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The fan is driven at high speed when cockpit ventilated temperature is above 0°C and (both packs
are OFF or the main door is not closed and locked).
The fan is driven at low speed otherwise.
In the case of a failure, the avionics fan is automatically powered OFF by its converter.
AIR CONDITIONING AND PRESSURIZATION
REV 51, Aug 14, 2006 Flight Crew Operating Manual
CSP 700−6
Volume 2
02−10−33
AIR DISTRIBUTION AND EXHAUST (CONT'D)
Avionics and Cockpit Display Ventilation (Cont’d)
The converter tries to restart the fan by automatic reset (up to three times), then if failure is still
detected, it will shut off the fan and post a message on EICAS.
NOTE
Check limits on ground operations with
failed Avionics fan and ECS OFF.
Maximum operating time of 30 minutes at
35 C.
GF0210_042
AVIONICS FAN FAIL
In case of a fan underspeed failure detected by the converter, a fault signal is provided to CAIMS,
but the fan remains running.
Auxiliary Pressurization
The auxiliary pressurization system provides an alternative pressurization source for the cabin, in
the event of loss of both cooling packs.
The AUX PRESS switch, when selected ON, sends a signal to each ACSC. The ACSC commands
the HASOVs to mid position and the trim valves to full open, for use of trim air, for pressurization.
The recirculation system should be selected ON, to reduce the supply temperatures in the
distribution ducts. Duct overheat detection is carried out by the ACSCs.
An EICAS message is displayed when AUX PRESS switch is selected.
GF0210_043
BLEED BLEED
RAM AIR
23 °C 23 °C 23 °C
10 °C
TRIM AIR
10 °C
R PACK
AUX PRESS ON
L PACK
AUX PRESS ON
AUX PRESS
ON
AUX PRESS
ON
AIR CONDITIONING AND PRESSURIZATION
Flight Crew Operating Manual REV 41, Jul 08, 2004
CSP 700−6
Volume 2
02−10−34
AIR DISTRIBUTION AND EXHAUST (CONT'D)
Humidifier System (Option)
The humidifier system provides additional humidity to the aircraft cabin compartments during high
altitude cruise. The humidity is provided directly to the Environment Control System (ECS) mix
manifold and then supplied to the cabin compartments via the ECS distribution ducting. The
humidifier system is comprised of the following main components:
• Humidifier water boiler assembly (HWB);
• humidifier trim air valve (TAV-H);
• humidifier water shutoff valve (HWSOV);
• humidifier water feed valve (HWFV);
• humidifier drain valve (HDV);
• humidifier cabin humidity sensor (HCHS); and
• humidifier control unit (HCU).
GF0210_088
POTABLE
WATER
SYSTEM
HWSOV
HWFV
HDV
HWB
TO AIRPLANE
WATER DRAIN
TO AFT
CABIN
TO
COCKPIT
TO FWD
CABIN
FROM LEFT
AIR−CONDITIONING
PACK
FROM RIGHT
AIR−CONDITIONING
PACK
RESTRICTOR
TAV−H
HASOV
HASOV
FROM RIGHT
ENGINE BLEED
FROM LEFT
ENGINE BLEED
MIX
MANIFOLD
TRIM AIR
VALVES
WATER
COLD AIR
HOT AIR
STEAMED AIR
LEGEND
ECS
ECS
ECS
AIR CONDITIONING AND PRESSURIZATION
REV 51, Aug 14, 2006 Flight Crew Operating Manual
CSP 700−6
Volume 2
02−10−35
AIR DISTRIBUTION AND EXHAUST (CONT'D)
Humidifier System (Option) (Cont’d)
Water is taken form the potable water system and routed to the boiler via 2 normally closed valves.
When the system is activated, the Humidifier Control Unit (HCU) will open both valves to replenish
the boiler. Trim air is used to heat the boiler. The generated steam is then supplied to the ECS mix
manifold. A humidity sensor (HCHS) is installed in the aft cabin to monitor the temperature and
moisture level. The reading from the sensor is feed to the HCU to determine the amount of steam
needed to bring the humidity level within the acceptable range. The amount of steam generated by
the boiler is controlled by the humidifier Trim Air Valve (TAV-H). The TAV-H modulates the air flow
that reaches the boiler thus affecting the amount of steam generated. A restrictor is added to limit
the maximum amount of trim air supplied to the boiler.
The system is activated through the EMS CDU SWITCH CONTROL page.
Effectivity:
• Airplanes 9002 thru 9122 not incorporating Service Bulletin:
• SB 700−24−045, AC and DC Power Distribution − Unit Change and Activation of Build 4
Electrical System.
Power is routed to the HCU via the EMS CDU SWITCH CONTROL page. The system is
　
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