Engine Power Control - BOMBARDIER Challenger 601-3A CL-600-2B16 Pilot Training Manual

Control
The automatic ignition system is controlled by
the stall protection computer using inputs
from the angle-of-attack vanes. The stall pro-
tection computer will initiate ignition A and
ignition B for both engines 3% before the
onset of the stick shaker and maintain ignition
operation until the angle of attack is reduced.
Indication
When the stall protection ignition is operat-
ing or during a stall protection system test, the
white IGN A ON and IGN B ON (Figure 7-8)
lights will be illuminated.
Power Sources
AC power at 115 volts and 400 Hertz is used for
the ignition system. Left and right engine igni-
tion A is supplied from the essential AC bus.
Left and right engine ignition B is supplied
from the battery bus through a static inverter.
Operation
Figure 7-10 is simplified schematic of the ig-
nition system used on the Canadair Challenger.
The switchlights on the ignition and start con-
trol panel provide for ignition arming and se-
lection of the ground start ignition mode, the
continuous ignition mode, and the in-flight
start ignition mode.
The stall protection system provides ignition
of the duration of stall warning regardless of
the position of all other ignition switches.

ENGINE POWER CONTROL

General
Engine power control is provided on a quad-
rant located on the center pedestal.
CL-600-2B16 PILOT TRAINING MANUAL
Thrust Levers
The individual engine thrust levers (Figure 7-
9) operate in quadrant slots from a full aft po-
sition labeled "SHUT OFF" to a full forward
position labeled "MAX POWER." An inter-
mediate position forward of SHUT OFF is la-
beled "IDLE."
A mechanical latch at the rear and below each
thrust lever knob must be raised before the
thrust lever can be moved to or from the SHUT
OFF position.
A go-around button is mounted in each thrust
lever knob. When either is pushed, it will dis-
engage the autopilot and place the AFCS sys-
tem in the go-around mode. Switches are
mounted in the throttle quadrant slots to provide
(1) takeoff configuration warning for flaps,
spoilers, and horizontal stabilizer, (2) pressur-
ization ground control mode, and (3) landing
configuration warning (landing gear not down
and locked at landing power settings).
Quadrant Friction Control
A single friction adjustment twist knob (Figure
7-9) is located on the quadrant aft of and between
FOR TRAINING PURPOSES ONLY
FlightSafety Canada
Figure 7-9. Throttle Quadrant
L t ée
L t d.
CL 601-3A 7-13