N198DMBeech 200 · 1984

On August 20, 2020, about 1542 central daylight time, a Beech B200 airplane (marketed as a King Air 200), N198DM, was destroyed when it was involved in an accident near Rockford, Illinois. The private pilot was fatally injured. The airplane was operated as a Title 14 Code of Federal Regulations (CFR) Part 91 positioning flight.

The purpose of the flight was to relocate the airplane to the pilot's home base at the DuPage Airport (DPA), West Chicago, Illinois. The airplane had been at Chronos Aviation, LLC (a 14 CFR Part 145 repair station), at the Rockford International Airport (RFD), Rockford, Illinois, for maintenance work.

Multiple airport-based cameras recorded the accident sequence. The videos showed the airplane taking off from runway 19. Shortly after liftoff, the airplane started turning left, and the airplane developed a large left bank angle as it was turning. The airplane departed the runway to the left and impacted the ground. During the impact sequence, an explosion occurred, and there was a postimpact fire. A video study estimated the airplane’s maximum groundspeed during the takeoff as 105.5 knots (kts).

Data recovered from an Appareo Stratus device onboard the airplane showed that about 1538, the airplane began taxing to runway 19. At 1540:34, the airplane crossed the hold short line for runway 19. At 1541:19, the airplane began a takeoff roll on runway 19. At 1541:42, the airplane began to depart the runway centerline to the left of the runway. Subsequent tracklog points showed the airplane gaining some altitude, and the tracklog terminated adjacent to a taxiway in a grassy area.

The Appareo Stratus data showed the airplane began to increase groundspeed on a true heading of roughly 185° about 1541. Airplane pitch began to increase at 1541:41 as the groundspeed reached about 104 kts. The groundspeed increased to 107 kts within the next 2 seconds, and the pitch angle reached around 4° nose-up at this time. In the next few seconds, pitch lowered to around 0° as the groundspeed decayed to around 98 kts. The pitch then became 15° nose-up as the groundspeed continued to decay to about 95 kts. A right roll occurred of about 13° and changed to a rapidly increasing left roll over the next 5 seconds. The left roll reached a maximum of about 86° left as the pitch angle increasingly became negative (the airplane nosed down). The pitch angle reached a maximum nose down condition of -73°. The data became invalid after 1541:53.4.

An airplane performance study based on the Appareo Stratus data showed that during the takeoff from runway 19, the airplane accelerated to a groundspeed of 98 kts and an airspeed of 105 kts before rotating and lifting off. The airplane pitched up, climbed, and gained height above the ground. Then, 4 seconds after rotation, the airplane began descending and slowing, consistent with a loss of power. A nose-left sideslip, a left side force, and a left roll were recorded, consistent with the loss or reduction in thrust of the left engine. The sideslip was reduced, likely due to opposite rudder input, and the airplane briefly rolled right. The airplane pitched up and was able to begin climbing again; however, it continued to lose speed. The sideslip then reversed, and the airplane rolled left again and impacted the ground.

One witness reported that he observed the accident sequence. He did not hear any abnormal engine noises, nor did he see any smoke or flames emit from the airplane before impact.

The airplane came to rest on a flat grass field to the east of runway 19 on airport property. The airplane sustained fire damage and was fragmented from impacting terrain.

The pilot established the King Air Academy in Phoenix, Arizona. The King Air Academy is a flight training facility that provides initial, recurrent, type rating, and simulator training for the King Air series of airplanes.

According to Federal Aviation Administration (FAA) records, the pilot did not hold a type rating for the accident airplane, nor was he required to hold one.

Maintenance Records

A review of the airplane’s maintenance records revealed no evidence of uncorrected mechanical discrepancies with the airframe, engines, or propellers. The recent maintenance work performed at Chronos Aviation, LLC, consisted of the installation of three new switches for the flaps, the installation of two auxiliary outboard fuel level senders, the adjustment of an ice vane door switch, work on a radar control data bus, and a patch repair to the left propeller de-ice boot.

Airplane Servicing

A fuel receipt showed that 304 gallons of Jet A fuel was purchased for the airplane at RFD on the day of the accident.

Airplane Systems

The airplane was certified for single-pilot operation. It was equipped with an autofeather system that was intended for use during takeoff and landing if there was a loss of engine power. The airplane was equipped with a rudder boost system, which was designed to reduce the required rudder pedal force in the event of an engine failure. The published minimum control airspeed (VMCA) was 86 kts.

The engine and propeller control levers on the accident airplane were located between the two cockpit seats. The power quadrant included two power levers (which controlled engine power from idle through takeoff) and two propeller levers (which controlled propeller speed and feathering) to the right of the power levers. When the power levers were lifted over the idle gate during ground operation, they controlled engine power and propeller blade angle through the ground fine and reverse ranges. Two engine condition levers were to the right of the propeller levers and had three positions: fuel cutoff, low idle, and high idle. The left condition lever controlled the left engine, and the right condition lever controlled the right engine.

Friction lock control knobs were located on the power quadrant. Each power lever had its own friction lock control knob at the base of the quadrant to adjust the power lever’s tension. One friction knob controlled the tension of both propeller levers. Turning the knobs counterclockwise increased tension and turning them clockwise reduced tension. The before engine starting checklist called for these friction locks to be set.

Weight and Balance

A review of the airplane’s weight and balance data showed that the airplane was within limitations for the accident flight.

The estimated density altitude for the airport was 2,545 ft mean sea level.

Maintenance Records

A review of the airplane’s maintenance records revealed no evidence of uncorrected mechanical discrepancies with the airframe, engines, or propellers. The recent maintenance work performed at Chronos Aviation, LLC, consisted of the installation of three new switches for the flaps, the installation of two auxiliary outboard fuel level senders, the adjustment of an ice vane door switch, work on a radar control data bus, and a patch repair to the left propeller de-ice boot.

