N6059G is a Cessna 150K. It is a fixed-wing single-engine aircraft with 2 seats, powered by a Cont Motor 0-200 series rated at 100 horsepower. The registration is active, with the registrant based in Montgomery, TX. Its standard airworthiness certificate was issued in Nov 1969. It has been registered to its current owner since Jul 2023. This page also carries 1 NTSB event.
2023
1969
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On September 6, 2023, about 1148 central daylight time, a Cessna 150K airplane, N6059G, was substantially damaged during an accident at Huntsville Municipal Airport (UTS), Huntsville, Texas. The flight instructor and student pilot were fatally injured. The airplane was operated as a Title 14 Code of Federal Regulations Part 91 instructional flight.
According to ADS-B flight track data, at 1027 the airplane departed from runway 14 at North Houston Regional Airport (CXO), Conroe, Texas. The airplane flew northeast about 6 nautical miles before it turned northwest toward UTS. About 1050, the airplane entered the traffic pattern for runway 36 at UTS. The airplane flew 6 traffic patterns consistent with touch-and-go landings on runway 36. The airplane would descend below ADS-B coverage about 700 ft mean sea level (msl), or about 337 ft above airport elevation, while it operated in the traffic pattern at UTS. About 1128, the airplane switched landing direction to use runway 18. The airplane flew 3 additional traffic patterns consistent with touch-and-go landings on runway 18. At 1146:54, the last ADS-B return was recorded about 830 ft msl as the airplane descended on the base leg for runway 18.
Two witnesses reported that the airplane was flying in the airport traffic pattern before the accident. They were on the ramp preparing for an instructional flight when they heard a sudden decrease in engine rpm. They turned and saw the airplane flying south over runway 18, about 500 ft above the runway, in a level pitch attitude with rocking wings. The airplane then entered a left turn toward east in a nose-down attitude. The flight instructor believed that the pilot of the airplane was attempting a descending left 180° turn to land on runway 36. He stated that the airplane completed about 90° of turn when it entered an aerodynamic spin and descended to the ground in a nose-down pitch attitude.
The airplane was equipped with a 26-gallon (22.5 gallons usable) fuel system, consisting of two 13-gallon main fuel tanks (11.25 gallons usable each). The two fuel tanks are combined before the fuel shutoff valve, as depicted in figure 1.
On December 9, 2022, the fight instructor, who was also the airplane owner, made an entry in the airplane’s discrepancy record that the airplane was using fuel from the left tank “slower” than the right tank. The airframe total time was 8,024.9 hours at the time of the discrepancy. The discrepancy was deferred until the next annual inspection. The discrepancy log entry further noted that the issue could not be duplicated during the annual inspection dated August 15, 2023. The signature on the discrepancy entry was comparable to signatures found in the flight instructor’s pilot logbook.
A postaccident review of the airplane’s maintenance logbooks revealed that the last maintenance of the fuel shutoff valve was completed about 8 years before the accident, on July 20, 2015, at 7,950.7 total airframe hours. The associated airframe logbook entry stated, in part, “Lubed fuel valve and installed new o-ring.”
According to maintenance documentation, about 20 days before the accident, on August 15, 2023, the last annual inspection of the airplane was completed at 8,029 total airframe hours and 2,723.2 hours since the last engine overhaul. A 100-hour inspection was completed on August 23, 2023, after the airplane was painted.
The airplane’s electronic tachometer was destroyed during impact. As such, the airplane’s total airframe and engine times at the time of the accident could not be precisely determined. However, according to an airplane utilization log, the last recorded flight was completed on September 4, 2023, at 8,041.4 hours total airframe time. Based on ADS-B flight track data, the accident flight was about 1.4 hours in duration.
Figure 1. Fuel system schematic.
The airplane was equipped with a 26-gallon (22.5 gallons usable) fuel system, consisting of two 13-gallon main fuel tanks (11.25 gallons usable each). The two fuel tanks are combined before the fuel shutoff valve, as depicted in figure 1.
On December 9, 2022, the fight instructor, who was also the airplane owner, made an entry in the airplane’s discrepancy record that the airplane was using fuel from the left tank “slower” than the right tank. The airframe total time was 8,024.9 hours at the time of the discrepancy. The discrepancy was deferred until the next annual inspection. The discrepancy log entry further noted that the issue could not be duplicated during the annual inspection dated August 15, 2023. The signature on the discrepancy entry was comparable to signatures found in the flight instructor’s pilot logbook.
