On June 14, 2018, about 1800 eastern daylight time, a Stinson L-5, N45TX, was involved in an accident near Thomson, Georgia. The commercial pilot was not injured. The airplane was operated as a Title 14 Code of Federal Regulations Part 91 personal flight. The pilot reported that the preflight inspection, engine runup, takeoff, and climb were normal. About 40 minutes into the flight, while flying at 2,200 ft mean sea level and 10 miles from the departure airport, he noticed the oil temperature “jumped” to the top of the green arc and the oil pressure was near the bottom of the green arc. He reduced engine power, adjusted the mixture to full rich, and turned toward the airport. Shortly thereafter, the engine lost total power and the pilot’s attempts to restore power were unsuccessful; the propeller was stationary and did not move during attempts to restart the engine. The pilot performed a forced landing to a lake and the airplane sank after the pilot egressed. The airplane was recovered and visually examined by a Federal Aviation Administration (FAA) inspector. The airplane’s left wing was substantially damaged. The inspector attempted to rotate the propeller by hand, but the propeller would not move. Review of the maintenance logbooks revealed that the last engine overhaul was performed on March 29, 1994. On two separate occasions, June 8, 2002, and September 16, 2002, the propeller was replaced due to a propeller strike/damage. There was no record of crankshaft inspections found in the maintenance logbooks. The last annual was performed on September 14, 2017, at 6,113.2 tachometer time. At the time of the accident, the airplane had flown 10.6 hours since the annual inspection and 711 hours since engine overhaul. The airplane was recovered for detailed teardown and examination of the engine. Removal of the Nos. 1 and 2 cylinders revealed that the crankshaft fractured at the No. 2 crank pin. (see Figure 1.)

Figure 1 Crankshaft fracture The thrust nut was removed in order to open the crankcase. The amount of torque required to loosen the thrust nut was not measured, but was significantly less than the 375 ft-lbs specified by the engine overhaul manual, as it required no special tools and little effort to remove. Upon opening the crankcase, it was confirmed that the crankshaft was fractured along with ancillary damage caused by the Nos. 1 and 2 pistons and connecting rods impacting their respective skirts. In addition to the main fracture, a separate crack was discovered slightly aft of the No. 1 main bearing that had propagated nearly the width of the crankshaft, but had not fully failed. On October 18, 2016, Lycoming issued a Mandatory Service Bulletin No. 533C (Superseded 533B) with recommended action for sudden engine stoppage, propeller/rotor strike, or loss of propeller/rotor blade or tip for all Lycoming reciprocating aircraft engines. The SB included detailed checklists for the inspection.