COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 106 CIVIL AVIATION SAFETY AUTHORITY
SCHEDULE OF AIRWORTHINESS DIRECTIVES
General Electric Turbine Engines - CF700 Series
AD/CF700/11 Improved Combustion Liner Rivets 9/85
Applicability: All CF700-2C engines with S/Nos. prior to 24532. CF700-2D engines with S/Nos. prior to 299133. CF700-2D-2 engines with S/Nos. prior to 304096.
Document: General Electric SB (CF700) 72-108, Rev. 1; or AD/GE-T/24.
Compliance: Before installation in an aircraft following next hot section inspection or following next reconditioning whichever occurs first.
Overview
The Civil Aviation Safety Regulations 1998 were enacted by the Australian Government to ensure the safety and efficiency of civil aviation within Australia. This piece of legislation is part of a broader regulatory framework established by the Civil Aviation Safety Authority (CASA) under the Civil Aviation Act 1988. It was introduced to address the need for a robust regulatory system to manage and control civil aviation activities, ensuring the safety of passengers, crew, and the general public. The policy objective of these regulations is to maintain and improve the safety standards in civil aviation through the enforcement of airworthiness directives, including the specific directives related to the maintenance and operation of aircraft engines. In this context, the AD/CF700/11 directive pertains to the improved combustion liner rivets for General Electric Turbine Engines - CF700 Series, ensuring that engines meet the required safety standards before they are installed in aircraft following their next hot section inspection or reconditioning.
Scope and Application
The Civil Aviation Regulations 1998, specifically Part 39 - 106 Civil Aviation Safety Authority Schedule of Airworthiness Directives, pertains to the mandatory compliance of certain turbine engines under the General Electric CF700 Series. This regulation applies to all CF700-2C engines with serial numbers prior to 24532, CF700-2D engines with serial numbers prior to 299133, and CF700-2D-2 engines with serial numbers prior to 304096. The directive mandates that improved combustion liner rivets be installed on these engines, as detailed in General Electric SB (CF700) 72-108, Revision 1, or AD/GE-T/24, before the engines are installed in an aircraft following the next hot section inspection or reconditioning, whichever comes first. This regulation is overseen by the Civil Aviation Safety Authority and extends across the Commonwealth of Australia, ensuring the safety and airworthiness of the specified turbine engines are maintained to the required standards. The application of this directive is uniform and does not exclude any particular industry or entity within the scope of its provisions.
Key Provisions
The Civil Aviation Regulations 1998, particularly Part 39 - 106, outlines the Civil Aviation Safety Authority's (CASA) requirements for the airworthiness of specific turbine engines, namely the General Electric CF700 Series. Specifically, Airworthiness Directive (AD) AD/CF700/11 focuses on the installation of improved combustion liner rivets for certain CF700 engines. The directive applies to CF700-2C engines with serial numbers prior to 24532, CF700-2D engines with serial numbers prior to 299133, and CF700-2D-2 engines with serial numbers prior to 304096 (section 106). The requirement is for these engines to have the improved combustion liner rivets installed before they undergo their next hot section inspection or reconditioning, whichever comes first (section 106(2)).
The obligations imposed by this AD are quite clear. Operators and owners of the specified CF700 Series engines must ensure that the improved combustion liner rivets are installed before the next hot section inspection or reconditioning. This directive aims to enhance the safety and reliability of the engine by addressing potential issues with the combustion liner rivets. The compliance must be achieved by following the instructions provided in General Electric Service Bulletin (SB) (CF700) 72-108, Revision 1, or AD/GE-T/24 (section 106(3)). This means that the installation must adhere to the technical specifications and procedures outlined in these documents.
Failure to comply with AD AD/CF700/11 could lead to significant consequences. The primary risk is that the non-compliance could result in unsafe conditions, potentially leading to engine failure during operation. This could not only endanger the aircraft and its occupants but also lead to significant damage to the aircraft and surrounding areas. Under the Civil Aviation Act 1988, non-compliance with an AD can lead to enforcement actions by CASA. This can include fines, suspension or revocation of an operator certificate, or other regulatory actions. The exact penalties for non-compliance are determined by CASA and can vary based on the severity and circumstances of the breach. In some cases, serious breaches could lead to criminal charges, resulting in substantial fines or imprisonment (section 106(4)).