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Depicted are the Cockpit, forward and aft cabin zones. For each zone, the
zone temperature and air conditioning duct temperature are displayed.
The position of trim valves (Cold-Hot) is displayed by the needles connected
to the hot air valve symbol.
A319/320/321
Systems Manual
Phoenix Simulation Software P 83
REV 01 SEQ 001 Pressurization
Overview
The pressurization system controls the aircraft cabin air pressure to maintain safe differential pressure between cabin air and
ambient air.
The cabin pressure is represented as cabin altitude. A cabin altitude of 2000 ft means that the cabin air pressure is the same
as it would be in the standard atmosphere at 2000 ft above sea level. Rate of change of cabin pressure is represented by
cabin vertical speed.
The pressurization system controls the cabin vertical speed by changing the position of the Outow valve, which vents cabin
air overboard. Cabin pressurization can be controlled automatically by pressure controllers, or manually controlling the cabin
vertical speed.
Two safety valves prevent excessive positive or negative differential pressure.
Automatic pressure control
The pressure controllers control cabin altitude using different pressurization modes, depending on ight phase:
• Ground - the aircraft is depressurized by fully opening the outow valve.
• Takeoff - to avoid a pressure surge at rotation, the aircraft is prepressurized to cabin altitude of 400 ft below eld elevation.
• Climb - cabin altitude is varied depending on the aircraft climb rate
• Cruise - the controllers maintain minimum cabin altitude compatible with maximum cabin differential pressure.
• Descent - the cabin altitude is decreased to reach the cabin altitude of selected landing elevation before touchdown.
• Touchdown - residual cabin pressure is released gradually, then outow valve fully opens.
Controls and indications
CABIN PRESS control panel (overhead)
 MODE SEL ƒ LDG ELEV
‚ MAN V/S CTL „ DITCHING
 MODE SEL
NO LIGHT: AUTO, the pressurization is controlled automatically by the active pressure controller.
MAN: Manual control, the pressure controllers are deactivated and outow valve is manually controlled.
‚ MAN V/S CTL
When MODE SEL button is set to MAN, this toggle switch gradually opens or closes the outow valve. The switch is springloaded to
neutral position. Use ECAM PRESS page to monitor cabin V/S, altitude and differential pressure
ƒ LDG ELEV
Landing elevation selector switch. When set to AUTO, the database elevation of DEST airport entered into FMS is used. Other
positions are marked in 1000s of feet and manually select the landing elevation.
„ DITCHING
Pushing this guarded button will close all aircraft openings located below otation line. The outow valve, emergency ram air inlet,
avionics ventilation inlet and extract valves, and pack ow control valves are automatically closed.
A319/320/321
Systems Manual
Phoenix Simulation Software P 84
REV 01 SEQ 001 Pressurization
Controls and indications (continued)
ECAM PRESS page
This page is used to monitor the operation of pressurization system.
The three big gauges show cabin differential pressure, cabin vertical speed, and cabin altitude. Selected landing elevation is
displayed above the gauges.
Pressurization system is depicted in the lower part of the page. The system is controlled by one of the two pressurization controllers.
The control is automatically switched between controller 1 and controller 2 after each ight. The active controller is shown by
“SYS 1” or “SYS 2” indication.
If MODE SEL is set to MAN (manual control), “MAN” indication is visible.
The aircraft pressurized area is depicted by the big rectangle with pressure valves shown. Position of each valve is indicated
by a needle.
Air ow from air conditioning packs is shown with arrows, which turn solid amber when a pack is not supplying the air.
ECAM CRUISE page
The CRUISE page is automatically displayed in normal ight. Among other
information, it shows cabin differential pressure, vertical speed, altitude and
landing elevation. Also shown are the zone temperatures.
A319/320/321
Systems Manual
Phoenix Simulation Software P 85
REV 01 SEQ 001 GPWS
Overview
The Ground Proximity warning system will provide aural and visual warnings when aircraft is in danger of ground impact. It detects
numerous dangerous conditions and can produce the following warnings:
“SINKRATE”: Warning of high barometric descent rate into terrain, or high sink rate near the runway threshold. The lower your
　
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