20040601011619A

(-23) INVESTIGATION REVEALED THAT THE AIRCRAFT'S LEFT WING CONTACTED THE ROOF OF A HOUSE AT A VERY HIGH ANGLE OF ATTACK CAUSING THE AIRCRAFT TO IMPACT THE GROUND AT A HIGH RATE OF SPEED. NOTE: WILL AMEND SECTIONS 23, 24, 25, 29, 31 AND 42-3/4/8/9 WHEN INFORMATION BECOMES AVAILABLE. (-23 AMENDMENT) AT APPROXIMATELY 2040 CST A CESSNA U-206-F N81685 WAS INVOLVED IN AN ACCIDENT FATALLY INJURING THE PILOT AND ALL THREE PASSENGERS. WEATHER AT THE TIME OF ACCIDENT: KOWA AUTO 320 11 G14KT 4 SM BKN008 OVC013 12/12 ALT 2969 RMKA02 INVESTIGATION REVEALED THAT THE LEFT WING OF THE AIRCRAFT CONTACTED THE ROOF OF A HOUSE LOCATED AT^PRIVACY DATA OMITTED^CREATING A THREE-FOOT WIDE SWATH CUT LATERALLY THROUGH THE ENTIRE TOP PORTION OF THE ROOF. THE AIRCRAFT IMPACTED THE GROUND CAUSING AN IMPACT CRATER APPROXIMATELY 10' LONG BY APPROXIMATELY 4' WIDE WHERE THE AIRCRAFT CONTACTED THE BASE OF A LARGE TREE. THE AIRCRAFT ENGINE AND A PORTION OF THE INSTRUMENT PANEL WAS FOUND AT THE BASE OF THE TREE AND THE REST OF THE AIRCRAFT AND CONTENTS WERE FOUND IN THE ENERGY PATH FROM POINT OF IMPACT OF TREE APPROXIMATELY 500' LONG AND 150' WIDE. THE CABIN OF AIRCRAFT WAS COMPLETELY DESTROYED; SEAT RAILS FOUND NOT INTACT, FOUR SEATS OBSERVED; ALL SEPARATED FROM SEAT RAILS. ALL RESTRAINTS EITHER OVERLOADED AT WEBBING OR SEPARATED AT ATTACH POINTS. NO VISUAL PRE-IMPACT ANOMALIES WERE OBSERVED DURING THE ON-SITE INSPECTION OF THE AIR FRAME ENGINE AND SYSTEMS. THE ELT WAS FOUND INTACT AND IN THE OFF POSITION. THE PROPELLER WAS FOUND IN THE IMPACT CRATER AND EXHIBITED S-BENDING, LEADING EDGE GOUGING AND CHORD WISE SCORING. FUEL; FUEL BLADDERS WERE BOTH BREACHED HOWEVER ODOR OF FUEL WAS PRESENT AT SITE. 100LL FUEL WAS OBSERVED INSIDE FUEL SELECTOR VALVE. THE FUEL SELECTOR VALVE POSITION WAS FOUND SELECTED BETWEEN THE LEFT TANK AND THE OFF POSITION. ENGINE; SPARK PLUGS WERE REMOVED FROM ENGINE AND APPEARED TO BE CLEAN. VACUUM PUMP WAS REMOVED FROM ENGINE AND APPEARED TO BE INTACT. VACUUM PUMP DRIVE WAS FOUND TO BE INTACT. MAIN FUEL SCREEN WAS REMOVED AND CLEAR. ENGINE OIL FILTER WAS REMOVED, OPENED UP AND NO FOREIGN MATERIAL FOUND. INSTRUMENTS; ATTITUDE GYRO WAS DISASSEMBLED AND SCORING WAS NOTED INDICATING THAT IT WAS SPINNING AT THE TIME OF IMPACT. HEADING GYRO WAS DISASSEMBLED AND SCORING WAS NOTED INDICATING THAT IT WAS SPINNING AT THE TIME OF IMPACT. ENGINE TACHOMETER INDICATED APPROXIMATELY 2900 RPM'S AND TACH TIME WAS 2048.4. FLIGHT CONTROL CONTINUITY: ELEVATORS: CONTINUITY ESTABLISHED FROM THE ELEVATOR BELL CRANK THROUGH EMPENNAGE. ELEVATOR TRIM TAB: CONTINUITY ESTABLISHED FROM SURFACE THROUGH EMPENNAGE. TRIM TAB ACTUATOR ROD WAS FOUND SEPARATED FROM TAB SURFACE RESULTING IN A NON-RELIABLE ELEVATOR TRIM SETTING. RUDDER: CONTINUITY ESTABLISHED FROM AFT SECTOR UP THROUGH EMPENNAGE. ELEVATOR/ELEVATOR TRIM/RUDDER: ALL CONTROL CABLES WERE FOUND TO BE TENSION OVERLOADED. CONTINUITY WAS NOT ESTABLISHED FROM EMPENNAGE THROUGH CABIN SECTION DUE TO IMPACT DAMAGE. AILERONS: CABLES AREA TENSION OVERLOADED. FLAPS: CABLES ARE TENSION OVERLOADED. FLAP JACKSCREW WAS INTACT AND EXTENDED 1/2 INCH INDICATING THE FLAPS 0 TO 5 DEGREES EXTENDED. NO FLIGHT CONTROL CABLE CONTINUITY ESTABLISHED IN COCKPIT DUE TO EXTENT OF DAMAGE. NOTE: ^PRIVACY DATA OMITTED^ CESSNA AIRCRAFT COMPANY/^PRIVACY DATA OMITTED^, TELEDYNE CONTINENTAL MOTORS, INC. WERE PRESENT DURING THE INVESTIGATION AND PERFORMED THE DISASSEMBLY OF ALL PARTS NOTED ABOVE.