Accident Details
On August 3, 2024, at approximately 2058 central daylight time, a De Bird gyroplane, registration N140DG, sustained substantial damage during an accident near Napoleon, Michigan. The pilot was fatally injured. The gyroplane was being operated as a personal flight under Title 14 Code of Federal Regulations Part 91.
The airstrip consisted of a single turf runway oriented approximately 160/340 degrees, with trees lining the majority of both sides. The accident takeoff was conducted on runway 34. The gyroplane came to rest in wooded terrain about 200 feet left of the runway centerline and about 250 feet short of the departure end of the runway. The aircraft was upright but leaning to its left side, supported by trees.
Witness Account
The pilot's husband reported that his wife was on an evening pleasure flight. He stated that weather conditions were good and that she was very experienced in the accident gyroplane, with an estimated 800 flight hours in that aircraft. He was approximately one-quarter mile away from their private airstrip and could hear the gyroplane during takeoff and climb. He reported hearing two loud thumps but did not note any unusual sounds prior, though he could not be certain about engine sounds as the gyroplane was farther away after takeoff. After hearing the thumps, he took off in another gyroplane to search but could not locate the accident aircraft.
Aircraft and Site Examination
Examination of the accident site revealed crushing of the forward and left side of the fuselage. The left main landing gear was fractured. The horizontal and fixed tail surfaces were found a short distance away from the fuselage on opposite sides of surrounding trees, consistent with separation before the gyroplane descended into the trees. The tail surfaces exhibited two separate areas of damage with features consistent with impact by the main rotor. The main rotor blades had yellow paint transfer, also consistent with impact against the tail. The tail boom was partially separated from the fuselage and remained attached only by the two rudder cables. The fracture pattern indicated the aft end of the boom bent toward the right prior to failure, consistent with a potential rotor strike given the counterclockwise rotation of the main rotor blades as viewed from above.
Systems Examination
The flight control system consisted of a cyclic control and a collective control that adjusted main rotor blade pitch depending on blade location during rotation. Directional control was accomplished by a single moveable vertical surface below the horizontal stabilizer and between the two fixed vertical stabilizers. Examination confirmed continuity of the cyclic, collective, and directional control systems, with all identified breaks consistent with impact damage. The engine examination was limited but confirmed continuity of the reciprocating and valve train system; compression was felt on all cylinders during rotation. No preimpact anomalies were found. The rotor drive system was intact except for a separation of the drive coupling in the top of the fuselage. All three main rotor blades were intact from root to tip but exhibited bending at various locations due to impact. All main rotor system components were intact, with damage consistent with impact.