WPR23LA343

The pilot departed the airport, conducted a low pass over the runway, and was climbing the airplane to pattern altitude when the engine began to lose power. The pilot stated that the engine did not lose complete power; however, the rpm and airspeed continued to decline and he chose to make a forced landing. The airplane landed in heavily vegetated terrain and during the landing roll the left main landing gear collapsed, resulting in substantial damage to the lower left wing. A postaccident examination of the airframe and engine revealed no evidence of any preaccident mechanical malfunctions or failures that would have precluded normal operation. Although remnants of a high-temperature cloth were found between the air filter and particle screen, no debris was found in the filter or induction screen and the air intake did not appear to be impeded. Based on the available information, the reason for the loss of engine power could not be determined.

On September 13, 2023, at 1100 mountain daylight time, a Boeing Stearman A75N1 (PT-17), N10KP, was substantially damaged when it was involved in an accident near Monticello, Utah. The pilot was not injured. The airplane was operated as a Title 14 Code of Federal Regulations Part 91 personal flight. The pilot reported that, after performing the preflight checklist and engine run-up, he departed from runway 16 and remained in the airport traffic pattern. He conducted a low pass over the runway, made a left crosswind turn, and began a climb. About 500 ft above the ground, the engine began to lose power. The engine did not exhibit a complete loss of power, but engine rpm and airspeed continued to decline. The pilot chose to make a forced landing to flat, sage brush-covered terrain. The left main landing gear collapsed during the landing roll, resulting in substantial damage to the lower left wing when it struck the surface. Examination of the airframe and engine revealed no evidence of any preaccident mechanical malfunctions or failures that would have precluded normal operation. Throttle and mixture control continuity was established from the rear cockpit controls to the engine. The fuel system was intact with no fuel leaks observed. The front spark plugs were removed, and the propeller was rotated by hand. Rotational continuity was established throughout the engine and valvetrain, and thumb compression was obtained for all 9 cylinders. The starter was engaged, and spark was obtained at all ignition leads. Removal of the induction system revealed remnants of a high-temperature cloth between the air filter and particle screen. No additional cloth debris was observed in the filter or induction screen. The carburetor remained secure at its mount and when the throttle was actuated by hand fuel was expelled from the accelerator pump port. The carburetor fuel screen was free of debris. The carburetor was removed and disassembled with no discrepancies noted. Fuel was obtained from the airframe fuel filter, carburetor, and fuel tank; all fuel samples were free of debris and blue in color. A review of the weather conditions reported by Blanding Municipal Airport (BDG), Blanding, Utah, about 21 nautical miles southwest of the accident site, indicated a temperature of 64.4°F, and a dew point of 50°F around the time of the accident.