Paul D. Bessler
Paul Douglas Bessler, 42, of Crown Point, New York, passed away December 23, 2016 doing what he loved — flying. Paul was a veteran of the United States Air Force. He was a devoted father, husband, brother and son. He was an integral part of his community and loved to talk to and help people. He was his brother’s hero and a friend to all who knew him. Paul had many accomplishments with all his knowledge of planes. He always had a joke and a smile.
The National Transportation Safety Board traveled to the scene of this accident.
Additional Participating Entities:
Federal Aviation Administration / Flight Standards District Office; Portland, Maine
Lycoming Engines; Atlanta, Georgia
Investigation Docket - National Transportation Safety Board: https://dms.ntsb.gov/pubdms
http://registry.faa.govN31202
Location: Middlebury, VT
Accident Number: ERA17FA072
Date & Time: 12/23/2016, 1145 EST
Registration: N31202
Aircraft: PIPER PA28
Aircraft Damage: Substantial
Defining Event: Loss of engine power (partial)
Injuries: 1 Fatal
Flight Conducted Under: Part 91: General Aviation - Personal
On December 23, 2016, about 1145 eastern standard time, a Piper PA-28-161 airplane, N31202, was substantially damaged when it impacted trees and terrain while maneuvering after takeoff from Middlebury State Airport (6B0), Middlebury, Vermont. The private pilot was fatally injured. The airplane was registered to PC Air Ventures Ltd and operated by the pilot under the provisions of Title 14 Code of Federal Regulations Part 91. Visual meteorological conditions prevailed, and no flight plan was filed for the local personal flight that was originating when the accident occurred.
According to a witness at the airport, the airplane was based at 6B0 and had not been flown during the past 2 months. The witness reported that the pilot arrived at the airport about 0815, cleared snow from the airplane's wings, put a battery charger on the battery, and plugged in the engine heater. The pilot then performed a preflight inspection and drained fuel samples from the fuel tanks. About 1135, the pilot taxied the airplane to runway 19 and departed. During the initial climb, about 150 ft above ground level, the airplane's wings "wagged." The airplane climbed about another 150 ft, and the engine "skipped" and then "went back to normal." The airplane continued to climb, made a slight right turn, and then entered a left turn. When the bank angle was about 45°, the airplane "stalled" and "rapidly" descended until it struck trees.
Another witness, who was at a business about 500 ft south of the departure end of runway 19, heard an engine "sputtering" and looked up and saw the airplane flying south. The airplane "then looped in a counter-clockwise direction" and headed north. The witness could not hear any engine noise from the airplane as it descended "at a fast rate" and collided with a tree. When the witness ran to the accident site, he smelled fuel and saw that a fire had erupted. The witness cut the pilot's seatbelt and pulled him from the airplane.
Pilot Information
Certificate: Private
Age: 42, Male
Airplane Rating(s): Single-engine Land
Seat Occupied: Left
Other Aircraft Rating(s): None
Restraint Used: Lap Only
Instrument Rating(s): None
Second Pilot Present: No
Instructor Rating(s): None
Toxicology Performed: Yes
Medical Certification: Class 3 None
Last FAA Medical Exam: 08/06/2009
Occupational Pilot: No
Last Flight Review or Equivalent:
Flight Time: 750 hours (Total, all aircraft)
According to Federal Aviation Administration (FAA) records, the pilot held a private pilot certificate with an airplane single-engine land rating. The pilot was issued a third-class medical certificate on August 6, 2009, with no limitations; this medical certificate expired on August 31, 2014. At that time, he reported 750 hours of total flight experience of which 54 hours were within the previous 6 months. In addition, the pilot held an airframe and powerplant mechanic certificate as well as an inspection authorization.
