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Emergency/Abnormal.................................................................................................. 10-12
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ILLUSTRATIONS
Figure Title Page
10-1 Citation Mustang Ice-Protection Systems.............................................................. 10-2
10-2 Ice-Protection Switches.......................................................................................... 10-3
10-3 Bleed Air/Pneumatic Ice-Protection Systems ........................................................ 10-4
10-4 Wing Stabilizer Automatic Deice Cycle ................................................................ 10-8
10-5 Windshield Anti-Ice/Defog Zones ......................................................................... 10-9
10-6 Windshield Anti-Ice Power Distribution ............................................................. 10-10
10-7 Windshield Anti-Ice Switches ............................................................................. 10-10
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CHAPTER 10
ICE AND RAIN PROTECTION
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GENERAL
Flight into known icing is the intentional flight
into icing conditions that are known to exist
by either visual observation or pilot weather
report information. Icing conditions exist any
time the indicated ram air temperature (RAT)
is +10°C or below, and visible moisture in
any form is present.
Engine anti-ice should be selected ON anytime
the indicated ram RAT is +10°C or below, and
visible moisture in any form is present.
WING/STAB DEICE should be selected as
soon as ice is observed to accrue anywhere on
the airplane. If ice remains on the airplane
during approach and landing, maximum flap
extension is limited to the TO/APR position.
Ice accumulations significantly alter the
shape of airfoils and increase the weight of
the airplane. Flight with ice accumulated on
INTRODUCTION
This chapter describes the ice and rain protection systems for the Citation Mustang. Antiicing
is provided for the engine inlets, instrument external sensors, and windshields.
Deicing is provided for the wings as well as the horizontal and vertical stabilizers. Rain
protection is also provided for the windshield.
the airplane will increase stall speeds and
alter the speeds for optimum performance.
Flight at high angle-of-attack (low airspeed)
can result in ice building on the underside of
the wings and the horizontal stabilizer aft of
areas protected by deice boots. 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.
The Mustang uses conventional methods of ice
protection. The engine inlets are anti-iced
using engine bleed air. The wing as well as the
horizontal and vertical stabilizer leading edges
are protected using pneumatic deice boots.
Electrical power protects the windshield, pitot
probes, static ports, stall warning vane, and engine
T2 probes. A passive rain repellent coating
on the windshield provides clear vision in
precipitation conditions. An overview of these
locations is in Figure 10-1.
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HORIZONTAL AND VERTICAL STABILIZER
DEICE SYSTEM (PNEUMATIC BOOTS)
ENGINE ANTI-ICE SYSTEM (BLEED AIR)
T2 PROBES (ELECTRIC HEAT)
WINDSHIELD ANTI-ICE
SYSTEM (ELECTRIC HEAT)
WING DEICE SYSTEM
(PNEUMATIC BOOTS)
　
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