Blade made of organic matrix composite material provided with a metal strip, and a method of fastening a metal strip on a blade fiber preform

A blade made of organic matrix composite material for a gas turbine aeroengine, the blade comprising:

• an airfoil extending transversely between a leading edge and a trailing edge;
• and
• a metal strip positioned on the leading edge of the airfoil, said metal strip having two flanges extending on either side of the leading edge over portions of side faces of the airfoil forming a pressure side face and a suction side face in such a manner that the metal strip fits closely to the profile of the leading edge, the metal strip being fastened to the leading edge of the airfoil by at least one stitching thread;
• wherein said stitching thread has at least one external thread segment extending substantially along a transverse direction of the blade between a hole formed through a flange of the metal strip and a passage formed in a portion of the airfoil that has a surface that is not covered by the metal strip, said transverse direction connecting the leading edge and the trailing edge of the blade.