|Year||Reg||Owner||Engine & Prop||Information (from DR or FAA)||Weight|
and flown in USA, later moved to Switzerland, ran out of fuel, fatal.
On December3, 2006, at 1426 coordinated universal time (1526 central European Time), a One Design DR107, US registered N107FP, owned by 107 5 Flying Corporation and piloted by the accident pilot,
was destroyed when it impacted terrain following engine problems while departing Langenthal Airfield, Switzerland. Visual meteorological conditions prevailed at the time of the accident. The pilot was fatally injured. The flight was originating at the time of the accident.
|UKN||N111PE||PIERCE ENTERPRISES INC||UKN|
|8/12/1998||N207TW||WAKELY TERRENCE J||I0360 SER A&C||N
number cancelled/on hold. Crashed, flipped over after prop strike,
pilot survived, aircraft being re-built.
The pilot said he was conducting touch and go landings in the amateur built airplane. He said that on the fourth or fifth landing he attempted a wheel landing, the airplane bounced and he aborted the landing attempt. During the climb the airplane experienced an increasing vibration. The pilot said he then initiated a forced landing to a crop field adjacent to the airport. During the rollout the airplane nosed over. Subsequent to the accident an examination revealed that the propeller sustained damage during the previous bounced landing.
|UKN||N212PJ||PIROS JAMES G||UNK|
|3/27/2003||N255HR||Robert Huber||Crashed, performing aerobatics, fatal|
& metal Sensenich.
The airline transport pilot reported that he was having difficulty maintaining control of the single-engine experimental airplane while attempting to land. He aborted the landing and executed a go-around. During the go-around, he reported that the engine lost power, and he subsequently made a forced landing in a wet field, one half-mile from the departure end of the runway. The airplane sustained structural damage to the main right main landing gear spars and both wings. The weather reported at the time of the accident was wind from 150 degrees at 5 knots, clear skies, unlimited visibility, and a temperature of 70 degrees Fahrenheit. The reason for the reported loss of engine power could not be determined.
|UNK||N386PT||THERMAN J M/THERMAN T E||UNK|
|UKN||N45U||REAGAN ROY D||UKN|
|9/11/1996||N555TE||ELLSBERG THOMAS R||UNK||Crashed,
Fatal, Inverted Spin recovered too low.
The pilot was practicing aerobatic maneuvers in the single-seat experimental airplane when the accident occurred. Witnesses observed the pilot make a low pass down the runway and then enter a vertical ascent. The airplane climbed to about 1,500 feet agl, at which point the pilot placed the airplane in a flat spin. After completing 4 to 5 rotations, the pilot recovered from the spin. The witnesses estimated that after the spin recovery, the airplane was at an altitude between 70 and 200 feet agl. The airplane continued to descend, impacted the ground, exploded and was consumed by fire. An on scene examination of the wreckage by an FAA inspector found no evidence of any pre-impact mechanical discrepancies.
|N55TE||Just after the pilot entered the aerobatic box in his experimental One Design aircraft, the airplane developed an "extreme vibration." The pilot therefore shut the engine off and began a glide toward a nearby road. During the descent, with the propeller windmilling, the aircraft shook so violently that it was very difficult for the pilot to see, and he became concerned that the engine might separate from the airframe. When the aircraft reached the ground, the pilot tried to land on a narrow road, but with his visibility still significantly effected by the vibration of the airframe, he was unable to keep the One Design within the lateral confines of the road. During the landing roll, one of the main wheels departed the side of the road and encountered soft terrain. The main gear wheel then began to sink into the soft terrain, and the aircraft nosed over onto its back. It was later determined that one of the propeller counterweight mounting brackets (along with the counterweight itself) had separated from the propeller. A post-accident inspection of the counterweight on the apposing blade revealed that one of its mounting bolts was under-torqued approximately 115 inch-pounds below the value listed in the associated assembly torque table. The propeller, which was a non-certified model with composite blades, had been loaned to the pilot by the manufacturer, while his propeller was undergoing a periodic inspection.|
|6/24/1998||N857JA||Jim Abraham/Ken Erickson||UNK||Crashed,
Destroyed-Rudder Cable swaging improperly done, pilot bailed out OK.
The pilot indicated the purpose of the flight was to practice outside snap rolls. When he pressed on the left rudder pedal, it went all the way to the floor with no resistance. He reported that the airplane was in straight and level flight when he reached down to verify that the cable was detached, hoping to be able to control the airplane when he realized that the cable was slack from the rear of the airplane. He then informed the tower of the emergency. The airplane entered a right bank from which the pilot could not recover and he jumped out of the airplane and parachuted to safety. The airplane wreckage was examined. The right rudder cable was found continuous from the cockpit pedal to the rudder control horn, with the horn end of the cable secured with a nicopress fitting. The left rudder cable was attached to the cockpit pedal but was detached from the rudder horn. The left cable to horn nicopress fitting was not on the cable's horn end and the left rudder cable end exhibited long and even splaying. When the cable was stretched out, it went all the way back to the rudder horn and was nearly identical in length to the right cable. A search of the accident site failed to locate the missing nicopress fitting.
number cancelled. Crashed, ran off runway, flipped over,- fatal.
The pilot was landing the amateur-built experimental category airplane on a dry, paved runway. FAA inspectors reported that tire marks on the runway indicated the airplane touched down on the runway, and at some point during the landing roll it veered left of the runway centerline. The airplane nosed over on the western edge of the runway. The airplane's canopy was crushed during the accident sequence and the pilot, the sole occupant, was killed. There were no witnesses to the accident. The pilot of a departing aircraft reported seeing the wreckage during his initial climb from the airport. The hourly Aviation Routine Weather Report (METAR) was, in part, wind from 280 degrees (true) at 10 knots; visibility, 15 statute miles; temperature 29 degrees C; altimeter, 29.91 inches.
|UNK||UNK - Canada||Pete Plumb||UNK||Test Pilot crashed, fatal, stall spin on takeoff after spinner broke and prop broke|
|1999||N31SH||Sean DeRosier||IO-360 PV & fixed pitch||Fatal accident at airrshow…