Citation Encore 560 - Anti-Ice;Deice Systems

SECTION II
MODEL 560 AIRPLANE AND SYSTEMS
ANTI-ICE/DEICE SYSTEMS
The anti-ice systems consist of bleed air heated engine inlets, wing leading edges, fan spinner and
stators, and electrically heated pitot tubes, static ports and angle-of-attack probe. The horizontal stabilizer
is deiced by pneumatic boots. Windshield anti-ice is provided by bleed air with alcohol backup.
All anti-ice systems should be turned on when operating in visible moisture and the indicated RAT is
+10°C (+50°F) or below.
CAUTION
f IF ANTI-ICE SYSTEMS ARE TO BE USED FOR TAKEOFF AND GROUND
AMBIENT TEMPERATURE IS BETWEEN 0°C (+32°F) AND +10°C (+50°F),
CLOSE THE R WINDSHIELD BLEED AIR MANUAL VALVE FOR TAKEOFF. THIS
WILL ENSURE ADEQUATE BLEED AIR TEMPERATURE REGULATION TO THE
PYLON PRE-COOLERS. AFTER THE THROTTLES HAVE BEEN REDUCED TO
CLIMB POWER, THE R WINDSHIELD BLEED AIR MANUAL VALVE MAY BE
OPENED AS DESIRED.
f ANY TIME ICE ACCUMULATION IS OBSERVED ON EITHER THE WINDSHIELD,
WING FENCES, OR WING LIGHT SHIELDS (NEAR WING TIP), THE FLIGHT
CREW MUST VISUALLY INSPECT BOTH WING LEADING EDGES AT A TIME
INTERVAL OF NO LESS THAN 5 MINUTES.
f IF ICE ACCUMULATION IS DETECTED ON THE HEATED PORTION OF THE
WING LEADING EDGE, THE ABNORMAL PROCEDURES FOR WING ANTI-ICE
FAILURE MUST BE OBSERVED.
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                                                                                                                            
Figure 2-21 Airplane Anti-ice/Deice Systems
I 56OMB-01 Configuration AA 2-45