N1401PAerofab LAKE LA-4-250 · 1984

On September 8, 2015, about 2048 eastern daylight time (EDT), an Aerofab Inc. Lake LA-4-250 amphibious airplane, N1401P, was destroyed when it impacted trees and terrain during a forced landing after takeoff from Somerset Airport (SMQ), Bedminster, New Jersey. The private pilot was fatally injured. Night visual meteorological conditions prevailed, and no flight plan was filed for the personal flight, which was conducted under the provisions of 14 Code of Federal Regulations Part 91.

The pilot was reported missing September 10, 2015, by coworkers, and a search by air and ground discovered the wreckage on the SMQ property about 1300.

According to the pilot's wife and his coworkers, he departed his office at 1700 on the day of the accident to recover his boat from a repair shop and return it to SMQ, where it shared hangar space with the accident airplane. A coworker estimated that, based on the time he departed the office, he would not reach SMQ until after 2000.

Multiple surveillance cameras around the terminal building and mounted on the pilot's hangar captured video on the night of the accident. Review of the video revealed that the pilot arrived at SMQ at 2022 (after sunset). He towed his airplane from its hangar, parked the boat inside, disconnected his vehicle from the boat trailer, and parked the vehicle outside the hangar at 2032.

The pilot then boarded his airplane, taxied away from the hangar at 2039, and departed runway 30 at 2048. Video from a camera located on the airport terminal captured a bright light travelling the opposite direction about 30 seconds after the takeoff. The light was seen descending approximately parallel to the runway in the wooded area that surrounded the accident site. The video faced toward the departure end of the runway and the wood line where the airplane came to rest. There were bright lights in the foreground, and the view beyond displayed very dark night conditions with little to no ambient lighting.

The NTSB Recorders Laboratory completed a day/night video overlay of the airport and the accident flight. The composite video product allowed for a comparison of the path of the airplane's light and the runway orientation.

According to Federal Aviation Administration (FAA) records, the pilot held a private pilot certificate with ratings for airplane single engine land and sea. He did not possess an instrument rating.

The pilot's most recent FAA third-class medical certificate was issued on September 8, 2015, and he reported 900 total hours of flight experience on that date. A pilot logbook was recovered, and entries began with 625 total hours of flight experience carried forward from a previous logbook. The pilot's total flight experience could not be reconciled due to incomplete entries; however, all entries appeared to reflect flight experience in the accident airplane.

The four-seat, single-engine, high-wing, retractable-gear, amphibious airplane was manufactured in 1984 and was equipped with a pylon-mounted Lycoming 250-horsepower reciprocating engine. According to the airplane's maintenance records, the most recent annual inspection was completed on April 27, 2015, at 1,612 total aircraft hours. The tachometer indicated 1,633 total aircraft hours at the accident site.

The airplane was configured with one main fuselage tank (40 gallons useable), two wing tanks (17 gallons each useable), and two wing-mounted auxiliary tanks (7 gallons each useable). Fuel was supplied to the engine from the main tank only. Fuel from the auxiliary tanks was supplied to the main tank by auxiliary fuel pumps. Fuel from the wing tanks to the main tank was gravity-fed through one-way valves.

The normal procedures checklist for the Supplemental Type Certificate (Installation of Wing Fuel Tanks) directs the pilot to check each tank for quantity and contamination:

2a. CHECK VISUALLY (DIPSTICK) FOR FUEL LEVEL. ANGLE DIPSTICK THROUGH AFT LIGHTNING HOLES INSIDE TANK.

2c. Fuel tank sump drain – DRAIN AND CHECK FOR CONTAMINATION

A fuel boost pump was actuated for takeoff and landing only. The engine-driven fuel pump provided fuel pressure to the engine in all other modes of flight.

According to airport and maintenance personnel, the pilot did not service the auxiliary tanks with fuel whenever he serviced the airplane.

The 2053 weather observation at SMQ included clear skies, calm winds, and 10 statute miles visibility. The temperature was 23° C, the dew point was 18° C, and the altimeter setting was 29.96 inches of mercury.

At the time of the accident, the moon was below the horizon with 19 percent of the visible disk illuminated.

The four-seat, single-engine, high-wing, retractable-gear, amphibious airplane was manufactured in 1984 and was equipped with a pylon-mounted Lycoming 250-horsepower reciprocating engine. According to the airplane's maintenance records, the most recent annual inspection was completed on April 27, 2015, at 1,612 total aircraft hours. The tachometer indicated 1,633 total aircraft hours at the accident site.

The airplane was configured with one main fuselage tank (40 gallons useable), two wing tanks (17 gallons each useable), and two wing-mounted auxiliary tanks (7 gallons each useable). Fuel was supplied to the engine from the main tank only. Fuel from the auxiliary tanks was supplied to the main tank by auxiliary fuel pumps. Fuel from the wing tanks to the main tank was gravity-fed through one-way valves.

