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by temperature sensors which will activate the ENG A/I COLD L-R CAS messages should the engine
inlet temperature fall below safe operating levels. When the system is initially turned on, the ENG A/I
COLD L-R messages will appear in white to indicate the anti-ice system is warming up. Once the
inlet reaches an operating temperature of approximately +21ºC (+70ºF) the white messages will
extinguish. If either engine inlet fails to reach operating temperature after two minutes, the
appropriate white CAS message will turn amber and the MASTER CAUTION will illuminate. Once
the inlets have initially warmed up, if either inlet temperature falls below approximately +10°C
(+50°F), the appropriate amber ENG A/I COLD L-R will be displayed to alert the pilot that the
indicated inlet is below a safe temperature for anti-ice system function.
CAUTION
During sustained ground operations in freezing precipitation, if the engines are
operated at idle, ice may form on engine components. This may cause engine
vibration. By increasing the engine speed to approximately 70% N2 or higher,
the engine vibration will be eliminated.
(Continued Next Page)
510FM-07 AA 3-153
SECTION III - OPERATING PROCEDURES MODEL 510
NORMAL PROCEDURES
FAA APPROVED
U.S. Configuration
ANTI-ICE AND DEICE SYSTEMS (Continued)
WING, HORIZONTAL STABILIZER, VERTICAL TAIL DEICE SYSTEM
The wing, horizontal stabilizer, and vertical tail are deiced by pneumatic boots controlled by the
WING/STAB - OFF/AUTO/MANUAL switch. The wing boots are separated into upper and lower
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 in front of the
pilot but will not power any defog zones or anti-ice zones on the copilot windshield.
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)
3-154.1 AG 510FM-07
MODEL 510 SECTION III - OPERATING PROCEDURES
NORMAL PROCEDURES
FAA APPROVED
Configuration U.S.
ANTI-ICE AND DEICE SYSTEMS (Continued)
PITOT-STATIC / STALL WARNING ANTI-ICE
Electric heating elements are provided in the pilot’s and copilot’s pitot tubes, static ports, and the stall
warning probe. The pitot-static anti-ice switch actuates all of these elements. Operation may be
checked during preflight by turning the switch to the PITOT-STATIC position for approximately 30
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Citation Mustang airplane flight manual 1(105)
