Fan rotor blade of aircraft jet engine

A fan rotor blade for an aircraft jet engine configured to be fitted in a fitting groove formed in a fan disk, and to take external air into a passage formed in an engine case by rotating integrally with the fan disk, the fan rotor blade comprising:

• a blade body made from a composite material of a resin and fibers, and including a pressure surface facing one side in a rotation direction and a suction surface facing the other side in the rotation direction;
• a fitting portion provided on one end side of the blade body in a longitudinal direction thereof, and fitted into the fitting groove in the fan disk;
• and
• a sheath being more rigid than the blade body, and fixed to the blade body in a state where the sheath covers a leading edge portion of the blade body and the vicinity thereof, the leading edge portion being located on an upstream side in a direction of intake of the external air;
• wherein the sheath extends in the longitudinal direction of the blade body from the one end side to the other end side of the blade body in the longitudinal direction, and
• a base end portion of the sheath, which is one end of the sheath in the longitudinal direction, is located closer to the one end side of the blade body than the passage formed in the engine case.