Aircraft and Owner/Operator Information
Aircraft Manufacturer: PIPER
Registration: N31202
Model/Series: PA28 161
Aircraft Category: Airplane
Year of Manufacture: 1978
Amateur Built: No
Airworthiness Certificate: Normal; Utility
Serial Number: 28-7816552
Landing Gear Type: Tricycle
Seats: 4
Date/Type of Last Inspection: 06/14/2016, Annual
Certified Max Gross Wt.: 1502 lbs
Time Since Last Inspection: 10 Hours
Engines: 1 Reciprocating
Airframe Total Time: 8582 Hours as of last inspection
Engine Manufacturer: LYCOMING
ELT: Installed, not activated
Engine Model/Series: O-320 SERIES
Registered Owner: PC AIR VENTURES LTD
Rated Power: 160 hp
Operator: PC AIR VENTURES LTD
Operating Certificate(s) Held: None
According to FAA records, the airplane was issued an airworthiness certificate on April 10, 1978. The 4-place airplane was equipped with a Sensenich fixed-pitch propeller and a 160-horsepower Lycoming O-320 engine. According to the airplane's maintenance logs, an annual inspection was performed on the airplane on June 14, 2016, at a total time of 8,582.0 hours. According to a witness, the airplane had been flown about 10 hours since the annual inspection was performed in June 2016.
The most recent fueling of the airplane at 6B0 was 15 gallons of 100LL aviation fuel on May 26, 2016.
According to the Pilot Operating Handbook (POH), the airplane was equipped with two 25-gallon fuel tanks. A drain was located at the bottom, inboard, rear corner of each fuel tank, and a fuel strainer with a drain was located on the lower left front of the firewall.
According to the "Handling, Servicing, and Maintenance" section of the POH, the fuel tank drains and the strainer should be drained daily before the first flight and after refueling to avoid the accumulation of contaminants such as water or sediment. The fuel strainer should be drained twice, once with the fuel selector valve on each tank. Each time fuel was drained, sufficient fuel should be allowed to flow to ensure removal of contaminants.
Meteorological Information and Flight Plan
Conditions at Accident Site: Visual Conditions
Condition of Light:Day
Observation Facility, Elevation: 6B0, 490 ft msl
Observation Time: 1135 EST
Distance from Accident Site: 0 Nautical Miles
Direction from Accident Site:
Lowest Cloud Condition: Scattered / 3200 ft agl
Temperature/Dew Point: 3°C / -3°C
Lowest Ceiling: None
Visibility: 10 Miles
Wind Speed/Gusts, Direction: 11 knots/ 14 knots, 180°
Visibility (RVR):
Altimeter Setting: 30.26 inches Hg
Visibility (RVV):
Precipitation and Obscuration: No Obscuration; No Precipitation
Departure Point: Middlebury, VT (6B0)
Type of Flight Plan Filed: None
Destination: Middlebury, VT (6B0)
Type of Clearance: None
Departure Time: 1145 EST
Type of Airspace:
The 1135 recorded weather observation at 6B0 included wind from 180° at 11 knots gusting to 14 knots, visibility 10 miles, scattered clouds at 3,200 ft above ground level, temperature 3°C, dew point -3°C, and altimeter setting 30.26 inches of mercury.
Airport Information
Airport: MIDDLEBURY STATE (6B0)
Runway Surface Type: Asphalt
Airport Elevation: 490 ft
Runway Surface Condition: Dry
Runway Used: 19
IFR Approach: None
Runway Length/Width: 2500 ft / 50 ft
VFR Approach/Landing: Unknown
6B0 was a public use airport located 3 miles southeast of Middlebury and did not have an operating control tower. It had one runway, runway 1/19, which was 2,500 ft long by 50 ft wide. The airport elevation was 490 ft above mean sea level.
Wreckage and Impact Information
Crew Injuries: 1 Fatal
Aircraft Damage: Substantial
Passenger Injuries: N/A
Aircraft Fire: On-Ground
Ground Injuries: N/A
Aircraft Explosion: None
Total Injuries: 1 Fatal
Latitude, Longitude: 43.981389, -73.094444 (est)
The airplane came to rest in an upright position about 300 ft from the departure end of runway 19. Pieces of tree branches that exhibited 45°-angle cuts and dark paint transfer were located along the debris path. The main wreckage was oriented on a 347° magnetic heading, the debris path was oriented on a 360°magnetic heading, and measured about 160 ft in length. All major components of the airplane were accounted for at the scene. The fuselage remained intact but was heavily damaged by impact forces and a postimpact fire. Flight control continuity was confirmed from all flight control surfaces to the cockpit through multiple control cable fractures that were consistent with overload. The fuel tanks were breeched; the left fuel tank exhibited thermal damage, and the right fuel tank exhibited heavy impact damage. The right fuel cap remained seated but the gasket exhibited cracking, and the left fuel cap remained seated but was thermally damaged.
