N142MK

On October 2, 2006, at 0930 Hawaiian standard time, an MD Helicopters, Inc., (MDHI) 369E, N142MK, experienced cyclic control difficulty during takeoff and landed hard at Hilo International Airport, Hilo, Hawaii. During the accident sequence, the tailboom was bent and the right skid collapsed. K and S Helicopters, Inc., was operating the helicopter as an on-demand air taxi tour flight under the provisions of 14 Code of Federal Regulations Part 135. The commercial pilot and two passengers were uninjured; two passengers sustained minor injuries. The helicopter sustained substantial damage. Visual meteorological conditions prevailed and a company flight plan was in effect. The 45-minute local tour flight was originating at the time of the accident with a planned return to Hilo.

The pilot submitted a written statement regarding the accident. On the second flight of the day, she had the helicopter refueled without shutting down. Once the helicopter was refueled, the four passengers were loaded onboard. After the passenger briefing, she removed the friction locks and conducted a gauge check. Then, the pilot showed the front passengers where to comfortably rest their feet during the flight so as not to conflict with her access to the radio stack. To do this, the pilot brought her right foot aft, demonstrating to the passengers how to position their feet. After receiving a tower clearance, she entered her squawk code into the transponder and applied flight controls to lift the helicopter off the ground. The cyclic felt heavy to the right, so she applied left cyclic trim to even out the flight control forces. The pilot felt the inputs to the cyclic control were normal and began to transition to forward flight. As the helicopter accelerated, more left trim was necessary to maintain coordinated flight. At this point, the pilot indicated that she ran out of left trim. The helicopter began rolling to the right and the pilot attempted to increase left cyclic input to counter the roll. The helicopter was about 5 to 10 feet above ground level when she aborted the takeoff and applied aft cyclic to slow the helicopter, but it continued to roll to the right. The helicopter impacted the ground, and the right skid collapsed as the helicopter slid to a stop. The pilot stated that she reached down and released the cyclic friction after impact.

A Federal Aviation Administration inspector from the Honolulu Flight Standards District Office examined the helicopter on October 11, 2006. The inspector indicated that the cyclic lateral and longitudinal frictions were off and that the cyclic was in a neutral position. Control continuity was obtained through the flight control systems and the trim system functioned optimally. In addition, the one-way lock valve function operated normally. The inspector attempted to simulate bumping the cyclic lateral lock lever to transition it from an unlocked position to a locked position. The inspector noted that when he brought one of his feet aft farther than normal, the lever might be inadvertently applied. According to the inspector, the installation of the lateral cyclic lock was in compliance with the Supplemental Type Certificate (STC) requirements, and the rotorcraft flight manual supplement required by the STC was onboard the helicopter.