Federal Register #2026-13-12

FAA Airworthiness Directives for Bell 430 Helicopter and Airbus BD5001A10/11 Airplane Safety Components

The Federal Aviation Administration (FAA), under the Department of Transportation, has issued new airworthiness directives (ADs) targeting specific helicopter and airplane models to address critical safety concerns. - Government Buyer: - Department of Transportation, Federal Aviation Administration, Aircraft Certification Service - OEMs Highlighted: - Bell Textron Canada Limited (Model 430 helicopters) - Airbus Canada Limited Partnership (Model BD5001A10 and BD5001A11 airplanes) - Products/Components Affected: - For Bell 430 helicopters (serial numbers 49001–49129): - Main rotor pitch link clevis (part number 430010411109), universal bearings, universal to pitch link bolts, pitch link tube assemblies, and rod end assemblies - Inspections, possible replacement, and re-identification of these components as per Transport Canada AD CF202440 - For Airbus BD5001A10/11 airplanes: - High pressure valve (HPV) butterfly clips, with dispatch prohibited if clips are missing or broken - Notable Requirements: - Mandatory compliance with Transport Canada AD CF202440 for Bell 430 helicopters, including detailed and repetitive inspections, conditional magnetic particle inspections, and component replacements based on inspection results - For Airbus airplanes, dispatch is restricted under certain conditions related to HPV butterfly clips - No reporting to the manufacturer required for Bell 430 directive - FAA provides exceptions to certain requirements in the Transport Canada AD - Quantities: - 29 units each for main rotor pitch link clevis, universal bearings, universal to pitch link bolts, pitch link tube assemblies, and rod end assemblies for Bell 430 helicopters - Scope: - Applies to Bell 430 helicopters (serial numbers 49001–49129) and Airbus BD5001A10/11 airplanes

Description

The FAA is superseding Airworthiness Directive (AD) 2025-09-03 for certain Bell Textron Canada Limited Model 430 helicopters. The previous AD reduced life limits on main rotor clevises, universal bearings, and bolts, and required re-identification of pitch link assemblies. This new AD modifies those actions based on comments received and addresses an unsafe condition involving fatigue damage and potential failure of the main rotor pitch link components, which could lead to loss of helicopter control. Compliance with Transport Canada AD CF202440 is required with specified exceptions.

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