N860JBeech B200

On February 20, 2020, about 0600 central standard time, a Beechcraft B200 airplane, N860J, was destroyed when it was involved in an accident near Lake Coleman, Texas. The pilot and two passengers were fatally injured. The flight was conducted as a Title 14 Code of Federal Regulations Part 91 personal flight.

A review of air traffic control communications revealed that the airplane was cleared for takeoff from Runway 35L at Abilene Regional Airport (ABI), Texas. Shortly after, the pilot was instructed to climb to 12,000 ft mean sea level (msl), then cleared to climb to 23,000 ft msl.

The pilot reported to the controller that they encountered freezing drizzle and light rime icing during the climb from 6500 ft to 8,000 ft msl.

As the airplane climbed through 11,600 ft msl, the pilot reported that they were having an issue with faulty deicing equipment and needed to return to the airport. The controller instructed the pilot to descend to 11,000 ft msl and cleared them direct to the ABI. The controller then issued a descent to 7,000 ft and asked if there was an emergency. The pilot stated that they “blew a breaker” when they encountered icing conditions, and that it was not resetting.

The controller then instructed the pilot to descend to 5,000 ft and to expect the ILS Runway 35R approach. The controller gave the pilot a heading of 310°. Shortly afterwards the controller asked the pilot if they were turning to the assigned heading; the pilot responded that they were having issues with faulty instruments. When the controller asked the aircraft to report their altitude, the pilot reported that they were at 4,700 ft. The controller then instructed the pilot to maintain 5,000 ft. The pilot responded he was “pulling up”. There was no further communication with the pilot.

Review of the airplane’s radar track showed the airplane’s departure from ABI and the subsequent turn and southeast track towards its destination. The track appeared as a straight line before a right turn was observed. The turn radius decreased before the flight track ended.

On the pilot’s second-class medical application dated November 27, 2019, the pilot listed 5,300 total flight hours and 150 hours in the last six months. The pilot had completed a FlightSafety International KingAir 90, Part 135 initial/transition training course on March 3, 2019.   At that time, the pilot had 625 total flight hours in the KingAir 200.

A review of the airplane maintenance records revealed two discrepancies regarding circuit breakers. The discrepancies noted, “Prop deice inop breaker popped” and “surface deice breaker popped.” The maintenance entry, dated January 2020, annotated the corrective action as, “Checked associated wiring at LH and RH prop. Torqued hardware on heater boot terminal blocks. Checked wiring at LH and RH de ice boots. Ground run ops check ok” and “Tested system on ground using airborne test kit. Ground run ops check ok.”

A review of the airplane maintenance records revealed two discrepancies regarding circuit breakers. The discrepancies noted, “Prop deice inop breaker popped” and “surface deice breaker popped.” The maintenance entry, dated January 2020, annotated the corrective action as, “Checked associated wiring at LH and RH prop. Torqued hardware on heater boot terminal blocks. Checked wiring at LH and RH de ice boots. Ground run ops check ok” and “Tested system on ground using airborne test kit. Ground run ops check ok.”

The airplane impacted terrain in a right-wing-low attitude. The wreckage path was oriented on a magnetic heading of 320° and continued for about 570 ft. The wreckage was highly fragmented along the wreckage path. There was a strong fuel odor at the site.

Figure 1: Wreckage path with fragmented wreckage

Various parts of the flight controls were located along the wreckage path. A section of the empennage wreckage contained the rudder, which remained attached; the left and right elevators which also remained attached. The counterweighed tips had impact separated and were located in the debris path.

Various pieces of the flight control cables were found in the wreckage path, and continuity could not be established due the fragmentation of the wreckage. Multiple pieces of both the left and right ailerons were located among the wreckage.

The damaged left inboard and outboard flap were in the wreckage. The right inboard and outboard flap separated into multiple sections and located in the debris path. Left outboard and inboard flap actuator housings were fractured and/or had separation of the flap drive cable. The right inboard actuator measurement equated to flaps 0 ° (flaps retracted).

Various landing gear components were located in the wreckage path, including the initial ground scar; the position of the landing gear before impact could not be determined.

Each engine was equipped with an MT composite, 5-bladed propeller under a supplemental type certificate, multiple fragments/pieces of the blades were located in the debris path.

Both engines were either buried or partially buried in the ground, just beyond the initial wing impact point. The right-side engine sustained heavy impact damage: the engine case, accessory gear box, exhaust ducts were crushed, deformed, or fragmented. Disassembly of the engine was conducted in the field; examination of the compressor turbine showed circumferential rubbing wear at the disc and blade firtree serration area from contact with the pressure turbine (1st stage) vane ring. The compressor turbine disc downstream side center bore, and lugs showed rubbing wear from contact with the interstage baffle. The compressor turbine shroud segments showed circumferential rubbing wear and corresponding rubbing wear was observed on the compressor turbine blade tips. A visual examination of the 1st stage compressor rotor showed several airfoils were bent in the opposite direction of rotation with material observed on the blade tips. The 1st stage compressor rotor airfoils showed impact marks on the leading edge.

