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/ATF3/3 H.P. Turbine Rotor Assembly P/No. 3001766-7 8/86
Applicability: ATF3-6-2C, -6-4C, -6A-3C and -6A-4C engines with H.P. turbine rotor assemblies whose serial numbers are listed in the Requirement Document.
Requirement: Inspect H.P. turbine rotor assemblies in accordance with G.T.E.C. S.B. ATF3-72-6070.
Compliance: Unless already accomplished, at the next removal of H.P. turbine rotor assembly but not later than the next periodic inspection that provides access to the H.P. turbine rotor assembly after 31 August 1986.
Background: The manufacturer has identified H.P. turbine rotor assemblies by serial number which may be susceptible to cracking in the curvic area of the disc.
This Directive is issued to inspect those suspect rotor assemblies.
Overview
The Civil Aviation Regulations 1998, specifically PART 39 - 106, was enacted to address safety concerns related to aircraft maintenance and operation. This legislation was introduced by the Parliament of Australia to ensure that civil aviation operations within the country adhere to stringent safety standards. One of the key gaps it aimed to fill was the need for comprehensive oversight and regulation of aircraft components and their maintenance to prevent potential safety hazards. The Civil Aviation Safety Authority (CASA) was designated as the enforcing body, with a clear policy objective to maintain and enhance the safety of civil aviation through rigorous adherence to Airworthiness Directives.
One such directive, AD/ATF3/3, pertains to the inspection of AlliedSignal (Garrett/AiResearch) Turbine Engines - ATF3 Series, particularly the H.P. turbine rotor assembly with parts number 3001766-7. The directive was issued following the identification by the manufacturer of potential cracking in the curvic area of the disc of certain serial numbers of the turbine rotor assemblies. This requirement ensures that inspections are conducted in accordance with specified guidelines to mitigate any risks associated with the identified safety concerns. The directive mandates inspections at specific intervals, ensuring that affected engines are checked at the next removal of the H.P. turbine rotor assembly or during the next periodic inspection that provides access to the assembly, but no later than after 31 August 1986.
Scope and Application
The AlliedSignal (Garrett/AiResearch) Turbine Engines - ATF3 Series Airworthiness Directive AD/ATF3/3 applies specifically to certain H.P. turbine rotor assemblies in ATF3-6-2C, -6-4C, -6A-3C and -6A-4C engines that have serial numbers listed in the Requirement Document. This directive mandates an inspection of these rotor assemblies in accordance with guidelines set out in G.T.E.C. S.B. ATF3-72-6070. The requirement for inspection must be met at the next removal of the H.P. turbine rotor assembly but no later than the next periodic inspection that provides access to the H.P. turbine rotor assembly after 31 August 1986. The directive is issued under the Commonwealth of Australia's Civil Aviation Regulations 1998, specifically within Part 39 - 106, which is overseen by the Civil Aviation Safety Authority. The purpose of this directive is to ensure the safety of these engines by identifying and addressing any potential cracking in the curvic area of the disc, which could compromise the integrity and performance of the rotor assembly.
Key Provisions
The Civil Aviation Regulations 1998, under Part 39 and specifically in Schedule 106, details the Airworthiness Directives for certain AlliedSignal (Garrett/AiResearch) Turbine Engines, particularly the ATF3 Series (AD/ATF3/3). This directive focuses on the H.P. turbine rotor assembly with the part number 3001766-7 and applies to ATF3-6-2C, -6-4C, -6A-3C, and -6A-4C engines. These engines must be inspected for any H.P. turbine rotor assemblies whose serial numbers are listed in the Requirement Document. The inspection must be conducted in accordance with the guidelines specified in G.T.E.C. S.B. ATF3-72-6070.
This requirement necessitates that inspections of the H.P. turbine rotor assemblies are performed unless they have already been completed. The inspection must occur at the next removal of the H.P. turbine rotor assembly but must not be deferred beyond the next periodic inspection that provides access to the assembly after 31 August 1986. The directive aims to identify any potential cracking in the curvic area of the disc, which the manufacturer has flagged as a potential issue. The directive is therefore a precautionary measure to ensure the safety and airworthiness of the specified engines.
Entities and parties governed by these regulations must comply with the inspection requirements detailed in the directive. This includes ensuring that the H.P. turbine rotor assemblies are inspected according to the specified guidelines and within the stipulated timeframe. Non-compliance with these directives can result in significant safety risks and may lead to the grounding of affected aircraft until the necessary inspections are completed. Compliance involves meticulous record-keeping and adherence to the manufacturer's guidelines to maintain the airworthiness of the engines.
Failure to comply with the Airworthiness Directives can result in various penalties and consequences. These may include civil penalties for non-compliance, as well as potential criminal charges in cases where non-compliance leads to serious safety incidents. The maximum penalties for such offences can vary, but they may include fines and, in severe cases, imprisonment. Additionally, non-compliance may lead to the suspension or revocation of airworthiness certificates, grounding of affected aircraft, and other regulatory actions taken by the Civil Aviation Safety Authority (CASA). The seriousness of the penalties reflects the critical importance of adhering to these safety directives to ensure the safety of all air travel.