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PITOT-STATIC
SENSORS (ELECTRIC HEAT)
WING DEICE SYSTEM
(PNEUMATIC BOOTS)
STALL WARNING TRANSDUCER
(ELECTRIC HEAT)
PITOT-STATIC
SENSORS (ELECTRIC HEAT)
Figure 10-1. Citation Mustang Ice-Protection Systems
Each engine has two bleed-air ports: one inboard
and one outboard. The inboard port
provides bleed air for interior air conditioning
and pressurization. The outboard port provides
bleed air for engine inlet anti-ice and for
inflating the deice boots. During single-engine
operation, check valves in the supply lines
from each engine prevent bleed air from one
engine back-flowing to the opposite engine.
The ice protection system is controlled by
green-capped switches on the pilot tilt panel,
which is to the left of the LANDING GEAR
handle (Figure 10-2). The status of ice protection
systems is displayed by messages on
the crew alerting system (CAS).
ENGINE INLETS
DESCRIPTION
Each engine inlet and the inlet of the generator-
cooling scoop is heated by regulated engine
bleed air. Temperature of the bleed air is directly
related to throttle position. Spent bleed
air exits via a vent in the bottom of the inlet.
This vent is inspected during preflight.
NOTE
There is no crossfeed between engines
for inlet heating. If an engine
fails, its inlet is no longer heated.
DC power is provided through an L or R A/I
circuit breaker on its respective side ELE #2
bus. If DC power fails, the engine anti-ice
valves automatically open, allowing hot air
into the nacelle leading edges.
COMPONENTS
Engine Anti-Ice Shutoff Valves
The hot bleed air flows into each engine inlet
through the engine anti-ice pressure-regulating
shutoff valve (PRSOV) (Figure 10-3).
When the valve energizes closed, the inlet is
not anti-iced. The engine inlet PRSOVs are operated
by the ENGINE ANTI-ICE switches
and are electrically actuated.
In the absence of electrical power, the valves
are pushed open by bleed-air pressure. When
electrical power is applied, a solenoid powers
the PRSOV closed. The PRSOVs control the
air pressure downstream of the valve. These
valves regulate the airflow of the engine antiice
system.
Engine Inlet Anti-Ice
Undertemperature Switches
The engine inlet undertemperature switches
are inside the nacelle leading edge. These
switches provide information through the
monitoring circuits in the left and right ice protection
system printed circuit boards (PCBs)
to drive the white and amber ENG A/I COLD
L or R messages.
Engine Inlet Anti-Ice Assembly
The engine inlet leading edge is hollow.
Inside the leading edge, a circular piccolo
tube is immediately behind the forward surface
of the inlet. The hot bleed air enters the
piccolo tube, sprays out of holes in the tube
CITATION MUSTANG OPERATING MANUAL
510OM-00 10-3
Figure 10-2. Ice-Protection Switches
CITATION MUSTANG OPERATING MANUAL
10-4 510OM-00
ENGINE ANTI-ICE
PRSOV
EFCV
EFCV
HP
HP
HP
HP
EFCV
EFCV
VERTICAL STAB DEICE BOOT
HORIZONTAL STAB DEICE BOOT
WING DEICE BOOT LOWER CHAMBER
WING DEICE BOOT UPPER CHAMBER
WING DEICE BOOT LOWER CHAMBER
WING DEICE BOOT UPPER CHAMBER
HORIZONTAL STAB DEICE BOOT
P
P
P
P
P
P
T
T
SERVICE AIR
REGULATOR
FAN COMPRESSOR
FAN COMPRESSOR
TO ECS
SYSTEM
ENGINE INLET
UNDERTEMP
SWITCH
TO ECS
SYSTEM
SERVICE
AIR CHECK
VALVES
VENTED
OVERBOARD
VENTED
OVERBOARD
DEICE BOOT
PRESSURE SWITCHES
ENGINE ANTI-ICE
PRSOV
ENGINE INLET
UNDERTEMP
SWITCH
VENTED
OVERBOARD
VENTED
OVERBOARD LEGEND
HOT HP ENGINE BLEED AIR
REGULATED SERVICE AIR
1ST CYCLE VACUUM
2ND CYCLE VACUUM
VENTED AIR
ENG A/I COLD L-R
T2 HTR FAIL
WING DE-ICE FAIL
TAIL DE-ICE FAIL
ENG A/I COLD L-R
SURFACE DE-ICE
Figure 10-3. Bleed Air/Pneumatic Ice-Protection Systems
CITATION MUSTANG OPERATING MANUAL
510OM-00 10-5
to circulate through the inlet leading edge,
then exhausts overboard through a vent in the
bottom of each inlet assembly.
CONTROLS AND INDICATIONS
Controls for the engine anti-ice system are
on the pilot tilt panel with the other ICE
PROTECTION controls (see Figure 10-2).
L and R ENGINE ANTI-ICE
Switches
The L and R ENGINE ANTI-ICE switches control
the flow of anti-icing bleed air to the engine
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Cessna塞斯纳公务机飞行手册(52)
