FSS Documentation Hub
E-Jet Series
E-Jet Series
  • Introduction
    • Welcome
    • First Steps
    • FAQs
    • How To Update
  • Normal Procedures
    • Checklist
    • Limitations
    • Approach Types
    • Procedure Guide
  • Systems Guide
    • Overhead Panel
      • ELECTRICAL - AC
      • ELECTRICAL - DC
      • COCKPIT LIGHTS
      • ENGINE FIRE HANDLE
      • FUEL
      • PASSENGER SIGNS
      • FIRE EXTINGUISHER
      • APU CONTROL
      • WINDSHIELD WIPER
      • EXTERNAL LIGHTS
      • HYDRAULIC
      • PRESSURIZATION
      • ICE PROTECTION
      • AIR COND / PNEUMATIC
      • PASSENGER OXYGEN
      • GND PROX TERR INHIB AND EMERG/PRKG BRAKE
    • Main Panel
      • Primary Flight Display (PFD)
        • SPEEDS
        • FLIGHT MODE ANNUNCIATORS (FMA)
        • ALTITUDES
        • MARKER BEACONS
        • FLIGHT PATH / ATTITUDE INDICATIONS
        • HORIZONTAL SITUATION INDICATOR (HSI)
        • LATERAL/VERTICAL DEVIATION INDICATION
        • VERTICAL NAVIGATION (VNAV)
        • WIND DISPLAY / TIMER
        • FMS MODE ANNUNCIATORS
        • COM / NAV
        • DISPLAYS
      • Multifunction Display (MFD)
        • GENERAL
        • SYSTEMS/STATUS
        • SYSTEMS/ANTI ICE
        • SYSTEMS/ECS
        • SYSTEMS/ELEC
        • SYSTEMS/FLTCTRL
        • SYSTEMS/FUEL
        • SYSTEMS/HYDR
        • TCAS
        • WEATHER
      • EICAS
        • THRUST
        • FUEL / OIL
        • SLATS / FLAPS / SPEEDBRAKE
        • CREW ALERTING SYSTEM (CAS)
        • GEAR / BRAKE
        • APU
        • CABIN ALT / LFE
        • TRIM
      • Reversionary Panel
      • Integrated Electronic Standby System (IESS)
      • Autobrake
      • Gnd Prox Terr Inhib and EMERG/PRKG Brake
      • Clock
      • Landing Gear
      • ELT and GND PROX G/S INHIB
      • LG WRN INHIB and ADS Probes Heater
    • Central Pedestal
      • Multifunction Control Display Unit (MCDU)
      • FLIGHT CONTROL MODE
      • STALL WARNING
      • POWERPLANT
      • T/O CONFIG and EICAS FULL
      • Cursor Control Device (CCD)
      • SPEEDBRAKE / SPOILERS
      • THRUST LEVER QUADRANT
      • Ram Air Turbine (RAT)
      • GND PROX FLAP OVRD and SLAT/FLAP LEVER
      • AUDIO CONTROL
      • TRIM
      • COCKPIT DOOR CONTROL
      • EMERGENCY/PARKING BRAKE / PA
      • ELEVATOR / AILERON DISCONNECT
      • CONTROL WHEEL
    • Cockpit Floor
    • Cockpit Side
    • Head-Up Display
  • Autopilot Guide
    • Flight Director (FD)
    • Autopilot (AP)
    • Yaw Damper (YD)
    • AFCS Indications on PFD
    • FGCS Lateral Modes
    • FGCS Vertical Modes
    • Steep Approach Mode
    • Speed Control
  • MCDU Guide
    • TRS - Thrust Rating System
  • ⭐Special Features
    • Cabin Announcements
    • GSX Automation
  • 📂Supplements
    • GSX Profiles
    • SimBrief Profiles
    • Hardware Integration
    • PaintKit
    • Landing Distance Calculator
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  • ENGAGEMENT
  • DISENGAGEMENT
  1. Autopilot Guide

Autopilot (AP)

ENGAGEMENT

Autopilot engagement is inhibited on the ground.

In flight the autopilot is engaged pushing the AP button on the guidance panel. The AP engagement is verified on the FMA on both PFD’s.

With the confirmation of the AP label on the FMA the autopilot is controlling the airplane pitch, roll and yaw according to the flight director selections.

DISENGAGEMENT

NORMAL DISENGAGEMENT

The autopilot is normally disengaged by pressing the quick disconnect PB on either control wheel.

Pressing the button once:

  • Disengages the autopilot;

  • Triggers the aural warning “AUTOPILOT”;

  • The FMA “AP” annunciation blinks in red.

Pressing the button the second time cancels the aural warning and the FMA annunciation.

The autopilot may be momentarily overridden by pressing the TCS button on the control wheel. Releasing the TCS, the autopilot resumes airplane control.

NON-NORMAL DISENGAGEMENT

The autopilot also disengages if one of the following conditions occurs:

  • AP button is pressed on the guidance panel;

  • Either manual pitch trim switch is actuated;

  • Either stick shaker is activated.

  • Windshear escape guidance is activated.

ABNORMAL DISENGAGEMENT

The following events cause an autopilot disconnect and EICAS message:

  • Reversion of the fly-by-wire system to direct mode.

  • Either the aileron or elevator control system is disconnected.

  • A pilot input contrary to the autopilot is made on the controls with a long time light force or a short time stronger force.

  • Internal monitor failure.

After Non-Normal or Abnormal Disengagement, pressing either AP disconnect button once cancels the flashing “AP” on the FMA and silences the aural alarm.

NOTE: AP disengagement by application of force on control column, through the forward and after movement, and control wheel, lateral movement, is indicated in red on FMA. The AP disengagement by application of force only on control wheel may be indicated in red on FMA and AP FAIL message may be displayed on the EICAS.

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Last updated 1 year ago