AD/HU 269/83 - Tail Rotor Fork Bolt

Overview

The Civil Aviation Regulations 1998, amended through legislative instruments such as F2006B10642, address specific safety concerns in civil aviation. This particular amendment, concerning the Schweizer (Hughes) 269 Series Helicopters, was introduced to mitigate the risk associated with the potential incomplete processing of tail rotor fork bolts, which could lead to cracking and failure. The problem arose from the possibility that bolts manufactured between 18 April 1986 and 28 August 1986 did not undergo adequate processing. The policy objective of this amendment is to ensure the safety of air operations by mandating actions in line with Schweizer Service Information Notice No. N-208. The requirement is that all affected helicopters and spare parts must comply with these specifications within 10 hours of service time after 16 March 1987 or before installation on an aircraft after that date. This was enacted by the Australian Government to safeguard against potential aircraft failures and enhance overall aviation safety.

Scope and Application

The Civil Aviation Regulations 1998, specifically Part 39 - 105, applies to all Schweizer (Hughes) 269 Series Helicopters fitted with a tail rotor assembly bearing part number 269A6034, as well as any such assemblies and tail rotor fork bolts part number 369A1602 held as spares. This regulation is concerned with the safety of these aircraft and spare parts, mandating compliance with Schweizer Service Information Notice No. N-208. The action required under this directive must be completed within 10 hours of time in service after 16 March 1987, and before any installation on an aircraft following that date. The directive aims to address potential manufacturing defects in tail rotor fork bolts produced between 18 April 1986 and 28 August 1986, which may not have undergone proper processing, thereby risking cracking and subsequent failure. This regulation applies across the Commonwealth of Australia and is enforced by the Civil Aviation Safety Authority.

Key Provisions

The Civil Aviation Regulations 1998, particularly Part 39, Section 105, outlines specific airworthiness directives for Schweizer (Hughes) 269 Series Helicopters, as referenced in AD/HU 269/83. This directive concerns the tail rotor fork bolt and applies to all 269 Series Helicopters fitted with the P/N 269A6034 tail rotor assembly, as well as all P/N 269A6034 tail rotor assemblies and P/N 369A1602 tail rotor fork bolts held as spares. The directive mandates actions in accordance with Schweizer Service Information Notice No. N-208, which was issued to address the potential manufacturing defect in tail rotor fork bolts produced between 18 April 1986 and 28 August 1986. Specifically, these bolts may not have been adequately processed during manufacturing, leading to a risk of cracking and subsequent bolt failure. The directive imposes clear obligations on the operators and maintainers of the affected helicopters. They must ensure compliance with the requirements specified within 10 hours of the helicopter being in service after 16 March 1987 or before any installation of the tail rotor assembly on an aircraft post this date. This includes the replacement or proper processing of any tail rotor fork bolts that fall within the specified date range. The aim is to prevent any potential in-flight failures that could compromise safety. Non-compliance with these directives can result in serious consequences. If an operator fails to adhere to the mandated actions, they could be subject to enforcement actions under the Civil Aviation Act 1988. This may include fines and other penalties. Additionally, operating a helicopter that does not comply with the airworthiness directives can result in severe safety risks, potentially leading to accidents or incidents. The safety and operational integrity of the aircraft are paramount, and any deviation from the prescribed actions can have significant legal and safety repercussions.