N47149Wilderoder GREAT LAKES 2TIA · 1978

On July 23, 2014, about 1020 central daylight time, an experimental, amateur-built Great Lakes 2T1A, N47149, operated by a private individual, was substantially damaged when it impacted a swamp near Lillian, Alabama. The private pilot and passenger were fatally injured. The local personal flight was conducted under the provisions of Title 14 Code of Federal Regulations Part 91. Visual meteorological conditions prevailed and no flight plan was filed for the flight that departed Ferguson Airport (82J), Pensacola, Florida, about 1010.

The pilot owned the airplane and based it at 82J. Prior to the accident flight, he had completed a 15-minute personal scenic flight uneventfully with a different passenger. That passenger then deplaned and the pilot boarded another passenger for another 15-minute local flight. When the airplane did not return, search and rescue procedures were initiated. An Alabama State Police helicopter tracked the pilot's mobile phone and located the wreckage about 1600, in swampy terrain approximately 5 miles northwest of 82J.

The airplane was not, nor was it required to be, equipped with a transponder. Review of radar data from the Federal Aviation Administration (FAA) revealed primary radar targets recorded near 82J about the time of the accident. The targets were consistent with a departure on runway 18, followed by a left downwind leg departure from the airport traffic pattern and a left turn to the west. After a westerly track that continued for about 4 miles, there was an approximate 1-mile gap in data, followed by five targets recorded on a northerly track near the accident site.

Two witnesses, who were at a residence near the accident site, reported seeing a biplane, consistent with the accident airplane, shortly after 1000. The airplane seemed low, below a cloud layer about 500 feet above ground level. It performed steep turns to reverse direction, but did not make any unusual maneuvers, or appear to be in distress. Both witnesses lived near a local airport, saw airplanes frequently, and paid no more attention to the airplane. They did not witness the accident.

According to the father of the previous passenger, the previous flight was unremarkable and no aerobatics were performed. His son recalled that the pilot reduced the engine power to idle and let the airplane glide for a while, which the son enjoyed.

The pilot held a private pilot certificate with a rating for airplane single-engine land. His most recent FAA third-class medical certificate was issued on October 9, 2012. At that time, he reported a total flight experience of 700 hours. Review of excerpts from the pilot's logbook revealed that he had flown 3 hours and 2 hours, all in the accident airplane, during the 90-day and 30-day period preceding the accident, respectively.

The two-seat tandem, bi-wing, tailwheel airplane, serial number 7115-J521, was assembled in 1978 and issued an FAA experimental airworthiness certificate. It was powered by a Lycoming O-320, 150-horsepower engine, equipped with a two-blade, fixed-pitch, McCauley propeller. The pilot purchased the airplane with a partner in 1988. According to the aircraft logbooks, the airplane's most recent annual condition inspection was completed on March 15, 2014. At that time, the airplane had accumulated 682.97 total hours of operation and the engine had accumulated 1404.08 hours since major overhaul. According to the tachometer, the airplane flew 8.25 hours from the time of the condition inspection, until the accident. Additionally, review of the engine logbook revealed that two overhauled magnetos were installed on February 11, 2013; however, the investigation was unable to determine where the magnetos were overhauled.

The mechanic who maintained the airplane stated that in January 2014, the left exhaust manifold was sent for repair due to cracking. To prevent further cracking, the repair facility installed ball-joints; however, the carburetor heat shroud had to be reduced by about half-size to facilitate the modification.

Pensacola International Airport (PNS), Pensacola, Florida was located about 13 miles east of the accident site. The recorded weather at PNS, at 1053, was: wind from 110 degrees at 6 knots; visibility 10 miles; scattered clouds at 2,000 feet; temperature 28 degrees Celsius; dew point 22 degrees Celsius; altimeter 30.06 inches of mercury.

Review of an FAA Carburetor Icing chart, for the given temperature and dewpoint, revealed that the weather conditions were conducive to the formation of "Serious Icing" at glide engine power settings.

