An inflatable device repair kit may include an openable repair packet having a patch surface, a sandpaper surface and a packet interior between the patch surface and the sandpaper surface. At least one tube repair patch may be detachably adhered to the patch surface of the repair packet. An abrasive sanding texture may be provided on the sandpaper surface of the repair packet. A patch cement may be provided in the packet interior of the repair packet. The abrasive sanding texture on the repair packet may be used to smoothen an exterior surface on an inflatable device wall of an inflatable device at a break in the inflatable device wall. The repair packet may be opened and the patch cement in the packet interior applied to the tube repair patch and the tube repair patch applied to the inflatable device wall over the break to seal the break.

Disclosed herein is a duplicator assembly for forming a first void, which can be layered, in a laminated material of a part that matches a second void in a scarf repair guide. The duplicator assembly comprises an arm that comprises a first end portion and a second end portion. The first end portion is spaced apart from the second end portion. The duplication assembly also comprises a probe that is fixed to the first end portion of the arm and configured to trace the second void in the scarf repair guide. The duplication assembly further comprises a milling tool that is fixed to the second end portion of the arm such that the milling tool is co-movably coupled with the probe via the arm.

A method of repairing an aircraft component having a structural core surrounded by an exterior skin of composite material includes removing damaged material from the component to create a cavity therein that exposes an undamaged portion of the structural core, applying a septum comprising composite material to the undamaged portion of the structural core within the cavity such that an orientation of fibers in the septum matches an orientation of fibers in the exterior skin, placing a repair core onto the septum in the cavity such that cells of the repair core are in alignment with cells of the undamaged portion of the structural core, inserting a shim into the cavity along a perimeter of the repair core, applying a patch that covers the cavity to the exterior skin, and co-curing the septum, shim, and patch to bond the repair core in place within the cavity.

Methods for repairing composite component voids are provided. For example, one method comprises locating a void in a composite component and subjecting the composite component to a process for repair. The process for repair includes creating a flow path through the void, applying a filler material to the composite component at the flow path, and processing the composite component having the filler material. In some embodiments, the flow path has a first opening on a first side of the composite component and a second opening on a second, opposite side of the composite component. In other embodiments, at least one portion of the flow path extends at a first angle with respect to a lateral direction defined by the CMC component, and at least another portion extends at a second angle with respect to the lateral direction.

Methods for repairing composite component voids are provided. For example, one method comprises locating a void in a composite component and subjecting the composite component to a process for repair. The process for repair includes creating a flow path through the void, applying a filler material to the composite component at the flow path, and processing the composite component having the filler material. In some embodiments, the flow path has a first opening on a first side of the composite component and a second opening on a second, opposite side of the composite component. In other embodiments, at least one portion of the flow path extends at a first angle with respect to a lateral direction defined by the CMC component, and at least another portion extends at a second angle with respect to the lateral direction.

Methods for repairing composite component voids are provided. For example, one method comprises locating a void in a composite component and subjecting the composite component to a process for repair. The process for repair includes creating a flow path through the void, applying a filler material to the composite component at the flow path, and processing the composite component having the filler material. In some embodiments, the flow path has a first opening on a first side of the composite component and a second opening on a second, opposite side of the composite component. In other embodiments, at least one portion of the flow path extends at a first angle with respect to a lateral direction defined by the CMC component, and at least another portion extends at a second angle with respect to the lateral direction.

Methods for repairing composite component voids are provided. For example, one method comprises locating a void in a composite component and subjecting the composite component to a process for repair. The process for repair includes creating a flow path through the void, applying a filler material to the composite component at the flow path, and processing the composite component having the filler material. In some embodiments, the flow path has a first opening on a first side of the composite component and a second opening on a second, opposite side of the composite component. In other embodiments, at least one portion of the flow path extends at a first angle with respect to a lateral direction defined by the CMC component, and at least another portion extends at a second angle with respect to the lateral direction.

A method of repairing an aircraft component having a structural core surrounded by an exterior skin of composite material includes removing damaged material from the component to create a cavity therein that exposes an undamaged portion of the structural core, applying a septum comprising composite material to the undamaged portion of the structural core within the cavity such that an orientation of fibers in the septum matches an orientation of fibers in the exterior skin, placing a repair core onto the septum in the cavity such that cells of the repair core are in alignment with cells of the undamaged portion of the structural core, inserting a shim into the cavity along a perimeter of the repair core, applying a patch that covers the cavity to the exterior skin, and co-curing the septum, shim, and patch to bond the repair core in place within the cavity.

The present invention is directed to a process for resurfacing a damaged surface of plastic lenses, such as vehicle headlights and taillights to restore the plastic lens surface to its original clarity and transparency. During process, a cleaned damaged surface is preferably orbital sanded with a moistened sand paper disc mounted on a sander for removing visible scratches and yellowing of the moistened damaged surface of the plastic lens. Thereafter, the sanded surface is preferably rotary polished with the slush-resistant polishing composition of the present invention applied on a polishing pad mounted on an polisher for removing any visible score marks that may have been created during the sanding step. Then, the polished surface is preferably rotary finished with the slush-resistant finishing composition of the present invention applied on a finishing pad mounted on a finisher for removing any visible swirls marks that may have been created during the polishing step.

An acoustic panel (200) for an aircraft nacelle (100) may comprise a perforated first skin (220), a second skin (230), and a core (210) sandwiched between them. A camera system (330) may scan a perforation pattern of a damaged portion (311) of the perforated first skin (220). The damaged portion (311) of the perforated first skin (220) may be removed. A replacement patch (660) may be formed. A CNC machine (450) may drill the replacement patch (660) according to the perforation pattern. The perforations (425) in the replacement patch (660) may be aligned with perforations (325) in the perforated first skin.