ERA10FA027

The pilot’s failure to remain clear of rising terrain while maneuvering at low altitude.

Shortly after takeoff, on a training flight to conduct terrain following maneuvers at low altitude and maximum gross weight, the airplane collided with trees on a mountain side. The airplane impacted at 3,761 feet above mean sea level on a 6,285-foot mountain peak. Although the airplane was nearly consumed by a post-crash fire, a postaccident examination of the engine and airframe found no mechanical anomalies that would have prevented the normal operation of the airplane. There were no witnesses to the accident.

HISTORY OF FLIGHT On October 22, 2009, at 1350 eastern daylight time, a Cessna U206G, N120MS, registered to Focus Aviation, collided with trees while conducting terrain following maneuvers at low altitude, in the Roan Mountains, in Elizabethton, Tennessee. The two pilots on board the airplane, a certificated commercial pilot who was receiving missionary flight training, and a certificated airline transport pilot with a flight instructor certificate (CFI) were killed. The airplane was destroyed by impact forces and post crash fire. The flight was operated as an instructional flight under the provisions of 14 Code of Federal Regulations (CFR) Part 91, and a visual flight rules (VFR) flight plan was filed from Elizabethton Municipal Airport (0A9), Elizabethton, Tennessee, to Avery County/Morrison Field (7A8), Spruce Pine, North Carolina. Visual meteorological conditions prevailed at the time of the accident. The flight originated from 0A9 at 1330. There were no witnesses to the accident. According to the airport manager, the pilots were conducting a low level (1,000 feet above ground level (AGL)) VFR flight from 0A9 to 7A8, which was about 27 nautical miles (NM) south of 0A9. The CFI was a missionary flight instructor and this was his 10th instructional flight with the commercial rated student pilot. According to the airplane's owner, the number 5 and number 6 seats were removed from the airplane and replaced with ratchet straps which secured ballast bags to simulate a fully loaded airplane. The airplane was also modified with a two axis autopilot, anti-icing system, and Flint Aero wing tip fuel tanks which increased the airplane's gross weight to 3,800 pounds. The airport manager stated that the airplane had an oil change and was topped off with 19 gallons of AVGAS in the left main fuel tank the day prior to the accident flight. According to the student pilot's wife, "He was starting his low level and heavy airplane training... this was his first low/heavy flight." She also stated that her husband complained that the airplane was running hot and that maintenance was performed on the airplane the morning of the flight, which delayed the accident flight until the afternoon. The on-field maintenance facility was not aware of any maintenance the airplane received the morning of the flight. However, both pilots were Airframe and Power Plant (A&P) mechanics. A witness that observed what he described as a short or soft field style take-off stated, "All aspects of the departure appeared normal, and sounded normal." A local resident located near the accident site said the plane flew by at "tree top level" and it was so loud she instinctively ducked. FAA Flight Service contacted the airport manager to notify him the airplane was overdue. The airport manager told flight service he was already aware of the accident. The ELT did not assist with locating the wreckage. No radar data was identified that pertained to the accident. PERSONNEL INFORMATION The CFI, age 70, held an FAA Airline Transport Pilot certificate for airplane single and multi-engine land, issued on April 13, 1964, and a flight instructor certificate, last updated on June 11, 2009. The CFI's most recent second class medical certificate was issued on June 5, 2008; with a restriction the he must wear corrective lenses. The pilot's personal logbook was observed in the wreckage; however, it was burned and yielded little useful information. On the CFI's most recent medical certificate he reported his total civilian flight hours as 21,148. The student pilot, age 38, held an FAA Commercial Pilot certificate, for airplane single-engine land and instrument airplane, issued on July 15, 2008, and a second class medical certificate issued September 10, 2009, with a limitation that he must wear corrective lenses. The pilot's logbook was not recovered for examination. On the pilot's most recent medical certificate he reported his total civilian flight hours as 412. AIRCRAFT INFORMATION The 6-seat, high-wing, fixed gear airplane, serial number (S/N) U20603668, was manufactured in 1977. It was powered by a Continental IO-520 F(21), 285-hp engine and equipped with a McCauley Model D3A4C401 aluminum, variable pitch propeller. A review of the airplane's logbook revealed that the most recent 100-hour inspection was completed on March 13, 2009, at an airframe total time of 6,327.1 hours, and an engine total time of 1,346.9 hours at the time of the inspection. METEOROLOGICAL INFORMATION A review of recorded data from the 0A9 automated weather observation station, at elevation 1,600 feet, revealed the following conditions at 1355: winds from 220 degrees at 5 knots, visibility 10 statute miles, cloud condition clear, temperature 20 degrees Celsius, dew point 7 degrees Celsius, and altimeter 30.09 inches of mercury. WRECKAGE AND IMPACT INFORMATION The aircraft contacted trees and rising terrain along a level flight path at an elevation of 3,761 feet mean sea level (MSL), and a 265 degree heading, approximately 13 nautical miles south of 0A9, at Roan High Knob Peak, which was the highest point on Roan Mountain, rising to 6,285 feet msl. The majority of the fuselage, right wing, inboard portion of the left wing, the empennage, and the tailcone were consumed by the post-crash fire. The initial impact with tree tops was approximately 100 yards from where the main wreckage came to rest inverted. The fuselage came to rest on a 050 degree heading. Examination of the cockpit found the instrument panel and flight controls fire damaged. The fuel selector was in the left tank position; the majority of the fuel lines were consumed by fire. The auxiliary fuel pump and fuel strainer bowl were fire damaged; the fuel strainer screen was not observed. The fuel tanks were mostly consumed by fire. One of the four fuel tank finger screens was observed and was encrusted with re-solidified aluminum. The fuel header tanks were consumed by fire. The engine-driven fuel pump screen, fuel control unit screen, and fuel distribution valve screen was free of debris. The fuselage came to rest on its left side inverted and was mostly consumed by fire. The left wing, inboard of the main fuel tank, was partially consumed by fire. The right wing was partially consumed by fire. Airplane flight control cable continuity was confirmed between the aerodynamic surfaces and the cockpit controls through overload separations located in the wing roots. The flap actuator measurement corresponded to a flap setting of 0 degrees. The empennage was fire damaged, but the horizontal and vertical stabilizers remained attached. The elevator trim tab actuator measurement corresponded to a 15 degree tab up setting. The leading edges of the wings, horizontals, vertical and propeller were equipped with an ice protection system. The icing fluid container was located in the tailcone. Examination of the airframe did not reveal any anomalies that would have prevented normal operation. The engine came to rest near the firewall within the cowling, but did not remain attached to the engine mounts. The engine was examined in a hangar at 0A9 on October 24, 2009. The engine was intact with all of the accessories attached. Heat discoloration and fire damage were observed in all areas of the engine. The throttle control was attached and in the 3/4 open position. The mixture control was attached and in the mid range position. The propeller governor control was attached and in the aft position. The rocker covers and the top spark plugs were removed along with the oil pump cover. The cylinders were borescoped. Normal deposits were observed on the piston heads and the cylinder cones. All of the valves were in place. The crankshaft was rotated using the propeller, and continuity was confirmed to all of the accessories at the real of the engine and to the oil pump. Thumb compression was confirmed on all of the cylinders. The fuel meterin