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EFFECTIVITY 30-11-00 Page 8
Aug 02/99
_A319/A320/A321 TECHNICAL TRAINING MANUAL
MECHANICS / ELECTRICS & AVIONICS COURSE 30 ICE & RAIN PROTECTION
UF94200
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WING ICE PROTECTION SYSTEM COMPONENTS
WING ANTI-ICE CONTROL VALVE (OPTIONAL) - CUT VIEW - MANUAL LOCKING LEVER
TMUIC1EZZ-P04 LEVEL 2
EFFECTIVITY 30-11-00 Page 9
Aug 02/99
_A319/A320/A321 TECHNICAL TRAINING MANUAL
MECHANICS / ELECTRICS & AVIONICS COURSE 30 ICE & RAIN PROTECTION
UF94200
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TMUIC1EZZ LEVEL 2
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Aug 02/99
_A319/A320/A321 TECHNICAL TRAINING MANUAL
MECHANICS / ELECTRICS & AVIONICS COURSE 30 ICE & RAIN PROTECTION
UF94200
EFFECTIVITY Page 26
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30 - ICE AND RAIN PROTECTION
30-11-00 WING ICE PROTECTION SYSTEM
COMPONENTS
CONTENTS:
Telescopic Duct
TMUIC2E01 LEVEL 3
EFFECTIVITY 30-11-00 Page 1
Aug 31/96
_A319/A320/A321 TECHNICAL TRAINING MANUAL
MECHANICS / ELECTRICS & AVIONICS COURSE 30 ICE & RAIN PROTECTION
UF94200
EFFECTIVITY Page 27
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WING ICE PROTECTION SYSTEM COMPONENTS
TELESCOPIC DUCT
LOCATION
ZONE : (LH) 522, (RH) 622
TMUIC2E01-T01 LEVEL 3
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_A319/A320/A321 TECHNICAL TRAINING MANUAL
MECHANICS / ELECTRICS & AVIONICS COURSE 30 ICE & RAIN PROTECTION
UF94200
EFFECTIVITY Page 28
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WING ICE PROTECTION SYSTEM COMPONENTS - TELESCOPIC DUCT
TMUIC2E01-P01 LEVEL 3
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Aug 31/96
_A319/A320/A321 TECHNICAL TRAINING MANUAL
MECHANICS / ELECTRICS & AVIONICS COURSE 30 ICE & RAIN PROTECTION
UF94200
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TMUIC2E01 LEVEL 3
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Aug 31/96
_A319/A320/A321 TECHNICAL TRAINING MANUAL
MECHANICS / ELECTRICS & AVIONICS COURSE 30 ICE & RAIN PROTECTION
UF94200
EFFECTIVITY Page 30
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30 - ICE AND RAIN PROTECTION
30-21-00 ENGINE AIR INTAKE ICE PROTECTION
SYSTEM PRESENTATION
CONTENTS:
Source
Valve
Controls
Users
ECAM Page
Self Examination
TMUICE306 LEVEL 1
EFFECTIVITY 30-21-00 Page 1
Sep 30/97
_A319/A320/A321 TECHNICAL TRAINING MANUAL
MECHANICS / ELECTRICS & AVIONICS COURSE 30 ICE & RAIN PROTECTION
UF94200
EFFECTIVITY Page 31
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ENGINE AIR INTAKE ICE PROTECTION SYSTEM PRESENTATION
SOURCE
Air is bled from a high pressure compressor stage of
each engine.
VALVE
For each engine, hot bleed air is ducted via an ON/OFF
valve. In the absence of air pressure, the valve is
spring loaded to the closed position.
Upon energization of the solenoid, the valve closes.
In case of loss of electrical power supply, the valve
is fully open provided engine bleed air pressure is
high enough.
CONTROLS
For each engine, the ON/OFF valve is controlled by a
pushbutton.
When both engine anti-ice valves are open, the Cabin
Zone Controller determines the bleed in demand for the
Full Authority Digital Engine Control (FADEC) system.
This decreases the N1 limit.
USERS
The engine air intake is protected by its related bleed
air, which heats the inlet lip in icing conditions.
The hot air is discharged overboard.
ECAM PAGE
If at least one of the engine air intake anti-ice
systems is selected ON, a message appears in green on
the ECAM MEMO display.
TMUICE306-T01 LEVEL 1
EFFECTIVITY 30-21-00 Page 2
Sep 30/97
_A319/A320/A321 TECHNICAL TRAINING MANUAL
MECHANICS / ELECTRICS & AVIONICS COURSE 30 ICE & RAIN PROTECTION
UF94200
EFFECTIVITY Page 32
ALL
TMUICE306-P01 LEVEL 1
ENGINE AIR INTAKE ICE PROTECTION SYSTEM PRESENTATION
EFFECTIVITY 30-21-00 Page 3
Sep 30/97
_A319/A320/A321 TECHNICAL TRAINING MANUAL
MECHANICS / ELECTRICS & AVIONICS COURSE 30 ICE & RAIN PROTECTION
UF94200
EFFECTIVITY Page 33
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SELF EXAMINATION
What happens in case of loss of electrical power
supply to the engine anti-ice valve ?
A - The valve opens when the engine is
stopped.
B - The valve opens when the engine is
running.
C - The valve closes when the engine is
running.
What happens in case of insufficient air pressure
to the engine anti-ice valve ?
A - The valve closes as it is spring loaded
closed.
B - The valve opens as it is spring loaded
open.
　
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