COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
SCHEDULE OF AIRWORTHINESS DIRECTIVES
Aerostar (Piper/Ted Smith) 600 and 700 Series Aeroplanes
AD/TSA-600/34 Hydraulic System Internal Leak Check 11/85
Applicability: All models not fitted with an auxiliary hydraulic pump system.
Requirement: With the aircraft on jacks, ensure that with the undercarriage fully retracted, the flap selector lever in neutral and the hydraulic pressure selected off, the landing gear remains in the fully retracted position for a minimum period of 30 minutes.
Compliance: Prior to the issue of the next Maintenance Release after 31 December 1985 and thereafter at each issue of a new Maintenance Release.
Background: In the event of a R/H engine failure in flight, the landing gear may automatically extend to the locked down position if an internal leak was present in the hydraulic system.
Overview
The Civil Aviation Regulations 1998, as amended by the legislative instrument F2006B07498, address safety concerns associated with hydraulic system failures in specific models of Aerostar aeroplanes. Enacted by the Commonwealth of Australia, this regulation aims to prevent potential hazards, particularly in the event of a right-hand engine failure during flight, where an internal leak in the hydraulic system could cause the landing gear to automatically extend. The regulation applies to Aerostar 600 and 700 series aeroplanes not equipped with an auxiliary hydraulic pump system. The policy objective is to ensure the continued airworthiness of these aircraft by requiring a mandatory internal leak check of the hydraulic system, ensuring the landing gear remains fully retracted under specified conditions for a minimum of 30 minutes. This measure is crucial for compliance with safety standards and must be performed prior to the issue of the next Maintenance Release following 31 December 1985 and subsequently with each new Maintenance Release.
Scope and Application
The Civil Aviation Regulations 1998, specifically Part 39 - 105, which pertains to the Civil Aviation Safety Authority (CASA) Schedule of Airworthiness Directives, applies to Aerostar (Piper/Ted Smith) 600 and 700 series aeroplanes that are not equipped with an auxiliary hydraulic pump system. This regulation mandates a hydraulic system internal leak check to ensure aviation safety. The requirement is that, with the aircraft on jacks, the landing gear must remain fully retracted for a minimum of 30 minutes under specific conditions: the undercarriage should be fully retracted, the flap selector lever in neutral, and the hydraulic pressure selected off. Compliance with this directive is necessary prior to the issuance of the next Maintenance Release following 31 December 1985 and must be repeated with each new Maintenance Release thereafter. This directive aims to mitigate risks associated with potential hydraulic system leaks, which could otherwise lead to unintended landing gear extension during flight in the event of a right-hand engine failure.
Key Provisions
The Civil Aviation Regulations 1998, specifically Part 39 - 105, contain the Civil Aviation Safety Authority (CASA) Schedule of Airworthiness Directives. This includes AD/TSA-600/34, which pertains to Aerostar (Piper/Ted Smith) 600 and 700 series aeroplanes. Section 39 - 105 requires an internal leak check on the hydraulic system of these aircraft models. This directive applies to all models not equipped with an auxiliary hydraulic pump system (AD/TSA-600/34, Applicability). The primary requirement is that when the aircraft is on jacks, with the undercarriage fully retracted, the flap selector lever in the neutral position, and the hydraulic pressure turned off, the landing gear must remain in the fully retracted position for a minimum of 30 minutes (AD/TSA-600/34, Requirement). This test must be conducted prior to the issuance of the next Maintenance Release after 31 December 1985, and subsequently at each new Maintenance Release (AD/TSA-600/34, Compliance). The rationale behind this directive is to ensure that in the event of a right-hand engine failure in flight, the landing gear does not inadvertently extend to the locked down position if there is an internal leak in the hydraulic system (AD/TSA-600/34, Background).
The obligations imposed by AD/TSA-600/34 on the relevant parties, primarily aircraft owners and operators, include conducting a thorough internal leak check on the hydraulic system of the specified aircraft models. This requirement must be fulfilled to ensure the continued airworthiness of the aeroplanes and to mitigate the risk of unintended landing gear extension due to hydraulic system leaks. The compliance must be verified and documented, with the check performed before each new Maintenance Release. This ensures that the aircraft meets the safety standards set by CASA and adheres to the stipulated operational protocols. Failure to comply with this directive could result in significant safety risks and potential non-compliance with civil aviation regulations.
Under the Civil Aviation Regulations 1998, non-compliance with AD/TSA-600/34 could lead to severe consequences. While the specific penalties for breaching this directive are not detailed in the provided text, general civil aviation regulations typically impose penalties for non-compliance with airworthiness directives. These could include fines, suspension or revocation of aircraft certificates, and potential criminal charges for more severe breaches. The exact penalties can vary depending on the nature and extent of the non-compliance, and enforcement actions are typically overseen by CASA. Ensuring adherence to these directives is critical for maintaining the safety and airworthiness of the aircraft in question.