HISTORY OF FLIGHT On April 22, 2002, approximately 1130 Pacific daylight time, a Hiller UH-12E, N3004T, registered to and being flown by a commercial pilot, and being operated by Sundance Helicopters, Inc., sustained substantial damage during a hard autorotation landing following a total loss of power while in cruise near Goshen, Oregon. The pilot and two accompanying passengers were uninjured. Visual meteorological conditions prevailed and a company flight plan was in effect. The flight, which was engaged in a migratory waterfowl count, was operated under 14CFR91, and had originated from Eugene, Oregon, approximately 1030. The pilot reported that while flying along the Middle Fork of the Willamette River at an elevation of 100 feet above ground the engine coughed once followed by a return of power and then a complete loss of power. The pilot reported that in order to avoid a water landing he had to maneuver over trees approximately 50 feet in height, and that he had insufficient rotor RPM to complete the autorotation. The helicopter landed hard breaking the skids and damaging the tail boom (refer to photograph 1). PERSONNEL INFORMATION The pilot held a commercial pilot license with a helicopter rating and all of his reported 4,000 hours of flight experience was acquired in rotorcraft equipment. He also reported 3,500 hours in the Hiller UH-12 helicopter. AIRCRAFT INFORMATION The Operator reported that the helicopter had undergone a 100-hour inspection on April 10, 2002, at a total time of 4095.0 hours (Hobbs time of 640.0 hours). The 100-hour engine inspection was documented within the rotorcraft's engine log (refer to Attachment JPG-I). The Hobbs reading at the accident site was 659.8 hours. Appendix D to Part 43 of the Federal Aviation Regulations states in part: (d) Each person performing an annual or 100-hours inspection shall inspect (where applicable) components of the engine and nacelle group as follows: (8) Exhaust stacks - for cracks, defects, and improper attachment. (refer to Attachment APP-D). METEOROLOGICAL INFORMATION The aviation surface weather observation for the Eugene airport, taken at 1127 on the morning of the accident reported variable winds of three knots, an overcast at 1,500 feet, temperature/dew point of 10 and 7 degrees Centigrade respectively and 10 miles visibility. The Eugene airport bears 280 degrees and is 10 nautical miles distant from the accident site. TESTS AND RESEARCH A test run of the helicopter's engine at the Operator's facilities following the accident with oversight by personnel from the Federal Aviation Administration's Boise Flight Standards District Office determined that the engine would run but could not sustain power. Fuel samples from the helicopter's dual carburetor, fuel pump and fuel tank as well as two different samples taken from the Operator's fueling truck were hand delivered to the Department of the Air Force's Aerospace Fuels Laboratory, Mukilteo, Washington, for testing and examination. No detectable contaminant was found in any of the samples with the additional finding of a fine yellow particulate in the pump and carburetor samples, which was reported as most likely lead monoxide (refer to Attachment AFL-I through V). The dual carburetor was taken to the facilities of Precision Air Motive, Everett, Washington, where it was examined and flow checked. Although running slightly rich, the tests revealed no malfunction and satisfactory operation with either carburetor unit (refer to Attachment PAM-I). The dual carburetor unit was returned to the Operator and re-installed in the accident helicopter. A mechanic from Pendleton Aircraft Service was contracted to test the helicopter's engine and fuel system with oversight by personnel from the Federal Aviation Administration's Boise Flight Standards District Office and the participancy of Lycoming (refer to Attachments PAS-I and LYC-I). The test revealed that the left hand exhaust stack tube inside the cylindrical stainless steel heat muffler was cracked and separated circumferentially (refer to Attachments JPG-II, III, and IV). The left side muffler was dedicated exclusively to providing engine heated air for carburetor heat application (the right muffler exclusively providing cabin heat). When the scat tubing was disconnected from the muffler outflow (allowing engine intake air to bypass the carburetor heat source) the engine ran without problem. The exhaust stack tube was observed to be thin and heat distorted and the circumferential split was noted to be in the vicinity of an old weld (refer to Attachment JPG-V). The exhaust tube was also noted to have shifted aft several inches at the rear face of the muffler. Additionally, the carburetor heat valve within the plenum to the carburetor was found to be out of rig such that when carburetor heat was fully de-selected in the cockpit (FULL COLD), engine heated air was still partially flowing to the carburetor intake (refer to Attachment JPG-VI).