Wasilla, AK, USA
N8008Z
JEFFERY D TUTTLE BDK Carbon Concepts
The commercial pilot reported that the accident flight was the first flight in the experimental, amateur-built airplane since he had completed building it. He added that, shortly after departure, while in level cruise flight, he heard a loud "pop" and immediately saw that the left wing's leading-edge slat had buckled and distorted, which made the airplane difficult to control. While maneuvering for an emergency landing, the pilot had to make significant power adjustments to maintain control. After making a right turn to begin the approach to the airport, the right wing's leading-edge slat failed, which resulted in an almost complete loss of airplane control. Subsequently, he guided the airplane to an open road using the rudder and varying the engine power settings. The airplane struck the top of a tree before impacting the road in a nose-low attitude, which resulted in substantial damage to both wings and the fuselage. Each wing was equipped with three carbon fiber leading-edge slats located center, inboard, and outboard. A detailed examination of the airframe and engine revealed that the right wing's leading-edge slats exhibited features consistent with compression failure of the leading edge, trailing edge bond failure, lack of adhesive in the joints, and ply bridging. In addition, the right inboard slat attachment bracket exhibited deformation patterns consistent with an overload failure. The left wing leading edge slats exhibited no leading-edge damage but had signatures consistent with resin starvation. In addition, the left attachment bracket between the inboard and center slats exhibited features consistent with an adhesive failure in the joint and a disbond at the attachment. Microscopic examination of the attachment bracket revealed a lack of adhesion, improper surface preparation, and improper adhesive thickness. No other airframe or engine anomalies were noted.
On September 16, 2016, about 1104 Alaska daylight time, a tailwheel-equipped, experimental amateur-built, Tuttle BDK Carbon Concepts airplane, N8008Z, sustained substantial damage following an inflight structural failure of the leading-edge wing slats, followed by a loss of control, and subsequent impact with terrain. The accident occurred as the pilot was attempting to return for an emergency landing near Wasilla, Alaska. The airplane was registered to and operated by the pilot, as a visual flight rules (VFR) flight under the provisions of 14 Code of Federal Regulations (CFR) Part 91 when the accident occurred. The certificated commercial pilot, the sole occupant of the airplane sustained serious injuries. Visual meteorological conditions prevailed, and no flight plan had been filed. The local area flight departed Anderson Lake Airport, Wasilla, Alaska at about 1100 with a planned stop at Palmer Airport, Palmer, Alaska for touch-and-go landings prior to returning to Anderson Lake Airport. During a telephone conversation with the National Transportation Safety Board (NTSB) investigator-in-charge (IIC) on September 21, the pilot reported, from his hospital room, that the accident flight was the first flight after he completed building the experimental, amateur-built airplane. He added that the airplane was equipped with carbon fiber, leading-edge wing slats, manufactured by Carbon Concepts LLC, Wasilla. The pilot said that after departure from Anderson Lake Airport, he flew the airplane westbound while climbing to an altitude of about 1,000 feet, followed by a turn to the east. After completing the turn to the east, the pilot heard a loud "pop" and he immediately saw that the airplane's left wing leading-edge wing slat had buckled and distorted making the airplane difficult to control about the longitudinal and vertical axis. He stated that while struggling to maintain control of the airplane he realized that he was too high to make an emergency, straight in approach to the Anderson Lake Airport, so he chose to overfly the airport while descending. He added that during the emergency descent to the airport, he was forced to make significant engine power adjustments in an effort to maintain control of the airplane. After overflying the airport, he made a right turn to begin the approach to the Anderson Lake Airport when the right wing leading-edge wing slat failed, resulting in almost a complete loss of control. He guided the airplane using the rudder and varying the engine power settings to an open road, with his main concern being not to cause undue harm to people or property on the ground. During the emergency descent the airplane struck the top of a tree before impacting the road in a nose low attitude, sustaining substantial damage to wings and fuselage. On September 29, 2016, the NTSB IIC, along with the rest of the investigative team examined the airframe and engine at a private residence in Wasilla. All the primary flight control surfaces remained connected to their respective attach points, and flight control continuity was verified from all of the primary flight control surfaces to the cockpit. Each wing was equipped with three carbon fiber leading-edge slats located center, inboard and outboard. The right wing's leading-edge slats revealed features consistent with a compression failure of the leading edge, trailing edge bond failure, lack of adhesive in the joints, and ply bridging. In addition, the inboard slat attachment bracket exhibited deformation patterns consistent with an overload failure. The left wing leading-edge slats had no apparent leading edge damage but revealed signatures consistent with resin starvation. In addition, the attach bracket between the inboard and center slat exhibited features consistent with an adhesive failure in the joint and a disbond at the attachment. Microscopic inspection of the attachment bracket revealed a lack of adhesion, improper surface preparation, and improper adhesive thickness. The propeller remained attached to the engine crankshaft and one of the propeller blades exhibited chordwise scratching. Examination of the Lycoming O-320-A2B engine revealed no anomalies, contamination, or evidence of malfunction in any of the engine accessories. The cylinders, pistons, valve train, crankshaft, and other internal components were all without evidence of anomaly or malfunction. The closest weather reporting facility is Wasilla Airport, Wasilla, Alaska about 8 miles southwest of the accident site. At 1056, an aviation routine weather report (METAR) at Wasilla, reported: wind from 070° at 5 knots; visibility, 10 statute miles; sky condition, scattered clouds 7,000 feet, scattered clouds 8,000 feet; temperature, 54° F; dew point 41° F; altimeter, 29.38 inHG. After repeated attempts, the pilot did not submit an NTSB Pilot/Operator Accident Report form (NTSB Form 6120.1) as required.
The structural failure of both wings’ leading-edge slats, which resulted in a loss of airplane control.
Source: NTSB Aviation Accident Database
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