Federal Register #2026-16502

FAA Proposed Airworthiness Directives for Rolls-Royce Trent 1000 Engines and Airbus Nose Landing Gear

This opportunity involves proposed airworthiness directives from the Federal Aviation Administration (FAA), part of the Department of Transportation, targeting safety and maintenance requirements for specific aircraft engines and landing gear components. - Government Buyer: - Department of Transportation, Federal Aviation Administration, Operational Safety Branch - OEMs Mentioned: - Rolls-Royce Deutschland Ltd & Co KG (Trent 1000 series engines) - Airbus SAS (A318, A319, A320, A321 series airplanes) - Products/Services Requested: - Repetitive borescope inspections of the high-pressure compressor (HPC) rear drum cavity and cavities between each HPC rotor disc for Rolls-Royce Trent 1000 engines - Quantity: 6 inspections (as referenced in the attachment) - Modification of the bolting arrangement at the HPC rotor shaft to high-pressure turbine rotor disc interface (serves as a terminating action for the repetitive inspections) - Quantity: 6 modifications - Special detailed inspection and replacement (if needed) of nose landing gear sliding tubes on Airbus A318, A319, A320, and A321 aircraft due to risk of overheat damage and cracks - Unique/Notable Requirements: - Compliance with European Union Aviation Safety Agency (EASA) AD 2025-0233 for Rolls-Royce engines - Removal of engine from service if inspection results warrant - Mandated modification of bolting arrangement as a permanent corrective action - Focus on preventing unsafe conditions such as engine failure or landing gear malfunction - No specific part numbers are provided; requirements are for maintenance actions and modifications rather than procurement of discrete products.

Description

The FAA proposes to supersede AD 2025-26-03 for certain Rolls-Royce Deutschland Ltd & Co KG Model Trent 1000 engines. The proposed AD requires repetitive borescope inspections of the high-pressure compressor rear drum cavity and cavities between each HPC rotor disc, with removal of the engine from service depending on inspection results. It also allows an alternative method of compliance if certain actions are performed, and requires modification of the bolting arrangement as a terminating action for the inspections. The goal is to address unsafe conditions related to the high-pressure compressor to prevent engine failure or other safety issues.

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