History of Flight
On June 23, 2018, at approximately 1408 mountain standard time, a Schempp-Hirth glider (registration N7880) was substantially damaged in an accident near Aguila, Arizona. The pilot sustained fatal injuries. The flight was conducted under Title 14 Code of Federal Regulations Part 91 as a personal flight.
Witnesses at Sampley's Airport (28AZ), Aguila, Arizona, reported that the pilot arrived earlier that day. The pilot flew one 3-minute flight that morning before departing on the accident flight at about 1359.
The driver of the glider tow vehicle stated that the launch was normal with no anomalies. He observed the glider depart the upwind leg of the traffic pattern and turn right, noting it was about 1,000 ft above ground level (agl) on the downwind leg. Approximately 3 minutes later, while reeling in the tow winch, he saw the glider near the approach end of runway 17 traveling west. The glider then made a right 360° turn with about a 30° bank angle at 400 ft agl. The turn continued, and the glider abruptly pitched 60° nose down and completed two spins before he lost sight of it about 100 ft agl.
Wreckage and Impact Information
A survey of the wreckage site revealed that the glider impacted flat, desert terrain in a steep nose-down attitude approximately 1,375 ft northeast of the approach end of runway 17. The glider came to rest inverted. The first point of impact was a shallow depression in the dirt 7 ft southwest of the main wreckage, measuring about 49-ft long, 1-inch wide, and 1-inch deep.
The forward fuselage and cockpit area were destroyed. The aft fuselage remained intact, but the fuselage-to-empennage section had separated; however, the flight control tubes remained connected. Flight control continuity was established from the rudder attach point forward to the rudder pedals. The stabilator remained attached to the top of the vertical stabilizer at all attach points. Flight control continuity was established from the stabilator forward to the control stick.
The left wing was partially separated from the fuselage at both attach points. The leading edge exhibited crushing damage consistent with vertical impact. The aileron control tube was separated at the hollow rivet attach point. The right wing remained attached to the fuselage, with its leading edge also showing crushing damage consistent with vertical impact. The aileron control tube and spoiler control tube remained attached to their respective bell cranks.
Post-accident investigation revealed no pre-impact mechanical malfunctions that would have precluded normal operation.
Medical and Pathological Information
The Maricopa County Office of the Medical Examiner performed a postmortem examination of the pilot. The cause of death was reported as blunt force injuries. The FAA Forensic Sciences Bioaeronautical Science Research Lab performed forensic toxicology on specimens from the pilot, with results negative for volatiles and tested-for-drugs.