Commonwealth legislation

AD/BELL 206/110 - Tail Rotor Pitch Links

RepealedCTH

This Act has been repealed and is no longer in force. It is retained for historical reference.

Jurisdiction

Commonwealth

Collection

legislative instrument

Plain English Summary

2/10 complexity

What this does

This airworthiness directive orders a one-time safety inspection of tail rotor pitch links—critical components that control the helicopter's tail rotor—on specific Bell helicopter models. The inspection checks for stress corrosion cracking in the spherical bearing housing.

Who it affects

Owners and operators of Bell 206A/B, 206BIII, 206L, L1, and L3 helicopters, but only if fitted with specific part numbers: P/N 206-010-793-101 or P/N 206-010-792-105.

What must be done

Conduct an inspection following the procedures in Bell Helicopter Alert Service Bulletin 206-87-39 or 206L-87-48 (depending on the helicopter model). This must be done within a specific flight hour limit or by a set calendar deadline, whichever comes first—unless the inspection was already completed.

Why this matters

Four pitch links were found cracked due to stress corrosion. A failed pitch link could cause loss of tail rotor control, potentially leading to catastrophic loss of the aircraft and lives.

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Current sections

Direct links to the current provisions in AD/BELL 206/110 - Tail Rotor Pitch Links.

AD/BELL 206/110 - Tail Rotor Pitch Links

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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.

Source text

Sourced from the Federal Register of Legislation (legislation.gov.au), CC BY 4.0.