AD/GAF-N22/53 - Taper Pins - Control Systems

Overview

The Civil Aviation Regulations 1998 (Cth) were enacted to ensure the safety and regulation of civil aviation within Australia. The Civil Aviation (Safety) Act 1998 (Cth) provided the legislative framework for these regulations, which were introduced by the Australian Government to address the need for comprehensive and enforceable safety standards within the civil aviation industry. Specifically, Part 39 - 105 addresses Airworthiness Directives for various aircraft types, including the GAF N22 and N24 Series Aeroplanes, with the objective of ensuring these aircraft maintain safe operational standards. The regulation mandates inspections and modifications for taper pins in control systems to prevent excessive movement of the control column, thereby enhancing flight safety. This legislative instrument was issued by the Civil Aviation Safety Authority (CASA), pursuant to section 92 of the Civil Aviation Act 1988 (Cth). The directive aims to ensure the continued airworthiness of specified aircraft by addressing potential safety issues related to taper pins, specifically their tendency to loosen and cause excessive movement in the control column, which could lead to dangerous flight conditions. The regulation requires specific actions to be taken within prescribed timeframes to maintain compliance with safety standards.

Scope and Application

The Civil Aviation Regulations 1998, specifically Part 39 - 105 concerning the Civil Aviation Safety Authority Schedule of Airworthiness Directives, applies to all Nomad N22, N22B, N22C, N22S, N24, and N24A aircraft within the Commonwealth of Australia. This legislation mandates specific actions concerning the control systems of these aircraft to ensure airworthiness and safety. For control column universal joints fitted with taper pins that have not incorporated modification N428, the requirement is to follow the instructions detailed in Nomad Alert SB ANMD-27-39. Additionally, all other control systems must undergo inspection for looseness or evidence of looseness in the taper pins. Compliance with these directives must occur within certain time frames post the date of issuance of the directive, specifically within 10 hours of service after 22 August 1988, and subsequently at intervals not exceeding 100 hours of service until the modification is completed as per the directive. If looseness is detected, modifications must be performed before further flight. The directive also requires inspection within 100 hours of service after 22 August 1988, or at the next scheduled inspection for Maintenance Release. This ensures ongoing compliance unless the aircraft is modified in accordance with a scheme approved by the Authority. The legislation does not explicitly state any exclusions or thresholds but relies on the application of the subordinate instruments like the Nomad Alert SB ANMD-27-39 for detailed procedures and modifications.

Key Provisions

The Civil Aviation Regulations 1998, specifically under Part 39 - 105, contains an Airworthiness Directive (AD) concerning the Nomad N22 and N24 series aeroplanes (sections 11/88 T). This directive applies to all Nomad N22, N22B, N22C, N22S, N24, and N24A aircraft. It mandates actions to ensure the safety of control systems by addressing the issue of taper pins working loose, which could lead to excessive free movement of the control column. The directive outlines two main requirements. Firstly, for left-hand (L.H.) and right-hand (R.H.) control column universal joints fitted with taper pins, but not incorporating modification N428, the directive requires action in accordance with Nomad Alert Service Bulletin (SB) ANMD-27-39. Secondly, for taper pins fitted to all other control systems, it mandates inspections for looseness or evidence of looseness. The obligations imposed by the AD include conducting the required actions and inspections within specified timeframes. For L.H. and R.H. control column universal joints, inspections and actions must be completed within 10 hours of time in service after 22 August 1988, and thereafter at intervals not exceeding 100 hours of time in service until the modification has been carried out in accordance with Part B of Nomad Alert SB ANMD-27-39. However, this must not be later than 300 hours of time in service after 22 August 1988 or by 22 November 1988, whichever occurs first. If taper pins are found loose or with evidence of looseness, modifications must be carried out before further flight. For all other control systems with taper pins, inspections must be completed within 100 hours of time in service after 22 August 1988 or at the next scheduled inspection for Maintenance Release issue after 22 August 1988, whichever occurs first. Thereafter, inspections must occur at each inspection for Maintenance Release, unless the control systems have been modified in accordance with a scheme approved by the Authority. Failure to comply with the requirements of the AD may result in serious safety implications. The regulations do not explicitly state penalties or specific consequences for non-compliance within the provided text. However, non-compliance with airworthiness directives can lead to civil or criminal penalties under broader aviation safety laws. The severity of penalties can vary, but they may include fines and potential grounding of the aircraft, which can have significant operational and financial impacts on the operators. It is essential for operators to adhere to these directives to ensure the continued airworthiness and safety of the aircraft.