HISTORY OF FLIGHT On March 24, 2011, about 1655 central daylight time, a Bell 206-L3 helicopter, N32041, impacted water shortly after takeoff from an offshore oil production platform, Main Pass 61A (MP61A), located in the Gulf of Mexico. The commercial pilot and two passengers received minor injuries. The helicopter was substantially damaged. The helicopter was registered to and operated by PHI, Inc., under the provisions of 14 Code of Federal Regulations Part 135 as an air taxi flight. Visual meteorological conditions prevailed for the flight and a company flight plan had been filed. According to the pilot and passengers, the helicopter lifted from the oil platform and started to depart, when they heard a loud bang. The pilot lowered the nose of the helicopter, initiated an autorotation, and deployed the floats. The helicopter impacted the water and immediately rolled over, coming to rest upside down in the water. The pilot and front seat passenger were able to exit the helicopter unassisted. The pilot then assisted the rear cabin passenger in exiting the helicopter. The pilot stated he tried to deploy the life rafts; however, the raft system did not deploy from the helicopter before a nearby boat assisted him and passengers from the water. The pilot further stated that they added fuel (hot refuel) to the helicopter prior to the departure from the oil platform. The pilot added that when the bang occurred, he saw the torque gauge read high, and did not notice any other gauges before looking back outside. The pilot also stated that he departed the platform in a northwest direction and into the wind. The pilot further added that the oil platform had exhaust pipes, but did not know what came out of them, or if they were flaring gas at the time of his departure. The production foreman on the platform later reported that they were venting methane gas about the time the helicopter departed the platform. WRECKAGE AND IMPACT INFORMATION The helicopter was recovered and transported to PHI’s facilities and an examination of engine and airframe conducted. Examination of one of the main rotor blade revealed that it had fractured just outboard of the doubler, the other rotor blade remained attached to the mast. The blade exhibited spanwise bending along the length, with a chord-wise tear, approximately mid-span. The mast exhibited heavy bending just below the rotating swash plate. During recovery from the water, the helicopter’s tailboom was torn from the fuselage just aft of its attachment point. The tailboom was not recovered from the water. The right side pilot’s door was not on the fuselage; the right side “A” pillar was fractured. Both left and right side windscreens and chin bubbles were broken. Prior to transport the main rotor head, main rotor blades and the mast were removed to facilitate transport. The examination of the engine and airframe did not reveal any abnormalities that would have precluded normal operation of the helicopter, prior to the accident. TEST AND RESEARCH The helicopter was equipped with an Intellistart engine data monitoring system which was downloaded and plotted. A review of the data reveals a slight “spike” on the engine torque and TOT (turbine outlet temperature) readings, which likely occurred at the same time the occupants, heard a loud bang. The chart then depicts the torque and TOT to drop sharply, before a rapid recovery. At the time of the spike, the helicopter’s main rotor speed has a slight increase, followed by a decrease, and recovery, before a sudden decrease in main rotor speed. The significant decrease in main rotor rpm is believed to be associated with the main rotor blades impacting the water surface. The helicopter was equipped with the Apical Industries, Inc. float and life-raft system. An alert service bulletin, SB2010-02, dated 01/18/11, was issued by Apical Industries, Inc. that recognized and addressed a problem with the system’s float inflation valve. The operator stated that the service bulletin’s updated valve was not installed in the accident helicopter, and would normally be incorporated into the helicopter’s regular maintenance schedule. The service bulletin allowed operators until May 1, 2011 to comply with the update. A review of the Height-Velocity diagram contained in the Bell 206L-3 helicopter’s Flight Manual, reveals that at 100 feet above ground level, operations with indicated airspeeds below 51 knots should be avoided. Per the Federal Aviation Administration Rotorcraft Flying Handbook, FAA-H-8083-21, the height/velocity (H/V) diagram depicts critical combinations of airspeed and altitude should an engine failure occur. Operations in crosshatched or shaded areas of the H/V diagram may not allow enough time for the critical transition from powered flight to autorotation. The pilot estimated the height of the helicopter’s platform was 100 to 120 feet above the water.