COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 106 CIVIL AVIATION SAFETY AUTHORITY
SCHEDULE OF AIRWORTHINESS DIRECTIVES
Pratt and Whitney Turbine Engines - JT8D Series
AD/JT8D/17 Eighth Stage Rear Compressor Front Hub 9/80
Applicability: All JT8D engines fitted with eighth stage rear compressor front hubs P/N 690908, 701308, 717608, 717708 and 738308 which contain balance cuts.
Document: 1. FAA Emergency Telegraphic AD TAD No. T80 15 51; or
2. Pratt & Whitney Aircraft Alert SB ASB 5154 Rev. 1; or 3. AD/PW-T/53.
Compliance: As detailed in Requirement Document No. 1.
Background: Overseas, a JT8D engine experienced an uncontained rupture of a rear compressor front hub, P/N 738308. Subsequent investigation concluded that a fracture originated in the transition radius of a machining cut on the balance flange. This Directive is issued in order to provide inspection procedures and compliance requirements needed to detect cracks in the affected areas of P/N 738308 and similar JT8D hubs.
Overview
The Civil Aviation Regulations 1998, as part of the Civil Aviation Safety Authority's efforts to ensure the safety of aviation operations in Australia, include specific airworthiness directives to address identified issues with aircraft components. One such directive, AD/JT8D/17, targets Pratt and Whitney JT8D turbine engines fitted with certain rear compressor front hubs. This directive was enacted in response to an overseas incident where a JT8D engine experienced an uncontained rupture of a rear compressor front hub, leading to the conclusion that a fracture had originated from a machining cut on the balance flange. The objective of this directive is to mandate inspection procedures and compliance requirements aimed at detecting cracks in the affected areas of specified hub part numbers, thereby preventing similar incidents within the Australian aviation sector.
The Civil Aviation Regulations 1998 were established by the Australian Parliament to regulate the safety of civil aviation, and amendments or additions, such as the airworthiness directive AD/JT8D/17, are introduced to address emerging safety concerns. This specific directive was issued to ensure that all JT8D engines equipped with the identified rear compressor front hubs undergo the necessary inspections and repairs, thereby mitigating the risk of uncontained engine failures. The policy objective is to enhance the safety and reliability of aircraft operations by proactively addressing potential mechanical failures through rigorous regulatory oversight.
Scope and Application
The Civil Aviation Regulations 1998, specifically under Part 39 - 106, establish comprehensive aviation safety standards that apply to all aviation operations within Australian territory. This includes mandating compliance with Airworthiness Directives issued by the Civil Aviation Safety Authority, ensuring that aircraft and related components meet required safety standards. The Pratt and Whitney Turbine Engines - JT8D Series AD/JT8D/17, pertaining to the eighth stage rear compressor front hub, applies to all JT8D engines installed in aircraft that are fitted with specific part numbers of the eighth stage rear compressor front hubs, namely P/N 690908, 701308, 717608, 717708, and 738308, which contain balance cuts. This directive is crucial for ensuring the safety of civil aviation operations within Australia by mandating specific inspection procedures and compliance requirements to detect and address potential cracks in the affected areas of the specified engine components. The applicability of this directive extends to all operators of the mentioned JT8D engines within the jurisdiction of Australian civil aviation regulations, with compliance being overseen by the Civil Aviation Safety Authority. The directive ensures that all relevant aircraft meet the necessary safety standards to prevent incidents similar to the uncontained rupture experienced overseas.
Key Provisions
The main sections of the Civil Aviation Regulations 1998 that apply to Pratt and Whitney Turbine Engines - JT8D Series in the context of AD/JT8D/17 require inspection and compliance measures for specific eighth stage rear compressor front hubs. These directives, outlined in the regulations, mandate that all JT8D engines fitted with certain parts (sections P/N 690908, 701308, 717608, 717708, and 738308) must be inspected to detect cracks that may have originated in the transition radius of a machining cut on the balance flange. The directive specifies that compliance must be in accordance with the FAA Emergency Telegraphic AD TAD No. T80 15 51 or the Pratt & Whitney Aircraft Alert SB ASB 5154 Rev. 1, or AD/PW-T/53 (section 1).
The obligations imposed on the parties governed by these regulations include conducting thorough inspections of the specified components to ensure that there are no cracks or defects that could lead to an uncontained engine rupture. This is particularly critical for the P/N 738308 hub, which was implicated in a previous incident. Operators and maintainers of these engines are required to follow the detailed inspection procedures provided in the requirement documents to maintain airworthiness and safety standards. Failure to comply with these requirements can result in serious safety risks and potential grounding of the aircraft involved.
Breaching the requirements set out in these regulations can lead to severe consequences. The Civil Aviation Safety Authority (CASA) can impose penalties for non-compliance, which may include fines or other civil penalties. Furthermore, there could be criminal implications if the non-compliance results in an accident or incident that endangers safety. The maximum penalties for such offences are not specified in the provided text but are generally determined based on the severity and impact of the non-compliance. It is essential for operators and maintainers to adhere strictly to these directives to avoid any legal repercussions and ensure the continued safe operation of the aircraft.