N110EB

HISTORY OF FLIGHTOn April 21, 2012, approximately 1220 eastern daylight time, a Cirrus Design Corp SR22, N110EB, registered to Photopheresis INC., of Morristown, New Jersey, was substantially damaged when it impacted heavily wooded terrain in the vicinity of Newcomerstown, Ohio. The private pilot, who was the sole occupant, sustained fatal injuries. Instrument meteorological conditions prevailed in the vicinity and an instrument flight rules (IFR) flight plan was filed. The flight was being operated under the provisions of 14 Code of Federal Regulations Part 91 as a personal cross country flight. The flight originated at 1013 from the Somerset Airport (SMQ), and its intended destination was Ohio State University Airport (OSU), Columbus, Ohio.

According to radar data and recorded radio communications provided to the NTSB by the FAA, approximately 5 minutes prior to the accident, the airplane was in cruise flight at 8,000 feet msl at 156 knots ground speed, when Indianapolis Air Route Traffic Control Center (ARTCC) updated the altimeter setting via radio. The pilot acknowledged the call and his voice sounded normal. No other radio transmissions or distress calls were from received from the pilot after the altimeter setting acknowledgment.

Radar data showed the airplane begin a descending right turn with airspeed increasing slightly through the turn and then suddenly decreasing to 61 knots as the radius of the turn decreased. The airplane had turned approximately 270 degrees of heading and descended to an altitude of 4,900 feet msl before radar contact was lost.

There were no eye-witnesses to the accident, however, a boy who was a passenger of a car reported that he thought that he saw the airplane coming out of the low clouds in a descent, about wings level before it disappeared out of sight behind a tree line. The boy stated that he then saw black smoke.

Recovered data from the on-board data module (RDM) showed an anomaly in the electrical bus voltages, autopilot mode changes, a momentary drop out of the pilot transmit frequency, and a descending right turn with a decreasing radius until impact. Detailed information is provided in the TESTS AND RESEARCH section of this report.

PERSONNEL INFORMATION

According to FAA records, the pilot held a valid private pilot certificate with Airplane Single Engine Land (ASEL) and Instrument Airplane ratings. He held a valid third class medical certificate, issued April 28, 2010. At the time of his most recent medical exam, the pilot reported about 1,200 hours total flight time, of which 100 hours were within the preceding 6 months. The pilot attended and completed the Cirrus Standard Perspective Differences and Cirrus Turbo Differences Course on April 14, 2009. Additionally, he completed the Cirrus Icing Awareness Course on October 5, 2009.

According to information provided by a flight instructor who had flown about once a month with the pilot in recent years, the pilot completed a successful bi-annual flight review in the SR22 on February 17, 2012.

Remnants of the pilot's logbook were found at the accident site, but the contents were damaged from impact and could not be documented.

AIRCRAFT INFORMATION

Cirrus SR22-3423, registration number, N110EB, received its standard airworthiness certificate on April 13, 2009. Cirrus records indicate that the pilot purchased the airplane new and took delivery on April 13, 2009. According to the records on file at Cirrus Aircraft, the airplane was equipped with: Garmin Perspective avionics with dual AHRRS and a single air data computer, Chartview, a GFC 700 autopilot with yaw dampener, Enhanced Vision System (EVS), Synthetic Vision, air conditioning, a Tornado Alley turbo-charging system, supplemental oxygen, engine monitoring, traffic alerting system, terrain awareness system (TAWS-B), XM weather/radio, FIKI, a Tanis heater, and a recoverable data module (RDM).

The cover for the airframe, engine, and propeller logbooks were found at the accident site, but the pages were not located.

The airplane was equipped with a two-alternator, two battery, 28-volt direct current (VDC) electrical system designed to reduce the risk of electrical system faults. The system provides uninterrupted power for avionics, flight instrumentation, lighting and other electrically operated and controlled systems during normal operation. The electrical system also provides automatic switching from either battery or alternator to the Essential Bus in the event of an electrical system failure by the opposing alternator or battery.

The bolster panel contains the pilot switches for operating ALT 1, ALT 2, BAT 1, and BAT 2. The switches are mounted adjoining so that a pilot can control all four switches with a single hand. Power generated from the alternators is fed into the Master Control Unit (MCU). The MCU regulates and distributes the power to the batteries and the system loads. Each alternator provides constant charging current for the corresponding battery and primary power to the aircraft electrical system during normal system operation.

