COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
SCHEDULE OF AIRWORTHINESS DIRECTIVES
Schweizer (Hughes) 269 Series Helicopters
AD/HU 269/66 Tail Rotor Swashplate Bearing Locknut - Increase in Torque
3/80
Applicability: All model 269A, 269A-1 and 269B. Model 269C with S/Nos. 0004 through 0789. Document: Hughes SIN N-163.
Compliance: Within 100 hours time in service after 31 March 1980.
Background: To prevent loosening of the tail rotor swashplate bearing locknut and possible loss of tail rotor control, the tightening torque of the locknut is increased.
Overview
The Civil Aviation Regulations 1998, which form part of the legislative framework overseen by the Civil Aviation Safety Authority (CASA) in Australia, include specific directives to ensure the safety and airworthiness of aircraft. One such directive is AD/HU 269/66, enacted to address the risk of tail rotor swashplate bearing locknut loosening in Schweizer (Hughes) 269 Series Helicopters. This directive was introduced to mitigate the potential loss of tail rotor control by increasing the tightening torque of the locknut, thus enhancing the safety of these aircraft models. The policy objective is to ensure that all applicable models, including 269A, 269A-1, 269B, and specified serial numbers of the 269C model, comply with this directive within 100 hours of time in service after 31 March 1980.
Scope and Application
The Civil Aviation Safety Authority Schedule of Airworthiness Directives under the Civil Aviation Regulations 1998 applies to all Schweizer (Hughes) 269 Series helicopters, specifically models 269A, 269A-1, and 269B, as well as model 269C with serial numbers ranging from 0004 through 0789. This legislation mandates compliance within 100 hours of time in service after 31 March 1980, aiming to prevent the loosening of the tail rotor swashplate bearing locknut, which could potentially result in a loss of tail rotor control. The directive is a Commonwealth regulation and is applicable nationally, ensuring that all operators of the specified helicopter models within Australia adhere to these safety standards. The regulation extends through subordinate instruments which may provide further detail or clarification on implementation and compliance procedures.
Key Provisions
The Civil Aviation Regulations 1998, particularly in Part 39, establish specific Airworthiness Directives (AD) aimed at ensuring the safety and reliability of aircraft. One such directive, AD/HU 269/66, pertains to Schweizer (Hughes) 269 Series Helicopters (sections 39-105 and AD/HU 269/66). This directive mandates that certain models of these helicopters must comply with new requirements to enhance the safety of the tail rotor system. Specifically, it requires an increase in the torque of the tail rotor swashplate bearing locknut to prevent its loosening, which could potentially lead to a loss of tail rotor control.
The directive applies to all Schweizer (Hughes) 269A, 269A-1, and 269B models, as well as model 269C helicopters with serial numbers ranging from 0004 through 0789. Compliance with this directive must be achieved within 100 hours of time in service after 31 March 1980. This requirement ensures that the bearing locknut is tightened to the specified torque, thereby mitigating the risk of it loosening over time and compromising the helicopter's control systems. Operators and owners of these helicopters must adhere to the stipulated timeframe and follow the specified procedures to achieve compliance.
The obligations imposed by this Airworthiness Directive are clear and specific. Operators and owners must ensure that the tightening torque of the tail rotor swashplate bearing locknut is increased according to the directive. This involves using appropriate tools and techniques to achieve the correct torque setting, as specified in Hughes SIN N-163. Compliance must be documented and verified, typically through maintenance records that attest to the adjustments being made within the required timeframe. Failure to comply with these obligations could result in the aircraft being deemed non-airworthy, which could prevent it from being operated until the necessary adjustments are made.
Failure to comply with the provisions of AD/HU 269/66 can lead to serious consequences. Non-compliance may result in enforcement actions by the Civil Aviation Safety Authority (CASA). The penalties for breaching these regulations can include fines, enforcement notices, and potential legal action. In severe cases, CASA may revoke the aircraft’s certificate of airworthiness, which would prevent it from flying until the necessary compliance measures are taken. Ensuring adherence to these directives is critical for maintaining the safety standards required under Australian aviation law.