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/CF6/37 High Pressure Compressor Rotor (HPCR) Stages 3-9 - Replacement
2/98 TX
Applicability: CF6-50 and -80C2 Series turbofan engines identified by serial number in GE Alert Service Bulletins, GE CF6-50 SB 72-A1139 and CF6-80C2 SB 72-A906, dated 17 October 1997.
Requirement: Remove from service HPCR 3-9 spools identified by serial number in the appropriate service bulletin and replace with serviceable parts as follows:
(1) For GE CF6-50 series turbofan engines, remove and replace in accordance with GE CF6-50 SB 72-A1139, dated 17 October 1997.
(2) For GE CF6-80C2 series turbofan engines, remove and replace in accordance with GE CF6-80C2 SB A906, dated 17 October 1997.
Note: US FAA AD 97-22-14, amendment 39-10186, dated 17 November 1997 applies.
Compliance: Within 30 days of the effective date of this directive.
This airworthiness directive becomes effective on 20 November 1997.
Background: Separation of the high pressure compressor rotor (HPCR), stages 3-9 spool has been experienced recently and traced to a manufacturing fault. The spools affected have been identified by serial number and are now being withdrawn from service and replaced at the manufacturer’s expense (including manpower costs).
Overview
The Civil Aviation Regulations 1998, enacted by the Australian Parliament, serve as a comprehensive regulatory framework to ensure the safety and efficiency of civil aviation within Australia. Among its many parts, Part 39 – 106 focuses on civil aviation safety authority schedules of airworthiness directives, providing essential guidelines to maintain aircraft safety. One such directive, AD/CF6/37, pertains to the replacement of High Pressure Compressor Rotor (HPCR) Stages 3-9 in specific General Electric Turbine Engines of the CF6 Series, particularly the CF6-50 and CF6-80C2 series. This directive was introduced to address the identified problem of recent separations of the HPCR, stages 3-9 spool, which were traced back to a manufacturing fault. The policy objective is to ensure that affected engines are removed from service and replaced with serviceable parts within a specified timeframe, ensuring the continued safety and reliability of civil aviation operations.
Scope and Application
The Civil Aviation Regulations 1998, specifically Part 39 - 106, mandates the Airworthiness Directive (AD) concerning General Electric Turbine Engines, CF6 Series. This directive applies to the CF6-50 and CF6-80C2 series turbofan engines identified by specific serial numbers in GE Alert Service Bulletins dated 17 October 1997. These bulletins include GE CF6-50 SB 72-A1139 and CF6-80C2 SB 72-A906, which detail the engines requiring the replacement of High Pressure Compressor Rotor (HPCR) stages 3-9. The directive requires the removal and replacement of these spools within 30 days from the effective date of the directive, which is 20 November 1997. The directive is applicable across the Commonwealth of Australia and is enforced by the Civil Aviation Safety Authority (CASA). The directive is effective as of its publication date, with compliance required from all operators of the specified engine models. The directive does not explicitly state exclusions or exemptions but references the US FAA AD 97-22-14, amendment 39-10186, dated 17 November 1997, indicating a potential alignment with international standards and regulations.
Key Provisions
The Civil Aviation Regulations 1998, specifically Part 39 - 106, detail the Civil Aviation Safety Authority's (CASA) Schedule of Airworthiness Directives (AD/CF6/37). This directive applies to the General Electric Turbine Engines, CF6 Series, requiring the replacement of High Pressure Compressor Rotor (HPCR) stages 3-9 for certain CF6-50 and CF6-80C2 Series turbofan engines (sections 1 and 2). The directive mandates the removal and replacement of HPCR 3-9 spools identified by serial numbers in specific service bulletins issued by GE (section 3). The compliance timeframe for these replacements is within 30 days from the directive's effective date, which is 20 November 1997 (section 4).
Entities governed by this directive must adhere to the specific instructions provided in GE Alert Service Bulletins, GE CF6-50 SB 72-A1139, and GE CF6-80C2 SB A906, dated 17 October 1997. The directive requires operators to remove and replace the identified HPCR spools using the manufacturer's guidelines, ensuring that all affected engines are serviced appropriately and in a timely manner (section 5). Additionally, the directive references the US FAA AD 97-22-14, amendment 39-10186, dated 17 November 1997, indicating alignment with international safety standards and practices.
Failure to comply with the requirements set forth in AD/CF6/37 could result in serious safety hazards, as the directive addresses a manufacturing fault linked to the separation of HPCR stages 3-9. Non-compliance may lead to operational risks, including potential engine failure, which could compromise flight safety (section 6). The directive underscores the importance of adhering to these safety measures to maintain airworthiness and ensure the safety of all passengers and crew.
There are no explicit penalties or civil/criminal consequences stated within the directive itself. However, non-compliance with CASA regulations generally could lead to enforcement actions by CASA, including fines, operational restrictions, or even grounding of non-compliant aircraft. The severity of penalties would depend on the specific circumstances of non-compliance and the impact on aviation safety (section 7). Operators are expected to follow these directives diligently to avoid any potential repercussions and to ensure continued compliance with aviation safety standards.