Patent ID: 9382018
Filing Date: 2016-07-05
CPC Classification: B29C,B64F,Y10T

Claim Text:
1. A repair method for a damaged area in the coating of a fiber-reinforced composite fuselage, comprising: drilling a circular hole, substantially centered on an intersection of sides of a polygonal outline of a cut-out in the fuselage around the damaged area, at corners of said outline; cutting lines of the cut-out that extend from the corners; fitting a coating liner with a polygonal outline, the liner having an area greater than an area of the cut-out and adjusting a shape of the fuselage so as to close the cut-out; fastening said liner to a fuselage skin outside of the damaged area with a plurality of fasteners, each respective edge of a perimeter of the liner having adjacent thereto N rows of plural fasteners, laid out parallel to the respective edge, wherein N is a positive integer greater than or equal to 2, and wherein at each respective corner of the liner, a diagonal of the fasteners is fitted, wherein a first end of the diagonal being a terminal fastener of an outermost row of plural fasteners on a first edge of the coating liner and being N fasteners away from a second edge of the coating liner, and a second end of the diagonal being is a second terminal fastener of an outermost row of plural fasteners on the second edge of the coating liner and being N fasteners away from the first edge of the coating liner, and wherein fasteners are not fitted outside the diagonal in a direction toward the respective corner.