On April 11, 2025, a Cessna 310R, registration N8930N, was destroyed following an accident near Boca Raton, Florida. The flight, operating under Part 91, was the first flight following the aircraft's annual inspection. The aircraft departed from Boca Raton Airport (BCT) bound for Tallahassee International Airport (TLH). The accident resulted in 3 fatal injuries to the two pilots and one passenger, while one individual on the ground sustained minor injuries.
What happened
During takeoff, airport surveillance video showed the aircraft maintained the runway centerline during the initial roll. However, shortly after rotation, the airplane yawed to the left and entered a continuous left turn. Witnesses observed the aircraft flying at a low altitude in a left yaw, with audio recordings indicating both engines were operating.
Preliminary ADS-B data showed that after takeoff, the aircraft drifted left and performed a series of turns, including a 180-degree turn and several 360-degree turns. The final data point recorded the aircraft making its ninth turn at 10:22, located 273 feet south of the initial impact point. During the event, one of the pilots reported via air traffic control recordings that the aircraft was experiencing rudder issues that prevented any turns to the right.
The aircraft first struck several trees in a road median before impacting the road and continuing to a main wreckage site located on railroad tracks, approximately 370 feet from the initial impact. The wreckage was highly fragmented, and a post-impact fire caused significant thermal damage, consuming much of the cockpit and fuselage.
The investigation
Investigators examined the flight control systems and engine components. The rudder was found near the initial impact point with impact and thermal damage. While the right rudder control cable was continuous, the rudder bellcrank attach bracket had separated from the bellcrank. The left rudder cable had fractured near both the rudder pedal attach point and the rudder bellcrank, with the ends showing a splayed appearance consistent with tension overload separation.
Regarding the elevator, the control cables were continuous, but the push/pull rods suffered impact damage and fractures. The aileron control cables also exhibited breaks consistent with tension overload or recovery cuts.
Both engines had separated from their installation points. The left engine's No. 1 cylinder head broke free from the cylinder barrel, and the crankcase sustained impact damage. The right engine's crankshaft was immobile due to impact damage, and cylinder heads for the No. 1 and No. 5 cylinders had broken free. Both propellers had separated from their respective crankshaft flanges, with various blades showing deformation, bending, and gouges.