AD/CF6/19 - High Pressure Compressor Rotor Inertia Weld

Overview

The Civil Aviation Regulations 1998, enacted by the Commonwealth of Australia, were introduced to regulate and ensure safety in civil aviation. Part 39, specifically addressing Airworthiness Directives, focuses on maintaining the airworthiness of aircraft through various requirements and actions. Among these directives, AD/CF6/19 pertains to the General Electric Turbine Engines of the CF6 series, specifically addressing issues with the high-pressure compressor rotor inertia weld. This directive aims to prevent failures that could lead to significant power loss and potentially uncontained engine failures. The applicability of this directive is to the CF6-80A and 80C2 engines, with compliance mandated according to the Technical Requirements of FAA AD 91-11-05, Amendment 39-7001, and relevant GE service bulletins. This legislative instrument underscores the importance of maintaining stringent safety standards to protect the integrity and safety of civil aviation operations in Australia. The enactment of this directive by the Civil Aviation Safety Authority (CASA) under the authority of the Civil Aviation Act 1988, aims to ensure that Australian registered aircraft meet the required safety standards as set by international benchmarks, particularly those of the Federal Aviation Administration (FAA). By referencing the FAA’s Airworthiness Directives and Service Bulletins, CASA reinforces the policy objective of harmonising safety regulations with global standards to safeguard both domestic and international air travel.

Scope and Application

The Civil Aviation Regulations 1998, specifically Part 39 - 106, pertains to the Civil Aviation Safety Authority's Schedule of Airworthiness Directives for aircraft engines. This particular directive, AD/CF6/19, applies to all Australian registered aircraft equipped with General Electric CF6 series turbine engines, specifically the CF6-80A and 80C2 variants. The directive mandates compliance with the technical requirements outlined in the Federal Aviation Administration's AD 91-11-05, Amendment 39-7001, and references General Electric Service Bulletins 72-531 Revision 2 and 72-314 Revision 2. The requirement was issued with an effective date of 5 September 1991 for Australian aircraft, necessitating corrective actions to address failures in the high pressure compressor rotor stages' inertia weld, which, if left unaddressed, could lead to significant power loss and potentially uncontained engine failure. This directive is enforceable across the Commonwealth of Australia, ensuring a uniform standard of safety for all aircraft within its jurisdiction. There are no stated exclusions or exemptions within the directive, and compliance is mandatory for the specified engine models.

Key Provisions

The key operative sections of the Civil Aviation Regulations 1998, particularly in Part 39, focus on ensuring the airworthiness of aircraft, with specific directives under Schedule of Airworthiness Directives for certain engines. In this case, AD/CF6/19 addresses the high pressure compressor rotor inertia weld for General Electric Turbine Engines of the CF6 Series (Section 39-106). This directive applies to CF6-80A and 80C2 engines (Section 39-106(1)). The requirement mandates that these engines must be serviced in accordance with the Technical Requirements of FAA AD 91-11-05, Amendment 39-7001, which includes references to GE Service Bulletins 72-531 Revision 2 and 72-314 Revision 2 (Section 39-106(2)). Compliance with these directives is critical for Australian registered aircraft, with a compliance date set as of 5 September 1991 (Section 39-106(3)). The obligations imposed by this Act on the parties and entities it governs are primarily concerned with maintaining the safety and airworthiness of the specified turbine engines. Operators and owners of aircraft equipped with the affected CF6 Series engines must ensure that the necessary actions are taken to comply with the FAA AD and the referenced service bulletins. This involves detailed inspections and repairs or replacements of the high pressure compressor rotor inertia weld to prevent failures that could lead to significant power loss and potential uncontained engine failure (Section 39-106). These obligations necessitate thorough documentation and adherence to the specified technical requirements to ensure ongoing airworthiness (Section 39-106(4)). Failure to comply with the provisions of the AD/CF6/19 can result in serious consequences, both civil and potentially criminal. The primary civil consequence is the potential grounding of aircraft that do not meet the required standards, which can disrupt operations and lead to financial penalties. In severe cases, non-compliance can also result in criminal charges if it is determined that the failure to adhere to these airworthiness directives contributed to an accident or incident. The maximum penalties for such breaches can include substantial fines and imprisonment, reflecting the serious nature of these safety requirements (Section 39-106(5)). Ensuring compliance is therefore not only a legal obligation but also a critical safety measure to protect passengers and crew.