History of Flight
On January 11, 2015, at 1246 mountain standard time, a Piper PA-28RT-201T single-engine airplane, registration N82828, impacted terrain while maneuvering near Brighton, Colorado. The airline transport pilot was fatally injured, and the airplane was destroyed. The airplane was registered to and operated by a private individual under 14 Code of Federal Regulations Part 91 as a personal flight. Day visual meteorological conditions prevailed, and no flight plan was filed. The flight departed from Van Aire Airport (CO12), Brighton, Colorado, about 1220.
According to witnesses who spoke with local authorities, the pilot taxied the airplane from inside his hangar and departed CO12. A witness described this as unusual because the pilot would typically tug the airplane out of the hangar and then start the engine. For several minutes, witnesses observed the airplane at a low altitude and maneuvering at high airspeeds. Witnesses last observed the airplane make a steep bank turn, descend, and impact terrain approximately 5 miles east of Van Aire Airport.
Local law enforcement, who spoke with the pilot's wife, had been advised that she believed he committed suicide. Recently, the pilot's wife had informed him that she wanted a divorce and was purchasing a home nearby. She stated that approximately five years ago, the pilot told her that if she ever left him, he would fly his airplane into the ground and kill himself.
Personnel Information
The pilot, age 41, held an airline transport pilot certificate, a commercial pilot certificate with an airplane single-engine land rating, and a flight instructor certificate with airplane single-engine, multi-engine, and instrument ratings. His most recent FAA first-class medical certificate was issued on November 20, 2014, with no limitations or restrictions. According to his most recent airman medical certificate application, the pilot had accumulated 10,600 total flight hours and 200 flight hours in the previous six months. His logbooks were not located during the investigation.
Aircraft Information
The four-seat, low-wing, retractable tricycle-gear airplane, serial number 28R-8131015, was manufactured in 1980. It was powered by a Continental Motors TSIO-360-FB1B, 200-horsepower engine, equipped with a Hartzell constant-speed propeller. The airplane was registered to the pilot on September 2, 2008. A review of the airplane logbooks revealed the most recent annual inspection was completed on September 6, 2014. At that time, the airframe and engine had accumulated 4,105.9 total hours, and the engine had accumulated 88.3 hours since major overhaul.
Meteorological Information
At 1253, the Denver International Airport automated surface observing system, located about 11 miles southwest of the accident site, reported wind from 360 degrees at 9 knots, 10 miles visibility, few clouds at 5,000 feet, ceiling overcast at 11,000 feet, temperature 4°C, dew point 1°C, and an altimeter setting of 30.00 inches of mercury.
Wreckage and Impact Information
The airplane wreckage came to rest in a dormant wheat field, and debris was distributed for approximately 200 feet along a bearing of 308 degrees. The initial impact point, consistent with the left wing, was a continuous ground scar that extended 24 feet to a ground crater measuring 2.5 feet deep. The propeller assembly, engine, and a portion of the forward fuselage were located within the crater. The wings, fuselage cabin, and empennage were fragmented and located within the debris field. All major components were accounted for at the accident site.
The cockpit and instrumentation were fragmented and destroyed. All four seats and seat assemblies were separated from their attach points. The left wing and fuel tank were fragmented; the left aileron and flap remained partially attached. The right wing and fuel tank were fragmented; the right aileron and flap remained partially attached. Both main landing gear assemblies were found in the retracted position.
Partial control cable continuity was established due to fragmentation. The aileron cables remained attached to the chain assembly, and the chain was separated in several sections. The fractured aileron cable ends were broomstrawed, consistent with overload failure. Both aileron bellcranks were separated and pulled from their attach points. The aileron cables were attached to their bellcranks and separated at the wing root. The rudder cables were attached to their cockpit attach points; the cables were fractured and broomstrawed, consistent with overload failure. The rudder cable assembly was detached from the rudder pulley. The horizontal stabilator cables were separated from the lower T-bar and were attached to the aft turnbuckle.
The engine sustained significant impact damage and remained partially attached to the firewall. The spark plugs were impact damaged and exhibited normal color and wear. Due to damage, the crankshaft was partially rotated by hand tool, and mechanical continuity was noted throughout. The crankshaft was fractured at the propeller flange; the fracture surface displayed 45-degree shear lips consistent with overload failure.
The propeller assembly remained attached to the fractured crankshaft flange. One propeller blade was bent aft, tip curled, and had chordwise blade polishing. One blade displayed s-type bending and chordwise blade polishing.
Medical and Pathological Information
An autopsy performed by the Office of the Coroner for Adams and Broomfield Counties, Colorado, listed the cause of death as "multiple blunt trauma injuries to the body due to airplane crash." The manner of death was determined to be suicide. The FAA's Bioaeronautical Sciences Research Laboratory performed toxicological testing, which was negative for all screened drugs and alcohol.