Accident Details
On December 6, 2024, at approximately 1240 eastern standard time, a Schleicher ASW 24 glider, registration N244RW, was substantially damaged when it crashed near Vero Beach, Florida. The pilot was fatally injured. The glider was owned by a local soaring club and operated as a Title 14 Code of Federal Regulations Part 91 personal flight.
Aircraft and Operator
The glider was based at New Hibiscus Airpark (X52) in Vero Beach, Florida, and was associated with the Treasure Coast Soaring Club. The pilot was a seasonal member of the club and had recently completed familiarization training in the high-performance single-seat glider. The accident flight was the pilot's first flight after completing that training.
Sequence of Events
According to club members, the glider departed X52 at about 1140 for a local flight. After approximately one hour, the glider approached the airport at an altitude of about 1,000 ft above ground level (agl) to enter the left downwind leg of the traffic pattern for runway 36. Witnesses reported that the glider appeared to get “too slow” as it approached the traffic pattern, then entered a stall/spin. The glider recovered from the spin at about 50 ft agl, then pitched up and entered a second stall/spin. The glider descended in a nose-down attitude and impacted a grass median between a divided highway, approximately one-half mile northwest of X52.
Post-Accident Examination
On-scene examination revealed that the glider came to rest upright near the center of the grass median. All major components were accounted for at the accident site. The cockpit area was fragmented and displaced upward. The right wing separated at midspan, with aft deformation noted to the leading edge of the separation area. An impact scar was observed on the ground about 3 ft in front of the right wing. The tail section was fractured and displaced to the right. Impact damage was noted to the elevator and horizontal stabilizer. The right aileron control tube was fractured at the wing separation area. The elevator control rod remained attached to its aft attach point and was separated at the aft fuselage separation area. Flight control continuity was established to the cockpit area except where impact separations were located. The wreckage was retained for further examination.