Specifications

SECTION II
MODEL 560 AIRPLANE AND SYSTEMS
TAIL DEICE
The horizontal tail is deiced by pneumatic boots controlled by the tail deice AUTO/OFF MANUAL
switch. Selecting the switch to AUTO will activate a controller which will inflate the boots one side at a time
and then repeat this cycle after 3 minutes, continuously, providing automatic deice of the stablizer.
Selecting the momentary MANUAL position will inflate both boots 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.
NOTE
Allow the tail deice boot system to complete at least one complete cycle
(approximately 18 seconds) before turning off.
Proper activation of the deice boots is annunciated by a white TL DEICE PRESS L or R advisory light
on the annunciator panel which illuminates when proper inflation pressure is reached in each deice boot.
CAUTION
DO NOT OPERATE DEICE BOOTS UNDER ANY OF THE FOLLOWING
CONDITIONS BECAUSE BOOT CRACKING MAY RESULT:
f AIRSPEEDS AT OR ABOVE 150 KIAS AND THE RAT IS LESS THAN OR EQUAL
TO -35
o
C (-31
o
F).
f AIRSPEEDS BELOW 150 KIAS AND THE RAT IS LESS THAN OR EQUAL TO -
40
o
C (-40
o
F).
Failure of the deice boots to activate properly is annunciated by an amber TL DEICE FAIL L or R
advisory light on the annunciator panel which illuminates when tail deice pressure is not sequenced
correctly to either deice boot.
If the switch is placed in MANUAL during a cycle of automatic operation, MANUAL will override the
AUTO function and all the tubes will simultaneously inflate.
NOTE
Airflow perturbations during manual boot cycle or during AUTO boot cycle with
significant ice on the stabilizer may cause a minor pitch bump.
If icing conditions are anticipated after takeoff, operation of the tail deice system should be functionally
checked prior to takeoff. The pilot should also check the system for proper operation prior to entering
areas in which icing may be encountered.
WINDSHIELD ANTI-ICE
The windshield bleed air system provides windshield anti-ice under all normal operating conditions.
This system also provides external windshield defog and rain removal. The system supplies engine bleed
air through an electrically actuated pressure regulating shutoff valve in the tailcone of the airplane and
manually positioned valves which regulate air to each windshield. The manual valves are located at each
bleed air nozzle and are left in the OFF position for all normal operation. A check should be made to
ensure that the rain removal knob is pushed IN for windshield anti-icing. When windshield anti-icing is
required, the WINDSHIELD BLEED AIR Knobs are turned ON and the W/S BLEED Switch is turned to LO if
the indicated OAT is above -18°C or to HI if the indicated OAT is -18°C or below. Normal system
operation is indicated by an increase in air noise as the bleed air discharges from the nozzles. A
temperature sensor is located near the discharge nozzles and automatically controls the windshield bleed
air temperature by modulating crossflow air through a heat exchanger in the tailcone.
I 56OMB-01 Configuration AA 2-47