Accident Overview
On July 22, 2024, at 1812 eastern daylight time, a Beech A36 airplane, registered N1089W, was substantially damaged in an accident near Ronkonkoma, New York. The private pilot and passenger were fatally injured. The flight was conducted as a personal flight under Title 14 Code of Federal Regulations Part 91.
Flight and Witness Observations
The pilot departed from Long Island MacArthur Airport (ISP), Islip, New York. After taxiing from the ramp via taxiways C to B, the airplane joined runway 24 for an intersection takeoff at the 4,100 ft-remaining point of the 7,006 ft-long runway. Security video from the airport terminal showed a normal takeoff roll, liftoff, and initial climb. The landing gear retracted before the aircraft exited the camera frame. Preliminary ADS-B data indicated a takeoff roll of about 1,200 ft with a groundspeed of about 82 kts during initial climb. Shortly after gear retraction, groundspeed steadily decayed to 62 kts, followed by a descending left turn. Several witnesses reported hearing “sputtering” and a “loud pop” during the climb. The airplane then rolled left and impacted terrain just off the paved runway threshold at an elevation of 106 ft.
Aircraft Examination
The wreckage path was oriented on a heading of about 165°. The initial impact left an 8 ft-long gouge in the grass, followed by propeller slash marks and a crater containing plexiglass and engine compartment pieces. The airplane came to rest upright with the nose facing the runway. The left wing was folded leading edge up against the fuselage; the flap and most of the aileron remained attached. The left main and wingtip fuel tanks were compromised and empty, though fuel spillage blight and blue staining were observed. The right wing sustained minor damage; its main tank contained about 20 gallons of 100LL aviation fuel, and the wingtip tank held about 2 gallons. Landing gear were retracted. Flight control continuity was established from surfaces to cockpit. Flaps were retracted. Elevator trim was deflected 8° trailing edge down.
The propeller remained attached; one blade showed a wave bend, chordwise scrapes, polishing, and a 30° aft bend; the other was uniformly bent aft 40° with minor scrapes and a tip gouge. The spinner was crushed and compressed on the hub. The propeller governor and control linkage were destroyed. Engine crankshaft rotation confirmed powertrain and valvetrain continuity. Compression was observed on all cylinders. Borescope examination of cylinders, pistons, valves, and camshaft lobes revealed no anomalies. Fuel lines contained 100LL fuel; fuel injectors were unobstructed. The engine-driven fuel pump produced suction and expulsion. The auxiliary boost pump switch was in the off position. The fuel selector held about 3 oz of fuel, moved freely, and low air pressure showed no obstructions. Oil filter pleats appeared normal, and no contaminants were on the oil suction screen. Spark plugs exhibited normal coloration and wear. Both magnetos produced blue/purple sparks on all posts at multiple rpm settings.
Post-Accident Findings
The wreckage was retained for further examination. No probable cause has been stated in the preliminary investigation.