CENTREVILLE, AL, USA
N6085P
PIPER PA-24-250
THE PILOT HAD PURCHASED THE AIRPANE 11 DAYS PRIOR TO THE ACCIDENT, AND HAD 9 HOURS OF FLIGHT EXPERIENCE IN THE AIRPLANE. AFTER DEPARTING RUNWAY 27, WITNESSES HEARD THE PILOT REPORT ON UNICOM THAT HE WAS RETURNING TO THE AIRPORT WITH AN UNSPECIFIED EMERGENCY. THE AIRPLANE WAS OBSERVED IN A STEEP LEFT BANK AND NOSE DOWN ATTITUDE JUST PRIOR TO IMPACT WITH THE TERRAIN WEST OF THE DEPARTURE END OF RUNWAY 27. THE AIRPLANE FUEL SELECTORS WERE FOUND IN THE TIP TANK SELECTED POSITION. THE FAA-APPROVED AIRPLANE FLIGHT MANUAL SUPPLEMENT FOR INSTALLATION OF BRITTAIN INDUSTRIES WING TIP FUEL TANKS ON PIPER PA-24-250 AIRCRAFT STATES THAT WING TIP TANK FUEL IS TO BE USED IN LEVEL FLIGHT ONLY.
HISTORY OF FLIGHT On January 28, 1994, about 1430 central standard time, a Piper PA-24-250, N6085P, was substantially damaged following a collision with terrain during a forced landing near Centreville, Alabama. The private pilot and his passenger were fatally injured. The aircraft was being operated under 14 CFR Part 91 by the pilot. Visual meteorological conditions existed at the time, and no flight plan had been filed for the personal flight. The flight departed Centreville at 1429, and was destined for Alabaster, Alabama. Witnesses reported that the pilot called on the unicom frequency immediately after take-off, and reported he was attempting to return to the airport with an unspecified emergency. The witnesses stated that they then observed the aircraft enter a steep left bank, and collide with the terrain in a nose down attitude just west of the departure end of runway 27. PERSONNEL INFORMATION The pilot held a private pilot certificate with airplane single and multiengine land ratings. He held a third class medical certificate. The pilot's flight log showed he had obtained a total of 9 hours of flight time in the PA-24-250 aircraft. Additional personnel information may be obtained on page 3 of this report under the section titled First Pilot Information. AIRCRAFT INFORMATION The Piper PA-24-250 "Comanche" is a four place, single engine aircraft. It is powered by a Lycoming O-540 250 horse power engine. The aircraft had been modified with the installation of Brittain Industries 15 gallon wing tip fuel tanks. The FAA approved Airplane Flight Manual Supplement for this installation states in the limitations section "Auxiliary Wing Tip Tank Fuel to be used in level flight only".(See Copy of FAA approved Airplane Flight Manual Supplement attached to this report.) Additional aircraft information may be obtained on page 2 of this report under the section titled Aircraft Information. METEOROLOGICAL INFORMATION Visual meteorological conditions existed at the time of the accident. Additional meteorological information may be obtained on page 3 of this report under the section titled Weather Information. WRECKAGE AND IMPACT INFORMATION The aircraft wreckage was located about 200 yards southwest of the departure end of runway 27. The aircraft propeller and approximately one third of the aircraft engine were imbedded in the soft terrain. There was extensive chordwise crushing and buckling of the leading edge of the right wing. The left and right wing tip tanks were separated from the wing tips. There was continuity of the aileron control cables into the cockpit area. The fuselage was broken just aft of the cabin section. Control continuity from the elevator and rudder was confirmed into the cockpit area. Inspection of the cockpit area revealed that the fuel selectors were selected to the wing tip tank positions. Inspection of the aircraft propeller showed no signs of chordwise scratching or twisting of the propeller blades. Examination of the aircraft engine was conducted after the aircraft was removed to the airport. There was no fuel found in the carburetor or the lines from the engine driven fuel pump to the carburetor. There was no fuel found in the engine driven fuel pump. The engine driven fuel pump operated properly. A small quantity of fuel was found in the electric fuel pump. All fuel lines were checked from the engine back to the fuel sector valves, and no rupture of these lines was found. There was continuity of the engine drive train. The magnetos produced strong sparks when rotated. The carburetor was damaged during the impact. The spark plugs appeared normal in color when compared to the manufacturers spark plug analysis chart. MEDICAL AND PATHOLOGICAL INFORMATION An autopsy of Mr. Ted Douglas Hulon was conducted by Dr. Kenneth E. Warner of the Alabama Department of Forensic Sciences, P.O. Box 2411, Tuscaloosa, Alabama 35403. A toxicological examination was conducted by the Federal Aviation Administration Toxicology and Accident Research Laboratory, P.O. Box 25082, Oklahoma City, Oklahoma 73125. ADDITIONAL INFORMATION The aircraft wreckage was released to Mr. Don Freeman of the Centreville, Alabama Airport Authority on January 29, 1994.
THE PILOT'S FAILURE TO ASSURE THAT THE FUEL SELECTOR WAS IN THE PROPER POSITION FOR TAKEOFF.
Source: NTSB Aviation Accident Database
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