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 269/95 Cyclic Pitch Control 7/90 DM
Applicability: All model 269C helicopters S/N 0004 thru 1456.
Requirement: Unless previously accomplished, action in accordance with Schweizer Service Bulletin B-237.
Note: FAA Emergency AD 90-09-07 refers.
Compliance: Prior to 18 May 1990.
Background: The manufacturer has advised that movement of the lower longitudinal cyclic control rod spring attachment clamp, P/N AN735-9, has occurred. Movement of this clamp could restrict cyclic control which could result in loss of helicopter control.
Overview
The Civil Aviation Regulations 1998, as amended by F2006B10653, were enacted to address specific safety concerns in the aviation sector, particularly those related to the airworthiness of aircraft. This legislative instrument is part of the broader framework overseen by the Civil Aviation Safety Authority (CASA) and aims to ensure that all aircraft in Australia meet stringent safety standards. The policy objective behind this regulation is to prevent potential hazards that could compromise flight safety, particularly by addressing known design or manufacturing defects that might lead to loss of control. In the context of Schweizer (Hughes) 269 Series Helicopters, the regulation mandates compliance with specific maintenance actions to prevent movement of the lower longitudinal cyclic control rod spring attachment clamp, which could otherwise lead to loss of helicopter control. This requirement ensures that all affected helicopters adhere to the standards set out in Schweizer Service Bulletin B-237 and related FAA directives, thereby enhancing overall aviation safety.
Scope and Application
The Civil Aviation Regulations 1998, as outlined in Part 39 - 105 of the Civil Aviation Safety Authority Schedule of Airworthiness Directives, applies to all Schweizer (Hughes) 269 Series model 269C helicopters with serial numbers ranging from 0004 to 1456. This legislation mandates compliance with Schweizer Service Bulletin B-237 to rectify the issue of the lower longitudinal cyclic control rod spring attachment clamp, P/N AN735-9, which can move and thereby restrict cyclic control, potentially leading to a loss of helicopter control. This directive, referenced by FAA Emergency AD 90-09-07, must be adhered to prior to 18 May 1990. The scope of the regulation is specific to the affected helicopter models and ensures that corrective action is taken to maintain the airworthiness of these aircraft. The regulation is applicable across the Commonwealth of Australia, overseen by the Civil Aviation Safety Authority, and does not specify any exclusions or exemptions within the provided text. The requirement is clear and the directive's application is limited to the specified helicopter models, with no mention of extensions or restrictions through subordinate instruments in the excerpt provided.
Key Provisions
The Civil Aviation Regulations 1998, particularly Part 39, Section 105, detail the Airworthiness Directives (ADs) that govern the operation and maintenance of aircraft in Australia. Specifically, AD/HU 269/95 pertains to Schweizer (Hughes) 269 Series Helicopters, focusing on the cyclic pitch control issue (Section 7/90 DM). This AD is applicable to all model 269C helicopters with serial numbers ranging from 0004 to 1456. The primary requirement is that unless the corrective action specified in Schweizer Service Bulletin B-237 has already been performed, operators must comply with this directive. The directive references FAA Emergency AD 90-09-07, which provides further context and urgency regarding the issue. The compliance date is set as prior to 18 May 1990, indicating that the corrective action must be completed by this date to ensure airworthiness.
Operators of Schweizer (Hughes) 269 Series Helicopters within the specified serial number range must adhere to the directive by ensuring that the lower longitudinal cyclic control rod spring attachment clamp, P/N AN735-9, is secured to prevent any movement. This clamp, if not properly fixed, could potentially restrict the cyclic control, leading to a loss of helicopter control. The obligation on the part of the operators is to conduct a thorough inspection and implement the necessary modifications as outlined in the referenced service bulletin to mitigate the risk of control issues.
Failure to comply with AD/HU 269/95 may result in severe consequences, including potential civil and criminal penalties. The Civil Aviation Regulations stipulate that non-compliance with ADs can lead to enforcement actions by the Civil Aviation Safety Authority (CASA). Such actions may include fines and other penalties as prescribed by the regulations. The seriousness of the issue, as highlighted by the FAA's emergency directive, underscores the importance of timely and effective compliance to ensure the safety and airworthiness of the aircraft.