The present invention relates to a method for repairing a damaged thermal protection covering a nacelle structure for an aircraft turbojet engine by adding a repair thermal insulation blanket as well as a repair sheet onto the damaged part.

The present disclosure is directed to a system and method for repairing an abradable material coated on a casing of a gas turbine engine. The system includes an articulating guide configured to fit into an access port of the gas turbine engine. Further, the articulating guide has a proximal end and a distal end. The system also includes a repair tool configured at a distal end of the articulating guide. The repair tool includes a body having a proximal end and a shaped distal end, with the shaped distal end extending away from the body. Thus, the shaped distal body is configured to trench out an area of the abradable material comprising a defect. The system also includes a filler material for filling the trenched out area.

A method for repair of a damaged stiffened panel of isogrid type, wherein the repair method comprises a step of removal of material with the aim of removing at least one damaged rib and also steps of fitting at least one structural reinforcement connecting at least two nodes positioned about the damaged zone and of at least one wall reinforcement connecting the wall of the stiffened panel and the structural reinforcement.

A method for repair of a damaged stiffened panel of isogrid type, wherein the repair method comprises a step of removal of material with the aim of removing at least one damaged rib and also steps of fitting at least one structural reinforcement connecting at least two nodes positioned about the damaged zone and of at least one wall reinforcement connecting the wall of the stiffened panel and the structural reinforcement.

Provided is a router guide that comprises: a guide part that has a first through-hole and a guide surface that guides a cutting tool attachment part of a router device along the first through-hole; a maintaining part that maintains the position of the guide surface; and a positioning part that positions the guide part. The guide surface is formed such that, in a state where the maintaining part is in contact with a surface of a composite material, the distance from the surface becomes smaller as the guide surface approaches a second through-hole. The guide part is formed so as to be elastically deformable. In a case where the guide part is caused to elastically deform along the surface shape of the composite material, the maintaining part maintains the position of the guide surface with respect to the surface at a position that corresponds to the surface shape.

The present invention relates to a method for repairing a damaged thermal protection covering a nacelle structure for an aircraft turbojet engine by adding a repair thermal insulation blanket as well as a repair sheet onto the damaged part.

The present disclosure is directed to a system and method for repairing an abradable material coated on a casing of a gas turbine engine. The system includes an articulating guide configured to fit into an access port of the gas turbine engine. Further, the articulating guide has a proximal end and a distal end. The system also includes a repair tool configured at a distal end of the articulating guide. The repair tool includes a body having a proximal end and a shaped distal end, with the shaped distal end extending away from the body. Thus, the shaped distal body is configured to trench out an area of the abradable material comprising a defect. The system also includes a filler material for filling the trenched out area.

Provided is a router guide that comprises: a guide part that has a first through-hole and a guide surface that guides a cutting tool attachment part of a router device along the first through-hole; a maintaining part that maintains the position of the guide surface; and a positioning part that positions the guide part. The guide surface is formed such that, in a state where the maintaining part is in contact with a surface of a composite material, the distance from the surface becomes smaller as the guide surface approaches a second through-hole. The guide part is formed so as to be elastically deformable. In a case where the guide part is caused to elastically deform along the surface shape of the composite material, the maintaining part maintains the position of the guide surface with respect to the surface at a position that corresponds to the surface shape.