Accident Overview
On May 7, 2018, about 1139 mountain daylight time, a Cessna 182E airplane, registration N3292Y, was substantially damaged when it departed the runway and nosed over near Broomfield, Colorado. The commercial pilot sustained minor injuries. The flight was conducted as a personal flight under Title 14 Code of Federal Regulations Part 91.
Flight and Landing Sequence
The pilot departed from an airport and flew to his private grass airstrip, where he performed two uneventful full-stop landings before returning to the departure airport. Upon returning, the pilot conducted a normal approach to runway 30L. The airplane initially touched down on the main landing gear, but when the nose landing gear contacted the runway, the airplane immediately swerved right and nosed over in the grass beside the runway.
Witness Observation
A witness reported seeing the airplane on final approach to runway 30L with its nose wheel rotated about 75° from its normal alignment. The airplane touched down on its main landing gear; however, when the nose wheel contacted the runway, it did not realign with the runway heading. The airplane immediately swerved to the right. The nose landing gear separated from the airplane about 100 yards into the right swerve. The airplane subsequently departed the right runway edge and nosed over.
Post-Accident Examination
An onsite examination revealed substantial damage to the vertical stabilizer, rudder, and right wing strut. The nose landing gear torque link assembly had fractured, which allowed the nose wheel to rotate freely on the landing gear strut. The fractured scissor assembly and associated hardware were retained for additional examination at the National Transportation Safety Board (NTSB) Materials Laboratory in Washington D.C.
NTSB Laboratory Findings
The NTSB laboratory examination of the torque link assembly revealed a fracture of the upper link arm near its upper end. The fracture exhibited features consistent with a downward bending overstress failure. The examination also identified an isolated area of preexisting fatigue on the right flange and a closed crack on the left flange, neither of which contributed to the bending overstress failure of the upper torque link.