The engine remained attached to the airframe through all but one engine mount and was removed to facilitate further examination. Engine crankshaft continuity was confirmed from the propeller flange to the rear accessory section of the engine. All cylinders remained attached to the crankcase. The rocker box covers were removed, and no anomalies were noted with the valve springs and rocker arms. Valve train continuity was confirmed when the crankshaft was rotated. The cylinders were examined with a borescope, and no anomalies were noted with the cylinders, pistons, and valves. Piston movement and thumb compression was observed on all cylinders. Both magnetos remained attached to the engine. The magnetos were removed, and sparks were observed on all towers when they were rotated by hand. The top spark plugs were removed, and their electrodes were dark gray in color consistent with the Champion Check-A-Plug chart.
The engine-driven fuel pump was removed and disassembled. The fuel pump expelled liquid that was consistent in odor with 100LL aviation fuel when the arm was actuated by hand. No debris was noted in the liquid. There were no anomalies noted with the fuel pump. Fuel was noted in the fuel line to the carburetor. The carburetor box was impact damaged. The carburetor was impact separated from the engine but remained attached through cables. The carburetor was disassembled, and no liquid was noted in the fuel bowl. The carburetor floats exhibited damage consistent with hydraulic deformation. Debris that was like the dirt at the accident site was noted in the carburetor. The carburetor inlet fuel screen was removed, and no debris was noted.
The propeller was separated from the engine and located about 20 ft forward of the main wreckage. Both blades exhibited slight S-bending and chordwise scratching.
Medical And Pathological Information
The Vermont State Department of Health's Office of the Chief Medical Examiner, Burlington, Vermont, performed the autopsy on the pilot. The autopsy report indicated that the pilot died as a result of multiple blunt impact injuries.
The FAA's Bioaeronautical Sciences Research Laboratory, Oklahoma City, Oklahoma, performed toxicological testing of the pilot. Fluid specimens from the pilot tested negative for carbon monoxide and ethanol. Levetiracetam was detected in urine and blood, and tramadol was detected in urine but not in blood.
Levetiracetam is an anticonvulsant prescription medication used to treat certain types of seizures in adults and children with epilepsy. This medication is disqualifying for FAA aeromedical certification. Tramadol is an opiate analgesic prescription medication used to relieve moderate to moderately severe pain. This medication has abuse potential and has the potential to impair the mental and/or physical ability required for the performance of potentially hazardous tasks such as driving, flying, and operating heavy machinery.
Medical records obtained from the Department of Veterans Affairs (VA) revealed that the pilot was first diagnosed with epilepsy in 1996. The pilot had been maintained on levetiracetam since 2010 without a complaint about somnolence. Then, in August 2015, he had a series of three seizures on the same day. He was prescribed levetiracetam twice a day to control the seizures and told not to drive a car for 6 months after this event. The pilot reported no further seizures to his VA providers through his last appointment, dated December 14, 2016.
Additional Information
Emergency Procedures - Engine Power Loss During Takeoff Checklist
According to the emergency procedures section of the POH, the following steps should be performed in the event of an engine power loss during takeoff:
If insufficient runway remains:
Maintain safe airspeed
Make only shallow turn to avoid obstructions
Flaps as situation requires
FAA Safety Team – Aircraft Control After Engine Failure on Takeoff
A pamphlet published by the FAA Safety Team titled, "Aircraft Control After Engine Failure on Takeoff," stated, in part: "Studies have shown that startle responses during unexpected situations such as a powerplant failure during takeoff or initial climb have contributed to loss of control of aircraft…Research indicates a higher probability of survival if you continue straight ahead following an engine failure after takeoff. Turning back actually requires a turn of greater than 180 degrees after taking into account the turning radius. Making a turn at low altitudes and airspeeds could create a scenario for a stall/spin accident."
NTSB Identification: ERA17FA072
14 CFR Part 91: General Aviation
Accident occurred Friday, December 23, 2016 in Middlebury, VT
Aircraft: PIPER PA28, registration: N31202
Injuries: 1 Fatal.
