NTSB Identification: WPR14FA158
14 CFR Part 91: General Aviation
Accident occurred Sunday, April 06, 2014 in Green River, UT
Aircraft: ROBINSON HELICOPTER R22 BETA, registration: N13HG
Injuries: 2 Fatal.

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. NTSB investigators either traveled in support of this investigation or conducted a significant amount of investigative work without any travel, and used data obtained from various sources to prepare this aircraft accident report.

On April 6, 2014, at an undetermined time, a Robinson R22 Beta, N13HG, collided with terrain near Green River, Utah. The pilot was operating the helicopter under the provisions of 14 Code of Federal Regulations (CFR) Part 91. The commercial pilot and one passenger sustained fatal injuries. The helicopter sustained substantial damage during the accident sequence. The local personal flight departed from private property near Green River about 1115. Visual (VMC) meteorological conditions prevailed, and no flight plan had been filed.

The family reported that the helicopter was overdue about 1800 on April 6, and the Utah Highway Patrol initiated a search. Using a signal from a cell tower and an emergency locator transmitter (ELT), they discovered the wreckage about 1300 the following day.

On-site documentation revealed that the white helicopter came to rest about 1/4 way up the south slope of an east-west gully with a dry creek bed in the bottom. The slope changed at the midpoint of the fuselage; it was 55 degrees downhill below the wreckage and 40 degrees uphill above it. The creek bed was 30 feet away, and the bottom of the bluff was about 75 feet away. The first identified point of contact (FIPC) was a ground scar that was on a 255-degree magnetic heading. The vertical and horizontal stabilizer assembly separated and was in a tree at the eastern end of the ground scar. A rock face was at the western end of the ground scar, and exhibited a 3-foot diameter area of white marks with white paint shards at its base. The nose of the cabin was in contact with the north end of the white marks on the rock face; the orientation of the fuselage was 180 degrees.

Both tail rotor blades separated a few inches from the hub. One blade was in the bottom of the gully; its fracture surface was angular and jagged. The other blade was in the tree with the stabilizer assembly; its fracture surface was angular and jagged and there was a dent in the leading edge near the tip. The aft skid crosstube was in the bottom of the dry creek about 30 feet from the tail rotor blade.

The main rotor blades were oriented north-south. The south blade did not exhibit any leading or trailing edge damage, but did have a puncture midspan and midchord that went through to the top of the blade. The north blade bent down about 2 feet from the hub; it did not exhibit any leading or trailing edge polishing or dents.

The engine did not show evidence of catastrophic failure. The exhaust exhibited ductile bending.

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