COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
SCHEDULE OF AIRWORTHINESS DIRECTIVES
Bell Helicopter Textron Canada (BHTC) 206 and Agusta Bell 206 Series Helicopters
AD/BELL 206/110 Tail Rotor Pitch Links 13/87 DM
Applicability: All model Bell 206A/B, 206BIII, 206L, L1 and L3 fitted with P/N 206-010-793-101 or 206-010-792-105 tail rotor pitch links.
Requirement: Inspect in accordance with Bell Helicopter Alert Service Bulletin 206-87-39 or 206L- 87-48, as applicable.
Compliance: Unless already accomplished within 25 hours time in service from 15 October 1987 or before 30 November 1987 whichever occurs first.
Background: Four tail rotor pitch links P/N 206-010-793-101 have been reported cracked due to stress corrosion in the area that houses the spherical bearing, requiring a one time inspection of the pitch link.
Overview
The Civil Aviation Regulations 1998, under PART 39 - 105 of the Civil Aviation Safety Authority Schedule of Airworthiness Directives, address safety concerns specific to the Bell Helicopter Textron Canada (BHTC) 206 and Agusta Bell 206 Series helicopters. This legislation, enacted by the Commonwealth of Australia, was introduced to ensure the safety of these aircraft models by addressing a particular issue with the tail rotor pitch links. The problem identified was the potential for stress corrosion in the tail rotor pitch links P/N 206-010-793-101 and P/N 206-010-792-105, which could lead to cracking and compromise the safety of the aircraft. The policy objective is to mandate a thorough inspection of these components to prevent any potential safety hazards.
The requirement, as outlined in AD/BELL 206/110, mandates an inspection of the tail rotor pitch links in accordance with Bell Helicopter Alert Service Bulletin 206-87-39 or 206L-87-48, as applicable, for all model Bell 206A/B, 206BIII, 206L, L1 and L3 helicopters fitted with the specified pitch links. Compliance with this directive is necessary unless the inspection has already been completed within 25 hours of time in service from 15 October 1987 or before 30 November 1987, whichever occurs first. This directive aims to ensure that the identified safety issue is promptly and effectively addressed to maintain the airworthiness of the affected aircraft.
Scope and Application
The Civil Aviation Regulations 1998, as amended, establish the framework for ensuring the safety and efficiency of civil aviation within Australia, with Part 39, specifically, outlining various directives to maintain airworthiness. Under this regulatory structure, the Airworthiness Directive AD/BELL 206/110 pertains to all model Bell 206A/B, 206BIII, 206L, L1 and L3 helicopters equipped with tail rotor pitch links P/N 206-010-793-101 or 206-010-792-105. This directive mandates an inspection of these components to address instances of stress corrosion that have been identified in the area housing the spherical bearing of the pitch links. Compliance with this directive requires that the inspection be completed within 25 hours of time in service from 15 October 1987 or before 30 November 1987, whichever is the earlier, unless the inspection has already been performed. This requirement applies nationally across all operators of the specified helicopter models within Australia and is enforced under the oversight of the Civil Aviation Safety Authority.
Key Provisions
The Civil Aviation Regulations 1998, specifically in Part 39 - 105, outlines the Civil Aviation Safety Authority's (CASA) schedule of airworthiness directives, including the AD/BELL 206/110 directive for Bell Helicopter Textron Canada (BHTC) 206 and Agusta Bell 206 Series Helicopters. Section 13/87 DM requires a specific inspection of the tail rotor pitch links for certain Bell 206 models. These models include the Bell 206A/B, 206BIII, 206L, L1 and L3 helicopters that are fitted with tail rotor pitch links with part numbers 206-010-793-101 or 206-010-792-105. The inspection must adhere to the guidelines provided in Bell Helicopter Alert Service Bulletins 206-87-39 or 206L-87-48, as applicable. Compliance with this directive is mandatory unless the inspection has already been completed within 25 hours of time in service from 15 October 1987 or before 30 November 1987, whichever comes first.
The obligations imposed by the AD/BELL 206/110 directive necessitate that operators of the specified Bell 206 models conduct the required inspection of the tail rotor pitch links. This involves a thorough examination to detect any signs of stress corrosion or cracking in the area housing the spherical bearing, as four such pitch links have already been reported to have failed due to this issue. The directive is clear in its requirement for adherence to the specified service bulletins, which provide detailed instructions on how to perform the inspection effectively and ensure the safety of the aircraft.
Failure to comply with the AD/BELL 206/110 directive can result in serious consequences. While the Civil Aviation Regulations 1998 do not explicitly state the penalties for non-compliance with this specific airworthiness directive, general regulatory frameworks suggest that non-compliance could lead to enforcement actions by CASA. These actions may include fines, suspension or revocation of airworthiness certificates, and other administrative penalties. Additionally, any resulting accidents or incidents caused by non-compliance could lead to criminal charges under aviation safety laws, potentially resulting in substantial fines and imprisonment for responsible individuals or entities.