AD/DH 82/3 - Rudder Bar Attachment Spigot - Modification

Overview

The Civil Aviation Regulations 1998, amended by F2006B08901, were enacted to address safety concerns related to the Tiger Moth series aeroplanes, specifically focusing on the rudder bar attachment spigot. The Civil Aviation Safety Authority, under the authority of the Parliament of Australia, introduced this legislative instrument to ensure compliance with safety standards and mitigate the risk of rudder bar malfunctions that could lead to hazardous situations during flight. The policy objective is to mandate modifications to the rudder bar attachment to prevent the locking pins from becoming unclipped or jammed, thereby enhancing the overall safety of these aircraft. Compliance with these directives is required forthwith, ensuring that all Tiger Moth series aeroplanes meet the specified safety requirements.

Scope and Application

The Civil Aviation Regulations 1998, specifically Part 39 - 105, as detailed in the Civil Aviation Safety Authority Schedule of Airworthiness Directives, applies to all DH 82 (Tiger Moth) series aeroplanes. This regulation mandates that modifications be made to the front and rear rudder bars to prevent the connecting rod locking pins from becoming unclipped or jammed by fouling the control box. The requirement includes relocating the connecting rod locking pins by drilling a No. 50 hole at a 90° angle to the existing athwartships holes in the rudder bar attachment spigots, ensuring the new holes are centrally located below the existing ones, and plugging the old holes with suitable wire rivets. The modification must be completed using an approved method and locking the rudder bar connecting rod ends with AGS No. 1551 Mk. 3 locking pins. Compliance with these modifications must be achieved forthwith, as specified in ANO 105.1.14.5.5.3. This regulation is applicable nationwide, under the Commonwealth of Australia's jurisdiction, and extends to all Tiger Moth series aeroplanes operating within Australia. There are no stated exclusions or exemptions, and the directive does not reference any subordinate instruments that might further extend or restrict its application.

Key Provisions

The Civil Aviation Regulations 1998 (Cth), under Part 39, contain specific airworthiness directives (ADs) aimed at ensuring the safety of aircraft operations. One such directive, AD/DH 82/3, pertains to the modification of the rudder bar attachment spigot for DH 82 (Tiger Moth) series aeroplanes. This directive, outlined in section 1, requires all models of these aeroplanes to undergo a specific modification to the rudder bar system to prevent potential control issues (section 1(1)). The modification involves relocating the connecting rod locking pins to ensure they do not become unclipped or jammed by fouling the control box (section 1(2)). To comply with this directive, the front and rear rudder bars must be modified according to an approved method. Firstly, a No. 50 hole must be drilled at a 90-degree angle to the existing athwartships holes in the front and rear rudder bar connecting rod attachment spigots (section 1(2)(a)). The new holes should be centrally located below the existing holes, ensuring they are sufficiently clear of the rudder bar connecting rod for the free fitment of the locking pins in a fore and aft direction. Secondly, the existing holes must be plugged with suitable wire rivets (section 1(2)(b)). Finally, when installing the rudder bar connecting rod, it must be locked up to the rudder bar spigots with AGS No. 1551 Mk. 3 locking pins (section 1(2)(c)). This procedure is intended to enhance the safety and reliability of the rudder bar system, thus preventing potential in-flight control problems. Operators and owners of DH 82 (Tiger Moth) series aeroplanes are obligated to implement these modifications promptly, as specified by the directive (section 1(3)). The directive mandates compliance forthwith, meaning that the required modifications must be completed without undue delay to ensure the continued airworthiness of the aircraft. Failure to adhere to these requirements may result in significant safety risks, potentially leading to non-compliance with the Civil Aviation Safety Authority’s standards and regulations. Additionally, non-compliance could result in enforcement actions, including fines and other penalties as outlined in the Civil Aviation Act 1988 (Cth) and the Civil Aviation Regulations 1998 (Cth). Violators of these airworthiness directives may face civil and criminal consequences. Under the Civil Aviation Regulations 1998, non-compliance with airworthiness directives can result in substantial fines. For corporations, the maximum penalty can extend to $525,000, as outlined in section 94A of the Civil Aviation Act 1988 (Cth). For individuals, the penalties can include fines of up to $105,000 and, in serious cases, imprisonment. Furthermore, the Civil Aviation Safety Authority has the authority to take enforcement actions, including grounding the aircraft until compliance is achieved, which can severely disrupt operations and incur additional costs for the operator. Therefore, it is imperative that all relevant parties adhere strictly to the AD/DH 82/3 directive to avoid these serious consequences.