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 269/73 Main Gearbox Ring Gear - Inspection
and Increase of Bolt Torque
9/82
Applicability: All models 269A, 269A-1, 269B, 269C fitted with main gear box assembly P/N 269A5175-7, -9, -11, -13, -15 or -17, except those gearboxes identified with a letter “W” adjacent to the serial number on the identification plate.
Document: Hughes SIN N-181.
FAA AD 82-15-01 refers.
Compliance: Within 100 hours time in service after 30 September 1982.
Background: We are advised that there have been several reports of looseness to the main gearbox ring gear attach bolts. The possible resulting fatigue failure to bolts or ring gear carrier could cause loss of rotor drive, or jamming of the main gearbox.
Overview
The Civil Aviation Regulations 1998, specifically Part 39 - 105, which includes the schedule of airworthiness directives, was enacted to ensure the safety of civil aviation in Australia by regulating the maintenance and operation of aircraft. This legislative instrument was introduced to address safety issues and ensure compliance with airworthiness standards. The Civil Aviation Safety Authority, under the authority of the Australian Government, is responsible for enacting these regulations to safeguard the aviation industry. The policy objective of this directive, as evidenced in the specific case of the Schweizer (Hughes) 269 Series Helicopters, is to mitigate the risk of mechanical failure that could potentially lead to severe consequences such as loss of rotor drive or jamming of the main gearbox, thus ensuring the safety of air travel.
The Civil Aviation Regulations 1998 mandate specific actions to be taken in response to identified safety concerns, such as the directive concerning the main gearbox ring gear of the Schweizer (Hughes) 269 Series Helicopters. This directive was issued due to reports of looseness in the main gearbox ring gear attach bolts, which could lead to catastrophic failures. Compliance with this directive is required within 100 hours of time in service after 30 September 1982, ensuring that all affected helicopters undergo necessary inspections and bolt torque increases to maintain operational safety and reliability.
Scope and Application
The Civil Aviation Regulations 1998, specifically Part 39 - 105 under the Civil Aviation Safety Authority's (CASA) Schedule of Airworthiness Directives, applies to Schweizer (Hughes) 269 Series helicopters that are models 269A, 269A-1, 269B, and 269C, and are fitted with a main gearbox assembly with certain part numbers. These directives mandate the inspection and adjustment of the main gearbox ring gear attach bolts to prevent potential fatigue failure, which could lead to loss of rotor drive or jamming of the main gearbox. The regulations are enforced across the Commonwealth of Australia, ensuring that all applicable helicopters adhere to the specified safety measures. Compliance with these directives is required within 100 hours of time in service after 30 September 1982, as referenced by Hughes Service Information Notice N-181 and FAA AD 82-15-01. Notably, this directive does not apply to gearboxes identified with a letter "W" adjacent to the serial number on the identification plate. The application of these regulations is subject to interpretation and enforcement by CASA, which may extend or clarify their scope through subordinate instruments if necessary.
Key Provisions
The Civil Aviation Regulations 1998, specifically Part 39 - 105, outlines various Airworthiness Directives (ADs) aimed at maintaining the safety of aircraft within Australia. One such AD, AD/HU 269/73, pertains to Schweizer (Hughes) 269 Series Helicopters. This directive, effective from 9 September 1982, mandates the inspection and increase of bolt torque for the main gearbox ring gear. It applies to all models 269A, 269A-1, 269B, and 269C equipped with specific main gearbox assemblies, excluding those identified with a letter "W" adjacent to the serial number on the identification plate. The directive references Hughes SIN N-181 and FAA AD 82-15-01 for compliance standards.
Under this directive, operators and owners of the specified helicopter models are required to inspect the main gearbox ring gear attach bolts for looseness within 100 hours of time in service following 30 September 1982. This inspection is critical as the directive was issued in response to multiple reports of looseness in these bolts, which could lead to potential fatigue failure. Such failure could result in a loss of rotor drive or jamming of the main gearbox, both of which are hazardous conditions that could compromise flight safety.
Compliance with AD/HU 269/73 involves ensuring that the bolts are tightened to the specified torque levels to prevent any looseness. This requirement is not merely a procedural formality but a vital safety measure to avert serious mechanical failures. The directive's background, citing previous reports of looseness leading to safety issues, underscores the necessity of rigorous adherence to the prescribed inspection and maintenance protocols.
Failure to comply with AD/HU 269/73 can result in serious consequences. The Civil Aviation Safety Authority (CASA) has the authority to enforce compliance and may impose penalties on non-compliant operators. These penalties can include fines and other administrative actions. Moreover, operating a non-compliant aircraft could lead to grounding, which poses significant risks to flight safety and operational continuity. Therefore, it is imperative for operators to meticulously adhere to the directive's requirements to avoid both regulatory penalties and potential safety incidents.