N747HW

HISTORY OF FLIGHTOn October 5, 2011, at 1738 eastern daylight time, an experimental amateur-built Arion LI, N747HW, was substantially damaged when it impacted a house near Hedgesville, West Virginia. The airplane had departed from the Green Landings Airport (WV22), Hedgesville, West Virginia, just prior to the accident. Day visual metrological conditions prevailed and no flight plan had been filed. The airline transport pilot was fatally injured. The personal local flight was conducted under the provisions of Title 14 Code of Federal Regulations Part 91.

According to several eyewitnesses, the pilot had been assembling the airplane since January 2011. The first flight in the airplane had taken place on October 3, 2011, and the pilot was attempting to acquire the 40 flight hours required in order to fly the airplane to his residence in Danbury, Connecticut. Several witnesses reported that shortly after takeoff, approximately 15 feet above ground level, the airplane pitched up to a 45 to 60 degree nose up attitude and then appeared to have stalled just prior to impacting the house.

According to an internet forum entry dated Monday, October 3, 2011, at 3:41 pm, it stated in part "first flight of the lightning N747HW today in West Virginia after 7 months building. Everything went as planned with no abnormal flight characteristics and smooth running engine... This is my second kit. First was a Glasair III and took 7 years to complete. Looking forward to many happy hours of flying. I will fly it to Connecticut after the 40 hours test phase." PERSONNEL INFORMATIONAccording to Federal Aviation Administration (FAA) records, the pilot, age 70, held an airline transport pilot certificate with a rating for multiengine land with numerous transport category class type ratings. He also held a commercial pilot certificate with airplane single-engine land privileges, a limited flight instructor certificate for airplanes and instrument airplane, a flight engineer certificate with a rating for turbojet powered, and a repairman experimental aircraft builder certificate for a Glasair model III aircraft. The pilot's most recent third class medical certificate was issued on December 4, 2007, with a limitation of "must have available glasses for near vision." At the time of the examination, the pilot reported a total of 21,811 flight hours. At the time of the accident, his medical certificated had expired but had never been denied. The accident airplane met the criteria for the light sport designation and the pilot was only required to have a valid driver's license and a pilot's certificate. AIRCRAFT INFORMATIONThe two-seat, low-wing, fixed gear, composite constructed airplane, serial number 128, was manufactured in 2011. According to FAA records, the airplane was issued a special airworthiness certificate on September 30, 2011, and was registered to the pilot. It was equipped with a Jabiru 3300A engine and according to a witness familiar with the construction of the airplane, it had about 4 total flight hours at the time of the accident. At the time of this writing no maintenance logbook records had been located. METEOROLOGICAL INFORMATIONThe 1753 recorded weather observation at Martinsburg Eastern West Virginia Regional/Shepherd Airport (MRB), Martinsburg, West Virginia, located approximately 10 miles to the south of the accident location, included wind from 340 degrees at 7 knots, visibility 10 miles, clear skies, temperature 23 degrees C, dew point 10 degrees C; barometric altimeter 30.19 inches of mercury. AIRPORT INFORMATIONThe two-seat, low-wing, fixed gear, composite constructed airplane, serial number 128, was manufactured in 2011. According to FAA records, the airplane was issued a special airworthiness certificate on September 30, 2011, and was registered to the pilot. It was equipped with a Jabiru 3300A engine and according to a witness familiar with the construction of the airplane, it had about 4 total flight hours at the time of the accident. At the time of this writing no maintenance logbook records had been located. WRECKAGE AND IMPACT INFORMATIONThe airplane impacted a concrete wall at a nearby residence in a nose down attitude and fractured into two pieces just aft of the aft baggage wall.

Continuity was confirmed to all flight control surfaces from the control column and the rudder pedals. Continuity was confirmed to the elevator via the push/pull tube that was bent approximately mid span and was co-located with the impact damage of the airframe. The ailerons were operated by a push/pull tube system and continuity was confirmed from the control column to the right aileron bell crank. The left control column push/pull tube was found fracture separated at the base of the control column. Continuity was confirmed from the fracture point to the aileron bell crank.

