| Crash location | 26.109167°N, 97.494166°W |
| Nearest city | Laureles, TX
26.109243°N, 97.494152°W 0.0 miles away |
| Tail number | N6203N |
|---|---|
| Accident date | 09 Jun 2016 |
| Aircraft type | Bell 47G 5 |
| Additional details: | None |
On June 9, 2016, about 1630 central daylight time, a Bell 47G-5 helicopter, N6203N, was substantially damaged during a loss of control while performing agricultural spraying operations near Laurels, Texas. The pilot received minor injuries. The helicopter impacted a tree and the ground and sustained damage to the fuselage, landing gear, and main rotor system. The aircraft was registered to and operated by Hendrickson Flying Service, Inc. under the provisions of 14 Code of Federal Regulations Part 137 as an aerial application flight. Visual meteorological conditions prevailed for the flight, which was not on a flight plan. The local flight originated at an unconfirmed time.
The pilot reported that while conducting a spray pass, he pulled on the collective and the rotor speed dropped. He said that he lowered the collective, applied maximum throttle and pulled on the collective again but the rotor speed continued to drop. He then attempted a landing in a yard next to a house where the tail boom struck a tree and the helicopter came to rest on its right side.
A witness, who was an experienced agricultural helicopter pilot reported that he had flown with the accident pilot for about 12 hours in the accident helicopter. He stated that the accident pilot's previous experience was in turbine powered helicopters with governed throttle. He flew with him to familiarize him with managing throttle on the piston engine powered Bell 47 that did not have a throttle governor. The witness stated that he was in the field watching the accident pilot perform spraying operations. The pilot made a downwind pass in the field in a tight area where the helicopter was in and out of the field quickly. He said that when the pilot pulled up for the trees at the end of the pass he heard the engine "bog down." He said that he thought that the pilot had pulled collective without adding throttle.
A postaccident examination of the helicopter and a satisfactory test run of the engine disclosed no preaccident mechanical malfunctions or anomalies that would have prevented normal operations.
The pilot's failure to apply additional engine power when he applied collective input, which led to a loss of rotor speed and the exceedance of the helicopter’s performance capability.