ERA22FA010

The non-instrument-rated pilot’s continued flight into deteriorating weather conditions, which resulted in a loss of control due to spatial disorientation.

The non-instrument-rated helicopter pilot was returning to his home airport as the height of the overcast ceiling gradually decreased along the route of flight, consistent with the forecast conditions. While flying along the river valley at an altitude of 1,800 to 1,900 ft above mean sea level (100 to 200 ft below the clouds), the helicopter flew beneath an area of light-intensity precipitation echoes as detected by weather surveillance radar. It is likely that, at this time, the pilot encountered reduced visibility in very light rain and potential clouds. About the same time, the helicopter began to climb, and its groundspeed decreased. Shortly after climbing above the altitude of the reported cloud ceiling, the helicopter entered a relatively constant-rate turn. About 9 seconds later, the track straightened for about 3 seconds, the climb rate plateaued at about 2,400 feet per minute, and the groundspeed began to increase. The helicopter continued to climb for another 10 seconds as the groundspeed increased to about 95 knots. During this time, it again turned toward the right for about 9 seconds. Just before the end of the turn, the helicopter began to descend rapidly. As it descended through the altitude of the cloud ceiling, the rate of descent reached 16,200 feet per minute. The tracking data ended about 2 seconds later in the vicinity of the accident site. Postaccident examination of the airframe revealed no preimpact anomalies that would have precluded normal operation. Damage and fragmentation to the main and tail rotor blades, along with score marks on a frame tube near the tail rotor drive intermediate coupling, were consistent with rotor system rotation during the impact sequence. Impact marks found on the upper drive sheave and dents found on two of the engine’s cooling fan blades were consistent with the engine’s crankshaft not rotating at the time of impact. The drive sheave mark was an imprint with an outline of teeth from starter ring gear, which was mounted on the engine crankshaft. The imprint, (rather than scoring or cut grooves) was consistent with the engine’s crankshaft was not rotating when it contacted the sheave. Similarly, the dents on the cooling fan blades, each found directly below airframe components that likely caused the dents, suggest the cooling fan was not rotating when its blades made contact during impact. Also, the fuel servo mixture arm was found bent and in the idle-cutoff (no fuel to engine) position. The mixture cable sheathing was found stretched in several locations, consistent with tension. Tension on the cable, and other impact forces, likely pulled the mixture arm toward the idle-cutoff position. Despite these findings, no evidence of any preimpact mechanical malfunctions or failures of the engine were discovered that would have precluded normal engine operation. The flight track information, which showed a simultaneous climb and increase in groundspeed before the accident, was consistent with the engine providing power; therefore, it is likely that the crankshaft stopped during the impact sequence before the helicopter came to rest. The pilot’s continued visual flight rules flight into an area of instrument meteorological conditions due to clouds and precipitation likely resulted in his loss of outside visual references, an environment conducive to the development of spatial disorientation, and the helicopter’s flight track was consistent with the known effects of spatial disorientation. According to the pilot’s logbook, he had not received any instrument training, nor was the helicopter certified for flight in instrument conditions. These factors increased the likelihood of the pilot becoming spatially disoriented after encountering reduced visibility conditions.

