An active vibration control actuator mounting system for reducing vibration and noise which can be sensed in an aircraft cabin comprising: at least one actuator bracket (200A, 200B, 300, 350) including an actuator interface member (210, 310, 410) configured to hold one or more active counter-vibration inducing actuators thereon in one or more predetermined orientations, and an aircraft engine mounting structure interface member (211, 311, 411) connected to the actuator interface member (210, 310), the aircraft engine mounting structure interface member (211, 311) being configured to couple the at least one actuator bracket (200A, 200B, 300, 350) to an aircraft engine mounting structure; wherein the at least one actuator bracket (200A, 200B, 300, 350) is configured for the installation and removal of a respective one of the one or more active counter-vibration inducing actuators to and from the actuator interface member (210, 310) while a respective one of the at least one actuator bracket (200A, 200B, 300, 350) remains coupled to the aircraft engine mounting structure, and wherein stiffness and mass of the at least one actuator bracket (200A, 200B, 300, 350) is configured so that a lowest modal frequency of the at least one actuator bracket is higher than an operational frequency of the respective one of the one or more active counter-vibration inducing actuators when mounted to the at least one actuator bracket (200A, 200B, 300, 350), wherein the operational frequency corresponds to a frequency of one or more spools of an aircraft engine. at least one actuator bracket (200A, 200B, 300, 350) including an actuator interface member (210, 310, 410) configured to hold one or more active counter-vibration inducing actuators thereon in one or more predetermined orientations, and an aircraft engine mounting structure interface member (211, 311, 411) connected to the actuator interface member (210, 310), the aircraft engine mounting structure interface member (211, 311) being configured to couple the at least one actuator bracket (200A, 200B, 300, 350) to an aircraft engine mounting structure; an actuator interface member (210, 310, 410) configured to hold one or more active counter-vibration inducing actuators thereon in one or more predetermined orientations, and an aircraft engine mounting structure interface member (211, 311, 411) connected to the actuator interface member (210, 310), the aircraft engine mounting structure interface member (211, 311) being configured to couple the at least one actuator bracket (200A, 200B, 300, 350) to an aircraft engine mounting structure; wherein the at least one actuator bracket (200A, 200B, 300, 350) is configured for the installation and removal of a respective one of the one or more active counter-vibration inducing actuators to and from the actuator interface member (210, 310) while a respective one of the at least one actuator bracket (200A, 200B, 300, 350) remains coupled to the aircraft engine mounting structure, and wherein stiffness and mass of the at least one actuator bracket (200A, 200B, 300, 350) is configured so that a lowest modal frequency of the at least one actuator bracket is higher than an operational frequency of the respective one of the one or more active counter-vibration inducing actuators when mounted to the at least one actuator bracket (200A, 200B, 300, 350), wherein the operational frequency corresponds to a frequency of one or more spools of an aircraft engine.