COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
SCHEDULE OF AIRWORTHINESS DIRECTIVES
Beechcraft 35 (Bonanza) Series Aeroplanes
AD/BEECH 35/59
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, administered by the Civil Aviation Safety Authority, was enacted to ensure the safety and efficiency of civil aviation within Australia. This regulatory framework includes specific directives to address identified safety concerns, such as the Airworthiness Directive AD/BEECH 35/59 Amendment 2 concerning Beechcraft 35 (Bonanza) series aeroplanes. The objective of this directive is to mitigate the risk of cracked rudder pedal arms, which can compromise the aircraft's control and safety. This directive requires a mandatory inspection of the upper portion of the rudder pedal arms, particularly focusing on the "I" section shank, the hollow crossbar, and the brake pedal attachment lugs, to detect any cracks. Such inspections are essential to ensure the airworthiness of these aircraft, with specific intervals set to address both routine maintenance and conditions where the aircraft is exposed to prolonged wind loads or incorrect towing practices.
Scope and Application
The Civil Aviation Safety Authority (CASA) has issued Airworthiness Directive AD/BEECH 35/59 Amendment 2, which applies to all Beechcraft 35 (Bonanza) series aeroplanes equipped with rudder pedal arms with part number 50-524326, regardless of the aircraft's dash number. This directive pertains specifically to the inspection of the upper portion of each rudder pedal arm for any signs of cracks, utilising the fluorescent dye penetrant method as stipulated in Civil Aviation Order (CAO) 108.10. The inspection must focus on 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. The regulation mandates an initial inspection before the release of the next maintenance update following 31 October 1987, with subsequent inspections required at intervals not exceeding 12 months. Additionally, an inspection must be conducted before flight if the aircraft has been stationary for more than three months with the rudder pedals locked, as this condition can lead to premature cracking. The directive also cautions against towing the aircraft with the rudder pedals locked, a practice prohibited by the Maintenance Manual, which can exacerbate the risk of cracking due to wind loads.
Key Provisions
The Civil Aviation Regulations 1998, specifically Part 39 - 105, address the safety requirements for Beechcraft 35 (Bonanza) Series Aeroplanes through Airworthiness Directive AD/BEECH 35/59 Amendment 2, focusing on rudder pedal arms. This directive applies to all Beechcraft 35 models equipped with rudder pedal arms identified by the part number 50-524326, regardless of the dash number (Section 4/95). The primary requirement is to inspect the upper portion of each rudder pedal arm for any cracks using the fluorescent dye penetrant method in compliance 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 special attention to the fillet radii and holes where cracks are most likely to occur.
The regulations impose specific compliance obligations on aircraft operators and maintenance personnel. Initially, the inspection must be conducted before the issue of the next maintenance release after 31 October 1987. Subsequently, these inspections must be repeated at intervals not exceeding 12 months (Section 1). Additionally, if the aircraft has been parked for more than three months with the rudder pedals locked, an inspection must be performed before the next flight. This requirement underscores the importance of adhering to the maintenance manual's prohibition on towing the aircraft with the rudder pedals locked, as this practice can lead to premature cracking of the rudder pedal arms.
Failure to comply with the inspection requirements and adherence to the stipulated procedures can lead to serious safety concerns. The Civil Aviation Regulations do not explicitly outline specific penalties for non-compliance in this context; however, non-compliance with airworthiness directives can generally result in enforcement actions by the Civil Aviation Safety Authority (CASA). These actions may include directives to correct the non-compliant state, fines, or other regulatory measures. It is crucial for operators and maintenance personnel to ensure strict adherence to these inspection intervals and practices to avoid any potential safety hazards or regulatory penalties.