BOMBARDIER Challenger 601-3A CL-600-2B16 Pilot Training Manual page 483

until test 98 L FLIGHT FAULT SUMMARY?
appears (B). To obtain the fault data, push the
RESET button, and data for the first flight
guidance computer appears (C).
The numerical codes should be copied for use
by maintenance personnel in troubleshooting
the problems. A second push of the RESET
button displays the fault data for the second
flight guidance computer, and stepping
through the above sequence displays the faults
for the FGC 2.
Upon completion of the flight fault summary
mode, return the DAFCS MAIN TEST switch
to the OFF position. Leaving the switch in the
ON position prevents autopilot engagement.
AFCS Operation
The basic philosophy of normal AFCS oper-
ation consists of one active FGC and one
standby FGC. The FGCs are always synchro-
nized and in the same modes. This allows the
standby FGC to automatically take over the au-
tomatic control functions if a fault is detected
within the active FGC (fail-operational).
Both FGCs receive sensor data from both the
pilot's and copilot's sensors. For flight guid-
ance computations, the FGC is coupled to the
left or right EHSI and DADC, indicated and
selected via the CPL pushbutton on the flight
guidance controller. The FGC uses the fol-
lowing data from the coupled side:
• DADC data from the coupled side
• Data displayed on the coupled side
EHSI, including navigation source,
heading error, selected course and course
error, and lateral and vertical deviations
The only exception is dual CPL, where both
EHSIs are coupled to the FGC. In dual CPL,
the ILS data are averaged by the autopilot.
Dual CPL is defined by:
CL-600-2B16 PILOT TRAINING MANUAL
At engagement, the system automatically se-
lects the pilot-side (L AFCS) and illuminates
the left arrow of the engaged function(s). If the
L AFCS is invalid at the instant of engagement,
the system automatically selects the R AFCS
and illuminates the right arrow of the engaged
function(s).
The AFCS consists of the following opera-
tions:
Automatic AFCS Reversion
Automatic FGC reversion occurs whenever a
fault is detected within one FGC; the FGC
failure is annunciated by a caution message on
the advisory display. If the failure occurs
within the active FGC, the cross-side or
standby FGC is automatically selected, and the
new active FGC is indicated on the flight guid-
ance controller pushbutton arrow.
FOR TRAINING PURPOSES ONLY
FlightSafety Canada
• NAV receivers tuned to LOC and valid
• APP selected and LOC /GS captured
NOTE
Engagement of the autopilot is in-
hibited via the WOW logic as long
as the aircraft is on the ground.
However, the yaw damper and Mach
trim engagement are not affected.
• Automatic AFCS reversion
• Autopilot disconnects
• Manual FD sensor data selection
• Invalid sensor data
• Annunciations
• Flight director command bars
• Flight director operation
• Navigation source control
L t é e
L t d .
CL 601-3A/R 16-71