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MAGENTA, READOUT
REV 56, Jan 31/03
Vol. 1 03--20--18
AUTOMATIC FLIGHT CONTROL SYSTEM
Flight Control and Guidance
Flight Crew Operating Manual MASTER
CSP A--013
Automatic Flight Control System EICAS Indications <MST>
Figure 03---20---7
AFCS MSG FAIL
Warning (red)
IAPS DEGRADED status (white)
Indicates that an IAPS bus has failed.
IAPS OVERTEMP status (white)
Indicates that an IAPS overtemperature
condition has been detected.
FD 1 or 2 FAIL status (white)
Indicates that the respective flight
director has failed.
SPEED REFS INDEP
Status (white)
Comes on to indicate
that the pilot’s and
copilot’s V--speed
selections are not
synchronized.
Comes on to indicate
the presence of an
invalid flight control
system (FCS)
message.
AFCS MSG FAIL
Primary Page
<0039>
<0006>
Status Page
FD 1 FAIL
<0039>
<0039>
FD 2 FAIL
IAPS DEGRADED
IAPS OVERTEMP
SPEED REFS INDEP
Vol. 1 03--20--19
REV 56, Jan 31/03
AUTOMATIC FLIGHT CONTROL SYSTEM
Flight Control and Guidance
Flight Crew Operating Manual
CSP A--013
MASTER
G. System Circuit Breakers
SYSTEM SUB--SYSTEM CB NAME BUS BAR CB
PANEL
CB
LOCATION
NOTES
Integrated
Avionics
Left AFCS IAPS LEFT
AFCS DC BAT 2 P7
Processor
System Right AFCS IAPS RIGHT
AFCS DC BUS 2 2 H3
REV 56, Jan 31/03
Vol. 1 03--20--20
AUTOMATIC FLIGHT CONTROL SYSTEM
Flight Control and Guidance
Flight Crew Operating Manual MASTER
CSP A--013
THIS PAGE INTENTIONALLY LEFT BLANK
Vol. 1 03--30--1
REV 56, Jan 31/03
AUTOMATIC FLIGHT CONTROL SYSTEM
Autopilot
Flight Crew Operating Manual
CSP A--013
MASTER
1. AUTOPILOT
The automatic flight control system (AFCS) provides a two axes, digital, fail-passive autopilot
(AP). The AP system automatically controls the aircraft in the pitch, roll and yaw axis, in
response to flight director commands, by actuating the appropriate control surfaces. The
fail-passive AP system is protected against internal single hardware faults and limits any
malfunctioning commands to a response that is easily controlled by the pilot. Command
inputs to the ailerons and elevators are provided by servos controlled by the flight control
computers (FCC’s). The FCC’s input the yaw damper system to control the rudder
To engage the autopilot, the following is required.
S Both flight control computers must be operative and detecting no failures
S The AP DISC switch--bar is in the UP position
S At least one channel of the horizontal stabilizer trim is operative
S At least one yaw damper is engaged
S At least one AHRS system is operable
S At least one IRS system is operable <0025>
S At least one air data computer (ADC) is operative
S There is no significant instability of the aircraft
NOTE
Significant instability exists during the following
conditions: pitch rate over 5 degrees/second, normal
acceleration less than --.4g or over.6g, roll rate over 21
degrees/second, bank angle over 45 degrees, pitch
angle below 15 degrees nose down or above 25
degrees nose up, or when the yaw rate exceeds 9
degrees/second.
The AP is annunciated with lights at the side of the AP ENG switch on the FCP and a green
AP message on the EICAS status page. During AP synchronization, the AP annunciation
changes to amber.
A warning for AP engagement during take--off is annunciated with a red CONFIG AP
message on the EICAS pimary page and a “CONFIG AUTOPILOT” aural alert.
Turbulence mode reduces autopilot gain so that flight control computer response to turbulent
flight conditions is slowed and aircraft motion is smoother. Turbulence mode is selected by
pushing the TURB switch on the FCP Turbulence mode cannot be selected, if the on-side
localizer is captured, or if the AP is disengaged. Turbulence mode can be cleared by
pushing the TURB switch again, by an on--side localizer capture or by AP disengagement.
REV 56, Jan 31/03
Vol. 1 03--30--2
AUTOMATIC FLIGHT CONTROL SYSTEM
Autopilot
Flight Crew Operating Manual MASTER
CSP A--013
Autopilot --- General <MST>
Figure 03---30---1
Flight Control Panel
Center Glareshield
<0015>
Primary Flight Display
Pilot’s and Copilot’s Instrument Panels
Green indicator lights on either
side of switch indicate engaged.
NOTE
Vol. 1 03--30--3
REV 56, Jan 31/03
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