AD/BELL 206/65 Amdt 2 - Main Rotor Pitch Link Clevises - Inspection

Overview

The Civil Aviation Regulations 1998, enacted by the Commonwealth of Australia, aim to ensure the safety of civil aviation through stringent regulatory oversight. A significant component of these regulations is Part 39, which includes the Airworthiness Directives (AD) issued by the Civil Aviation Safety Authority (CASA). One such directive, AD/BELL 206/65 Amendment 2, pertains specifically to the inspection of main rotor pitch link clevises in Bell Helicopter Textron Canada (BHTC) 206 and Agusta Bell 206 series helicopters. This directive was introduced to address the potential risks associated with the structural integrity of the main rotor pitch link clevises, ensuring that these components are thoroughly inspected to prevent in-flight failures. The policy objective behind this directive is to enhance aviation safety by mandating regular inspections and timely maintenance of critical helicopter components, thereby mitigating the risk of catastrophic failures that could endanger flight safety. The directive applies to all models 206A, 206B, and AB206 series helicopters, requiring inspections with approved dye penetrant methods on the threaded portions of specified clevises. Furthermore, it mandates checking the force required to move a specific bearing before reinstalling pitch links, with a directive to replace the bearing if the force exceeds ten pounds. Compliance with these inspection and maintenance requirements must be achieved within 100 hours of time in service after 5 May 1975, and prior to each subsequent installation on an aircraft. This regulatory approach underscores the importance of proactive maintenance in upholding the high safety standards expected in civil aviation.

Scope and Application

The Civil Aviation Regulations 1998, specifically under Part 39 - 105, pertains to the Civil Aviation Safety Authority's (CASA) schedule of airworthiness directives, which in this instance concerns Bell Helicopter Textron Canada (BHTC) 206 and Agusta Bell 206 Series Helicopters. The scope of this particular directive, AD/BELL 206/65Amdt 2, applies to all models 206A, 206B, and AB206 series helicopters. The regulation mandates that inspections of the main rotor pitch link clevises must be conducted using an approved dye penetrant method to ensure the entire threaded portion of the upper and lower clevises in specific pitch link assemblies is examined. The directive allows for the use of a fluorescent dye penetrant, with a preference noted, but also permits the use of a colour contrast penetrant if fluorescent is not available. The requirement also includes a pre-reinstallation check of the force needed to move the bearing, with a specified threshold for replacement if the force exceeds ten pounds. Compliance with this directive is mandatory within 100 hours of time in service after the directive's effective date, 5 May 1975, and must be repeated before each subsequent installation on an aircraft. The regulatory framework is national in reach, applying across all jurisdictions within Australia under the Commonwealth's authority.

Key Provisions

The Civil Aviation Regulations 1998, under Part 39 - 105, include specific safety directives for certain aircraft models, such as the Bell Helicopter Textron Canada (BHTC) 206 and Agusta Bell 206 series. One of the critical directives is AD/BELL 206/65 Amendment 2, which focuses on the inspection of main rotor pitch link clevises (section 1). The directive applies to all models 206A, 206B, and AB206 series. The main requirement of this directive is to inspect the entire threaded portion of the upper and lower clevises in the pitch link assemblies P/Nos. 206-010-330 and 206-010-342. This inspection must be carried out using an approved dye penetrant method, with a preference for fluorescent dye penetrant, although colour contrast penetrant is acceptable if fluorescent dye is not available (section 1(1)). The second requirement involves checking the force needed to move bearing P/N 206-010-469-1 in the swashplate outer ring horns before reinstalling the pitch links (section 1(2)). Specifically, the bearing force should be tested by installing a NAS 1305-27D bolt through the bearing, securing it with a cotter pin, and then measuring the force required to move the bearing. If the force exceeds ten pounds, the bearing must be replaced (section 1(2)). Compliance with this directive must be achieved within 100 hours of time in service after 5 May 1975, and it must be repeated before each installation on an aircraft (section 1). Operators and entities governed by this directive must ensure that the inspections and checks are performed in accordance with the specified methods and within the stipulated timeframes. Failure to comply with these requirements can result in serious safety risks, as the directive aims to prevent potential failures in the main rotor pitch link assemblies, which could compromise the aircraft's safety. The consequences of non-compliance can include severe penalties, both civil and criminal. Under the Civil Aviation Act 1988, failure to comply with Airworthiness Directives can result in hefty fines and potential prosecution, with maximum penalties for serious offences reaching up to $500,000 for corporations and $100,000 for individuals, alongside imprisonment terms of up to five years (section 6). These stringent measures underscore the importance of adhering to the safety directives to ensure the safety and integrity of civil aviation operations.