COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 106 CIVIL AVIATION SAFETY AUTHORITY
SCHEDULE OF AIRWORTHINESS DIRECTIVES
AlliedSignal (Garrett/AiResearch) Turbine Engines - ATF3 Series
AD/ATF3/2 Exhaust Splitter Seal Bolted Flange System 8/86
Applicability: ATF3-6-4C, -6A-3C and -6A-4C models with Part and Serial numbers as listed in the Requirement.
Requirement: Install exhaust splitter seal bolted flange system in accordance with G.T.E.C. S.B. ATF3-72-6092 Rev. 2.
Note: FAA AD T84-20-51 refers.
Compliance: Unless already accomplished, at the next removal of H.P. turbine module but not later than 200 engine operating hours or 6 calendar months after 31 August 1986 whichever occurs first.
Background: An ATF3 engine has experienced an uncontained failure of the 6th stage L.P. turbine rotor blades as the result of detachment of the exhaust splitter seal from the exhaust liner.
FAA AD T84-11-51 issued 25 May 1984 (superseded by FAA AD T84-20-51 October 84) instituted repetitive inspections of the stationary seal/6th stage L.P. turbine rotor for evidence of seal/rotor contact and/or looseness I.A.W. SBs A72-6090 and 6089; and the relevant engine L.M.M.s. These inspections are not necessary on engines which incorporate the splitter seal bolted flange system. This Directive is issued to prevent the possibility of an uncontained engine failure from this cause.
Overview
The Civil Aviation Regulations 1998, enacted by the Australian Parliament, are designed to ensure the safety and efficiency of civil aviation operations within Australia. Within this legislative framework, Part 39 specifically addresses airworthiness directives, which are regulatory measures to ensure that aircraft and their components meet safety standards. The document F2006B02559 pertains to the AlliedSignal (Garrett/AiResearch) Turbine Engines ATF3 Series, highlighting the critical requirement to install an exhaust splitter seal bolted flange system in certain models. This directive was introduced to mitigate the risk of uncontained engine failures, specifically addressing an incident where the detachment of the exhaust splitter seal from the exhaust liner led to a catastrophic failure of the 6th stage L.P. turbine rotor blades. The policy objective of this directive is to prevent such failures by mandating the installation of the bolted flange system, ensuring that the specified models comply with safety standards within a stipulated timeframe.
Scope and Application
The Civil Aviation Regulations 1998, specifically Part 39 - 106, addresses the requirements for the airworthiness of AlliedSignal (Garrett/AiResearch) Turbine Engines, particularly the ATF3 Series, with a focus on the exhaust splitter seal bolted flange system. This regulation applies to ATF3-6-4C, -6A-3C, and -6A-4C models identified by specific Part and Serial numbers. The directive mandates the installation of the exhaust splitter seal bolted flange system as per G.T.E.C. S.B. ATF3-72-6092 Rev. 2 to mitigate the risk of uncontained engine failure, a critical safety measure following the detachment of the exhaust splitter seal from the exhaust liner. Compliance with this directive necessitates the installation of the system at the next removal of the H.P. turbine module but must be achieved within 200 engine operating hours or 6 calendar months after 31 August 1986, whichever occurs first. This legislative instrument ensures that the specified aircraft engines meet stringent safety standards, thereby protecting both aircraft and personnel from potential hazards associated with uncontained engine failures.
Key Provisions
The Civil Aviation Regulations 1998, under PART 39 - 106, specifically address the Civil Aviation Safety Authority Schedule of Airworthiness Directives, focusing on the AlliedSignal (Garrett/AiResearch) Turbine Engines, ATF3 Series. Within this section, AD/ATF3/2 outlines requirements for the exhaust splitter seal bolted flange system, applicable to certain models of the ATF3 engine as detailed in the Requirement (section 1). Essentially, this directive mandates the installation of the exhaust splitter seal bolted flange system in accordance with G.T.E.C. S.B. ATF3-72-6092 Rev. 2 to mitigate the risk of uncontained engine failure due to detachment of the exhaust splitter seal from the exhaust liner. This directive references FAA AD T84-20-51 for additional context, indicating a history of similar safety concerns.
The obligations imposed by this directive require operators of the specified ATF3 engine models to ensure the installation of the exhaust splitter seal bolted flange system. This installation must occur at the next removal of the H.P. turbine module, but not later than 200 engine operating hours or 6 calendar months following 31 August 1986, whichever comes first (section 2). Compliance with this directive is crucial to prevent the risk of an uncontained engine failure, which could have catastrophic consequences for both the aircraft and those on board.
Failure to comply with the provisions of this directive can lead to severe consequences. Although the Civil Aviation Regulations do not explicitly state penalties within the text provided, non-compliance with airworthiness directives generally can result in civil or criminal penalties. These may include fines, imprisonment, or both, depending on the severity of the breach and the discretion of the court. Additionally, non-compliance could result in the grounding of the aircraft until the required modifications are completed, potentially leading to significant operational disruptions and financial losses for the operator.
The regulatory framework is designed to ensure that all relevant parties, including aircraft operators and maintenance providers, are aware of and adhere to these critical safety measures. By mandating the installation of the exhaust splitter seal bolted flange system, the directive aims to eliminate the risk of uncontained engine failure, thereby enhancing the overall safety of air travel.