Zero AOA SSEC discrete
The ADR uses this discrete to select the SSEC as a function of
angle of attack. When this program pin indicates Use SSEC
(open), the SSEC as a function of AOA is computed. When this
program pin indicates Ignore SSEC (ground), the ADR uses zero
correction.
The A/C is wired with this discrete open.
AIR FRM ID Code discrete
The ADR uses input discretes to identify the aircraft (type,
engine model) on which the ADIRU is fitted, and to select the
appropriate set of correction laws for Static Source Error
Correction (SSEC) and AOA corrections.
The ADIRU memory has the capacity to store 128 different sets
of laws.
To perform this coding, the ADR wires seven input discretes
and one discrete for parity to a common.
ADR Remote Test discrete
The ADR uses one discrete to select the remote test by
external control.
When this discrete is open, the test is not activated.
When this discrete is grounded, the test is activated.
The A/C is wired with this discrete open (unused).
The test is activated via the CFDS (Ref. 34-18-00).
R 1EFF : 051-099, 106-149, 204-299, 301-399, 1 34-13-00Page 12 1401-499, 1Config-3 Aug 01/05 1 1 1CES 1 16 ADR OFF DISCR input discrete
__ The ADR uses this discrete input to toggle its state between ON and OFF. When the ADR is OFF, the output buses are disabled and the ADR FAULT legend is inhibited whenever the momentary action ADR pusbutton switch is pushed. When the ADR is ON, the output buses output data and the ADR FAULT legend operates normally. The ADR OFF DISCR input does not modify Air Data computation.
17 Baro Analog/Digital Sel discrete
__ The ADR uses this discrete to select either the analog or digital baro correction. When this discrete is grounded, the analog baro correction is selected. When this discrete is open, the digital baro correction is selected. The A/C is wired with this discrete open.
18 Baro Corr 3 Active discrete
__ The ADR uses this discrete to determine for BITE purposes whether the baro correction 3 is connected or not. When the discrete is grounded, the baro correction 3 is connected. When the discrete is open, the baro correction 3 is not connected. The A/C is wired with this discrete open.
R 1EFF : 051-099, 106-149, 204-299, 301-399, 1 34-13-00Page 13 1401-499, 1Config-3 Aug 01/05 1 1 1CES 1 (3) Acquisition and processing of the sensor inputs
(a) Pressure computation (Ref. Fig. 002) Based on pressure raw data received from the ADM (Ref. para. 2.A.(2)(a)1), the software converts the asynchronous pressure inputs into regularly-scheduled pressure data. During correction of static pressure, the software calculates the limited left, right and average static pressure in a range of 100 to 1100 hPa from the ADM inputs. From the average static pressure (Psm), the software calculates the corrected static pressure based on the SSEC factor:
( G1 G2 ) Psc = Psm (1 + ---- + ----) ( 1000 1000)
-G1 depends on flaps and Mach is interpolated in a table (2 flaps position and 19 Mach values are considered)
-G2 depends on Mach and AOA corrected and is interpolated in a
table (6 AOA values and 18 Mach values are considered). The correct SSEC factor depends on the sensor location and on the aircraft configuration. The ADR memory contains several tables and the appropriate one is selected according to the following input discretes:
. SDI . aircraft Ident . SSEC Alternate.
Two input discretes can be used to force the SSEC factor to be
independent from AOA or Mach: . zero MACH SSEC . zero AOA SSEC.
Ref. Para. 2.A.(2)(c) for more details. R No correction is needed for the total pressure received from the R ADM.
The results of the above computation is available on these output
labels: . label 176 Left Static Pressure . label 177 Right Static Pressure . label 242 Total Pressure . label 245 Averaged Static Pressure . label 246 Corrected Static Pressure
R 1EFF : 051-099, 106-149, 204-299, 301-399, 1 34-13-00Page 14 1401-499, 1Config-3 Aug 01/05 1 1 1CES 1
Pressure Computation - Block Diagram
Figure 002
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(b) Temperature computation (Ref. Fig. 003) The resistance measured by the ADR and compensated for aircraft wiring is then converted into a temperature value (TAT) according to the Callender-Van Dusen equation given for a 500 ohm platinum sensing element:
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