N68PK

HISTORY OF FLIGHT

On January 16, 2013, about 0556 eastern standard time, a Pilatus PC-12/45, N68PK, operated by LabCorp, Inc., as Skylab 53 (SKQ53), was substantially damaged when it impacted terrain shortly after takeoff from Burlington-Alamance Regional Airport (BUY), Burlington, North Carolina. The airline transport pilot was fatally injured. Instrument meteorological conditions prevailed and an instrument flight rules (IFR) flight plan had been filed for the flight destined for the Morristown Municipal Airport (MMU), Morristown, New Jersey. The corporate flight was transporting medical specimens and was conducted under the provisions of 14 Code of Federal Regulations Part 91.

Review of Federal Aviation Administration (FAA) air traffic control (ATC) audio data revealed that at 0541, the pilot contacted Greensboro (GSO) clearance delivery, while on the ground at BUY, and requested an IFR clearance to MMU. The pilot was advised that there was no flight plan stored in the ATC system. His original flight plan had a proposed departure time of 0315 and the flight plan was only good for 2 hours. The pilot subsequently requested to file an IFR flight plan and provided the routing details.

At 0550, GSO ATC provided an IFR clearance to SKQ53 from BUY to MMU, which included an initial altitude of 3,000 feet. ATC subsequently provided a transponder code of 2531, an altimeter setting of 30.01, an initial vector of a left turn to 360 degrees after takeoff, and a clearance void time of 0600, at 0551:30. The pilot acknowledged, read back the assigned transponder code as 2501, and stated that he would be airborne in about 30 seconds.

At 0554, the pilot advised GSO ATC that he was "climbing through thirty." The pilot was asked to "ident" and responded that he was turning to a heading of 360 degrees at 3,000 feet. The pilot was then directed to reset his transponder to code 2531, which he acknowledged with "531."

At 0555, ATC advised the pilot that his transponder indicated a code of 2501 at an altitude of 2,000 feet. The pilot did not respond and ATC made numerous attempts to contact SKQ53 without success. The airplane was not radar identified by ATC.

The airplane was subsequently found fragmented in an athletic field that was located about 5 miles northeast of BUY.

PERSONNEL INFORMATION

According to FAA and company records, the pilot, age 57, held an airline transport pilot and flight instructor certificates, with ratings for airplane single-engine land, airplane multiengine land, and instrument airplane. The pilot's most recent FAA second-class medical certificate was issued on November 19, 2012.

According to the pilot's most recent logbook entry, as of January 11, 2013, he had accumulated about 6,370 hours of total flight experience, which included about 315 hours in the same make and model as the accident airplane. He had also logged about 600 hours of flight experience in actual instrument meteorological conditions, and about 3,245 hours as night flight experience. In addition, he had accumulated about 45 hours in the same make and model as the accident airplane during the 90 days preceding the accident, which included about 25, and 20 hours logged in night and actual meteorological conditions; respectively.

According to the company chief pilot, the accident pilot had been flying the PC12 approximately 4 days per week since September 2012. His current schedule called for morning flights with "show times" at 0330. On the day prior to the accident, the pilot flew from BUY to Charleston, West Virginia (CRW). He took a nap at CRW before flying to Columbus, Ohio (OSU), and returned to BUY about 0940. His duty time ended at 1015, on January 15, 2013.

According to company records, in November 2012, the chief pilot arranged for an evaluation flight for the accident pilot in a Pilatus PC12. The chief pilot asked the instructor pilot conducting the evaluation flight to not allow the accident pilot to use the autopilot and preferred that the flight be conducted without flight director programming.

Following the evaluation flight, the flight instructor noted that the accident pilot seemed to get behind the airplane because of lack of trim usage. This was usually masked when using the autopilot, which would input the correct trim for the airplane and was magnified when only using, or not using at all, the flight director. The instructor pilot made some suggestions to the accident pilot that included engine power settings and trim verification, which markedly improved his handling of the airplane. The instructor pilot added that the last two-thirds of the evaluation flight were satisfactory to FAA standards for an instrument rating and commercial pilot single-engine land privileges.

