Schweizer 269D N333UC

Summary

On 9 June 2002 at about 17:00 local time, a Schweizer 269D registered N333UC was involved in an accident near Crawford, Texas, United States. 2 people were on board and nobody was injured. The aircraft was substantially damaged. The NTSB has published a probable cause for this accident; it is quoted in full below.

Date

9 June 2002 at 17:00

Classification

Accident

Location

Crawford, Texas, United States

Nearest airport

Wales Air Field (TE92)

Coordinates

31.5897, -97.3692

Aircraft

Schweizer 269D

Registration

N333UC

Category

Helicopter

Engines

1

Operator

Not recorded

Operating rule

Part 91: General Aviation

Purpose of flight

Personal

Phase of flight

Not recorded

Route

Crawford → Unknown

Aircraft damage

Substantial

Weather

VMC

Light

Day

NTSB number

FTW02LA179

Nobody was injured.

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.

Quoted verbatim from the NTSB record. This site does not paraphrase or interpret it.

Read the full NTSB narrative

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.

Quoted verbatim from the NTSB record.