Patent ID: 6923405

Claim:
A power control unit for an aircraft, the aircraft to include a control surface and a command path, the power control unit comprising: an override mechanism coupled to the control path; a first control member coupled to the override mechanism whereby the override mechanism transfers a control command from the command path to the first control member; a second control member coupled to the control path whereby the command path transfers the control command to the second control member; a first and a second actuator member coupled to the first and the second control members respectively such that the first and second control members respectively attempt to move to the first and second actuator members in response to the control command, whereby the override mechanism allows the second control member to move the second actuator member when the first control member resists moving in response to the control command; an actuator including a first piston coupled to the first actuator member and a second piston coupled to the second actuator member and adapted to be coupled to the control surface, whereby the actuator moves the control surface in response to the command; a housing containing the first and the second pistons; a first pressure sensor connected across the first piston to electronically sense a first delta pressure across the first piston; a second pressure sensor connected across the second piston to electronically sense a second delta pressure across the second piston; and a comparator adapted to electronically compare the first and second delta pressures and activate a standby actuator when the difference between the first and the second delta pressures exceeds a predetermined threshold indicative of the first control member resisting moving in response to the control command.