On May 15, 2024, a Cessna 150L, registration N1701Q, was destroyed during an instructional flight near Godley, Texas. The accident resulted in 1 fatality involving the student pilot.
What happened
At approximately 19:48, the aircraft departed from runway 15 at Cleburne Regional Airport (CPT) as part of a Part 91 instructional flight. After completing one landing, the aircraft flew south, performing several 360-degree turns at altitudes between 3,200 and 3,300 feet MSL. The flight continued with various maneuvers, including climbing to 4,100 feet MSL and performing descending turns over the Brazos River near Lake Granbury.
At 20:38, ADS-B data showed the aircraft climbing through 1,950 feet MSL. Shortly thereafter, the aircraft entered a left turn and began a rapid descent. During the final seconds of recorded data, the aircraft's vertical speed was measured between -6,000 and -10,000 feet per minute. The final data point recorded the aircraft descending through 1,000 feet MSL at 75 knots airspeed.
A witness near the site reported seeing the airplane flying very slowly, appearing to almost "hover," before it suddenly entered a spiraling nosedive. The witness observed the aircraft complete at least 6 to 8 rotations in a descending spiral before disappearing behind a hill. Following the impact, smoke and fire were visible from the site.
The investigation
The wreckage was located in an open grass pasture. The aircraft came to rest upright and wings level. A significant post-impact fire destroyed the cockpit, instrument panel, and much of the cabin.
Investigators examined the flight controls and found that all primary surfaces—including the elevators, ailerons, and rudder—were intact and that all control cables maintained continuity from the cockpit to the surfaces. The elevator trim was found in a 7-degree trailing edge up position, and the flaps were found in the fully extended 40-degree position.
The engine examination showed that the crankshaft rotated freely and the engine was capable of compression in cylinders 2, 3, and 4. While cylinder no. 1 showed no compression, this was attributed to exhaust valve springs that had taken a new set (becoming shorter) due to the heat of the post-impact fire. The propeller showed a slight bend on one blade, but the investigation revealed no evidence of a pre-impact mechanical malfunction or failure that would have prevented normal operation.