Thrust Reversers; General; Control - BOMBARDIER Challenger 601-3A CL-600-2B16 Pilot Training Manual

side being tested will move to 4.0 MILLS DA.
When the switchlight is held pressed for more
than 3 seconds, the respective amber CORE
and FAN lights will illuminate accompanied
by an engine M/C light.
NOTE
The test system does not test the en-
gine-mounted transducers or cable
circuitry. The indicator needle re-
sponse following engine starting in-
dicates proper operation of the system.
Figure 7-23. Engine Vibration-Monitoring
Panel (AC 5105
and Subsequent)

THRUST REVERSERS

GENERAL

The Canadair Challenger is equipped with
electrically energized, pneumatically oper-
ated thrust reversers to aid in deceleration on
the ground. The reversers are installed im-
mediately aft of the fan section.
The reversers are certificated for ground use
only, and the control circuits are wired through
the WOW system. The reverser consists of a
tracked translating sleeve that is moved aft by
an air motor driving a flexible shaft connected
to 4 ballscrew actuators. As the translating sleeve
moves aft, cascade vanes are exposed to redirect
the fan bypass airflow forward over the nose
cowl assembly. The aft motion of the translat-
ing sleeve also causes 10 blocker doors to block
the fan air exit nozzle and directs the airflow ra-
dially outward through the cascade vanes.
7-26 CL 601-3A
CL-600-2B16 PILOT TRAINING MANUAL
Forward movement of the translating sleeve
positions the blocker doors to lie flat and form
part of the fan airflow exit nozzle.

CONTROL

The thrust reversers are controlled by levers
(Figure 7-9) piggyback-mounted on the thrust
levers. The thrust reverser levers are latched
in the fully forward position. The latch must
be manually released by the pilot, allowing
each thrust reverser lever to be moved be-
tween three basic positions: stow (fully for-
ward), deploy (20° aft of full forward), and
reverse thrust which is a variable position.
Stow and deploy are fixed positions.
When the thrust reverser lever is unlatched,
then moved upward and aft, a solenoid is en-
gaged to prevent more than 20° of lever travel
while the air motor operates the ballscrew
jacks to drive the translating sleeve aft, ex-
posing the cascade vanes and closing the 10
blocker doors in the bypass duct. At this point,
a microswitch is operated to release the thrust
reverser lever lock solenoid. Further aft mo-
tion of the thrust reverser lever acts through
the FCU power lever to increase fuel flow and
provide proportionally more reverse thrust.
Figure 7-24 shows the CF34 engine in for-
ward thrust and reverse thrust configurations.
FOR TRAINING PURPOSES ONLY
FlightSafety Canada
NOTE
Only fan airflow is reversed. The re-
verser system does not affect the core
engine airflow which continues on its
normal path to the atmosphere.
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