Accident Overview
On May 25, 2025, at approximately 1007 eastern daylight time, an experimental, amateur-built Zenith STOL CH701 (registration N514JG) was substantially damaged when it impacted trees and terrain near Geneva, Ohio. The flight was conducted as a Title 14 Code of Federal Regulations Part 91 test flight. The pilot was fatally injured, and the pilot-rated passenger sustained serious injuries.
Flight History
According to the pilot-rated passenger, who also owned the airplane, he purchased it in October 2024. The wings were removed, and the airplane was transported to Germack Airport (7D9) in Geneva, Ohio, for reassembly and inspection. The purpose of the flight was a test flight following reassembly.
During the preflight inspection, the pilot verified that the flight controls were free and correct, and no anomalies were noted during the engine run-up check. The passenger reported that during the initial takeoff roll, the airplane did not seem ready to fly, prompting the pilot to abort the takeoff. The pilot taxied back to the departure end of runway 19 and initiated a second takeoff. The airplane became airborne approximately 1,800 feet down the 3,260-foot-long paved runway.
During the initial climb, at about 150 feet above ground level (agl), the airplane could not gain additional altitude. The pilot pitched the nose down to increase airspeed, but the airplane could not maintain level flight. A surveillance video captured an engine sound consistent with operating power as the airplane descended toward trees in a nose-up attitude.
The airplane struck trees and terrain about half a mile southwest of the departure end of the runway. The first point of impact was a tree about 40 feet agl. The airplane came to rest upright on a heading of approximately 330°, about 30 feet from the initial impact point. Several tree limbs in the wreckage area exhibited angular cuts with black transfer marks. A postcrash fire consumed most of the fuselage and the right-wing fuel tank.
Wreckage Examination
All major components were accounted for within the wreckage area. Both wings were partially separated from the fuselage and showed semicircular impressions on their leading edges. Flight control continuity was established from the cockpit to the rudder and elevator. The flaperon control was observed retracted, and continuity was confirmed to the flaperon mixer assembly and bellcranks. The left and right flaperon control rods were impact-separated from the flaperons.
Approximately 10 gallons of fuel were recovered from the left wing. A fuel sample was free of contaminants and tested negative for water using water-finding paste. The fuel valve was in the on position and was confirmed functional during a field test with low-pressure air. Most of the fuselage-mounted fuel lines were thermally destroyed.
The engine remained attached to the fuselage, with thermal damage to the accessory area. Spark plug electrodes were undamaged and showed normal wear and coloration. Both magnetos produced spark when the propeller was rotated by hand. Crankshaft continuity was established from the propeller flange to the rear gears, and valvetrain continuity was also confirmed. Compression and suction were attained from all four cylinders. No anomalies were noted to the induction air filter or exhaust system. The throttle control cable was attached to the carburetor and observed in the open position, while the mixture control cable was attached and in the rich position. The carburetor fuel inlet screen was clear of debris.
The three-bladed composite propeller remained attached to the engine. One blade separated at the hub, and the remaining two blades exhibited impact damage to their leading edges. The wreckage was retained for further examination.