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DFGC 1 and 2 receive inputs from the digital Central Air Data Computers (CADC 1 and 2), VHF navigation systems (VOR / LOC 1 and 2), compass systems 1 and 2, vertical gyros 1 and 2, radio altimeters 1 and 2, dual three-axis accelerometer, dual lateral accelerometer, performance management computer, and sensors of other airplane systems and functions. A Flight Guidance Control Panel (FGCP) is provided for selection of desired FGS modes of operations by the Captain and First Officer.
DFGC 1 or 2, as selected, provides data inputs for the following integrated FGS functions: Autopilot (AP); stability augmentation; Flight Director (FD); Speed Control (SC); Autothrottle System (ATS); thrust (EPR) rating; Automatic Reserve Thrust (ART); and altitude alert.
Aircraft in the Continental fleet are equipped with a -904, -906, or -930 DFGC.
Flight Mode Annunciators (FMAs) are provided for the Captain and First Officer. The FMAs display the following: annunciations for selected FGS mode of operation; legend annunciations to indicate that the navigation instrument comparator monitor has detected a difference between redundant systems, or to indicate a system failure (associated with an indicator flag); AP and THROTTLE warning lights; and FD and AP selection.
An ANNUN / DIGITAL LTS TEST button is provided on the overhead panel for testing the legend annunciation and warning lights and digital alphanumeric display lights on both FMAs, and the digital display lights on the FGCP and VHF NAV control panels. When the button is pushed, the THROTTLE, AP, legend annunciation, and digital alphanumeric display lights on the FMA’s will come on, and the digital display lights on the FGCP and VHF NAV control panels will come on. Each of the four digital alphanumeric displays on each FMA will form a lighted starburst. When the test button is released, FMA displays ILS, HORIZON, HEADING, and MONITOR, go out for 0.5 seconds, and then come back on. All amber caution lights will return to normal display 5 seconds after the test button is released.
Continental
Rev. 12/01/00 #29 Flight Manual
AUTOPILOT
The Autopilot (AP) function, operating in conjunction with the yaw damper function, automatically controls the airplane in pitch, roll, and yaw maneuvering axes. Appropriate control surfaces are actuated by the AP to control the airplane for the selected AP mode of operation.
The FGCP contains the necessary controls for the Captain and First Officer to select desired AP modes of operation. The AP modes of operation will automatically control the airplane pitch and roll attitude for the following maneuvers: maintain an existing altitude; descend or climb to and maintain, a preselected altitude; maintain a selected vertical speed, indicated airspeed or Mach number; fly a Performance Management System (PMS) profile (if installed); maintain an existing heading; fly to and maintain a preselected heading; fly to, capture, and track a selected VOR or localizer course; capture and track a glideslope; runway alignment and flare for automatic landing. A DFGC switch is provided on the FGCP for selection of DFGC 1 or 2 for data input for AP operation.
The AP warning light on the FMAs will illuminate when the AP disengages for any reason. An AP TRIM annunciator light on the FMAs will illuminate to indicate that the horizontal stabilizer is out of trim. The light will extinguish when horizontal stabilizer is in trim. Appropriate annunciations will appear on both FMAs to indicate existing AP operating mode.
STABILITY AUGMENTATION
Mach Trim Compensator
DFGC 1 or 2 provides computations for the Mach Trim Compensator (MTC) function if MACH TRIM COMP switch is in NORM. CADC inputs through the DFGC control the MTC actuator in relation to Mach number. The MTC compensates for nosedown pitching moments that are generated during operation at high Mach numbers. MTC function can be inhibited by moving MACH TRIM COMP switch to OVRD.
Yaw Damper
The yaw damper function is activated at any time the AP is engaged when the YAW DAMP switch is ON or OFF. With AP disengaged, the yaw damper function is activated by moving the YAW DAMP switch to ON. Rudder movements generated by the yaw damper function are not transmitted to the rudder pedals. Yaw damper function can be inhibited by moving the YAW DAMP switch to OVRD.
FLIGHT DIRECTOR
The Flight Director (FD) provides visual guidance commands to fly the airplane manually or to visually monitor AP response to the guidance commands. The visual guidance commands (pitch, roll, and speed control) are integrated with FGS operating modes selected on the FGCP for AP operation. The FGS operating modes (except LAND) can be selected for FD only with the AP disengaged.
Pitch (including speed control) and roll guidance cues from the DFGC are displayed on the Attitude Director Indicator (ADI). A V-command bar on the ADI directs the pilot to turn, climb, or descend. A fast / slow indicator reflects airplane speed in relation to speed selection on the FGCP or computed safe speed above stall (ALFA speed) or the target speed as computed by PMS.
　
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