N2371N

HISTORY OF FLIGHT

On January 5, 2002, at 1703 eastern standard time, a Cessna 172R, N2371N, registered to National Aviation Holdings, Inc., and operated by a student pilot for the purpose of committing suicide, collided in-flight with the Bank of America Bank Building in Tampa, Florida. The unauthorized flight was operated under the provision of Title 14 CFR Part 91, and visual flight rules. Visual meteorological conditions prevailed and no flight plan was filed. The student pilot received fatal injuries and the airplane was destroyed. The flight departed St. Petersburg-Clearwater International Airport, St. Petersburg, Florida, at 1651.

According to the student pilot's flight instructor, the student was instructed to preflight the airplane and wait on the instructor before beginning his flight training. Witnesses stated that the student pilot proceeded to the airplane, removed the tie downs, started the airplane, and immediately taxied to runway 35R, and took off without communicating with the Air Traffic Control Tower. The controllers stated that after takeoff the airplane turned right to the southeast. The tower controllers notified Tampa approach and a Coast Guard Helicopter flying in the local area. Additionally, the controllers attempted to contact the pilot via radio frequency 121.5, but were unsuccessful. The Coast Guard Helicopter was asked to intercept the airplane. The airplane proceeded to Mc Dill Air Force Base, over flying the control tower by just a few feet, over flew two aircraft on the runway, and three hangars on the base before proceeding to the Bank of America Building. While enroute to the Bank of America Building the Coast Guard Helicopter intercepted the airplane and attempted to get the pilot to land. According to the Coast Guard Helicopter pilots, they believed the student pilot saw their hand gestures and gestured back, however, the Coast Guard pilots could not determine what kind of gestures the student pilot was making. Shortly there after, the airplane collided with the bank building imbedding itself into the 28th floor.

PERSONNEL INFORMATION

The student pilot held a third class medical dated November 17, 2001. The pilot had accumulated about 19.3 total hours of dual instructional flight time beginning with his first lesson on May 17, 1998. However, the majority of the students training was gained beginning in February of 2001, and continued once or twice each month until the time of the accident. A two page note was found on the pilots person indicating his intention to commit suicide.

AIRCRAFT INFORMATION

The Cessna 172R, N2371N, S/N 17280838, was a four (4) seat, single engine airplane, and was registered to National Aviation Holding, Inc. Clearwater, Florida. The airplane's most recent maintenance inspection was a phase one, which was completed on December 27, 2001. The airplane had accumulated 15.8 hours of operation since that inspection and had a total time of 1,721.3 hours.

METEOROLOGICAL INFORMATION

Visual meteorological conditions prevailed at the time of the accident. Weather conditions were reported at Tampa International at 1736, as; scattered clouds at 500 feet, broken clouds at 2500 feet, visibility 10 statute miles, wind calm, and altimeter setting at 30.15 millimeters of mercury.

WRECKAGE AND IMPACT INFORMATION

The airplane impacted the 28th floor of the Bank of America building in downtown Tampa, Florida. The airplane had been removed from the building prior to the arrival of this investigator. The airplane had been cut into sections and taken to a hangar at the Peter O'Knight Airport in Tampa, Florida. An inspection of the airplane was performed on January 7, 2002. No evidence of fire was observed. All flight controls were accounted for during the review. The left and right wings were separated from the fuselage. The left and right main landing gear remained attached to the fuselage.

The left wing was intact and the aileron and flap remained attached to the wing. Aileron control cable continuity was established from the control surface to the wing root. The aileron control cables were broom strawed at the wing root. The flap cables remained attached at the bellcrank and the cables had broom strawed at the wing root. The left lift strut was separated at the fuselage and remained attached to the wing. The leading edge of the wing had impact damage. The left aileron had impact damage.

The right wing was observed in two pieces. The wing was separated outboard of the flap and the fuel tank. The leading edge of the wing was pushed aft, forward of the fuel tank. The outboard section of the wing including the right lift strut which remained attached to the wing. The aileron and flap remained attached to the wing. Aileron and flap control cable continuity was established from the surfaces to the wing root. The aileron and flap cables were broom strawed at the wing root. the flap actuator was observed in the retracted position.