The left engine was located slightly further along the debris path. The exhaust ducts were still attached to the engine and were crushed, deformed, and folded over the engine exhaust case. The engine also displayed heavy impact damage. Disassembly of the left engine was conducted in the field; examination of the compressor turbine disc found it was fractured at the compressor rear air seal area and released from the compressor. Circumferential rubbing wear was observed on the compressor disc upstream side from contact with the compressor turbine vane ring. The downstream side of the compressor turbine disc showed circumferential rubbing wear across the entire disc face from contact with the 1st stage power turbine vane ring and interstage baffle. The compressor turbine blades were fractured and showed secondary impact damage. The fracture surfaces showed evidence of tensile overload. The compressor turbine shroud segments showed circumferential scoring. The corresponding portion of the fracture compressor turbine disc remained inside the engine. The compressor turbine vane ring airfoils showed debris, otherwise no pre-impact distress was observed.

The power turbine stator housing was fractured, deformed, and mangled due to impact. The 1st stage power turbine vane ring was fragmented. The interstage baffle was deformed and wrapped around the 1st stage power turbine disc. The power turbine (1st stage) disc upstream side showed circumferential rubbing wear from contact with the interstage baffle. The 1st stage power turbine blades were all fractured and the fracture surface showed evidence of tensile overload. The 2nd stage power turbine vane ring was deformed, and several airfoils were bent and fractured. The 2nd stage power turbine disc downstream side showed circumferential rubbing wear from contact with the exhaust case. The 2nd stage power turbine blades were all fractured at various heights and the fracture surfaces showed evidence of tensile overload.

The left and right engine examinations did not identify any pre-impact abnormalities.

Figure 2: Initial impact point and Engines

The instrument panel was highly fragmented, with pieces of instruments scattered along the wreckage path. Due to the impact damage, instrument readings and the position of switches and levers in the cockpit were not considered reliable. The right-side pneumatic attitude indicator was located; the instrument had impact separated from the panel and displayed heavy impact damage. The rotor/gyro was outside of the case; light circumferential scoring/rubbing was noted. A remote gyro unit was in the debris path. The unit also had heavy impact damage with circumferential scoring/rubbing on the rotor/gyro system.

Figure 3: N860J panel

Excerpt from: Pilot’s Handbook of Aeronautical Knowledge FAA H-8083-25B Spatial Disorientation pilot handbook 17-6

Spatial Disorientation and Illusions

Spatial disorientation specifically refers to the lack of orientation with regard to the position, attitude, or movement of the airplane in space. The body uses three integrated systems that work together to ascertain orientation and movement in space.

• Vestibular system—organs found in the inner ear that sense position by the way we are balanced

• Somatosensory system—nerves in the skin, muscles, and joints that, along with hearing, sense position based on gravity, feeling, and sound

• Visual system—eyes, which sense position based on what is seen

All this information comes together in the brain and, most of the time, the three streams of information agree, giving a clear idea of where and how the body is moving. Flying can sometimes cause these systems to supply conflicting information to the brain, which can lead to disorientation. During flight in visual meteorological conditions (VMC), the eyes are the major orientation source and usually prevail over false sensations from other sensory systems. When these visual cues are removed, as they are in instrument meteorological conditions (IMC), false sensations can cause a pilot to quickly become disoriented.

Graveyard Spiral

As in other illusions, a pilot in a prolonged coordinated, constant-rate turn may experience the illusion of not turning. During the recovery to level flight, the pilot will then experience the sensation of turning in the opposite direction causing the disoriented pilot to return the aircraft to its original turn. Because an aircraft tends to lose altitude in turns unless the pilot compensates for the loss in lift, the pilot may notice a loss of altitude. The absence of any sensation of turning creates the illusion of being in a level descent. The pilot may pull back on the controls in an attempt to climb or stop the descent. This action tightens the spiral and increases the loss of altitude; this illusion is referred to as a “graveyard spiral.” This may lead to a loss of aircraft control.

The South Plains Forensic Pathology, PA. Lubbock, Texas, under the authority of the Justice of the Peace, Coleman County, conducted an autopsy on the pilot. The cause of death was determined to be: "multiple blunt impact injuries”.

The Federal Aviation Administration’s (FAA) Forensic Sciences Laboratory, Oklahoma City, Oklahoma, conducted toxicological testing on the pilot. The tests were negative for ethanol. The test was positive for diphenhydramine.

Diphenhydramine is used in over-the-counter medicines and is commonly used to treat sneezing, runny nose, watery eyes, hives, skin rash, itching, and other cold or allergy symptoms.