Page 1: Title Page - Ice and Rain Protection Introduction
Page 2: Ice and Rain Introduction
This module introduces the Ice and Rain Protection Systems of the A320.
These systems allow the aircraft to operate in icing and heavy rain conditions.
Additional training on Ground De-ice Procedures and Preflight Inspections are provided
in another module.
Page 3: Protected Areas
Ice Protection is provided by hot bleed air for the wings and engine inlets, while electric
conductive heating is provided for the Probes, Window Heat, and for heating of the waste
water drain masts.
Rain Protection is provided by Windshield Wipers and Rain Repellent.
Page 4: Controls and Indicators
The controls for the Anti-ice system are located on the forward portion of the Overhead
Panel.
Indications consist of pushbutton lights, memos on the E/WD, and displays on the ECAM
Bleed page.
We will now introduce each subsystem of the Anti-ice and Rain Protection system.
Page 5: Wing Anti-ice
The Wing Anti-ice is provided to the three most outboard slats (3-4-5) of each wing by
hot air from the pneumatic system. There is one Wing Anti-ice valve in each wing that
controls the delivery of hot air to the slats. Wing Anti-ice is controlled by a single
ON/OFF pushbutton. Wing Anti-ice operates in flight, although the flight crew can
operate the system for 30 seconds on the ground to test the system. With loss of normal
electrical power the Wing Anti-ice valves fail to the closed position.
Page 6: Engine Anti-ice
The Engine Anti-ice is provided to the engine nacelle by hot air from the bleed of the
respective engine.
There is one ON / OFF pushbutton to control the Anti-ice on each engine.
Engine Anti-ice is operable in flight or on the ground.
With loss of normal electrical power, the Engine Anti-ice valves fail to the open position
regardless of the pushbutton position.
Page 7: Probe and Window Heat
Probe, Windshield, and Window Heat is provided by electric elements and controlled by
one pushbutton on the Overhead Panel.
It can be selected to AUTO or ON.
Notice the electrically heated items shown on this frame.
Page 8: Waste Water Drain Masts
The Waste Water Drain Masts are not controlled by a switch but are heated whenever the
aircraft is electrically powered.
Page 9: Rain Protection Introduction
Windshield Wiper controls are provided for each pilot. In addition to the operation of the
windshield wipers, the rain repellent can be dispensed to provide a cleaning effect on the
windshields during moderate to heavy rain; it should not be used to wash a dry
windshield. This completes the introduction to Ice and Rain Protection for the A320.
Now to answer some questions...
Page 1: Title Page - Ice and Rain Protection Controls Indicators
Page 2: Controls and Indicators
The Wing Anti-ice System is used in flight when icing conditions exist. It is controlled by
a single pb on the ANTI ICE overhead panel.
Page 3: Prevents and Removes Ice
Wing Anti-ice can be used to prevent ice formation, or to remove ice accumulation from
the wing leading edges. Extended flight in icing conditions with slats extended should be
avoided.
Page 4: Wing Anti-ice
The Wing Anti-ice valve in each wing is electrically controlled and pneumatically
operated. Pneumatic air is provided to each Wing Anti-ice valve by the respective side of
the pneumatic system. When the WING pb is selected ON, the valves are signaled to
open. If pneumatic pressure is available, the valves will open to provide hot air to the
three outboard slats (3-4-5) of each wing.
Page 5: Wing Anti-ice
If the WING pb is selected ON when the aircraft is on the ground, a timer allows the
system to operate for 30 seconds, after which the wing anti-ice valves will close. This
feature allows the crew to test the system when the aircraft is on the ground.
Page 6: Wing Anti-ice Valves Fail Closed
If the WING pb is selected ON when the aircraft is inflight, the system will operate until
the crew selects the pb to OFF. Selection of OFF causes both Wing Anti-ice valves to
close.
Note: with loss of normal electrical power, both Wing Anti-ice valves fail to the closed
position.
Page 7: Wing Anti-ice ECAM Display
When the WING pb is selected ON, the blue ON light in the pb illuminates and a green
WING A. ICE memo displays on the E/WD. Additionally the Wing Anti-ice operation is
displayed graphically on the ECAM BLEED page. When the WING pb is selected OFF,
the ON light goes off and the WING A. ICE memo blanks. The amber FAULT light
illuminates briefly when the valves are in transit. This is a normal display condition. You
can click the labeled hotwords and the pb to view system operation and displays.
