| Crash location | 43.323889°N, 76.385833°W
Reported location is a long distance from the NTSB's reported nearest city. This often means that the location has a typo, or is incorrect. |
| Nearest city | Fulton, NY
42.558687°N, 74.442920°W 111.6 miles away |
| Tail number | N31BF |
|---|---|
| Accident date | 16 Aug 2008 |
| Aircraft type | Socata MS894A |
| Additional details: | None |
On August 16, 2008, at 1540 eastern daylight time, a Socata MS894A, N31BF, was substantially damaged during a forced landing following a loss of engine power, approximately 2 miles south of the Oswego County Airport (FZY), Fulton, New York. The certificated private pilot and passenger sustained minor injuries. Day visual meteorological conditions prevailed and no flight plan was filed for the personal local flight. The flight was conducted under the provisions of Title 14 Code of Federal Regulations Part 91.
The airplane was owned by the pilot and based at FZY. It had been fueled on the morning of the accident with 22.2 gallons and a report from the lineman was that it was "topped off."
According to the pilot after making a low pass along the drop zone, he pulled up and leveled off at about 400 feet above ground level. He then heard a "bang," followed by vibration, and then the engine stopped. He immediately pitched for a "glide speed of 90 miles per hour," and flew toward a field. On the final leg of the approach, the airplane impacted trees, nosed over on touchdown, and then rotated approximately 180 degrees.
Examination of the airplane by a Federal Aviation Administration inspector revealed that control continuity was confirmed to all control surfaces from the control column and rudder pedals. Both propeller blades had slight "S-bending." Left had gear assembly was separated and located in front of the airplane. Inside the cockpit the throttle, propeller, and mixture controls were in the off or minimum position and the trim indicator was
A preliminary inspection of the engine revealed that a hole was located in the case in the area near the number three piston and the No. 2 connecting rod was separated and located approximately 20 feet from the airplane along the direction of travel. Continuity could not be confirmed through the crankshaft and a further teardown examination revealed that the crankshaft was fractured at the connection point of the number three connecting rod. The oil filter was removed, examined, and contained metal particles throughout.
According to the airplane's maintenance logbook the engine was overhauled on December 17, 2004. On April 2, 2005 due to a bearing recall the engine was disassembled, cleaned, and inspected. The crankshaft was "turned .010 on mains, .010 on rods" and was overhauled with a tachometer time of 1,548.63 hours. An annual inspection for the airplane was recorded on April 9, 2008 with a tachometer time of 1,576.81 hours. According to the pilot the airframe had a total time of 1,599 hours at the time of the accident.
The recovered crankshaft and connecting rods were submitted to the National Transportation Safety Board Materials Laboratory Division. Examination of the fracture faces on cheek C4 revealed mechanical damage and three zones that displayed relatively smooth surfaced and arced cracked arrest marks which are consistent with fatigue. Measurements of the bearing journals revealed that the diameter of main journals M1 to M4 ranged between 2.2405 and 2.2385 inches a tolerance of 0.0020-inch, and the diameter of the rod journals ranged between 1.9280 and 1.9260 inches a tolerance of 0.0020-inch. According to the table limits in the overhaul manual the tolerance on the main and rod journals was 0.0010-inch. Examination of the connecting rod bearings revealed the numbers "18020" and according to the illustrated parts catalog, the standard bearing was "17739." Bearing journal R3 was cut adjacent to cheek C5 and revealed an arced initiation that followed a circumferential machining mark in the radius between the journal and the cheek. Bearing journals and crankshafts are normally surface hardened by a nitriding process and a sample from journal R3 was metallurgically mounted, polished and etched. Metallographic examination of the polished and etched sample revealed a uniform acicular (needle-like) structure in the base material and in the surface layer, consistent with tempered martensite.
A loss of engine power due to fatigue failure of the crankshaft and the No. 3 engine cylinder connecting rod as a result of improper machining of the engine crankshaft during engine overhaul by maintenance personnel.