N797AAdams Donald E DA1 · 2009

On March 2, 2015, about 1150 eastern standard time, an experimental amateur-built Adams DA1, N797A, owned and operated by a private individual, was substantially damaged during an off-airport landing and subsequent postcrash fire, shortly after takeoff from the Sebring Regional Airport (SEF), Sebring, Florida. The private pilot was fatally injured. Visual meteorological conditions prevailed and no flight plan had been filed for the personal flight that was conducted under the provisions of 14 Code of Federal Regulations Part 91.

The airplane was built by the pilot and based at SEF.

According to a friend of the pilot, about 2 years prior to the accident, the pilot was flying the airplane when it experienced a loss of engine power just after takeoff, due to a clogged fuel filter. The pilot landed back on the runway and the airplane sustained a propeller strike. The accident flight was the airplane's first flight since that incident. Recent maintenance included replacing the fuel filter and converting the airplane from a tailwheel to tricycle landing gear configuration.

Witnesses near the accident site reported hearing a "spitting and sputtering" engine as they observed the airplane descending from a low altitude. The pilot was able to land the airplane on grass about 1 mile south of SEF; however, after landing a postcrash fire erupted and destroyed the cockpit before the pilot could exit the airplane.

The pilot, age 76, held a private pilot certificate with ratings for airplane single-engine land and instrument airplane. The pilot's logbook were not recovered. He reported 1,950 hours of total flight experience, with 40 hours accumulated during the preceding 6 months, on his most recent application for a Federal Aviation Administration (FAA) third-class medical certificate, which was issued on November 10, 2014. In addition, at that time, he reported no chronic medical conditions and no medication use.

The single-engine, fixed-gear airplane, serial number 01, was issued an experimental special airworthiness certificate by the FAA on July 7, 2009. Its construction was based on a Sonerai homebuilt airplane kit, and it was powered by a converted Volkswagen 75-horsepower automobile engine, equipped with a Sterba wood propeller. The fuselage was constructed of steel tubing with fabric covering and the wings were constructed of aluminum.

The pilot's wife not able to locate the airplane's maintenance records, nor were they observed in the hangar where the airplane was kept.

A weather observation taken at SEF, at 1155, reported: wind from 130 degrees at 6 knots, 10 statute miles visibility, scattered clouds at 3,400 and 4,000 feet, temperature 26 degrees Celsius (C), dew point temperature 17 degrees C, and an altimeter setting of 30.28 in-Hg.

The single-engine, fixed-gear airplane, serial number 01, was issued an experimental special airworthiness certificate by the FAA on July 7, 2009. Its construction was based on a Sonerai homebuilt airplane kit, and it was powered by a converted Volkswagen 75-horsepower automobile engine, equipped with a Sterba wood propeller. The fuselage was constructed of steel tubing with fabric covering and the wings were constructed of aluminum.

The pilot's wife not able to locate the airplane's maintenance records, nor were they observed in the hangar where the airplane was kept.

The airplane touched down on the ground, and slid for about 75-feet on a magnetic heading about 070 degrees before it came to rest upright, adjacent to a canal, behind a residence.

All major portions of the airplane were located at the accident site. The right aileron, nose landing gear, and wooden propeller fragments were located along a ground scar leading to the main wreckage. The fuel tank, which was located aft of the engine firewall and in front of the cockpit area was compromised during the off-airport landing. A postcrash fire destroyed the cockpit, and consumed the propeller and all fuselage fabric coverings forward of the empennage, which was undamaged. The right wing sustained impact damage to the tip and forward outboard leading edge corner. In addition, the right wing inboard trailing edge corner was deformed diagonally approximately 1-foot. The inboard 4 feet of the left wing was consumed to the spar and the majority of the wing was fire damaged. Flight control continuity was confirmed from the cockpit controls to the rudder and elevator control surfaces. The respective left and right aileron connections were displaced consistent with impact damage. The airplane's entire fuel system, which included the fuel tank, the carburetor and fuel filter were consumed by fire.

The engine was also fire damaged, and could not be rotated. Subsequent disassembly of the engine at SEF, which included examination of all cylinders, pistons, rocker arms, valves, and spark plugs did not reveal any evidence of preimpact mechanical malfunctions.

An autopsy was performed on the pilot by the Office of the District 10 Medical Examiner, Winter Haven, Florida. The autopsy report identified hypertensive and atherosclerotic heart disease and indicated the cause of death was due to the postcrash fire.

Toxicological testing performed on the pilot by the FAA Bioaeronautical Science Research Laboratory, Oklahoma City, Oklahoma, was positive for the following:

"0.665 (ug/ml, ug/g) Citalopram detected in Blood

Citalopram detected in Liver

Desloratadine detected in Blood

Desloratadine detected in Urine

Ephedrine detected in Urine

Ephedrine NOT detected in Blood

Loratadine detected in Blood

0.368 (ug/mL, ug/g) N-Desmethylcitalopram detected in Blood

N-Desmethylcitalopram detected in Liver

Pseudoephedrine detected in Blood

Pseudoephedrine detected in Urine

Tamsulosin detected in Blood

Tamsulosin detected in Urine"