BOMBARDIER Challenger 601-3A CL-600-2B16 Pilot Training Manual page 381

• The forward nose landing gear doors
hydraulically open, and the red NOSE
DOOR OPEN light illuminates.
• All three landing gear extend.
• All three landing gear downlocks me-
chanically engage.
• The green LEFT, NOSE, and RIGHT
landing gear position indicator lights
illuminate.
• The forward nose landing gear doors
hydraulically close, and the red NOSE
DOOR OPEN light extinguishes.
• The red landing gear handle lights cease
to flash.
• The selector valve remains energized,
maintaining hydraulic pressure in the
landing gear downlines.
Emergency Extension
If the landing gear control system malfunc-
tions, or if there is a loss of No. 3 hydraulic
system pressure, the landing gear can be man-
ually unlocked and allowed to free-fall. The
main landing gear is then locked in the down
position by No. 2 hydraulic system pressure.
Move the landing gear handle to the DN position
so that the red handle light will cease flashing
when the landing gear is locked down.
Pulling the LG PULL (landing gear manual re-
lease) handle (Figure 14-10) mechanically
unlocks the forward nose landing gear doors,
disengages all three landing gear uplocks, and
positions a dump valve to release fluid from
the landing gear actuators and the forward
nose landing gear door actuator.
A selector valve is automatically positioned
to direct No. 2 hydraulic system pressure to
the two main landing gear downlock assist
actuators. These actuators assure main land-
ing gear downlocking after gear free-fall. Nose
landing gear free-fall is aided by the airstream;
14-8 CL 601-3A/R
CL-600-2B16 PILOT TRAINING MANUAL
downlocking is assured by downlock assist
springs (see Figure 14-6). When the landing
gear is safely down, the three green lights will
illuminate. The nose doors remain open.
The system linkage is held in the emergency
operating position by a ratchet in the LG PULL
handle. To reset the system, press the button
on the handle and slowly return it to the stowed
position. This allows springs to reset the com-
ponents in the system.
NOSEWHEEL STEERING
GENERAL
The steer-by-wire nosewheel steering system
is powered by a hydraulically actuated rack and
pinion steering actuator mounted on the nose
landing gear strut. The system is operative
only when armed and on the ground, being
electrically disabled at lift-off. Steering is
available 55° either side of center with a con-
sole-mounted control wheel, or 7° either side
of center through rudder pedal deflection. Any
failure, or operation beyond 55°, deactivates
the system and illuminates a N/W STEER
FAIL light on the pilot's instrument panel.
With the N/W STEER switch in the OFF po-
sition, the nosewheels can be castered beyond
that range by differential braking or for tow-
ing. Even with the system disengaged, the
nosewheel steering actuator functions as a
shimmy damper.
The nosewheels are centered at lift-off by a
centering device in the nose landing gear strut.
OPERATION
With the N/W STEER switch in the ARMED
position, movement of the hand wheel on the
pilot's side console (Figure 14-11) positions
a potentiometer, which in turn provides steer-
ing signals to an electronic control unit. The
electronic control unit actuates a control valve
to direct No. 3 hydraulic system pressure to
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