AD/S-76/43 - Tail Rotor Servo Actuator Linkage

Overview

The Civil Aviation Regulations 1998, amended by the legislative instrument F2006B06724, was introduced to address safety concerns associated with the Sikorsky S-76 series helicopters. Specifically, this legislation targets the tail rotor servo actuator linkage, responding to reports of potential bolt misalignment in the servo actuator input crank assembly, which could lead to fretting of the bolt. Enacted by the Australian Parliament, the policy objective of this regulation is to ensure the safety and reliability of civil aviation operations by mandating inspections and modifications to the affected helicopters. The regulation requires operators of model S-76A helicopters to inspect the specified components within 25 hours of service after 31 October 1986 and at intervals not exceeding 25 hours of service until the necessary modifications are completed. Furthermore, the modifications must be carried out prior to 31 November 1986, following the guidelines provided in Sikorsky S76 Alert Service Bulletin No. 76-67-24 and HR Textron Service Bulletin No. SB272.

Scope and Application

The Civil Aviation Regulations 1998, specifically under PART 39 - 105, applies to all model S-76A Helicopters, imposing requirements for the inspection and modification of the tail rotor servo actuator linkage. This directive, identified as AD/S-76/43, is issued by the Civil Aviation Safety Authority and mandates adherence to the guidelines outlined in Sikorsky S76 Alert Service Bulletin No. 76-67-24 and HR Textron Service Bulletin No. SB272. The inspection must be conducted within 25 hours of time in service after 31 October 1986 and then at intervals not exceeding 25 hours of time in service until the modification is implemented. Furthermore, the modification must be completed prior to 31 November 1986. This legislation is pertinent to all operators of the specified helicopter model, ensuring compliance with safety standards to prevent potential issues such as bolt misalignment on the servo actuator input crank assembly, which could lead to fretting of the bolt. The scope of this regulation is geographically limited to the Commonwealth of Australia, ensuring that all operators within its jurisdiction adhere to these safety directives. There are no exclusions or exemptions specified in this particular directive, meaning all model S-76A helicopters must comply with the outlined inspection and modification requirements. The application of this legislation can potentially be extended or further detailed through subordinate instruments, which may provide additional clarification or enforce specific conditions related to the compliance process.

Key Provisions

The main sections of the Civil Aviation Regulations 1998, Part 39 - 105, particularly AD/S-76/43, focus on the Sikorsky S-76 Series Helicopters, specifically addressing the tail rotor servo actuator linkage. Section 39-105 mandates that all model S-76A Helicopters must undergo inspection and modification as outlined in Sikorsky S76 Alert Service Bulletin No. 76-67-24 and HR Textron Service Bulletin No. SB272. These bulletins provide the necessary guidelines for identifying and rectifying potential issues with the tail rotor servo actuator linkage, which is crucial for the safe operation of the helicopter. Under this legislation, helicopter operators and maintenance personnel are obligated to adhere strictly to the inspection and modification requirements. The inspection must be conducted within 25 hours of time in service after 31 October 1986 and subsequently at intervals not exceeding 25 hours time in service until the modification is carried out. This stringent timeline ensures that any potential issues are identified and addressed promptly, reducing the risk of operational failures. The modification itself must be completed prior to 31 November 1986, ensuring that all affected helicopters meet the required safety standards. Failure to comply with the provisions set out in AD/S-76/43 could result in severe consequences. The legislation stipulates that non-compliance could lead to operational risks, potentially resulting in civil and criminal liabilities. Although the specific penalties are not detailed within the text, non-compliance with aviation safety directives typically results in significant penalties, including fines and possible suspension or revocation of the helicopter's airworthiness certificate. These measures are in place to enforce the stringent safety standards mandated by the Civil Aviation Regulations.