Monitoring the creep of an aircraft turbomachine vane

A method for monitoring the creep of a turbomachine vane, in particular of an aircraft, the vane being made of a metal alloy and comprising at least one platform connected to at least one blade, the method comprising the following steps:

• a) determining at least one geometric parameter for monitoring the vane, this parameter having a value which changes as a function of the deformations by creep of the vane,
• b) determining an acceptability threshold for the or each parameter,
• c) verifying in particular in situ the conformity of the or each parameter with respect to the corresponding threshold, by mounting at least one verifying template directly on the vane, this template having a shape complementary to a portion of the vane comprising the parameter to be verified, and by detecting the possible presence of a clearance(s) between the template and this portion of the vane on which the template is positioned, and
• d) concluding on the conformity of the vane as a function of the results of the verification.