Page 8: Amber FAULT Light
The amber FAULT light illuminates in the pb and an ECAM caution appears if one or
both valves are not in the selected position or the available pneumatic pressure is too low.
Page 9: Wing Anti-ice - N1 Limit
When Wing Anti-Ice is selected on, the N1 RPM limit is automatically reduced and the
idle RPM is automatically increased. Therefore, selection of Wing Anti-ice on during
climb will reduce the available thrust, and selection of Wing Anti-ice during descent may
extend your descent profile.
Page 10: Engine Anti-ice
Engine Anti-ice is used on the ground or inflight when icing conditions exist. Pilots
should not wait for ice build up but should select the system on before or as soon as the
temperature and visible moisture meet the specified criteria, especially if the aircraft is
"cold-soaked".
Page 11: Engine A/I Controls
Engine Anti-ice is controlled for each engine by a pb on the overhead ANTI ICE panel.
Pneumatic air is directly supplied from the respective engine's high pressure bleed
manifold.
Page 12: Engine Anti-ice pbs
When the ENG 1(2) pb is selected to ON, the engine anti-ice valve is signaled to open
and high pressure bleed air is delivered to the engine nacelle area.
Page 13: Engine Anti-ice pbs
When a ENG 1(2) pb is selected ON, the ON light in the pb illuminates blue and the
green memo ENG A. ICE displays on the E/WD. The memo displays if one or both
Engine Anti-ice pbs are on. When the Engine Anti-ice pb is selected OFF, the ON light
goes off and the MEMO blanks.
Page 14: Engine Anti-ice pbs
With Engine Anti-ice selected ON and operating, Continuous Ignition is automatically
provided.
Page 15: Engine A/I Valve Pressure
If ENG 1(2) is selected ON after engine start, there may not be adequate pressure to open
the anti-ice valve on an engine. If a valve does not open as expected, Follow the
ECAM/QRH Procedure, as a reference, the procedure will request a slight run-up to
provide additional pressure for valve operation. As soon as the valve opens, retard thrust
to idle.
Page 16: Engine Anti-ice FAULT Light
The amber FAULT light illuminates in the pb and an ECAM caution appears if the
position of a valve disagrees with the respective ENG 1 (2) pb selection. The amber
FAULT light illuminates briefly when the valves are in transit. This is a normal display
condition.
Page 17: Engine A/I Valves Fail Closed
An Engine Anti-ice valve fails to the closed position if there is no engine bleed air
pressure. On the other hand, if normal electrical power is lost and bleed air is available,
the engine Anti-ice valve fails to the open position.
Page 18: Engine Anti-ice - N1 Limit
When the Engine Anti-ice is selected ON, selected on, the N1 RPM Limit is
automatically reduced and the idle RPM is automatically increased to provide the
required air pressure for operation of Engine Anti-ice.
Therefore, selection of Engine Anti-ice during climb will reduce the available thrust, and
selection of Engine Anti-ice during descent may extend your descent profile.
Page 19: Window Heat
Window Heat is used for all flight operations, regardless of weather conditions. The
aircraft uses electrical heating for anti-icing each windshield and demisting the cockpit
side windows. Two independent Window Heat Computers (WHCs), one on each side,
automatically regulate the system, protect it against overheating, and indicate faults.
Page 20: Normal and Low Heat
Heat to the windshields is provided in a normal mode in flight, but is provided in a low
heat mode on the ground. The other windows are provided heat at one level regardless of
flight or ground condition.
Page 21: Automatic or Manual
Window heat can be selected to operate in the automatic or manual mode. The
PROBE/WINDOW HEAT pb determines the operating mode - Automatic or Manual. If
the PROBE/WINDOW HEAT pb is selected to AUTO, Window heat comes on
automatically when at least one engine is running, or when the aircraft is in flight.
Page 22: Window and Probe Heat
If the PROBE/WINDOW HEAT pb is selected to ON, the blue light in the pb illuminates
and Window and Probe heat comes on. If manual selection is desired before engine start,
the crew will select the pb ON, otherwise the heat will come on automatically after the
first engine start.
Page 23: PROBE/WINDOW HEAT pb
Window and Probe heat both require normal electrical power.
