WPR18FA077

The pilot's failure to perform weight and balance calculations before departing on the flight, which resulted in his operation of the helicopter outside of its published weight and balance limitations and a subsequent loss of control shortly after takeoff.

The private pilot of the helicopter departed with three passengers on a cross-country flight in day visual meteorological conditions. Surveillance video of the takeoff showed that the helicopter assumed a nose-low attitude upon lifting off the ground and mostly maintained that attitude throughout the takeoff and initial climb. Radar data indicated that the helicopter reached a maximum altitude of 500 ft mean sea level before it entered a rapid descent and impacted homes and the ground less than 1 mile from the departure airport. The surviving passenger described the descent as "straight down." An examination of the airframe, engine, and related systems revealed no evidence of preimpact mechanical malfunctions or failures that would have precluded normal operation. Weight and balance calculations revealed that the helicopter was operating 76 lbs over its published maximum gross weight and near the published forward center of gravity (CG) limits. The helicopter's observed nose-low attitude throughout the flight is consistent with a forward CG, which would have required additional aft cyclic control inputs to maintain level flight and may have resulted in reduced cyclic control travel. The passenger stated that the pilot did not ask any of the passengers for their weights, nor did he instruct them where to sit, suggesting that the pilot did not perform weight and balance calculations before the flight. Given the lack of mechanical anomalies, it is likely that the pilot experienced a loss of helicopter control due to his decision to operate the helicopter outside of its published weight and balance limitations.

