COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 106 CIVIL AVIATION SAFETY AUTHORITY
SCHEDULE OF AIRWORTHINESS DIRECTIVES
AlliedSignal (Garrett/AiResearch) Turbine Engines - TPE 331 Series
AD/TPE 331/42
Amdt 1
Torque Sensor 1/94
Applicability: TPE331-1, -2, -3, -5, -6, -8 and -10 series engines fitted with a part number 3101726- 1 hydraulic torque sensor gear assembly.
Requirement: Replace the part number 3101726-1 hydraulic torque sensor with a P/N 3101726-2 torque sensor in accordance with Allied Signal Aerospace SB TPE331-72-0232 Revision 6 or, with a P/N 3101726-3 torque sensor in accordance with Allied Signal Aerospace SB TPE331-72-0555 Revision 4.
Compliance: Effective 6 January 1994; at next engine overhaul or next access to the affected part, whichever occurs first.
Background: This Directive requires the replacement of the P/N 3101726-1 torque sensor. The requirement reflects concern that failure of the torque sensor could result in the loss of fuel control drive. This amendment reflects the availability of the P/N 3101726-3 torque sensor which provides larger, directly lubricated "idler" gearshaft bearings.
Overview
The Civil Aviation Regulations 1998, as amended by F2006B07453, address specific safety concerns related to the AlliedSignal (Garrett/AiResearch) Turbine Engines - TPE 331 Series. Enacted by the Parliament of Australia, these regulations aim to ensure the continued airworthiness of the specified turbine engines by addressing potential failures that could compromise safety. The legislative instrument mandates the replacement of the part number 3101726-1 hydraulic torque sensor with either a part number 3101726-2 or 3101726-3 torque sensor to prevent the risk of loss of fuel control drive, thereby enhancing overall aviation safety. Compliance with this directive is required by 6 January 1994, or at the next engine overhaul or access to the affected part, whichever occurs first.
The policy objective underpinning this amendment is to mitigate safety risks associated with the hydraulic torque sensor by ensuring that all applicable engines are equipped with improved components that are less prone to failure. By specifying the use of more reliable torque sensors, the regulations aim to maintain the high standards of safety expected within the civil aviation sector in Australia.
Scope and Application
The Civil Aviation Regulations 1998, specifically under PART 39 - 106, apply to the AlliedSignal (Garrett/AiResearch) Turbine Engines - TPE 331 Series, as outlined in the AD/TPE 331/42 Amendment 1. This regulation is applicable to TPE331-1, -2, -3, -5, -6, -8, and -10 series engines that are fitted with a part number 3101726-1 hydraulic torque sensor gear assembly. The requirement is to replace the specified torque sensor with either a P/N 3101726-2 torque sensor in accordance with Allied Signal Aerospace Service Bulletin TPE331-72-0232 Revision 6, or a P/N 3101726-3 torque sensor as per Allied Signal Aerospace Service Bulletin TPE331-72-0555 Revision 4. The compliance with this directive must be met by 6 January 1994, at the next engine overhaul, or the next access to the affected part, whichever occurs first. The directive aims to mitigate the risk of loss of fuel control drive due to the potential failure of the torque sensor. The application of this regulation is within the jurisdiction of the Commonwealth of Australia and is enforced by the Civil Aviation Safety Authority (CASA). There are no specific exclusions or exemptions mentioned in the directive, and it applies uniformly across the relevant engines and parts specified.
Key Provisions
The main operative sections of this legislative instrument are found in Part 39 of the Civil Aviation Regulations 1998, specifically within the Schedule of Airworthiness Directives. Section 106 focuses on the AlliedSignal (Garrett/AiResearch) Turbine Engines - TPE 331 Series, and more specifically, AD/TPE 331/42 Amendment 1, which pertains to the torque sensor. This directive applies to TPE331-1, -2, -3, -5, -6, -8 and -10 series engines equipped with a part number 3101726-1 hydraulic torque sensor gear assembly. The requirement is to replace the existing torque sensor with either a P/N 3101726-2 or a P/N 3101726-3 torque sensor, in accordance with specified technical bulletins and revisions. Compliance with this directive must occur by 6 January 1994, at the next engine overhaul, or the next access to the affected part, whichever is sooner.
The obligations imposed by this Act are specific to the maintenance and safety of the engines covered by the directive. Engine operators and maintenance personnel must ensure that the specified torque sensor replacement is carried out as required. This involves adhering to the technical bulletins and revisions outlined in the directive, which provide detailed instructions for the replacement process. The directive also requires that compliance be achieved within the specified timeframe, ensuring that the engines are maintained to the required safety standards. Additionally, the directive mandates that the replacement must be completed at the next scheduled engine overhaul or the next time the affected part is accessible, whichever comes first.
The consequences for non-compliance with this directive can be significant. Failure to adhere to the requirements and timelines set out in the directive can result in serious safety risks, including the potential for loss of fuel control drive. Such risks not only endanger the operation of the aircraft but can also lead to serious regulatory consequences. The Civil Aviation Safety Authority (CASA) has the authority to enforce compliance and can impose penalties for non-compliance. While the specific penalties are not detailed in the directive itself, it is understood that CASA can take action to ensure that the safety requirements are met, which may include fines, suspension of airworthiness certificates, or other enforcement actions as deemed necessary.