You can click the hotwords on this frame and the pb to see the results.
Page 24: Probe Heat
Probe Heat is used for all flight operations, regardless of weather conditions. Electrical
heating to the Probes is controlled by the PROBE/WINDOW HEAT pb.
Page 25: Probe Heat Components
Electrical heating protects the pitot probes, static ports, angle-of-attack probes, and the
total air temperature probes. On the ground, the total air temperature probes are not
heated. Pitot heating operates at low level while on the ground but automatically change
to normal power in flight.
Page 26: PHCs
Three independent Probe Heat Computers (PHCs) automatically control and monitor the
Captain's probes; the F/O's probes; and the STBY probes. The PHCs also protect against
overheating and indicate faults when they are detected.
Page 27: PROBE/WINDOW HEAT Auto
When the PROBE/WINDOW HEAT pb is selected to AUTO, the probes are heated
automatically if at least one engine is running, or when the aircraft is inflight.
Page 28: PROBE/WINDOW HEAT On
If the PROBE/WINDOW HEAT pb is selected to ON, the blue light in the pb illuminates
and the probe heat comes on. If this manual mode is desired, the crew selects the pb ON
before engine start. Probe heat requires normal electrical power (Capt. Pitot and AOA is
powered by essential busses.) You can click the hotwords on this frame and the pb to see
the results.
Page 29: Wipers
Each front windshield is equipped with a 2 speed electric powered wiper. There is a
rotary switch for control of each pilot's wiper. The Wiper speed can be selected to
SLOW, FAST, or OFF. The OFF position will cause the wipers to park out of view.
Wiper operation requires normal electrical power.
Page 30: Rain Repellent
Rain repellent is stored in a bottle in the rear of the cockpit. The bottle is equipped with a
pressure gauge that displays the nitrogen pressure in the bottle. When the needle of the
gauge is in the yellow sector, the bottle should be replaced. Additionally, when the bottle
is low on repellent fluid, a REFILL float will be in view to indicate the bottle should be
replaced.
Page 31: Rain Repellent pb
There is one Rain Repellent pb for each pilot windshield. When the pilot pushes a button,
a timer applies a measured quantity of repellent on the associated windshield. The Rain
Repellent will not operate when on the ground with the engines stopped. Rain Repellent
should never be applied to dry glass and should be used in moderate to heavy rain.
Page 32: Visual Ice Indicator
The external visual ice indicator is installed between the two windshields. The indicator
also has a light.
Page 33: Preflight
Preliminary Cockpit Preparation:
Before electrical power is applied to the aircraft, ensure the Wipers are selected OFF, and
check that the Probe/Window heat is selected to AUTO.
Page 34: After Engine Start
After Engine Start
Select the Engine Anti-ice as required by conditions. The Flight Manual normal
procedures explain static run-ups on the ground to ensure no ice accumulates on the
spinner, fan blades and low compressor stators.
Page 35: Wing Anti-ice ON
Select the Wing Anti-ice as required by conditions. If the Wing Anti-ice is selected ON
when the aircraft is on the ground, the anti-ice valves will open for 30 seconds and then
close. They will open upon liftoff.
Page 36: After Takeoff
After takeoff, if selected OFF for takeoff, select engine anti-ice and wing anti-ice as
required by conditions.
Page 37: Descent
Descent: Select the Engine and Wing Anti-ice as required by conditions. Make note that
the engine idle speed will increase when the Wing or Engine Anti-ice is on. This may
reduce the descent path angle and the pilot can compensate for this by increasing the
descent speed and/or extending up to half speedbrakes.
Page 38: Gear Down for Landing
After Gear are Down for Landing:
The Wing Anti-ice should only be turned on for the final phase of the approach if severe
icing conditions are encountered.
Page 39: After Landing
After Landing:
Wing Anti-ice shuts down upon landing.
Page 40: Flap/Slat Retract Inspection
If the landing was made in icing conditions or if the runway was contaminated with slush
or snow, don't retract the flaps or slats until the ground crew has inspected them for
obstruction of ice or snow.
Page 41: Engine Runup
The same requirements for operation of Engine Anti-ice exist after landing as before
takeoff. Additionally, engine run-up may be required to remove ice build up on the
engine or to keep ice from accumulating. Now, let's answer some questions.