The tailcone was cut from the fuselage during recovery of the aircraft into two pieces. The right rear portion of the tailcone had impact damage. The horizontal stabilizer and left and right elevator were cut from the empennage during recovery. The elevators remained attached to the stabilizer. The elevator trim tab remained attached to the right elevator. The trim tab was measured at approximately 2 3/8 inches, which is beyond limits. The elevator trim tab was deflected upwards. The elevator trim cable showed indication of overload or being cut at the actuator.

The rudder remained attached to the vertical fin. The rudder cables remained attached to the control surface and the cables were observed in the tailcone. The control cables in the tailcone had indications of overload or being cut. The aileron, rudder, elevator, and elevator trim control cables were observed at the rear portion of the cabin area along the floor. The cables had indication of overload or being cut. Control cable continuity was confirmed from the rear portion f the cabin to the forward cabin area.

The cockpit area was destroyed by impact damage or had been cut during the recovery. The side so the fuselage was separated from the cockpit floor. The top of the fuselage was separated from the fuselage. The left, right, and rear seats were separated from the cabin floor. The left and right front seats were cut at the four vertical portions of the seat from by recovery personnel. The inboard and outboard seat tracks of the left front seat were distorted. The bottom aft portion of the seat frame remained attached to the seat tracks for the left seat. The bottom forward portion of the seat from was distorted and bent for the left seat. The left seat back was separated fro the seat bottom. The left seat belt/shoulder harness remained in the outboard seat belt receptacle. The left seat shoulder harness and seat belt portion of the belt were cut by recovery personnel. The left shoulder harness inertial reel was observed separated from the fuselage.

The cockpit throttle and mixture controls were full forward. The left and right seat control wheels were separated from the control column. The left and right control wheels were intact. Control cables were observed at the pulleys for the control column.

Examination of the engine found it removed from the fuselage. Continuity could not be verified due to impact damage. No fuel was found in the fuel system. All engine components and accessories were located, and no defects or pre-impact mechanical deficiencies were noted. Examination of the magnetos found them impact separated from the accessory housing. The left magneto would not produce spark, however, the right magneto was operational. The number 1 and number 3 fuel injector lines were impact separated at the flow divider. The fuel pump was destroyed, the fuel injection servo and all controls were impact separated. The number one spark plug (top and bottom) was impact destroyed. All other spark plugs were clean with a low service life and displayed color consistent with "normal" combustion when compared to the Champion Spark Plug Comparison Chart. The oil system was impact destroyed. The oil cooler was impact breached, the oil lines were impact separated, and there was no oil found in the oil reservoir. There was oil found on the engine, in the oil lines, in the oil cooler and on the floor at the site. The number 1 cylinder exhaust push rod was impact damaged. The rocker arms would not move and the rocker cover was impact separated. Both spark plugs on the number 1 cylinder were impact destroyed and the exhaust header was destroyed. The number 2, cylinder oil return line was impact destroyed. The fuel injector nozzle was impact destroyed and the exhaust header was impact destroyed. The number 3, cylinder was in good condition, however, the exhaust header was impact destroyed. The number 4, cylinder was impact destroyed. The rocker arms and bosses were impact broken, and the exhaust header was impact destroyed.

Examination of the propeller found that blade "A" displayed aft bending, S bending and cord wise scratches. Blade "B" displayed S bending and part of the tip was missing. The blade showed cordwise scratches and leading edge gouging. It also displayed saw tooth gouging. Additionally, there was mid-length trailing edge rotational twisting.

MEDICAL AND PATHOLOGICAL INFORMATION

A post mortem examination of the student pilot was conducted by the Hillsborough County Medical Examiners Department, in Tampa, Florida. The cause of death was listed as Lacerations of brain with fractures of skull due to blunt impact to head. The manner of death was listed as Suicide. On January 9, 2002, a Toxicology examination of the pilot was conducted by the FAA Toxicology Research Laboratory. The examination revealed no Ethanol or drugs detected in the blood.

WITNESS INTERVIEWS

The flight instructor stated that when the student pilot showed up for his lesson, he was jus...