Airplane Servicing

A fuel receipt showed that 304 gallons of Jet A fuel was purchased for the airplane at RFD on the day of the accident.

Airplane Systems

The airplane was certified for single-pilot operation. It was equipped with an autofeather system that was intended for use during takeoff and landing if there was a loss of engine power. The airplane was equipped with a rudder boost system, which was designed to reduce the required rudder pedal force in the event of an engine failure. The published minimum control airspeed (VMCA) was 86 kts.

The engine and propeller control levers on the accident airplane were located between the two cockpit seats. The power quadrant included two power levers (which controlled engine power from idle through takeoff) and two propeller levers (which controlled propeller speed and feathering) to the right of the power levers. When the power levers were lifted over the idle gate during ground operation, they controlled engine power and propeller blade angle through the ground fine and reverse ranges. Two engine condition levers were to the right of the propeller levers and had three positions: fuel cutoff, low idle, and high idle. The left condition lever controlled the left engine, and the right condition lever controlled the right engine.

Friction lock control knobs were located on the power quadrant. Each power lever had its own friction lock control knob at the base of the quadrant to adjust the power lever’s tension. One friction knob controlled the tension of both propeller levers. Turning the knobs counterclockwise increased tension and turning them clockwise reduced tension. The before engine starting checklist called for these friction locks to be set.

Weight and Balance

A review of the airplane’s weight and balance data showed that the airplane was within limitations for the accident flight.

All the major structural components of the airplane were located at the accident site. Flight control continuity was established for the airframe. The airplane’s fuel system was destroyed by the postimpact fire. All landing gear were found in the retracted position. The postimpact fire consumed most of the instrument and switch panels in the cockpit. The flap handle was found in the full up position; the rudder trim knob was found 4 units to the left; and the aileron trim knob was found 6 units to the right. The autofeather switch was found in the ARM position. The rudder boost switch (a gated switch) was found in the OFF position. The before engine starting checklist called for the rudder and aileron trim controls to be set and for the rudder boost switch to be in the ON position.

The power quadrant was destroyed by the impact sequence and the postimpact fire. When compared to an exemplar power quadrant, the throttle levers appeared to be full forward, and the propeller levers appeared to be forward of the feather range. Damage sustained to the control lever friction components precluded determining the friction setting during the accident flight.

Teardown examination of the left engine found rotational scoring damage to compressor turbine and power turbine rotor disk faces and adjacent stator structures consistent with loss of operating clearances during engine operation due to impact loads experienced during an accident sequence. The engine propeller shaft was fractured consistent with sudden arrest of rotation during operation (torsional failure). No evidence of preimpact failure was found. The left propeller blades displayed leading edge and chordwise rotational scoring; the blades were predominately bent aft and twisted toward low pitch. Disassembly found marks indicating that the left propeller was not feathered at the time of impact. All the damage was consistent with impact.

Teardown examination of the right engine found 360° rotational scoring of compressor turbine and power turbine rotor disk faces and adjacent stator structures consistent with engine operation during impact. The engine propeller shaft was fractured, and the fracture was consistent with torsional failure. No evidence of preimpact failure was found. The right propeller blades displayed leading edge and chordwise rotational scoring; the blades were predominately bent forward in the thrust direction and were twisted toward high pitch. Disassembly found marks indicating that the right propeller was not feathered at the time of impact. All the damage was consistent with impact.

The Australian Transport Safety Bureau has published Safety Advisory Notice AO-2021-034-SAN-01 Power Lever Friction Lock Adjustment, for the Beechcraft King Air series airplanes, and states in part:

The Australian Transport Safety Bureau advises pilots and operators of the King Air series aircraft (90, 200, and 300) that the power lever friction locks require careful adjustment to prevent power lever migration towards the idle position, particularly during take-off. Inadvertent migration of one power lever towards idle can result in power reduction and yaw that, when occurring at low height, can result in catastrophic outcomes. Operators should ensure pre-flight checks provide opportunities to confirm friction lock settings before the take-off run, and ensure pilots have adequate knowledge of friction lock sensitivity to help prevent and recover from inadvertent power lever migration.

The airplane was not equipped with a crashworthy flight data recorder or a cockpit voice recorder, nor was it required to be.

According to the autopsy performed by the Winnebago County Coroner’s Office, the pilot’s cause of death was thermal injuries. In addition, left ventricular wall thickening, coronary artery disease with stent present in the circumflex artery, and a 3-centimeter scar in the left ventricular wall from a previous heart attack were identified. No other significant disease was identified.

Toxicology testing performed at the request of the coroner by NMS Labs identified caffeine (a mild stimulant found in coffee, tea, and sodas), cotinine (a product of tobacco use), and a carboxyhemoglobin level of 6% (which may be related to smoking). Toxicology testing performed by the FAA Forensic Sciences Laboratory identified carvedilol (a beta blocker used to prevent recurrent heart attacks) and atorvastatin (a cholesterol lowering drug) in the pilot’s blood and urine. These two medications are not considered impairing.

Simulator Research

Textron Aviation used a Beechcraft 260 simulator (not as a formal test flight) to replicate a takeoff with the postaccident positions found for the rudder trim knob (4 units to the left) and the aileron trim knob (6 units to the right). The elevator was set for a normal takeoff. Two takeoffs were performed, one with the flaps down and one with the flaps up. The simulator pilot reported the two takeoffs were normal until rotation at which point, he noticed a slight tendency to roll to the right. He had to input a slight left bank to counteract it, but it was nothing substantial. The pilot had no issue following the checklist and getting the main landing gear retracted. Once the airplane reached 200 kts, the pilot reported the offset trims required more effort to overcome.