History of Flight
On February 8, 2020, at 1317 central standard time, a Beech F33A airplane, N6665U, was substantially damaged when it impacted terrain near Granbury, Texas. The pilot was fatally injured. The flight was conducted under Title 14 Code of Federal Regulations Part 91 as a personal flight.
Review of radar and ADS-B data showed the airplane approached Granbury Regional Airport (GDJ) from the northwest about 1301, overflew runway 14 at 900 feet above ground level, then turned right onto a wide downwind leg, descending to about 400 feet agl. After a right base turn, the first data set ended at 1305:07. Radar data resumed at 1314:18 with a target on the southwest side of GDJ proceeding north. The final radar return was at 1316:51, with the accident site 0.39 nautical miles north-northeast of that point.
At least three other airplanes were flying in the GDJ airport environment simultaneously. As the accident airplane was on short final, one airplane had just departed GDJ; another was ahead in the right traffic pattern; a third circled above then followed the accident airplane into the pattern. The pilot of the third airplane recalled seeing the accident airplane, entered the pattern behind it, performed an S-turn for spacing, watched it land and taxi toward hangars, and did not see it again. The GDJ airport manager stated that his employees did not see the accident airplane arrive.
Personnel Information
The pilot had recently completed a flight review on January 7, 2020. That flight was a 1.2-hour round trip from Mineral Wells Airport (MWL) to GDJ and back, including steep turns, slow flight, stalls, cross-country navigation, preflight planning, autopilot use, and three takeoffs and landings.
Aircraft Information
A Federal Aviation Administration inspector spoke to an MWL airport employee who fueled the accident airplane before departure. The pilot requested fuel "to the slots," and 13 gallons were added to reach that level. The fuel filler port placards on the wings stated, "CAP TO TAB SLOT 35 GAL (32 USABLE)."
Wreckage and Impact Information
The accident site was located in flat, rocky terrain about 3.75 miles northwest of GDJ at 830 feet mean sea level. The airplane impacted in a 45° nose-down attitude on a 068° true heading. The empennage was bent upward and slightly left, with elevators resting on a tree. The airplane remained on top of initial ground impact marks.
Leading edges of both wings were breached at rivet lines and split open. 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 were ejected, found about 10 feet forward of the wing. Wing tip tanks sustained impact damage, with large portions fractured and displaced forward and outward. Dirt and organic debris in front of the wings were displaced forward.
The fuel selector handle was positioned to the left main tank. The flap actuator indicated flaps retracted at impact; landing gear were found extended. Flight control continuity was established. Examination revealed no mechanical malfunctions or anomalies that would have precluded normal operation.
Examination of the engine showed most impact damage to the bottom. Crankshaft and camshaft continuity was confirmed when rotated by hand. Five of six cylinders produced suction and compression; the sixth exhibited impact damage to the intake pushrod. Borescope inspection of cylinder interiors displayed normal operating signatures with no anomalies. Spark plug electrodes showed normal wear. The fuel manifold valve remained attached and undamaged. The fuel line from the fuel flow transducer to the manifold valve was disconnected at the transducer; a small amount of liquid was drained, with an odor consistent with fuel, clear color, and negative for water. Small amounts of gray fibrous material were found in several places in the fuel system (unfiltered side of manifold valve, metering assembly inlet screen, and fuel selector strainer) but in insufficient quantity to affect fuel passage.
The propeller assembly was impact-separated from the crankshaft and embedded in the initial impact crater. Two blades remained attached to the hub: one mostly straight and unremarkable, the other bent slightly forward. The third blade had separated, was found under the engine, bent aft about mid-span, with about one foot of scratches and superficial damage near the root.
Medical and Pathological Information
The Tarrant County Medical Examiner performed an autopsy; the pilot's cause of death was massive blunt force trauma. Toxicology testing by the FAA Forensic Sciences Laboratory detected ethanol and propanol in muscle, likely post-mortem. No drugs or medications were detected.