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The bleed-air manifolds (10th and 14th stages)
and their associated shutoff valves (SOV) are
located in the rear fuselage compartment. The
10th stage provides air to the air conditioners,
pressurization jet pump, and air turbine
starters. The 14th-stage bleed air is used for
cowl and wing anti-icing and to operate the
thrust reversers.
The APU compressor is capable of supplying air
to the 10th-stage bleed-air manifold when 10th-
stage engine bleed-air source is not selected.
An approved external air source can be used
to supply the 10th-stage bleed-air manifold
when engine and APU bleed-air supplies are
not available.
PNEUMATIC
SUBSYSTEMS
Six pneumatic subsystems require air for ei-
ther control or operation. These subsystems are:
1. Engine starting
2. Thrust reversers
3. Cowl anti-icing
4. Pressurization control jet pump
5. Air conditioning
6. Wing anti-icing
SUPPLY AND
DISTRIBUTION
The bleed-air supply and distribution is achieved
by a valving system consisting of electropneu-
matic valves. These valves require electrical
power and pneumatic pressure to operate.
All bleed SOV are spring-loaded closed except
the 14th stage bleed SOV which are spring-
loaded open. Cowl anti-ice SOV are fail safe
open if loss of electrical power occurs.
9-2 CL 601-3R
CL-600-2B16 PILOT TRAINING MANUAL
BLEED-AIR VALVES
(10TH STAGE)
The 10th-stage bleed-air manifold supply is
controlled by three identical valves called the
left engine and right engine bleed-air shutoff
valves and the isolation valve. The engine
bleed-air shutoff valves permit flow in both di-
rections and are primarily used to control
bleed-air extraction from their associated en-
gine. The isolation valve also provides two-
way flow, and its function is to divide the
bleed-air manifold into a left and a right sec-
tion. Therefore, the isolation valve is nor-
mally closed in flight.
CONTROL AND INDICATION
The engine bleed-air valves and the isolation
valve respond to both manual and automatic
control systems.
Manual Control
Manual control is achieved by switchlights
on the bleed-air panel (Figure 9-1) located at
the lower center of the overhead panel. The
switchlights are labeled "L," "R," and "ISOL."
Each engine bleed-air switchlight has a split
l eg e n d . T h e w h i t e u p p e r h a l f i s l a b e l e d
"BLEED CLOSED" and the red bottom half
is labeled "DUCT FAIL." The ISOL switch-
light has a single green OPEN legend. The
engine bleed-air switchlights receive power
from DC bus 1 and DC bus 2, respectively. The
ISOL switchlight receives power from the DC
ESS bus.
When an electrical power source and a pneu-
matic pressure source are available, pushing
the L or R bleed-air switchlight (Figure 9-1)
will electrically energize a solenoid on the
appropriate valve and pneumatic pressure will
open the valve. At the same time, the BLEED
CLOSED light will extinguish.
Pushing the ISOL switchlight when electrical
and pneumatic power are available will open the
valve, and the green OPEN legend will illuminate.
FOR TRAINING PURPOSES ONLY
FlightSafety Canada
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