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N2300W accident description

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Crash location Unknown
Nearest city Sarasota, FL
27.336435°N, 82.530653°W

Tail number N2300W
Accident date 15 Mar 1996
Aircraft type Beech A23A
Additional details: None

NTSB description


On March 15, 1996, about 1633 eastern standard time, a Beech A23A, N2300W, registered to a private owner, operating as 14 CFR Part 91 personal flight, crashed while maneuvering about 14 miles east of Sarasota, Florida. Visual meteorological conditions prevailed and no flight plan was filed. The airplane was destroyed and a postcrash fire ensued. The private pilot was fatally injured. The flight originated from the Sarasota-Bradenton Airport about 30 minutes before the accident.

Review of Tampa Air Traffic Control transcripts revealed N2300W had terminated radar service 15 miles east of Sarasota, Florida, and requested to remain on frequency for traffic advisories. At 1631, the pilot of N2300W stated, "mayday november two three zero zero whiskey is in a stall in a spin." A pilot who heard the transmission transmitted, "opposite rudder mayday opposite rudder get that nose down get it out of the spin." There were no other recorded transmissions from N2300W.


The wife of the deceased pilot stated her husbands pilot logbook was located in his flight bag which was kept in the airplane. Additional information pertaining to the pilot is contained in NTSB Form 6120.4.


Review of the aircraft logbooks revealed the last annual inspection was conducted on July 3, 1995. The tach time was 534.73 and the total time in service was 2115.73. The total time since major overhaul of the engine was 1074.73. The last known recorded work order on N2300W was on January 23, 1996, at a tach time of 596.25. The tachometer was consumed by the postcrash fire. Additional information pertaining to the airplane is contained in NTSB Form 6120.4.


Visual meteorological conditions prevailed at the time of the accident. For additional information see NTSB Form 6120.4.


Examination of the crash site indicated the airplane collided with the ground in a near vertical descent, 35 degree nose-down attitude, with no evidence of forward motion rotating around its vertical axis to the left. The airplanes longitudinal axis was found to be at rest on a heading of 041 degrees magnetic.

The propeller and engine were displaced to the right. The propeller had separated aft of the propeller flange. Both propeller blades had evidence of torsional twisting, "s" bending, and were bent forward. One propeller blade was imbedded in the ground with evidence of chordwise scarring. The left wing was displaced aft and the right wing was accelerated forward. Both fuel tanks were ruptured during the impact sequence.

Examination of the airframe, flight control system, and engine assembly revealed no evidence of a precrash mechanical failure or malfunction. All components necessary for flight were present at the crash site. Continuity of the flight control system was confirmed for pitch, roll, and yaw. All engine accessories sustained fire damage. The fuel pump would not rotate by hand and the fuel pump coupling was intact. The mixture control lever was in the full rich position and the throttle body had been consumed by fire. The fuel manifold screen was not contaminated, and the fuel nozzles were unobstructed. Both magnetos could be rotated by hand. The top spark plugs were removed from cylinders 1, 2, 3, and 4. The spark plug electrodes, revealed the color, wear, and deposits were normal. The oil sump was crushed upward.


Postmortem examination of the pilot was conducted by Dr. W. Pearson Clack, Medical Examiner's Office, Sarasota, Florida, on March 16, 1996. The cause of death was multiple injuries of blunt trauma. Postmortem toxicology studies of specimens from the pilot were performed by Sarasota Memorial Hospital. These studies were negative for alcohol and positive for caffeine and an unidentified compound. The specimens were not tested for basic, acidic, and neutral drugs.


Review of Tampa ATCT continuous data recording radar revealed N2300W was observed on radar at 1630:04, heading 090 degrees, with a ground speed of 102 mph, at 2,400 feet. At 1630:13, the ground speed decreased to 98 mph, and the airplane turned to the right to a heading of 110 degrees. At 1630:18, the airspeed continued to decrease. The airplane turned back to the left to 090 degrees, and back to the right to 130 degrees. At 1630:36, the airplane starts a continuous turn to the left. The last radar return was received at 1631:18. The airplane was at 1,800 feet, heading 060 degrees, with a ground speed of 74 mph.

The Pilot's Operating Handbook for the Beechcraft A23A, Section 5, Performance, states at a gross weight of 2,400 pounds, flaps-up, 30-degree bank, the airplane will stall at 77 mph or 67 knots. Performance data provided by Beechcraft revealed at a gross weight of 2,000 pounds, 15 degree flaps, 30 degree angle of bank, the airplane will stall at 58 knots. At a 60-degree bank, the airplane will stall at 72 knots.


The airplane wreckage was released to Mr. Don Huntington, Quality Aircraft Salvage, Groveland, Florida, on March 17, 1996. The airplane logbooks were released to Mr. Tyler Dedman, Sample International Inc., on March 28, 1996.

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