Abstract: A method for repairing a laminated article having a damaged area comprising the steps of: removing the damaged area from the laminated article so as to leave a repair site; positioning a repair patch to cover the repair site; placing one or more heat blankets over the repair patch and other selected locations; placing the laminated article with the repair patch in a vacuum bag; placing the vacuum bag in an autoclave; operating the autoclave within a selected range of desired temperatures and pressures; and, curing the repair patch of the laminated article without disturbing or damaging the adjacent bondments within a composite structure.

Abstract: An annular molded composite wear sleeve (40) is bonded with epoxy or other bonding agent in an annular V-groove (34) in a groove ring (64). Wear sleeve (40) may include forward and aft sleeve walls (46, 48) extending at forward and aft sleeve obtuse angles (50, 52) away from a sleeve bottom (44) and may include annular forward and aft sleeve fillets (54, 56) between sleeve bottom (44) and forward and aft sleeve walls (46, 48). Aft sleeve wall (48) may include an aft flap (60) compliant with an annular aft taper (62) on groove ring (64). An aircraft gas turbine engine cowl clamping mechanism (22) for clamping a clamshell cowl (20) to a fan casing (26) includes groove ring (64) on a fan casing (26) and molded composite wear sleeve (40) bonded with epoxy or other bonding agent in annular V-groove (34) in groove ring (64). Annular V-blade (30) is on clamshell cowl (20) rotatable to insert annular V-blade (30) in annular V-groove (34).