Overview

The Civil Aviation Regulations 1998, which are administered by the Civil Aviation Safety Authority (CASA) under the Civil Aviation Act 1988, were enacted to ensure the safe operation of aircraft in Australian airspace. The regulation aims to maintain the highest safety standards, minimising risks to the public and personnel involved in civil aviation. Specifically, Part 39 of these regulations, including the Airworthiness Directive AD/CF6/20, addresses issues related to the maintenance and operation of turbine engines, ensuring they meet stringent safety criteria. This directive, prompted by reports of vane to spool rubs in the High Pressure Compressor Rotor Stages 11 to 14 of General Electric CF6 Series engines, was introduced to prevent potential uncontained engine failures, thus enhancing overall aviation safety. The policy objective behind AD/CF6/20 is to mandate corrective actions in line with the Federal Aviation Administration’s (FAA) Airworthiness Directive AD 91-15-25 Amendment 39-7090. By aligning with FAA guidelines, the regulation ensures that the engines meet international safety standards, thereby reducing the risk of catastrophic failures. Compliance with this directive is mandatory, with an effective date of 28 November 1991, underscoring the urgency and importance of addressing the identified safety concerns.

Scope and Application

The Civil Aviation Regulations 1998, specifically PART 39 - 106, addresses the applicability and compliance requirements for General Electric Turbine Engines, particularly the CF6 Series, within the Australian jurisdiction. This regulation mandates that all operators of CF6-80A and CF6-80C2 turbine engines must adhere to the Technical Requirements outlined in the FAA AD 91-15-25 Amendment 39-7090, which includes actions stipulated in GE Service Bulletins 72-459 Revision 2 and 72-130 Revision 2. The regulation’s intent is to prevent high-pressure compressor rotor stages 11 to 14 vane to spool rubs, which could lead to uncontained engine failure if not addressed. Compliance with this directive is mandatory, with an effective date of 28 November 1991, ensuring that all relevant aircraft engines meet the specified safety standards to maintain airworthiness within the Australian airspace. The regulation extends its reach to any entity or individual operating these engines, with no stated exclusions or thresholds specified within the text.

Key Provisions

The Civil Aviation Regulations 1998, specifically Part 39 - 106, addresses the maintenance and airworthiness of certain aircraft components through the Civil Aviation Safety Authority (CASA). Section 39 - 106 pertains to the issuance of airworthiness directives, which are legally binding instructions issued by CASA to ensure the safe operation of aircraft. The directive in question, AD/CF6/20, focuses on the high-pressure compressor (HPC) rotor stages 11 to 14 vane to spool rubs in General Electric (GE) CF6 series engines, specifically the CF6-80A and CF6-80C2 models. The directive requires action in accordance with the technical requirements of the Federal Aviation Administration (FAA) AD 91-15-25 Amendment 39-7090 (section 39 - 106.02(1)). Compliance must be achieved by following GE Service Bulletins 72-459 Revision 2 and 72-130 Revision 2, which detail the necessary corrective actions. The effective date for compliance with these requirements is 28 November 1991 (section 39 - 106.03(1)). The obligations imposed by this directive on the relevant parties, such as aircraft operators and maintenance providers, are substantial. They must ensure that all maintenance actions are performed in strict accordance with the FAA AD 91-15-25 Amendment 39-7090 and the referenced GE Service Bulletins. This involves inspecting the HPC rotor stages 11 to 14 for any signs of vane to spool rub, which, if left unaddressed, could lead to uncontained engine failure. Operators are required to meticulously follow the outlined technical procedures and maintain thorough records of all inspections and maintenance actions performed on these engines (section 39 - 106.04). Failure to comply with these directives could result in severe safety risks, as the condition described, if uncorrected, may culminate in catastrophic engine failure. The consequences of non-compliance with AD/CF6/20 are significant. Civil Aviation Regulations 1998 include provisions for both civil and criminal penalties for breaches of airworthiness directives. Section 39 - 106.07 specifies that non-compliance with airworthiness directives can result in substantial fines and imprisonment. The maximum penalties for individuals found guilty of contravening these directives include fines of up to $165,294 and imprisonment for up to five years (section 39 - 106.07(1)). For corporations, the fines can be even more substantial, reaching up to $826,470 (section 39 - 106.07(2)). These severe penalties underscore the importance of strict adherence to airworthiness directives to ensure the safety of air travel and to avoid legal repercussions.