AD/CA21/6 - Life Limited Components

Overview

The Civil Aviation Regulations 1998 (Cth), specifically Part 39 - 105 concerning the Civil Aviation Safety Authority's schedule of airworthiness directives, introduces the AD/CA21/6 Life Limited Components directive for Skyfox Aviation (Calair/Hedaro) CA21 and CA22A series aeroplanes. This legislative instrument was enacted to address the issue of ensuring the airworthiness and safety of these aircraft by imposing mandatory retirement times for specific components based on their maximum allowable time in service. The enactment of this regulation by the Civil Aviation Safety Authority aims to mitigate risks associated with the fatigue life of critical aircraft components, thereby enhancing overall aviation safety. The directive applies to all CA21 and CA22A aircraft and specifies the retirement of various structural components, including wing front and rear spars, wing lift struts, carry-through structures, and the horizontal stabiliser spar, among others. These requirements are grounded in the best estimates of fatigue life, derived from stress and fatigue analyses provided by the manufacturer. Compliance with these airworthiness directives is mandatory, with the directive coming into effect from 29 February 1996, ensuring that aircraft remain within safe operational parameters throughout their service life.

Scope and Application

The Civil Aviation Regulations 1998, specifically Part 39 - 105, applies to all CA21 and CA22A aircraft within the Commonwealth of Australia, and it is enforced by the Civil Aviation Safety Authority. This legislation mandates the retirement of specified components at certain times to ensure airworthiness and safety. The Act applies directly to the aircraft operators and owners of CA21 and CA22A series aeroplanes, requiring them to adhere to the outlined component retirement schedules to maintain the aircraft's airworthiness. The regulation sets forth the maximum time in service for various components, such as the wing front and rear spars, wing lift struts, carry-through structure, and horizontal stabiliser spar, with some components requiring retirement at 4000 hours and others at 8000 hours. This legislation does not specify exclusions or exemptions, and compliance is mandatory as per the requirements set out in the regulation. The scope of this legislation is further extended through subordinate instruments that may provide additional details or clarifications regarding compliance and enforcement.

Key Provisions

The main operative sections of this legislation (Civil Aviation Regulations 1998, Part 39-105) pertain specifically to the Skyfox Aviation (Calair/Hedaro) CA21 and CA22A series aeroplanes, outlining the Airworthiness Directives (AD/CA21/6) concerning life-limited components. These provisions (Section 39-105) require certain components of these aircraft to be retired from service at specified times, determined by the maximum number of flight hours they can accumulate before reaching their fatigue limits. For example, the wing front and rear spars, as well as the wing lift struts and carry-through structure, must be retired after 4000 flight hours, while the horizontal stabiliser spar must be retired after 8000 flight hours, and all other structures, excluding doors and fairings, must also be retired after 8000 flight hours. These directives apply to all CA21 and CA22A aircraft. The obligations imposed by these regulations require operators of CA21 and CA22A series aeroplanes to ensure compliance with the specified time limits for retiring components. Operators must keep accurate records of flight hours for each component and ensure that components are removed from service at the prescribed intervals. This includes conducting regular inspections and maintenance checks to ascertain the number of flight hours each component has accumulated, and taking appropriate action when the limits are reached. The directives mandate that these actions take effect from 29 February 1996, thereby establishing a clear timeline for compliance. Failure to adhere to these Airworthiness Directives can result in significant consequences. Non-compliance with the specified retirement times for components may lead to serious safety hazards, potentially resulting in aircraft accidents. Under the Civil Aviation Act 1988, breaches of these regulations may be subject to enforcement actions, including fines and other penalties. The specific maximum penalties for non-compliance are not detailed in the provided text, but they can include substantial financial penalties and potential criminal charges for operators who fail to meet these safety standards. These consequences underscore the importance of strict adherence to the directives to ensure the continued airworthiness and safety of the aircraft.