The flight instructor who had given the pilot his most recent bi-annual flight review reported that there had been one instance whereby the autopilot had disengaged during a flight sometime in the fall of 2011. He recalled that the problem may have been associated with a battery issue, but could not recall all of the details.

METEOROLOGICAL INFORMATION

The closest weather reporting location to the accident site was from Zanesville Municipal Airport (ZZV), Zanesville, Ohio, located approximately 24 miles southwest of the accident site at an elevation of 900 feet. The airport had an un-augmented ASOS and reported the following conditions at the approximate time of the accident: Zanesville (ZZV) special weather observation at 1222 EDT, automated, wind from 340º at 5 knots, visibility 7 miles in light rain, ceiling broken at 800 feet agl, overcast at 1,200 feet, temperature 6º C, dew point 4º C, altimeter 29.89 inches of Hg. Remarks - automated observation system, ceiling 600 variable 1,000 feet, hourly precipitation 0.01 inch.

The pilot of N110EB contacted the Washington, DC, Federal Aviation Administration (FAA) contract Automated Flight Service Station (AFSS) at 0745 EDT (1145Z) on April 21, 2012 and obtained a weather briefing and filed an IFR flight plan. A copy of the event reconstruction for that briefing was obtained and is included as Attachment 1 in the NTSB Meteorology Group Chairman's Factual Report. An audio file was also reviewed and documented to evaluate the accuracy and content of that briefing, which follows: The pilot initially contacted the AFSS for an outlook briefing for the flight departing at 0800 EDT on April 22, 2012.

A complete meteorological factual report prepared by a NTSB meteorology specialist is available in the supporting docket for this report.

FLIGHT RECORDERS

The Recoverable Data Module (RDM) was located in the debris field and sent to the NTSB Vehicle Recorder Laboratory in Washington DC for evaluation and download.

WRECKAGE AND IMPACT INFORMATION

General

The airplane's main wreckage was located on a heavily wooded hillside at 40°14'58.32" North latitude, 81°32'44.95" West longitude at an approximate elevation of 1,060 feet msl. The direction of energy was about 093 degrees magnetic. The hillside had a 10-degree up slope. The initial point of impact consisted of two trees about 31 feet apart. One tree had missing bark and tree scars on one of its large branches approximately 44 feet above the ground. The second tree's trunk was broke off approximately 34 feet above the ground. Three more tree trunks in the direction of energy ranging in size from 4-8 inches were freshly broken off.

About 80 feet from the initial point of impact there was a 3-4 foot deep crater that measured approximately 11 feet long. Within the crater, the propeller hub remained attached to a portion of the crankshaft, which still had the #6 cylinder attached to it by the piston and connecting rod. There were two trees at the far end of the crater. The main wreckage including the firewall, engine, instrument panel, and center console, was found leaning uphill against the trees.

The remainder of the airplane was severely fragmented and dispersed over a debris field that measured roughly 370 feet long by about 250 feet wide at its widest point. Evidence of spot fires were present throughout the debris field. Brown wilted vegetation was present that was consistent with fuel damage. Evidence at the site was consistent with the airplane impacting the trees about 25-30 degrees nose down and level wings.

Engine

The main portion of the engine was located approximately four feet from the impact crater and exhibited impact damage. The forward portion of the crankshaft and propeller hub, and the number six cylinder were located in the impact crater and was embedded the ground. Fractured pieces of the engine crankcase and oil sump were located in the impact crater along with a turbocharger, forward section of the cam shaft, parts of the propeller governor,and magneto drive gears. The engine and all components and accessories exhibited impact damage. The right magneto was separated from the engine, exhibited impact damage and the housing was fractured. The magneto was disassembled with no pre-impact anomalies noted. The left magneto was separated from the engine, exhibited impact damage and the housing was fractured exposing the internal parts of the magneto. The magneto was disassembled with no pre-impact anomalies noted. The ignition harness exhibited impact damage. The spark plugs exhibited impact damage and had light colored combustion deposits. The electrodes were normal when compared to the Champion Check A Plug chart. The fuel pump was fractured free of the engine and located in the debris field. The fuel pump exhibited impact damage. The drive coupling was fractured and only half of it was located. T...