Ice and Rain Protection

Question 1

Icing Conditions?

Answer 1

When OAT on gnd or just airborne, or TAT in flight is below 10 Deg and there is visible moisture in the air (Clouds, Fog with vis less than 1nm, rain, snow,sleet, ice crystals or standing water, slush, ice or snow is present on taxiway or runway.

Question 2

Engine anti ice on?

Answer 2

At all times of icing conditions EXCEPT during CLIMB and CRUISE when SAT is below MINUS 40 Deg.
EAI must be on at ALL times in icing conditions on descent, EVEN if SAT is below Minus 40 degrees

Question 3

Wing Anti Ice?

Answer 3

WING ANTI ICE may either be used to prevent ice formation, or to remove ice accumulation
from the wing leading edges.
WING ANTI ICE should be selected ON, whenever there is an indication that airframe icing
exists. This can be evidenced by ice accumulation on the visual ice indicator (located between
the two cockpit windshields), or on the windshield wipers.

Question 4

SLATS caution?

Answer 4

1. Extended flight, in icing conditions with the slats extended, should be
   avoided.
2. If there is evidence of significant ice accretion and to take into account ice
   formation on non heated structure, the minimum speed should be :
   ‐ In configuration full, VLS +5 kt.
   ‐ In configuration lower than FULL, VLS +10 kt.
   For Landing Performance assessment, refer to QRH FPE-IFL.
3. If there is evidence of ice accretion on de-iced parts (WING ANTI ICE
   inoperative) of the airframe, the minimum speeds should be :
   ‐ In clean configuration, VLS + 15 kt.
   ‐ In CONF 1, 2, 3, FULL, VLS + 10 kt. For Landing Performance
   assessment, refer to QRH FPE-IFL.

Question 5

Severe Ice Accretion

Answer 5

Icing conditions are severe when there is approximately 5 mm of ice accretion on the airframe.

Question 6

Rain Repellant

Answer 6

If the rain repellent is operative, the flight crew should only use the rain repellent in moderate to
heavy rain.

Question 7

Gnd Ops In heavy Rain

Answer 7

When the aircraft is parked on the ground during heavy rain, it can take rainwater into the avionics
ventilation system via the open skin air inlet valve.
To prevent this, the following procedure must be applied :
 After landing :
EXTRACT………………………………….OVRD
This closes the avionics ventilation system, preventing rainwater from entering.
PACKS 1 and 2……………………………………………………………………………………………… CHECK ON
This adds air from the air conditioning system to ventilation air. If bleed air is not available, the
arrangement can function for a limited time, as follows :
• OAT ≤ 39 °C : no limit
• 39 °C ≤ OAT ≤ 45 °C : 3 h
• OAT ≥ 45 °C : 30 min
 After takeoff :
EXTRACT…………………… AUTO

Question 8

Sytem Failure considerations

Answer 8

Pitots?…….. ADR faults Possible unreliable speed
EAI valves Closed Cant Open? Avoid icing conditions.
EAI Vlves open, Cant close; Thrust Limit Penalty.

Question 9

Ice and Rain protection Authoristation

Answer 9

Allows unrestricted operation of the aircraft in icing conditions and heavy rain.

Question 10

Hot Air Protection

Answer 10

Three Outboard leading edge slats of each wing.

Engine air intakes.

Question 11

Elecritrical heating

Answer 11

• Flight compartment windows
• Sensors Pitot Probes and Static ports.
• Water waste drain mast.

Question 12

Rain Removal

Answer 12

Wipers, and when necessary fluid reain repellant, remove rain from front windshield.

Question 13

WAI System description

Answer 13

In flight, hot air from the pneumatic system heats the three outboard slats (3-4-5) of each wing.
Air is supplied through one valve in each wing.
The WING pushbutton on the ANTI ICE panel controls the valves.
When the aircraft is on ground, the flight crew can initiate a 30 s test sequence by turning the system
ON.
If the system detects a leak during normal operation, the affected side’s wing anti-ice valve
automatically closes (Refer to DSC-36-10-50 LEAK DETECTION).
When wing anti-ice is selected, the EPR limit is automatically reduced, and the idle EPR is
automatically increased.
If the electrical power supply fails, the valves close.

