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AUTOTHROTTLE SYSTEM (CONT'D)
Description
The autothrottle system drives the throttle lever cables directly which, in turn, provides automatic
throttle lever input commands to the engines.
The ATS is comprised of the following:
• Computer;
• Dual servo-clutch pack assembly;
• Control panel, and the mode status display (MSD); and
• Disconnect switches (ATS DISC).
Components
ATS Computer
The ATS computer is located in the avionics bay, and receives inputs from various aircraft
systems, sensors and switches, and supplies power for ATS control and the servo drive
assembly. The ATS performs an automatic self-test when all the sensors become valid following
computer power-up.
The ATS computer only receives data inputs from the pilot’s side that includes FD 1, IRS 1,
ADC 1, etc. When the AFCS transfer (XFR) mode is selected, the flight control computers use
the copilot side data, and ATS operation is not available.
Autothrottle Computer
Figure 04−10−45
Dual Servo-Clutch/Servomotor
Each power lever assembly is linked to one servo-motor drive with a clutch assembly. This dual
assembly is installed in the main avionics bay area, attached below the cockpit center console,
and is mechanically interconnected with the throttle control cables.
The mechanical clutches, that are driven by each servo, provide identical feel to the pilot when
manually operating the throttle levers with the ATS engaged, disengaged, or when overriding
the ATS.
AUTOMATIC FLIGHT CONTROL SYSTEM
Description
Vol. 2 04−10−57
Oct 05/06
CL−605 Flight Crew Operating Manual
PSP 605−6
AUTOTHROTTLE SYSTEM (CONT'D)
When the ATS is driving the throttles, the pilot’s throttle levers move in the same manner as if
they were being positioned manually. The engine throttle levers react in unison with respect to
each other’s movement, and manual operation of any one throttle lever does not affect the
other.
The throttle lever friction mechanism is set at a predetermined fixed value for throttle lever
operations. Therefore, adjustment of the throttle lever friction is not required, and the throttle
levers do not experience any creep caused by vibration.
The throttle levers may be manually overridden when the ATS is engaged, and upon release the
ATS servos resume control of the throttle levers.
Dual Servo Clutch/Servomotor
Figure 04−10−46
ATS Control Panel
The ATS is controlled by a glareshield-mounted ATS control panel that incorporates a system
engage pushbutton (ATS), two green LED engaged annunciators, plus an N2 synchronization
pushbutton (N2 SYNC).
Whenever the ATS servos are engaged, the two green LED annunciators located immediately
left and right of the ATS pushbutton illuminate.
AUTOMATIC FLIGHT CONTROL SYSTEM
Description
Vol. 2 04−10−58
Oct 05/06
CL−605 Flight Crew Operating Manual
PSP 605−6
AUTOTHROTTLE SYSTEM (CONT'D)
ATS Mode Status Display
Two mode status display (MSD) units, located in the glareshield (pilot and copilot positions),
provide mode annunciation and caution messages for the ATS.
Each MSD incorporates a 2-line, 8-character LED alphanumeric display. The top line is green,
and displays ATS mode messages. The bottom line is amber, and displays ATS caution and
disengaged messages.
Lighting
The ATS control backlighting intensity is controlled by the center instrument panel lighting
dimmer control. The MSD intensity and the ATS control engaged annunciator intensity are
controlled by the IND LTS BRT/DIM intensity selector on the overhead panel. If the ATS is
powered up with the IND LTS switch in the DIM position, the ATS control green LED
annunciators and MSD remain in bright mode until the BRT/DIM switch is cycled.
ATS Control Panel
Figure 04−10−47
ATS Modes of Operation
There are two modes of operation for the ATS:
• N1 mode – The ATS computer develops a throttle drive command derived from the FMS N1
computation for takeoff, based on pilot input from the FMS.
• Speed mode – Controlled by using the SPEED knob on the FCC control panel.
The ATS is capable of controlling engine thrust from takeoff to touchdown, using the AFCS vertical
modes and VNAV-plan speeds. The system uses the FMS thrust management table-based N1
limit and target calculations, displayed on the EICAS N1 fan speed displays. ATS thrust or speed
mode selections are automatic, based on the AFCS mode logic. The AFCS airspeed reference
(speed bug) is used to select ATS speed targets, displayed on the primary flight display (PFD). In
　
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