AD 2017-17-18
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| engine | General Electric | Company | Airworthiness Directives; General Electric Company Turbofan Engines |
Unsafe Condition
Analysis showed that stresses in the pinholes of affected fan blades could result in crack initiation at pinhole surfaces beyond 19,000, 19,500, or 25,000 cycles-since-new (CSN), depending on the engine model, leading to fan blade failure, uncontained blade release, engine damage, and airplane damage.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Initial and repetitive eddy current inspections (ECIs) of affected fan blades are required until their removal. Affected fan blades must be removed before reaching 41,000 CSN. Repairs to affected blades are allowed, extending their life by an additional 28,000 cycles before removal.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
Within 50 flight hours after the effective date of the AD.
AI-generated summary from the source AD text. Verify against the official source before acting.
Affected Aircraft
General Electric Company CF34-8 model turbofan engines, as specified in the AD, with affected fan blades.
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
This site is not affiliated with or endorsed by the FAA. Always verify with official sources.