N3342L

HISTORY OF FLIGHTOn September 26, 2021, at 1009 eastern daylight time, a Beech C-23, N3342L, was substantially damaged when it was involved in an accident in Lansing, West Virginia. The private pilot and two passengers were fatally injured. The airplane was operated as a Title 14 Code of Federal Regulations Part 91 personal flight.

The airplane was departing New River Gorge Airport (WV32) when the accident occurred. The airport owner, his brother, and a neighbor witnessed the accident, and each provided statements; their versions of events were consistent throughout. The airplane had been parked at the airport in front of the owner’s hangar all weekend. On the day of the accident (Sunday), the pilot and two passengers arrived, loaded their luggage and camping gear, and the pilot started the airplane and taxied from its mid-field parking spot to the approach end of runway 22, which was 2,950 ft long.

According to the witnesses, the airplane “powered up” and accelerated. When the airplane reached the point where “airplanes usually lift off,” it continued accelerating down runway 22. The takeoff was aborted, the airplane continued to the runway end, turned around, and subsequently attempted to depart from runway 04.

One witness said, “I thought he would take off this time.” Instead, the airplane continued to accelerate until engine power was reduced, and the second takeoff attempt was aborted. The airplane continued to the departure end of runway 04, turned around again, and began to takeoff from runway 22 for a third attempt. One witness stated that, as the airplane approached the departure end, “…he was going too fast to stop at the end of the runway but not fast enough to take off.”

The airport owner’s brother stated that the airplane lifted off “maybe” 800 ft before the departure end of the runway, cleared the trees at the departure end, and flew over Mill Creek, which ran below and perpendicular to the runway. The terrain on the opposite bank was higher than the runway and included mature trees. The airport owner said, “I thought he might make it…” over the trees, but instead the airplane banked steeply left and disappeared below the trees. He estimated that the airplane’s bank angle was 45° and that the engine sound was smooth and continuous from engine start until the sound of impact. PERSONNEL INFORMATIONThe pilot held a private pilot certificate with ratings for airplane single-engine land and instrument airplane. Review of his logbook revealed 395.7 total hours of flight experience, with an estimated 312 hours of experience in the accident airplane make and model. METEOROLOGICAL INFORMATIONThe reported weather conditions resulted in an estimated density altitude of 1,845 ft at the time of the accident. WRECKAGE AND IMPACT INFORMATIONThe airplane came to rest on the opposite side of Mill Creek, about 880 ft south of the departure end of runway 22. The initial impact point was a treetop about 60 ft above the ground and uphill from where the airplane came to rest. The wreckage path was about 75 ft long and oriented on a magnetic heading of 090°. Several pieces of angularly cut wood were found along the wreckage path. The main wreckage came to rest upright and was also oriented on a 090° heading; all major components of the airplane were accounted for at the scene.

The engine was dislodged from its mounts, rested inverted, and the propeller spinner displayed torsional twisting. The two propeller blades showed similar spanwise bending and leading-edge gouging. The engine firewall, instrument panel, windscreen posts, and cockpit floor were destroyed by impact. The windscreen was separated.

The leading edges of both wings were crushed aft in compression, and the skin of the right wing outboard of the right main landing gear was separated and found uphill from the main wreckage. The right aileron remained attached to the separated section. Flight control cable continuity was established for all flight controls.

The engine crankshaft was rotated through the vacuum pump drive. Engine continuity was established through the accessory section to the powertrain and valvetrain. Compression was confirmed using the thumb method. The magnetos each produced spark at all leads. The spark plugs displayed minimal normal wear signatures. Fuel was observed at the fuel pump and the carburetor. The carburetor fuel inlet screen was clean and absent of debris.

Two pipes used for smoking cannabis were found in the personal effects. One pipe was found by first responders, the other pipe and cannabis were found by the investigative team and turned over to police. ADDITIONAL INFORMATIONThe maximum allowable gross weight of the airplane was 2,450 lbs, and the calculated useful load of the accident airplane was 862.4 lbs.

The luggage and camping gear onboard the airplane was weighed with a bathroom scale and the total cargo weight was 253 lbs. The estimated occupant weight combined with the cargo weight was an estimated 813 lbs. Total fuel weight was estimated at either 193 lbs (32.2 gallons) or 83 lbs (13.8 gallons) based on either full tanks (60 gallons) or 2/3 tanks (40 gallons) at the time of departure from the airplane’s home base and the fuel likely consumed during the 2.5-hour flight to WV32. The pilot did not purchase fuel at WV32 before departing on the accident flight.

