NTSB CEN13FA066 — 2012-11-21 · Watkins, Colorado, United States

N17SE has since been reassigned. It is now registered to a different aircraft (PILATUS AIRCRAFT LTD PC-12/47E, built 2011), which was not involved in this event.

Aircraft involved

N17SE Brian P North RAF SE5A Replica Fatal

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

FAA avdata. C = Cause, 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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