PROBLEM TO BE SOLVED: To provide a method, system and computer program product for assessing residual life of an airfoil which would experience high cycle fatigue failure under at- or near-resonance vibration condition.SOLUTION: The method includes receiving, at a processing system, at least one vibration response parameter associated with the airfoil. The method processes at least one cracked airfoil finite element model. Steps for processing the cracked airfoil finite element model include: a step for accessing the cracked airfoil finite element model; a step for computing a modal stress intensity factor (SIF) of the cracked airfoil finite element model using fracture mechanics based finite element analysis; and a step for computing a vibratory SIF based on the modal SIF and the at least one vibration response parameter. The method then computes a residual life indicator of the airfoil based, at least in part, on the vibratory SIF.