Specifications

SECTION II
AIRPLANE AND SYSTEMS
MODEL 560
Figure 2-23. Pilot’s Switch Panel with Anti-ice System Controls
An additional temperature sensor is located in the bleed air line, which automatically actuates the electrical
shutoff valve and illuminates the WS AIR O'HEAT annunciator light should the bleed air temperature exceed
the normal control value. This condition should not occur unless a sustained high power, low airspeed
condition is maintained or a system malfunction occurs. If the WS AIR O'HEAT light illuminates, the
WINDSHIELD BLEED AIR Knobs should be modulated to reduce the flow. If the light remains on for over
60 seconds, position the WINDSHIELD BLEED AIR Knobs to OFF. The WS AIR O'HEAT light will also
illuminate if the electrical shutoff valve in the tailcone opens with the W/S BLEED Switch in the OFF
position.
Self-test of the temperature monitor system is normally accomplished during the preflight warning
systems check by turning the windshield bleed air switch to either the HI or LO position and selecting the
W/S temperature position on the rotary test switch. Proper system function is verified by illumination of the
W/S AIR O'HEAT annunciator light. Self-tests may also be accomplished in flight, if desired.
If the windshield bleed air anti-ice system fails, a backup alcohol anti-ice system is provided for the left
windshield only. Sufficient alcohol is provided for ten minutes of operation; therefore, plans should be made
to leave the icing environment without delay.
Verification of proper operation of the windshield bleed anti-ice system may be accomplished prior to
flight with the engines running by turning the manual windshield bleed valves to MAX and selecting
windshield bleed to LOW. Presence of bleed flow can be determined by the air noise audible in the cockpit.
PITOT-STATIC AND ANGLE-OF-ATTACK ANTI-ICE
Electric heating elements are provided in the pilot's, copilot's and standby pitot tubes; pilot's, copilot’s,
and standby static ports, RAT probe, and the angle-of-attack probe. The pitot static anti-ice switch actuates
all of these elements. Operation may be checked on preflight by turning the switch ON for approximately
30 seconds, then OFF; then feel each element during the external inspection. Failures of pitot and static
heating elements and of the angle-of-attack probe element are annunciated by P/S HTR L or R, STBY P/S
HTR and AOA HTR FAIL lights, respectively, in the annunciator panel.
CAUTION
LIMIT GROUND OPERATION OF PITOT STATIC HEAT TO TWO MINUTES ON
WITH TWO MINUTES OFF BETWEEN CYCLES TO PRECLUDE SYSTEM DAMAGE.
ICE DETECTION AND WING INSPECTION LIGHTS
The ice detection and wing inspection lights are utilized at night or in conditions of poor visibility to
visually detect the presence of any ice accumulating on the lower center portion of the windshield and
wings. One ice detection light is located on each side of the windshield center post. These lights would
typically be used first to visually detect the presence of any ice accumulating on the windshield. The ice
detection lights come on when the battery switch is in the BATT position. If any ice is detected, the wing
inspection lights located on the fuselage sides may then be used to determine to what extent ice is
accumulating on the wings.
RAIN REMOVAL
This system utilizes the normal windshield bleed air anti-ice system for rain removal with augmenter
doors to provide increased airflow over each windshield in heavy rain. These doors are manually operated
by pulling the PULL RAIN handle located under the WINDSHIELD BLEED AIR knobs on the copilot's
subpanel. For rain removal, the manual windshield bleed air controls on the copilot's subpanel should be
turned to the MAX position, the PULL RAIN handle pulled out and the W/S BLEED switch positioned to
LOW. Augmenter door opening will be difficult should the W/S BLEED switch be turned on first. It may
also be difficult to open above 175 KIAS.
I 2-48 Configuration AA 56OMB-01