On August 25, 2003, at 1045 central daylight time, a Robinson R22 Beta helicopter, N731BA, was substantially damaged during a forced landing following a loss of tail rotor effectiveness while maneuvering near Ozona, Texas. The helicopter was registered to and operated by Holt Helicopters Inc., of Uvalde, Texas. The commercial pilot and passenger were seriously injured. Visual meteorological conditions prevailed, and a flight plan was not filed for the 14 Code of Federal Regulations part 91 flight. The local flight originated from a staging area three miles west of the accident site, approximately 30 minutes before the time of the accident. The 15,367-hour pilot reported in the Pilot/Operator Aircraft Accident Report (NTSB Form 6120.1/2), that he and a passenger were hunting hogs for animal damage control on a ranch south of Ozona. During the flight he was following a hog up the side of a rocky ridgeline at approximately 25 feel agl. As the helicopter started to overtake the hog, he pulled the helicopter into a hover to keep from over flying it. The pilot stated the helicopter "hit some dirty air and lost some tail rotor effectiveness." He then "added left pedal and increased power, but the helicopter didn't respond." The pilot further stated he "had no altitude, or airspeed to make a recovery." Subsequently, the helicopter spun to the right and settled into the side of the ridge coming to rest on its left side. According to FAA's Advisory Circular 90-95, loss of tail rotor effectiveness (LTE) "is a critical, low-speed aerodynamic flight characteristic that can result in an uncommanded rapid yaw rate which does not subside of its own accord and, if not corrected, can result in the loss of aircraft control. LTE is not related to a maintenance malfunction and may occur in varying degrees in all single main rotor helicopters in some of the conditions conducive to LTE include a high power setting, low airspeed, and a tailwind or left crosswind." Examination of the helicopter by an FAA inspector, who responded to the site of the accident, revealed the tail boom was separated in three places, both main rotor blades were bent, both tail rotor blades were bent, and both landing skids were separated.