Vienna, MO, USA
N76379
Cessna 140
The airplane impacted terrain during a forced landing after a loss of engine power. The pilot recently purchased the airplane and had taken delivery of it on the day of the accident. Examination of the engine revealed three of the crankshaft cluster gear bolts were fractured completely through. The bolt fracture surface features were consistent with fatigue. Additionally, the crankshaft gear had a hole where a crankshaft dowel had been installed following a design change in 1948 and was reflected in subsequent maintenance manuals. The dowel is used as a reference in machining the crankshaft. During the disassembly, the tappets fell out when the engine was overturned during the disassembly. It was later noted that the tappets did not contain retaining hardware. The interior of the crankcase halves contained a black colored residue when the oil was drained. Logbook entries show that the engine was last overhauled on July 25, 1990, and accumulated a total time since overhaul of 257.5 hours. Teledyne Continental Service Information Letter, SIL98-9A, Time Between Overhaul Periods, states that engines are to be overhauled at least every twelve years.
On December 9, 2006, at 1430 central standard time, a Cessna 140, N76379, owned and piloted by a private pilot, received substantial damage on impact with terrain during a forced landing on a farm field near Vienna, Missouri. The pilot stated that the engine lost power after he heard a "bang." Visual meteorological conditions prevailed at the time of the accident. The pilot reported no injuries. The flight last departed from Rolla National Airport (VIH) Rolla/Vichy, Missouri, at 1410. The pilot purchased the airplane and had taken delivery of it at VIH on the day of the accident. The airplane was powered by a Continental C-85-12F engine, serial number 25578-6-12, which according to logbook entries, was last overhauled on July 25, 1990, and accumulated a total time since overhaul of 257.5 hours. A disassembly examination of the engine at Teledyne Continental Motors, Mobile, Alabama, revealed three of the crankshaft cluster gear bolts were fractured through. The bolt fracture surface features were consistent with fatigue. Additionally, the crankshaft gear had a hole where a crankshaft dowel was later installed following a design change in 1948 and was reflected in subsequent maintenance manuals. The dowel is used as a reference in machining the crankshaft. During the disassembly, the tappets fell out when the engine was overturned during the disassembly. It was later noted that the tappets did not contain retaining hardware. The interior of the crankcase halves contained a black colored residue when the oil was drained. Teledyne Continental Service Information Letter, SIL98-9A, Time Between Overhaul Periods, states that engines are to be overhauled at least every twelve years.
The loss of engine power during cruise flight due to fatigued crankshaft cluster gear bolts and the inadequate major overhaul of the engine that was last performed by other maintenance personnel. An additional cause was a subsequent major engine overhaul not performed by the pilot after he purchased the airplane and operated it with an engine that exceeded the engine manufacturer's time between overhaul criteria.
Source: NTSB Aviation Accident Database
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