AD/CESSNA 210/58 Amdt 1 - Turbocharger Oil Reservoir Outlet Fitting

Overview

The Civil Aviation Regulations 1998, administered by the Civil Aviation Safety Authority (CASA), aim to ensure the safety and efficiency of civil aviation operations in Australia. The specific legislative instrument in focus is the AD/CESSNA 210/58 Amendment 1, which addresses a critical safety concern identified in certain Cessna 210 series aeroplanes. This regulation was enacted to address the risk of turbocharger oil reservoir outlet fitting cracking, which could lead to rapid loss of engine oil and compromise flight safety. The policy objective behind this directive is to mandate compliance with specific maintenance actions to prevent such safety hazards and ensure the continued airworthiness of affected aircraft. The Civil Aviation Regulations 1998, through this specific directive, require all applicable Cessna 210N, 210R, and T210R aeroplanes to adhere to either the Cessna Service Bulletin SEB 85-11 or the FAA AD 85-11-07. The directive mandates an initial inspection before further flight after 13 June 1985 and subsequent inspections every 25 hours of operation until the required modifications are made. Compliance with this directive is essential to mitigate the risk of engine oil loss and maintain the safety standards required under Australian civil aviation law.

Scope and Application

The Civil Aviation Regulations 1998, specifically under Part 39 - 105, which pertains to the Civil Aviation Safety Authority's schedule of airworthiness directives, apply to all model P210N, P210R, and T210R Cessna 210 Series aeroplanes with serial numbers ranging from P21000001 to P21000855 and from 21064898 to 21064929. This regulation mandates compliance with either Cessna Service Bulletin SEB 85-11 or FAA AD 85-11-07 concerning the turbocharger oil reservoir outlet fitting. The requirement necessitates immediate action before further flight after 13 June 1985, and if no cracks are identified during the initial inspection, a subsequent inspection must occur every 25 hours of time in service until the fitting is modified according to the specified requirement documents. It is noteworthy that adherence to the previous version of this directive satisfies the compliance criteria of this amended version. This legislative instrument extends its jurisdictional reach throughout the Commonwealth of Australia, overseen by the Civil Aviation Safety Authority.

Key Provisions

The Civil Aviation Regulations 1998, under Part 39 - 105, specifically address the airworthiness directives for certain Cessna 210 series aeroplanes. One such directive, AD/CESSNA 210/58 Amendment 1, pertains to the turbocharger oil reservoir outlet fitting for model P210N, P210R, and T210R with specific serial numbers. This directive requires compliance with either Cessna Service Bulletin SEB 85-11 or FAA AD 85-11-07 to ensure the safety and airworthiness of these aircraft. To comply with this directive, all affected aircraft must adhere to specific actions before any further flight after 13 June 1985. Initially, an inspection must be conducted to identify any cracks in the turbocharger oil reservoir outlet fitting. If no cracks are found, the aircraft may continue to operate pending further inspection, which must occur every 25 hours of time in service until the fitting is modified as per the requirement document. It is also noted that compliance with the previous issue of this directive satisfies the requirements of this current issue. The obligations imposed by this directive are clear and specific. Operators of the affected Cessna 210 series aeroplanes must ensure that their aircraft are inspected and, if necessary, modified to comply with the outlined requirements. This involves a thorough initial inspection and subsequent regular inspections every 25 hours until modifications are completed. Failure to adhere to these requirements could result in the aircraft being deemed unairworthy, potentially leading to severe operational disruptions and safety risks. Failure to comply with the provisions of this airworthiness directive may result in significant consequences. The primary concern is the risk of rapid loss of engine oil due to cracked turbocharger oil reservoir outlet fittings, which could lead to engine failure mid-flight. This could result in accidents and potentially catastrophic outcomes. While the regulations themselves do not specify particular penalties, any resultant accidents or safety breaches could lead to investigations, fines, or other penalties under broader aviation safety laws. Ensuring compliance is therefore critical for maintaining the safety and airworthiness of the aircraft.