曝光台 注意防骗
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Minimum sustained airspeed for flight in icing conditions (except approach and landing) is 160 KIAS.
Prolonged flight with the flaps and/or landing gear extended is not permitted except as required for
approach and landing. Use of Flaps LAND (30°) is prohibited when any ice is observed adhering to
the outside of the airplane. Trace or light amounts of icing on the horizontal stabilizer can significantly
alter airfoil characteristics which will affect stability and control of the airplane.
NOTE
With residual ice on the airplane, stall characteristics are degraded and stall speeds
are increased.
Freezing rain and clear ice will be deposited in layers over the entire surface of the airplane and can
“run back” over control surfaces before freezing. Rime ice is an opaque, granular, and rough deposit
of ice that usually forms on the leading edges of wings, tail surfaces, pylons, engine inlets, and
antennas, etc. Flight crews are to make sure that the airplane is free from ice prior to dispatch.
3-152 AA 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
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
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Citation Mustang airplane flight manual 1(103)
