N8372Y

HISTORY OF FLIGHTOn December 26, 2013, about 0530 eastern standard time, a Piper PA-30, N8372Y, was destroyed following an inflight break up, and impact with terrain near Biglerville, Pennsylvania. Night visual meteorological conditions prevailed and no flight plan was filed for the flight. The certificated private pilot and passenger were fatally injured. The personal flight was conducted under the provisions of Title 14 Code of Federal Regulations Part 91. The flight originated from Bloomsburg Municipal Airport (N13), Bloomsburg, Pennsylvania, around 0445, with an intended destination of Summerville Airport (DYB), Summerville, South Carolina.

According to witnesses, the airplane was flying "low" and the engine noise was "loud." One witness reported that he heard the engine "miss" once, then the engine "revved up," and a few seconds later he heard the sound of impact. Another witness stated that when he heard the engine "spike."Radar tracking data that was obtained from the Federal Aviation Administration (FAA) Harrisburg Approach Control Radar facility located in Harrisburg, Pennsylvania. The radar data indicated that, the airplane was flying on a southwesterly heading at an altitude around 10,000 feet mean sea level (msl). Then around 0525, the airplane descended to 7,400 feet msl. At 0527 the airplane entered a left turn and descended. A few seconds later the radar target completed a 180 degree turn and the data indicated a 2,000 foot per minute descent and a 7.5 degrees per second turn rate. The last radar data, located in/near the accident location indicated that the airplanewas at 2,700 feet msl and a recorded ground speed of 179 knots. PERSONNEL INFORMATIONAccording to FAA records, the pilot held a private pilot certificate with ratings for airplane single-engine land and multiengine land, and a third-class medical certificate issued on October 31, 2013, which included a restriction of "must wear corrective lenses for near and distant vision."

The pilot's logbook was recovered from the accident site and it listed a total of 196.1 hours of flight time. It also indicated that the pilot recorded a total of 12.3 hours of flight time at night, 1.2 hours of flight in actual instrument conditions, and 3.8 hours of flight time in simulated instrument conditions. In addition, there were 4.5 hours of flight time is the past 12 months, of which 4 hours occurred between December 20, 2013, and December 25, 2013. AIRCRAFT INFORMATIONAccording to FAA records, the airplane was issued an airworthiness certificate in 1967 and was registered to the pilot on June 18, 2012. It was equipped with two Lycoming IO-320-series, 160- horsepower engines. It was also equipped with two 2-bladed Hartzell controllable pitch propellers. At the time of this writing, the maintenance logbooks had not been located. However, a receipt for maintenance performed on the airplane included an annual inspection that was dated November 18, 2014. METEOROLOGICAL INFORMATIONAn observation site from a National Weather Service source for Fountain Dale (RYT), Hamiltonban, Pennsylvania, located approximately 15 miles southwest of the accident site, at the time of the accident, showed rapidly changing conditions during the period with a band of snow moving across the region.

The RYT weather observation at 0453 indicated wind from 220 degrees at 3 knots, visibility 10 miles, ceiling overcast clouds at 7,000 feet above ground level (agl), temperature minus 4 degrees C, dew point minus 8 degrees C, and an altimeter setting 30.22 inches of mercury.

The RYT weather observation at 0553 indicated wind calm, visibility 10 miles, ceiling overcast at 3,200 feet agl, temperature minus4 degrees C, dew point minus 9 degrees C, and an altimeter setting of 30.21 inches of mercury.

The RYT weather observation at 0608 indicated calm wind, visibility 3 miles in light snow, ceiling broken at 2,800 feet, overcast at 7,000 feet, temperature minus 4 degrees C, dew point minus 8 degrees C, and an altimeter setting of 30.20 inches of mercury. In addition, the remarks section stated that snow began at 0556.

According to the Astronomical Applications Department at the United States Naval Observatory, the official moonset was at 1224, the official beginning of civil twilight was at 0659, and official sunrise was at 0729. The phase of the moon on the day of the accident was waning crescent, with 38 percent of the moon's visible disk illuminated.