The two-seat tandem, bi-wing, tailwheel airplane, serial number 7115-J521, was assembled in 1978 and issued an FAA experimental airworthiness certificate. It was powered by a Lycoming O-320, 150-horsepower engine, equipped with a two-blade, fixed-pitch, McCauley propeller. The pilot purchased the airplane with a partner in 1988. According to the aircraft logbooks, the airplane's most recent annual condition inspection was completed on March 15, 2014. At that time, the airplane had accumulated 682.97 total hours of operation and the engine had accumulated 1404.08 hours since major overhaul. According to the tachometer, the airplane flew 8.25 hours from the time of the condition inspection, until the accident. Additionally, review of the engine logbook revealed that two overhauled magnetos were installed on February 11, 2013; however, the investigation was unable to determine where the magnetos were overhauled.

The mechanic who maintained the airplane stated that in January 2014, the left exhaust manifold was sent for repair due to cracking. To prevent further cracking, the repair facility installed ball-joints; however, the carburetor heat shroud had to be reduced by about half-size to facilitate the modification.

Due to the terrain, the investigative team could not safely access the wreckage at the accident site. The wreckage was subsequently examined at a salvage facility following its recovery. One of the recovery personnel stated that tree damage at the accident site was consistent with a level attitude on a westbound heading. He also noted a strong smell of fuel at the accident site. The examination revealed that the rudder remained attached to the empennage and the stabilator had separated. The elevator remained attached to the stabilator. The right elevator had a fixed trim tab and the stabilator was equipped with a manual trim control system. Continuity was confirmed from the rudder, elevator attach point, and stabilator trim jackscrew to the rear cockpit area where the cables were cut by recovery personnel.

The airplane was equipped with upper and lower ailerons and was not equipped with flaps. The lower ailerons were controlled via push-pull tubes from the cockpit and connected to the upper ailerons. The fuel tank located at the center of the upper wing was compromised. The fuel sump contained water, but the wreckage had been submerged in approximately 2 feet of water prior to recovery. The cockpit remained intact. The mixture and throttle levers were in the full forward position and the fuel valve was on. The carburetor heat control was in the rear (on) position. The magnetos switch was selected to the "both" position and the primer was in and locked. The fuel boost pump was off. The elevator trim indicator displayed full nose up; however, the preimpact trim indicator position could not be determined. An emergency locator transmitter was not recovered.

The spark plugs and valve covers were removed from the engine. The top spark plug electrodes were intact. The No. 1 top spark plug electrode was lead fouled. The No. 4 bottom spark plug contained sediment. The carburetor was also removed. Its float and needle were intact. The carburetor fuel screen was absent of debris. The valve was in the full open position and could be actuated by hand. One propeller blade was bent aft and the other exhibited a slight s-bend. The oil filer was also absent of debris. When the propeller was rotated by hand, camshaft, crankshaft, and valve train continuity were confirmed and thumb compression was attained on all cylinders.

There was no evidence that the magnetos were submerged in water. According to the data plate and company records, the right magneto (Part No. 51360-29, Serial No. 342061) was remanufactured at the Bendix factory in 1973. When the shaft was rotated via an electric drill, the right magneto produced spark at all leads. The left magneto (Part No. 51360-30, Serial No. 980196 was manufactured at the Bendix factory in 1968. When the shaft was rotated via an electric drill, the left magneto did not produce any spark. It was subsequently forwarded to the NTSB Materials Laboratory, Washington, D.C., for further examination. The Bendix factory did not perform overhauls of magnetos and the investigation could not determine how many field overhauls of the magnetos occurred during their approximate 40-year life.

Metallurgical examination of the left magneto revealed that the points did not make electrical contact when closed. The carbon electrodes and gear electrode exhibited heavy deposits and erosion, consistent with extended age and operation. Additionally, the points, distributor and brushes appeared to be at the end of their useful life and not consistent with a magneto that was recently overhauled (for more information see Materials Laboratory Factual Report in the NTSB Public Docket).

An autopsy was performed on the pilot on July 25, 2014, by the Alabama Department of Forensic Sciences, Huntsville, Alabama. The cause of death was reported as "blunt force injuries."

Toxicological testing on the pilot was performed by the FAA's Civil Aerospace Medical Institute, Oklahoma City, Oklahoma. All test results were negative for drugs and alcohol.