---------------------------------------------------------------------
| Bit |Data | | Position | | |-------------------------------------------------------------------| | 1-8 |Octal Label 270 | | 9-10 |SDI | | 11-20 |P/N coded in binary (currently 329) | | 21-27 |Version number coded in binary | | 28-29 |Logic 0 | | 30-31 |Logic 0. Set the SSM to NO for a maintenance word | | 32 |Odd parity | ---------------------------------------------------------------------
Table 5 = Discrete Word 1 (Label 270)
---------------------------------------------------------------------| Bit |Data | Bit Status | | Position | | 0 | 1 | |-------------------------------------------------------------------| | 1-8 |Octal Label 271 | | | | 9-10 |SDI | | | | 11-13 |Logic 0 | 0 | | | 14 |EEPROM program memory | Failure | OK | | 15 |Discrete input parity | Failure | OK | | 16 |CPU | Failure | OK | | 17 |ARINC output | Failure | OK | | 18-20 |Logic 1 | | 1 | | 21 |Pressure period range |off.range | OK | | 22 |Temperature period range |off.range | OK | | 23 |Absolute pressure range |off.range | OK | | 24-26 |Logic 1 | | 1 | | 27 |Pressure counter | Failure | OK | | 28 |Temperature counter | Failure | OK | | 29 |Logic 1 | | 1 | | 30-31 |Logic 0. Set the SSM to NO for a | 0 | | | |maintenance word | | | | 32 |Odd parity | | | ---------------------------------------------------------------------
Table 6 = Discrete Word 2 (Label 271)
R 1EFF : 001-049, 101-105, 151-199, 201-203, 1 34-11-00Page 23 1 1 Config-1 May 01/05 1 1 1CES 1 ---------------------------------------------------------------------| Bit |Data | | Position | | |-------------------------------------------------------------------| | 1-8 |Octal Label 377 | | 9-10 |SDI | | 11-24 |Serial Number coded in binary | | 25-29 |Logic 0 | | 30-31 |Logic 0. Set the SSM to NO for a maintenance word | | 32 |Odd parity | ---------------------------------------------------------------------
Table 7 = Hardware Identification word (Label 377)
---------------------------------------------------------------------| Bit |Data | | Position | | |-------------------------------------------------------------------| | 1-8 |Octal Label 040 | | 9-10 |SDI | | 11-12 |Logic 0 | | 13-16 |LSD software version number | | 17-20 |MSD software version number | | 21-24 |LSD manufacturer ident number | | 25-28 |MSD manufacturer ident number | | 29 |Logic 0 | | 30-31 |Logic 0. Set the SSM to NO for a maintenance word | | 32 |Odd parity | ---------------------------------------------------------------------
Table 8 = Software Ident (Label 040)
R 1EFF : 001-049, 101-105, 151-199, 201-203, 1 34-11-00Page 24 1 1 Config-1 May 01/05 1 1 1CES 1
D. Total Air Temperature (TAT) Sensor (Ref. Fig. 008) The aircraft is equipped with two TAT sensors with two sensing elements each. The sensing elements of the sensor have variable resistances. The TAT sensor 1 is linked to the ADR portion of ADIRUs 1 and 3, the TAT sensor 2 is linked to the ADR portion of ADIRU 2. The TAT sensors are set at 2.33 m from the nose and at 0.60 m of the aircraft axis below the fuselage. The TAT sensor 1 is located on the left side and the TAT sensor 2 on the right side. The air flow enters the scoop of the sensor, goes through a calibrated choke and flows over the hermetically sealed platinum resistance sensing element where the temperature is measured. The speed of the flow over the element is controlled by the choke in the element tube. The ADR portion is designed to operate with 500 ohms (at 0 deg. C) temperature sensor unit corresponding to the basic Callender - Van Dusen equation. To improve the accuracy of the sensor, a network of precision resistors is used. This technique is identified by the term Precision Calibration Interchangeability (PCI). These sensors are heated with 115VAC through the probe heating system. The heating element must not be energized on the ground. The heating element is implanted in the scoop and strut and keeps the probe free of ice under the most severe icing conditions.
NOTE : Probe ice protection is described in 30-31-00.
____
R 1EFF : 001-049, 101-105, 151-199, 201-203, 1 34-11-00Page 25 1 1 Config-1 May 01/05 1 1 1CES 1
ADIRS - TAT Sensor
Figure 008
R 1EFF : 001-049, 101-105, 151-199, 201-203, 1 34-11-00Page 26 1 1 Config-1 May 01/05 1 1 1CES 1
E. Angle Of Attack (AOA) Sensor
R **ON A/C 001-049, 101-102, 201-203,
(Ref. Fig. 009)
R **ON A/C 103-105, 151-199,
(Ref. Fig. 009A)
R **ON A/C 001-049, 101-105, 151-199, 201-203,
The aircraft is equipped with three AOA sensors. Two are located on the left side and one on the right side of the fuselage. Each of these AOA sensors is respectively linked to each ADR portion of the ADIRUs. The AOA sensors 1 and 3 are set at 6.08 deg. and 31 deg. below the fuselage datum line (Z = 0) on the left side. The AOA sensor 2 is set at 6.08 deg. below the fuselage datum line (Z = 0) on the right side. The angle of attack sensor is of the wind vane type. Its sensing element is a small wing which is positioned in the direction of airflow. The small wing is mechanically linked to a free turn-shaft which drives the devices transmitting the local angle of attack signal. These transmitting devices are made up of resolver transformers which convert the angular information into proportional electrical information (angle sine and cosine). The resolvers are supplied with a 26VAC signal. The same signal is also received by the ADIRU as a reference for the decoding of AOA values. Each sensor has three resolver outputs but only two are wired to the ADIRU. The whole mechanism is stabilized around the rotation axis. In addition, a damping device enables a satisfactory dynamic response to be obtained (filtering of mechanical oscillation). A self-regulated heating element (CTP resistances: positive coefficient of temperature) inserted into the vane eliminates or avoids icing. It is supplied with 115VAC through the PHC (Ref. 30-31-00). The AOA sensor is equipped with a self-test device which is activated by a 28VDC signal, from the ADR (through the relay 21FP1, 21FP2 or 21FP3) when the test is entered via the maintenance system (CFDIU and MCDU). The self-test positions the vane at a resolver angle of +15 deg. (left side test) or -15 deg. (right side test). The mounting and wing of AOA resolvers determine the relationship between the measured resolver angle and indicated angle of attack. This relationship for each resolver input is as follows: (Ref. Fig. 010)
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 NAVIGATION 導航1(57)
