W DOC AIRBUS | AMM A320F

AIR CONDITIONING - DESCRIPTION AND OPERATION

** ON A/C NOT FOR ALL
1. General
F Air Conditioning System - General ** ON A/C NOT FOR ALL
F Air Conditioning System - General ** ON A/C NOT FOR ALL
F Air Conditioning System - General ** ON A/C NOT FOR ALL
F Air Conditioning System - General ** ON A/C NOT FOR ALL
The air conditioning system keeps the air in the pressurized fuselage compartments at the correct pressure, temperature and freshness.
In normal conditions, the pneumatic system supplies air to the air conditioning system from:
  • the main engine compressors,
  • the APU compressor,
  • a high-pressure ground-air supply-unit.
The hot compressed air is cooled, conditioned and supplied to the fuselage compartments and then discharged overboard through the outflow valve.
You can also supply conditioned air to the distribution system through a low pressure ground-connection.
** ON A/C NOT FOR ALL
2. System Description
The air conditioning system gives satisfactory values of pressure, temperature and freshness of the air in the pressurized fuselage .
A. Sub-systems
The air conditioning system consists of the following sub-systems:
  • distribution
  • pressurization control,
  • air cooling,
  • temperature control.
(1) Distribution System (Ref. AMM D/O 21-20-00-00)
The distribution system delivers conditioned air to the pressurized fuselage.
(2) Pressurization Control System (Ref. AMM D/O 21-30-00-00)
The pressurization control system controls the pressure in the fuselage. It operates fully automatically and has a manual backup. The pressure change rate is controlled to give satisfactory pressure values of safety and comfort for the passengers and crew.
(3) Air Cooling System (Ref. AMM D/O 21-50-00-00)
The air cooling system decreases the temperature of the hot bleed air from the pneumatic system. It also reduces the quantity of water in the hot bleed air.
Emergency ram air is supplied if there is a failure in the two air conditioning packs.
(4) Temperature Control System (Ref. AMM D/O 21-60-00-00)
The temperature control system controls the temperature of the air supplied to the cockpit and cabin. You can adjust the temperature in the cockpit and the cabin independently.
B. Air Supply Quantities and Flow Split
For the normal operation and most important failure cases the total airflows supplied to the cockpit and passenger cabin are shown in table 1. All cases are nominal values.
(1) Total Fresh Air Quantities (Table 1)
----------------------------------------------------------------------------
! f * Qvs * Pc ! !
! - Q = ---------------- ! !
! 2.87 * Tc ! !
! ! !
! - Q = mass flow ! kg/s !
! - f = selected flow factor ! (0.8/1.0/1.2) !
! - Pc = cabin pressure ! mbar !
! - Tc = cabin temperature ! 297 K !
! - Qvs = normal volumetric flow at sea level ! 0.928 cbm/s !
! - 2.87 = constant factor ! !
----------------------------------------------------------------------------

The nominal values from the use of the above formula:
----------------------------------------------------------------------------
! ground kg/s cruise kg/s !
!----------------------------------------------------------------------------!
! normal flow (100%) ! 1.102 ! 0.817 !
! minimum flow ! 80 % of norm. ! 80 % of norm. !
! maximum flow ! 120 % of norm. ! 120 % of norm. !
! one pack off ! 60 % of norm. ! 60 % of norm. !
----------------------------------------------------------------------------

These nominal flows can vary by plus 5 % or minus 2 %.
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! Total fresh air required from the APU: !
!----------------------------------------------------------------------------!
! hot day ! +38 DEG.C (100.4 DEG.F) ! 1.00 kg/s !
! cold day ! -23 DEG.C (-9.4 DEG.F) ! 1.28 kg/s !
! normal day ! - 5 DEG.C (+23 DEG.F) to +30 DEG.C (86 DEG.F) ! 0.82 kg/s !
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(2) Total Fresh Air Quantities:
----------------------------------------------------------------------------
! f * Qvs * Pc ! !
! - Q = ---------------- ! !
! 2.87 * Tc ! !
! ! !
! - Q = mass flow ! kg/s !
! - f = selected flow factor ! (0.8/1.0) !
! - Pc = cabin pressure ! mbar !
! - Tc = cabin temperature ! 297 K !
! - Qvs = normal volumetric flow at sea level ! 1.088 cbm/s !
! - 2.87 = constant factor ! !
----------------------------------------------------------------------------

The nominal values from the use of the above formula:
----------------------------------------------------------------------------
! ground kg/s cruise kg/s !
!----------------------------------------------------------------------------!
! normal flow (100%) ! 1.293 ! 0.96 !
! minimum flow ! 80 % of norm. ! 80 % of norm. !
! one pack off ! 60 % of norm. ! 60 % of norm. !
----------------------------------------------------------------------------

