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VNAV-plan speeds, the ATS tracks the PFD magenta speed cursor.
The following table is a summary of the ATS operating modes and displays.
AUTOMATIC FLIGHT CONTROL SYSTEM
Description
Vol. 2 04−10−59
Oct 05/06
CL−605 Flight Crew Operating Manual
PSP 605−6
AUTOTHROTTLE SYSTEM (CONT'D)
ATS Operating Modes and MSD Messages
ATS MODE THRUST/SPEED MODE MSD MESSAGE AFCS
TAKEOFF N 1 N1 TO TO
TAKEOFF (≥80 KIAS to
320 ft above takeoff
elevation)
SERVO COMMANDS
CEASE
N 1HOLD TO
CLIMB (except FLC) MACH or IAS SPEED ANY (except FLC)
CLIMB (FLC) N 1 N1 CLB FLC
CRUISE MACH or IAS SPEED Altitude
CRUISE (N2 SYNC) MACH SPEED N2 Altitude
DESCENT (except FLC) MACH or IAS SPEED ANY (except FLC)
DESCENT (FLC)
SERVO COMMANDS
CEASE
DESCENT FLC
MANEUVERING/
APPROACH
IAS SPEED ANY (except FLC)
LANDING (<50 FT RA)
THROTTLE LEVER
RETARD
RETARD DISENGAGED
GO-AROUND
(Certification pending)
N 1 N1 TO GA
ATS Operation
The following section provides a summary of autothrottle system operations during aircraft
power-up, and for all phases of flight.
ATS Tests
ATS Computer Self-Test
The ATS performs an automatic self-test when all sensors become valid following autothrottle
computer power-up. Prior to all sensors becoming valid and completion of the ATS self-test,
the ATS MSD displays an amber FAIL message.
AUTOMATIC FLIGHT CONTROL SYSTEM
Description
Vol. 2 04−10−60
Oct 05/06
CL−605 Flight Crew Operating Manual
PSP 605−6
AUTOTHROTTLE SYSTEM (CONT'D)
The computer’s satisfactory self-test function results in illumination of two green LEDs, located
on the ATS panel, and an MSD scrolling SELFTEST message is indicated. This test ensures
system integrity and logic to allow ATS engagement only if specific system requirements are
satisfied. At the completion of the self-test, the green LED annunciators will extinguish, and
both MSDs will blank. If the system detects a failure, the ATS FAIL message in the MSD is
annunciated.
NOTE
The LED displays in the MSDs and the ATS control panel can be
tested by selecting and holding the LAMP TEST switch in position 1
or 2. The ATS will also perform a system self-test and each MSD
returns to a blank display upon release of the LAMP TEST switch.
If the ATS is powered up with the IND LTS on DIM, cycle the
selector to BRT, then DIM, to establish intensity control after the
SELFTEST function has passed.
ATS Ground Test Function
ATS ground testing is accomplished by:
• Placing the throttles at the mid-travel position
• Selecting the LAMP TEST switch to position 1 or 2, and within 15 seconds
• Pressing and holding the ATS engage button.
The following events occur during the test:
• SERVOTEST message is displayed on the MSD for 7 seconds, and the MSD will blank;
• Throttle levers will retard to the FLIGHT IDLE position.
The ATS ground test that has been previously described is not represented on the illustration
that follows, because it is considered a ground maintenance test function. The test is carried
out to check the throttle levers to engine interface circuit.
AUTOMATIC FLIGHT CONTROL SYSTEM
Description
Vol. 2 04−10−61
Oct 05/06
CL−605 Flight Crew Operating Manual
PSP 605−6
AUTOTHROTTLE SYSTEM (CONT'D)
ATS Computer Testing
Figure 04−10−48
Autothrottle Mode of Operation
The flight guidance vertical mode is normally determined by the flight director or autopilot, and is
influenced by the FMS during vertical navigation control. The autothrottle mode of operation
results in autothrottle thrust control, which complements the pitch control being performed by the
flight guidance system.
The following graphic outlines the integrated functional control provided by the autothrottle for
the various control modes of the autopilot/flight director and FMS. The graphic represents
specific phases of a typical flight, and an explanation of each phase is detailed within the next
several pages.
AUTOMATIC FLIGHT CONTROL SYSTEM
Description
Vol. 2 04−10−62
Oct 05/06
CL−605 Flight Crew Operating Manual
PSP 605−6
AUTOTHROTTLE SYSTEM (CONT'D)
ATS Takeoff Mode
Figure 04−10−49
Takeoff
The takeoff thrust limit is selected in the FMS “THRUST LIMIT” page, and confirmed on the
EICAS in the form of N1 display.
At aircraft line-up, the pilot presses the TOGA switch and confirms that the N1 TO message is
　
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