N6665UBeech F33A · 1979

On February 8, 2020, at 1317 central standard time, a Beech F33A airplane, N6665U, was substantially damaged when it was involved in an accident near Granbury, Texas. The pilot was fatally injured. The airplane was operated as a Title 14 Code of Federal Regulations Part 91 as a personal flight.

A review of the recorded radar and automatic dependent surveillance – broadcast (ADS-B) data revealed that the airplane approached Granbury Regional Airport (GDJ), Granbury, Texas, from the northwest about 1301 and overflew runway 14 at 900 ft above ground level (agl). After overflying the runway, the airplane turned right toward the northwest on a wide downwind leg and gradually descended to about 400 ft agl. The airplane made a right base turn, where the first set of data ended at 1305:07, about 440 ft agl, and 93 knots groundspeed. At 1314:18, radar data showed a target on the southwest side of GDJ that proceeded to the north toward the accident site and ended at 1316:51. The accident site was located 0.39 nautical miles north-northeast of the final radar return. Figure 1 shows the recorded flight track with the accident site and GDJ airport labeled.

Figure 1 – Radar and ADS-B track in red with the accident site and GDJ airport labeled

Further review of the ADS-B data showed that at least three other airplanes were also flying in the immediate GDJ airport environment at the same time as the accident airplane. As the accident airplane was on short final, one airplane had just departed GDJ and proceeded southeast. The second airplane was in a right traffic pattern and ahead of the accident airplane. The third airplane was circling above the traffic pattern, then descended and followed the accident airplane into the traffic pattern. The pilot of this third airplane remembered the accident airplane and stated that he entered the traffic pattern behind it and completed an S-turn maneuver for appropriate spacing. He continued in the pattern behind the accident airplane and watched it land and taxi toward the hangars and did not see the airplane again. The GDJ airport manager stated that his employees did not see the accident airplane arrive that day.

The pilot recently completed a flight review on January 7, 2020. The flight was a 1.2-hour round trip from Mineral Wells Airport (MWL), Mineral Wells, Texas, to GDJ and back, and included steep turns, slow flight, stalls, cross-country navigation, preflight planning, autopilot use, and three takeoffs and landings.

The responding Federal Aviation Administration (FAA) inspector spoke to an MWL airport employee who fueled the accident airplane before the pilot departed on the accident flight. She stated that the pilot requested fuel "to the slots," and she added 13 gallons of fuel to obtain that level. The fuel filler port placards on the airplane wings stated, "CAP TO TAB SLOT 35 GAL (32 USABLE)."

The responding Federal Aviation Administration (FAA) inspector spoke to an MWL airport employee who fueled the accident airplane before the pilot departed on the accident flight. She stated that the pilot requested fuel "to the slots," and she added 13 gallons of fuel to obtain that level. The fuel filler port placards on the airplane wings stated, "CAP TO TAB SLOT 35 GAL (32 USABLE)."

The accident site was located in an area of flat, rocky terrain about 3.75 miles northwest of GDJ at 830 ft mean sea level. The airplane impacted the ground in a 45° nose-down attitude and was oriented on a 068° true heading. The empennage was bent upward and slightly to the left, and the elevators rested on a tree. The airplane remained situated on top of the initial ground impact marks.

Examination of the wreckage revealed that the leading edges of both wings were breached at the rivet lines and were split open. The fuel bladders in each wing had ruptured and were significantly damaged. A large portion of the right main fuel bladder and the entire fuel transmitter assembly had been ejected and were found about 10 ft in front of the wing. The wing tip tanks sustained impact damage and large portions of the tanks were fractured and displaced forward and outward. The dirt and organic debris in front of the wings was displaced forward. The fuel selector handle was positioned to the left main tank. The flap actuator revealed that the flaps were retracted during the impact and also the landing gear were found extended. Flight control continuity was established, and the examination did not reveal any mechanical malfunctions or anomalies that would have precluded normal operation.

Examination of the engine revealed that most of the impact damage was sustained to the bottom of the engine. Crankshaft and camshaft continuity were confirmed when the crankshaft was rotated by hand. Five of six cylinders produced suction and compression and the sixth cylinder exhibited impact damage to the intake pushrod. The inside of each cylinder was examined with a lighted borescope; the cylinders displayed normal operating signatures with no anomalies noted. The spark plug electrodes all displayed normal wear and operating signatures. The fuel manifold valve remained attached to its installation point and was undamaged. The fuel line from the fuel flow transducer and the manifold valve was disconnected from the transducer and a small amount of liquid was drained. Its odor was consistent with fuel; the liquid was clear in color and tested negative for water. A small amount of gray, fibrous material was found in the fuel system in several places but was of insufficient quantity to affect fuel passage. The material was found in the unfiltered side of the manifold valve, in the inlet screen of the metering assembly, and in the fuel selector strainer.

The propeller assembly was found in the initial impact crater embedded in the ground under the engine and was impact-separated from the engine crankshaft. Two of the propeller blades remained attached to the hub; one blade was mostly straight and unremarkable and the other was bent slightly forward. The third blade had separated from the hub; it was found directly under the engine and was bent aft about mid-span. This blade also exhibited about one foot of scratches and superficial damage near the blade root.

The Office of the Chief Medical Examiner, Tarrant County Medical Examiner's District, Tarrant County, Texas, performed an autopsy of the pilot. The pilot's cause of death was massive blunt force trauma.

The FAA Forensic Sciences Laboratory performed toxicology testing on specimens from the pilot. The specimens were positive for ethanol and propanol in the muscle, which were likely post-mortem. There were no drugs or medications detected.