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segments that inflate independently. The lower wing and left horizontal stabilizer boots inflate
simultaneously as do the upper wing, right horizontal stabilizer, and vertical tail boots. Selecting the
switch to AUTO activates a controller which will inflate the boots one set at a time and then repeat
this cycle after 2 minutes, continuously, providing automatic deice of all protected surfaces. Selecting
the momentary MANUAL position will inflate all boots simultaneously as long as the pilot holds the
switch in the MANUAL position. Vacuum is supplied to deflate the boots after each cycle and keep
them deflated between cycles and when OFF.
Proper activation of the deice boots is indicated by a white SURFACE DEICE message which
displays when proper inflation pressure is reached in each deice boot.
CAUTION
The Deice Boots should not be activated at indicated RAT below -30°C
(-22°F). Boot cracking may result.
WINDSHIELD ANTI-ICE
The DC powered windshield anti-ice system provides windshield anti-ice and defog under all normal
operating conditions. Each windshield is heated by a wire filament heating grid embedded within the
windshield assembly. Each windshield incorporates two anti-ice zones located in front of the
respective pilot station, and a single defog zone on the outboard and upper portions of each
windshield.
DC electrical power from each starter/generator is provided to the windshield wire filament heaters
through a pair of windshield anti-ice controllers. The LH starter/generator provides power to the LH
anti-ice controller and the RH starter/generator provides power to the RH anti-ice controller. Each
anti-ice controller then provides power to one anti-ice zone on each windshield and to its respective
LH/RH defog zone. In the event of a single generator failure, the windshield anti-ice controller and
associated anti-ice/deice zones on the failed generator side will be inoperative. The windshield antiice
controller on the operating generator side will continue to power one anti-ice zone on each
windshield but will not power any defog zones.
Self-test of the windshield anti-ice system is accomplished upon selection of the L and R
WINDSHIELD ANTI-ICE switches. The windshield anti-ice controllers perform a built-in test upon
power-up. During the BIT test the CAS messages W/S A/I FAIL L-R and W/S O’HEAT L-R will
appear in white. The messages will extinguish upon successful completion of the BIT test. If either
controller is not functioning normally, the appropriate message will turn amber and post a Master
Caution.
(Continued Next Page)
3-154 AF 510FM-07
MODEL 510 SECTION III - OPERATING PROCEDURES
NORMAL PROCEDURES
FAA APPROVED
Configuration U.S.
ANTI-ICE AND DEICE SYSTEMS
The wing, horizontal stabilizer, and vertical tail are deiced by pneumatic boots. The anti-ice system
consists of electrically heated pitot tubes, static ports, stall warning probe, and windshield and bleed
air heated engine inlets.
The engine and windshield anti-ice systems should be turned on when operating in visible moisture
and the indicated RAT is +10°C (+50°F) or below. The WING/STAB deice system should be turned
on at the first indication of ice accumulation on any part of the airplane. Selecting WING/STAB
DEICE turns on the wing, horizontal stabilizer, and vertical tail deice boots as well as shifting the stall
warning system to account for higher stall speeds with ice on the airplane. When operating on the
shifted stall warning schedule, the STALL WARN HI CAS message will be displayed and the
appropriate STALL WARNING-HIGH performance tables must be used. If the airplane can later be
visually confirmed to be clear of ice, the stall warning system may be reset to the normal schedule by
momentarily selecting RESET STALL WARN on the PITOT-STATIC switch. When the STALL WARN
HI message is not posted, the STALL WARNING-NORMAL performance tables should be used.
CAUTION
The Deice Boots should not be activated at indicated RAT below -30°C
(-22°F). Boot cracking may result.
NOTE
The windshield anti-ice system may be operated at any temperature to assist in the
prevention or removal of fog or frost on the windshield.
ENGINE ANTI-ICE SYSTEM
When the ENGINE ANTI-ICE switches are turned on, hot bleed air flows through the respective
engine inlet providing anti-ice protection to the engine inlet and generator cooling air inlet. The
engine fan, stators and spinner are aerodynamically deiced. Ice will build on the spinner, engine fan,
and stators, and shed due to centrifugal and aerodynamic forces. Minor acoustical vibrations may be
evident at some power settings as this ice builds and sheds. The engine anti-ice system is monitored
　
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本文鏈接地址：Citation Mustang airplane flight manual 1(104)