Abstract: A method for repairing a composite laminate component includes removing a first portion of the composite laminate component. The composite laminate component extends between and to a first component side and a second component side. The composite laminate component includes a first plurality of layers having a first sequential arrangement from the first component side to the second component side, and the first portion includes the first plurality of layers. The method further includes preparing a second portion for the composite laminate component. The second portion extends between and to a first portion side and a second portion side. The second portion includes a second plurality of layers having a second sequential arrangement from the first portion side to the second portion side. The second sequential arrangement is different than the first sequential arrangement. The method further includes positioning the second portion on the composite laminate component and curing the second portion.

Abstract: A method for repairing a composite laminate component includes removing a first portion of the composite laminate component. The composite laminate component extends between and to a first component side and a second component side. The composite laminate component includes a first plurality of layers having a first sequential arrangement from the first component side to the second component side, and the first portion includes the first plurality of layers. The method further includes preparing a second portion for the composite laminate component. The second portion extends between and to a first portion side and a second portion side. The second portion includes a second plurality of layers having a second sequential arrangement from the first portion side to the second portion side. The second sequential arrangement is different than the first sequential arrangement. The method further includes positioning the second portion on the composite laminate component and curing the second portion.

Abstract: A method is provided involving a fairing for a turbine engine. During this method, a detail is provided. The detail includes a carrier and an exterior layer bonded to the carrier. The carrier is configured from or otherwise includes fiber-reinforced composite material. The exterior layer is configured from or otherwise includes polymer material. The detail is arranged with the fairing. The fairing includes an exterior side and an edge. The detail covers and extends along at least a portion of the exterior side. The detail wraps at least partially around the edge. The carrier and at least a first overhang portion of the exterior layer are bonded to the fairing.

Abstract: A method is provided involving a fairing for a turbine engine. During this method, a detail is provided. The detail includes a carrier and an exterior layer bonded to the carrier. The carrier is configured from or otherwise includes fiber-reinforced composite material. The exterior layer is configured from or otherwise includes polymer material. The detail is arranged with the fairing. The fairing includes an exterior side and an edge. The detail covers and extends along at least a portion of the exterior side. The detail wraps at least partially around the edge. The carrier and at least a first overhang portion of the exterior layer are bonded to the fairing.

Abstract: A heat blanket for use in the repair of aircraft outer casings and method for using the heat blanket are provided. The heat blanket has an inner and outer layer of thermally conductive material. A series of heating elements are disposed between the inner and outer layers of materials and arranged into a plurality of heating zones. A control apparatus has a plurality of temperature sensors, each of which corresponds to one of the plurality of heating zones. The control apparatus provides power to the heating elements to control temperature for each respective zone as a function of sensed temperature. The blanket is shaped to cover a portion of the engine nacelle.