A postaccident review of the airplane’s maintenance logbooks revealed that the last maintenance of the fuel shutoff valve was completed about 8 years before the accident, on July 20, 2015, at 7,950.7 total airframe hours. The associated airframe logbook entry stated, in part, “Lubed fuel valve and installed new o-ring.”
According to maintenance documentation, about 20 days before the accident, on August 15, 2023, the last annual inspection of the airplane was completed at 8,029 total airframe hours and 2,723.2 hours since the last engine overhaul. A 100-hour inspection was completed on August 23, 2023, after the airplane was painted.
The airplane’s electronic tachometer was destroyed during impact. As such, the airplane’s total airframe and engine times at the time of the accident could not be precisely determined. However, according to an airplane utilization log, the last recorded flight was completed on September 4, 2023, at 8,041.4 hours total airframe time. Based on ADS-B flight track data, the accident flight was about 1.4 hours in duration.
Figure 1. Fuel system schematic.
The airplane crashed into an open grass area about 407 ft south of the end of runway 18 at UTS and about 40 ft east of the extended runway centerline. The airplane came to rest upright and nose down on a west heading. All structural components and flight control surfaces were located at the accident site. The left and right wings and their wing struts remained attached to their attachment points. The leading edge of both wings were crushed aft to their respective main spars. The tail was canted forward and to the right beginning about 3 ft aft of the rear cabin window. The empennage was relatively undamaged with minimal impact damage.
The elevators, ailerons, rudder, trim tabs, and flaps were accounted for at the accident site. Continuity of the flight control cables was confirmed from the cockpit to the flight control surfaces. Continuity of the pitch trim control cables was confirmed from the cockpit to the trim surface.
The cockpit control column assembly exhibited impact-related damage. The aileron control chain remained intact and partially attached to each control column sprocket. The aileron forward bellcrank/arm assembly remained attached to the control column with attached cables. The aileron balance cable remained continuous between the aileron bellcranks. The elevator control tube remained attached to the cockpit control column. The aft end of the elevator control tube was displaced aft about 6 inches and separated from the elevator forward bellcrank, which fractured into two halves with attached cables; the fracture exhibited signatures consistent with an overstress separation due to impact-related damage. The rudder cables were continuous from the cockpit pedals to the rudder control horn, where all hardware was present and connected.
The left and right ailerons remained attached to their wing attachment points. The rudder remained attached to its attachment points on the vertical stabilizer. The left and right elevators remained attached to their respective horizontal stabilizer. The elevator trim actuator extension measured 1.4 inches and was consistent with a neutral pitch trim tab position.
The left and right flaps remained attached to their respective wing attachment points. The flap handle in the cockpit was found in the UP position. The flap actuator/motor was found in the fully retracted position and was consistent with fully retracted flaps at impact.
The wreckage examination did not reveal any preimpact flight control anomalies that would have prevented normal operation.
The left- and right-wing metal fuel tanks exhibited hydraulic deformation along the forward and top tank surfaces. The fuel tank finger strainer screens were not obstructed. The fuel lines from each wing fuel tank to the fuel shutoff valve assembly remained intact. The fuel lines from each wing fuel tank combined through a Y-shaped fuel fitting upstream of the fuel shutoff valve, as previously shown in figure 1. The fuel line from the fuel shutoff valve assembly to the fuel strainer assembly was impact separated about 2 inches forward of the fuel shutoff valve assembly. The fuel strainer assembly was displaced aft through the firewall into the cockpit floor area. The filter bowl was separated from the fuel strainer assembly and was impact damaged. The fuel strainer screen filter remained attached to the fuel strainer and exhibited debris. The fuel line from the fuel strainer assembly to the carburetor was separated and not observed.
The fuel line connected to the inlet port of the fuel shutoff valve was removed to examine the shutoff valve. There was fuel-wetted debris present that obstructed the inlet elbow fuel fitting, as shown in figure 2. The fuel shutoff valve outlet port exhibited accumulated debris affixed to its inside diameter, as shown in figure 3. Additional debris was recovered from inside the fuel shutoff valve when tapped on a table, as shown in figure 4.
Figure 2. Inlet to fuel shutoff valve.
Figure 3. Outlet of fuel shutoff valve.
Figure 4. Fuel shutoff valve with debris from inlet port.