This is preliminary information, subject to change, and may contain errors. Any errors in this report will be corrected when the final report has been completed. NTSB investigators either traveled in support of this investigation or conducted a significant amount of investigative work without any travel, and used data obtained from various sources to prepare this aircraft accident report.
On December 23, 2016, about 1145 eastern standard time, a Piper PA-28-161, N31202, was substantially damaged after it impacted trees and terrain during the initial climb from Middlebury State Airport (6B0), Middlebury, Vermont. The private pilot was fatally injured. Visual meteorological conditions prevailed, and no flight plan was filed for the local flight. The personal flight was conducted under the provisions of 14 Code of Federal Regulations Part 91.
According to a witness, the airplane was not flown during the past 2 months. The pilot cleared off snow from the airplane's wings the morning of the flight and preheated the airplane. He then performed a preflight inspection and sumped the fuel tanks. The pilot taxied the airplane to runway 19 and departed. During the initial climb, about 150 feet above ground level (agl), the airplane's wings "wagged," the engine "skipped," and then the engine sound "went back to normal." The airplane continued to climb, it made a slight right turn, and then entered a left turn. When the angle of bank was about 45-degrees, the airplane "stalled," and "rapidly" descended until it struck trees. Another witness stated the engine "sputtered" several times, and that after the airplane struck the ground, a postimpact fire erupted.
According to Federal Aviation Administration (FAA) records, the pilot held a private pilot certificate with a rating for airplane single-engine land. The pilot was issued a third-class medical certificate on August 6, 2009, with no limitations. At that time, he reported 750 hours of total flight time, of which 54 hours were within the previous 6 months. In addition, the pilot held an airframe and powerplant certificate with an inspection authorization.
According to FAA records, the four-place airplane was issued an airworthiness certificate on April 10, 1978, and was registered to a corporation. It was equipped with a Lycoming O-320 series, 160-horsepower engine with a Sensenich fixed-pitch propeller. According to airplane maintenance logbooks, an annual inspection was performed on June 16, 2016, at a total time in service of 8,582 hours.
The airplane impacted trees, the ground, and came to rest in an upright position about 300 feet from the departure end of runway 19. The main wreckage was oriented on a 347-degree magnetic heading, the debris path was oriented on a 360-degree magnetic heading, and was approximately 160 feet in length. All major components of the airplane were accounted for at the scene. The fuselage remained intact but was heavily damaged by impact forces and a postimpact fire. Flight control continuity was confirmed from all flight control surfaces to the cockpit through multiple control cable fractures that were consistent with overload. The fuel tanks were breeched; the left fuel tank exhibited thermal damage, and the right fuel tank was heavily impact damaged.
The engine remained attached to the airframe through all but one engine mount and was removed to facilitate further examination. Engine crankshaft continuity was confirmed from the propeller flange to the rear accessory section of the engine. All cylinders remained attached to the crankcase. The rocker box covers were removed and no anomalies were noted with the valve springs and rocker arms. Valvetrain continuity was confirmed when the crankshaft was rotated. The cylinders were examined with a borescope and no anomalies were noted with the cylinders, pistons, and valves. Piston movement and thumb compression was observed on all cylinders. Both magnetos remained attached to the engine. Each were removed, and sparks were observed on all towers, when they were rotated by hand. The top spark plugs were removed and their electrodes were dark gray in color.
The engine driven fuel pump was removed and disassembled. The fuel pumped liquid that was consistent in odor with 100LL aviation fuel when the arm was actuated by hand. No debris was noted in the liquid. There were no anomalies noted with the fuel pump. Fuel was noted in the fuel line to the carburetor. The carburetor box was impact damaged. The carburetor was impact separated from the engine but remained attached through cables. The carburetor was disassembled and no liquid was noted in the fuel bowl. However, the carburetor floats exhibited damage consistent with hydraulic deformation. Debris, similar to the terrain at the accident site, was noted in the carburetor. The carburetor inlet fuel screen was removed and no debris was noted.
The 1135 recorded weather observation at 6B0 included wind from 180 degrees at 11 knots, gusting to 14 knots, visibility 10 statute miles, scattered clouds at 3,200 feet agl, temperature 3 degrees C, dew point -3 degrees C; and an altimeter setting of 30.26 inches of mercury.
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