Patent ID: 6532637
Filing Date: 2003-03-18
Classification: F16D,Y10T

Abstract:
A method of converting an aircraft brake assembly designed as original equipment to be convertible from a first heat sink of one of carbon and steel brake assemblies to a second heat sink of another of the carbon and steel brake assemblies, the aircraft brake assembly for connection with a surrounding wheel via rotor disks of the respective heat sink, each heat sink including a pressure plate disk, rotor disks, stator disks, and a backing plate disk, the brake assembly comprising the first heat sink, a torque tube connected with the stator disks of the first heat sink and including a backing plate with pad means for engaging the backing plate disk, a piston housing connected by means for connecting with the torque tube, and a spacer member, the piston housing having a plurality of piston bushing assemblies with pistons located a distance from the pressure plate disk, the first heat sink having an overall axial length substantially filling an axial space between the pistons and pad means, comprising the steps of:disassembling the piston housing, piston bushing assemblies, torque tube, connecting means, spacer member, and first heat sink, and assembling the second heat sink, torque tube, piston housing with piston bushing assemblies, connecting means, and spacer member, the piston housing having longer piston bushing assemblies, wherein the second heat sink comprises a steel heat sink and includes friction material on one of the rotor disks and stator disks thereof with the friction material having axial thicknesses such that the second heat sink has a shorter overall axial length than the first heat sink and the longer piston bushing assemblies position the pistons at substantially said distance from the pressure plate disk of the second heat sink.