Ice / Rain Flashcards
does the hawker have anti or deice
Anti-ice
if ice gets built up on the wings….
the anti-ice system cannot be turned on
ice detection
rotary cutter ice detector on left forward fuselage and ice detection
two position ice detection switch
AUTO - weight off wheels
OVRD - operates continuously
what is ice detection powered by
AC from XS2
when does ice detected switch go off
after 60 seconds of no ice detection
ice(/logo) detection light powered by
PS1
airframe anti-icing
TKS for horizontal stab and leading edges
how long does the TKS provide protection for
108 minutes
how much TKS protection at EMPTY
12 minutes
what temperature should the anti-ice not be run at
below -28C
ANTICE LO PRESS
low system pressure with pump on
ANTICE LO QTY
30 minutes of TKS remaining
windshield anti-iciing
heated electrically by engine driven alternators
ALT 1 powers
left windscreen, right sidescreen, left stall vane
ALT 2 powers
right windscreen, left sidescreen, right stall vane
If one alternator / engine fails… (windshield wise)
both forward windscreens are heated but widescreens are shed
PITOT/VANE HEAT switch
heats pitot heads / masts, static plates, rudder bias struts, AoA vanes
L/R PITOT/VANE switch
L/R selectable shows associated pitot heat amps
if on for one minute, how many amps indicate normal operation for L/R PITOT/VANE
5-10 amps
engine anti-ice
leading edge cowling heated by hot air from bleed air
In loss of power, engine anti-ice
will automatically open
speed limitation below ______ ft if windscreen becomes inoperative or turned off
257kts, 8000ft
engine anti-ice should not be used above ____ for any more than
50F / 10C
10 seconds
ICE DETECTD
ice is detected
turns off after 60 seconds of no ice
ICE PROT
look up ice protection annunciator
ICE PROT SELECTED
engine ice protection system is selected
are the upper and lower static ports heated
upper yes
lower no
ice warning powered by the _____
PE bus bar
if left pitot heat fails ___
air data computer 1 fails
if right pitot heat fails ____
air data computer 2
standby airspeed indicator
additional special order equipment
may fail
the engine anti-icing system is ____ powered from the ____ bus bar
Dc powered, PE bus bar
if the windshield limitations are not met, airspeed is restricted to
257 kts below 8000 ft
aircraft is cold soaked at -10
windscreen heat for 5 minutes before takeoff
aircraft cold soaked at -20
windscreen heat on for 15 minutes
the following components are anti-iced by the use of hot bleed air
A engine inlet cowlings
for takeoff or landing approach in icing conditions, the following switches must be turned on
ENG IGNITION
ENG ANTICE
WING/TAIL ANTICE
the following switches provide DC power to rudder bias heater muffs
PITOT/VANE HEAT
engine inlet cowling is heated by
hot bleed air
the ICE PROT annunciator on the MWS panel does not illuminate when
PITOT/VANE HEAT is on and operating normally
the following component may fail to operate satisfactorily when the least pitot heat is inoperative
ADC No 1
the ENG 1 or A/ICE annunciator indicates
That anti-icing air pressure is not available at sufficient pressure
the PITOT AMPS ammeter checks amps of
the left or right pitot heating elements
the forward static plates are heated
only when airborne
when engine anti-icing is required, the ENG ANTICE switches should be turned on
before takeoff power is set
the TKS fluid supply lasts for approximately
108 minutes
the airframe anti-icing system
should be primed before flight
the following ICE PROTECTION switches shall always be switched on before takeoff and remain on throughout the light
PITOT/VANE HEAT and SCREEN HEAT
with the ENG ANTICE switch energized and computer switch in AUTO, electrical power is supplied to heating elements on the
P2T2 sensor
When not in icing conditions, engine anti-icing must not be used for more than ______ in ambient air temperatures above 10C
10 seconds
Where is the TKS lid
under pilot seat
