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Sept 04
BLEED/ANTI-ICE SYNOPTIC
The BLEED/ANTI-ICE synoptic is selected using the EICAS Control Panel, located
on the pedestal.
For more information on the Anti-Ice system see Chapter 3, ICE AND RAIN
PROTECTION.
For more information on the Starter Pop-Up see Chapter 17, POWER PLANT.
STAT
HYD
AC
ELEC
BLEED
AIR
COND
DC
ELEC
FUEL
FLT
CTRL
SCROLL
EICAS
SYSTEMS SELECT
NORM
MFD 1 MFD 2
BLEED / ANTI-ICE
APU
LP
AIR
COND
HP
L
LP
HP 40
PSI
40
PSI
R
EICAS CONTROL PANEL
Leading Edge
Wing Anti-Ice
Pressure
Regulating
Shutoff Valve
(WAIV)
Wing Anti-Ice Cross
Bleed Valve (CBV)
Cowl Anti-Ice Valve
(CAIV)
Bleed Air Starter Pop-Up Display
and Starter Air Valve
(Only displayed if an engine is not
operating)
GX_13_004
For Training Purposes Only
Sept 04
13-7
P I LOT T R A I N I N G GU I D E
INTEGRATED AIR MANAGEMENT SYSTEM
The BLEED/ANTI-ICE synoptic is selected using the EICAS Control Panel, located
on the pedestal.
For more information on the APU see Chapter 4, AUXILIARY POWER UNIT.
For more information on the engines see Chapter 17, POWER PLANT.
BLEED / ANTI-ICE
APU
LP
AIR
COND
HP
L
LP
HP 26
PSI
26
PSI
R
STAT
HYD
AC
ELEC
BLEED
AIR
COND
DC
ELEC
FUEL
FLT
CTRL
SCROLL
EICAS
SYSTEMS SELECT
NORM
MFD 1 MFD 2
EICAS CONTROL PANEL
Engine Outline
Cross Bleed
Valve (CBV)
Load Control Valve
APU Outline
Bleed Pressure Pressure Regulator
Valve (PRV)
High Pressure
Valve (HPV)
GX_13_005
P I LOT T R A I N I N G GU I D E
INTEGRATED AIR MANAGEMENT SYSTEM
13-8 For Training Purposes Only
Sept 04
BLEED MANAGEMENT CONTROLLERS (BMC)
There are two BMCs, one for the left hand side and one for the right hand side of the
airplane. Each BMC is comprised of two redundant channels (control and monitoring).
The control channel ensures on/off switching and the following control functions for
its associated side:
• Bleed on/off
• Wing anti-ice on/off switching and monitoring
• Wing anti-ice temperature regulation and monitoring
• Crossbleed valve (CBV) and cross anti-ice functions
The monitoring channel controls monitoring functions and leak detection, and
provides:
• Leak detection for the complete airplane. The redundancy on the leak detection is
achieved by the two monitoring channels of the two BMCs
• Redundancy on control and monitoring of bleed switching and anti-ice switching,
and wing anti-ice temperature regulation
GX_13_006
THC
P
THC
P
P P
R AIR
TURBINE
STARTER
LOW
PRESS
PORT
LOW
PRESS
PORT
HIGH
PRESS PORT
HIGH
PRESS PORT
L STARTER
AIR VALVE
R STARTER
AIR VALVE
HIGH
PRESS
VALVE
HIGH
PRESS
VALVE
L AIR
TURBINE
STARTER
GROUND
AIR SUPPLY
FAN AIR
VALVE
FAN AIR
VALVE
CROSS BLEED
VALVE
L WING
A/I VALVE
R WING
A/I VALVE
PRECOOLER
PRECOOLER
PRV PRV
FAN
AIR
PORT
FAN
AIR
PORT
COWL
A/I VALVE
COWL
A/I VALVE
COWL ANTI-ICE COWL
PRESSURE
SENSOR / SWITCH
(TYPICAL)
BLEED AIR
VALVE
(TYPICAL)
CHECK VALVE
(ARROW INDICATES
DIRECTION OF FLOW)
LOAD
CONTROL
VALVE (LCV)
P
EXHAUST
L AIR
COND
R AIR
COND
EXHAUST
P P
ANTI-ICE
IPPT IPPT
BPT BPT
- ANTI-ICE
- BLEED PRESSURE TRANSDUCER
- INTERMEDIATE (LOW PRESSURE) PORT PRESSURE TRANSDUCER
- PRESSURE REGULATING VALVE
- TEMPERATURE CONTROL THERMOSTAT
A/I
BPT
IPPT
PRV
THC
APU
For Training Purposes Only
Sept 04
13-9
P I LOT T R A I N I N G GU I D E
INTEGRATED AIR MANAGEMENT SYSTEM
BLEED AIR TRANSFER/PRESSURE REGULATION
The BMC selects air from either the low-pressure port (5th stage) or high-pressure
port (8th stage) on the engine depending on the pressure available. The Pressure
Regulating Valve (PRV) limits the pressure supplied to 43 ± 3psig.
Under normal operating conditions (in-flight), the air is bled from the low-pressure
　
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