What happened
On May 25, 2025, an experimental, amateur-built Zenith STOL CH701, registration N514JG, was involved in an accident near Geneva, Ohio. The flight was being conducted as a Part 91 test flight following the reassembly of the aircraft's wings.
During the preflight inspection, the pilot confirmed that flight controls were free and correct, and no issues were identified during the engine run-up. During the first takeoff attempt on the 3,260-foot paved runway at Germack Airport (7D9), the pilot aborted the takeoff because the aircraft did not appear to be performing as expected.
The pilot then attempted a second takeoff from the departure end of runway 19. The aircraft became airborne approximately 1,800 feet down the runway. While climbing at about 150 feet above ground level, the aircraft failed to gain further altitude. Although the pilot pitched the nose down to increase airspeed, the airplane could not maintain level flight. Surveillance video showed the engine producing power consistent with operating levels as the aircraft descended toward trees in a nose-up attitude.
The aircraft struck trees and terrain approximately one-half mile southwest of the runway departure end. The first impact occurred with a tree at roughly 40 feet above ground level. The aircraft came to rest upright on a heading of approximately 330 degrees. A post-crash fire occurred, destroying much of the fuselage and the right-wing fuel tank. The accident resulted in 1 fatality and 1 serious injury.
The investigation
Investigators examined the wreckage and found that the left wing contained approximately 10 gallons of fuel, which was free of contaminants and water. The fuel valve was functional and in the on position.
The engine remained attached to the fuselage. While the accessory area showed thermal damage, the spark plug electrodes were undamaged, and both magnetos produced spark during testing. The engine's valvetrain, compression, and suction were all functional, and no issues were found in the induction air filter or exhaust system. The throttle was in the open position and the mixture was in the rich position. The three-bladed composite propeller remained attached, though one blade had separated at the hub and the others showed impact damage.
Flight control continuity was established from the cockpit to the rudder and elevator. The flaperon control was retracted, and while the control rods had separated from the flaperons due to impact, the connection from the cockpit to the mixer assembly and bellcranks was intact.