A drive system, comprising: a housing; a gear set for moving an aircraft control surface; a permanent magnet generator comprising a permanent magnet stator disposed on the housing and a permanent magnet rotor disposed on an output member of the gear set and rotatably disposed within the permanent magnet stator; and a health monitoring system in communication with the gear set, the health monitoring system comprising: a temperature sensor disposed on a gear of the gear set and arranged to provide a signal indicative of at least one of a temperature and a temperature rise of the gear; and a control system arranged to receive the signal, wherein: the temperature sensor is provided with a transmitter which is configured to provide signal processing and wireless communication between the temperature sensor and the control system, and wherein a permanent magnet generator powered diode is arranged to power the transmitter; the temperature sensor is part of a temperature sensor assembly of the health monitoring system disposed within the housing and wherein the gear set is positioned within the housing, and wherein the control system is in communication with the temperature sensor assembly, and the control system is configured to output for display an indicator responsive to at least one of the temperature and the temperature rise of the gear set being greater than a threshold; an actuator of the drive system includes the housing and the gearset disposed within the housing, and the gear set includes the gear, the gear being suitable for being drivably connected to the aircraft control surface, and wherein the actuator is a line replaceable unit suitable for being arranged to provide a rotary or linear output to the aircraft control surface or vary a position of the aircraft control surface. a housing; a gear set for moving an aircraft control surface; a permanent magnet generator comprising a permanent magnet stator disposed on the housing and a permanent magnet rotor disposed on an output member of the gear set and rotatably disposed within the permanent magnet stator; and a health monitoring system in communication with the gear set, the health monitoring system comprising: a temperature sensor disposed on a gear of the gear set and arranged to provide a signal indicative of at least one of a temperature and a temperature rise of the gear; and a control system arranged to receive the signal, a temperature sensor disposed on a gear of the gear set and arranged to provide a signal indicative of at least one of a temperature and a temperature rise of the gear; and a control system arranged to receive the signal, wherein: the temperature sensor is provided with a transmitter which is configured to provide signal processing and wireless communication between the temperature sensor and the control system, and wherein a permanent magnet generator powered diode is arranged to power the transmitter; the temperature sensor is part of a temperature sensor assembly of the health monitoring system disposed within the housing and wherein the gear set is positioned within the housing, and wherein the control system is in communication with the temperature sensor assembly, and the control system is configured to output for display an indicator responsive to at least one of the temperature and the temperature rise of the gear set being greater than a threshold; an actuator of the drive system includes the housing and the gearset disposed within the housing, and the gear set includes the gear, the gear being suitable for being drivably connected to the aircraft control surface, and wherein the actuator is a line replaceable unit suitable for being arranged to provide a rotary or linear output to the aircraft control surface or vary a position of the aircraft control surface. the temperature sensor is provided with a transmitter which is configured to provide signal processing and wireless communication between the temperature sensor and the control system, and wherein a permanent magnet generator powered diode is arranged to power the transmitter; the temperature sensor is part of a temperature sensor assembly of the health monitoring system disposed within the housing and wherein the gear set is positioned within the housing, and wherein the control system is in communication with the temperature sensor assembly, and the control system is configured to output for display an indicator responsive to at least one of the temperature and the temperature rise of the gear set being greater than a threshold; an actuator of the drive system includes the housing and the gearset disposed within the housing, and the gear set includes the gear, the gear being suitable for being drivably connected to the aircraft control surface, and wherein the actuator is a line replaceable unit suitable for being arranged to provide a rotary or linear output to the aircraft control surface or vary a position of the aircraft control surface.