Event ERA22LA039

Factual narrative

On October 31, 2021, about 1640 eastern daylight time, a Bell 47D1 helicopter, N132BR, was substantially damaged when it was involved in an accident in Zelienople, Pennsylvania. The pilot was not injured. The helicopter was operated as a Title 14 Code of Federal Regulations Part 91 solo instructional flight. According to the pilot, an annual inspection was just completed on the helicopter at Zelienople Airport (PJC), and he met his flight instructor there to continue the training necessary to add a rotorcraft-helicopter rating to his pilot certificate. He serviced the helicopter with about 10 gallons of fuel, and they departed on the instructional flight to Butler Air Show Airport (3G9), Butler, Pennsylvania, where they landed, shut down the helicopter, and the instructor endorsed the pilot’s logbook for solo flight. The pilot and instructor then returned to PJC, where the instructor disembarked while the engine continued to run, and the pilot departed back to 3G9. About 3 to 4 miles east of PJC, the engine “sputtered,” and there was a “drop” in both the engine and main rotor rpms. The pilot performed a 180° turn back toward PJC, and when he leveled the helicopter, engine and rotor rpm “returned.” The pilot continued in the direction of PJC for about 2 miles before the helicopter lost total engine power. He entered autorotation and maneuvered the helicopter for a “flat” open area but lacked the altitude and rotor rpm to reach it. The pilot landed on sloped terrain, which resulted in the destruction of the main rotor blades and substantial damage to the landing gear and tailboom. The pilot stated that there was nothing wrong with the performance and handling of the helicopter before the loss of engine power. The pilot reported 334 total hours of flight experience, of which 54 hours were in helicopters, and 14 hours were in the accident helicopter make and model. Examination of FAA and maintenance records revealed that the helicopter was manufactured in 1951 and was powered by a Franklin 6U-335-A, 210-horsepower, carbureted engine. Its most recent annual inspection was completed October 21, 2021, at 3,863.2 total aircraft hours. Examination of the helicopter by FAA aviation safety inspectors revealed that the 28-gallon fuel tank contained about 5 gallons of fuel. The accessory drive case at the bottom of the vertically mounted engine was found fractured. The tachometer generator, the engine-driven oil pump, and one magneto were all separated from the engine, but remained attached to the helicopter by associated wires and hoses. Fractured pieces of the accessory case were collected and forwarded to the National Transportation Safety Board Materials Laboratory in Washington, DC for examination. Examination of the accessory case fragments revealed that the features displayed by the fracture surfaces were consistent with overstress fracture due to impact. Other than the fractured accessory case, the initial wreckage exam revealed no evidence of mechanical anomalies. The helicopter’s subsequently owner blocked access to the wreckage and no additional examination of the helicopter was performed. Examination of the weather reported in the area at the time of the accident revealed atmospheric conditions conducive to serious carburetor icing at glide power. The pilot receiving instruction and the flight instructor picked up the helicopter following maintenance and performed a brief instructional flight. The instructor disembarked while the helicopter’s engine continued to run, and the pilot subsequently departed for a solo flight to the home airport. Shortly after departure, the engine “sputtered,” and there was a “drop” in both the engine and main rotor rpms. The pilot performed a 180° turn back toward the departure airport, and when he leveled the helicopter, engine and rotor rpm “returned.” However, soon after, the helicopter lost total engine power. The pilot entered autorotation and maneuvered the helicopter for a “flat” open area but lacked the altitude and rotor rpm to reach it. He landed on sloped terrain, which resulted in the destruction of the main rotor blades and substantial damage to the landing gear and tailboom. Initial examination of the wreckage by Federal Aviation Administration inspectors revealed a fragmented engine accessory case. Examination of the accessory case fragments revealed that the fracture surface features were consistent with overstress due to impact. Other than the fractured accessory case, the initial wreckage examination revealed no evidence of mechanical anomalies. The helicopter’s owner blocked access to the wreckage, and no further examination of the helicopter could be performed. Weather conditions reported in the area at the time of the accident was conducive to the development of serious carburetor icing at a glide power setting. It is possible that carburetor ice may have developed during the time the helicopter was operating on the ground while the instructor disembarked; however, the pilot’s use of carburetor heat was not determined, and other reasons for the loss of engine power could not be ruled out due to the lack of a more extensive examination of the helicopter. Therefore, the reason for the loss of engine power could not be determined based on the available information. Source: NTSB Aviation Accident Database Retrieved: 2026-02-12

NTSB Findings

Hierarchical cause / factor breakdown from the FAA bulk avdata database. Each finding tagged C (Cause) or F (Factor).

• — Not determined-Not determined-(general)-(general)-Unknown/Not determined