AD 2001-20-01
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| engine | Pratt & Whitney | Canada PT6A-25C and -114A Series | Airworthiness Directives; Pratt & Whitney Canada PT6A-25C and -114A Series Turboprop Engines |
Unsafe Condition
Wear on the compressor bleed valve assembly cover, guide pin shaft, and cotter pin, as well as particles from diaphragm wear, may cause valve orifice blockage, resulting in a loss of power, an inability to accelerate the engine, and an in-flight shutdown.
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Required Actions
Perform an initial visual inspection of the compressor bleed valve assembly components within 150 flight hours after the effective date, followed by repetitive inspections every 600 flight hours. Replace the compressor bleed valve assembly with a redesigned valve assembly at the next shop visit, but no later than five years from the effective date.
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Compliance Time
Within 150 flight hours for initial inspection, and every 600 flight hours for repetitive inspections. Replacement must occur at the next shop visit but no later than five years from the effective date.
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Affected Aircraft
Pratt & Whitney Canada PT6A-25C and -114A Series turboprop engines that have incorporated P&WC S.B. 1510, installed on but not limited to Pilatus PC-7 and Cessna 208 Caravan airplanes.
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Source: Official FAA Source ↗
Retrieved: Apr 6, 2026
Rights: U.S. Government Public Domain
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