N8615Z

HISTORY OF FLIGHTOn September 18, 2015, about 0855 eastern daylight time, a Cessna U206E amphibious airplane, N8615Z, collided with terrain near Spring Hill, Florida. The commercial pilot was fatally injured and the airplane was substantially damaged. The airplane was registered to Keystone Seaplane, LLC, Odessa, Florida, and operated by the pilot as a 14 Code of Federal Regulations Part 91 personal flight. Instrument meteorological conditions prevailed at the time of the accident, and an instrument flight rules (IFR) flight plan was filed for the flight, which departed Page Airport (FMY), Fort Myers, Florida, about 0727.

A review of air traffic control communications provided by the Federal Aviation Administration (FAA) revealed the pilot's original flight plan was from FMY to the Lake Keystone Seaplane Base (57FL), Odessa, Florida, where the airplane was based. When the pilot arrived near 57FL, he told air traffic control that he had the seaplane base in sight and cancelled his IFR flight plan at 0833. A review of radar data revealed that the airplane then made a series of turns in the vicinity of the seaplane base before the pilot requested an IFR clearance to the Brooksville-Tampa Bay Regional Airport (BKV), Brooksville, Florida. The pilot was cleared by air traffic control for the ILS RWY 9 instrument approach into BKV. Radar data revealed that the airplane was established on the approach until reaching the final approach fix, when it descended below the glideslope and radar contact was lost about 1 mile from the airport. There were no distress calls from the pilot. The last recorded radar return indicated the airplane was at an altitude of 625 ft mean sea level (msl) and a ground speed of 68 knots.

A handheld Garmin GPS 796 unit was located in the wreckage. Data downloaded from the unit revealed the airplane departed FMY about 0726:40, proceeded to Keystone Lake, circled the area for several minutes before proceeding to and executing the instrument approach into BKV. The last GPS data point was recorded at 0851:22, about 4 minutes before the accident. At that time, the airplane was on a heading of 081° at 2,121 ft msl and a ground speed of 95 knots.

Several witnesses observed the airplane right before it impacted the ground. One witness stated that he first heard the airplane's engine "cut out." When he looked up, he saw the airplane come out of the clouds and it "started to spiral down" over his house. The airplane then veered to the north before the sound of an impact was heard. A second witness said he heard the airplane approaching and the engine "got extremely loud, almost at full throttle" just before it came into his view. The witness said the airplane was at an "extremely angled," nose-down pitch attitude and was descending at a high speed. He did not see the impact due to trees. PERSONNEL INFORMATIONThe pilot held a commercial pilot certificate with ratings for airplane single-engine land, single-engine sea, and instrument airplane. His most recent FAA second-class medical certificate was issued on August 11, 2014. A review of the pilot's logbook revealed that as of September 17, 2015, he had accrued a total of 559 flight hours, of which 320.7 hours were in the accident airplane make and model. He also had 55.5 hours of simulated instrument time, and 15.8 hours of actual instrument experience. In the 6 months preceding the accident, the pilot logged 3.0 hours of actual instrument time, of which 1.8 hours were logged two days before the accident while receiving instruction for his instrument flight instructor rating. The instruction included holding procedures and six instrument approaches. He also logged 5.8 hours of simulated instrument time in the 6 months preceding the accident, which included navigation and standard terminal arrival routes. AIRCRAFT INFORMATIONThe accident airplane was a float-equipped Cessna U206E. It was a six-seat, high-wing airplane that was powered by a Continental Motors IO-550F, 300 hp, six-cylinder engine equipped with a three-bladed McCauley propeller. The airplane's last annual inspection was completed on August 12, 2015, at an airframe total time of 2,898 hours. The engine had a total of 301 hours since factory overhaul. METEOROLOGICAL INFORMATIONThe weather conditions reported at BKV at 0853, included wind from 030° at 6 knots, visibility 10 statute miles, overcast ceiling 500 ft (variable between 400 and 800 ft), temperature 24° C, dew point 22° C, and an altimeter setting of 29.84 inches of Hg. AIRPORT INFORMATIONThe accident airplane was a float-equipped Cessna U206E. It was a six-seat, high-wing airplane that was powered by a Continental Motors IO-550F, 300 hp, six-cylinder engine equipped with a three-bladed McCauley propeller. The airplane's last annual inspection was completed on August 12, 2015, at an airframe total time of 2,898 hours. The engine had a total of 301 hours since factory overhaul. WRECKAGE AND IMPACT INFORMATIONThe airplane came to rest in the backyard of a private residence. All major components of the airplane were accounted for at the site, and there was no postimpact fire. The point of initial impact was a stand of trees that were about 80 ft tall. The airplane then collided with a fence and the ground before coming to rest about 75 ft from the initial impact point. Severed tree limbs, the left elevator, the left elevator tip fairing, a tire, and a propeller blade were scattered along the wreckage path. The main wreckage included the propeller, engine, fuselage, tail section, and both pontoons. Several of the severed tree limbs exhibited flat, 45° cut surfaces with black paint transfer.

