Method for correcting the radial moment weight of a vane for an aircraft turbine engine

A method for correcting a radial moment weight of a vane for an aircraft turbine engine, the method comprising the following steps:

• (a) providing the vane extending along an axis of elongation between a free end and opposite a root, the vane comprising a blade made of composite material and having a leading edge, a trailing edge connected to the leading edge by a suction side, and a pressure side opposite the suction side, the vane further comprising a protective shield attached to the leading edge;
• (b) measuring the radial moment weight of the vane;
• and
• (c) comparing the measured radial moment weight with a reference value and adjusting the radial moment weight of the vane as a function of the result of the comparison, wherein in step (a), the vane comprises at least one adjustment cavity extending along the leading edge and opening onto the free end of the vane, and in step (c), the adjustment is carried out by inserting a first material into the adjustment cavity.