Plane Crash Reports 2003

2003 Plane Crash Report Result

Title: SCHWEIZER 269C, N98TH, DESCENDED INTO TERRAIN IN A MARSH AREA OF

Report Date: 01/16

Plane Crash Problem: On January 4, 2003, about 1532 Pacific standard time, a Schweizer 269C, N98TH, descended into terrain in a marsh area of the Sacramento River Delta near Collinsville, California. The helicopter was operated by the private pilot under 14 CFR Part 91. The pilot, the sole occupant, sustained fatal injuries, and the helicopter was destroyed. Visual meteorological conditions prevailed for the local area personal flight that departed from the Concord, California, airport about 1430. No flight plan was filed. Two witnesses in a boat observed the helicopter flying about 500 feet above the terrain/water. One reported seeing it in normal straight and level flight while over the water, and the engine sounded "tinny." The helicopter turned toward land, the engine sound became quiet, and it descended rapidly to the ground. The other witness reported that his attention was drawn to the helicopter when he heard a "pop" followed by a grinding noise. He noticed that the rotors were slowing down as the helicopter dropped while in a left-hand turn or rotation. Post accident examination of the helicopter and its systems was performed by the Safety Board investigator, Federal Aviation Administration personnel, and manufacturer representatives. The engine was examined for valve train continuity, cylinder compression, appearance of the spark plugs, magneto timing, and oil filter contaminants. Also, portions of the fuel system were examined including the fuel screens and the fuel boost pump, which was functionally tested. The remaining fuel onboard was measured to be about 10 gallons between both fuel tanks. Its quantity was found above the level required to activate the low level switch, which was functionally tested. The helicopter clutch, drive system, and controls were examined. The continuity of the control system was confirmed. All chip detectors were found to be clean. Annunciator light bulbs were examined for element stretch. The tail rotor system was examined. Minimal damage was observed to the tail rotor blades. Two of the main rotor blades also exhibited minimal damage. The engine was removed from the airframe and all sumps were drained of oil and water. The engine was lubricated with fresh oil to displace water entrapped inside. The engine is being shipped to the manufacturer for an additional examination including a test cell run.

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