Table of Contents
Advertisement
3. External system
4. Emergency system
Primary AC system power normally supplies
all the airplane electrical needs in flight. Each
engine drives an integrated drive generator
(IDG) which supplies 3-phase, 115-/200-volt,
400-Hz AC power, rated at 30 kva.
Auxiliary AC system power is supplied by an
APU whose output has the same rating as ei-
ther IDG. It is used to supply all electrical re-
quirements on the ground and can be used as
an emergency supply in the air.
External AC system power is received through
a receptacle located on the right-hand nose
section of the fuselage. If either main gen-
erator or the APU generator is brought on
line, external power automatically reverts to
standby status.
Emergency AC system power is supplied by
an air-driven generator which can be deployed
manually or automatically when both main
generators fail or are not available in flight.
Once deployed, it cannot be restowed until
after the airplane lands.
DC System
DC power can be supplied from two sources,
static conversion and the battery. On the
ground, DC power can also be supplied through
an external power receptacle on the right rear
of the fuselage. In normal operation, primary
DC power is derived from the AC system
through the use of four transformer-rectifier
units (TRU's). The battery system provides
power to start the APU and to supply DC power
when all other sources of DC power have failed
or are not available. It also supplements the
available DC power supply when the ADG is
the only source of airplane power.
LIGHTING
The lighting system, controlled from the cock-
pit, provides illumination both externally and in-
ternally throughout the airplane. The exterior
CL-600-2B16 PILOT TRAINING MANUAL
lighting includes four landing lights and two
taxi/recognition lights; two rotating red bea-
cons; standard red, green , and white navigation
lights; wing-ice inspection lights; and anticol-
lision/strobe lights. The interior lighting in-
cludes boarding and dome lights to illuminate
the passenger door area, service compartment
lights, and flight compartment lighting.
In addition, the airplane is equipped with an
emergency lighting system which illuminates
the right wing and passenger door area for
emergency evacuation.
WARNING SYSTEMS
Warning systems provide the flight crew with
18 visual indications of systems malfunctions
through the master caution system and draw
attention to 8 significant events through the
aural warning system.
The Annunciator Section in this manual dis-
plays all light indicators, and page ANN-1
should be folded out and referred to while
studying this manual.
FUEL SYSTEM
The Challenger uses a wet-wing box struc-
ture which forms two main tanks in the out-
board wing sections and an auxiliary tank in
the wing center section. Maximum fuel ca-
pacity is approximately 17,900 pounds with
a tail tank.
Ejector pumps are used to ensure the delivery
of fuel to the collector tanks and to supply it
to the engines. Electric standby fuel pumps op-
erate automatically during engine starting and
in the event of main ejector pump failure.
A cross flow valve may be opened to allow
gravity flow to correct a fuel imbalance be-
tween the main tanks.
Fueling may be accomplished by gravity feed
but it is normally done through a single-point
pressure refueling connection located in the
right wing root.
FOR TRAINING PURPOSES ONLY
FlightSafety Canada
CL 601-3A/R 1-15
L t é e
L t d.
Advertisement
Chapters
Table of Contents
