Accident Details
On October 24, 2020, about 1028 mountain standard time, a Lancair 235 airplane, registration N25NL, was substantially damaged when it impacted terrain near Cordes Lakes, Arizona. The pilot and passenger were fatally injured. The airplane was operated as a Title 14 Code of Federal Regulations Part 91 personal flight.
Flight History
The flight departed from Deer Valley Airport (DVT), Phoenix, Arizona, with an intended destination of Page, Arizona. Data from the Dynon Skyview D700 electronic flight information and engine monitoring system showed departure about 1011. About four minutes later, the airplane turned to a northerly heading and climbed until reaching a peak altitude of 8,000 ft msl around 1023. Indicated airspeed increased from about 130 to 150 knots during the climb.
At 1028:38, while at about 7,700 ft msl, the airplane executed a left 360° roll maneuver. During the roll, the airplane descended to about 6,500 ft msl, and vertical acceleration ranged from -0.7 to 2.9 G. At that time, the airplane was about 0.6 miles southwest of the accident site. Shortly after the roll, at 1028:50, engine rpm and oil pressure dropped to zero, and attitude, acceleration, and airspeed parameters became unreliable.
Pilot Information
A friend of the pilot reported that the pilot had recently learned how to perform rolls in a different type of airplane; the friend did not specify the make, model, or date of training.
Wreckage and Impact Examination
The accident site was located in mountainous terrain at an elevation of about 3,720 ft msl. The airplane impacted on a magnetic heading of about 045°. The main wreckage came to rest inverted, except for the empennage, which remained upright. All major structural components were attached. Debris was scattered within 15 ft of the forward area.
The fuselage fragmented into multiple sections. The empennage was mostly intact and undamaged, with the vertical stabilizer undamaged and the rudder attached with slight impact damage to its bottom. Rudder control continuity was established from the rudder pedals to the rudder; all four rudder cables had separated. Elevator control continuity was established; the elevator torque tube exhibited an upward fracture about 20 inches forward of the rod end bearing, with an additional right bend about 14 inches forward of the fracture. Aileron control continuity was established from the cockpit to both ailerons. Left and right flap torque tubes were intact.
Examination of recovered engine and airframe parts revealed no evidence of a preexisting mechanical malfunction that would have precluded normal operation.
Medical and Pathological Information
An autopsy of the pilot performed by the Yavapai County Medical Examiner determined the cause of death as multiple injuries. Toxicological testing by the FAA Forensic Sciences Laboratory detected no drugs. Ethanol was detected in the pilot’s cavity blood but not in his urine. N-Butanol was also detected in the cavity blood.