AD 2025-21-03
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| engine | CFM | International | Airworthiness Directives; CFM International, S.A. Engines |
Unsafe Condition
cracks in the high-pressure turbine (HPT) rotor stage 1 blades
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
initial and repetitive borescope inspections (BSIs) of the HPT rotor stage 1 blades, depending on the results of the BSIs, additional BSIs at reduced intervals or replacement of the HPT rotor stage 1 blades
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
Within 50 flight hours
AI-generated summary from the source AD text. Verify against the official source before acting.
Affected Aircraft
CFM International, S.A. Model LEAP-1A23, LEAP-1A24, LEAP-1A24E1, LEAP-1A26, LEAP-1A26CJ, LEAP-1A26E1, LEAP-1A29, LEAP-1A29CJ, LEAP-1A30, LEAP-1A32, LEAP-1A33, LEAP-1A33B2, and LEAP-1A35A engines operating in the South Asia region
AI-generated summary from the source AD text. Verify against the official source before acting.
Source: Official FAA Source ↗
Retrieved: Apr 4, 2026
Rights: U.S. Government Public Domain
This site is not affiliated with or endorsed by the FAA. Always verify with official sources.