Flight and Accident
The helicopter was returning from a flight to photograph the adult passenger's parent's house. While descending for an approach to a ball field at an altitude between 250 to 300 feet above ground level (agl) and an indicated airspeed between 60 to 65 knots, the helicopter yawed. The pilot corrected the yaw with anti-torque pedal and observed that the engine rpm and main rotor rpm needles were 'split'—the main rotor rpm was within the green arc, but the engine rpm indicated zero.
Pilot Actions
In response, the pilot rolled the throttle to the right toward the fuel-on position, then lowered full collective and maintained 40 to 45 knots while descending for an autorotative landing to a down-sloping road. He cleared a bridge ahead and, at approximately 15 feet agl, applied aft cyclic to decelerate 'somewhat' and pulled full collective. Touchdown occurred at an indicated airspeed between 20 and 30 knots on a road that curved left. The pilot later reported, 'we didn't hit real easy.' After touchdown, he lowered full collective, and while sliding, the right skid contacted grass on the side of the road, causing the right skid to collapse. The helicopter then rolled onto its right side and slid approximately 4 to 5 feet before coming to rest. There was no postcrash fire or fuel leakage.
Post-Accident Examination
An FAA Airworthiness Inspector examined the helicopter and found 8 to 9 gallons of fuel on board. The carburetor bowl was approximately half full and contained a slight amount of contamination. The engine-driven fuel pump would not produce 2 psi flow and would not produce any flow with a minor restriction. Additionally, the auxiliary fuel pump strainer was 'so clogged and corroded it had to be removed with a metal hook and screw driver.' The helicopter had last been inspected in accordance with a 100-hour inspection signed off on January 5, 2001, and had accumulated approximately 24 hours since that inspection at the time of the accident. Review of the helicopter flight manual sections pertaining to engine failure above 325 feet agl indicate procedures including maintaining 50 to 60 mph glide speed, pulling cyclic stick steadily back at approximately 75 feet agl, and, when 10 to 15 feet above the landing surface, leveling the helicopter with forward cyclic and applying collective pitch to cushion the landing. The manual also notes that to reduce rate of descent and forward speed during an autorotation landing, the flight path should be flared or leveled out prior to ground contact.