HISTORY OF FLIGHT On April 2, 1999, approximately 1425 Pacific standard time, a Cessna 210-5 (205), N8464K, registered to and being flown by a private pilot, was substantially damaged during a forced landing approximately two nautical miles southwest of Edison, Washington, following a complete loss of power in cruise. The pilot sustained minor injuries. Visual meteorological conditions existed and no flight plan had been filed. The flight, which was personal, was to have been operated under 14CFR91, and originated from the Bellingham International airport, Bellingham, Washington, at 1415. The pilot reported to the investigator-in-charge that he departed Bellingham, climbed to 3,000 feet above mean sea level (MSL) and set cruise power. Approximately three to four minutes later, and while flying southbound over Samish Bay, the engine began to lose power. The pilot attempted to troubleshoot the problem adjusting throttle and mixture without success, and after approximately 30 to 60 seconds all power was lost. With the propeller continuing to windmill and only muddy fields available, the pilot initiated a forced landing to a north/south paved road at the south end of Samish Bay. The pilot, observing power lines along the west side of the road, landed along the east side. During the landing roll the left wing impacted a sign and the aircraft rolled off the left side of the road into a deep ditch. Post-crash examination of the engine by an inspector from the Federal Aviation Administration's Flight Standards District Office revealed a discontinuity in the engine crankshaft. Specifically, when the propeller was rotated by hand no accessory gear train rotation was observed. AIRCRAFT INFORMATION Records indicated that the Continental IO-470-D engine had been manufactured 02/26/76 and was subsequently overhauled at an unknown time and date. The first entry in the engine log, dated 09/19/90, indicated that the engine had been removed from N86627 and that "Logbook [had been] lost, maintenance records show engine has 420 hrs approximately since factory overhaul. Engine disassembled to confirm time. Crankshaft magnafluxed OK. Replaced main & rod Brgs, seals & gaskets -." The next logbook entry, dated January 1991, stated that the engine was "removed from 310G, 60 hrs operation since previous entry -." The next logbook entry, dated 05/16/92, stated that "Engine time SMOH [since major overhaul] is 480 hrs. S/N CS105475R. Engine installed in Cessna 205 N8464K." The next logbook entry, also dated 05/16/92, stated that "Annual Inspection. Verified that this engine has been converted from an IO-470D to an IO-470S for inst. in Cessna 205 N8464K S/N 205-0460. I certify that this engine has been inspected per Annual inspection and found to be airworthy." There was no record within the engine log of any core maintenance (crankshaft or bearings) having been accomplished following the 05/16/92 inspection. The last engine inspection was recorded on 06/10/98 at a total time in service (SMOH) of 1121.9 hours. The engine had been operated an additional 61 hours between this date and the accident. Documentation provided by the engine manufacturer showed no difference between the buildup of the IO-470-D version compared to the IO-470-S (refer to ATTACHMENT TCM-I). TESTS AND RESEARCH The engine was shipped to the facilities of Teledyne Continental where it was disassembled and examined on 04/28/99 under the oversight of an Air Safety Investigator from the Board's Northwest Regional Office. The examination revealed that the crankshaft had separated at the number six cheek. No other significant disparities were noted (refer to ATTACHMENT TCM-II). The crankshaft and connecting rods were shipped to the Board's Office of Research and Engineering, Material Laboratory Division. Examination revealed that a large area in the central portion of number six cheek fracture surface displayed a smooth texture and contained multiple crack arrest features, characteristic of fatigue progression (refer to MATERIALS LABORATORY FACTUAL REPORT 99-133). Additionally, the report stated that "the curvature of the crack arrest positions indicated that the fatigue initiated at the outboard flat surface of the crankcheek, approximately at the mid point between the horizontal centerlines for the main and rod journals." Further examination with a scanning electron microscope revealed that "post-separation heat and mechanical damage destroyed all discernable fracture features in this piece." ADDITIONAL INFORMATION The engine was returned to Chuckanut Aviation Center, Burlington, Washington, in early May 1999. The crankshaft and connecting rods were returned to a representative of the insurance holder on July 2, 1999. Formal release of the engine (S/N CS105475R) was documented on NTSB Form 6120.15 (attached).