N421KL

HISTORY OF FLIGHT

On March 4, 2017, about 0023 eastern standard time, a Cessna 421B, N421KL, was substantially damaged during an attempted go-around and subsequent collision with terrain at Cherokee County Airport (CNI), Canton, Georgia. The commercial pilot was fatally injured. The airplane was registered to and was being operated by the pilot under the provisions of Title 14 Code of Federal Regulations Part 91. Night visual meteorological conditions prevailed, and no flight plan was filed for the personal cross-country flight. The flight originated about 1930 on March 3, 2017, from Richard Lloyd Jones Jr Airport (RVS), Tulsa, Oklahoma, and was destined for CNI.

According to personnel at an aviation brokerage company in Oklahoma, the pilot purchased the airplane on March 2, 2017. A flight instructor reported that he and the pilot flew the airplane on March 1, 2017, for 1.5 hours to go over the various systems of the Cessna 421B. On March 2, 2017, the flight instructor flew with the pilot again for 45 minutes conducting pattern work. The flight instructor said that the pilot told him that he had previously owned two Cessna 421Cs, was a little "rusty," and had not flown that type of airplane since 1984. The instructor reported that, overall, the pilot was knowledgeable of the operation of airplane. He also reported that the pilot departed with enough fuel for the cross-country flight. A review of the pilot's logbook revealed that the flight instructor signed off a flight review on March 3, 2017.

Radar and audio data obtained from the Federal Aviation Administration (FAA) revealed that the pilot was in contact with air traffic control and receiving visual flight rules (VFR) flight following services while inbound to CNI. The pilot cancelled flight following when he had the airport in sight. Radar data continued to show the airplane on approach to CNI until 2,500 ft when the airplane descended below radar coverage.

A review of airport video surveillance footage revealed that the runway lights were illuminated during the airplane's approach to runway 05. The airplane's landing lights became visible as the airplane neared the runway. On short final, the airplane pitched up and rolled to the right. The airplane then descended in a nose-down attitude into a ravine on the right side of the runway. The video footage stopped for a second, and then a fire was seen in the ravine.

Witnesses observed the airplane flying extremely low before noticing a "ball of fire" erupt near the airport.

PERSONNEL INFORMATION

The 69-year-old pilot held a commercial pilot certificate with ratings for airplane single-engine land and instrument airplane. On his most recent FAA second-class medical certificate application, dated April 13, 2016, he reported a total flight experience of 4,000 hours with no hours flown during the last 6 months. The medical certificate indicated a limitation for glasses for near vision. A review of the pilot's current logbook, which was labeled logbook No. 3, revealed a total of 11.9 hours of flight experience since January 16, 2017.

AIRCRAFT INFORMATION

The multi-engine airplane was manufactured in 1970, and it was powered by two Continental GTSIO-520-series engines driving Hartzell PHC-C3YD-2UF controllable-pitch propellers. The most recent annual inspection was completed on March 1, 2017, at a recording hour meter time of 2,048.4 hours. The right engine was a GTSIO-520-D21CH engine, serial number 219483-R; it had a total time of 2,048.4 hours and a time since overhaul of 38.2 hours at the last inspection. The left engine was a GTSIO-520-H engine, serial number 218284-R; it had a total time of 2,048.4 hours and a time since overhaul of 430.9 hours.

METEOROLOGICAL INFORMATION

At 0010, the recorded weather at CNI included calm wind, 10 miles visibility, and clear skies. The temperature was 5°C; the dew point was -15°C; and the altimeter setting was 30.54 inches of mercury.

WRECKAGE AND IMPACT INFORMATION

Examination of the accident site revealed that the airplane contacted a wire about 380 ft to the right of the runway and parallel the runway. The airplane came to rest in a retention pond about 420 ft on the right of the runway centerline and runway threshold. The nose of the airplane was crushed aft, and the wind screen on the left side was broken away from the fuselage. Examination of the cockpit revealed that the instrument panel was crushed toward the left side of the fuselage. The flap control was in the fully extended position. The left engine throttle control was full forward, and the right engine throttle control was at the halfway mark. The left mixture control was full rich, and the right mixture control was at the halfway mark. The left propeller control was at the halfway mark, and the right propeller control was full forward. The left fuel selector handle was in the left main tank position, and the right fuel selector handle was in the right main tank position. Examination of the flight controls revealed continuity from the cockpit to all the flight control surfaces.