With 32 gallons of fuel on board at departure, the airplane’s calculated weight was 2,574 lbs, which was 124 lbs above the maximum allowable gross weight and aft of the airplane’s aft cg limit. With 14 gallons of fuel on board at departure, the airplane’s calculated weight was 2,463.4 lbs, which was 13 lbs above the maximum allowable gross weight and aft of the airplane’s aft cg limit.

Based on the C23 Pilot’s Operating Handbook, Take-Off Distance – Hard Surface performance chart, and the following conditions: max gross weight of 2,450 lbs, density altitude of 1,845 ft, headwind of 4 knots, and temperature 15°C, the interpolated ground roll was 1,280 ft and the distance to clear a 50 ft obstacle was 2,239 ft. The liftoff speed was 65 knots and 74 knots at 50 ft. Stall speed with flaps retracted in a 45° bank was 74 knots.

A piece of notebook paper titled, “1/25/2021 New Personal Minimums” was found inside the back cover of the pilot’s personal logbook. The paper included a section titled, “Aircraft Performance,” which listed the maximum gross weight of the airplane, empty weight, and maximum fuel capacity. The list included a 328-lb “non-pilot” weight, which was consistent with the airplane’s payload capacity given full fuel tanks and the weight of the accident pilot.

The section also listed, “Min rwy: 2400 ft (std); 3000 ft (hot).” (see figure.)

Figure. Excerpt from "Personal Minimums" document found in pilot's logbook

The FAA Weight and Balance Handbook, FAA-H-8083-1, stated:

Most modern aircraft are so designed that, when all seats are occupied, the baggage compartment is full, and all fuel tanks are full, the aircraft is grossly overloaded. This type of design requires the pilot to give great consideration to the requirements of each specific flight. If maximum range is required, occupants or baggage must be left behind, or if the maximum load must be carried, the range, dictated by the amount of fuel on board, must be reduced.

Overloading an aircraft can create a variety of problems:

• The aircraft needs a higher takeoff speed, which results

in a longer takeoff run.

• Both the rate and angle of climb are reduced.

• The service ceiling is lowered.

• The cruising speed is reduced.

• The cruising range is shortened.

• Maneuverability is decreased.

• A longer landing roll is required because the landing

speed is higher.

• Excessive loads are imposed on the structure,

especially the landing gear.

The POH or AFM includes tables or charts that give the pilot an indication of the performance expected for any weight. An important part of careful preflight planning includes a check of these charts to determine if the aircraft is loaded so the proposed flight can be safely made. MEDICAL AND PATHOLOGICAL INFORMATIONAccording to the State of West Virginia, Office of the Chief Medical Examiner, Charleston, West Virginia autopsy report, the cause of the pilot’s death was generalized blunt impact injuries and the manner of death was accident. No significant natural disease was identified.

Toxicology testing performed by the FAA Forensic Sciences Laboratory detected the primary psychoactive compound of cannabis, tetrahydrocannabinol (THC), in the pilot’s cavity blood at 1.1 nanograms per milliliter (ng/mL); THC was not detected in his liver tissue. THC’s inactive metabolite carboxy-delta-9-tetrahydrocannabinol (THC-COOH) was detected in the pilot’s cavity blood and liver tissue at 6.1 ng/mL and 30.9 nanograms per gram, respectively. Ethanol was not detected in cavity blood. Toxicology testing performed for the medical examiner’s office was positive for THC at 1.2 ng/mL and THC-COOH at 8.0 ng/mL in the pilot’s pleural blood. Ethanol was detected in pleural blood at 0.026 grams per deciliter (gm/dL).

Tetrahydrocannabinol (THC) is the primary psychoactive cannabinoid compound in cannabis. THC’s mood-altering effects include euphoria and relaxation. In addition, cannabis causes alterations in motor behavior, time and space perception, and cognition. Significant performance impairments are usually observed for at least 1-2 hours following cannabis use, and residual effects have been reported up to 24 hours.

THC is rapidly metabolized, but the rate of metabolism is not linear and depends on the means of ingestion (smoking, oil, and edibles), potency of the product, frequency of use, and user characteristics. The primary metabolite, 11-hydroxy-delta-9-THC, is equally psychoactive but is rapidly metabolized to the non-psychoactive metabolite THC-COOH. THC is fat soluble, so is stored in fatty tissues and can be released back into the blood long after co...