Right wing

The right wing exhibited impact damage to the leading edge. The outboard section of the wing was impact separated beginning on the leading edge approximately 74.5 inches from the wing root and on the trailing edge, approximately 108 inches from the wing root, exposing the main wing spar. The main wing spar, comprised of fiberglass/composite material, was impact damaged and bent at the damaged point in the positive direction. The aileron was impact separated at the bell crank and located near the wreckage. The flap was impacted separated and co-located with the aileron. The right main landing gear remained attached at the fuselage attach point; however, was bent outward approximately 40 degrees beyond its normal position.

Empennage

The empennage was impact fractured approximately 65 inches forward of the elevator attach point and approximately 10 inches aft of the rear bulkhead. The elevator trim tab indicated approximately 8 degrees trailing edge down. The elevator and rudder remained attached to their respective attach points.

Left Wing

The left wing remained attached at the wing root; however, exhibited impact damage approximately 74 inches outboard of the fuselage attach point. The initial impact damage was consistent in dimension to the 6 inch by 6 inch anchor post, utilized to elevate the deck on the private residence, which the airplane impacted. The trailing edge impact separation point was slightly inboard of the aileron. The flap was impact separated at its respective attach points and was co-located with the wing and the anchor post. The aileron remained connected to its respective attach point; however, the associated push/pull tube was impact separated from the bell crank.

Engine

The engine remained attached to the firewall and the wood propeller blades were impact separated at the propeller hub. The engine mounts exhibited impact damage and numerous bends. The gascolator was of glass construction and was impact damaged. The propeller spinner exhibited torsional twisting.

The fuel pump remained attached to the engine, was removed, and examined. It contained a blue fluid similar in color and smell as 100LL aviation fuel.

The sparkplugs were removed and appeared to be relatively new with little wear and were tan in color. Thumb compression was achieved on all cylinders via hand rotation of the propeller hub. The right front cylinder indicated impact damage on the leading edge of the cylinder fins and was weaker in compression than the other 5 cylinders. The cylinder cover was removed and all parts were observed operating normally and smoothly with no malfunctions or abnormalities noted. The nose gear was impacted separated from the nose strut; however, the strut remained attached to the engine.

The magneto was spun utilizing the propeller hub and spark was observed at 4 of the cylinders. The other 2 cylinder lead wires exhibited impact damage.

The throttle and mixture controls were found in the full forward position; however, due to cockpit, firewall, and airframe damage, an exact setting on the engine could not be determined.

The engine oil dipstick was found in the engine and was removed; the dipstick had oil present.

Cockpit

The cockpit area exhibited impact crush damage. The left side of the cockpit wall was impact damaged and the fiberglass/composite and aluminum substructure was fractured and bowed outward. The seats remained attached to the airframe and the seatbelts and shoulder harnesses remained attached at their respective attach points. The right seat belts remained connected and operated normally. The left seat belt webbing indicated stretching and the male/female end were disconnected by first responders to facilitate removal of the pilot. The shoulder harnesses attached point was located in the tail section aft of the break near the elevator. The rudder pedals were manual adjusted rudder pedals utilizing a bungee and tube system. The firewall appeared to have been slid aft approximately 7 inches and was buckled approximately midspan. The cockpit canopy was impact damaged and pieces of the plexiglass canopy were co-located with the wreckage. The cabin area midline seam exhibited a longitudinal fracture along the entire roof of the cabin area to the impact fracture.

Fuel

The cockpit fuel selector valve was found in the "R" position indicating the right tank was selected. The left wing fuel tank was full of fuel and the right wing fuel tank had approximately 1 inch in depth of fuel. Both fuel tank caps remained secured and in place. A fuel receipt was produced by a local fixed base operator indicating that the day prior to the accident the airplane was fueled with 16.0 gallons of fuel.

The Emergency Locator Transmitter (ELT) was located in the wreckage; however, no signal was reported around the time of the accident. ADDITIONAL INFORMATIONA Garmin 696 GPS was recovered from the accident airplane and was sent to the NTSB Records Laboratory for download. The GPS began recording data earlier in the day and also included data just prior to the accident. The last recorded data occurred at 1737:44 with a ground...