A mechanism is described for an aircraft having a primary hydraulically operated flight control system with a plurality of hydraulic actuators, and a redundant secondary manually operated mechanical flight control system. The mechanism provides for the automatic and immediate operability of the manually operated system, when the hydraulic system fails. The mechanism includes mechanical locks in each hydraulic actuator, with the locks linked together to move in unison. The locks are preloaded by springs, and hydraulic pressure in any of the actuators maintains the locks in an open condition. However, in the event that hydraulic pressure is completely lost, the locks become operable (i.e., close) and permit the continued control of the aircraft by use of the manually operated mechanical flight control system. (Author)
Mode Shift and Redundant Control
1976
15 pages
Report
No indication
English