NTSB CAROL · Event
Event CEN13FA066
Registry · N17SE
FAA Aircraft Registry record.
Make / Model
PILATUS AIRCRAFT LTD PC-12/47E
Year of manufacture
2011 · 1 years old at event
Engine
P&W CANADA PT6A-67P (1272 hp)
Seats / Engines
11 seats · 1 engine
Last airworthiness date
20111109
ADS-B equipped
Yes — Mode-S A11869
Registrant of record
BETA FLEET LLC
Source: FAA Aircraft Registry (releasable master file).
Aircraft involved
Probable cause & findings
The pilot’s loss of airplane control and inadvertent stall while attempting to return for landing.
Factual narrative
HISTORY OF FLIGHT
On November 21, 2012, about 1358 mountain standard time, a Brian P. North RAF SE5A replica experimental airplane, N17SE, owned by the pilot, was substantially damaged after impacting terrain near Watkins, Colorado. The certificated private pilot, the sole occupant, was fatally injured. The personal flight was conducted under the provisions of 14 Code of Federal Regulations Part 91, with no flight plan filed. Visual meteorological conditions prevailed. The flight departed Front Range Airport (FTG), Denver, Colorado, about 1355. While departing from Runway 26 at FTG, witnesses noticed the airplane climbing at a slow rate. On the downwind leg of the traffic pattern, witnesses noticed the airplane attempting to climb with a high pitch attitude. The pilot requested to return for a full stop landing from the air traffic control tower, due to “climb performance”. Witnesses observed the airplane enter a spiral descent while approaching the turn to base point of the pattern. The airplane impacted in a fallowed wheat field about 0.7 miles north of the Runway 26 threshold, and a post impact fire ensued.
PERSONNEL INFORMATION
The pilot, age 72, held a private pilot (foreign based) certificate with an airplane single-engine land rating. On May 3, 1999, the pilot was issued a Class 3 limited medical (foreign based) certificate, which required corrective lenses be worn. A review of records indicates the pilot had flown a total of 491 hours and 7 hours in the accident airplane. A friend of the pilot, who assisted with preflight actions on the day of the accident, stated that the pilot was in good health, both physically and mentally.
AIRCRAFT INFORMATION
The accident airplane was initially assembled by the pilot in the United Kingdom in 2008. After shipping the airplane to the United States and reassembling at FTG, an airworthiness certificate was issued by the Federal Aviation Administration (FAA) on May 17, 2012. Prior to the accident, the airplane flew four times at FTG, twice by the pilot and twice by his friend. The airplane had accumulated a total of 12 hours prior to the accident. The airplane was equipped with a 100-horsepower Continental Motors O-200A engine. The engine had accumulated 1,523 hours prior to being installed on the airplane and 12 hours after installation.
METEOROLOGICAL INFORMATION
The weather observing station at FTG reported the following conditions at 1350: wind 140 degrees at 5 knots, visibility 50 miles, clear skies, temperature 22 degrees Celsius, dew point minus 10 degrees Celsius, altimeter setting 29.95. Calculated density altitude for these conditions was 7,567 feet. During the four previous flights at FTG, calculated density altitude ranged from about 6,400 to 6,900 feet. The friend of the pilot, who piloted two of these four flights, stated that climb performance during these previous flights was satisfactory, with a climb rate between 400 and 450 feet per minute.
WRECKAGE AND IMPACT INFORMATION
The airplane impacted in a fallowed wheat field in a near vertical nose down spiral based on witness observations. On impact, the airplane continued to twist, coming to rest upright about 15 feet from the initial impact point, where the airplane caught fire and was destroyed. Located in the nose impact ground scar were fragmented propeller pieces. Propeller warping and tracking were not able to be examined due to impact damage. Flight control continuity was confirmed to all flight control surfaces. The engine was examined at a recovery location. The crankshaft was rotated by hand and mechanical continuity was established between the crankshaft and the camshaft; all of the rocker arms were observed to operate. A borescope inspection was performed on all the cylinders, with no signs of distress or abnormalities with any of the cylinder walls, pistons, or valves. All of the spark plugs were removed from the engine and displayed normal characteristics when compared to Champion Aviation Service Manual AV6-R. The #2 and #4 sparkplugs were oil soaked which was consistent with the orientation of the engine while at rest. It was noted that the #3 cylinder sparkplug electrodes appeared grayer in color when compared to the rest of the sparkplugs. The carburetor was disassembled and visually inspected; although thermally damaged, no abnormalities were noted. The oil filter was removed and cut open; the internal components sustained thermal damage, but exhibited no signs of metal deposits in the filter pleats. Due to the severity of thermal damage to the magnetos, the magneto internal and magneto engine timing was unable to be determined. Examination of the airframe, engine and propeller did not reveal any anomalies associated with a pre impact failure or malfunction.
