N450JW

HISTORY OF FLIGHT

On June 22, 2013, at 1247 eastern daylight time, a Boeing IB75A, N450JW, impacted terrain at the Dayton International Airport (KDAY), Dayton, Ohio. The commercial pilot and wing walker were both fatally injured. The airplane was destroyed. The airplane was registered to a private individual and operated by Jane Wicker Airshows under the provisions of 14 Code of Federal Regulations Part 91 as an airshow performance. Visual meteorological conditions prevailed for the flight, which operated without a flight plan. The local flight originated from KDAY about 1235.

The flight was performing for the 2013 Vectren Dayton Air Show, which was located at KDAY. The performance was the fourth act scheduled on June 22. Video and photos submitted by spectators, who witnessed the accident, captured the airplane during the performance. The evidence showed the airplane completed a left "tear drop" style turn as the wing walker positioned herself on the lower left wing. The airplane then rolled left to fly inverted. While flying from the southwest to the northeast in front of the spectators, the airplane's nose pitched slightly above the horizon. The airplane then abruptly rolled to the right and impacted terrain in a left wing low attitude. A post impact fire ensued and consumed a majority of the right wing and forward portion of the fuselage.

Statements gathered by the NTSB and Federal Aviation Administration (FAA) indicated that the pilot and wing walker had practiced the performance the day prior to the accident. Following the practice, neither the pilot nor the pilot-rated wing walker, reported any mechanical anomalies with the airplane to the air show crew.

PERSONNEL INFORMATION

Pilot

The pilot, age 64, held a commercial pilot certificate with ratings for airplane single engine land, airplane single engine sea, and glider. On August 30, 2012, he was issued a second class medical certificate with the restriction that he must wear corrective lenses. The pilot reported his use of Lisinopril and Triamterene to control hypertension with no reported side effects. On September 16, 2012, the pilot was issued a statement of acrobatic competency. He was authorized to perform solo aerobatics, fly wing walker maneuvers, and "circle the jumper." His altitude limitation was level 1 restricted and he was authorized to perform these events in all variants of the Extra 300, Boeing Stearman, and Pitts Special. A review of the pilot's log book revealed that the pilot had 1,190 hours, 95 hours in make and model, and about 11 hours in N450JW. The pilot did not log any flights from October 20, 2012, until April 13, 2013, which could be attributed to the air show off season. From April 13, 2013, he logged 16 hours of total time, 4.5 hours in make and model and about 1.5 hours in N450JW. The last airshow that the pilot performed with the accident wing walker was August 21, 2012.

The pilot practiced the aerial routine the day prior without incident. Members of the airshow crew ate dinner with the pilot the night prior, between 1900-2100. The pilot consumed about 1.5 beers with his meal. The pilot and crew went back to their hotel. They met the following morning from 0745-0830 the crew ate breakfast and the pilot ate a bagel with cream cheese. At 1100 the pilot ate lunch. Throughout the day the crew recalled that the pilot stayed out of the sun and was drinking water. Prior to flight, the pilot sat in an air conditioned truck for at least 10 minutes. Interactions with him where uneventful and his behavior was described as normal.

Wing walker

The wing walker, age 45, held a commercial pilot certificate for airplane single engine land, airplane multi-engine land, and instrument airplane. The wing walker had about 6 years of experience and had been performing the planned routine for the previous 3 years. The wing walker was also the owner of the accident airplane.

AIRCRAFT INFORMATION

The Boeing-Stearman IB75A, serial number 75-789 was manufactured in 1941 as a model A75N1. In 1950, modifications were made to the airplane and the model type changed to IB75A. A 450-horsepower Pratt & Whitney R-985-AN-1 fuel-injected engine drove a two bladed, metal, Hamilton Standard 2D30 propeller. On December 8, 2009, the pilot purchased the airplane and on May 3, 2010, the airplane was registered with the FAA under the experimental exhibition category. On September 26, 2011, the airplane was last registered under the restricted category for the purpose of wing walking. The airplane was modified with an inverted fuel and oil system, and a four aileron system.

A combined 100 hour and annual inspection were accomplished on April 23, 2013, at a tachometer time of 260.7 hours, and 597.5 hours since the engine's last major overhaul.