The Office of the Medical Examiner, Orange County, New York, performed an autopsy on the pilot. The autopsy report indicated the cause of death was blunt impact injuries. Toxicology testing of the pilot was performed at the FAA Forensic Sciences Laboratory. Tamsulosin was detected in liver and muscle. Tamsulosin (Flomax) is an alpha blocker used to treat prostate hypertrophy and is acceptable for FAA medical certification. The helicopter was equipped with inflatable landing gear floats and a flight control stability augmentation system. The pilot held a private pilot certificate with rotorcraft-helicopter rating. He did not have an instrument rating. A review of his logbook revealed that he had not recorded any actual or simulated instrument flight experience, and no instrument training was noted in the remarks section of any log entries. In November 2020, one flight was remarked with “IFR Conditions, asked for special VFR.” In May of 2021, one flight was remarked with “low clouds, rain, autopilot through clouds.” On October 10, 2021, at 1357 eastern daylight time, a Robinson R44 II, N637HP, was destroyed when it was involved in an accident in Cornwall, New York. The pilot was fatally injured. The helicopter was operated as a Title 14 Code of Federal Regulations Part 91 personal flight. According to fueling records, the pilot purchased 24.6 gallons of fuel before his departure from Floyd Bennet Memorial Airport (GFL), Glenn Falls, New York. The flight departed about 1247 with a destination of MacArthur Airport (ISP), Ronkonkoma, New York, where the helicopter was based. According to ADS-B tracking data and National Weather Service (NWS) records, as the helicopter flew south along the Hudson River at an altitude of 1,800 to 1,900 ft above mean sea level (msl), the overcast cloud ceiling height was decreasing. As it passed by Poughkeepsie, NY (POU) at 1349, the ceiling reported there was about 2,364 ft msl. At 1353, about 7 miles further south, the helicopter passed by the Stewart International Airport (SWF) where the ceiling was reported to be about 1,991 ft msl. At 1356, the helicopter began to climb (see figure 1). Figure 1 – Helicopter’s ADS-B-derived flight track (red/green dots) and cloud heights at nearby airports (yellow text) According to NWS weather surveillance radar data, near the time the climb began, the helicopter encountered an area of light intensity echoes that were moving to the north-northwest (see figure 2). Figure 2 – Helicopter’s flight track (magenta) and weather radar base reflectivity at 1357 At 1356:03 while at an altitude of 1,875 ft msl, and a ground speed of 101 knots, the helicopter began to climb straight ahead. About 9 seconds later, it reached an altitude of 2,025 ft, which was above the cloud ceiling height reported at SWF (1,991 ft). About 5 seconds later it began the first of two right turns (see figure 3). The first turn lasted about 9 seconds, with an average turn rate of 7 to 11° per second. Figure 3 – Helicopter’s flight track during climbing turn and subsequent descent (red and green dots) From the start of the climb until about the end of the first right turn, the rate of climb continually increased, and the airspeed continually decreased. At the end of the first turn, the rate of climb plateaued at about 2,400 feet per minute, and the airspeed had decreased to about 45 knots. Just as the rate of climb plateaued, the airspeed trend reversed and began to increase. The helicopter continued to climb for about 10 seconds, as the airspeed increased to about 95 knots. During this time the second right turn began, lasted for about 9 seconds, at an average turn rate of 9-12° per second. At 1356:34, just before the end of the second turn, the helicopter began to descend rapidly from its peak altitude of 2,650 ft. About 6 seconds later, the descent rate reached 7,200 feet per minute. As it descended through 1,900 ft (just below the cloud ceiling height reported at SWF), the descent rate reached 16,200 feet per minute. The tracking data ended about 2 seconds later, about 0.6 nautical miles north of the accident site. The entire flight was about 70 minutes long and the accident site was located about 120 nautical miles south of GFL. A witness on a hiking trail about 0.1 mile southeast of the accident site reported hearing the helicopter’s engine “falter and die.” One to two seconds later, he heard a swishing sound, which he attributed to the helicopter “spinning” or being “out of control;” however, he could not see the helicopter due to the tree canopy. Shortly thereafter, he heard a series of loud noises that he described as “backfires, at machine gun speed” for about 2 seconds, which he surmised was “the engine catching and the rotors slapping,” and then the sounds stopped. He reported that the visibility was “clear,” and the clouds were higher than the mountain peaks; there was no fog over the river, and he could see the river clearly from his location on the hiking trail. A second witness located about 1/2-mile northwest of the accident site reported hearing a “loud noise” that he believed was the helicopter’s engine. When he turned toward the noise, he observed the helicopter in a nose-down attitude of nearly 90°, travelling at a “high speed…straight down.” The witness lost sight of the helicopter as it descended below a tree line; shortly thereafter, he “heard it crash.” The noise he associated with the helicopter’s engine was continuous until the sound of impact. Examination of the accident scene revealed a debris path that was about 110 ft-long and oriented on a heading of about 168° magnetic. It began with damaged treetops and broken limbs, where the tail rotor assembly and fragments of the tail rotor guard were located. The tail rotor blades were largely intact with leading edge gouge damage. The main impact crater, which contained fragmented landing gear components, was about 60 ft from the damaged tree, with the main wreckage located about 60 ft beyond the impact crater. The fuselage was fragmented and compressed from the nose toward the rear seats. Flight control continuity could not be confirmed due to impact damage and some system portions were not located. However, all flight control attachment fittings remained attached at their ends. Most of the flight control push-pull tubes were fractured, some in multiple locations, consistent with overload. The overriding clutch operated normally and smoothly when rotated by hand. The upper drive sheave had impact marks on the front and rear faces adjacent to the clutch centering strut and fuselage frame tubes, respectively. A 3-inch imprint consistent with the starter ring gear was present in the grooves of the upper sheave. The main and auxiliary fuel tanks were impact damaged; their bladders were breached, and a trace amount of fuel remained in the bladders. Some vegetation surrounding the impact crater and the main wreckage showed evidence of fuel blight. A portion of each main rotor blade (about 4 to 6 ft) remained attached to the hub. Most of the spar of one blade also remained attached. Fragments of damaged main rotor blades were found along the debris path; the outboard 3 ft of one blade was found 273 ft northwest of the main wreckage. Some fragments were found with wood debris in the leading edge, others with chordwise streaks of brown residue on the surface consistent with tree material. Score marks oriented in the direction of rotation were found on a fuselage frame tube adjacent to the tail rotor drive shaft intermediate coupling. The filament of the low rotor speed warning lamp on the cockpit instrument panel was found intact and demonstrated hot filament stretching. The engine crankshaft rotated smoothly when turned by hand at the cooling fan. Crankshaft and valvetrain continuity were confirmed as the crankshaft was rotated. Two of the cooling