Engine Vibration-Monitoring System; Thrust Reversers; General - BOMBARDIER Challenger 601-3A CL-600-2B16 Pilot Training Manual

ENGINE VIBRATION-
MONITORING SYSTEM

General

An engine vibration-monitoring system con-
tinuously monitors the vibration level of each
engine and provides cockpit indication of
these levels. A warning system alerts the crew
if predetermined levels are exceeded.
Components
A transducer mounted on the compressor cas-
ing of each engine generates an electrical sig-
nal proportional to the intensity of the engine
vibration. The generated signal is sent to the
cockpit indicator, for fan vibration only. If
fan vibration exceeds 2.7 mils DA for more
than 3 seconds, an amber FAN annunciator
will also come on, accompanied by an EN-
GINE master caution light. If core vibration
exceeds 1.7 mils DA for more than 3 seconds,
only the amber CORE annunciator will come
on plus an ENGINE master caution light but
no needle deflection occurs on the vibration
indicator (Figure 7-22).
Figure 7-22. Engine Vibration-Monitoring
Panel
The 3-second time delay eliminates nuisance
warnings due to high transient engine vibration.
Each engine has their own CORE and FAN an-
nunciator lights.
Test
The vibration indicating system can be tested
by pressing and holding in each of the CORE
and FAN indicator switchlights on the EVM
7-24 CL 601-3R
CL-600-2B16 PILOT TRAINING MANUAL
indicator panel; in turn, the pointer on the
side being tested will move to 4.0 mils 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.

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.
Forward movement of the translating sleeve
positions the blocker doors to lie flat and form
part of the fan airflow exit nozzle.
FOR TRAINING PURPOSES ONLY
FlightSafety Canada
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.
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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