AD 2005-18-01
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| engine | General Electric | Company CT7-5 | Airworthiness Directives; General Electric Company CT7-5, -7, and -9 Series Turboprop Engines |
Unsafe Condition
Reports of six stage 2 turbine aft cooling plates found cracked during inspection. Stage 2 aft cooling plate separation could result in uncontained engine failure and damage to the airplane.
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Required Actions
Perform a one-time eddy current inspection (ECI) of the stage 2 turbine aft cooling plate boltholes using GE Alert Service Bulletin (ASB) No. CT7-TP S/B 72-A0464, Revision 2. Remove from service any stage 2 turbine aft cooling plate that does not pass the return to service criteria specified in the bulletin.
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Compliance Time
Before accumulating an additional 6,000 cycles-in-service after the effective date of the AD, unless already done.
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Affected Aircraft
General Electric Company CT7-5A2, -5A3, -7A, -7A1, -9B, -9B1, and -9B2 turboprop engines, with stage 2 turbine aft cooling plate, part number (P/N) 6064T07P01, 6064T07P02, 6064T07P05, or 6068T36P01 installed. These engines are installed on, but not limited to, Construcciones Aeronauticas, SA CN-235 series and SAAB Aircraft AB SF340 series airplanes.
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Source: Official FAA Source ↗
Retrieved: Apr 6, 2026
Rights: U.S. Government Public Domain
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