Question 14

WAI control

Answer 14

WING ANTI ICE pb sw
This switch controls the wing anti ice system on the left and right sides simultaneously.
ON : It lights up blue.
WING A. ICE appears on the ECAM MEMO page.
Wing anti ice control valves open if a pneumatic supply is available.
On the ground the wing anti-icing control valves open for 30 s only (test sequence).
Off : ON light goes off.
Wing anti-icing control valves close.
FAULT : Amber light comes on, and caution appears on ECAM, if:
‐ the position of the anti-icing control valve is not the required position, or
‐ low pressure is detected.
Note: The amber FAULT light comes on briefly as the valves transit.

Question 15

EAI System description

Answer 15

An independent air bleed from the high pressure compressor protects each engine nacelle from ice.
Air is supplied through a two-position (open and closed) valve that the flight crew controls with two
pushbuttons, one for each engine.
The valve automatically closes, if air is unavailable (engine not running).
When an engine anti-ice valve is open, the EPR limit is automatically reduced and, if necessary, the
idle EPR is automatically increased for both engines in order to provide the required pressure.
If electrical power fails, the valves open.

Question 16

EAI Control

Answer 16

ENG 1 (2) ANTI ICE pb-sw
ON : Iight comes on blue.
ECAM MEMO displays “ENG A. ICE”.
Engine anti-icing valve opens if bleed air is available from the engine.
Continuous ignition is selected when the valve is opened and the ENG ANTI ICE
pb-sw is selected ON. This makes the IGNITION memo appear on the ECAM.
Off : ON light goes out.
Engine anti-ice valve closes.
FAULT : Amber light comes on, and caution message appears on ECAM, if the position of
the anti-ice valve disagrees with the ENG 1 (2) pushbutton selection.
Note: The amber FAULT light comes on briefly as valve transits.

Question 17

Window Heat Description

Answer 17

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.
Window heating comes on:
‐ automatically when at least one engine is running, or when the aircraft is in flight.
‐ manually, before engine start, when the flight crew switches ON the PROBE/WINDOW HEAT
pushbutton switch.
Windshield heating operates at low power on the ground and at normal power in flight. The
changeover is automatic.
Only one heating level exists for the windows.

Question 18

Probes Heat Description

Answer 18

Electrical heating protects:
‐ Pitot heads
‐ Static ports
‐ Angle-Of-Attack probes (AOAs)
‐ Total Air Temperature (TAT) probes.
Three independent Probe Heat Computers (PHCs) automatically control and monitor:
‐ Captain probes
‐ F/O probes
‐ STBY probes.
They protect against overheating and indicate faults.
The probes are heated:
‐ Automatically when at least one engine is running, or when the aircraft is in flight.
‐ Manually, when the flight crew switches ON the PROBE/WINDOW HEAT pb.
On the ground, the TAT probes are not heated and pitot heating operates at a low level (the
changeover to normal power in flight is automatic).

Question 19

Probes/Windows heat control

Answer 19

PROBE/WINDOW HEAT pb
AUTO : Probes/Windows are heated automatically :
‐ In flight, or
‐ On the ground (except TAT probes) provided one engine is running.
ON : Probes and windows are heated permanently. Blue light comes on.

Question 20

Wipers

Answer 20

Each front windshield has a dual-speed electric wiper, which are each controlled by a rotary selector.

Question 21

Rain repellant

Answer 21

In moderate to heavy rain, the flight crew can spray a rain repellent liquid on the windshield to
improve visibility.
After about 30 s, the windows are covered with spray.
Separate pushbuttons control rain repellent application on each side of the windshield.

Question 22

Wiper/Repellant Control

Indicator

Answer 22

RAIN RPLNT pushbuttons 
Each of these buttons controls the application of rain repellent fluid to the corresponding side of
the front windshield.
When the flight crew pushes the button, the timer applies a measured quantity of rain repellent
to the windshield. To repeat the cycle, the flight crew must push the button again.
This function is inhibited when the aircraft is on the ground and the engines are stopped.
RAIN RPLNT pressure indicator
This gauge shows the nitrogen pressure in the rain repellent bottle. When the needle is in the
yellow sector the bottle should be replaced.
(2) RAIN RPLNT quantity indicator
When the REFILL float is in view the bottle should be replaced

Question 23

Visual Ice Indicator

Answer 23

An external visual ice indicator is installed between the two windshields.
The indicator has also a light.