20150520007129A

5/20/2015: This FSDO received a call at approximately 1115 about an occurrence at the Kearny heliport (65NJ) involving a Bell 206L-3, s/n 51379, N210MH, operated by new york helicopter, inc. the helicopter was being leased from meridian helicopters LLC, broussard, LA. The aircraft was operating as a CFR part 91 sight-seeing flight, and had just been refueled prior to the incident. The pilot reported that he had taken on 350 lbs. Of fuel, was lifting off from the landing dolly into a hover and at 20 feet he started to get a right yaw, at which time he applied about half of his remaining left pedal; the aircraft continued to yaw, at which time he applied the remaining left pedal. The aircraft continued to yaw and pick up speed; the aircraft did at least 3 full rotations as it travelled back over behind the landing dollies, at which time the pilot stated he was able to bring the aircraft into a 10 foot hover. He rolled the throttle off and pulled on the collective as the aircraft touched down, still yawing to the right. He shut the engine down and exited the aircraft. An eyewitness observed the incident and stated that the helicopter was in an uncontrolled right-hand spin, that it spun approximately 4 times, and that the tail rotor blades were not spinning at full power during his observation.

Upon arrival at the heliport, it was noted that the helicopter came to rest upright and was located approximately 60 feet aft and to the left of the landing dolly from which it departed. There were marks on the ground consistent with the helicopter rotating prior to coming to a complete stop. The left-hand vertical fin, attached to the horizontal stabilizer, and the left-hand side of the tail rotor driveshaft cover, showed impact damage consistent with main rotor rotation contact from the main rotor blades; both main blades showed contact and paint transfer from impacting the left-hand vertical fin and driveshaft cover. The tips of both tail rotor blades, as well as the lower portion of the horizontal stabilizer, exhibited impact damage consistent with contact with the ground,. The aft, lower section of the tailboom skin was wrinkled, and the fiberglass fairing at the airframe-to-tailboom juncture was cracked consistent with tail boom flexing. Both landing gear crosstubes were bent, with the airframe exhibiting a lean to the left. It was noted that when the main rotor was rotated, the tail rotor assembly did not rotate. The helicopter was moved to the hangar, where the tail rotor driveshaft cover was removed. Further investigation revealed that the aft bonded flange of the # 3 tail rotor driveshaft was loose on the driveshaft assembly, p/n 206-040-370-011. There was material residue found on top of the tailboom, under the driveshaft flange, and on the inside of the tail driveshaft cover. The end of the driveshaft exhibited rotational grooves consistent with the shaft spinning inside the flange. The inside of the flange and the outer surface of the driveshaft showed signs of corrosion. The tail rotor driveshaft bearing, just aft of the driveshaft, showed no signs of overheating, and rotated freely.

The aircraft records indicated that the airframe had been installed (9/2/2014) in an airframe fixture by arrow aviation (FAA crs # Y3AR527Y), and then an annual type (100, 300 & 1200 hour airframe inspections) and hard landing inspections were completed on 4/28/2014 @ airframe total time: 2949.9.