The Orange County Coroner, Santa Ana, California, performed an autopsy on the pilot. The autopsy report indicated that the cause of death was multiple blunt force traumatic injuries. Toxicology testing on specimens recovered from the pilot performed at the FAA Forensic Sciences Laboratory identified unspecified amounts of Irbesartan in the blood and urine. Irbesartan is a prescription medication used alone or in combination with other medications to treat high blood pressure. It is not considered to be impairing. A review of recorded data from the SNA automated weather observation station, located about 2 miles north of the accident site, revealed that the conditions at 1353 included wind from 210° at 5 knots, visibility 10 statute miles, few clouds at 13,000 ft above ground level (agl), broken cloud layer at 18,000 ft agl, temperature 26°C, dew point -2°C, and an altimeter setting of 29.98 inches of mercury. The pilot held a private pilot certificate with a rotorcraft-helicopter rating and a third-class FAA medical certificate issued on July 11, 2016, with no limitations. The pilot reported on the application for the medical certificate 195 total hours of flight experience, of which 25 hours were in the previous 6 months. The pilot's logbooks were not located. The helicopter impacted multiple residential structures and a residential street about 0.95 nm miles south-southeast of the departure end of runway 20R at SNA. The initial impact point was identified by damage to the roof of a single-story home. The tail rotor gearbox and one tail rotor blade were located on top of the roof of a single-story home, partially lodged within a hole in the roof. The empennage and opposing tail rotor blade were located between the two homes, surrounded by thick vegetation. Additional impact damage was observed to a palm tree located between the homes. Numerous impact gouges and paint transfer marks were located on the street in front of both homes, consistent with fuselage and main rotor blade impact. The helicopter came to rest on its left side against a single-story home on a heading of about 189° magnetic, about 86 ft from the first identified point of impact. Throughout the wreckage debris path, plexiglass fragments, clay roofing material, palm tree fragments, and portions of both main rotor blades were observed. The empennage and the aft section of the tailcone were separated from the airframe. The empennage was separated from the tailcone. The tail rotor gearbox was separated from the empennage and tailcone. The skids were detached and folded underneath the wreckage. The forward section of the tailcone was bent forward almost 180°. The forward tail rotor drive shaft flex coupling was intact. The intermediate flex coupling was distorted and detached at one arm. The tail rotor drive shaft was separated into multiple sections. The tail rotor drive shaft damper assembly was detached from the tailcone and the tail rotor drive shaft bearing. The bearing rotated freely. The friction at the damper linkage was normal. The aft flex coupling was detached at the tail rotor gearbox yoke input arms. The tail rotor gearbox rotated freely and contained oil. The slider bearing rotated freely. One of the tail rotor blades was separated and distorted. The opposing blade remained attached and exhibited leading edge damage. The drive belts remained intact and in place within their respective grooves. The sprag clutch operated normally. The belt tension actuator was intact and when operated, the belt tension actuator extended and contracted. Both the upper and lower actuator bearings rotated freely. The main rotor blades remained attached to the hub. Both main rotor blades were intact. One of the rotor blades was bent upward about mid-span and exhibited slight bending opposite of the direction of rotation near the blade tip. A portion of the blade honeycomb skin structure was torn away from the spar at the blade tip. The opposing main rotor blade exhibited dents and scuffs about 10 inches outboard of the hub. The blade was bent downward about 135° about 2 ft outboard of the hub. The blade was also bent upward mid-span and bent aft opposite of the direction of rotation along the outboard third of the blade. A portion of the blade honeycomb skin structure was torn away from the blade tip. Dents observed in the oil cooler were consistent with impact from the starter ring gear. At the upper belt sheave, score marks consistent with rotational contact from adjacent components were observed. Flight control continuity was established throughout the helicopter from the cockpit controls to the main rotor and tail rotor controls through various overload fractures. The engine remained attached to the airframe. The upper spark plugs were removed. The electrodes were undamaged and exhibited color consistent with normal operation with the exception of the No. 3 spark plug, which was oil-soaked. The engine crankshaft was rotated using the cooling fan. Compression and suction were obtained on all six cylinders. The oil sump screen was removed and contained two small plastic fragments consistent with the magneto drive bushings. The oil filter was removed and cut open. The internal filter element exhibited no debris. The engine was installed on a test stand. In order to facilitate an engine run, a slave starter and propeller were installed. The engine was started and ran uneventfully. During the engine run, the No. 3 cylinder was not producing any exhaust gas temperature (EGT) readings on the engine monitoring unit installed on the test stand. The engine was shut down and further inspected. The bottom spark plug lead of the No. 3 cylinder was found impact damaged, and the upper spark plug lead was pulled away from the ignition cap. A serviceable ignition harness was installed for both the left and right magnetos. The engine was started a second time and operated throughout various power settings. At maximum power, the engine produced 2,600 rpm at 29 inches of manifold pressure. Engine rpm drops during magneto tests were within specification. The engine ran uneventfully until it was shut down using the mixture cut-off. No evidence of any preexisting mechanical malfunction was observed with the airframe or engine. For further information, see the Accident Site, Airframe, and Engine Examination Summary report and Robinson Helicopter's report within the public docket for this accident. The accident helicopter was a Robinson Helicopter R44, serial number 1295, and was powered by a 235-horsepower Lycoming O-540-F1B5 engine, serial number L-25375-40A. The most recent 100-hour inspection was completed on December 7, 2017, at a Hobbs time of 568.6 hours and an airframe total time of 6,966.3 hours. The most recent annual inspection was completed on June 1, 2017, at a Hobbs time of 383.9 hours, airframe total time of 6,781.6 hours, and engine time since major overhaul of 383.9 hours. According to representatives from a fixed-base operator located at SNA, the helicopter was refueled with 15.8 gallons of 100 low-lead aviation fuel based on a request to top off the main fuel tank only. Using the basic empty weight of the helicopter, fuel load, and weights of the occupants and baggage, the helicopter weighed about 2,476 lbs at the time of takeoff with a longitudinal center of gravity (CG) of 93.42 inches. The calculated weight exceeded the published maximum gross weight of 2,400 lbs and the CG was near the forward range noted in the R44 Pilot Operating Handbook. On January 30, 2018, about 1350 Pacific standard time, a Robinson Helicopter R44, N7530R, was destroyed when it impacted houses near Newport Beach, California shortly after takeoff. The private pilot and two of the three passengers sustained fatal injuries, one passenger sustained serious injuries, and one person on the ground sustained minor injuries. The helicopter was registered to Spitzer Helicopt