ASN Wikibase Occurrence # 297172
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| Date: | Sunday 9 June 2002 |
| Time: | 11:00 LT |
| Type: | Schweizer 269D |
| Owner/operator: | |
| Registration: | N333UC |
| MSN: | 0006 |
| Year of manufacture: | 1994 |
| Total airframe hrs: | 709 hours |
| Engine model: | Rolls-Royce 250-C20W |
| Fatalities: | Fatalities: 0 / Occupants: 2 |
| Aircraft damage: | Substantial |
| Category: | Accident |
| Location: | Crawford, Texas -
 United States of America
|
| Phase: | Unknown |
| Nature: | Private |
| Departure airport: | Crawford, TX (TE92) |
| Investigating agency: | NTSB |
| Confidence Rating: |  Accident investigation report completed and information captured |
The pilot made a forced landing following a loss of engine power after takeoff. The 4,950-hour pilot reported that the aircraft was in a climb at 75 feet AGL, an airspeed of 40-50 knots, and approximately 200 feet south of the takeoff point, when the engine lost power. The pilot executed an autorotation straight ahead and landed. Examination of the engine revealed no damage in the gearbox, but significant thermal distress to several turbine components. The compressor rotated freely and the N1 and N2 sides of the accessory gearbox rotated freely. The compressor and accessory gearbox were not opened. The first stage nozzle shield appeared normal. The first stage nozzle exhibited heat distress on vanes. The first stage turbine wheel exhibited heat distress to all blades; approximately 40-50 percent of the airfoil burned away. The second stage turbine wheel exhibited heat distress to approximately 1/3 of the blades; approximately 30 percent of the airfoil burned away. The third and fourth stage turbine wheels and nozzles appeared normal. The turbine to compressor coupling exhibited rotational marks on the compressor end. The fuel control unit and power turbine governor were tested, and no anomalies were noted.
Probable Cause: The loss of engine power as a result of the pilot's exceedence of the engine's temperature limits, resulting in the melting of blades on the first and second stage turbine wheels. A contributing factor was the lack of suitable terrain for the forced landing.
Accident investigation:
 |
|
Sources:
NTSB FTW02LA179
Revision history:
| Date/time | Contributor | Updates |
|---|---|---|
| 14-Oct-2022 15:21 | ASN Update Bot | Added |
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