The normal procedures checklist for the Supplemental Type Certificate (Installation of Wing Fuel Tanks) directs the pilot to check each tank for quantity and contamination:

2a. CHECK VISUALLY (DIPSTICK) FOR FUEL LEVEL. ANGLE DIPSTICK THROUGH AFT LIGHTNING HOLES INSIDE TANK.

2c. Fuel tank sump drain – DRAIN AND CHECK FOR CONTAMINATION

A fuel boost pump was actuated for takeoff and landing only. The engine-driven fuel pump provided fuel pressure to the engine in all other modes of flight.

According to airport and maintenance personnel, the pilot did not service the auxiliary tanks with fuel whenever he serviced the airplane.

The wreckage was examined at the accident site on September 11, 2015, and all major components were accounted for at the scene. There was no odor of fuel and no evidence of fuel spillage. The wreckage came to rest upright on flat wooded terrain. The wreckage path was 93 ft long, and oriented about 090 degrees magnetic. The initial impact was in trees about 50 ft above the ground, and the left wing and right wing auxiliary tanks were found between the first tree strike and the main wreckage. Several pieces of angularly-cut wood were found along the wreckage path.

The nose of the airplane faced approximately opposite the direction of travel. The cabin roof was separated to the aft cabin. The aft cabin, wing box structure, empennage, and tail section were collapsed and wrapped in a "U" shape such that the tail section rested immediately adjacent to the nose section. The empennage lay atop the right wing, while the engine pylon was fractured at its base, and lay adjacent to the left wing. The left and right wing tanks were both breached on impact, contained no residual fuel, and there was no evidence of fuel blighting of the vegetation surrounding the wreckage. Both auxiliary tanks were intact and contained no fuel.

The engine remained inside the nacelle, and the nacelle appeared intact and undamaged. The 3-bladed propeller displayed similar twisting, bending, leading-edge gouging, and chordwise scratching. Two blades displayed similar curling at the tips, and one blade tip was separated. The fracture surface displayed features consistent with overload.

During recovery of the airplane, flight control continuity was confirmed from the flight controls in the cockpit to all flight control surfaces. The aft fuselage, which contained the main fuel tank, was inverted for transport, and trace amounts of fuel drained from the vent lines. The main fuel tank was intact and contained no fuel.

Engine Examination

The engine was examined and placed in a test cell at the manufacturer's facility in Williamsport, Pennsylvania.

The top spark plugs were removed to visually inspect the cylinder condition and provide a thumb compression check. All cylinders were unremarkable, and all produced thumb compression. Mechanical continuity of the valve train was confirmed with hand rotation of the crankshaft via the crankshaft propeller flange. Magneto-to-engine timing was confirmed to be 25 degrees before top dead center in accordance with the data plate specification. All accessories not needed in the production test cell were removed, including the starter, alternator, vacuum pump, and oil cooler. The original fuel servo was installed and used for the test run.

The engine started immediately, accelerated smoothly, and ran continuously without interruption at all power settings.

Previous Flight Activity

A portable Garmin GPS unit was recovered from the wreckage and was forwarded to the NTSB Recorders Laboratory for examination and download. The batteries removed from the device were corroded, and no useful flight history data was recovered.

Based on a pilot logbook entry, fuel receipts, and data stored on a commercial flight-following website, the airplane completed a flight from SMQ to Yeager Airport (CRW), Charleston, West Virginia on August 16, 2015.

Before departing SMQ, the pilot purchased 51 gallons of fuel. It could not be determined if that fuel service filled all of the fuel tanks. The pilot purchased 45.5 gallons of fuel at CRW before the return flight. No fuel purchase was purchased at SMQ after the return flight, and the usage of the airplane between August 16, 2015 and the day of the accident could not be determined.

The commercial flight-following website captured only a portion of the flight between SMQ and CRW and did not capture the return flight. Interpolation of the radar data, performance data, and the fuel purchase at CRW revealed an approximate fuel consumption rate of 15 gallons per hour (gph), which was consistent with available performance data for the airplane.

A Shadin fuel flow indicator was removed from the airplane and sent to the NTSB Recorders Laboratory for examination. The panel-mounted gauge acted as a digital fuel management system, and had capabilities to interface with other devices via a RS-232 serial connection. It provided endurance (time), fuel flow (gph), fuel used (gallons), and fuel remaining (gallons) when the operator set the initial fuel level correctly before starting the engine. The system included a non-volatile memory that retained fuel remaining and fuel used information when power to the unit was removed.

Power was applied, the self-test report was "good," and the gallons-used display showed 44.7 gallons, and the gallons-remaining display showed 21.0 gallons, for an approximate total of 66 gallons. The fuel values displayed could not be directly attributed to a specific flight before the accident flight..

A review of the pilot's logbook revealed that the pilot recorded the flight to CRW, and the return flight to SMQ, as a single entry of 7.45 hours.

The Office of the State Medical Examiner, Newark, New Jersey, performed the autopsy on the pilot and noted the cause of death as blunt traumatic injuries.

Toxicological testing was performed on the pilot by the FAA Bioaeronautical Sciences Research Laboratory, Oklahoma City, Oklahoma. The results were negative for any tested-for substances.