METEROLOGICAL INFORMATION

Weather at the time of the accident was wind from 220 degrees at 10 knots, visibility 9 miles, a broken ceiling at 3,500 feet, temperature 86° Fahrenheit (F), dew point 72° F, and a barometric pressure of 30.18 inches of mercury.

AIRPORT INFORMATION

The air show airspace was orientated along runway 6L/24R. The scheduled wing walking performance was flown by the accident pilot with events being performed by the wing walker. The designated airshow area was 12,000 feet long and 2,700 feet wide. The accident airplane was assigned to the Category III performance area which provided a 500 foot airspace buffer between the performance and the spectators. The wreckage came to rest over 500 feet from the fence line of the spectator area within the assigned performance area. A document depicting the airshow's layout is included in this report's docket.

The airport's elevation is 1,009 feet. Utilizing the barometric pressure, the pilot would have set about 29.09, in order to achieve "QFE" or a reading of 0 feet on the airplane's altimeter.

WRECKAGE AND IMPACT INFORMATION

The crash site was a grass area south of the intersection of taxiway R and taxiway Z. The debris field followed a 050° heading and was about 145 feet long. The first ground scars were two parallel scars consistent with the left wing's impact. About 40 feet from the beginning of the ground scars was the impact crater. The crater was 11 feet long, 6 feet wide, and at least 13 inches deep. The main wreckage came to rest 105 feet from the impact crater.

A postaccident examination of the airplane was conducted by the NTSB and FAA. Rudder and elevator control continuity was established from the rudder to the aft seat rudder pedals and the elevator to the control stick. The ailerons controls were broken and torn in multiple locations. The breaks and tear patterns were identified on each opposite surface. Thermal damage was sustained to the right aileron's connecting rod from the inboard connector to the outboard hinge. However, each of the rod ends remained attached and secured in their respective hinges.

The cockpit instrumentation sustained minor damage. The following readings, in part, displayed:

Altimeter: 300 feet

Kollmans window: 29.09

Manifold pressure: 30 inches

Tachometer hour: 284.9

The two metal propeller blades were labelled A and B for documentation purposes only. Blade A displayed leading edge polishing, nick and gouges, and chord wise scratches. From the blade's mid-span to the blade tip, the blade was curled rearward. Blade B displayed leading edge polishing, nicks and gouges, and chordwise scratches. The blade displayed an S-bend along its entire length. Cylinders number 2, 3, and 4 were found separated from the engine. No preimpact anomalies were detected with the airframe or engine.

MEDICAL AND PATHOLOGICAL INFORMATION

An autopsy was performed on the pilot by the Montgomery County Coroner's Office. The coroner ruled the cause of death as the result of multiple trauma. The manner of death was ruled an accident.

Forensic toxicology was performed on specimens from the pilot by the FAA Bioaeronautical Sciences Research Laboratory, Oklahoma City, Oklahoma. Testing was negative for presence of carbon monoxide and ethanol. Triamterene was detected in urine and blood. The pilot's use of triamterene was previously reported to the FAA.

TESTS AND RESEARCH

Accident sequence

Several videos and photographs were taken of the accident sequence by the airshow spectators. The description of the deflection of the flight controls are described using the airplane's upright orientation and the direction is not reversed when describing the flight control position when the airplane is inverted.

The accident maneuver began with the pilot climbing up and away from the crowd in order to allow the wing walker to position herself under the right lower wing. During the maneuver, the airplane is turned and aligned parallel to and behind the Category III show line. The accident sequence climb out was gradual as the airplane completed the teardrop maneuver and turned to position along the show line. At 8 seconds prior to impact, the airplane pitched nose up and began a left roll. As the airplane rolled left through 45°, the pilot applied right rudder and the rudder would remain deflected right throughout the accident sequence. At 6 seconds prior to impact, the airplane rolled through 90°, the airplane's elevator is near neutral with a slight deflection downward toward the "nose-down" position, and the rudder deflected right. The airplane did not reach a completely inverted positions and stops turning about 150°. At 2 seconds prior to impact and nearly inverted, the ailerons deflect to command a right roll and the elevator deflects upward, trailing edge up relative to the fuselage. The airplane pitched toward the ground and begins a descending right roll. The control inputs continued as the airplane collided with terrain.

Video study

A study of videos submitted to the NTSB was conducted in order to better under the airplane's flight parameters prior to the accident. Of the numerous videos submitted, five were selected for the study...