Abstract: A non-destructive method for determining an amount of temperature exposure to a Bismaleimide Resin (BMI) matrix substrate, the method includes determining component data of a Bismaleimide Resin (BMI) matrix component via fourier transform infrared (FTIR) spectroscopy; correlating the component data to model data to determine a structural debit from temperature exposure; and bounding a structurally damaged area in response to the correlating.

Abstract: A hinge arm having a hinge pin hole having a worn bore, for example a hinge arm of a hinge assembly of an access door on a gas turbine engine, is repaired by forming in the worn hinge arm a new hole with a keyway extending outwardly from the new hole. A keyed bushing is provided having a cylindrical body having a central bore extending axially therethrough and a key extending outwardly from the cylindrical hole. The keyed bushing is inserted into the new hole and keyway formed in the hinge arm thereby preventing rotation of the bushing relative to the hinge arm.

Abstract: A composite component includes a honeycomb, a skin bonded to the honeycomb, a repair section bonded adjacent to the skin, and at least one cover secured on at least a portion of the repair section to resist peeling of the repair section.

Abstract: A method of restoring a section of a composite includes the steps of removing an undesirable section of a perforated composite and depositing a repair material in the location of the removed, undesirable section. The repair material is then cured. Before completing the curing step, one or more opening are formed through the repair material to produce one or more perforations through the repair material upon completing the curing step.

Abstract: A method of reinforcing a thermoplastic part includes softening a portion of the thermoplastic part to form a pool, embedding fibers in the softened pool, and re-solidifying the pool embedded with fibers into a weld that strengthens the thermoplastic part.

Abstract: A method of repairing a circumferential flanged ring of a gas turbine engine with a bushing includes the steps of removing a damaged portion from a flange of a circumferential flanged ring that has an original profile to define a new profile and removing a portion of a bushing to define a bushing profile that matches the new profile of the flange. The method further includes the step of attaching the bushing to the flange of the circumferential flanged ring.

Abstract: A fireshield fastener hood and method of bonding a cover to a substrate therefor.

Abstract: A shim is provided for repairing damage in a surface of a mechanical piece at or near an outer edge of a bore in the surface. The damage may penetrate a given distance within the surface and the bore is in close proximity to an attachment hole. The shim has a body having a first side and a second side and a thickness therebetween that is equal to or greater than the depth of the damage penetrating the given distance and contiguous to the attachment opening, wherein the body fits within an area machined into an outer surface surrounding the bore.

Abstract: An example method of replacing an aperture in a component includes placing layers of a filler material into a first aperture. The layers of the filler material arranged in a stacked relationship relative to each other within the first aperture. The method cures the filler material and establishes a second aperture that is at least partially defined by the filler material.

Abstract: A process for repairing a workpiece includes the steps of: providing a workpiece having at least one interior surface requiring restoration; providing a source of repair material; and depositing the repair material onto the at least one interior surface using a technique which is a near non-line of sight technique.

Abstract: A fire blanket assembly includes a thermal insulation material defining an opening, a metallic foil layer positioned along a first surface of the thermal insulation material and over at least a portion of the opening, an insert disc positioned adjacent to a second surface of the thermal insulation material opposite the first surface and further being positioned at the opening in the thermal insulation material, and a detail. The detail includes a base positioned at least partially within the opening in the thermal insulation material, a sidewall extending from the base, and a flange extending from the sidewall at a location spaced from the base, a perimeter of the flange turned at least partially away from the metallic foil layer.

Abstract: A shaft assembly that includes a locked spacer mounted to a shaft shoulder.

Abstract: A method is provided for forming a seal element on a substrate surface. A layer of base material is formed on the substrate surface and a plurality of crenellations are formed in the layer of base material prior to forming a layer of seal material on the crenellated layer of base material. The method may be applied to making an original seal element or to repairing an existing seal element. The resulting seal includes a layer of base material bonded to a substrate and having a plurality of crenellations formed in a face surface of the layer of a base material and a layer of a seal material bonded thereto, the seal material filling the crenellations.

Abstract: A method of restoring a section of a composite includes the steps of removing an undesirable section of a composite and securing a repair section in the location of the removed undesirable section. One or more covers are secured on at least a portion the repair section to prevent or resist peeling of the repair section.

Abstract: A hinge arm having a hinge pin hole having a worn bore, for example a hinge arm of a hinge assembly of an access door on a gas turbine engine, is repaired by forming in the worn hinge arm a new hole with a keyway extending outwardly from the new hole. A keyed bushing is provided having a cylindrical body having a central bore extending axially therethrough and a key extending outwardly from the cylindrical hole. The keyed bushing is inserted into the new hole and keyway formed in the hinge arm thereby preventing rotation of the bushing relative to the hinge arm.

Abstract: A method of restoring a section of a composite includes the steps of removing an undesirable section of a composite and securing a repair section in the location of the removed undesirable section. One or more covers are secured on at least a portion the repair section to prevent or resist peeling of the repair section.

Abstract: A method of restoring a section of a component having a honeycomb bonded to a skin includes the steps of separating a first honeycomb from the skin, wherein the honeycomb includes an uneven surface. At least a portion of the uneven surface is removed to form a bonding surface on the skin. A conformable layer is bonded to the uneven surface. Then a replacement honeycomb is then bonded to the conformable layer.

Abstract: A repair device and method for repairing a forward frame v-blade on an aircraft engine are described in which the repair device replaces a section of the forward frame v-blade. In one embodiment, the repair device includes a supplemental part, which is secured to the forward frame v-blade. The supplemental part includes a central web and a pair of legs with a leg thickness that is greater than the thickness of corresponding flanges on the forward frame v-blade. Fasteners such as rivets are used to couple the supplemental part to the forward frame v-blade.

Abstract: A method of reinforcing a thermoplastic part includes softening a portion of the thermoplastic part to form a pool, embedding fibers in the softened pool, and re-solidifying the pool embedded with fibers into a weld that strengthens the thermoplastic part.

Abstract: A process for repairing components includes the steps of providing a component having an affected area on a surface of a component to be repaired; depositing a repair material over the affected area on the surface of the component so that the repair material plastically deforms without melting and bonds to the affected area upon impact with the affected area and thereby covers the affected area; providing a sulfuric acid based anodizing solution; anodizing a deposited repair material on the surface of said component in the sulfuric acid based anodizing solution; consuming only a portion of the deposited repair material to form a hard anodized coating layer upon the deposited repair material to form a hard anodized coated component; providing a corrosion resistant sealant solution; and contacting a hard anodized coated component with the corrosion resistant sealant solution to form a corrosion resistant sealant coating on the hard anodized coated component.