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Glideslope capture can only occur after LOC capture, and is possible from above or below the
glideslope beam. Prior to GS capture, the FCCs operate in the current active vertical mode.
Upon GS capture, the previously active vertical mode clears automatically, and a green GS
annunciation is displayed in the vertical capture field of the FMA. The capture point is a function
of the closure rate, and the capture will always occur if the deviation is less than 10% of
full-scale deflection (under 0.2 dots).
Glideslope mode is cleared by:
• Selection of NAV mode;
• Loss of approach mode; or
• Loss of localizer (NAV SOURCE change or loss of signal).
Vertical Navigation
Pushing the VNAV button on the FCP alternately selects and clears vertical navigation mode.
VNAV is active when it is selected and valid. VNAV is valid when the following conditions are
met:
• An active flight plan with a TO waypoint exists in the FMS;
• The active navigation source is either a valid FMS or localizer; and
• Preselected altitude, barometric altitude, and airspeed or Mach are all valid.
AUTOMATIC FLIGHT CONTROL SYSTEM
Description
Vol. 2 04−10−43
Oct 05/06
CL−605 Flight Crew Operating Manual
PSP 605−6
FLIGHT DIRECTORS (CONT'D)
When VNAV is active, the letter “V” appears in front of the active/captured vertical mode
annunciation of the FMA. Other distinct VNAV modes may also be annunciated on the vertical
armed or active/captured fields of the FMA.
Selecting vertical navigation mode (VNAV) allows the FMS to provide vertical steering
commands to the flight director, to ensure the vertical flight profile of the active flight plan is
honored. With VNAV active, the FMS will automatically sequence the vertical flight modes, and
set target airspeeds and altitudes to follow the programmed flight profile. The flight crew may
also manually select other vertical modes (pitch, flight level change, vertical speed, altitude
hold), and modify airspeed/Mach references while VNAV is active. These actions will suspend
FMS control, but do not prevent subsequent mode activation by the FMS.
NOTE
The altitude preselector overrides any VNAV commands except FMS
glide path (GP) mode.
In the event the FMS vertical flight plan is not valid when VNAV is selected, a yellow VNAV
annunciation appears in the vertical armed field of the FMA.
VNAV mode is cleared by:
• Pushing the VNAV button;
• Capturing an ILS glideslope;
• Changing the NAV SOURCE on the coupled side; or
• Pushing the TOGA button.
For additional information on VNAV, refer to the Collins FMS–6000 Flight Management System
Pilot’s Guide.
Turbulence (TURB) Mode
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.
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.
TURB mode is cleared by any one of following:
• Pushing the TURB button again;
• On-side LOC capture; or
• Autopilot disengagement.
NOTE
The maximum IAS or MACH for turbulent air penetration is 280 KIAS or
0.75 MACH.
AUTOMATIC FLIGHT CONTROL SYSTEM
Description
Vol. 2 04−10−44
Oct 05/06
CL−605 Flight Crew Operating Manual
PSP 605−6
FLIGHT DIRECTORS (CONT'D)
Turbulence Mode Button
Figure 04−10−37
AUTOMATIC FLIGHT CONTROL SYSTEM
Description
Vol. 2 04−10−45
Oct 05/06
CL−605 Flight Crew Operating Manual
PSP 605−6
CONTROLS AND INDICATORS
General
The flight control panel (FCP) provides the majority of controls for flight director and autopilot
operation. The reversionary/inhibit panel allows selection between AFCS 1 and 2. Both the pilot’s
and copilot’s control wheel incorporates push-buttons for autopilot disconnect and flight director
synchronization.
The PFD flight mode annunciator (FMA) provides an indication of autopilot and flight director
status. The EICAS primary and status pages provide the system warning, caution and status
messages respectively.
Reversionary/Inhibit Panel
Reversionary/Inhibit Panel
Figure 04−10−38
AUTOMATIC FLIGHT CONTROL SYSTEM
Description
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