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/CF6/35 Compressor Rear Frame Midflange 13/95
Applicability: General Electric CF6-80A engines.
Requirement: Action in accordance with the technical requirements of FAA AD 95-17-16 Amendment 39-9347.
Note: GE CF6-80A SB No. 72-593 Revision 2 also refers.
Compliance: Effective 7 December 1995:
Unless previously accomplished, as specified in the Requirement Document, except for paragraph (b) which has a revised compliance date of 30 June 1997.
Note: Paragraph (b) requires replacement or rework of the CRF midflange which is considered terminating action for the inspections.
Background: General Electric has advised that axial cracks have been found in the CRF midflanges and in one event a CRF midflange crack resulted in flange separation and a subsequent rejected take-off.
This Directive mandates a repetitive on-wing eddy current inspection or optional on- wing fluorescent particle inspection (FPI), repetitive shop level FPI of the CRF midflange area and replacement or rework of the CRF midflange.
Overview
The Civil Aviation Regulations 1998, as amended, are fundamental to ensuring the safety and regulation of civil aviation in Australia. Among these amendments, the 1995 directive AD/CF6/35 was introduced to address the critical issue of axial cracks found in the compressor rear frame midflanges of General Electric CF6-80A series turbine engines. This problem was identified after an incident where a crack led to flange separation and a rejected takeoff, highlighting the need for stringent safety measures. The directive was enacted by the Civil Aviation Safety Authority and is aimed at preventing similar incidents by mandating repetitive inspections and, where necessary, replacement or rework of the affected midflanges. The compliance dates for these measures were set to ensure that aviation safety was promptly and effectively enhanced.
Scope and Application
The Civil Aviation Regulations 1998, under Part 39, mandates specific airworthiness directives to ensure the safety of aircraft operations. This particular directive, AD/CF6/35, applies to General Electric CF6-80A engines, necessitating compliance with the technical requirements of FAA AD 95-17-16 Amendment 39-9347. The directive was enacted in response to identified axial cracks in the compressor rear frame midflange, which in one instance led to flange separation and a rejected take-off. Compliance with this directive is mandatory for all operators of the affected engines, with the inspections and actions specified in the directive document to be completed by the designated compliance dates, except for certain actions which have a later compliance deadline of 30 June 1997. The directive allows for repetitive on-wing inspections or alternative shop-level inspections and requires the replacement or rework of the CRF midflange to mitigate identified risks. Subordinate instruments may further detail specific procedural requirements or exceptions, but the primary focus remains on ensuring the structural integrity of the specified engine components.
Key Provisions
The main operative sections of the Civil Aviation Regulations 1998 (CAR) part 39, particularly the Airworthiness Directive AD/CF6/35 concerning General Electric Turbine Engines - CF6 Series, specify the requirements for the compressor rear frame (CRF) midflange of the CF6-80A engines (section 13/95). These sections require compliance with the technical specifications outlined in FAA AD 95-17-16 Amendment 39-9347, and reference GE CF6-80A Service Bulletin No. 72-593 Revision 2 for additional guidance. The directive applies specifically to General Electric CF6-80A engines and mandates actions including on-wing eddy current inspections or fluorescent particle inspections (FPI), shop level FPI of the CRF midflange area, and the replacement or rework of the CRF midflange. Compliance is effective from 7 December 1995, with a specific revised compliance date of 30 June 1997 for paragraph (b) concerning the replacement or rework of the CRF midflange.
The obligations imposed by this Act are primarily on the operators and maintenance personnel of aircraft equipped with the affected CF6-80A engines. Operators must ensure that all inspections and necessary repairs or replacements are conducted in accordance with the specified technical requirements and timelines. Maintenance personnel must perform the repetitive on-wing and shop level inspections as outlined, and ensure that any identified issues with the CRF midflange are addressed appropriately. The directive also requires that records of inspections, repairs, and replacements be maintained to demonstrate compliance with the Act.
The Civil Aviation Regulations 1998, under this directive, impose penalties and consequences for non-compliance with the specified airworthiness directives. Operators who fail to comply with the requirements for the inspections and actions mandated by the AD/CF6/35 may face enforcement actions by the Civil Aviation Safety Authority (CASA). The specific penalties and consequences are not detailed in the directive but typically include fines, potential grounding of the aircraft, and other regulatory sanctions to ensure the continued airworthiness and safety of the aircraft. The severity of the penalties will depend on the nature and extent of the non-compliance.