COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
SCHEDULE OF AIRWORTHINESS DIRECTIVES
Beechcraft 36 (Bonanza) Series Aeroplanes
AD/BEECH 36/31
Amdt 2
Rudder Pedal Arms 4/95
Applicability: All models fitted with rudder pedal arms P/N 50-524326, all dash numbers.
Requirement: Inspect the upper portion of each rudder pedal arm for cracks, using the fluorescent dye penetrant method in accordance with CAO 108.10. The area to be inspected includes the upper part of the “I” section shank, the hollow crossbar and the brake pedal attachment lugs. Particular attention must be paid to the fillet radii and holes.
Compliance: 1. Initially inspect before the issue of the next maintenance release after 31 October 1987. Re-inspect at intervals not to exceed 12 months.
2. Inspect before flight if the aircraft has been parked for more than 3 months with the rudder pedals locked.
Note: The Maintenance Manual prohibits towing with the rudder pedals locked. This practice may also cause premature cracking.
Background: A review of cracked rudder pedals suggests that the primary cause of cracking is wind loads when the aircraft is parked on the ground with the rudder pedals locked, normal operating loads being a secondary factor. The inspection interval is now based on calendar time, special provision is made for aircraft parked in the open for long periods and a warning has been added about correct towing practice.
Overview
The Civil Aviation Regulations 1998, as amended by the Legislative Instrument F2006B03886, address the safety concerns associated with the cracking of rudder pedal arms in Beechcraft 36 (Bonanza) series aeroplanes. This regulation was enacted to mitigate the risk of structural failure in the rudder pedal arms, which could potentially lead to serious flight safety issues. The policy objective, as outlined in the legislative instrument, is to ensure the airworthiness of these aircraft by mandating regular inspections of the rudder pedal arms to detect and address any cracks before they compromise the aircraft's safety. The Civil Aviation Safety Authority (CASA) administers these regulations, with the aim of maintaining high safety standards in the aviation sector. The inspection regime is designed to catch potential issues early, especially given the identified cause of cracking due to wind loads when the aircraft is parked with the rudder pedals locked, thereby ensuring that these aeroplanes remain safe for operation.
Scope and Application
The Civil Aviation Regulations 1998, as amended by AD/BEECH 36/31, apply specifically to all Beechcraft 36 (Bonanza) series aeroplanes equipped with rudder pedal arms bearing part number 50-524326, regardless of their dash numbers. This directive is issued under the authority of the Civil Aviation Safety Authority (CASA) and pertains to the inspection of the upper portions of the rudder pedal arms for cracks, particularly focusing on the "I" section shank, the hollow crossbar, and the brake pedal attachment lugs, with special attention to the fillet radii and holes. Compliance with this airworthiness directive involves an initial inspection before the release of the next maintenance update following 31 October 1987, and subsequent inspections must occur at intervals not exceeding 12 months. Furthermore, an inspection is mandated before flight if the aircraft has been stationary for more than three months with the rudder pedals locked, and operators are cautioned against towing with the rudder pedals locked due to potential premature cracking. This directive is applicable across the Commonwealth of Australia, encompassing both state and territory jurisdictions, and is integral to maintaining the airworthiness and safety standards of the specified aircraft models.
Key Provisions
The Civil Aviation Regulations 1998, specifically Part 39 - 105, outlines the Airworthiness Directive (AD) concerning the Beechcraft 36 (Bonanza) Series Aeroplanes. This directive, identified as AD/BEECH 36/31 Amendment 2, pertains to the rudder pedal arms of all models fitted with rudder pedal arms P/N 50-524326, regardless of the dash number. The directive mandates a comprehensive inspection of the upper portion of each rudder pedal arm for any cracks. This inspection must be performed using the fluorescent dye penetrant method, as stipulated in CAO 108.10. The focus of the inspection should be on 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 (Section 4/95).
To comply with this directive, operators must initially inspect the rudder pedal arms before the release of the next maintenance update after 31 October 1987. Following this initial inspection, further inspections must be conducted at intervals not exceeding 12 months. In addition to the periodic inspections, operators are required to inspect the rudder pedal arms before flight if the aircraft has been parked for more than three months with the rudder pedals locked. It is noteworthy that the Maintenance Manual prohibits towing with the rudder pedals locked, as this practice may lead to premature cracking of the rudder pedal arms.
Failure to comply with the requirements set out in this directive can lead to serious consequences. The primary cause of cracked rudder pedal arms, as identified in the background information, is wind loads when the aircraft is parked on the ground with the rudder pedals locked. Normal operating loads are a secondary factor. By adhering to the specified inspection intervals and maintaining correct towing practices, operators can mitigate the risk of structural failure due to cracked rudder pedal arms. Non-compliance could result in safety risks and potential regulatory action.