N91361Cessna 180H · 1969

On June 16, 2023, about 1135 Alaska daylight time, a Cessna 180H airplane, N91361, was substantially damaged when it was involved in an accident near Shaktoolik, Alaska. The pilot and passenger were fatally injured. The airplane was operated as a Title 14 Code of Federal Regulations Part 135 on-demand charter flight.

The airplane was operated by Golden Eagle Outfitters, Inc. in support of a remote bear hunting excursion. Two hunting guides were waiting on a remote off-airport mountain ridgeline airstrip near their camp to be picked up and flown to Unalakleet Airport (PAUN) after a hunting trip. An hour before the accident, the pilot departed with two hunters/clients and told the guides he would be back to pick them up. When the pilot returned, he boarded one of the guides and some of their gear, then arranged to return for the other and the remaining gear.

The guide who witnessed the accident stated that the winds “were gusting and changing a lot” and increased during the hour they waited for the pilot’s return. He stated he had flown with the pilot many times and had witnessed the pilot perform takeoffs and landings from the airstrip many times.

The airstrip was about 750 ft long and situated atop a down-sloping, rock- and grass-covered ridgeline. The airplane normally landed uphill on about a 060° heading, then departed in the opposite direction, downhill, on a heading about 240°. During previous departures, after takeoff, the airplane would dip below the airstrip off the departure end, out of sight, then climb back into view and out of the valley.

The witness watched the initial portion of the downhill takeoff roll, and nothing appeared abnormal, so he turned away and did not watch the remainder of the takeoff. When he did not hear the engine noise during climbout or see the airplane climbing, he ran to the ridgeline’s edge and saw the airplane had impacted the tundra 300 ft below the airstrip. He sent an SOS alert from his personal GPS tracker, then hiked down to the airplane to check for survivors.

According to the Pilot’s Operating Handbook (POH), the Cessna 180’s maximum takeoff gross weight is 2,800 pounds. The airplane’s weight and balance listed the airplane’s empty weight as 1,969 pounds.

Based on weight of the occupants, cargo, and fuel, the estimated gross weight of the airplane at takeoff was 2,578 pounds, about 222 pounds under the maximum gross weight of the airplane.

The pilot departed from and was returning to Unalakleet Airport (PAUN), located 42 miles southwest of the accident site, at an elevation of 27 ft.

Shaktoolik Airport (PFSH) had the closest official weather station to the accident site, about 31 miles west-southwest at an elevation of 24 ft.

The observations from the PFSH automated weather observation system around the accident time identified visual meteorological conditions with a northerly wind between 15 and 20 knots, while PAUN identified southwesterly winds between 5 to 10 knots and visual meteorological conditions.

Weather data retrieved from the National Weather Service Aviation Weather Center experimental website indicated a 10- to 15-knot northeast wind over the accident site.

The winds and temperature aloft forecast valid for the closest point to the accident site was 020° and 13 knots at 3,000 ft.

A search of archived information indicated that the accident pilot did not request weather information from Alaskan Flight Services. It is unknown what weather information, if any, the accident pilot checked or received before or during the accident flight.

A pilot who responded to the accident site about 45 minutes after the accident said that the winds were “unusual” that day. Winds were variable, gusting 10 to 12 knots from the north, calmed, then gusted 5 knots from the south, and then the pattern repeated.

According to the Pilot’s Operating Handbook (POH), the Cessna 180’s maximum takeoff gross weight is 2,800 pounds. The airplane’s weight and balance listed the airplane’s empty weight as 1,969 pounds.

Based on weight of the occupants, cargo, and fuel, the estimated gross weight of the airplane at takeoff was 2,578 pounds, about 222 pounds under the maximum gross weight of the airplane.

Examination of the airstrip revealed a small cluster of trees about 2/3 of the distance from the beginning of the airstrip, on the left side and downslope. One 12-ft tree, about 4 inches in diameter, was fractured about 4 ft from its base. The separated portion of the tree was found next to its trunk and displayed fragments of red paint that matched the accident airplane’s paint color.

Figure 1. View of the fractured tree with fragments of red paint.

Examination of the wreckage revealed that it impacted tundra in a steep, nose-down, wings-level attitude about 1,200 ft from the broken tree. The wings were displaced by impact and the right wing leading edge was uniformly crushed aft along its span. The upper and lower wing skins were crushed aft in compression. Flight control continuity was established through several breaks to the flight control surfaces. All breaks and separations were consistent with impact and overstress failure. The engine was separated from the airframe and came to rest inverted behind the left wing. The propeller hub was fractured, and the propeller blades were separated from the hub.

The left horizontal stabilizer displayed a concave dent perpendicular to the leading edge about 1 ft outboard of the stabilizer root. Tree sap and embedded tree fibers were observed in the leading edge of the horizontal stabilizer. The right horizontal stabilizer and elevator did not exhibit leading edge impact signatures, and the elevator remained attached.

The engine was separated and located forward of the initial ground impact point and behind the left wing. It came to rest upside down; the oil pan was crushed upward. The fuel boost pump was observed fractured into pieces. The fuel lines were also fragmented.

The engine exhibited heavy impact damage to the nose and sump and, except for the impact damage, the internal components of the engine were intact. The internal engine components exhibited normal operating signatures. The crankshaft flange was impact fractured. The crankshaft would not rotate by hand until the case was opened due to impact damage.

The right magneto was removed and produced spark when tested. The left magneto would not rotate. It was disassembled and the stator in the housing was displaced from its location, which was adjacent to impact damage on the external housing.

Figure 2. View of the aft crushing on the horizontal stabilizer.

A Garmin Aera 760 portable GPS unit was removed from the airplane and sent to the National Transportation Safety Board (NTSB) Vehicle Recorders Laboratory for further examination and data download. The device was opened, and the memory chip was dislodged from the circuit board and significant damage was observed. The data from the chip was downloaded; however, the accident flight was not captured.

An autopsy of the pilot was performed by the Alaska State Medical Examiner, Anchorage, Alaska. According to the autopsy report, the cause of death was multiple blunt force injuries and the manner of death was accident. Toxicology testing performed at the FAA Forensic Sciences Laboratory found no drugs of abuse.