AD 91-01-04
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| engine | General Electric Company | CF6-45A | GENERAL ELECTRIC COMPANY CF6-6, -45, -50, -80A Series Engines |
| engine | General Electric Company | CF6-45A2 | GENERAL ELECTRIC COMPANY CF6-6, -45, -50, -80A Series Engines |
| engine | General Electric Company | CF6-50A | GENERAL ELECTRIC COMPANY CF6-6, -45, -50, -80A Series Engines |
| engine | General Electric Company | CF6-50C | GENERAL ELECTRIC COMPANY CF6-6, -45, -50, -80A Series Engines |
| engine | General Electric Company | CF6-50C1 | GENERAL ELECTRIC COMPANY CF6-6, -45, -50, -80A Series Engines |
| engine | General Electric Company | CF6-50C2 | GENERAL ELECTRIC COMPANY CF6-6, -45, -50, -80A Series Engines |
| engine | General Electric Company | CF6-50C2B | GENERAL ELECTRIC COMPANY CF6-6, -45, -50, -80A Series Engines |
| engine | General Electric Company | CF6-50C2D | GENERAL ELECTRIC COMPANY CF6-6, -45, -50, -80A Series Engines |
| engine | General Electric Company | CF6-50CA | GENERAL ELECTRIC COMPANY CF6-6, -45, -50, -80A Series Engines |
| engine | General Electric Company | CF6-50E | GENERAL ELECTRIC COMPANY CF6-6, -45, -50, -80A Series Engines |
Unsafe Condition
Stage 1 fan disk post failure could result in multiple fan blade release, engine power loss, and uncontained engine failure.
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Required Actions
Ultrasonic inspect and fluorescent penetrant inspect (FPI) the stage 1 fan disk dovetail post for cracks at the next fan disk exposure after the effective date. Reinspect at each fan disk exposure, but not to exceed 7,500 cycles since last inspection (CSLI). Remove cracked parts from service prior to further flight.
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Compliance Time
Required as indicated, unless previously accomplished.
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Affected Aircraft
General Electric Company CF6-6, -45, -50, -80A Series Engines installed on McDonnell-Douglas DC-10, Boeing 747, Boeing 767, Airbus A310, and Airbus A300 aircraft.
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Source: Official FAA Source ↗
Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
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