AD 2009-07-03
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| engine | General Electric | Company CF6-80C2 and CF6-80E1 Series | Airworthiness Directives; General Electric Company CF6-80C2 and CF6-80E1 Series Turbofan Engines |
Unsafe Condition
Reports of 12 cracked high-pressure compressor rotor (HPCR) spool shaft stage 14 disk webs. Cracks may propagate to an uncontained failure of the disk and damage to the airplane.
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Required Actions
Perform a one-time eddy current inspection (ECI) of the HPCR spool shaft stage 14 disk web for crack indications. Remove from service any parts with web cracks.
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Compliance Time
At the next engine shop visit where the separation of a major engine flange will occur after the effective date of this AD.
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Affected Aircraft
General Electric Company CF6-80C2 and CF6-80E1 series turbofan engines with HPCR spool shaft stage 14 disks, part number (P/N) 1703M49G02, 1703M49G03, or 1509M71G10 installed. These engines are installed on, but not limited to, Airbus A300-600R/F, A310-200/300, A330-200/300, and Boeing 747-200B/300/400/400D/400F, 767-200/300/400F/400ER, and MD-11 airplanes.
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Source: Official FAA Source ↗
Retrieved: Apr 6, 2026
Rights: U.S. Government Public Domain
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