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P604_04_029
AP Engage Button
AUTOMATIC FLIGHT CONTROL SYSTEM
For Training Purposes Only
May 03
4-5
P I LOT T R A I N I N G GU I D E
Autopilot Engagement Criteria
The autopilot can be engaged provided the following conditions exist:
• at least one yaw damper is engaged (normally, both YDs are engaged)
• AP DISC switch-bar on the FCP is in the normal position
• no faults detected in the active Flight Control Computers (FCCs)
• no significant instability exists, including:
- adverse pitch / roll / yaw rates
- G-loads exceeding predetermined values
- adverse pitch / roll attitudes exceeding predetermined values
Autopilot Engagement
Figure 4-3
7000
10000 1.0
10
10
MDA
A
A
HDG
A
DR ALTS
A
AP
2500M 4
4
2
2
1
1
M.454
280
240
220
250
260
10
100
200
900
800
000
29.92 IN
P604_04_033
AP Engage
Annunciation
AUTOMATIC FLIGHT CONTROL SYSTEM
4-6 For Training Purposes Only
May 03
P I LOT T R A I N I N G GU I D E
Autopilot Servomotors
When the autopilot is engaged, the active pair of FCCs direct roll and pitch commands
to the aileron and elevator servos, and stabilizer trim commands through the HSTCU.
When a change in roll or pitch is required, the FCCs signal the aileron servo or
elevator servo to bias the control cables and displace the associated control surface.
The aileron servo is located on the control cable run for the right aileron. Since the left
and right ailerons are normally interconnected, the servo is capable of moving both
ailerons.
The elevator servo is located in the left elevator control cable run. The servo moves
both elevators when the elevators are interconnected.
Autopilot Pitch Trim
Automatic pitch trim is enabled whenever the autopilot is engaged. The autopilot
issues commands to the Horizontal Stabilizer Trim Control Unit (HSTCU) to remove
continuous loads from the elevator servomotor.
Protracted trim operation causes the trim clacker aural to sound. Autopilot pitch trim
failure is annunciated by an AP PITCH TRIM caution EICAS message.
Autopilot Mistrim Conditions
The AFCS continuously monitors both axes of the autopilot when it is engaged. Any
significant elevator or aileron mistrim condition causes an amber E (elevator) or A
(aileron) to be displayed on the upper left of the PFD. In conjunction with the PFD
annunciations, the EICAS will display an AP TRIM IS NU or AP TRIM IS ND
caution EICAS message (autopilot is counteracting a significant nose-up or nosedown
mistrim) for a significant elevator mistrim condition, or an AP TRIM IS LWD or
AP TRIM IS RWD caution EICAS message (indicating left or right wing down) for an
aileron mistrim.
When the autopilot is disengaged during a mistrim condition,
expect an abrupt change in control force.
NOTE
AUTOMATIC FLIGHT CONTROL SYSTEM
For Training Purposes Only
Sept 04
4-7
P I LOT T R A I N I N G GU I D E
Autopilot Elevator and Aileron Mistrim Annunciation
Figure 4-4
Autopilot monitors aileron mistrim conditions but cannot change
aileron trim settings
NOTE
7000
20000 1.0
10
10
MDA
A
A
HDG
A
DR ALT
A
AP
2500M 4
4
2
2
1
1
M.454
280
240
220
250
260
10
100
200
900
800
000
29.92 IN
P604_04_062
E
A
AUTOMATIC FLIGHT CONTROL SYSTEM
4-8 For Training Purposes Only
May 03
P I LOT T R A I N I N G GU I D E
Turbulence (TURB) Mode
Turbulence mode is available when the autopilot is engaged and can be selected by
pressing the TURB button on the FCP. The green status indicator lights on each side of
the TURB button illuminate when turbulence mode is selected. There is no indication
of TURB mode selection on the PFDs.
When turbulence mode is active, the FCC reduces autopilot gains for turbulent flight
conditions. This prevents the FCC from instantaneously responding to pitch and roll
changes brought about by flight through turbulent air.
TURB mode is cleared by any one of the following:
• pushing the TURB button again
• on-side LOC capture, or
• autopilot disengagement
Turbulence Mode Button
Figure 4-5
The maximum IAS or MACH for turbulent air penetration is 280
KIAS or 0.75 MACH.
NOTE
ALT
ALT CRS2
XFR FD
TURB AP DISC
　
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