TYLER, TX, USA
N533CA
CESSNA T-210M
THE ENGINE LOST POWER INSIDE THE OUTER MARKER ON A PRACTICE ILS APPROACH. ACCORDING TO THE PILOT, HE SWITCHED TANKS FROM LEFT TO RIGHT, BUT COULDN'T RESTART THE ENGINE. HE REPORTED THE RIGHT TANK FUEL GAUGE INDICATED FULL, AND THE LEFT GAUGE INDICATED 1/2 FULL WHILE HE WAS SWITCHING TANKS. THE AIRPLANE THEN DESCENDED INTO TREES 3/4 MI FROM THE APPROACH END OF THE RUNWAY AND CAME TO REST APPROX WINGS LEVEL AND SLIGHTLY NOSE DOWN. DURING AIRCRAFT RECOVERY 19 HRS AFTER THE ACCIDENT, THE RIGHT FUEL TANK WAS OBSERVED TO BE EMPTY, AND THE LEFT FUEL TANK CONTAINED 27 GALS OF FUEL. NO FUEL SPILLAGE WAS NOTED AT THE SITE. THE RIGHT WING FUEL TANK WAS CHECKED FOR LEAKS; A 1 DROP PER SECOND LEAK WAS NOTED NEAR A DAMAGED AREA OF THE WING LEADING EDGE WHICH WAS CRUSHED BACK TO THE SPAR. NO PREVIOUS FUEL STAINS WERE NOTED NEAR THE CRUSHED AREA. THE ENGINE OPERATED NORMALLY DURING POST ACCIDENT TESTS ON BOTH LEFT AND RIGHT FUEL TANK SELECTOR VALVES.
On October 29, 1994, at 1347 central daylight time, a Cessna T-210M, N533CA, was substantially damaged during a forced landing in the vicinity of Tyler, Texas. The private pilot and one passenger received minor injuries. Visual meteorological conditions prevailed for the local personal flight. The pilot reported, in his endorsed statement, that while on a practice ILS approach to runway 13 at Tyler's Pounds Field, the "engine sputtered" during the outbound leg to procedure turn. He then switched fuel tanks from RIGHT to LEFT. Inside the outer marker, the "engine sputtered" again and lost power. The pilot then switched fuel tanks from LEFT to RIGHT, operated the boost pump, but could not restart the engine. The pilot further reported that the RIGHT fuel gauge indicated FULL and the LEFT gauge indicated "a little less than" 1/2 FULL while he was switching tanks. The airplane then descended into trees approximately 3/4 mile from the approach end of the runway and came to rest approximately wings level and slightly nose down. During aircraft recovery, 19 hours after the accident, the right fuel tank was observed to be empty and approximately 27 gallons of fuel was found in the left fuel tank. No evidence of fuel spillage was noted at the site. The right wing fuel tank was filled with water to check for leaks. It was noted that water seeped at a rate of 1 drop per second near a damaged area of the wing leading edge which was crushed back to the spar. No previous fuel stains were noted near the crushed area. Two engine runs were performed after the accident. One using the fuel selector valve on the RIGHT TANK position, and one using the LEFT TANK position. The engine started normally on both runs and was operated normally to 2500 RPM each time. Manifold pressure was observed as 23 inches on the LEFT TANK fuel selector, and 25 inches on the RIGHT selector. The main fuel screen was examined and found to be clean and clear.
LOSS OF ENGINE POWER DUE TO INADEQUATE FUEL MANAGEMENT AND FUEL STARVATION. A FACTOR WAS THE LACK OF SUITABLE TERRAIN AVAILABLE FOR THE FORCED LANDING.
Source: NTSB Aviation Accident Database
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