No fatalities

12 Jun 2019: Cessna 140 (N73053) — Independence, OR

Independence, OR, United States

On 12 Jun 2019, a Cessna 140 Undesignat (registration N73053) was involved in an aviation accident near Independence, OR. No fatalities were reported. Investigators recorded the probable cause as: Fatigue failure of the right landing gear axle, which resulted in a loss of control during the landing roll. This summary draws on records from NTSB; 12 related events involving the same aircraft type or operator are linked below.

SourcesNTSBPrimary reportUpdated 1778583330Data APIEditorial standards

On June 12, 2019, a Cessna 140 (N73053) suffered substantial damage during a training landing near Independence, Oregon, when the right wheel assembly separated. Neither instructor nor student was injured.

Incident Overview

On June 12, 2019, at approximately 1435 Pacific daylight time, a Cessna 140 airplane, registration N73053, sustained substantial damage during a landing accident near Independence, Oregon. The flight instructor and student pilot were not injured. The airplane was being operated as a Title 14 Code of Federal Regulations Part 91 instructional flight.

Sequence of Events

According to the flight instructor, the accident landing was the second landing of the flight. As the airplane slowed down and began to exit the runway, a loud "clunk" was heard. The airplane then slid sideways, bounced, and ground looped, resulting in substantial damage to the fuselage. The instructor reported that the right wheel assembly had separated at the axle.

Pilot and Aircraft Information

The student pilot, who was also the owner of the airplane, reported purchasing it in April 2019. He had been flying one to three times per week while working toward his private pilot certificate. No issues had been noted during previous flights.

Examination of the Axle

A post-accident examination of the fractured axle assembly revealed that the axle fractured at the transition radius between the longitudinal barrel (tube) portion and the plate portion. A fatigue crack had emanated from multiple origins at the outer surface of the transition radius and extended circumferentially around the outer surface. The fracture features outside the fatigue region showed characteristics consistent with overstress separation. The maintenance history of the landing gear and axle could not be determined.

Contributing factors

Fatigue/wear/corrosionAttain/maintain not possible