![]() This sensor comprises of two potentiometers providing the two artificial feel computers with yaw deflection data. They initiate the computer monitoring channel tests.Ī Yaw deflection sensor (C246), located in zone 121 and driven by a link actuated by the Yaw torque tube. Two press-to-test push buttons (IC245 and 2C245) located on panel 29-214 at Flight Engineer’s station. These allow activation of the system and transmit orders generated by the computer. ![]() Two Artificial Feel engage switch units (IC236 andĢC236) which are located on overhead panel. They develop load laws and monitor the system. Computer No.2 (2C235) in right-hand electronics rack, on shelf -6-216. Two Artificial Feel computers: Computer No.1 (IC235) is located in left-hand electronics rack, on shelf 6-215. The two systems comprise of the following: These two systems operate simultaneously. There are two identical Artificial Feel systems provided on the aircraft. The stand-by hydraulic pressure (Yellow) is not used.Ī spring rod provides the resistance corresponding to tow speed conditions and ensures a minimum safety in case of a double electro-hydraulic failure. When both the YAW switches are engaged, the Green jack automatically replaces the Blue jack in the case of a failure of the latter. “The second jack is supplied with Green hydraulic system pressure and the jack control computer is activated when the YAW switch on the ARTIFICIAL FEEL engage switch unit No.2 (on overhead panel in the flight deck compartment) is engaged. The control computer is activated when the YAW switch on the ARTIFICIAL FEEL engage switch unit No.1 (on overhead panel in the flight deck compartment) is engaged. The first jack, which acts in priority, is supplied with pressure from the Blue hydraulic system. Both jacks are controlled permanently, but only one is operative, the second one remaining at a stop. The variable resistance is ensured by two hydraulic jacks, each controlled by a computer. For the yaw axis, the object is to apply to rudder pedals a load proportional to a function of calibrated airspeed and to the defection limit imposed by structure.
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