JACKSONVILLE, FL, USA
N2200Q
BEECH 95-A55
SHORTLY AFTER LIFT-OFF, WITNESSES OBSERVED THE LEFT WING LEADING EDGE OUTBOARD OF THE ENGINE EXPLODE AND ERUPT IN FLAMES. THE AIRCRAFT IMMEDIATELY ROLLED TO THE LEFT AND CRASHED INVERTED. THE AIRCRAFT WAS CONSUMED BY FIRE. THE LEFT PITOT TUBE AND STRUCTUAL COMPONENTS FROM THE LEFT WING WERE FOUND ON THE RUNWAY BETWEEN 300 AND 600 FT FROM WHERE THE AIRCRAFT CAME TO REST. THE EXPLOSION OCCURRED IN THE LEFT WING LEADING EDGE FORWARD OF THE FRONT WING SPAR AND JUST AFT OF THE STALL WARNING SYSTEM VANE. THE TOP SPAR CAP WAS BENT UPWARD AND THE BOTTOM SPAR CAP WAS BENT DOWNWARD. THE SPAR CAPS WERE SEPARATED FROM THE SPAR WEBB. THE WING LEADING EDGE SHEET METAL WAS RIPPED OPEN AND CURLED AFT OVER AND BELOW THE WING. THE FUEL SYSTEM AND ELECTRICAL SYSTEM COMPONENTS IN THE AREA OF THE EXPLOSION HAD SUSTAINED MASSIVE FIRE DAMAGE.
HISTORY OF FLIGHT On July 14, 1993, at 2053 eastern daylight time, a Beech 95-A55, N2200Q, registered to B. C. Engineering, Inc., crashed during takeoff at Craig Airport, Jacksonville, Florida, while on a 14 CFR Part 91 business flight. Visual meteorological conditions prevailed at the time and an instrument flight rules flight plan was filed. The aircraft was destroyed and the private-rated pilot was fatally injured. The flight was originating at the time of the accident. Witnesses reported hearing a loud "pop" or explosion and seeing N2200Q engulfed in flames at about 1100 feet into the takeoff on runway 14. The aircraft was about 5 feet off the ground at this time. The aircraft continued to climb and obtained an altitude of 25 and 50 feet. The aircraft then rolled to the left and crashed inverted on the left side of the runway. PERSONNEL INFORMATION Information on the pilot is contained under First Pilot Information. AIRCRAFT INFORMATION Information on the aircraft is contained under Aircraft Information. METEOROLOGICAL INFORMATION Visual meteorological conditions prevailed at the time of the accident. Meteorological information is contained under Weather Information. WRECKAGE AND IMPACT INFORMATION The aircraft crashed while departing runway 14 at the Craig Airport, Jacksonville, Florida. The aircraft came to rest inverted, 100 feet to the left side of runway 14, adjacent to a point 2,450 feet from the runway approach end. The aircraft wreckage was on about a 80-degree heading. Structural components from the left wing leading edge and left wing tip were found on runway 14 beginning 1,800 feet from the approach end. The left wing pitot tube, a wing inspection panel, and a fuel vent line connector was found at the 1,900-foot point. None of these components had sustained fire damage. Scrape marks were present on the left side of runway 14, 2,150 feet from the approach end. The scrape marks angled about 60 degrees toward the east from runway center line. About 10 feet further two sets of cut marks began, 5 feet left and 5 feet right of the scrape marks. Both sets of cut marks ran parallel to the scrape marks and averaged 1 foot 3 inches between cuts. There were six cut marks on the left and nine cut marks on the right. The scrape marks continued toward the east and a runway light was knocked down in the path of the scrape marks. The marks continued into the grass area east of the runway and ended at the inverted wreckage of N2200Q. All components of the aircraft necessary for flight were located on or around the main wreckage. Continuity of all flight control and engine control cables was confirmed. Examination of the left engine and propeller indicated that the propeller separated from the engine during the crash sequence. The propeller was found 50 feet behind the aircraft wreckage. The engine rotated normally and continuity of the crankshaft, camshaft, valve train, and accessory drives was confirmed. Each cylinder produced compression. The left magneto produced spark and the engine driven fuel pump drive shaft had continuity. The engine fuel system had sustained fire damage. The fuel screen from the fuel metering unit was free of debris. The engine exhaust system showed no evidence of exhaust leakage. The left propeller blades were at a low pitch angle and each blade had extensive curling and damage from ground impact. Examination of the right engine and propeller indicated that the right propeller separated from the engine during the crash sequence. The propeller was found adjacent to the engine and aircraft wreckage. The engine rotated normally and continuity of the crankshaft, camshaft, valve train, and accessory drives was confirmed. Each cylinder produced compression. The left magneto produced spark when the fire damaged condenser was replaced. The engine driven fuel pump drive shaft had