AD 2011-18-02
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| engine | General Electric | Company CF34-10E2A1 | Airworthiness Directives; General Electric Company CF34-10E2A1; CF34-10E5; CF34-10E5A1; CF34-10E6; CF34-10E6A1; CF34-10E7; and CF34-10E7-B Turbofan Engines |
Unsafe Condition
High-cycle fatigue cracking of the fan rotor spinner support attachment lugs, leading to separation of the fan rotor spinner assembly, uncontained failure of the engine, and damage to the airplane.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Remove from service the 24 fan rotor blade retainers, P/N 2050M56P02. Remove from service the fan rotor spinner support that operated with the fan rotor blade retainers removed. Do not install or re-install any fan rotor blade retainers or fan rotor spinner supports after the effective date.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
Within 1,800 hours-in-service after the effective date of this AD.
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Affected Aircraft
General Electric Company CF34-10E2A1, CF34-10E5, CF34-10E5A1, CF34-10E6, CF34-10E6A1, CF34-10E7, and CF34-10E7-B turbofan engines with fan rotor spinner part numbers 2050M34G03, 2050M34G04, 2050M34G05, 2050M34G06, 2437M60G01, or 2437M60G02 installed.
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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