Cessna 560 Destroyed in Atlanta, Georgia, on December 20, 2018 (N188CW)

Accident Overview and Flight Sequence On December 20, 2018, about 1210 eastern standard time, a Cessna 560, N188CW, was destroyed when it was involved in an accident in Atlanta, Georgia. The airline transport pilot and three passengers were fatally injured. The airplane was operated as a Title 14 Code of Federal Regulations Part 91 personal flight. Air traffic control data showed that the local ground controller cleared the pilot for takeoff from runway 8 at Fulton County Airport Brown Field (FTY) and instructed him to turn left to a heading of 310°. A cockpit voice recorder (CVR) recorded increased engine sound and the pilot stating “airspeed alive.” Radar data from the Federal Aviation Administration (FAA) indicated that the airplane departed from runway 8 while climbing about 3,500 ft per minute. The airplane then began a left turn toward the north, climbing to about 3,250 ft msl (2,410 ft agl), reaching a maximum rate of climb of about 9,600 ft per minute and decelerating to about 75 knots. Thirty-four seconds after the engine sound increased, the CVR recorded the engine sound decreasing. Two “beeps” sounded within 9 seconds of each other after the engine sound decreased, and 3 seconds after the second beep, a sound similar to the stick shaker was heard. A grunt and heavy breathing followed, along with the stick shaker and another beep. An electronic voice then announced “sink rate” and “pull up” four times before the sound of impact. Radar data indicated that the airplane entered a descending right 180° turn before radar contact was lost at an altitude of about 1,175 ft msl (335 ft agl). A security camera about 1/2 mile from the accident site captured the airplane descending in a left turn before it rolled inverted and disappeared behind trees; fire and smoke appeared shortly thereafter. ## Personnel and Aircraft Information The pilot’s training records showed that he satisfactorily completed a 4-day Citation V Single Pilot Exemption course on October 21, 2018, accumulating 12 hours of simulator time, of which 8.7 hours were counted as instrument experience. On the first day, the instructor noted that the pilot needed to review stall series and practice steep turns and single-pilot duties, using available cockpit resources as part of crew resource management. On the third day, the instructor noted overall improvement in all areas of single-pilot operation but stated that the pilot still needed more simulator time to reach the required level of proficiency for single-pilot exemption. The airplane was maintained under a continuous airworthiness inspection program. A pilot who flew the airplane on the evening before the accident reported no anomalies. According to the airplane operating manual, the stall speed in a level bank angle could be between 81 and 95 knots, depending on weight. The airplane was equipped with a stall warning system using a stick shaker mounted on the forward side of the pilot’s control column, which vibrates approximately 8% to 10% above the actual stall speed. ## Meteorological and Airport Information The 1216 recorded weather observation at FTY, about 1 mile southwest of the accident location, included wind from 050° at 10 knots, 7 miles visibility, light rain, overcast clouds at 600 ft agl, temperature 8°C, dew point 8°C, and an altimeter setting of 29.52 inches of mercury. Geostationary Operational Environmental Satellite number 16 (GOES-16) data revealed an extensive layer of cloud cover over the accident site moving from southwest to northeast. The Atlanta Center Weather Service Unit issued a Center Weather Advisory at 1056, valid until 1255, warning of areas of occasional low instrument flight rules ceilings below 500 ft agl and occasional visibilities below 2 miles in rain and fog, with conditions expected to continue beyond the end of the period. AIRMET advisories Sierra and Tango were valid for the accident site at the accident time, warning of moderate turbulence below 18,000 ft msl and instrument flight rules and mountain obscuration conditions due to clouds, precipitation, and mist. FTY issued a Terminal Aerodrome Forecast valid at the time of the accident that expected wind from 070° at 10 knots, 3 miles visibility, moderate rain showers, and an overcast ceiling at 700 ft agl between 1100 and 2200. The pilot did not request a weather briefing through Leidos Flight Service, nor did he review or request any weather information from ForeFlight on the day of the accident. The pilot did check weather information on the day before the accident via ForeFlight for other flight routes flown that day. ## Wreckage and Impact Information The airplane impacted a tree before impacting a field about 50 ft beyond the initial tree strike. All major components were located in the vicinity of the main wreckage. The debris path was about 325 ft long and oriented on a 142° heading. The airplane was highly fragmented along the debris path. The forward wing spar was separated from the airframe and came to rest about 200 ft from the initial ground impact point. The empennage was impact separated and located about 275 ft from the initial impact crater. Both engines were impact separated from the airplane. The cockpit, cabin, and wings were highly fragmented and destroyed. Control continuity was not confirmed due to fragmentation and multiple breaks in the control cables and bellcranks, but all fractures appeared consistent with overload failure. The attitude indicator was located and indicated that the airplane was in an inverted attitude at the time of impact. Disassembly revealed rotational scoring on both the gyro and the gyro housing. The standby attitude indicator was removed and disassembled, and rotational scoring was noted on the housing and the gyro. The engines were shipped to the manufacturer’s facility for further examination. The forward section of the left engine was impact damaged, and several fan blades were impact separated. The left engine exhaust case was removed, and rotational scoring was noted on the trailing edge of the third stage low turbine and on the second stage shroud. Debris and dirt were noted on the inside of the engine near the third stage turbine. The low turbine shaft was separated and exhibited a torsional fracture. Examination of the right engine revealed that all fan blades were bent opposite the direction of rotation. Several blades exhibited leading edge gouging, and one blade was impact separated. The exhaust case was removed to access the hot section of the engine. The low-pressure turbine could be rotated by hand, and debris was noted on the blades. Scoring was noted on the trailing edge of the third stage turbine blades. The low turbine shaft was separated from the forward section of the engine and exhibited a torsional fracture. ## Additional Information and Medical Findings The FAA Civil Aeromedical Institute’s publication, “Introduction to Aviation Physiology,” defines spatial disorientation as a loss of proper bearings or a state of mental confusion as to position, location, or movement relative to the position of the earth. Factors contributing to spatial disorientation include changes in acceleration, flight in instrument meteorological conditions (IMC), frequent transfer between visual meteorological conditions (VMC) and IMC, and unperceived changes in aircraft attitude. The FAA Airplane Flying Handbook (FAA-H-8083-B) stated that the pilot must believe what the flight instruments show about the airplane’s attitude regardless of what the natural senses tell. The vestibular sense can and will confuse the pilot, as the sensory areas of the inner ear cannot detect slight changes in airplane attitude nor accurately send attitude changes that occur at a uniform rate over a period of time. False sensations are often generated, leading the pilot to believe the attitude of the airplane has changed when, in fact, it has not. These false sensations result in the pilot experiencing spatial disorientation. The Office of the Medical Examiner, Atlanta, Georgia, performed the autopsy on the pilot. The autopsy report indicated the cause of death was multiple blunt force injuries. Toxicology testing performed by the FAA Forensic Sciences Laboratory on the pilot’s kidney and muscle tissue detected the non-sedating cough suppressant dextromethorphan, its metabolite dextrorphan, and the non-sedating expectorant guaifenesin. Kidney, muscle, and lung tissue were positive for ethanol at 0.752 grams per hectogram (gm/hg), 0.133 gm/hg, and 0.021 gm/hg, respectively. N-propanol was also detected in kidney tissue. Tissue samples were reported as exhibiting putrefaction, thus, the ethanol was likely produced postmortem.