The present disclosure is directed towards a kit for approximating texture of a building surface (e.g., a wall or ceiling). The kit can include a repair compound, a texture holding material, and optionally one or material to textured more pressing and shaping tools. The texture holding compound can be used to create a mold or stamp of surface texture in a non-damaged area of the building surface needing repair. The texture mold can be used to impart consistent surface texture to the repair compound as it dries, allowing a repaired area to at least approximate the texture of the area of the building surface surrounding the repaired area. The tool, if provided, can include a planar surface that can be used to conform the texture holding material to the surface texture, maintain contact between the texture mold and the repair compound to impart the mimicked texture, or both.

The present disclosure is directed towards a kit for approximating texture of a building surface (e.g., a wall or ceiling). The kit can include a repair compound, a texture holding material, and optionally one or material to textured more pressing and shaping tools. The texture holding compound can be used to create a mold or stamp of surface texture in a non-damaged area of the building surface needing repair. The texture mold can be used to impart consistent surface texture to the repair compound as it dries, allowing a repaired area to at least approximate the texture of the area of the building surface surrounding the repaired area. The tool, if provided, can include a planar surface that can be used to conform the texture holding material to the surface texture, maintain contact between the texture mold and the repair compound to impart the mimicked texture, or both.

There is disclosed a fixing apparatus (10) for fixing a secondary component (14) to a fan blade, the fixing apparatus comprising: a first clamp part (16) comprising a first inner surface (20) and a second clamp part (18) comprising a second inner surface (22), the first inner surface and the second inner surface having a profile corresponding to a profile of a portion of the fan blade (102). The first clamp part and/or the second clamp part comprises a recess (24) in the respective first inner surface and/or second inner surface for receiving the secondary component, and a corresponding heater (28, 30) for applying heat to the secondary component located in the recess in use. The first clamp part and the second clamp part are configured to cooperate with one another to clamp the portion of a blade between them in a clamping operation and to hold the secondary component against the blade when the secondary component is received within the recess.

A hole plug that can be used during rework or repair of a composite fiber assembly includes various features that allow placement of a vacuum force to the surface being reworked or repaired. In some implementations, the hole plug can include a plurality of nubs positioned around a shank. The nubs can secure the hole plug to the composite fiber assembly until a cure of an adhesive. The hole plug can further include a plurality of longitudinally oriented grooves extending along the shank and positioned between the plurality of nubs, and can include a notch positioned circumferentially around the shank. The grooves and notch can be used as adhesive carriers that assist with dispersal of a sufficient volume of the adhesive onto other portions of the shank and the composite fiber assembly during insertion of the hole plug into a hole in the composite fiber assembly.

Provided herein is a method to reinforce a junction of fiber-composite aircraft components forming an elongate conduit. The method comprises (a) abrading the junction and (b) applying sealant along the junction from a tool moveable through the conduit, the tool exerting force on an interior surface of the conduit opposite the junction.

A method of correcting, in a composite component, an inappropriate countersink with an inappropriate maximum diameter and/or depth, the inappropriate countersink being provided in the composite component at a fixation opening having a first opening diameter, the method comprising at least the steps of: Preparing a repair patch; Arranging the repair patch on the composite component in an area surrounding the inappropriate countersink; Pressing the repair patch at least partly into the inappropriate countersink by means of an associated pressure tool; and Fixing the repair patch in the inappropriate countersink.

A method of correcting, in a composite component, an inappropriate countersink with an inappropriate maximum diameter and/or depth, the inappropriate countersink being provided in the composite component at a fixation opening having a first opening diameter, the method comprising at least the steps of: Preparing a repair patch; Arranging the repair patch on the composite component in an area surrounding the inappropriate countersink; Pressing the repair patch at least partly into the inappropriate countersink by means of an associated pressure tool; and Fixing the repair patch in the inappropriate countersink.

Thermal curing of a potting material within a hole in a surface of a composite material is described utilizing a flexible vacuum compression device that includes a chemical-based heating pack. The vacuum compression device includes an internal compartment within a cavity that retains the chemical-based heating pack, and a vacuum port having a passage into the cavity. An end of the vacuum compression device includes an interface that forms an air-tight seal between the cavity and the surface when applied to a surface of the composite material. Drawing a vacuum via the vacuum port collapses the vacuum compression device and positions the chemical-based heating pack proximate to the surface, enabling heat from the chemical-based heating pack to thermally cure the potting material.

The present disclosure describes one or more systems, methods, routines and/or techniques for thermal management. One or more systems, methods, routines and/or techniques may provide advice or guidance (e.g., to a repair technician) regarding how to perform a hot bond repair, for example, on an aircraft component that has been damaged. The thermal management advisor may provide advice or guidance regarding how to prepare a repair field prior to running a thermal survey. For example, thermal management advisor may recommend a particular heat blanket, a configuration of the heat blanket, placement of various temperature sensors and other preparation guidance. The thermal management advisor may provide advice or guidance regarding how to alter or manage the repair setup during a thermal survey and during the actual curing process. For example, thermal management advisor may recommend particular temperature sensors or areas of the repair field that should be insulated.

The present disclosure describes one or more systems, methods, routines and/or techniques for thermal management. One or more systems, methods, routines and/or techniques may provide advice or guidance (e.g., to a repair technician) regarding how to perform a hot bond repair, for example, on an aircraft component that has been damaged. The thermal management advisor may provide advice or guidance regarding how to prepare a repair field prior to running a thermal survey. For example, thermal management advisor may recommend a particular heat blanket, a configuration of the heat blanket, placement of various temperature sensors and other preparation guidance. The thermal management advisor may provide advice or guidance regarding how to alter or manage the repair setup during a thermal survey and during the actual curing process. For example, thermal management advisor may recommend particular temperature sensors or areas of the repair field that should be insulated.