A fan case suitable for covering fan blades of an aircraft jet engine, the fan case comprising: a case body in a cylindrical shape; a linking ring, the linking ring being made of Al, having an annular groove opened in a centrifugal direction, and being fitted and fixed to an outer peripheral side of a peripheral wall in a rear end portion of the case body, the rear end portion being, when installed in the aircraft jet engine, located on a rear side of the aircraft jet engine, the annular groove being configured to be linked to a reverse thrust transmission body and receiving a reverse thrust load; and a ring constituent body, the ring constituent body being made of Ti alloy, having an arcuate groove opened in the centrifugal direction, and being placed on the peripheral wall in the rear end portion of the case body, the arcuate groove being linked to the reverse thrust transmission body and being configured to undertake a reverse thrust load larger than the reverse thrust load received by the linking ring, wherein the ring constituent body is fitted in a notch, the notch being formed in the linking ring and being, when installed in the aircraft jet engine, opened toward rear of the aircraft jet engine, so that the linking ring and the ring constituent body are integrated with each other, the ring constituent body is positioned relative to the case body in an axial direction and in a radial direction respectively by bringing the ring constituent body, placed on the peripheral wall of the case body, into contact with, and fixing the ring constituent body to, an outward receiving wall formed on the linking ring and protruding in the centrifugal direction, and the annular groove of the linking ring and the arcuate groove of the ring constituent body continue to each other, characterised by the case body being made of a composite material in which reinforcing fibers are impregnated with a thermosetting resin. a case body in a cylindrical shape; a linking ring, the linking ring being made of Al, having an annular groove opened in a centrifugal direction, and being fitted and fixed to an outer peripheral side of a peripheral wall in a rear end portion of the case body, the rear end portion being, when installed in the aircraft jet engine, located on a rear side of the aircraft jet engine, the annular groove being configured to be linked to a reverse thrust transmission body and receiving a reverse thrust load; and a ring constituent body, the ring constituent body being made of Ti alloy, having an arcuate groove opened in the centrifugal direction, and being placed on the peripheral wall in the rear end portion of the case body, the arcuate groove being linked to the reverse thrust transmission body and being configured to undertake a reverse thrust load larger than the reverse thrust load received by the linking ring, wherein the ring constituent body is fitted in a notch, the notch being formed in the linking ring and being, when installed in the aircraft jet engine, opened toward rear of the aircraft jet engine, so that the linking ring and the ring constituent body are integrated with each other, the ring constituent body is positioned relative to the case body in an axial direction and in a radial direction respectively by bringing the ring constituent body, placed on the peripheral wall of the case body, into contact with, and fixing the ring constituent body to, an outward receiving wall formed on the linking ring and protruding in the centrifugal direction, and the annular groove of the linking ring and the arcuate groove of the ring constituent body continue to each other, characterised by the case body being made of a composite material in which reinforcing fibers are impregnated with a thermosetting resin.