AD/CESSNA 210/5 Amdt 2 - Rear Spar - Inspection

Overview

The Civil Aviation Regulations 1998, specifically within Part 39 - 105, detail the Civil Aviation Safety Authority’s (CASA) Schedule of Airworthiness Directives for the Cessna 210 Series Aeroplanes. This legislative instrument was enacted to address issues of aircraft safety, ensuring that all civil aircraft operate under stringent airworthiness standards. The objective of these regulations is to mitigate potential safety risks by mandating specific inspections and maintenance procedures. For instance, AD/CESSNA 210/5 Amendment 2 requires a detailed visual inspection of the main plane rear spar web and the upper flange of the rear spar channel, especially at the outer end of the attachment fitting, to detect any fatigue cracks. This inspection is crucial for all applicable Cessna 210 models, excluding cantilever wing models prior to the 210G model, and must be performed at intervals not exceeding 100 hours of time in service post 1 September 1971. This instrument aims to ensure that any potential structural weaknesses in the rear spar of these aircraft are identified and rectified promptly, thereby enhancing overall aviation safety. The regulations are enforced by CASA and require adherence to the specified inspection methods, which may involve using magnifying glasses or other inspection tools to ensure comprehensive checks. The detailed inspection procedures outlined in the regulations are intended to prevent structural failures and ensure the continued airworthiness of the affected aircraft.

Scope and Application

The Civil Aviation Regulations 1998, as amended, apply to all aircraft operations within Australia, ensuring that airworthiness directives such as AD/CESSNA 210/5 Amendment 2 are adhered to. This particular directive applies to Cessna 210 series aeroplanes, excluding cantilever wing models and those produced before the 210G model. The regulation mandates a specific inspection of the rear spar of these aircraft to detect potential fatigue cracks that may compromise safety. The directive requires a thorough visual inspection of the rear spar web at the root attachment area and the upper flange of the rear spar channel using a magnifying glass or an approved alternative device. If there is any uncertainty, the trailing edge root end rib must be removed for a more detailed inspection. This directive extends its requirement to all Cessna 210 series aircraft, barring the specified exclusions, and mandates compliance at intervals not exceeding 100 hours of time in service post 1 September 1971. The directive is enforced to maintain the highest safety standards within civil aviation operations across Australia.

Key Provisions

The Civil Aviation Regulations 1998, specifically Part 39 - 105, addresses the requirements for airworthiness directives for various aircraft types, including the Cessna 210 Series Aeroplanes. One such directive, AD/CESSNA 210/5 Amendment 2, focuses on the inspection of the rear spar of these aircraft. This amendment applies to all models except those with cantilever wings, specifically those prior to model 210G. The primary requirement of this directive is to visually inspect the main plane rear spar web at the root attach area and the upper flange of the rear spar channel, particularly at the outer end of the attachment fitting (Section 1). The inspection is to identify any fatigue cracks that may originate from the radius beneath the attachment fittings (Section 2). This inspection should be conducted using a magnifying glass with at least 4X magnification or an alternative device such as the "Syte Ade" (Section 3). In cases where the trailing edge root end rib fits closely to the spar, making detection of cracks difficult, the trailing edge root end should be removed for a more detailed inspection if there is any doubt (Section 4). The Cessna 210 Series Aeroplanes governed by this directive must adhere to strict compliance protocols. Operators are required to conduct these inspections at intervals not exceeding 100 hours of time in service after 1 September 1971. This periodic inspection ensures the aircraft's structural integrity and safety, as the identified areas are critical to the aircraft's overall performance and stability. The directive references Rex Aviation Technical Memorandum No. 12 dated 10 May 1960, which illustrates the affected areas for clarity and accuracy during inspections. Failure to comply with the requirements of AD/CESSNA 210/5 Amendment 2 can result in significant consequences. While the specific civil or criminal penalties are not detailed in the provided text, non-compliance with airworthiness directives generally can lead to enforcement actions by the Civil Aviation Safety Authority (CASA). These actions may include fines, suspension or revocation of airworthiness certificates, and other regulatory sanctions. The severity of these penalties can vary depending on the nature and extent of the non-compliance, as well as any resulting safety risks. Ensuring adherence to these directives is crucial for maintaining the safety and airworthiness of the aircraft in question.