Accident Overview
On November 21, 2021, at 0826 central standard time, a Cessna 210 airplane, registration N5779J, was substantially damaged in an accident near Brent, Alabama. The pilot, who was the sole occupant, sustained minor injuries. The flight was conducted under Title 14 Code of Federal Regulations Part 91 as a personal flight.
Flight Events
The airplane departed from Tuscaloosa Regional Airport (TCL), Tuscaloosa, Alabama, on an instrument flight rules flight plan. Approximately 14 minutes after takeoff, during cruise flight, the flight system monitor annunciated “check oil pressure.” The pilot observed that the oil pressure indicated 0 psi. He declared an emergency, established best glide speed, and navigated toward the nearest airport. Air traffic control cleared the pilot to descend and inquired whether he could reach the diversion airport. The pilot decided it was prudent to land immediately. During descent, he exited cloud cover and selected a road for a forced landing site. After touchdown, the right wing collided with several road signs. The airplane subsequently impacted a ditch and several trees, coming to rest upright in a nose-down attitude.
Postaccident Examination
A Federal Aviation Administration (FAA) inspector examined the wreckage. The fuselage, firewall, and both wings sustained substantial damage. The tail cone exhibited compression wrinkling forward of the vertical stabilizer. The front windscreen was broken. The left-wing fuel tank was breached and contained no fuel; the right-wing fuel tank remained intact with fuel.
Engine Data and Examination
Data from the JPI EDM-830 engine data monitoring device indicated normal engine operation until 0818, when oil pressure began to drop. Shortly thereafter, manifold pressure decreased, and most other engine parameters showed corresponding reductions. GPS data showed the aircraft began descending from 7,000 ft mean sea level around that time. Data ended at 0826.
Engine examination revealed an F&M screw-on oil filter adapter. Oil was observed on the lower area of the oil adapter fiber gasket seal, in the engine compartment, and on the underside of the fuselage. Using a digital torque wrench, the tightening torque of the oil filter adapter installation measured 38.5 ft-lbs, and the loosening (breakaway) torque measured 34.0 ft-lbs. According to Stratus Tools Technologies mandatory service bulletin SB-001 Rev B (revised June 17, 2021, originally issued October 25, 2019), the oil adapter transfer cylinder should be tightened to 65 ft-lbs during installation. Upon removal, the fiber gasket between the engine oil pump assembly and the oil filter adapter was found torn and indented. The revised SB required removal of the fiber gasket (if installed) and replacement with a copper gasket, and also required inspection of the adapter for security, leaks, seepage, or gasket damage within the next 10 flight hours, annual inspection, or 100-hour inspection, whichever occurred first. The SB stated that only copper gaskets are approved for initial installation or reinstallation. Review of maintenance records found no entries specifically addressing the SB; the most recent entry related to the adapter was in May 2015, when the adapter was removed and the gasket and crush washer were replaced.
Pilot Statement
In a postaccident interview, the pilot stated he had not experienced any anomalies or malfunctions prior to the loss of oil pressure. He also stated that he had read about the oil filter adapter issue a few weeks before the accident but did not believe his installation was at issue, given that “it had lasted this long.”