MEDICAL AND PATHOLOGICAL INFORMATION
On November 28, 2012, an autopsy was performed on the pilot by the Adams & Broomfield Counties Coroner. The autopsy noted severe whole body burns and also identified that 3 vessels of the heart had 50% to 60% narrowing, but the heart muscle was unremarkable. The cause of death was attributed to whole body burns. The FAA's Civil Aeromedical Institute in Oklahoma City, Oklahoma, performed toxicology tests on the pilot. Zopiclone, which is a prescription medication used in the treatment of insomnia, was detected in the urine and also at trace levels in the blood. No other drugs or ethanol were detected. The pilot had requested to return to the airport for a full stop landing. According to a witness, the airplane appeared to be in a slow, labored climb in an abnormally high pitch attitude about 300 feet above the ground on the downwind leg in the traffic pattern. The airplane then entered a spiral descent while approaching the turn to base and impacted the ground about 0.7 miles north of the runway threshold; a postimpact fire ensued. Examination of the airplane and engine did not reveal any anomalies that would have precluded normal operation. The slow flight and high pitch followed by a spiral descent are indicative of an aerodynamic stall. Source: NTSB Aviation Accident Database Retrieved: 2026-02-12
NTSB Findings
Hierarchical cause / factor breakdown from the FAA bulk avdata database. Each finding tagged C (Cause) or F (Factor).
- C Aircraft-Aircraft oper/perf/capability-Performance/control parameters-(general)-Not attained/maintained - C
- C Personnel issues-Task performance-Use of equip/info-Aircraft control-Pilot - C
- — Environmental issues-Conditions/weather/phenomena-Temp/humidity/pressure-(general)-Contributed to outcome
Verbatim from NTSB's published report. Source file
NTSB_2012_CEN13FA066.txt.
Findings + structured fields enriched from FAA avall.mdb.
Full investigation docket on
data.ntsb.gov ↗.
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Related research
What the literature says.
Academic papers and agency reports matching this event's aircraft type or causal vocabulary (stall). Sourced from NASA NTRS, NTSB Safety Studies, FAA CAMI, AOPA Air Safety Institute, Embry-Riddle Scholarly Commons, arXiv, and the Semantic Scholar academic graph.
- NASA NTRS 2026 · Conference Paper
Computational Analysis of Steady State Aerodynamics of Transonic Truss-Braced Wing Configuration in Deep Stall
This study presents a computational investigation of steady state aerodynamics of the Subsonic Ultra-Green Aircraft Research (SUGAR) Transonic Truss-Braced Wing (TTBW) configuration over a wide range …
- arXiv 2023 · arXiv preprint
Automating Bird Diverter Installation through Multi-Aerial Robots and Signal Temporal Logic Specifications
This paper tackles the task assignment and trajectory generation problem for bird diverter installation using a fleet of multi-rotors.
- arXiv 2023 · arXiv preprint
Variation of Critical Crystallization Pressure for the Formation of Square Ice in Graphene Nanocapillaries
Two-dimensional square ice in graphene nanocapillaries at room temperature is a fascinating phenomenon and has been confirmed experimentally.
- arXiv 2023 · arXiv preprint
Polycrystallinity enhances stress build-up around ice
Damage caused by freezing wet, porous materials is a widespread problem, but is hard to predict or control. Here, we show that polycrystallinity makes a great difference to the stress build-up process…
- arXiv 2022 · arXiv preprint
Enhanced Prediction of Three-dimensional Finite Iced Wing Separated Flow Near Stall
Icing on three-dimensional wings causes severe flow separation near stall. Standard improved delayed detached eddy simulation (IDDES) is unable to correctly predict the separating reattaching flow due…
- Embry-Riddle Scholarly Commons 2021 · Journal article (JAAER)
Analysis on the Negative Emotional, Physiological, and Cognitive Responses Elicited from of the Activation of a Stall Alarm
Failing to identify an aerodynamic stall can lead to the inability of an aircraft to sustain flight. To warn pilots of an impending or fully-developed stall, many aircraft have safety devices installe…
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