2 minutes. The distributor panels must then
be checked for fluid flow. If it does not, re-
select the time switch for brief periods until
flow occurs. Refill the tank as necessary
after priming.
The WING/TAIL ANTICE switch controls
an electrically operated pump for up to 10
minutes. Each time it is energized, the first
minute of operation is at a high flow rate, after
which the system reverts to normal flow.
When the selected time expires, a warning
chime is given via the audio system as the time
switch returns to zero and deenergizes the
pump. When this pump is operating, it feeds
fluid from the tank to a filter and check valve.
The valve, open during system operation,
closes when the pump is inoperative and pre-
vents undesired delivery of fluid by cabin
pressure. The airframe deice pump and chime
are powered from bus bar PS2.
Fluid flows from the filter to distributor pan-
els via a compensating valve. This valve cor-
r e c t s s y s t e m p r e s s u r e l e v e l s f o r h e a d
variation between the wings and stabilizers.
The fluid is supplied to each distribution
panel via a proportional unit, which supplies
the correct fluid flow to each panel cavity.
From the cavity, fluid passes through a porous
plastic sheet and a porous stainless steel
outer skin to the atmosphere, where airflow
spreads it rearward over the airfoil.
NOTE
At very low temperatures of –28°C
or less, ice crystals can exist in the
atmosphere, but do not present a
hazard. If the airframe ice protec-
tion system is used at these low
temperatures, the water/alcohol
content of the fluid will evaporate,
leaving solidified glycol which, to-
gether with the impinging ice crys-
tals, can give the appearance of ice.
Use of the airframe ice protection
system, under these conditions, is
not advisable. Therefore, operation
of the WING/TAIL ANTICE time
switch should be limited to the
priming procedures, and additional
use in flight only when weather
conditions warrant.
The aircraft must be clear of snow,
ice and frost before takeoff with the
exception of the following areas:
• Frost is allowable on the under-
side of the wings over the general
area of the fuel tanks provided
that the depth does not exceed
0.125 inch. If frost is present in
this region, the WAT limited take-
off weight must be reduced by
1,000 pounds. The net flight path
reference and fourth segment
climb gradients must be obtained
using a weight 1,000 pounds
higher than the actual weight.
• Frost is allowable on the fuse-
lage provided the layer is thin
enough to distinguish the sur-
face features such as paint lines
or markings underneath; but, all
vents, probes and ports must be
clear of frost.
WARNING ANNUNCIATORS
With the TKS pump running, system low pres-
sure is indicated by the illumination of the
amber ANTICE LO PRESS annunciator on
the roof panel and the amber ICE PROT
↑
re-
p e a t e r a n n u n c i a t o r o n t h e M W S p a n e l
(Annunciators Chapter).
Fluid low quantity is indicated by illumina-
tion of the amber ANTICE LO QTY annun-
ciator on the roof panel and the amber ICE
PROT
↑
repeater annunciator on the MWS
panel. The ANTICE LO QTY annunciator il-
luminates when there is 30 minutes of TKS
WARNING
10-6
FOR TRAINING PURPOSES ONLY
HAWKER 800 XP
PILOT TRAINING MANUAL
FlightSafety
international
Summary of Contents for 800 XP
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