A search of Flight Service Station records revealed that the pilot requested weather information and Notice to Airman (NOTAMs) on the day of the accident for Williamsport Regional Airport (IPT), Williamsport, Pennsylvania, and Farmville Regional Airport (FVX), Farmville, Virginia. The pilot did not file a flight plan and did not receive any other services for the accident flight.

The weather reported at IPT, which was approximately 27 miles northwest of the departure airport, around the departure time, indicated wind from 090 at 8 knots, visibility 1 ¾ statute mile, light snow, clouds overcast at 2,600 feet agl, temperature minus 4 degrees C, dewpoint minus 7 degrees C. AIRPORT INFORMATIONAccording to FAA records, the airplane was issued an airworthiness certificate in 1967 and was registered to the pilot on June 18, 2012. It was equipped with two Lycoming IO-320-series, 160- horsepower engines. It was also equipped with two 2-bladed Hartzell controllable pitch propellers. At the time of this writing, the maintenance logbooks had not been located. However, a receipt for maintenance performed on the airplane included an annual inspection that was dated November 18, 2014. WRECKAGE AND IMPACT INFORMATIONThe airplane impacted the ground and came to rest inverted. The wreckage path was oriented on a 179 degree heading and the debris path began about 2,350 feet prior to where the main wreckage came to rest. The main wreckage was oriented on about a 180 degree heading. Several pieces of airframe skin were located in the field leading up to the main wreckage. The first piece of airframe skin was located approximately 2,350 feet prior to the main wreckage. First responders reported an odor similar to 100LL in the field where the main wreckage was located.

The nose landing gear was located in the vicinity of and was separated from, the main wreckage.

The left and right engines were separated from the main wreckage, embedded in the field, and located approximately 10 feet from the main wreckage. When they were removed from the ground, fuel and oil were present in the craters.

One propeller blade was located in the field approximately 400 feet from the main wreckage and its associated propeller hub was located in the field approximately 500 feet from the main wreckage . The other propeller blade was not located. The second propeller was located about 50 feet aft of the main wreckage. Both blades remained attached to the propeller hub and flange. Both spinners were separated from the engines and located in the field along the debris path.

The outboard 6 foot of the right wing was located along the debris path about 600 feet from the main wreckage in the field. The inboard approximate 10 feet remained attached to the fuselage and exhibited crush damage. The right wing tip, was separated and located approximately 50 feet from the outboard section of the right wing. The right aileron remained attached to the right outboard section of the wing through one attach point. The right flap remained attached to the right wing through all attach points. The right wing fuel cap remained intact and seated, however that section was separated from the right wing. The right main landing gear remained attached to the right wing in the retracted position.

The aft section of the fuselage was separated at the aft pressure bulkhead. The rudder, vertical stabilizer, and inboard section of the left stabilator was located about 200 feet from the main wreckage. The right section of the stabilator was located approximately 675 feet from the main wreckage in an area of trees. The forward section of the left stabilator remained attached to the empennage. The main spar of the stabilator remained attached to the aft bulkhead. The rudder remained attached to the vertical stabilizer through all attach points and exhibited impact damage.

The outboard approximate 6 foot of the left wing was found separated from the fuselage and located in a field about 600 feet from the main wreckage. The left aileron was located in the field approximately 200 feet from the left outboard section of the wing. The inboard approximate 10 feet of the left wing remained attached to the fuselage and exhibited crush and impact damage. The forward section of the left wing was separated from the left wing spar and located approximately 10 feet forward of the main spar. The left inboard section of the flap remained attached to the inboard section of the wing through the outboard attach point. Aileron control cable continuity was confirmed from the base of the control column to the associated fracture points out to the aileron attach point. The aileron cable exhibited tensile overload at all fracture points. The main landing gear remained in the up and in the retracted position.

The cockpit exhibited extensive crush damage and was separated from the fuselage. The engine controls were intact. The throttle levers and propeller levers were in the midrange position. Flight control continuity was confirmed from the cockpit to all flight control surfaces through the respective tensile overload breaks. The air driven attitude indicator was disassembled and the gyro and gyro housing exhibited rotational scoring, consistent with operating at the time of impact. The electric turn and bank indicator was disassembled and the internal gyro and housing exhibited rotational scoring, consistent with operating at the time of impact.

The fuselage came to rest inverted in a corn field and it exhibited extensive impact...