Abstract: A vibration-preventing tail wheel conversion system prevents an aircraft tail wheel from shimmying during the takeoffs and landings. The system retrofits to the original equipment tail wheel fork. A rigid insert in the form of an inverted T comprises a cylindrical base that is pressed down into the upper end of the factory fork assembly and welded therewtihin. A rigid, reduced diameter and coaxially-centered stein projects integrally upwardly from the insert base, with an annular shoulder defined therebetween. An elongated, threaded bolt rigidly penetrates the insert and extends upwardly outwardly for threadable connection to a suitable nut. A hollow, sleeve-like hub is coaxially coupled to the end of the fork assembly, externally surrounding the insert. The hub's lower, internal shoulder contacts and rests against the fork tube and the insert's annular shoulder. An upper shoulder concentrically defined by the hub receives a bearing assembly.

Abstract: A vibration-preventing tail wheel assembly prevents an aircraft tail wheel from shimmying during the takeoffs and landings. The unit retrofits and mounts between the aircraft tail spring and the original equipment tail wheel fork. A rigid hub assembly comprising a sleeve-like, central hub is rotatably coupled to the spindle assembly. The spindle assembly has a mounting flange connected to the aircraft tail wheel fork. A rigid arm projecting from the hub is bolted to the tail spring. The spindle assembly comprises a rigid sleeve coaxially extending from a mounting flange through and within the hub assembly. A pair of bearing assemblies fitted within suitable recesses on opposite ends of the central hub contact a special bushing.