Federal Register #2026-22776

FAA safety directive for Airbus helicopter tail rotor blade assemblies

The FAA issued a helicopter safety directive requiring inspections and corrective actions for certain Airbus tail rotor blade assemblies. - Government agency: Federal Aviation Administration (FAA), U.S. Department of Transportation. - OEM: Airbus Helicopters Deutschland GmbH (AHD), manufacturer of the affected helicopters and blade assemblies. The European Union Aviation Safety Agency (EASA) issued the referenced technical directive. - Affected aircraft: Airbus AHD Model EC135P1, EC135P2, EC135P2+, EC135P3, EC135T1, EC135T2, EC135T2+, EC135T3, and EC635T2+ helicopters. - Affected components: Tail rotor blade assemblies, part numbers L642A2002111 and L642A2002112. The directive estimates 359 U.S.-registered helicopters are affected, with up to 10 assemblies per helicopter potentially inspected. - Required safety actions: Conduct repetitive inspections for cracks, remove cracked assemblies, and replace an affected part to end the repetitive inspection requirement. Inspection Method A is discontinued, and installation of affected assemblies is restricted unless specified requirements are met. - Safety concern and estimated costs: A blade assembly could separate and reduce helicopter control. The FAA estimates inspections may cost up to $305 per helicopter and replacement up to $51,550 per assembly. - Opportunity status: This is a regulatory safety action, not a procurement request; no contract products, services, or period of performance are specified.

Description

The Federal Aviation Administration issued a final rule superseding Airworthiness Directive 2024-04-10 for specified Airbus Helicopters Deutschland GmbH (AHD) EC135 and EC635T2+ helicopter models. It retains prior requirements and requires repetitive inspections of specified tail rotor blade assemblies for cracks, removal of cracked assemblies, and replacement of an affected part as terminating action for repetitive inspections. The rule discontinues inspection Method A and prohibits installation of an affected assembly unless specified requirements are met. It is effective December 14, 2026.

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