N161LA

On December 5, 2025, about 0858 central standard time, a Hughes 369D, N161LA, was substantially damaged when it was involved in an accident near Pryor, Oklahoma. The pilot was fatally injured. The helicopter was operated as a Title 14 Code of Federal Regulations Part 91 aerial observation flight.

According to the operator, the helicopter departed from a landing zone about 1 mile from the accident site, about 28 minutes prior to the accident. The purpose of the flight was to visually monitor power line replacement operations.

According to multiple witnesses who were employed by the power line company, the helicopter was hovering above and alongside the power distribution line being constructed. During the hover, the helicopter was moving at a slow rate of speed, about 4 knots, while the pilot was observing a device called a “sock,” being pulled along the power distribution line by ground based equipment. The witnesses reported that the helicopter suddenly pitched up to a near inverted attitude, flew backward, then turned and pitched straight down, toward the ground. They described the sequence as if it looked like the helicopter “flipped over on its back and fell to the ground.”

Examination of the accident site revealed that the helicopter impacted an open field, in a nose low attitude, about 250 ft south of the power distribution line where the ‘sock’ was being observed. The first identifiable point of contact (FIPC) was a ground impression with various fragments of debris consistent with the forward fuselage and cabin area, and ground penetration scars consistent with the left and right skid toes. The skid toe and forward 2-3 ft of the right skid was separated from the rest of the right skid and remained impaled in the ground at the FIPC. The main wreckage came to rest on its right side, on a magnetic heading of about 040°, about 6 ft south of the FIPC. The majority of the debris field remained within about a 50 ft diameter of the main wreckage. One main rotor blade was located about 110 ft south of the main wreckage and another main rotor blade was located about 160 ft southeast of the main wreckage. A section of main rotor blade section was located about 160 ft south of the main wreckage, and one pitch horn was located about 170 ft south of the main wreckage. (See figure 1.) All major components of the helicopter were located at the accident site.

Figure 1. Debris field

The wreckage was recovered to a secure facility for further examination.