Missoula, MT, USA
N43MA
BELL 206B III
The fixed base and helicopter operator was conducting an evaluation of a prospective pilot-employee for the company. The prospective employee had obtained most of her flight experience in a helicopter model that was different from the single-rotor helicopter being used for the evaluation. On the day of the accident, after a brief flight with another company pilot, the prospective employee landed the helicopter and remained in the right seat, while the other pilot exited, and the company chief pilot took the left seat. The prospective employee then flew the helicopter to another location. The approach and landing were into the wind, on a heading variously reported as either west or parallel to runway 29; she landed uneventfully on a dry, level, dirt and grass field adjacent to the airport. After a brief discussion in which it was agreed that the chief pilot would demonstrate the next maneuver, the chief pilot attempted to lift off. According to the chief pilot, the right skid felt like it was "stuck" to the ground. Despite his efforts to correct the situation, he was unable to successfully set the helicopter fully back down. The helicopter rolled over onto its right side and sustained substantial damage. Immediately after they exited the helicopter, the two pilots attempted to determine what had caused the right skid to become stuck to the ground, but their efforts were curtailed by a fuel leak and small fire. The chief pilot did not report any prerollover mechanical deficiencies or failures of the helicopter, and a postaccident examination of the helicopter by Federal Aviation Administration (FAA) inspectors did not detect any such deficiencies or failures. Single-rotor helicopters are susceptible to a lateral rolling tendency, called dynamic rollover, when lifting off, and the FAA Rotorcraft Flying Handbook noted that two "critical conditions" for dynamic rollover were "right side skid down" and "crosswinds from the left." Detailed evaluation of the wind data from two different nearby sensors revealed that the wind direction was between about 265 and 290 degrees, at 10 to 22 knots. Neither the wind direction at the accident site nor the exact heading of the helicopter were measured, so the crosswind component could not be accurately determined. However, given the lack of any other evidence supporting the event, it is likely that the helicopter experienced a dynamic rollover due to a left crosswind.
HISTORY OF FLIGHTOn April 4, 2014, about 1548 mountain daylight time, a Bell 206B III helicopter, N43MA, was substantially damaged during a liftoff attempt at Missoula International Airport (MSO), Missoula, Montana. Both pilots on board received minor injuries. The helicopter was operated by Minuteman Aviation Incorporated (MAI), and the evaluation flight was conducted under the provisions of Title 14 Code of Federal Regulations Part 91. Visual meteorological conditions prevailed, and no Federal Aviation Administration (FAA) flight plan was filed for the flight. According to the pilot under evaluation, the purpose of the flight was regarding her possible employment by the operator as a Bell 206 pilot. On the day of the accident, after a flight with another MAI pilot, she landed and remained in the right seat with the engine running, while the other pilot exited and the MAI chief pilot (CP) took the left seat. She then flew the helicopter to, and landed on, a field adjacent to the airport. That field was referred to by MAI personnel as the "practice area." The landing surface was dry, level, and consisted of mixed dirt and clumps of grass, which the evaluee described as a "normal dry livestock field." The approach and landing were into the wind, on a heading variously described as either west or approximately parallel to MSO runway 29. After a brief discussion in which it was agreed that the CP would demonstrate the next maneuver that he wanted to see, the CP attempted a liftoff. According to the CP, the right skid felt like it was "stuck" to the ground. Despite his efforts to correct the situation, the CP was unable to successfully set the helicopter fully back down. The helicopter rolled over onto its right side, and sustained substantial damage to the fuselage, tail boom, and main rotor. The CP shut the helicopter down, and both occupants exited the aircraft. The CP did not report any pre-rollover mechanical deficiencies or failures of the helicopter, and a post-accident examination of the helicopter by FAA inspectors did not detect any such deficiencies or failures. PERSONNEL INFORMATIONChief Pilot The CP held a commercial pilot certificate with multiple ratings, including helicopter. He reported a total flight experience of about 19,000 hours, including about 5,310 hours in helicopters, and about 1,500 hours in the accident helicopter make and model. His most recent flight review was completed in March 2014, and his most recent FAA second-class medical certificate was issued in February 2014. Pilot Under Evaluation The pilot under evaluation held a commercial pilot certificate with airplane single-engine land and helicopter ratings. She reported a total flight experience of about 1,200 hours, including about 1,080 hours in helicopters, and about 5 hours in the