AD/BEECH 55/69 Amdt 2 - Rudder Pedal Arms

Overview

The Civil Aviation Regulations 1998, specifically Part 39 - 105, addresses the safety concerns associated with the rudder pedal arms of Beechcraft 55, 58, and 95-55 (Baron) series aeroplanes. Enacted by the Commonwealth of Australia, this legislation aims to mitigate the risks of cracked rudder pedal arms, which can compromise the safety of the aircraft. The Rudder Pedal Arms Airworthiness Directive, AD/BEECH 55/69 Amendment 2, requires detailed inspections of the upper portions of the rudder pedal arms to detect cracks, utilising the fluorescent dye penetrant method as per CAO 108.10. This proactive measure responds to identified issues where wind loads and incorrect towing practices have contributed to pedal arm failures. The directive mandates an initial inspection before the next maintenance release following 31 October 1987, with subsequent inspections to occur at intervals not exceeding 12 months, and additional inspections before flight if the aircraft has been parked with locked rudder pedals for more than three months. This regulation underscores the importance of adhering to correct operational practices to ensure the continued airworthiness and safety of the aircraft.

Scope and Application

The Civil Aviation Safety Authority (CASA) under the Civil Aviation Regulations 1998 mandates specific airworthiness directives for Beechcraft 55, 58, and 95-55 (Baron) series aeroplanes. AD/BEECH 55/69 Amendment 2 applies to all models equipped with rudder pedal arms part number 50-524326, irrespective of the dash number. The directive requires the inspection of the upper portion of each rudder pedal arm for cracks, employing the fluorescent dye penetrant method in accordance with Civil Aviation Order (CAO) 108.10. The inspection must cover the upper part of the "I" section shank, the hollow crossbar, and the brake pedal attachment lugs, with a particular emphasis on the fillet radii and holes. The initial inspection must occur before the next maintenance release following 31 October 1987, with subsequent inspections required at intervals not exceeding 12 months. For aircraft that have been parked for more than three months with the rudder pedals locked, an inspection must be conducted before flight. This regulation is crucial as it addresses the issue of premature cracking, which is primarily caused by wind loads when the aircraft is parked with the rudder pedals locked, rather than normal operating loads. Additionally, the Maintenance Manual prohibits towing with the rudder pedals locked, and this directive includes a warning against such practices.

Key Provisions

The Civil Aviation Regulations 1998, under PART 39 - 105, contains the Civil Aviation Safety Authority (CASA) Schedule of Airworthiness Directives. Specifically, AD/BEECH 55/69 Amendment 2 pertains to the inspection requirements for rudder pedal arms in Beechcraft 55, 58, and 95-55 (Baron) Series Aeroplanes. The directive applies to all models equipped with rudder pedal arms bearing the part number 50-524326, regardless of dash number. The primary requirement of this directive is to conduct an inspection of the upper portion of each rudder pedal arm to detect any cracks, utilising the fluorescent dye penetrant method as specified in Civil Aviation Order (CAO) 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 where cracks are most likely to occur. Compliance with this directive involves two key steps. Firstly, an initial inspection must be carried out before the issuance of the next maintenance release following 31 October 1987. Subsequent inspections are mandated at intervals not exceeding 12 months. Additionally, the aircraft must be inspected before flight if it has been parked for more than three months with the rudder pedals locked. This additional inspection is crucial because the Maintenance Manual prohibits towing with locked rudder pedals, a practice that can cause premature cracking. This directive underscores the importance of adhering to proper maintenance and operational practices to ensure the airworthiness of the aircraft. The obligations imposed by AD/BEECH 55/69 Amendment 2 on the operators and maintenance personnel are clear and specific. Operators and maintenance personnel must ensure that the inspections are conducted as required, using the specified inspection method and paying particular attention to the identified high-risk areas of the rudder pedal arms. The directive also mandates that any detected cracks be appropriately addressed before the aircraft is returned to service. Failure to comply with these inspection requirements can result in serious safety risks, as cracked rudder pedal arms can compromise the aircraft's control and structural integrity, potentially leading to in-flight failures. Failure to comply with the provisions of AD/BEECH 55/69 Amendment 2 can result in significant legal and safety consequences. The Civil Aviation Regulations provide for both civil and criminal penalties for non-compliance with airworthiness directives. Civil penalties can include fines and orders for corrective action, while criminal penalties may include imprisonment for individuals responsible for the non-compliance. The exact penalties depend on the severity of the non-compliance and any resultant safety risks. It is crucial for operators and maintenance personnel to adhere to these directives to avoid these severe consequences and to maintain the highest standards of aviation safety.