On June 8, 2000, at 1630 central daylight time, a Piper PA-28R-200 single engine airplane, N4861T, was substantially damaged when the nose and main landing gear collapsed during the landing roll at the Mesquite Metro Airport, near Mesquite Texas. The airplane was registered to, and operated by the pilot. The private pilot and his passenger were uninjured. Visual meteorological conditions prevailed and a flight plan was not filed for the 14 Code of Federal Regulations Part 91 local flight. The flight originated from the Mesquite Metro Airport approximately 1615. The 237-hour pilot reported to the NTSB investigator-in-charge that a few flights prior to the accident flight, the airplane was yawing to the right. The pilot stated that his mechanic found the right main landing gear would not retract completely. He added that the mechanic made "adjustments" to the right main landing gear the morning of the accident, and he was going to test fly the airplane. The pilot stated that after the test flight, he landed on runway 17. He added that "after touchdown on the rollout, after all three wheels were on the ground, the plane leaned to the right and turned to the right." In an attempt to correct for the right turn, the pilot applied full left rudder. Subsequently, the airplane spun 180 degrees to the left and came to rest in the grass adjacent to the runway with the nose and main landing gear collapsed. At 2153 UTC, the weather observation facility at the Mesquite Metro Airport reported the wind from 130 degrees at 13 knots. The pilot reported the wind at the time of the accident was from 130 degrees at 7 knots. On June 22, 2000, an FAA inspector, a representative from the aircraft manufacturer, and the owner's representative, conducted an examination of the wreckage. According to the report from the aircraft manufacturer, the right main landing gear assembly was found "pulled loose from its normal position." The right main landing gear truss assembly was buckled near mid-span between attach points. The damage to the right main landing gear assembly and truss assembly was "consistent with sideways (inboard) pressure in excess of design limits being applied." The left main landing gear was extended beyond its "normal travel." The bolt that attaches the left main landing gear truss assembly and the link assembly had been pulled sideways (outboard) with "sufficient force to pull the bolt through the mounting hole and cause failure of the left main landing gear truss assembly." The bolt remained attached to the link assembly. The nose landing gear was extended and the strut assembly was bent to the left. The nose landing gear lock link was broken at the lower pivot point. The steering cam assembly was broken at the center pivot point. The breaks on the nose landing gear structure were found "clean with no indication of corrosion or pre-existing damage." The aircraft manufacturer representative stated that all damage noted was consistent with application of (sideways) force in [excess] of design limits. No indication of pre-impact failure or malfunction was noted."