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Mach digital readout displayed on the PFDs remains the selected airspeed type. If
Mach is the selected airspeed type, the display automatically transitions from
Mach to IAS when descending through 32,400 feet
• The speed target is set to 250 kts upon ASEL becoming the active FD mode
• Selection of any lateral or vertical FD mode while in EDM results in the EDM
annunciation flashing for five seconds
• The FD flies a HDG/FLC descent to 15,000 ft. The FD performs a normal
transition to ASEL and then ALT mode upon leveling at 15,000 ft. The EDM
annunciation flashes for five seconds upon transitioning between modes. The FD
vertical mode annunciation remains EDM until the mode is exited
• The FD system remains in EDM until the autopilot is disengaged. This is the only
way to cancel the emergency descent mode
P I LOT T R A I N I N G GU I D E
AUTOMATIC FLIGHT CONTROL SYSTEM
2-42 For Training Purposes Only
Sept 04
• Activation of TCS for greater than 1 second is considered an autopilot
disengagement
• The autopilot is disengaged at anytime while in EDM
• When the autopilot is disengaged, the FD modes remain the lateral and vertical
modes active at the time. The FD mode is HGD/FLC if the autopilot is disengaged
while in the descent and ASEL is not active, HDG/ASEL if the autopilot is
disengaged while transitioning from descent to level flight or HDG/ALT if the
autopilot is disengaged after capturing the selected altitude target
• Autothrottle is automatically engaged upon initiation of the emergency descent
mode
• Cancellation of the emergency descent mode does not disengage the autothrottles
• Autothrottles are manually disengaged and reengaged while in EDM. The
autothrottles are not automatically reengaged if disengaged. Auto engagement
occurs only upon initiation of the emergency descent mode
• The EMERGENCY DESCENT CAS message is recorded by the FDR when
posted
AUTOPILOT – FLIGHT DIRECTOR EICAS MESSAGES
789
1 . 65
GX_02_044
AP PITCH TRIM FAIL
AP TRIM IS NU
AP TRIM IS ND
AP TRIM IS LWD
AP TRIM IS RWD
AFCS ENGAGE INVAL
YD 1 FAIL
YD 2 FAIL
YD OFF
YD 1-2 FAIL
AP PITCH TRIM FAIL
Indicates that autopilot
pitch trim is inoperative.
AP TRIM IS NU-ND
Indicates that autopilot
pitch mistrim monitor
detects excessive forces.
AP TRIM LWD-RWD
Indicates that autopilot roll
mistrim monitor detects
excessive forces.
YD OFF
Indicates that fault warning
computer detects that no
yaw damper is engaged.
AFCS ENGAGE INVAL
Indicates that fault warning
computer detects invalid
autopilot engagement.
YD 1 (2) FAIL
Indicates that yaw
damper 1 (2) has failed.
YD 1-2 FAIL
Indicates that both
yaw dampers
failed
have
For Training Purposes Only
Sept 04
2-43
P I LOT T R A I N I N G GU I D E
AUTOMATIC FLIGHT CONTROL SYSTEM
AUTOPILOT – FLIGHT DIRECTOR EICAS MESSAGES (Cont)
GX_02_045
AFCS 1 (2) FAIL
Indicates that AFCS (one or both)
functions has failed. The AFCS
functions include yaw damper, autopilot
and flight director.
YD NOT CENTERED
Indicates that the YD linear actuator is
not centered while on the ground.
789
1 . 65
AFCS 1 FAIL
AFCS 2 FAIL
YD NOT CENTERED
P I LOT T R A I N I N G GU I D E
AUTOMATIC FLIGHT CONTROL SYSTEM
2-44 For Training Purposes Only
Sept 04
EMS CIRCUIT PROTECTION
M
M
M
M
BRT
CIRCUIT BREAKER SYSTEM
STAT SYS BUS
PREV
PAGE
NEXT
PAGE
CNTL TEST
BUS
EMER
CONT
GX_02_046
CB - AFCS SYSTEM 1/3
A/T CTLR
A/T SERVOS
AP 1 SERVOS
AP 2 SERVOS
GUID PANEL CH 1
GUID PANEL CH 2
AC 1
DC 1
DC1
DC 2
BATT
DC ESS
IN
IN
IN
IN
IN
IN
CCBP
CB - AFCS SYSTEM 2/3
IAC 1
IAC 2
IAC 3
YD 1
YD 2
YD HEAT 1
BATT
DC ESS
BATT
BATT
DC ESS
DC 1
IN
IN
IN
IN
IN
IN
CB - AFCS SYSTEM 3/3
YD HEAT 2 DC 2 IN
CIRCUIT BREAKER - SYSTEM 1/1
AFCS
AIR COND/PRESS
APU
BLEED
CAIMS
COMM
DOORS
ELEC
ENGINE
FIRE
FLT CONTROLS
FUEL
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AUTOMATIC FLIGHT CONTROL SYSTEM(16)
