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A/ICE
VALVE
CHECK
VALVE
PRV
GF0210_007
When the pressure is insufficient at the low pressure port, the HPV is signaled to open by the BMC and air from the 8th stage of compression (high pressure port) drives the intermediate pressure check valve closed.
HIGH PRESS
HIGH PRESS PORT
GF0210_008
Rev 2A, Apr 11, 2005 Flight Crew Operating Manual Volume 2
Engine Bleed Air (Cont’d)
A cross.bleed valve (CBV) is installed between the left and right pneumatic ducts which can be opened, automatically by the BMC or manually through the OPEN selection, to provide bleed air from one side to the other, for example engine starting. For more information, see Chapter 18, POWER PLANT.
GF0210_009
The L (R) FIRE DISCH handles, when pulled, will close the affected PRV and the BMC will close the affected HPV. For more information, see Chapter 9, FIRE PROTECTION.
APU Bleed Air
The APU can be used on the ground and in the air, to supply the pneumatic system for air conditioning or engine starting.
Opening the Load Control valve (LCV), automatically by the BMC or manually through the ON selection, allows air from the APU to feed the left pneumatic duct.
Volume 2 Flight Crew Operating Manual Rev 2A, Apr 11, 2005 02.10.10 CSP 700.5000.6
APU Bleed Air (Cont’d)
The air pressure delivered in the pneumatic duct is displayed on the synoptic page in PSI.
or
PRESSURE READOUT
LOAD CONTROL VALVE
NOTE
APU bleed air volume is insufficient to supply the wing anti.ice system.
GF0210_011
Opening the cross.bleed valve (CBV), automatically by the BMC or manually through the ON selection, allows air from the APU to feed the right pneumatic duct.
or
HANDLE PULLED
GF0210_012
The APU FIRE DISCH handle, when pulled, will close the LCV. For more information, see Chapter 9 FIRE PROTECTION.
NOTE
Engine bleed has priority over APU bleed and MAN has priority over AUTO.
If both PRVs are open (engines running), the BMC will automatically close the LCV and the CBV, if LCV and CBV are in AUTO or Manual.
Rev 2A, Apr 11, 2005 Flight Crew Operating Manual Volume 2
AIR CONDITIONING AND PRESSURIZATION
Bleed Leak Detection
Hot air leaks are monitored in the airplane by dual loop continuous fire detection sensing elements, routed along the airplane ducts. Each dual loop consists of loop A and loop B. Loop A is connected to the left BMC monitoring channel and loop B is connected to the right BMC monitoring channel.
Leak detection elements consist of two concentric tubes. The space between the tubes is filled with an insulated eutectic salt. In case of temperature increase, the salt becomes conductive and the measured resistance between the tubes drops suddenly, triggering an EICAS message.
FGF0210_009
Volume 2 Flight Crew Operating Manual Rev 2A, Apr 11, 2005
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