AD 93-25-17
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| engine | General Electric Company | CT7-2A | GENERAL ELECTRIC Models CT7-5A2, -7A, and -9C Engines; and Models CT7-2A, and -6 Engines |
| engine | General Electric Company | CT7-5A2 | GENERAL ELECTRIC Models CT7-5A2, -7A, and -9C Engines; and Models CT7-2A, and -6 Engines |
| engine | General Electric Company | CT7-6 | GENERAL ELECTRIC Models CT7-5A2, -7A, and -9C Engines; and Models CT7-2A, and -6 Engines |
| engine | General Electric Company | CT7-7A | GENERAL ELECTRIC Models CT7-5A2, -7A, and -9C Engines; and Models CT7-2A, and -6 Engines |
| engine | General Electric Company | CT7-9C | GENERAL ELECTRIC Models CT7-5A2, -7A, and -9C Engines; and Models CT7-2A, and -6 Engines |
Unsafe Condition
Fatigue cracks in the gas generator turbine (GGT) disks and cooling plates can result in uncontained engine failure.
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Required Actions
Remove from service affected GGT rotor stage disks and cooling plates prior to exceeding the 'Max total allowable cycles' as listed in specified GE service bulletins, and replace with serviceable parts. Compliance may be adjusted with FAA approval.
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Compliance Time
Prior to exceeding the 'Max total allowable cycles' as listed in the referenced GE service bulletins.
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Affected Aircraft
General Electric Models CT7-5A2, -7A, -9C Turboprop Engines; CT7-6, -2A Turboshaft Engines with GGT disks and cooling plates listed by P/N and S/N in GE SB A72-252, A72-17, and A72-18.
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Source: Official FAA Source ↗
Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
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