AD 2023-05-17
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| engine | General Electric | Company | Airworthiness Directives; General Electric Company Turbofan Engines |
Unsafe Condition
Cracking and rockback of the high-pressure turbine (HPT) stage 2 nozzles due to thermal distress in the fillet radius of the leading edge, resulting in rotor-stator contact with the HPT stage 2 blade platform, blade liberation, severe rotor imbalance, and liberation of the exhaust centerbody.
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Required Actions
Initial and repetitive borescope inspections (BSIs) of the forward platforms of the HPT stage 2 blades or the leading edges of the HPT stage 2 nozzles. Depending on inspection results, removal and replacement of the HPT stage 2 nozzles with parts eligible for installation. Mandatory terminating action requires replacing the HPT stage 2 nozzles.
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Compliance Time
Before accumulating 22,000 flight hours (FH) since new or since last overhaul, or within 250 flight cycles (FCs) after the effective date of this AD, whichever occurs later.
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Affected Aircraft
General Electric Company (GE) GE90-76B, GE90-85B, GE90-90B, and GE90-94B model turbofan engines.
AI-generated summary from the source AD text. Verify against the official source before acting.
Source: Official FAA Source ↗
Retrieved: Apr 6, 2026
Rights: U.S. Government Public Domain
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