What happened
The FAA’s narrative, in sentence case. The FAA writes it in capitals and removes private details.
Aircraft departed from the aircraft privacy data omitted private strip on northwest heading. During initial climb, aircraft began left turn and crashed into wooded area adjacent to departure strip, fatally injuring the pilot and causing substantial damage to the aircraft.
The left-hand side of fuselage was damaged, and gyroplane came to rest partially laying on its left side. Left landing gear was broken off from impact. The horizontal tail and vertical tips were short distance to the west of fuselage approx. 20'. The tail surface had been struck by the main rotor blades evident from the deformation on top of horizontal stabilizer matching leading edge profile of main rotor blades. Matching paint marks on main rotor blades concurred approximate location of strike on horizontal and vertical tail locations. The horizontal tail section had departed prior to impact but was located at ground level and not in the canopy of the surrounding trees. The tail boom structure was fractured off but held to main structure by the cables for the rudder and was located to the aft right of main structure consistent with the rotor strike of the horizontal tail structure. The gyroplane’s fuel tank was ruptured from surrounding woodland brush and the smell of fuel was evident. The gyroplane had one pusher blade busted off but was found within 3 feet of engine. A small sapling was wedged between the engine case and the propeller hub and vertical marring was consistent with the gyroplane sliding straight down the sapling. Continuity was intact for the cyclic, collective and directional controls. Engine was intact and check of engine was limited in field. Engine developed compression on all cylinders when rotated thru and valve train continuity was observed with valve covers removed. The rotor drive system was intact except at the drive coupling separated from impact and had slid apart at the sleeved connection. All rotor blades were connected at hub with no real damage sustained except for bending encountered on final rotational impact with tree 6 feet above ground level.
As the FAA filed it
AIRCRAFT DEPARTED FROM THE AIRCRAFT ^PRIVACY DATA OMITTED^ PRIVATE STRIP ON NORTHWEST HEADING. DURING INITIAL CLIMB, AIRCRAFT BEGAN LEFT TURN AND CRASHED INTO WOODED AREA ADJACENT TO DEPARTURE STRIP, FATALLY INJURING THE PILOT AND CAUSING SUBSTANTIAL DAMAGE TO THE AIRCRAFT.
THE LEFT-HAND SIDE OF FUSELAGE WAS DAMAGED, AND GYROPLANE CAME TO REST PARTIALLY LAYING ON ITS LEFT SIDE. LEFT LANDING GEAR WAS BROKEN OFF FROM IMPACT. THE HORIZONTAL TAIL AND VERTICAL TIPS WERE SHORT DISTANCE TO THE WEST OF FUSELAGE APPROX. 20'. THE TAIL SURFACE HAD BEEN STRUCK BY THE MAIN ROTOR BLADES EVIDENT FROM THE DEFORMATION ON TOP OF HORIZONTAL STABILIZER MATCHING LEADING EDGE PROFILE OF MAIN ROTOR BLADES. MATCHING PAINT MARKS ON MAIN ROTOR BLADES CONCURRED APPROXIMATE LOCATION OF STRIKE ON HORIZONTAL AND VERTICAL TAIL LOCATIONS. THE HORIZONTAL TAIL SECTION HAD DEPARTED PRIOR TO IMPACT BUT WAS LOCATED AT GROUND LEVEL AND NOT IN THE CANOPY OF THE SURROUNDING TREES. THE TAIL BOOM STRUCTURE WAS FRACTURED OFF BUT HELD TO MAIN STRUCTURE BY THE CABLES FOR THE RUDDER AND WAS LOCATED TO THE AFT RIGHT OF MAIN STRUCTURE CONSISTENT WITH THE ROTOR STRIKE OF THE HORIZONTAL TAIL STRUCTURE. THE GYROPLANE’S FUEL TANK WAS RUPTURED FROM SURROUNDING WOODLAND BRUSH AND THE SMELL OF FUEL WAS EVIDENT. THE GYROPLANE HAD ONE PUSHER BLADE BUSTED OFF BUT WAS FOUND WITHIN 3 FEET OF ENGINE. A SMALL SAPLING WAS WEDGED BETWEEN THE ENGINE CASE AND THE PROPELLER HUB AND VERTICAL MARRING WAS CONSISTENT WITH THE GYROPLANE SLIDING STRAIGHT DOWN THE SAPLING. CONTINUITY WAS INTACT FOR THE CYCLIC, COLLECTIVE AND DIRECTIONAL CONTROLS. ENGINE WAS INTACT AND CHECK OF ENGINE WAS LIMITED IN FIELD. ENGINE DEVELOPED COMPRESSION ON ALL CYLINDERS WHEN ROTATED THRU AND VALVE TRAIN CONTINUITY WAS OBSERVED WITH VALVE COVERS REMOVED. THE ROTOR DRIVE SYSTEM WAS INTACT EXCEPT AT THE DRIVE COUPLING SEPARATED FROM IMPACT AND HAD SLID APART AT THE SLEEVED CONNECTION. ALL ROTOR BLADES WERE CONNECTED AT HUB WITH NO REAL DAMAGE SUSTAINED EXCEPT FOR BENDING ENCOUNTERED ON FINAL ROTATIONAL IMPACT WITH TREE 6 FEET ABOVE GROUND LEVEL.
NTSB investigation
The NTSB’s investigation of this event, with its probable cause and findings. Matched to this report by N-number and date.