History of Flight
On October 18, 2008, about 1400 mountain daylight time, N151HT, a Heisler Lancair Legacy, collided with terrain shortly after takeoff from Parowan Airport, Parowan, Utah. The airplane was registered to a private company and operated under 14 CFR Part 91. The airline transport pilot was killed, and the passenger sustained serious injuries. The airplane was substantially damaged. Visual meteorological conditions prevailed, and no flight plan was filed for the personal flight to North Las Vegas Airport, Nevada, where the airplane was based.
Local law enforcement reported that the pilot owned a cabin in the Parowan area and rented a hangar at the airport. Witnesses driving northeast of the airport observed the airplane depart runway 04 and climb to an estimated 400 to 500 feet above ground level. Initially mistaking the airplane for a cropduster due to its low altitude, witnesses saw objects fall from the airplane as it entered a left turn. The airplane continued turning left, lost altitude, and impacted the ground left wing first, raising a cloud of dust. First responders located personal effects, including clothing, at the area where objects fell.
Personnel Information
The 59-year-old pilot held an airline transport certificate for single-engine airplanes and commercial certificates for multi-engine airplanes, rotorcraft, gliders, and lighter-than-air free balloon. He held a second-class medical certificate issued May 1, 2007, with a corrective lenses restriction. His last medical application reported 5,000 flight hours; a logbook review showed about 4,469 hours total, with 150 hours in the accident airplane.
Aircraft Information
The two-seat, low-wing, retractable-gear airplane, serial number L2K-267, received its airworthiness certificate in 2006. It was powered by a Teledyne Continental IO-550-C engine with an Aerocomposites propeller. The last condition inspection occurred June 11, 2008, at 69.6 hours total time; oil was changed September 25, 2008, at 89.6 hours.
Meteorological Information
At 1353, a METAR at Cedar City Regional Airport, 17 nautical miles southwest of the accident site, reported wind from 170 degrees at 10 knots gusting to 21 knots, visibility 10 statute miles, clear sky, temperature 73°F, dew point 19°F, altimeter 30.21 inHg. Initial responders indicated winds at Parowan were consistent with those conditions.
Wreckage and Impact Information
The debris field measured approximately 200 feet on flat, grassy terrain. The first identified point of impact contained green lens fragments. The main wreckage came to rest facing northeast. One propeller blade separated and was found in the debris field.
Medical and Pathological Information
The State of Utah Medical Examiner’s autopsy classified the pilot’s death as accidental due to blunt force injuries. The report noted other significant conditions: atherosclerotic coronary artery disease, cardiomegaly, and acute mixed drug intoxication. FAA toxicology tests were negative for carbon monoxide, cyanide, and volatiles, but positive for acetaminophen, diazepam, dihydrocodeine, doxazosin, hydrocodone, and nordiazepam in blood; dihydrocodeine, doxazosin, hydrocodone, hydromorphone, and nordiazepam in urine.
The pilot’s May 2007 medical application reported only allopurinol, atorvastatin, and aspirin; a precautionary coronary angiogram in 2006 showed no blockage per that application. However, records from the pilot’s cardiologist regarding the September 25, 2006 angiogram indicated a totally occluded small left anterior descending coronary artery with good collaterals, otherwise normal arteries. The cardiologist’s records also noted high blood pressure (for which the pilot was discharged from the Army), a ruptured disc, and medications including ramipril, dutasteride, propranolol, atorvastatin, fish oil, vitamins, and aspirin—none fully disclosed on the medical application. At autopsy, near-total stenosis of the proximal left anterior descending coronary artery with no acute thrombosis and mild right ventricular dilatation were noted; the pilot’s height was 182 cm, weight 112 kg.
Tests and Research
Wreckage examination revealed extensive impact damage. Both wings remained attached at the fuselage inboard edges; the empennage separated. Flight control surfaces and cables were traced; control continuity was confirmed. The aileron and elevator trim actuators were neutral; the rudder actuator showed slight left trim. The landing gear was retracted, the gear lever in the up position. The flaps were retracted. The canopy system was documented: the manually actuated lever and spring system had interlocking access stairs; latching pins were undamaged; forward hinges were twisted forward and left. The Lancair representative stated no cockpit indication confirms secure latching.
The engine was borescoped; thumb compression was obtained on all cylinders. Magnetos sparked at all leads except initially the left magneto’s number 2 cylinder lead, but after disassembly and reassembly, all leads sparked. The fuel manifold valve contained fuel consistent with 100 low lead. Spark plugs showed normal wear; cylinders 1, 3, 5 were oil-soaked; cylinders 2 and 6 had light carbon deposits; cylinder 4 had slightly more carbon. The propeller blades showed damage consistent with impact; blade 1 separated at the butt; blades 2 and 3 remained in the hub with leading edge marks and chordwise striations. No evidence of preimpact mechanical malfunction was found.