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Upon occurrence of any single failure, the autopilot will not: -Cause significant displacement of the aircraft from its approach path or altitude loss below the nominal glide path -(Upon system disconnection) Involve any out-of-trim condition not easily controlled by the pilot -Cause any action to occur with the flight control system that is not readily apparent to the pilot, either by control column movement or advisory display The automatic flight-control system (AFCS) consists of dual-independent flight directors, a three axis autopilot, and auto-matic pitch trim and yaw damper system. The AFCS operates with the integrated-avionics processor system (IAPS). The IAPS collects the data for the avionics sys-tems. The AFCS gives the course, heading, and preselected altitude data to the electronic flight instrument system (EFIS). The AFCS calculates the vertical and lateral flight-guidance commands to keep the aircraft on the correct pitch/roll attitude. The flight directors show the flight-guidance commands on the primary flight displays. ENGAGEMENT PARAMETERS The autopilot can be engaged using the AP switch on the FGP, if the following conditions exist: -Yaw damper is operable -Both flight guidance computers (FGCs) are serviceable -At least one channel of the horizontal stabilizer trim is engaged and the FCCs detect no faults with the horizontal stabilizer trim system -No significant instability of the aircraft exists COMPONENTS AND OPERATION AUTOPILOT ENGAGEMENT The autopilot is engaged by pressing the AP switch located on the flight guidance panel. When the autopilot is engaged, both channels of the autopilot are coupled to the onside flight guidance computer. Autopilot engagement is indicated on the PFD by a green AP indication. Pressing the AP switch on the FGP when the autopilot is engaged will cause the autopilot to disengage. AUTOPILOT SERVO MOTORS AUTOMATIC FLIGHT CONTROL SYSTEM
Volume 2 Flight Crew Operating Manual May 06/2005 CSP 100-6 REV 2 |
