On July 28, 2024, about 0815 Pacific daylight time, a Beechcraft C23 airplane, N2248L, was substantially damaged when it was involved in an accident near Elko, Nevada. The pilot sustained minor injuries. The airplane was operated as a Title 14 Code of Federal Regulations Part 91 personal flight. The pilot reported that the accident flight was the airplane’s first flight since its recent annual inspection. After conducting a preflight inspection, which included observing fuel through the fuel tank filler necks, he estimated that the airplane had a total amount of about 25 gallons of fuel onboard. The engine started with some hesitation after multiple attempts. After the standard engine run-up, he decided to taxi around the airport since about one month had elapsed since the airplane’s last flight. The pilot reported that the takeoff was normal, but during the initial climb, about 300 to 400ft above ground, the engine lost total power. The pilot stated that there were buildings in front of him and he chose to maneuver to an open field to his left. During the landing approach, the stall warning horn sounded, and he pitched the nose over before impacting the ground. Postaccident examination of the airplane revealed substantial damage to both wings and the fuselage. The airplane impacted a grass-covered field about 1 mile southwest of the airport. The wreckage debris path was about 100 ft long and oriented on a southerly heading. The right wing tip was near the initial ground impact marks. The main wreckage remained upright and the fuselage was buckled throughout. The engine and firewall partially separated from the fuselage, revealing the forward cabin area. The right wing separated from the forward and main spars at the wing root area and was folded aft against the fuselage. The maintenance records revealed that the annual inspection was completed on July 1, 2024, at a total airframe time of 3,644.4 hours. The airplane had 0.3 hours of operation since the last inspection. During the inspection, the oil was changed, the oil filter was disassembled and clear of contaminants, cylinder compression was checked, and the tachometer was replaced. An examination of the accident site was conducted by the FAA. The left and right fuel tanks contained 10 to 15 gallons (estimated) of total fuel. The gascolator, engine fuel pump, and carburetor separated from their engine mounts. Fuel was present in each of the components and their damaged fuel lines. The fuel selector handle was found near the right fuel tank position. A follow-up examination of the recovered wreckage was conducted at a secured facility in Phoenix, Arizona, several months after the accident. The examination revealed no preaccident mechanical malfunctions or failures with the airframe or engine that would have precluded normal operation. Internal continuity of the engine was confirmed, and no anomalies were observed when the cylinders were examined with a lighted borescope. Both magnetos produced spark from their ignition leads when rotated. The carburetor was impact-separated from the engine but exhibited no anomalies upon disassembly. No fuel was present in the airplane’s fuel system during the examination. The wing fuel tanks and associated lines to the fuel selector were unobstructed. The fuel selector valve functioned normally and the gascolator was disassembled; both were free of obstructions. The fuel boost pump inlet fitting and control wiring were sheared off the pump. The boost pump open inlet port was obstructed by organic material. The organic material was pink in color and tube-shaped. The boost pump screen was clean and also had several tube-shaped formations in the boost pump. The check valve adjacent to boost pump had fracture separated inlet plumbing and also contained the same organic material that was contained in the boost pump. The organic material was bougainvillea leaves and insect larvae. Additional research indicated that this bougainvillea plant species is not native to Elko, Nevada, where the airplane was based, but is abundant in the Phoenix, Arizona, area. The starter remained engaged with the starter ring gear during the examination of the engine. The starter ring gear showed some wear in areas. The starter was removed from the engine and the gear remained in the engaged position. The starter motor was removed, and the starter control shaft and housing were undamaged. A small amount of spring resistance was observed in the pinon gear spring, but it would not retract to its resting position. The assembly was connected with electrical power; the motor spun up normally and the pinon gear rotated, but would not retract to its resting position. The motor and spring shaft connection area had sufficient grease and the gears were undamaged. No thermal discoloration was noted.