AD/BEECH 56/27 Amdt 2 - Rudder Pedal Arms

Overview

The Civil Aviation Regulations 1998, under Part 39 - 105, issued by the Civil Aviation Safety Authority, aim to ensure the safety and airworthiness of aircraft within Australian airspace. Specifically, the regulation AD/BEECH 56/27Amdt 2 addresses issues related to the rudder pedal arms of Beechcraft 56TC (Turbo Baron) Series aeroplanes. The enactment of this regulation was in response to concerns over cracked rudder pedal arms, primarily caused by wind loads when the aircraft was parked on the ground with the rudder pedals locked. The regulation mandates inspections of the upper portion of the rudder pedal arms for cracks using the fluorescent dye penetrant method. The policy objective is to mitigate the risk of structural failure by ensuring regular inspections and adherence to correct maintenance practices. The regulation stipulates an initial inspection before the next maintenance release following 31 October 1987, with subsequent inspections at intervals not exceeding 12 months. Additionally, inspections are required before flight if the aircraft has been parked for more than three months with the rudder pedals locked. The regulation also includes a warning against towing with the rudder pedals locked, as this practice can lead to premature cracking. This legislative measure aims to maintain the safety and reliability of Beechcraft 56TC aeroplanes by addressing the identified issues with rudder pedal arms.

Scope and Application

The Civil Aviation Regulations 1998, specifically under Part 39 - 105, pertains to the Airworthiness Directives for certain aircraft models, with the focus here being on the Beechcraft 56TC (Turbo Baron) Series Aeroplanes. This regulation applies to all models of the aircraft equipped with rudder pedal arms with specific part numbers, namely 50-524326, across all dash numbers. The regulation mandates an inspection of the upper portion of each rudder pedal arm to identify any cracks using the fluorescent dye penetrant method as outlined in Civil Aviation Order 108.10. The inspection must cover the upper part of the 'I' section shank, the hollow crossbar, and the brake pedal attachment lugs, with particular attention to the fillet radii and holes. The requirement necessitates an initial inspection before the next maintenance release following 31 October 1987 and subsequent inspections at intervals not exceeding 12 months. Moreover, an inspection is mandated before flight if the aircraft has been parked for over three months with the rudder pedals locked, a practice which the Maintenance Manual prohibits due to its potential to cause premature cracking. The regulation applies nationally, ensuring that all relevant operators and maintainers within Australia adhere to these safety standards.

Key Provisions

The Civil Aviation Regulations 1998, specifically in Part 39, includes the Civil Aviation Safety Authority's Schedule of Airworthiness Directives, which mandates detailed maintenance requirements for specific aircraft types. For the Beechcraft 56TC (Turbo Baron) Series Aeroplanes, the AD/BEECH 56/27 Amendment 2, issued on 4th September 1995, pertains to the rudder pedal arms (Section 1). This directive applies to all models fitted with rudder pedal arms with part number 50-524326, irrespective of the dash number. The directive requires an inspection of the upper portion of each rudder pedal arm for cracks, employing the fluorescent dye penetrant method in line with CAO 108.10 (Section 2). The inspection should focus on the upper part of the ‘I’ section shank, the hollow crossbar, and the brake pedal attachment lugs, with special attention to the fillet radii and holes (Section 3). Compliance with the directive involves conducting the initial inspection before the release of the next maintenance update following 31 October 1987. Thereafter, the inspections must be conducted at intervals not exceeding 12 months (Section 4). Additionally, an inspection is required before any flight if the aircraft has been stationary for more than three months with the rudder pedals locked (Section 5). It is noteworthy that the Maintenance Manual prohibits towing with the rudder pedals locked, as this practice can lead to premature cracking (Section 6). The directive's background indicates that wind loads when the aircraft is parked on the ground with the rudder pedals locked are the primary cause of cracking, with normal operating loads being a secondary factor (Section 7). As a result, the inspection interval is now based on calendar time, with special provisions made for aircraft parked in open areas for extended periods, and a warning has been added regarding correct towing practices (Section 8). Breach of the requirements outlined in the AD/BEECH 56/27 Amendment 2 may result in severe consequences. Civil Aviation Regulations 1998, under Section 129, stipulates that failure to comply with an Airworthiness Directive can lead to serious safety risks, which may result in enforcement actions. The Civil Aviation Safety Authority (CASA) has the authority to take measures such as grounding the aircraft, imposing fines, or pursuing legal action against the operator or maintenance provider who fails to comply with the directive (Section 9). Additionally, operators and maintenance providers are required to maintain detailed records of inspections and any corrective actions taken, as stipulated in the regulations (Section 10). The potential penalties for non-compliance could include substantial fines and the possibility of criminal charges, depending on the severity of the breach and its impact on aviation safety (Section 11).