Temperature Control - General Diagram
Figure 001
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1CES 1
Cockpit and Cabin Temperature Control System
Figure 002
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Pack Temperature Control-System
Figure 003
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Pack Temperature Control-System
Figure 003A
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R **ON A/C 001-049, 051-099, 101-149, 151-199, 201-299, 301-399,
A. System Description of the ECS The ECS consists of a temperature trim system which has a zone controller and all the necessary valves, sensors and switches to control the air properties in the independent zones. Each of the two air conditioning packs are controlled by its own independent pack controller. All three controllers, the zone controller and the two pack controllers are in fully digital technics and incorporate, in addition to its control function, a Built In Test Equipment (BITE). To further enhance reliability all controllers are equipped with one main and one independent secondary computer. In case of a main computer failure the secondary computer takes over the control automatically and provides the necessary control functions. In normal operation the secondary computer's function is limited to display and monitor system functions. System information, failures and warnings are output from the controllers to be used for display on ECAM and CFDS.
(1) Sub-Systems of the ECS More specific information is available in the following chapters of the ECS:
-Flow Control and Indicating (Ref. 21-51-00),
-Air Cooling System (Ref. 21-52-00),
-Pack Cooling Air Control (Ref. 21-53-00),
-Emergency Ram Air Inlet (Ref. 21-55-00),
-Pack Temperature Control (Ref. 21-61-00),
-Cockpit and Cabin Temperature Control (Ref. 21-63-00).
R **ON A/C 401-499,
A. System Description of the ECS The environmental temperature control is performed via a temperature trim system which consists of all necessary valves, sensors and switches to control the air properties in the independent zones. It is controlled by both Air Conditioning System Controllers (ACSC). Each of the two air conditioning packs are controlled by its own independent ACSC. Both ACSC's are in fully digital technics and incorporate, in addition to its control function, a Built In Test Equipment (BITE). To further enhance reliability and get a high level of redundancy, both ACSC's are equipped with two identical lanes. In case of one lane failure the second lane takes over the entire control automatically and provides all functions. System information, failures and warnings are outputs from the controllers to be used for display on ECAM and CFDS.
(1) Sub-Systems of the ECS More specific information is available in the following chapters of the ECS:
-Flow Control and Indicating (Ref. 21-51-00),
-Air Cooling System (Ref. 21-52-00),
-Pack Cooling Air Control (Ref. 21-53-00),
-Emergency Ram Air Inlet (Ref. 21-55-00),
-Pack Temperature Control (Ref. 21-61-00),
-Cockpit and Cabin Temperature Control (Ref. 21-63-00).
R **ON A/C 001-049, 051-099, 101-149, 151-199, 201-299,
B. System Description of the ECS Control The ECS controls the environment for the three independent zones (flight deck, two passenger zones) with a minimum of crew inputs. The only cockpit and cabin crew activated controls (on the overhead panel 30VU) are:
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the HOT AIR pushbutton switch,
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the COCKPIT temperature selector,
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the FWD CABIN temperature selector,
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the AFT CABIN temperature selector,
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the PACK FLOW selector,
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the PACK 1 pushbutton switch,
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