The left wing from the engine nacelle outboard exhibited postimpact fire damage. Fire damage exposed the main fuel tank attachment and baffle, which were intact. The left engine nacelle also showed signs of fire damage. The wing flaps were observed in the extended position.

Examination of the right wing revealed that it remained intact with very little postimpact fire damage, which was confined to the area around the engine nacelle. Fuel was observed in the right main fuel tank, the right-wing auxiliary tank, and the right nacelle locker tank; about 25 gallons of fuel were drained from the tanks. The right main fuel tank exhibited striations and flattening to the upper surface of the tank, which were consistent with a contact with a wire. Leading edge damage to the right wing was observed, which was consistent with contact with a wire. A power wire was observed wrapped around the right main landing gear. The wing flaps were observed in the extended position. Examination of the empennage revealed that the vertical stabilizer, horizontal stabilizer, rudder, and elevators remained attached. Both horizontal stabilizers were buckled.

All three landing gear were broken away from the airplane at the struts. The landing gear trunnions were observed in the down positions. The landing gear handle in the cockpit was observed in the down position.

Examination of the left engine revealed that it remained partially attached to the airframe by two engine mounts, hoses, wires, and cables. The engine displayed impact damage as well as some thermal damage to the rear of the engine. The crankcase remained intact and displayed impact damage. All the cylinders remained attached to their cylinder bays and displayed varying amounts of impact damage. The internal portions of the cylinders were inspected using a lighted borescope. The piston faces, valve heads, and cylinder bores did not display any anomalies. The crankshaft was rotated, and all six cylinders had thumb compression and suction. The overhead components (valves, springs, and rocker arms) were examined and did not display any anomalies. The external components of the engine (fuel pump, throttle, metering unit, and both magnetos) remained attached and displayed thermal damage. The ignition harness remained attached to both magnetos and displayed impact damage to the No. 2 and the No. 6 bottom ignition leads. All the spark plugs remained secured in their cylinders. The spark plugs were removed, and it was noted that all the electrodes displayed normal operating signatures when compared to Champion Aviation Service Manual AV6-R. The magnetos were removed, and both magneto drive shafts were rotated using an electric drill. The spark plugs were installed onto the ignition harness, and it was noted that all the spark plugs sparked between the ground and center electrodes.

The left turbocharger remained attached to the airframe and displayed minor impact damage. The wastegate remained attached to its installation point and was undamaged. The compressor and the turbine were undamaged and did not display any anomalies. The exhaust system displayed impact damage, and no signs of exhaust leaks were noted.

Examination of the right engine revealed that it remained partially attached to the airframe and displayed impact and thermal damage. All six cylinders remained attached to their cylinder bays and displayed varying amounts of impact damage. The internal portions of the cylinders were inspected using a lighted borescope; the cylinder bores, piston faces, and valve heads displayed normal operating and combustion signatures. The crankshaft was rotated, and all six cylinders had good thumb compression and suction. The overhead components (valves, springs, and rocker arms) were examined and did not display any anomalies. The external components of the engine (fuel pump, throttle, metering unit, and both magnetos) remained attached and displayed impact and thermal damage. The ignition harness displayed impact damage signatures to the No. 6 bottom ignition lead, which was partially severed. The magnetos were removed, and both magneto drive shafts were rotated using an electric drill. The magnetos produced spark on all six posts individually. The spark plugs were removed and visually inspected. All the spark plugs displayed normal operating and wear signatures when compared to Champion Aviation Service Manual AV6-R. The spark plugs were installed onto the ignition harness, and it was noted that all the spark plugs sparked between the ground and center electrodes.

The right turbocharger remained attached to the airframe and displayed minor impact damage. The wastegate remained attached to its installation point and was undamaged. The compressor and the turbine were undamaged and did not display any anomalies. Rotation and continuity were established between the two sections of the turbine and com...