The National Transportation Safety Board's preliminary report on a June 22, 2022, helicopter crash in Logan County, W.Va., that killed six people.

1. Page 1 of 3 ERA22FA279
This is preliminary information, subject to change, and may contain errors. Any errors in this report will be corrected when
the final report has been completed.
National Transportation Safety Board
Aviation Accident Preliminary Report
Location: Amherstdale, WV Accident Number: ERA22FA279
Date & Time: June 22, 2022, 16:45 Local Registration: N98F
Aircraft: Bell UH-1B Injuries: 6 Fatal
Flight Conducted
Under:
Part 91: General aviation - Other work use
On June 22, 2022, about 1645 eastern daylight time, a Bell UH-1B helicopter, N98F, was
destroyed when it was involved in an accident in Amherstdale, West Virginia. The private
pilot, two pilot rated passengers and three additional passengers were fatally injured. The
helicopter was operated by MARPAT Aviation, LLC, as a Title 14 Code of Federal Regulations
Part 91 flight.
The flight was associated with the “7th Annual Huey Reunion” during which the operator gave
passengers the opportunity to “fly” the former military helicopter with a “safety pilot” seated
in the left front seat for a “required donation” or “ride” for a suggested donation. The accident
flight was the last flight of the day, and the accident occurred about 15 minutes after departure
from Logan County Airport (6L4), Logan, West Virginia. There were no known witnesses to
the accident.
The helicopter impacted a rock face about 3.5 nautical miles east of 6L4 and came to rest
partially inverted on its right side on an asphalt road. The wreckage spanned the 26-ft road
and continued into a ditch at the base of a rock face. The main wreckage was 542 ft past a
utility cable that crossed about 180 ft above the road. Two utility cables were fractured
consistent with tensile overload and were displaced toward the main wreckage near the
roadside at 220 ft and 397 ft from the remaining utility cable. All major components of the
helicopter were located in the vicinity of the accident site.
Examination of the wreckage revealed that the cockpit and cabin had impacted the road and a
guardrail, and both were consumed by a postimpact fire. The empennage, composed of the tail
boom, vertical fin, and horizontal stabilizer, remained attached to the aft fuselage. The right
horizontal stabilizer was impact-deformed at its tip and the left horizontal stabilizer was
intact. The vertical stabilizer and tail boom were wrinkled. The right landing skid was located
adjacent to the aft fuselage; however, first responders stated that it was moved to facilitate
rescue efforts. The left landing skid was located in the ditch. Additional wreckage including
pieces of Plexiglas, the aft cap of the left skid, a section of a tail rotor blade and a rock with
green paint transfer were observed about 40 ft above the wreckage on a ledge of the steep rock
face.

2. Page 2 of 3 ERA22FA279
This is preliminary information, subject to change, and may contain errors. Any errors in this report will be corrected when
the final report has been completed.
Both main rotor blades remained attached to their respective grips and drag braces, which
remained attached to the hub. The hub remained attached to the main rotor mast. The main
gearbox was present in its normally installed area separated from the airframe. The input
driveshaft was separated from both the main gearbox and the engine and was observed under
the main gearbox. The leading edge spar of the white main rotor blade was continuous
through the blade span with sections of afterbody that had separated from the blade located
adjacent to it in the main wreckage. The leading edge spar of the red main rotor blade was
continuous to the tip with a chordwise upward bend near the inboard side of the blade. The
outboard half of the red main rotor blade exhibited leading edge deformation in the direction
opposite of normal rotation and the afterbody in this section was fragmented into multiple
pieces that were observed near the main wreckage. The main rotor controls were impact
separated in multiple locations from the pitch change links to the swashplate and collective
lever control tubes. The main rotor controls forward of the swashplate and collective lever
control tubes were consumed by the postimpact fire.
The tail rotor drive train was continuous through the intermediate gearbox and impact-
separated between the intermediate and tail rotor gearboxes; however, portions of the forward
end were consumed by fire. The tail rotor gearbox input housing remained attached to the
vertical fin and the tail rotor gearbox and tail rotor were located intact in the vicinity. Both tail
rotor blades exhibited chordwise fractures near their doublers and the outboard portions of
the blades were found in the vicinity of the main wreckage. One of the two tail rotor pitch
change links was separated from its pitch horn and its hardware was not located. The tail
rotor controls were impact separated in multiple locations from the tail rotor to the forward
section of the tail boom. The tail rotor controls were consumed by the postimpact fire forward
of the tail boom.
The engine remained attached to the engine mounts which were separated from the airframe.
The engine gearbox was mostly consumed by the postimpact fire. The engine throttle was near
the 100% setting; however, the engine throttle linkage was fractured near the left engine mount
connection. Visual examination of the power turbine blades through the engine exhaust
revealed that two non-consecutive blades were fractured near their roots and not present. A
single power turbine blade of full length was present between the two missing blade locations.
There was evidence of tip rubbing between the power turbine blades and the engine case.
The wreckage was retained. The engine and the tail rotor controls were removed for further
examination.

3. Page 3 of 3 ERA22FA279
This is preliminary information, subject to change, and may contain errors. Any errors in this report will be corrected when
the final report has been completed.
Aircraft and Owner/Operator Information
Aircraft Make: Bell Registration: N98F
Model/Series: UH-1B Aircraft Category: Helicopter
Amateur Built:
Operator: Operating Certificate(s)
Held:
None
Operator Designator Code:
Meteorological Information and Flight Plan
Conditions at Accident Site: VMC Condition of Light: Day
Observation Facility, Elevation: 6L4,2514 ft msl Observation Time: 16:45 Local
Distance from Accident Site: 3.3 Nautical Miles Temperature/Dew Point: 32°C /21°C
Lowest Cloud Condition: Scattered / 4900 ft AGL Wind Speed/Gusts, Direction: 6 knots / ,
Lowest Ceiling: None Visibility: 10 miles
Altimeter Setting: 30 inches Hg Type of Flight Plan Filed: None
Departure Point: Logan, WV (6L4) Destination: Amherstdale, WV
Wreckage and Impact Information
Crew Injuries: 1 Fatal Aircraft Damage: Destroyed
Passenger Injuries: 5 Fatal Aircraft Fire: On-ground
Ground Injuries: N/A Aircraft Explosion: None
Total Injuries: 6 Fatal Latitude,
Longitude:
37.874614,-81.833039 (est)
Administrative Information
Investigator In Charge (IIC): Spencer, Lynn
Additional Participating Persons: Todd Gentry; FAA/AVP100; Washington, DC
Wayne Bond; Ozark Aeroworks, LLC; Springfield, MO
Note: