Federal Register #2026-16-10

FAA Airworthiness Directives for Airbus EC130T2 Helicopters and Rolls-Royce Trent 1000 Engines

This opportunity involves new airworthiness directives from the Federal Aviation Administration (FAA) targeting two major aircraft OEMs: - Government Buyer: - Federal Aviation Administration (FAA), Transportation Department - OEMs and Vendors: - Airbus Helicopters (Model EC130T2) - Rolls-Royce Deutschland Ltd & Co KG (Trent 1000 series engines) - Products/Services Requested: - For Airbus Helicopters EC130T2: - Installation of a manufacturer-developed modification: new rear drive shaft, sliding flange, and equipped splined sleeve - Repetitive vibration level inspections of the tail rotor drive shaft - Prohibition on installation of certain parts and balance corrections unless requirements are met - Estimated 108 helicopters affected - For Rolls-Royce Trent 1000 engines: - Repetitive borescope inspections of intermediate pressure compressor variable inlet guide vanes - Removal and replacement of vanes if cracks are found - Unique or Notable Requirements: - Compliance with EASA procedures for Airbus Helicopters - Restrictions on maintenance actions to prevent unsafe conditions (tail rotor drive shaft failure, compressor vane cracking) - No specific part numbers provided; applies to all EC130T2 helicopters and Trent 1000 engines as identified - Estimated costs and scope provided for 108 helicopters - Ongoing, repetitive inspection and modification requirements

Description

The FAA is superseding Airworthiness Directive (AD) 2023-25-14, which applied to certain Airbus Helicopters Model EC130T2 helicopters. This AD requires installing a manufacturer-developed modification of the rear drive shaft, sliding flange, and equipped splined sleeve, and repetitively inspecting the vibration level of the tail rotor drive shaft. It also prohibits the installation of certain parts and the performance of a balance correction unless specific requirements are met. The AD addresses an unsafe condition that could result in failure of the tail rotor drive shaft and loss of yaw control of the helicopter.

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