COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
SCHEDULE OF AIRWORTHINESS DIRECTIVES
Beechcraft 65 and 70 (Queen Air) Series Aeroplanes
AD/BEECH 65/62
Amdt 3
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, are integral to maintaining airworthiness standards for aircraft in Australia. The 1998 regulations, which include amendments, aim to ensure the safety of civil aviation operations by setting out the requirements for airworthiness, licensing, and other operational aspects of aircraft. The Rudder Pedal Arms Airworthiness Directive (AD/BEECH 65/62 Amendment 3) is one such measure designed to address the specific issue of cracked rudder pedal arms on Beechcraft 65 and 70 series aeroplanes. This directive was introduced to mitigate the risk of structural failure caused by cracked rudder pedal arms, which can compromise the integrity of the aircraft's control systems. The policy objective is to enhance flight safety by mandating regular inspections of the rudder pedal arms, particularly focusing on areas prone to cracking, and providing guidelines for compliance and corrective actions.
Scope and Application
The Civil Aviation Regulations 1998, specifically under PART 39 - 105, applies to all Beechcraft 65 and 70 (Queen Air) Series Aeroplanes fitted with rudder pedal arms P/N 50-524326, irrespective of their dash numbers. This regulatory directive is enacted under the authority of the Civil Aviation Safety Authority (CASA) and is applicable throughout the Commonwealth of Australia, ensuring a consistent standard of airworthiness across the nation. The legislation mandates that inspections of the upper portions of the rudder pedal arms must be conducted for any signs of cracks, utilising the fluorescent dye penetrant method as outlined in CAO 108.10. This involves scrutinising the upper part of the "I" section shank, the hollow crossbar, and the brake pedal attachment lugs, with a specific focus on the fillet radii and holes. The requirement for compliance includes an initial inspection before the issuance of the next maintenance release after 31 October 1987, followed by re-inspections at intervals not exceeding 12 months. Additionally, inspections are necessary before flight if the aircraft has been stationary for more than three months with the rudder pedals locked, as per the maintenance manual. The regulation also cautions against towing with locked rudder pedals due to the risk of premature cracking caused by wind loads.
Key Provisions
The Civil Aviation Regulations 1998, under Part 39 - 105, focus on the maintenance and safety of aircraft, with specific attention to the Beechcraft 65 and 70 (Queen Air) series aeroplanes. Section AD/BEECH 65/62 Amendment 3 pertains to the rudder pedal arms of these aircraft. The regulation mandates that the upper portion of each rudder pedal arm, specifically those with part number 50-524326 across all models, must be inspected for cracks using the fluorescent dye penetrant method as stipulated in 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.
The obligations under this regulation are clear and must be adhered to strictly. Operators of these aircraft are required to conduct an initial inspection before the next maintenance release after 31 October 1987. Subsequent inspections must occur at intervals not exceeding 12 months. Furthermore, if an aircraft has been parked for more than three months with the rudder pedals locked, an inspection is mandated before flight. It is important to note that the maintenance manual prohibits towing with the rudder pedals locked, as this practice can lead to premature cracking and compromise the safety of the aircraft.
Failure to comply with these provisions can lead to serious consequences. While the regulations do not explicitly state penalties, non-compliance with Civil Aviation Regulations can result in enforcement actions by the Civil Aviation Safety Authority (CASA). Potential outcomes may include fines, enforcement notices, or suspension of the aircraft’s certificate of airworthiness. These measures underscore the importance of adhering to the inspection requirements to ensure the continued airworthiness and safety of the aircraft in question.