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WING ICE PROTECTION SYSTEM WARNINGS
EFFECTIVITY 30-11-00 Page 2
Aug 06/99
_A319/A320/A321 TECHNICAL TRAINING MANUAL
MECHANICS / ELECTRICS & AVIONICS COURSE 30 ICE & RAIN PROTECTION
UF94200
EFFECTIVITY Page 12
ALL
30 - ICE AND RAIN PROTECTION
30-11-00 WING ICE PROTECTION SYSTEM
INTERFACES
CONTENTS:
Pushbutton Switch
Engine Interface Unit (EIU)
Landing Gear Control and Interface Unit (LGCIU)
System Data Acquisition Concentrator (SDAC)
Zone Controller
TMUIC4001 LEVEL 3
EFFECTIVITY 30-11-00 Page 1
Sep 30/98
_A319/A320/A321 TECHNICAL TRAINING MANUAL
MECHANICS / ELECTRICS & AVIONICS COURSE 30 ICE & RAIN PROTECTION
UF94200
EFFECTIVITY Page 13
ALL
WING ICE PROTECTION SYSTEM INTERFACES
PUSHBUTTON SWITCH
The wing anti-ice pusbutton switch allows the wing
anti-ice system to be activated either during flight
operation or during ground test operation for a limited
time.
It also sends the pushbutton switch configuration to
the System Data Acquisition Concentrators and to the
Engine Interface Units (EIUs).
The wing anti-ice pusbutton switch acquires a discrete
signal from the fault relay for the illumination of
the "FAULT" light, during either valves transit or in
case of disagreement between valves position and system
selection or in case of a low pressure detection.
ENGINE INTERFACE UNIT (EIU)
The Engine Interface Units acquire system selection
for engine power increase according to the bleed
demand.
LANDING GEAR CONTROL AND INTERFACE UNIT (LGCIU)
The Landing Gear Control and Interface Units (LGCIUs)
send a shock absorber extended signal to the control
relay to enable the system control when the aircraft
is in flight configuration.
SYSTEM DATA ACQUISITION CONCENTRATOR (SDAC)
The System Data Acquisition Concentrators (SDACs)
acquire discrete inputs to display system status on
ECAM warning page, ECAM MEMO page and ECAM BLEED page.
ZONE CONTROLLER
The Zone Controller acquires discrete inputs to monitor
the system and manage the bleed air.
It stores failure data of the wing anti-ice system.
TMUIC4001-T01 LEVEL 3
EFFECTIVITY 30-11-00 Page 2
Sep 30/98
_A319/A320/A321 TECHNICAL TRAINING MANUAL
MECHANICS / ELECTRICS & AVIONICS COURSE 30 ICE & RAIN PROTECTION
UF94200
EFFECTIVITY Page 14
ALL
WING ICE PROTECTION SYSTEM INTERFACES
TMUIC4001-P01 LEVEL 3
EFFECTIVITY 30-11-00 Page 3
Sep 30/98
_A319/A320/A321 TECHNICAL TRAINING MANUAL
MECHANICS / ELECTRICS & AVIONICS COURSE 30 ICE & RAIN PROTECTION
UF94200
EFFECTIVITY Page 15
ALL
THIS PAGE INTENTIONALLY LEFT BLANK
TMUIC4001 LEVEL 3
EFFECTIVITY 30-11-00 Page 4
Sep 30/98
_A319/A320/A321 TECHNICAL TRAINING MANUAL
MECHANICS / ELECTRICS & AVIONICS COURSE 30 ICE & RAIN PROTECTION
UF94200
EFFECTIVITY Page 16
ALL
30 - ICE AND RAIN PROTECTION
30-11-00 WING ICE PROTECTION SYSTEM
COMPONENTS
CONTENTS:
Wing Anti-Ice Control Valve (HYMATIC)
Wing Anti-Ice Control Valve (GRIMES)
TMUIC1EZZ LEVEL 2
EFFECTIVITY 30-11-00 Page 1
Aug 02/99
_A319/A320/A321 TECHNICAL TRAINING MANUAL
MECHANICS / ELECTRICS & AVIONICS COURSE 30 ICE & RAIN PROTECTION
UF94200
EFFECTIVITY Page 17
ALL
WING ICE PROTECTION SYSTEM COMPONENTS
WING ANTI-ICE CONTROL VALVE (HYMATIC)
This valve is basically installed on A319 and A320.
It can be optionally installed on A321.
IDENTIFICATION
FIN : (LH) 9DL, (RH) 10DL
LOCATION
ZONE : (LH) 522, (RH) 622
COMPONENT DESCRIPTION
The wing anti-ice control valve is an
electrically-controlled, pneumatically-operated
valve.
The valve has these primary components :
- an actuator body assembly,
- a controller/damper housing assembly,
- a valve body/shaft assembly,
- a solenoid valve assembly,
- a position indicator,
- two pressure switches,
- two ground test points,
- a filter.
The valve controls its outlet pressure at 22.5 psi
(1,55 bar).
If the pressure increases to 32 psi or decreases to
13 psi the related switch gives a "high pressure" or
"low pressure" signal.
NOTE: If a failure of the electrical or air supply
occurs, the butterfly disc always closes.
TMUIC1EZZ-T01 LEVEL 2
EFFECTIVITY 30-11-00 Page 2
Aug 02/99
_A319/A320/A321 TECHNICAL TRAINING MANUAL
MECHANICS / ELECTRICS & AVIONICS COURSE 30 ICE & RAIN PROTECTION
UF94200
EFFECTIVITY Page 18
　
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