accident helicopter make and model. Her most recent flight review was completed in September 2013, and her most recent FAA first-class medical certificate was issued in July 2013. AIRCRAFT INFORMATIONFederal Aviation Administration (FAA) information indicated that the helicopter was configured with a single main rotor system and a tail rotor near the aft end of the tail boom. The helicopter was manufactured in 1991, and was equipped with an Allison (Rolls-Royce) 250-C20 series turboshaft engine. MAI information indicated that the helicopter had accumulated a total time in service of approximately 7,484 hours. Its most recent annual inspection was completed on January 27, 2014. METEOROLOGICAL INFORMATIONThe airport was equipped with two separate wind sensor systems. One sensor system displayed wind speed and magnetic direction information in the air traffic control tower (ATCT), and that display was the data source for wind information issued to pilots by the controllers during their normal radio communications. The wind speed and direction information itself was not recorded; the only records of those values were any communications of the values in the controllers' transmissions. This method can introduce some temporal uncertainty (typically less than a minute, but possibly a few minutes) into the data. The ATCT wind sensor was located about 3,600 feet east of the accident location. According to information provided by personnel from the company that operated the ATCT, the wind speed and direction values that were issued during the 24-minute period during which the helicopter was operating were always from 290 degrees, and varied between 10 and 18 knots. In the few minutes surrounding the accident period, maximum gusts up to 22 knots were reported. The second wind sensor was part of the automated surface observation system (ASOS), and was the data source for the METARs and ATIS (automated terminal information service); that data is recorded at 1-minute intervals, and permanently archived. ASOS wind direction values are in degrees true; the magnetic variation must be accounted for in order to directly compare the ASOS and ATCT values. The ASOS wind sensor was located about 2,500 feet north-northeast of the accident location. Review of the ASOS 1-minute data indicated that in the 5 minutes either side of the reported time of the accident, the wind direction varied between about 267 and 298 degrees magnetic, at speeds between 10 and 17 knots, with gusts up to 20 knots. The MSO 1553 automated weather observation included winds from 320 degrees at 11 knots, visibility 10 miles, few clouds at 6,500 feet, temperature 11 degrees C, dew point minus 2 degrees C, and an altimeter setting of 29.81 inches of mercury. The accident report form filed by the CP indicated that the wind was from 250 degrees at 13 knots, with gusts to 20 knots. AIRPORT INFORMATIONFederal Aviation Administration (FAA) information indicated that the helicopter was configured with a single main rotor system and a tail rotor near the aft end of the tail boom. The helicopter was manufactured in 1991, and was equipped with an Allison (Rolls-Royce) 250-C20 series turboshaft engine. MAI information indicated that the helicopter had accumulated a total time in service of approximately 7,484 hours. Its most recent annual inspection was completed on January 27, 2014. WRECKAGE AND IMPACT INFORMATIONThe practice area being used by the pilots was 3,000 feet south-southeast of the intersection of runways 7/25 and 11/29, just outside the airport perimeter fence. According to the pilots, the helicopter came to rest on its right side, oriented on an approximate heading of 270 degrees magnetic. The pilots reported that that direction was the same direction that the helicopter was facing at the beginning of the attempted liftoff. The helicopter sustained substantial damage to the fuselage and tail boom. The main rotor blade assembly was fracture-separated from the mast, the cabin was deformed, the tailboom was bent, and several cockpit/cabin windows were broken. Immediately after they exited the helicopter, the two pilots attempted to determine what had apparently caused the right skid to become stuck to the ground, but a fuel leak and a small fire caused them to move away from the helicopter. The investigation did not obtain any information to either substantiate or refute the CP's assertion that the right skid became stuck to the ground. ADDITIONAL INFORMATIONDynamic Rollover The FAA Rotorcraft Flying Handbook (H-8083-21) stated that a single-rotor helicopter "is susceptible to a lateral rolling tendency, called dynamic rollover, when lifting off the surface," and that if the helicopter's critical rollover angle "is exceeded, the helicopter rolls on its side regardless of the cyclic corrections made." The Handbook also noted that two "critical conditions" for dynamic rollover were "right side skid down" and "crosswinds from the left." The directionality of those parameters is primarily a function of the direction of rotation of the main rotor blades; the stated directionality is applicable to the accident helicopter.
A dynamic rollover during attempted liftoff.
Source: NTSB Aviation Accident Database
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