These nominal flows can vary by plus 5 % or minus 2 %.
----------------------------------------------------------------------------
! Total fresh air required from the APU: !
!----------------------------------------------------------------------------!
! hot day ! +38 DEG.C (100.4 DEG.F) ! 1.00 kg/s (Garrett) !
! hot day ! +38 DEG.C (100.4 DEG.F) ! 1.09 kg/s (APIC) !
! cold day ! -23 DEG.C (-9.4 DEG.F) ! 1.28 kg/s (Garrett) !
! cold day ! -23 DEG.C (-9.4 DEG.F) ! 1.49 kg/s (APIC) !
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(3) Distribution Data
F Air flows and cabin temperatures for normal operating and 1 pack failure cases ** ON A/C NOT FOR ALL
F AIR flows and cabin temperatures for normal operating and 1 pack failure cases ** ON A/C NOT FOR ALL
F AIR flows and cabin temperatures for normal operating and 1 pack failure cases ** ON A/C NOT FOR ALL
Distribution data for all normal operational cases and important failure cases are shown in table 1. For each case the following data is given:
  • Qt = total fresh airflow to the pressurized fuselage,
  • QFD = fresh airflow to the cockpit,
  • Qc = fresh airflow to the passenger cabin,
  • Qr = recirculation airflow from two recirculation fans,
  • number of cabin occupants,
  • mixed blown air per cabin occupant,
  • fresh air per flight crew member,
  • mixed blown air per flight crew member.
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3. Power Supply
F Power Supply
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4. Interface
The air conditioning system has interfaces with:
The air conditioning system has interfaces with:
The air conditioning system has interfaces with:
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5. Operation/Control and Indicating
A. Failure Indications
F Controls And Indicator Locations
If there is an important failure, indications are shown in the cockpit. The indications can be:
  • the MASTER WARN lights come on and a continuous repetitive chime is heard,
  • the MASTER CAUT lights come on and a single chime is heard,
  • the applicable FAULT light comes on,
  • a warning message on the Upper Display of the Electronic Centralized Aircraft Monitoring System (ECAM) comes on,
  • the applicable page comes on the Lower Display of the ECAM and shows the abnormal condition.
B. Electronic Centralized Aircraft Monitoring (ECAM)
F Air Bleed Display
F Air Cond. Display ** ON A/C NOT FOR ALL
F Air Cond. Display ** ON A/C NOT FOR ALL
F Air Cond. Display ** ON A/C NOT FOR ALL
F Air Cond. Display ** ON A/C NOT FOR ALL
F Cabin Pressure Display ** ON A/C NOT FOR ALL
F Cabin Pressure Display ** ON A/C NOT FOR ALL
F Cruise Display (CAB PRESS IN AUTO) ** ON A/C NOT FOR ALL
F Cruise Display (CAB PRESS IN AUTO) ** ON A/C NOT FOR ALL
F Cruise Display (CAB PRESS IN AUTO) ** ON A/C NOT FOR ALL
F Cruise Display (CAB PRESS IN MAN) ** ON A/C NOT FOR ALL
F Cruise Display (CAB PRESS IN MAN) ** ON A/C NOT FOR ALL
F Cruise Display (CAB PRESS IN MAN) ** ON A/C NOT FOR ALL
The ECAM system is designed to give operational help for both normal and abnormal operations. It is a display system which gives the crew all necessary information on the functioning of the aircraft systems. This operational aid shows messages and system overviews on two Cathode Ray Tubes (CRT'S). The displayed information is used in normal operations for monitoring systems or to help the crew in their diagnosis and corrective actions during abnormal operations.
C. CFDS Displays
The Centralized Fault Display System (CFDS) displays are used by the maintenance personnel for the simplification of failure search. These displays appear on the Multipurpose Control Display Units (MCDU) located in the cockpit, when the maintenance personnel request failure information. The appropriate CFDS messages are shown in the respective ATA subchapter.
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6. Bite Test
The subsequent controllers of the air-conditioning system have Built-In Test Equipment (BITE) installed to monitor the subsystems:
The subsequent controllers of the air-conditioning system have Built-In Test Equipment (BITE) installed to monitor the subsystems:
The subsequent controllers of the air-conditioning system have Built-In Test Equipment (BITE) installed to monitor the subsystems:
The subsequent controllers of the air-conditioning system have Built-In Test Equipment (BITE) installed to monitor the subsystems:
[Rev.10 from 2021] 2026.04.01 06:10:17 UTC
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