Filter Assembly Figure 014A
R 1EFF : 1 1 1CES 002-049, 051-099, 101-105, 1 111 21-26-00 Page 34 May 01/05
Filter Assembly Figure 014B
R 1EFF : 1 1 1CES 301-399, 401-499, 1 111 21-26-00 Page 35 Aug 01/05
R **ON A/C 001-049, 101-149, 151-199, 201-299,
R Post SB 21-1087 For A/C 001-049,101-105,
M. Filter Assembly (Ref. Fig. 014C) The two-stage filter assembly 2082HM, 2083HM is installed upstream of the blower fan 20HQ. The filter features a centrifugal machine which removes water particules and a 5 micron disposable filter which removes any particule. The filter assembly is designed to allow easy access for cleaning.
**ON A/C ALL
N. Duct Temperature Sensor (Ref. Fig. 015) The duct temperature sensor 26HQ is installed upstream of the aft electronics rack 80VU. It consists of a thermistor mounted in a stainless-steel tube with an electrical connector at the top. If an overheat condition is detected, the indications and actions are the same for the blowing low flow as described in Para. 7.A.(4)(b). The set temperature values are:
-increasing temperatures 62 deg.C (143.6 deg.F) +1 deg.C (+33.8 deg.F),
-decreasing temperatures 60 deg.C (140 deg.F) +1 deg.C (+33.8 deg.F).
P. Pressure Switch (Ref. Fig. 016) Three pressure switches 17HQ, 19HQ and 30HQ are installed in the avionics ventilation system, two in the blowing system and one in the extraction system. The switches are of the capsule/microswitch type with an electrical connector at the top. A low flow indication is given at a differential pressure of 1.7 mbar plus 1.3 or minus 0.5 mbar.
Q. Skin Heat Exchanger A skin heat exchanger is located in the upper fuselage between frames 12 and 14 and is used to cool the avionics ventilation air in normal flight operations. A thermally insulated internal wall is bolted to these frames to form two rectangular ducts. This internal wall is easily removed for structural inspection. A drainage system is included to remove any condensation when the heat exchanger is in operation.
Filter Assembly Figure 014C
R 1EFF : 1 1 1CES 001-049, 101-149, 151-199, 201-299, 1 111 21-26-00 Page 37 May 01/05
Duct Temperature Sensor Figure 015
1EFF : 1 1R 1CES ALL 1 11 1 21-26-00 Page 38 Aug 01/04
Pressure Switches 17HQ/19HQ/30HQ Figure 016
1EFF : 1 1R 1CES ALL 1 11 1 21-26-00 Page 39 Aug 01/04
**ON A/C 001-049, 051-099, 101-105, 151-154, 201-207,
R. Smoke Detector The smoke detector 1WA is installed upstream of the extract fan 18HQ. It is of the duct photo-electrical type used in stand alone mode with an electrical connector for connection to the warning circuits and the AEVC 10HQ (Ref. 26-00-00).
R **ON A/C 106-149, 155-199, 208-299, 301-399, 401-499,
R. Smoke Detector The smoke detector 1WA is installed upstream of the extract fan 18HQ. It is of the duct optical type used in stand alone mode with an electrical connector for connection to the warning circuits and the AEVC 10HQ (Ref. 26-00-00).
**ON A/C ALL
S. Skin Temperature Sensor (Ref. Fig. 017) The skin temperature sensor 28HQ is installed on the inside of the fuselage skin. It consists of a sensor element through which an electrical current passes to measure the potential difference proportional to the temperature. The set temperature values are as follows: - on ground, increasing values +12 deg.C (+53.60 deg.F), decreasing
values +9 deg.C (+48.20 deg.F),
-after takeoff increasing values +35 deg.C (+95.00 deg.F), decreasing values +32 deg.C (+89.60 deg.F).
7. Operation/Control and Indicating
________________________________
A. Operation (Ref. Fig. 004, 005, 018) The avionics equipment is cooled with air supplied in different ways depending on temperature conditions: - open circuit,
-closed circuit,
-partially open circuit,
-cockpit supply air (in failure cases).
Skin Temperature Sensor Figure 017
1EFF : 1 1R 1CES ALL 1 11 1 21-26-00 Page 41 Aug 01/04
Avionics Equipment Ventilation - Operation Table Figure 018
1EFF : 1 1R 1CES ALL 1 11 1 21-26-00 Page 42 Aug 01/04
(1)
Open circuit The avionics equipment is cooled with ambient air when the aircraft is on the ground and the skin temperature is above +12 deg.C (+53.60 deg.F). Ambient air, drawn through the skin air inlet valve 15HQ is blown through the check valve 2150HM and filter assembly 2081HM, 2082HM, 2083HM. The air drawn by the blower fan 20HQ is blown through the check valve 2140HM into the system. The air, after cooling the equipment, is drawn by the extract fan 18HQ directly overboard through the skin air outlet valve 22HQ. The skin heat exchanger is by-passed because the skin exchanger isolation valve 24HQ is closed.
中國航空網 m.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：A320飛機維護手冊 AMM AIR CONDITIONING 空調 1(149)
