AD/BEECH 90/78 Amdt 2 - Rudder Pedal Arms

Overview

The Civil Aviation Regulations 1998, enacted by the Australian Parliament, aim to ensure the safety and efficiency of civil aviation within Australia. Among these regulations, Part 39 – 105 Civil Aviation Safety Authority Schedule of Airworthiness Directives specifically addresses the maintenance and safety requirements for various aircraft models. One such directive is AD/BEECH 90/78 Amendment 2, which pertains to the inspection of rudder pedal arms on Beechcraft 90 and 65-90 (King Air) series aeroplanes. This directive was introduced to address the issue of cracked rudder pedal arms, which pose a significant safety risk. The policy objective is to enhance the safety of these aircraft by mandating regular inspections and maintenance of the rudder pedal arms, thereby reducing the likelihood of structural failure during flight. The directive emphasises the importance of thorough inspections using specific methods to detect cracks, particularly in critical areas such as the fillet radii and holes, and provides guidelines for the frequency and conditions under which these inspections should be conducted.

Scope and Application

The Civil Aviation Safety Authority's regulations, specifically Part 39 - 105 within the Civil Aviation Regulations 1998, address airworthiness directives concerning Beechcraft 90 and 65-90 (King Air) Series Aeroplanes. This legislation applies to all aircraft models equipped with rudder pedal arms P/N 50-524326, regardless of their dash numbers. The directive mandates a thorough inspection of the upper portion of each rudder pedal arm for any signs of cracks, utilising the fluorescent dye penetrant inspection method as outlined in CAO 108.10. The areas requiring attention include the upper part of the “I” section shank, the hollow crossbar, and the brake pedal attachment lugs, with a special emphasis on the fillet radii and holes. This regulatory requirement is designed to ensure the ongoing airworthiness and safety of the aircraft, particularly focusing on preventing premature cracking that can arise from wind loads when the aircraft is parked with the rudder pedals locked, and from standard operational stresses. The regulations mandate an initial inspection before the next maintenance release following 31 October 1987, with subsequent inspections required at intervals not exceeding 12 months. Additionally, an inspection is necessary before any flight if the aircraft has been stationary for more than three months with the rudder pedals locked. This directive aims to mitigate risks associated with such extended periods of inactivity and provides specific guidance on appropriate towing practices to avoid exacerbating the issue of pedal arm cracking.

Key Provisions

The Civil Aviation Regulations 1998, specifically Part 39, Section 105, which concerns the Civil Aviation Safety Authority’s Schedule of Airworthiness Directives, includes a provision for the Beechcraft 90 and 65-90 (King Air) series aeroplanes. This directive, AD/BEECH 90/78 Amendment 2, pertains to the inspection of rudder pedal arms. Section (4/95) outlines the requirement to inspect the upper portion of each rudder pedal arm for cracks. The inspection must be conducted using the fluorescent dye penetrant method in accordance with CAO 108.10. The areas of focus for this inspection include the upper part of the "I" section shank, the hollow crossbar, and the brake pedal attachment lugs, with special attention given to the fillet radii and holes. The obligations imposed by this directive require that the initial inspection be completed before the issue of the next maintenance release after 31 October 1987. Furthermore, the regulation mandates that subsequent inspections occur at intervals not exceeding 12 months. An additional requirement is that an inspection must be conducted before flight if the aircraft has been parked for more than three months with the rudder pedals locked. The directive also notes that the Maintenance Manual prohibits towing with the rudder pedals locked, and such practices may lead to premature cracking. This directive is designed to address the issue of cracked rudder pedals, which are primarily caused by wind loads when the aircraft is parked on the ground with the rudder pedals locked, with normal operating loads being a secondary factor. In the event of non-compliance with the provisions outlined in AD/BEECH 90/78 Amendment 2, there are potential civil and criminal consequences. While the specific penalties are not detailed in the text, it is clear that failure to adhere to the inspection requirements and intervals could result in serious safety issues. The Civil Aviation Safety Authority may impose penalties, and in severe cases, the breach of these regulations could lead to criminal charges. The exact penalties would depend on the specific circumstances of the non-compliance and the discretion of the enforcement authorities. However, the overarching objective is to ensure the safety and airworthiness of the aircraft in accordance with the stringent standards set forth by the Civil Aviation Regulations 1998.