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/CF6/8 Low Pressure Turbine Cooling Air Manifold 4/87
Applicability: CF6-45,-50 series engines.
Requirement: 1. Carry out the requirements of General Electric SB 75-55 Paragraph 2.
2. Inspect left hand side 7th stage low pressure turbine cooling air manifold tubes in accordance with the requirements of General Electric SB 75-58 Paragraphs 2A, 2B, 2C and 2D(4)(b).
3. Remove 7th stage low pressure turbine cooling air tubes and carry out a fluorescent - penetrant inspection in accordance with the requirements of General Electric CF6-50 Task Numbered Shop Manual, GEK 50481.
Reference Documents:
FAA AD 85-25-56 R1
G.E. SB 75-55 R2
G.E. SB 75-58
G.E. CF6-50 Task Numbered Shop Manual, GEK 50481 Compliance: 1. Unless already accomplished - Prior to 31 March 1987.
2. At intervals not to exceed 250 cycles.
3. At each scheduled engine shop visit.
Background: This Directive has been issued to require inspection of the 7th stage low pressure turbine cooling air manifold tubes. Failure of the cooling air manifold tubes could result in an overtemperature condition of the low pressure turbine and subsequent 1st stage turbine disc rupture.
Overview
The Civil Aviation Regulations 1998, which were enacted by the Parliament of Australia, form a comprehensive regulatory framework governing civil aviation safety, including the issuance of Airworthiness Directives (ADs). One such directive, AD/CF6/8, pertains specifically to General Electric CF6 Series turbine engines, targeting issues related to the low-pressure turbine cooling air manifold. This directive was introduced to address the risk of failure in the 7th stage low pressure turbine cooling air manifold tubes, which could lead to overtemperature conditions and potentially catastrophic engine failure. The policy objective of this directive is to ensure the ongoing airworthiness of the specified engine types by mandating rigorous inspection and maintenance procedures to mitigate identified risks. Compliance with these directives is mandatory to ensure the safety of civil aviation operations.
Scope and Application
The Civil Aviation Regulations 1998, under Part 39 and specifically Schedule 106, mandates airworthiness directives related to certain turbine engines, including the General Electric CF6 Series, within the Commonwealth of Australia. This legislative instrument applies to CF6-45 and CF6-50 series engines, ensuring that these components meet specific safety standards to prevent failures that could result in severe consequences such as turbine overtemperature and 1st stage turbine disc rupture. The requirement is for these engines to adhere to the instructions outlined in the referenced General Electric Service Bulletins and Shop Manuals, ensuring regular and thorough inspections and maintenance. The applicability of these directives is national, encompassing all entities operating within Australia’s jurisdiction, including airlines and maintenance providers. There are no stated exclusions or exemptions within the text, implying that all relevant entities and engines must comply with the specified directives. The application of these regulations can be extended or clarified through subordinate instruments, allowing for updates and adaptations to evolving safety standards and technological advancements.
Key Provisions
The Civil Aviation Regulations 1998, specifically Part 39 - 106, include a section dedicated to the Civil Aviation Safety Authority Schedule of Airworthiness Directives (AD/CF6/8). This directive pertains to General Electric Turbine Engines of the CF6 series, focusing on the low pressure turbine cooling air manifold (section 4). The applicability of this directive extends to the CF6-45 and CF6-50 series engines (section 4). The directive stipulates several key requirements. Firstly, operators must adhere to General Electric Service Bulletin 75-55, paragraph 2 (section 1). Secondly, it mandates that the left-hand side 7th stage low pressure turbine cooling air manifold tubes be inspected in accordance with General Electric Service Bulletin 75-58, paragraphs 2A, 2B, 2C, and 2D (section 2). Lastly, the directive requires the removal of these tubes for a fluorescent-penetrant inspection in line with the General Electric CF6-50 Task Numbered Shop Manual, GEK 50481 (section 3).
The obligations imposed by this directive on the operators and entities it governs are quite specific. Primarily, they must ensure that the aforementioned inspections and inspections are carried out correctly and in a timely manner. The directive mandates that any required actions be completed unless they have already been accomplished prior to 31 March 1987 (section Compliance 1). Furthermore, these inspections must occur at intervals not exceeding 250 cycles and at each scheduled engine shop visit (sections Compliance 2 and 3). These obligations are designed to maintain the airworthiness of the affected turbine engines and ensure safety in civil aviation.
Failure to comply with the requirements set out in this directive can result in serious consequences. The regulations do not explicitly detail specific offences, penalties, or civil/criminal consequences for breach within the excerpt provided. However, given the nature of airworthiness directives and the critical role they play in aviation safety, non-compliance could likely lead to enforcement actions by the Civil Aviation Safety Authority. These actions might include fines, suspension of airworthiness certificates, or other regulatory penalties as stipulated by the Civil Aviation Act 1988 and related regulations. Given the potential for significant safety implications, the penalties for non-compliance could be substantial.