AD 93-13-10
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| engine | General Electric Company | CF6-45A | GENERAL ELECTRIC COMPANY Model (GE) CF6-45/-50 Series Engines |
| engine | General Electric Company | CF6-45A2 | GENERAL ELECTRIC COMPANY Model (GE) CF6-45/-50 Series Engines |
| engine | General Electric Company | CF6-50A | GENERAL ELECTRIC COMPANY Model (GE) CF6-45/-50 Series Engines |
| engine | General Electric Company | CF6-50C | GENERAL ELECTRIC COMPANY Model (GE) CF6-45/-50 Series Engines |
| engine | General Electric Company | CF6-50C1 | GENERAL ELECTRIC COMPANY Model (GE) CF6-45/-50 Series Engines |
| engine | General Electric Company | CF6-50C2 | GENERAL ELECTRIC COMPANY Model (GE) CF6-45/-50 Series Engines |
| engine | General Electric Company | CF6-50C2B | GENERAL ELECTRIC COMPANY Model (GE) CF6-45/-50 Series Engines |
| engine | General Electric Company | CF6-50C2D | GENERAL ELECTRIC COMPANY Model (GE) CF6-45/-50 Series Engines |
| engine | General Electric Company | CF6-50CA | GENERAL ELECTRIC COMPANY Model (GE) CF6-45/-50 Series Engines |
| engine | General Electric Company | CF6-50E | GENERAL ELECTRIC COMPANY Model (GE) CF6-45/-50 Series Engines |
Unsafe Condition
Cracks in the stage 12 compressor disk web-to-rim transition area or insufficient thickness (less than 0.070 inches) of the stage 11-13 compressor spool could lead to engine stall, aborted takeoff, or inflight engine shutdown.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Perform visual and fluorescent penetrant inspections (FPI) and mechanical/ultrasonic thickness measurements of the stage 12 compressor disk web-to-rim transition area per GE SB 72-1006. Replace spools with cracked areas or thickness below 0.070 inches. Reidentify spools with thickness between 0.070 and 0.074 inches with a new part number and impose a 16,000 CSN life limit. Mark spools with 0.074 inches or more thickness with 'SB 72-1006' and retain 19,000 CSN life limit.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
By the next engine shop visit, within 3,500 cycles after the AD's effective date (September 21, 1993), or by December 31, 1997, whichever occurs first for listed spools; for others, by next piece-part exposure or December 31, 1997, whichever occurs first.
AI-generated summary from the source AD text. Verify against the official source before acting.
Affected Aircraft
General Electric Company CF6-45A/-50 series engines installed on McDonnell Douglas DC-10, Airbus A300, and Boeing 747 series aircraft.
AI-generated summary from the source AD text. Verify against the official source before acting.
Source: Official FAA Source ↗
Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
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