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/CF700/16 Turbine Torque Rings and Compressor Driveshafts 5/98
Applicability: General Electric CF700 series turbine engines incorporating turbine torque rings and/or compressor driveshafts identified in General Electric Service Bulletin number (CF700) 72-155.
Requirement: Replace affected turbine torque rings and compressor driveshafts in accordance with General Electric Service Bulletin number (CF700) 72-155.
Note: FAA AD 97-25-08 also refers.
Compliance: Affected turbine torque rings are to be replaced within 50 hours time in service or 60 days from the effective date of this Directive whichever occurs first.
Affected compressor driveshafts are to be replaced within 300 hours time in service or 12 months from the effective date of this Directive whichever occurs first.
This airworthiness directive becomes effective 23 April 1998.
Background: This Directive is prompted by advice from the manufacturer that some turbine torque rings and compressor drive shafts were manufactured from contaminated material.
Failure of a discrepant component could result in an uncontained engine failure.
Overview
The Civil Aviation Regulations 1998, enacted by the Parliament of the Commonwealth of Australia, serve to maintain high safety standards in the aviation industry. One specific legislative instrument under this Act, F2006B08505, pertains to the safety of General Electric CF700 series turbine engines, particularly addressing issues with turbine torque rings and compressor driveshafts. This instrument was introduced to address the risk of uncontained engine failure due to the use of contaminated material in the manufacturing of these components, as identified by the engine manufacturer. The policy objective is to ensure the continued airworthiness and safety of the affected engines by mandating the replacement of specified parts within stipulated timeframes, thereby preventing potential catastrophic failures that could compromise flight safety.
Scope and Application
The Civil Aviation Regulations 1998, specifically Part 39 - 106, mandates that the Civil Aviation Safety Authority issue airworthiness directives concerning certain aircraft components to ensure safety in aviation. In this instance, AD/CF700/16 applies to General Electric CF700 series turbine engines that include turbine torque rings and/or compressor driveshafts identified in General Electric Service Bulletin number (CF700) 72-155. This directive applies nationally, overseen by the Commonwealth of Australia, and affects any entity operating aircraft with these specified engine components. The directive requires affected turbine torque rings to be replaced within 50 hours of time in service or 60 days from the effective date of this directive, whichever comes first, and compressor driveshafts within 300 hours of time in service or 12 months from the effective date, whichever comes first. This airworthiness directive became effective on 23 April 1998. The directive was issued due to the potential risk of failure of these components, which could lead to uncontained engine failure, and it references FAA AD 97-25-08 for additional context. The directive is a direct implementation of the regulatory framework and does not specify exclusions or exemptions, implying that all affected engines must comply.
Key Provisions
The Civil Aviation Regulations 1998, specifically Part 39 - 106, establish Airworthiness Directives that govern the maintenance and operation of civil aviation aircraft in Australia. One such directive, AD/CF700/16, pertains to General Electric CF700 series turbine engines. This directive mandates the replacement of affected turbine torque rings and compressor driveshafts as outlined in General Electric Service Bulletin number (CF700) 72-155. The directive applies to turbine engines identified in the service bulletin and also references FAA AD 97-25-08 for further guidance.
The primary obligations imposed by AD/CF700/16 are to replace the specified turbine torque rings and compressor driveshafts within specific timeframes. Turbine torque rings must be replaced within 50 hours of time in service or within 60 days from the effective date of the directive, whichever is sooner. Similarly, compressor driveshafts must be replaced within 300 hours of time in service or within 12 months from the effective date of the directive, whichever is sooner. This directive is effective as of 23 April 1998, and operators of affected aircraft must comply with the stipulated timelines to ensure continued airworthiness.
Failure to comply with AD/CF700/16 can result in serious consequences. The directive is prompted by concerns that some turbine torque rings and compressor driveshafts may be manufactured from contaminated material, posing a risk of uncontained engine failure. This risk could endanger flight safety and lead to severe regulatory repercussions. While the Civil Aviation Regulations 1998 do not explicitly outline specific penalties for non-compliance with airworthiness directives, failure to adhere to such directives can result in severe civil and criminal penalties under broader aviation regulations. These may include fines, suspension or revocation of aircraft operating certificates, and potential criminal charges for individuals responsible for non-compliance.