Examination of the main wreckage revealed it was twisted, crushed, and partially lying on its right side. Flight control continuity was established for all major flight control surfaces. The flaps were fully retracted and the wheels were extended. The elevator trim tab was in the 10° down position.

The left wing remained attached to the fuselage and sustained impact damage. The fuel tank was breached, and first responders reported fuel draining from the wing upon their arrival at the scene. The right wing also sustained impact damage and had separated from the fuselage at the wing root. First responders reported fuel draining from the right wing's tank; in addition, about 5 gallons of 100LL fuel were drained during the recovery process. The two header tanks appeared to be undamaged. The fuel selector valve was selected to the right tank. The firewall fuel strainer remained attached to the firewall and the bowl was full of fuel. Some fuel was also found in the engine-driven fuel pump and fuel manifold valve. No evidence of water or contamination was observed. According to a fuel provider at FMY, the airplane was topped off with 36.5 gallons of 100LL fuel the day before the accident.

The engine remained partially attached to the airframe by control cables, and the three-bladed propeller had separated from the engine at its hub. The spinner exhibited rotational damage. One blade had separated from the propeller hub and was found in the initial impact crater. The blade was bent forward. The other two blades remained in the hub, which was located about 4-ft from the fuselage. The second and third blades were twisted.

The engine crankcase sustained impact damage to the lower forward area and was leaking oil. The top spark plugs were removed and exhibited normal wear as per the Champion Check-A-Plug chart. The rocker covers were removed and the engine was manually rotated. Compression and valve train continuity was established on all but the No. 6 cylinder. Further examination revealed the push rod and push rod tube for the No. 6 cylinder was impact-damaged.

The left magneto remained attached to the engine; however, the right had separated from its mounting pad and remained attached via the ignition leads. When the engine was rotated, spark was produced to each of the left magneto's ignition leads. An electric drill was used to spin the right magneto, and spark was produced to each ignition lead.

The fuel manifold valve was removed from the engine and disassembled. A small amount of fuel was in the valve and the diaphragm was intact. The fuel screen was absent of debris. Although the No. 1 injector sustained some impact damage, each of the injectors were removed from the engine and found absent of debris. The fuel pump was removed from the engine and fuel was present in the pump. The pump rotated freely when turned and the drive coupling was intact. The throttle body and metering unit were absent of debris and the throttle body moved freely when the throttle arm was moved manually.

The vacuum pump was removed and disassembled. The pump rotated smoothly and the carbon vanes were intact. The interior of the drum was absent of any rotational scoring.

The oil pump remained attached to the engine. The oil pressure relief valve was removed and inspected. The plunger and spring were intact. The valve seat was inspected, and no damage was noted. The oil filter was removed and the filament was removed. It was absent of debris. The oil sump and cooler sustained impact damage.

The propeller governor remained attached to the engine, but sustained impact damage. The control arm was in the full forward position.

Physical examination of the engine revealed there were no discrepancies that would have precluded normal operation prior to impact.

The airplane was equipped with a J.P. Instruments (JPI) EDM-930 engine monitor. The data downloaded from the unit included the accident flight and began at 0713:02 and ended at 0855:13. Eleven engine parameters were recorded every six seconds. These parameters included exhaust gas temperature, cylinder heat temperature, oil pressure and temperature, manifold pressure, outside air temperature, turbocharger inlet temperature, engine rpm, fuel remaining and fuel used, fuel flow, and battery voltage/current. The data was plott...