AD 2024-11-03
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | International | Aero | Airworthiness Directives; International Aero Engines, AG Engines |
Unsafe Condition
Failure of the high-pressure compressor (HPC) 7th-stage integrally bladed rotor (IBR-7) due to a nickel powdered metal anomaly, similar in nature to an anomaly previously observed on March 18, 2020, when an Airbus Model A321-231 airplane, powered by IAE AG Model V2533-A5 engines, experienced an uncontained HPT 1st-stage hub failure that resulted in high-energy debris penetrating the engine cowling.
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Required Actions
Performing an angled ultrasonic inspection (AUSI) of certain high-pressure turbine (HPT) 1st-stage hubs and HPT 2nd-stage hubs for cracks and replacing if necessary, and accelerated replacement of certain HPT 1st-stage hubs and HPT 2nd-stage hubs.
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Compliance Time
Within 50 flight cycles (FC) from the effective date of this AD.
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Affected Aircraft
IAE AG Model V2500 engines, manufactured from the same production campaign (a batch of nickel powdered metal) as the HPT 1st-stage hub that failed on March 18, 2020, defined by serial number within the service information documents that are incorporated by reference in this AD.
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Source: Official FAA Source ↗
Retrieved: Apr 6, 2026
Rights: U.S. Government Public Domain
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