continuity. The engine fuel metering unit inlet screen was free of debris. The engine fuel system had sustained fire damage. The engine exhaust system showed no evidence of exhaust leakage. The right propeller blades were at a low pitch angle and each blade had extensive curling and damage from ground impact. Examination of the left wing leading edge revealed the leading edge skin was ripped open and bent aft on the bottom and top at a point 2 feet outboard from the engine nacelle. A large hole was present in the wing leading edge. The front spar cap was separated from the spar web and bent upward on the top and downward on the bottom. The spar web was pushed aft. The landing light assembly mounted near the wing tip structure had sustained damage and the wing tip had sustained damage. The complete wing had sustained massive fire damage. The pitot tube and an inspection panel which was found on the runway 300 to 600 feet from the aircraft was normally located in the area of spar and leading edge damage 2 feet outboard of the engine nacelle. The pitot tube and inspection panel did not have any fire damage. The stall warning system vane mounted on the left wing leading edge in the area of the damage was in place on the wing skin. The auxiliary fuel tank fuel level sending unit wiring passed through the wing spar web in the area of the damage. The left wing main fuel cell is mounted forward of the left wing front spar in the area aft of the engine nacelle. The fuel cell had sustained some fire damage. The fuel vent outlet and fuel return inlet to this fuel cell, which is located on the outboard end of the cell, were in place on the cell. The fuel vent line had continuity to the point it connected to the overboard vent fitting at the bottom side of the wing leading edge. The connector had pulled loose from the overboard vent fitting. The fuel return line had continuity for about 12 inches where fire had destroyed the remainder of the line. Pressure checking of the fuel vent and fuel return lines at the cell revealed no leakage from the lines under a 10 to 20 psi pressure. No evidence of fuel leakage from the main fuel tank was found. The left wing auxiliary fuel tank was destroyed by the postcrash fire. All fuel return and fuel vent lines to this tank were damaged by fire. The fuel vent connector found on the runway could not be identified as to it's location in the left wing. All electrical wiring located in the left wing leading edge area forward of the wing spar had sustained extensive fire damage. MEDICAL AND PATHOLOGICAL INFORMATION Postmortem examination of the pilot was conducted by Dr. Margarita Arruza, M. D., Associate Medical Examiner, Jacksonville, Florida. The pilot died as a result of craniocerebral injuries. Postmortem toxicology testing on specimens obtained from the pilot was performed by Dr. Arruza and Dr. Dennis V. Canfield, Ph. D., Manager Toxicology Laboratory, Federal Aviation Administration, Oklahoma City, Oklahoma. The tests were negative for ethanol alcohol, basic, acidic, and neutral drugs. The tests were positive for 6 percent carbon monoxide, .340 ug/ml cyanide, and a trace of caffeine. For additional medical and pathological information see supplement K to this report and the toxicology test reports attached to this report. FIRE Witnesses observed the left wing area outboard of the engine explode and erupt in fire shortly after the aircraft lifted off the runway. The fire continued to burn as the aircraft rolled inverted and crash on the side of the runway. The aircraft was consumed by fire after it came rest. TESTS AND RESEARCH Computations using a computer based program indicated that a 78 inch diameter, three blade propeller, similar to the propellers on N2200Q, would be rotating at 2700 rpm if the aircraft touched down at an estimated speed of 100 knots and the cut marks on the ground were 1 foot 3 inches apart. The takeoff propeller rpm for N2200Q is 2700 rpm. METALLURGICAL EXAMINATION Metallurgical examination of the left wing stall warning vane, and left wing forward spar web at the point the auxiliary fuel tank fuel level sending unit wiring passes through the spar web was examined by Frank P. Zakar, Materials Engineer, NTSB, Washington, D. C. No indications of any electrical arching was found. See attached Metallurgist's factual report. ADDITIONAL INFORMATION The aircraft wreckage was released on July 16, 1993 to B. C. Engineering, Inc., c/o Jeffrey Stutz, Northeast Florida Aircraft Maintenance, Inc., Craig Airport Hangar 12, Jacksonville, Florida.
AN EXPLOSION AND FIRE FROM UNDETERMINED FUEL AND IGNITION SOURCES IN THE LEFT WING.
Source: NTSB Aviation Accident Database
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