NTSB Factual Report

On August 18, 2002, about 0936 eastern daylight time, a homebuilt Reviere Vans RV6A, N747ES, registered to, and operated by an individual, impacted with a concrete wall of a dry dock at the Port of Tampa, Tampa, Florida. Visual meteorological conditions prevailed at the time, and no flight plan was filed. The local personal flight was conducted under 14 CFR Part 91. The airplane was destroyed. The private-rated pilot in command and commercial-rated second pilot were fatally injured. There were no injuries to anyone on the ground. The flight had originated from the Peter O'Knight Airport, Tampa, Florida, at 0925.

According to witnesses at the airport, the flight departed on runway 17, and about 1 mile from the airport, the flight turned 180 degrees, and headed downwind back to the airport in line with runway 35. The witnesses thought the flight appeared to be landing; however, the airplane stayed about 25 to 50 feet above the runway, they heard power being applied, the airplane started a steep climb. Initially, the aircraft started to go into a left turn, but then turned right, over the water. The flight was then observed going into a steep spiral descent and crashing. There was no smoke observed coming from the airplane prior to the crash.

According to the FAA inspector's statement, the pilot topped off both of N747ES's fuel tanks with 33.3 gallons of 1OO low lead (LL) fuel, the morning of August 18, 2002, at Plant City, Florida. The weight of the aircraft during the accident flight sequence could not be positively determined. The available aircraft records showed the gross weight as 1,850 pounds. The last known weight of the pilot was 280 pounds and his passenger was 200 pounds. The estimated gross weight of the airplane at takeoff was 1,824 pounds, without any consideration of any baggage that may have been on board.

The engine was examined under the supervision of the FAA, on August 22, 2002, and revealed that the engine with the aircraft firewall assembly had separated from the airframe. The engine had sustained impact and postimpact fire damage. Impact damage was noted to be more severe on the front right and bottom sections. The engine did not display any external indications of mechanical failure or malfunction. The oil sump was crushed. The propeller had separated from the engine, the propeller hub remained attached to the engine crankshaft flange, the crankshaft was fractured aft of the flange. One propeller blade was torn in two places. About two inches of tip material was not located or recovered. About ten inches of span material was torn at both sides and exhibited torsional twisting. The inboard section of blade, was bent aft about twenty-four inches. The opposite blade was bent aft slightly and exhibited signs of rotation, leading edge damage and chord wise scoring. The propeller governor had separated and displayed fire damage. The control mechanism was destroyed. The fractured surfaces of the crankshaft displayed signs of torsional overload. Impact damage to the front right number 1 cylinder assembly was noted; the cylinder head, rocker box and push rods were displaced. Multiple cracks along the front right quadrant of the engine crankcase were observed, including areas between the number 1 and 3 cylinders. Crankshaft rotation was not obtainable due to the extent of damage. Accessory components were impact separated and fire damaged. Each component was individually examined, no discrepancies were noted. Disassembly examination of the engine was accomplished which revealed no discrepancies. Internal engine continuity was established. All internal components of the power section, including crankshaft, camshaft, gears and valve train remained connected.

An autopsy was performed on both pilots, at the Hillsborough County Medical Examiner's Office, Tampa, Florida, on August 19, 2002. According to the autopsy report the cause of death was "...Multiple...Blunt Impacts to head and torso." No significant pre-existing disease was noted on the autopsy.

Toxicological tests were conducted on the second pilot at the Federal Aviation Administration, Research Laboratory, Oklahoma City, Oklahoma, and revealed that, "No ethanol or drugs were detected. "

Toxicological tests were conducted on the pilot-in-command (PIC) at the Federal Aviation Administration, Research Laboratory, Oklahoma City, Oklahoma, and revealed, "No ethanol was detected. The following drugs were detected: NORTRIPTYLINE present in Urine 0.117 (ug/ml, ug/g); NORTRIPTYLINE detected in Blood; PAROXETINE present in Urine 0.579 (ug/mL, ug/g); PAROXETINE detected in Blood; Amitriptyline present in Urine 0.052 (ug/ml, ug/g); Amitriptyline detected in Blood.

Amitriptyline is a prescription antidepressant also known by the trade name Elavil. Paroxetine is a prescription antidepressant often known by the trade name Paxil.

The pilot did not indicate the use of medications or a history of migraine headaches on his last application for Airman Medical Certificate; however, in a phone conversation with the NTSB investigator-in-charge, on October 30, 2003, the pilot's brother revealed that the pilot had been treated for migraine headaches, and had been on medication to treat the headaches for a number of years. The FAA's 1999 Guide for Aviation Medical Examiners notes (page 70) "...the use of a psychotropic drug is considered disqualifying. This includes all sedatives, tranquilizers, antipsychotic drugs, antidepressant drugs, analeptics, anxiolytics, and hallucinogens." The Guide also indicates (page 63) that a history or the presence of migraine headaches precludes the issuance of a medical certificate.

NTSB Probable Cause

the failure of the pilot to maintain airspeed, which resulted in an inadvertent stall/spin, while maneuvering, and subsequent impact with a concrete wall. A factor in this accident was the impairment of the pilot in command due to the use of prescription drugs.