Glider Appeared To Get “Too Slow” As It Approached The Traffic Pattern Then Entered A Stall/Spin

Location: Vero Beach, FL Accident Number: ERA25FA066
Date & Time: December 6, 2024, 12:40 Local Registration: N244RW
Aircraft: Schleicher ASW24 Injuries: 1 Fatal
Flight Conducted Under: Part 91: General aviation - Personal

On December 6, 2024, about 1240 eastern standard time, a Schleicher ASW 24 glider, N244RW, was substantially damaged when it was involved in an accident near Vero Beach, Florida. The pilot was fatally injured. The glider was owned by a local soaring club and was operated as a Title 14 Code of Federal Regulations Part 91 personal flight.

The pilot was a seasonal member of the Treasure Coast Soaring Club based at New Hibiscus Airpark (X52), Vero Beach, FL. According to club members, the glider departed X52 about 1140 for a local flight. After about 1 hour, the glider approached the airport at about 1,000 ft above ground level (agl) to enter the left downwind leg of the traffic pattern for runway 36. They further 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 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 about 1/2-mile northwest of X52. 

Members of the club further stated that the accident flight was the pilot’s first flight after recently completing his familiarization training in the high performance single-seat glider. The on-scene examination revealed the glider came to rest in an upright position near the center of the grass median, and all major components of the glider were accounted for at the accident site. The cockpit area was fragmented and displaced upward. The right wing was separated about 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. 

FMI: www.ntsb.gov