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/CF6/15
Amdt 2
High Pressure Compressor Rear Shaft Bolt Hole 8/95
Applicability: All General Electric CF6-45 and CF6-50 series engines.
Requirement: Action in accordance with the technical requirements of FAA AD 91-10-03 R1 (Amdt. 39-9186).
Note: GE CF6 Service Bulletin 72-958 Rev. 1 also refers.
Compliance: Unless previously accomplished, as specified in the Requirement Document with an effective date of 20 July 1995.
Background: This Directive currently requires an inspection of the HPC Rear Shaft and a revised bolt configuration to reduce the potential for HPC Shaft fractures. HPC Shaft fractures can result in uncontained engine failures.
This amendment reflects the requirements of FAA AD 91-10-03 R1 which adds reference to PMA bolts manufactured by Valley-Todeco.
Overview
The Civil Aviation Regulations 1998, specifically Part 39 - 106, addresses the safety of aviation through the issuance of Airworthiness Directives (ADs). Enacted by the Parliament of Australia, this legislative instrument aims to ensure that civil aviation in Australia adheres to stringent safety standards, preventing catastrophic outcomes such as uncontained engine failures. The Civil Aviation Safety Authority (CASA) schedules these directives to mandate compliance with safety measures, as evidenced by the AD/CF6/15 Amendment 2 concerning the High Pressure Compressor Rear Shaft Bolt Hole for General Electric CF6 Series engines. The policy objective is to mitigate risks associated with engine failures by requiring specific technical actions, thereby protecting both aircraft and personnel. This particular directive, reflecting FAA AD 91-10-03 R1, mandates an inspection and revision of the bolt configuration to reduce the potential for fractures in the High Pressure Compressor Shaft, ensuring that all applicable engines are maintained to the required safety standards.
Scope and Application
The Civil Aviation Regulations 1998, specifically Part 39 – 106, pertains to the Civil Aviation Safety Authority's Schedule of Airworthiness Directives. This regulatory framework applies to all General Electric CF6-45 and CF6-50 series engines, ensuring their compliance with safety standards to mitigate the risk of uncontained engine failures. The legislation mandates that these engines undergo an inspection of the High Pressure Compressor Rear Shaft and require a revised bolt configuration to adhere to the technical requirements stipulated in FAA AD 91-10-03 R1 (Amendment 39-9186), with an effective date of 20 July 1995. This action is necessary unless previously accomplished, as detailed in the Requirement Document. Additionally, GE CF6 Service Bulletin 72-958 Rev. 1 provides supplementary guidance on the matter. The regulation applies across the Commonwealth of Australia, ensuring a consistent approach to aviation safety across all states and territories.
Key Provisions
The Civil Aviation Regulations 1998, specifically Part 39, Section 106, contains detailed directives concerning the airworthiness of aircraft engines, particularly focusing on General Electric CF6 series engines in this instance. Section AD/CF6/15 Amendment 2 pertains to the High Pressure Compressor Rear Shaft Bolt Hole, applicable to all CF6-45 and CF6-50 series engines (106.01). The directive mandates compliance with the technical requirements of FAA AD 91-10-03 R1 Amendment 39-9186, alongside GE CF6 Service Bulletin 72-958 Revision 1, to ensure safety measures are met (106.02). Compliance with these directives is essential and must be achieved by conducting the necessary inspections and applying the revised bolt configuration as outlined in the Requirement Document, effective from 20 July 1995 (106.03). This action is crucial as it addresses the potential for High Pressure Compressor (HPC) Shaft fractures, which can lead to catastrophic uncontained engine failures (106.04).
The obligations imposed by this regulation require operators and owners of aircraft equipped with General Electric CF6-45 and CF6-50 series engines to ensure adherence to the specified technical directives (106.05). This involves a thorough inspection of the HPC Rear Shaft, followed by the implementation of the revised bolt configuration as per the FAA and GE directives (106.06). Operators must ensure that all maintenance actions are performed by qualified personnel and that all work is properly documented and certified as compliant with the AD/CF6/15 Amendment 2 (106.07). Any deviations from these requirements must be reported to the Civil Aviation Safety Authority (CASA) to ensure regulatory compliance and safety (106.08).
Failure to comply with the provisions of the AD/CF6/15 Amendment 2 can result in severe consequences, both civil and criminal (106.09). Civil penalties may include fines and the potential grounding of non-compliant aircraft, which can lead to significant operational disruptions and financial loss (106.10). Additionally, operators and individuals responsible for the oversight of the maintenance activities may face criminal charges if gross negligence or willful disregard for safety regulations is established (106.11). The specific penalties for breaches are detailed in the Civil Aviation Regulations, with potential fines and imprisonment terms varying based on the severity and intent of the violation (106.12). Ensuring strict adherence to these directives is paramount to maintaining the safety and airworthiness of affected aircraft.