On November 7, 2003, at 1715 central standard time, a Hughes 269A, N1015T, registered to Hoverwork Helicopters Inc., operated by Liberty Flight Center, as a 14 CFR Part 91 instructional flight, collided with the ground next to taxiway "B", at the Birmingham International Airport, Birmingham, Alabama, while on approach to a hover. Visual meteorological conditions prevailed and no flight plan was filed. The helicopter received substantial damage. The commercial pilot flight instructor (CFI) and commercial pilot receiving instruction reported no injuries. The flight originated from Birmingham International Airport on November 7, 2003, at 1710. The CFI stated a preflight inspection was conducted and no anomalies were noted. They entered the helicopter, conducted the required checks, started the helicopter, and contacted Birmingham Tower for taxi clearance. They received clearance to hover to the sod area located in the vicinity of taxiway "B". The pilot receiving instruction initiated the hover and hovered to the sod area at 50 feet. The rotor rpm was in the green and the manifold pressure indicated 25 inches. The landing light was not used. The pilot receiving instruction started his descent over the sod area and planned to come to a 3-foot hover. The rotor rpm remained in the green and manifold pressure was decreased to 20 inches. The pilot receiving instruction continued the descent down to about 5 feet. The CFI stated the ground was coming up and the manifold pressure was still at 25 inches. The CFI took over the flight controls with the other pilot, and increased the throttle, but there appeared to be no response. The CFI leveled the helicopter and it collided with the ground in a level attitude. Everything appeared to be ok, but it felt like something gave way or broke on the airframe. The CFI increased collective pitch and was able to hold the helicopter level for about 3 to 4 seconds before it rolled over on its left side. Examination of the helicopter after they exited revealed the cross tubes on the left side had broken. Examination of the crash site revealed the left skid of the helicopter dug into the ground on a 45-degree angle clockwise to the flight path. The left skid collapsed, and the cross tube support brackets were broken. The right skid was intact. The helicopter rolled over on its left side. All three main rotor blades were damaged and tail boom separated. A compression test was performed on all engine cylinders. The compression was 70/80 on all cylinders except for cylinder 4. The compression on the No. 4 cylinder was 21/80.