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N9612M accident description

Nevada map... Nevada list
Crash location 37.253333°N, 115.103333°W
Nearest city Alamo, NV
37.364961°N, 115.164461°W
8.4 miles away
Tail number N9612M
Accident date 09 Oct 2007
Aircraft type Mooney M20F
Additional details: None

NTSB Factual Report


On October 9, 2007, about 1244 Pacific daylight time, a Mooney M20F, N9612M, made a forced landing following a loss of engine power near Alamo, Nevada. The pilot/owner operated the airplane under the provisions of 14 Code of Federal Regulations (CFR) Part 91 as a personal cross-country flight. The airplane sustained substantial damage with structural damage to the wings. The private pilot and one passenger were not injured. The flight departed the Gooding Municipal Airport (GNG), Gooding, Idaho, about 1100 mountain daylight time (MDT), en route to the North Las Vegas Airport (VGT), Las Vegas, Nevada. Visual meteorological conditions prevailed and a visual flight rules (VFR) flight plan had been filed.

According to the Federal Aviation Administration (FAA), at 1220 a controller from Nellis Air Force Base radar identified the airplane, and was providing flight following services when the event occurred. At 1225, the pilot stated that the engine was losing power, and he was having a hard time maintaining altitude. At 1237, the Nellis controller lost radar and radio contact. Shortly thereafter, an airplane was sent out to find the accident airplane. The search airplane located, and then watched, as the accident airplane made a gear up landing on the desert floor.

The pilot reported that he had flown the airplane for 3.2 hours the day before the accident. He had departed for that flight to GNG with 6.5 quarts of oil. The next day he refueled at GNG with 44.7 gallons of fuel for a total of 64 gallons of fuel, and added 1 quart of oil to the engine for a total of 7 quarts of oil. He departed, and there were no problems experienced with the flight until they reached the Alamo area; about 2 hours into the flight. A few minutes before contacting Nellis, the pilot switched the fuel selector from the left tank to the right tank position. About 15 minutes later, the pilot observed the oil temperature gauge rise to about 200 degrees. He opened the cowl flaps and increased the mixture control, which dropped the exhaust gas temperature (EGT) by about 200 degrees. The oil temperature continued to rise for the next 2 minutes and the pilot declared an emergency with the Nellis controller. The pilot requested vectors to the nearest airport, but then determined that Alamo (Alamo Landing Field Airport), the closest airport, could not be reached. He prepared for a forced landing on a dirt road. The pilot observed the oil pressure needle to be well below the green arc. The propeller pitch went flat and the engine revolutions per minute (rpm) indicated 2,800 rpm's, which was the highest indication the pilot had ever seen on the rpm gauge.

The pilot stated that the engine began to backfire. When the airplane was about 500 feet above the ground, the engine froze and the airplane rolled sharply to the right. The pilot landed the airplane gear up in a sagebrush field, during which the airplane encountered a bush and sustained structural damage to the wing.

An FAA inspector responded to the accident site, and noted that the airplane came to rest upright on its belly and the propeller was in the feathered position. They visually inspected the airplane and did not remove the cowl, and found no oil on the outside of the airplane. The inspector was able to manually move the propeller about 8 inches in either direction.


The airplane was inspected by a National Transportation Safety Board investigator. A visual examination revealed a small hole in the crankcase above the number 4 cylinder. There was no evidence of oil observed on the cowling or airframe. Partial rotation of the propeller via the crankshaft was obtained. The throttle, mixture, and propeller control lines remained attached and secure in their normal positions. The Safety Board investigator drained about 0.50 to 0.75 quarts of oil from the oil sump. The investigator removed the engine from the airframe and disassembled it.

Both magnetos remained secured at their respective mounting pads. Manual rotation of both magnetos produced spark at their respective posts. The starter remained attached and rotated freely by hand. The investigator removed the spark plugs. When compared to the Champion Check-A-Plug comparison card, the top and bottom spark plugs exhibited worn to worn-out normal signatures. The top and bottom one, three, and four spark plugs exhibited light gray deposits within the electrode area. The top and bottom number two spark plugs were black in color within the electrode area.

The oil pump drive shaft rotated freely by hand, and exhibited scoring on the internal cavity. The investigator noted about .25 to .50 quarts of oil remaining inside the oil sump. Debris, including portions of crankcase, lifter, piston, and connecting rod material, was observed in the oil sump.

The Safety Board investigator noted that the oil filter remained attached to the oil filter adapter and was secure with the safety wire intact. The oil filter was removed and cut open. Metallic debris was noted throughout the internal oil filter element.

The camshaft remained intact and exhibited some mechanical damage. The crankshaft was intact and undamaged. The crankcase exhibited internal mechanical damage within all cylinder bays. The most extensive damage was observed around all four quadrants of the number four cylinder bay. The investigator observed a hole in the crankcase above the number four cylinder, and another hole below the cylinder extruding into the oil sump area. The numbers 3 and 4 cylinders were not removed due to damage of the cylinder skirts. The number 4 connecting rod separated at the rod yoke, with the connecting rod cap remnants, bolts, and nuts located in the engine and oil sump. The number 4 connecting rod journal also exhibited thermal damage.

The investigator removed the number one and two cylinders and pistons, both of which exhibited mechanical damage. The number 1 and 2 piston rings remained intact and moved freely within their respective ring lands. The number 2 piston compression ring remained in its respective ring land, but had fragmented into multiple pieces. There was no notable damage to the number 2 ring land, and the oil control ring was bound within its respective ring land. The investigator noted extensive oil coking signatures around the circumference of the number 2 piston in the area of the ring land.

NTSB Probable Cause

Failure of the number 2 cylinder piston compression ring, which resulted in oil exhaustion and a catastrophic internal engine failure.

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