A detailed procedure is presented that enables astronauts in extravehicular activity (EVA) to efficiently assemble and repair large (i.e., greater than 10m-diameter) segmented reflectors, supported by a truss, for space-based optical or radio-frequency science instruments. The procedure, estimated timelines, and reflector hardware performance are verified in simulated 0-g (neutral buoyancy) assembly tests of a 14m-diameter, offset-focus, reflector test article. The test article includes a near-flight-quality, 315-member, doubly curved support truss and 7 mockup reflector panels (roughly 2m in diameter) representing a portion of the 37 total panels needed to fully populate the reflector. Data from the tests indicate that a flight version of the design (including all reflector panels) could be assembled in less than 5 hours - less than the 6 hours normally permitted for a single EVA. This assembly rate essentially matches pre-test predictions that were based on a vast amount of historical data on EVA assembly of structures produced by NASA Langley Research Center. Furthermore, procedures and a tool for the removal and replacement of a damaged reflector panel were evaluated, and it was shown that EVA repair of this type of reflector is feasible with the use of appropriate EVA crew aids.Lake, Mark S. and Heard, Walter L., Jr. and Watson, Judith J. and Collins, Timothy J.Langley Research CenterORBITAL ASSEMBLY; EXTRAVEHICULAR ACTIVITY; REFLECTORS; TRUSSES; ORBITAL WORKERS; SPACE MAINTENANCE; ASTRONAUT TRAINING; AEROSPACE ENVIRONMENTS; SPACE TOOLS; PANELS; WEIGHTLESSNESS; SIMULATION; SPACE ERECTABLE STRUCTURES