AD 95-13-08
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| engine | Pratt & Whitney Canada, Inc. | PT6A-67D | Airworthiness Directives; Pratt & Whitney Canada Model PT6A-67D Turboprop Engines |
Unsafe Condition
Cracking and irregularities in the compressor turbine (CT) disk and blades due to high cycle fatigue (HCF) fractures in the fir tree area of the blade while exposed to normal engine vibrations.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Inspect the compressor turbine (CT) disk and blades for cracking and irregularities using visual and fluorescent penetrant inspections. Install improved engine components including CT stator assembly, shroud housing, small exit duct assembly, blades, and feather seals. Remove AFM amendments and cockpit placards after installing improved components.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
Within specified intervals based on time-in-service (TIS) since last inspection or by the next shop visit after the AD's effective date, whichever comes first. Compliance with inspections must occur within 50, 100, or 250 hours TIS depending on prior TIS, and component installations must be completed within 30 days or at the next shop visit after July 12, 1995.
AI-generated summary from the source AD text. Verify against the official source before acting.
Affected Aircraft
Pratt & Whitney Canada PT6A-67D turboprop engines as specified in the AD, including those installed on Beech Model 1900D aircraft requiring AFM amendments and placards.
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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