2 disc rim and inner bolt holes. This directive applies universally to all aircraft operators utilising these engines and requires adherence to the technical specifications provided in the September 1994 corrected issue of the Federal Aviation Administration (FAA) AD 94-09-18. The directive references pertinent General Electric Service Bulletins to guide operators through necessary modifications. Compliance with this amendment must be achieved by a revised effective date of 8 December 1994, ensuring that the safety incidents related to high-pressure turbine failures are mitigated. This regulatory framework underscores CASA's commitment to maintaining high safety standards within Australia's civil aviation industry.
Key Provisions
The Civil Aviation Regulations 1998, Part 39 - 106, pertains to the Civil Aviation Safety Authority's (CASA) Schedule of Airworthiness Directives, specifically focusing on the General Electric Turbine Engines - CF6 Series, detailed in AD/CF6/29 Amendment 1. This amendment addresses the high pressure turbine stage 1 disc rim bolt holes and stage 2 disc rim and inner bolt holes. Section 13/94 of the legislation mandates compliance with the technical requirements outlined in the September 1994 corrected issue of the Federal Aviation Administration (FAA) AD 94-09-18. Reference is also made to General Electric Service Bulletins 72-1002, 1003, 1057, and 1059. Compliance with this directive must be achieved in accordance with the FAA AD, but with a revised effective date of 8 December 1994.
Under this Act, the primary obligation is for operators and owners of General Electric CF6-45/50/-6 series engines to ensure that their engines meet the specified technical requirements. This includes adhering to the corrective actions detailed in FAA AD 94-09-18 and the referenced service bulletins. The directive applies to all engines within the specified series and requires that the relevant modifications and inspections be carried out to address the risk of uncontained high pressure turbine disc failure, which could potentially lead to aborted take-offs.
The Act imposes a clear requirement that any deviations from the outlined technical specifications could lead to significant safety risks. Specifically, non-compliance with the airworthiness directives could result in severe operational issues, including engine failure during critical phases of flight. This poses a risk not only to the aircraft and its occupants but also to personnel on the ground.
In terms of legal consequences, failure to comply with the provisions of this directive may result in enforcement actions by CASA. Under the Civil Aviation Act 1988, breaches of airworthiness directives can lead to substantial penalties, including fines and potential prosecution. The maximum penalties for non-compliance can be significant, reflecting the serious nature of air safety regulations. Operators and owners are therefore required to ensure strict adherence to the specified requirements to avoid any legal repercussions.