AIRCRAFT INFORMATION

According to FAA records, the low wing, T-tail, retractable-gear airplane, serial number 265, was issued an airworthiness certificate on July 6, 1999. It was constructed primarily of aluminum and powered by a Pratt & Whitney Canada PT6A-67B, turboprop engine, with a takeoff power rating of 1,200 shaft horsepower that was equipped with a Hartzell four-bladed hydraulically actuated, constant-speed propeller assembly.

According to the airplane flight manual, the flight control system utilized push-pull rods and carbon steel cables and were equipped with electric trim systems. Each wing contained a single piece fowler-type flap that was electrically actuated. The airplane was also equipped with a stick shaker-pusher system to improve handling in the low speed flight regime by preventing the airplane from inadvertently entering a stall condition.

According to maintenance records, the airplane's most recent inspection was a "300-hour mini inspection" that was performed on January 14, 2013, at a total airframe time of 4,637 hours. A crack on the underside of the left flap was repaired on January 15, 2013. At the time of the accident, the airplane had been operated for about 4,650 total hours.

METEOROLOGICAL INFORMATION

The 0554 recorded weather observation at BUY included wind from 040 degrees at 4 knots, visibility 10 statute miles, broken cloud celling at 700 feet, overcast at 1,700 feet, temperature 4 degrees Celsius (C), dew point 3 degrees C; and an altimeter setting of 30.02 inches of mercury.

The 0700 Greensboro-High Point, North Carolina upper air sounding depicted a frontal inversion extending immediately about the surface to 3,533 feet agl. While the surface temperature was 4 degrees C, the freezing level was identified at 11,553 feet. No icing was indicated on the sounding due to the frontal inversion.

AERODROME INFORMATION

Burlington-Alamance Regional Airport was a non-tower-controlled airport with a common traffic advisory. It was equipped with single runway designated as runway 06/24. Runway 06/24 was constructed of asphalt, 6,405-feet-long, and 100-feet-wide. The field elevation for the airport was 616 feet above mean sea level (msl).

FLIGHT RECORDERS

The airplane was not equipped, nor was it required to be equipped with a cockpit voice recorder or flight data recorder.

WRECKAGE AND IMPACT INFORMATION

The elevation at the accident site was 531 feet msl and the majority of the wreckage was located strewn in a field. All major portions of the airplane, including all flight control surfaces and associated counterweights were located at the accident site. A debris path that was about 800 feet long, and 300 feet wide, was observed on a magnetic heading about 140 degrees. The right wing pitot tube was located about 10 feet from the initial impact point. Various sizes of wing spar segments were located in an impact crater. The crater was located on a berm, extended about 50 feet, and varied in depth to about 3 feet. The propeller hub, two propeller blades and the front reduction gear box were located in the crater. The third propeller blade was located about 200 feet along the debris path. The spinner was located in the vicinity of the third propeller blade. The fourth propeller blade and the propeller overspeed governor were located about 400 feet along the path. All four propeller blades exhibited S-bending damage.

The cabin area, just aft of frame 24 and forward of the aft pressure bulkhead, was located about 300 feet along the debris path. The right aileron and about one-third of the right flap were located with the cabin and with the nose landing gear. The empennage was located in the vicinity of the cabin. The horizontal and vertical stabilizers were impact damaged. The horizontal stabilizer came to rest inverted. The vertical stabilizer was fractured and came to rest on the horizontal stabilizer. The left wing was located on the right side of the debris path, about 350 feet from the initial impact point. Signatures on the bottom on the left wing, similar to fence impressions were noted. The cockpit was located about 350 feet from the initial impact point. Both cockpit seats and the throttle quadrant were located in the vicinity of the cockpit.

Flight control continuity was confirmed for the aileron, elevator, and rudder. Mechanical trim control continuity was confirmed for the horizontal stabilizer, aileron, and rudder trim systems. Measurement of the horizontal stabilizer trim actuator corresponded with a trim setting consistent in the takeoff range. Measurement of the aileron trim actuator corresponded with a neutral trim setting. The rudder trim actuator measured 1.125 inches, which was near the full right trim position of 1.18 inches. Examination of the inboard and outboard flap actuators corresponded to the retracted flap position. All 3 landing gear were in the up position.

The engine was located within the debris path. In the vicinity of the engine, there was evidence of a small postcrash fire. There was no soot staining or thermal damage observed on the wreckage that would have been consistent with an in-flight fire.

The engine sustained impact damage and was partially dissembled at the ac...