AD/CESSNA 205/5 Amdt 1 - Rear Spar

Overview

The Civil Aviation Regulations 1998 (Cth) were enacted to regulate civil aviation safety in Australia, aiming to ensure that all aviation operations meet the necessary safety standards. This legislative instrument, in particular, addresses the maintenance and airworthiness of aircraft, specifically targeting the Cessna 205 (210-5) Series Aeroplanes. The regulation was introduced to address the identified safety issue of fatigue cracks in the rear spar of certain models, which could potentially compromise the structural integrity of the aircraft. This safety directive, AD/CESSNA 205/5Amdt 1, mandates regular inspections of the rear spar to detect and prevent such cracks, ensuring the ongoing airworthiness of these aircraft. The compliance requirements are set forth to maintain high safety standards within the civil aviation sector, overseen by the Civil Aviation Safety Authority. The Civil Aviation Regulations 1998, overseen by the Commonwealth Parliament, aim to ensure that all civil aviation operations in Australia adhere to stringent safety standards. The specific airworthiness directive concerning the Cessna 205 (210-5) Series Aeroplanes, AD/CESSNA 205/5Amdt 1, targets the rear spar of these aircraft, requiring detailed inspections for fatigue cracks to prevent potential structural failures. The policy objective is to enhance the safety of air travel by mandating regular checks and maintenance procedures, thereby reducing the risk of in-flight incidents due to structural weaknesses. This directive was issued by the Civil Aviation Safety Authority to ensure that operators comply with the stipulated inspection intervals, maintaining the safety and reliability of these aircraft in Australian airspace.

Scope and Application

The Civil Aviation Regulations 1998, under Part 39 - 105, specify the Airworthiness Directives (AD) issued by the Civil Aviation Safety Authority (CASA). The particular legislation in focus here pertains to Cessna 205 (210-5) Series Aeroplanes, with AD/CESSNA 205/5 Amendment 1 addressing the inspection of the rear spar. This directive applies to all models of the Cessna 205 series except those identified by specific rear spar part numbers 0523400-90 LH, -91 RH, -111 LH, and -112 RH. The requirement is for a visual inspection of the main plane rear spar web at the root attachment area and the upper flange of the rear spar channel at the outer end of the attachment fittings for fatigue cracks, which typically originate in the radius beneath the attachment fittings. The inspection must be performed using a magnifying glass of at least 4X magnification, or an approved device like the “Syte Ade.” If cracks are suspected but difficult to detect due to the close fit of the trailing edge root end rib to the spar, the rib may be temporarily removed for a more detailed examination. This directive is applicable to any aircraft within 100 hours of time in service after 30 November 1967 and requires subsequent inspections at intervals not exceeding 100 hours of time in service.

Key Provisions

The Civil Aviation Regulations 1998 (Cth), specifically Part 39 - 105, establish the Civil Aviation Safety Authority's Schedule of Airworthiness Directives. One such directive is AD/CESSNA 205/5 Amendment 1, which pertains to the rear spar of Cessna 205 (210-5) Series Aeroplanes, excluding those with certain rear spar part numbers. The directive requires a visual inspection of the main plane rear spar web at the root attachment area and the upper flange of the rear spar channel at the outer end of the attachment fittings for any fatigue cracks (Section 1). These cracks must be inspected specifically for those originating in the radius located beneath the attachment fittings. The inspection can be performed using a magnifying glass of at least 4X magnification, or alternatively, a device such as the “Syte Ade” may be employed. In cases where the trailing edge root end rib fits closely to the spar, and there is doubt regarding the presence of cracks, the trailing edge root end rib must be removed for a more detailed inspection. The directive imposes obligations on the operators and maintenance personnel to ensure that the specified inspections are carried out diligently. Operators must conduct these inspections within 100 hours of the aircraft's time in service after 30 November 1967 and thereafter at intervals not exceeding 100 hours of time in service. The inspection must be thorough and accurate to ensure that any fatigue cracks are identified and addressed to maintain the airworthiness of the aircraft. The affected area is illustrated in Rex Aviation Technical Memorandum No. 12 dated 10 May 1960, providing further guidance on the specific areas that need to be inspected. Failure to comply with the requirements set out in this directive may result in serious safety risks. The Civil Aviation Safety Authority enforces these regulations rigorously, and non-compliance could lead to serious civil or criminal consequences. The specific offences, penalties, or consequences for breach are not detailed in the provided text, but generally, violations of airworthiness directives can result in penalties under the Civil Aviation Act 1988 (Cth), which may include fines and potential imprisonment for serious breaches. The exact penalties would depend on the severity of the non-compliance and the impact on aviation safety.