BOMBARDIER Challenger 601-3A CL-600-2B16 Pilot Training Manual page 400

If the trim motor overspeeds, the amber OVSP
switchlight illuminates and system operation
ceases. Transfer to Channel 2 can be made by
pressing the OVSP–CHNG CHAN switchlight.
In the event of system failure from causes other
than motor overspeed, the amber CHAN 1
INOP switchlight illuminates and system op-
eration automatically transfers to Channel 2.
Trim inputs from the pilot override those made
by the copilot, the autopilot, and the MACH
TRIM system. Copilot inputs override the au-
topilot and the MACH TRIM system.
Autopilot inputs result in stabilizer trim move-
ment at the rate of from 0.1 ° to 0.5 ° per sec-
ond, depending on airspeed. With the autopilot
disengaged, MACH TRIM inputs result in a
trim rate of from 0.01° to 0.1 ° per second.
To disengage the system or to halt a trim run-
away, press the PITCH TRIM DISC button on
top of either pilot' s control wheel . This re-
moves electrical power from the system and
applies the brake on the actuator motor. To
reengage the system, press the CHAN 1
INOP–CHAN 2 INOP switchlight. If there is
n o m a l f u n c t i o n o n C h a n n e l 1 , p r e s s t h e
OVSP–CHNG CHAN switchlight.
LIFT MODULATION
SYSTEMS
GENERAL
The hydraulically powered flight spoilers, lo-
cated forward of the outboard flaps, are me-
chanically controlled by a lever on the center
pedestal. They can be extended in increments
up to 40°.
The ground spoilers, forward of the inboard
flaps, are hydraulically powered and operate
automatically if the system is armed and WOW
or wheel spinup occurs.
The slotted flaps, consisting of four panels, are
actuated by two electric motors driving flexible
15-10 CL 601-3A/R
CL-600-2B16 PILOT TRAINING MANUAL
shafts. Airflow is directed over the flaps by
fixed- and variable-position vanes.
FLIGHT SPOILERS
General
The flight spoiler on each wing is powered by
two PCU's; one by the No. 1 hydraulic system,
the other by the No. 2 hydraulic system.
The FLIGHT SPOILER lever on the center
pedestal is mechanically detented to be held
in any operating position, and is mechanically
gated from inadvertently exceeding the MAX
position.
Operation
To ex t e n d t h e f l i g h t s p o i l e r s , m ove t h e
FLIGHT SPOILER lever aft to the desired ex-
tend position (Figure 15-11). This mechani-
cally positions hydraulic selector valves to
direct No. 1 and No. 2 hydraulic systems pres-
sures to the PCU's at each spoiler. Both spoil-
ers extend to the selected position.
Spoiler movement out of the fully stowed po-
sition illuminates the amber LH FLT SPLR and
the RH FLT SPLR lights on the glareshield.
Spoiler position is constantly displayed on
the flight SURFACE position indicator.
Spoiler extension past the half-travel (20 °) re-
sults in automatic positioning of asymmetric
protection, as indicated by illumination of the
green LEFT and RIGHT lights on the spoiler
control panel. Illumination of the lights indi-
cates that a spoiler will retract only to the
half-travel point if both PCU's fail. In such an
event, the resultant roll tendency could be
overcome with the ailerons.
If the FLIGHT SPOILER lever is moved to the
MAX position for 40° extension, a mechani-
cal gate prevents further aft movement.
To retract the flight spoilers, move the FLIGHT
SPOILER lever forward to the desired posi-
tion. The spoilers retract to the selected po-
sition, as indicated by the flight SURFACE
FOR TRAINING PURPOSES ONLY
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