The fuel line from each wing fuel tank was disconnected and air was blown through the fuel line to the disconnected line at the fuel shutoff valve. Fuel and traces of debris were extracted from the left and right fuel lines. The recovered debris, as shown in figures 5 and 6, was consistent with the debris found in the inlet/outlet ports of the fuel shutoff valve. Borescope examination of the left- and right-wing fuel tanks revealed additional loose debris inside each fuel tank.
The NTSB Materials Laboratory used x-ray florescence analysis to identify the elemental composition of the debris recovered from the fuel shutoff valve and fuel lines. The debris consisted mostly of silicon, iron, and lead. Silicon and iron are consistent with soil. The presence of lead was consistent with transfer contact with fuel system components where leaded fuel, such as aviation 100 low-lead fuel, had been present.
Figure 5. Debris from left fuel line.
Figure 6. Debris from right fuel line.
The engine was displaced upwards, compressed aft into the firewall, and was rotated/twisted to the left side of the aircraft. The engine crankshaft did not rotate by hand through the propeller. The crankshaft was displaced aft about 0.5 inches, consistent with damage sustained during a nose-down impact. The removal of the rear accessories revealed additional damage to the accessory gears consistent with the entire crankshaft being displaced aft of its normal position.
Borescope examination of each cylinder revealed no anomalies with the cylinders, pistons, valves, valve seats, or bottom spark plugs. There were no mechanical failures observed during a borescope examination of the drivetrain components. There was evidence of ample oil in the crankcase, accessory gearbox, valve covers, and the oil filter. The spin-on type oil filter was removed, cut open, and exhibited no evidence of debris.
Both magnetos produced spark at all four leads when rotated by hand. The impulse coupling for each magneto functioned normally. The spark plugs exhibited features consistent with normal engine operation.
The carburetor separated from the engine during impact. Engine control continuity to the carburetor could not be established due to impact-related damage. The intake air box assembly remained attached to the carburetor but exhibited impact damage. The carburetor heat control cable separated from the intake air box.
The carburetor fuel inlet with inlet screen fractured from the carburetor body during impact and was not located during the investigation. The fuel line from the fuel strainer assembly to the carburetor was not located. The throttle valve did not rotate due to impact damage. The carburetor fuel bowl contained about 1 fluid ounce of uncontaminated 100 low-lead aviation fuel. There was no evidence of sediment or debris in the carburetor fuel bowl. The fuel metering float and float valve appeared intact and functional.
The engine examination revealed no evidence of a preexisting mechanical malfunction or failure that would have prevented normal operation.
The fixed-pitch 2-blade propeller remained attached to the engine crankshaft flange. One propeller blade exhibited a slight bend aft and in direction of blade rotation, and chordwise rotational scoring along the leading edge on the cambered side. The blade tip trailing edge exhibited gouge marks. The other propeller blade did not exhibit any remarkable bend/twist but had chordwise rotational scoring along the leading edge on the cambered side.
The Fort Bend County Medical Examiner's Office performed the flight instructor’s autopsy at the request of a Walker County Justice of the Peace. According to the flight instructor’s autopsy report, his cause of death was blunt force injuries and the manner of death was accident. FAA Forensic Sciences Laboratory toxicological testing of postmortem specimens from the flight instructor did not detect any carboxyhemoglobin, ethanol, glucose, or tested-for drugs.
The Fort Bend County Medical Examiner's Office performed the student pilot’s autopsy at the request of a Walker County Justice of the Peace. According to the student pilot’s autopsy report, his cause of death was blunt force injuries and the manner of death was accident. FAA toxicology testing did not detect any carboxyhemoglobin, ethanol, or glucose. The toxicology testing detected cetirizine at 24 ng/mL in cavity blood and at 631 ng/mL in urine. Metoprolol also was detected in cavity blood and urine.
Cetirizine is a second-generation antihistamine medication that is available over the counter and is commonly used to treat allergy symptoms. Cetirizine often carries a warning that users may experience drowsiness and should be careful when driving a motor vehicle or operating machinery. Data on sedation and psychomotor impairment from cetirizine are mixed, with some studies finding some sedating and impairing effects. The FAA states that pilots should wait 48 hours after using cetirizine before flying to allow time for the drug to be cleared from circulation.
Metoprolol is a prescription cardioselective beta-blocker medication that can be used as part of treatment for high blood pressure, certain arrhythmias, and certain types of heart failure. It sometimes also may be used for migraine headache prevention. Metoprolol is not generally considered impairing.
The student pilot’s mother stated that her son had been diagnosed with hypertension and in the weeks before the accident he began taking medication to lower his blood pressure. She noted no other concerns pertaining to the student pilot’s health.
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