Commonwealth legislation

AD/BELL 206/128 - Main Rotor Blade and Trim Tab

In ForceCTH

Jurisdiction

Commonwealth

Collection

legislative instrument

Plain English Summary

3/10 complexity

Requires operators of specified Bell 206 helicopters fitted with certain main rotor blades to inspect the inboard trim tab and adjacent blade surfaces for cracks using a 10× magnifier. Blades with trim-tab cracks may be reworked per Bell Alert Service Bulletins; blades with cracks elsewhere must be removed from service. Work must be completed within 50 hours time in service. Operators pay for inspections and repairs; maintenance must follow the service bulletins to address reported trailing‑edge cracking.

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Current sections

Direct links to the current provisions in AD/BELL 206/128 - Main Rotor Blade and Trim Tab.

AD/BELL 206/128 - Main Rotor Blade and Trim Tab

COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY

SCHEDULE OF AIRWORTHINESS DIRECTIVES

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Bell Helicopter Textron Canada (BHTC) 206 and Agusta Bell 206 Series Helicopters

AD/BELL 206/128 Main Rotor Blade and Trim Tab 2/95

Applicability: All Bell 206A, 206B, 206L, 206L-1, 206L-3 and 206L-4 helicopters equipped with main rotor blade P/N 206-015-001-107 or P/N 206-010-200-133 and having a serial number beginning with prefix “A”. Those blades P/N 206-010-200-133 or P/N 206- 015-001-107 with “A” prefixed serial numbers listed in Bell Alert Service Bulletins 206-93-77 or 206L-93-92 are not affected by this AD.

Requirement: 1. Visually inspect, for cracking, the inboard trim tab and the upper and lower surfaces of the main rotor blade in the area of the inboard trim tab.

Inspect using a 10X magnifying glass and polish out any grinding or sanding marks in accordance with Part I of the applicable Bell Alert Service Bulletins.

Blades with cracks in the inboard trim tab may be returned to service after reworking in accordance with Part II of the applicable Bell Alert Service Bulletins. Blades with cracks at other locations shall be removed from service.

Note: FAA AD 94-15-07 refers.

Compliance: Inspect and rework as required within 50 hours time in service from 2 February 1995.

Background: A number of cracks have been reported in the main rotor blade trailing edge near the inboard trim tab. Timely inspection will prevent failure of the rotor blade and loss of the helicopter.

Source text

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

1 AD/BELL 206/128 - Main Rotor Blade and Trim Tab