| 摘要 |
An aircraft brake assembly (10, 100, 200) designed as original equipment to have convertible heat sinks comprises one of a steel heat sink (140) and a carbon-carbon composite heat sink (40). When a carbon-carbon composite heat sink (40) is contained within the brake assembly (10), the piston housing (30) contains a plurality of piston bushing assemblies (32) with bushings (33), pistons (34) and adjuster mechanisms (36). The backing plate (28) of the torque tube (20) has riveted thereto a series of connectors (33) which are received within corresponding openings (29) of a carbon-carbon composite backing plate friction material stator disc (27). When the brake assembly (10) is converted to a steel heat sink (140, 240), the carbon-carbon composite heat sink (40) is separated from the torque tube (20) and piston housing (30), the connectors (33) removed from the rivets (31) and backing plate (28), and the piston bushing assemblies (32) removed from the piston housing (30). Whithin the piston housing (30), a second group of piston bushing assemblies (132, 232) are inserted, which have internal components that are dimensionally different from the first group of piston bushing assemblies (32). Backing plate pads are riveted to the backing plate (28) as the steel heat sink (140, 240) is assembled with the torque tube (20) and piston housing (30). The steps are reversed in order to convert the steel heat sink aircraft brake assembly (100, 200) to the carbon-carbon composite heat sink aircraft brake assembly (10). |
