AIR DATA - DESCRIPTION AND OPERATION

** ON A/C NOT FOR ALL

1. General
The Air Data Reference (ADR) portion of the Air Data/Inertial Reference Unit (ADIRU) provides main data sources which are air data references for the aircraft avionics systems.
The ADR receives and processes the outputs of the Air Data Modules (ADM) and other sensors (Ref. AMM D/O 34-11-00-00). It computes the aerodynamic parameters in the form of ARINC 429 low speed buses.
For more details concerning the user systems, ref. 34-12-00.

** ON A/C NOT FOR ALL

2. System Description

A. ADR Operation - General
The ADR software performs five basic computational elements which are under the air data calculations as follows:

pressure altitude functions (ALT/ALT rate)
Mach calculation (M)
airspeed calculation (CAS/TAS)
temperature calculation (SAT/TAT)
output signal processing.

Aircraft-dependent calculations are also included in the operational software:

static source error correction
Angle Of Attack (AOA)
maximum operating speed (MMO/VMO).

The system tests include continuous in-flight monitoring and manually-activated test modes. The in-flight monitoring includes test of:

input signal integrity
input interface integrity
memory integrity
computational integrity
output signal integrity.

The continuous monitoring detects and annunciates faults in the ADR during normal operation.
Faults are stored in BITE history EEROM and sent to the Centralized Fault Display System (CFDS) via digital words (Ref. AMM D/O 34-18-00-00).

B. ADR Operation - Back-up Speed and Altitude Scales

Back-Up Speed and Altitude Scale ** ON A/C NOT FOR ALL

When all the ADRs have been switched off by the crew, the back-up speed and altitude scales replace the speed and altitude indications displayed on the Primary Flight Display (PFD).
The barometric altitude is replaced by the Global Positioning System (GPS) altitude:

The GPS ALT indication appears under the altitude scale
The GPS indication is displayed near the GPS altitude.

Since the GPS altitude is less accurate than the barometric altitude, the last two insignificant digits are dashed.
The CAS usually displayed on the PFD is replaced by the median value of the three AOA values coming from the ADRs via the Internal Reference (IR) bus. Contrary to the nominal speed scale, the Back-Up Speed Scale (BUSS) is not graduated but divided into five colored areas (one green area, two amber arrows and two red areas) easily usable and understandable by the pilots. An AOA which is too low means an airspeed that is too fast and the opposite is true too. Moreover, a bug represented by a green arrow indicates the speed to aim at for the pilot.

C. ADR Operation - Digital Inputs

(1) Air Data Modules (ADM) inputs
The ADR receives three input buses from its corresponding ADM. These buses transmit the following input data words depending on the ADM installation:
Label 242 : Total Pressure
Label 176 : Left Static Pressure
Label 177 : Right Static Pressure
Label 245 : Averaged Static Pressure.
Each of these words is a 32-bit word with the following format:

----------------------------------------------------------

! BIT POSITION ! DATA !

----------------------------------------------------------

! 1 - 8 ! Label !

! 9 - 10 ! SDI !

! 11 - 28 ! Pressure Value !

! 29 ! Sign bit (0 = positive) !

! 30 - 31 ! Status matrix !

! 32 ! Parity bit !

----------------------------------------------------------

Table 1 - ADM Input Label

These data words are output on all eight Air Data output data buses and used for calculation of corrected pressure data.

(2) Flight Control Unit (FCU) inputs
The ADR receives one input bus from the FCU, for digital baro corrections.
The FCU output bus sends:

BCD label 234 Baro Correction 1(hPa) for CAPT side

BCD label 236 Baro Correction 2(hPa) for F/O side.

Each ADR receives the two FCU output bus according to the discrete selection as explained in Para. 2.A.(2)(c) (discrete inputs).
Each of these words is a 32-bit BCD word with the following format:

-----------------------------------------------------------

! BIT POSITION ! DATA !

-----------------------------------------------------------

! 1 - 8 ! Label !

! 9 - 10 ! SDI !

! 11 - 28 ! Value !

! 29 ! Sign bit !

! 30 - 31 ! Status matrix !

! 32 ! Parity !

-----------------------------------------------------------

Table 2 - FCU Input Label

(3) Centralized Fault Display Interface Unit (CFDIU) input
For maintenance purposes, the ADR receives one input bus from the CFDIU.
For more details, ref. 34-18-00.

(4) Air Data Reference (ADR) input
Each ADR receives two intercommunication buses from the other ADRs for cross channel comparison purpose.

D. ADR Operation - Analog Inputs

(1) Total Air Temperature (TAT) input
The ADR measures the resistance of the sensing element of the TAT sensor (Ref. 34-11-00).
The ADR subtracts a fixed value function of system number from the measured input resistance to compensate for aircraft wiring resistance.

(2) Angle of Attack (AOA) inputs

AOA/ADR Wiring ** ON A/C NOT FOR ALL

The ADR receives two resolver inputs for angle of attack computation.
The following requirements apply to the analog resolver inputs:

load: 15 kilohms minimum
reference: 26V, 400 Hz (same as AOA)
transformer ratio: 0.415 nominal plus or minus 10 %
phase shift: 24 deg. leading
source impedance:
Zro = A + jB A less than 315, B less than 725
Zso = C + jD C less than 150, D less than 165
electrical range input: plus or minus 60 deg.

(3) Analog baro correction inputs
The ADR receives three resolver inputs for analog baro correction (from the altimeter for example).
These inputs are not used.

E. ADR Operation - Discrete Inputs (Ref. Table 3)
For pin assignment, Ref. 34-12-00.
The ADR is provided with the following input discretes:

----------------------------------------------------------------

! INPUT SIGNAL ! INPUT ! INPUT DEFINITION !

----------------------------------------------------------------

! ADR ARINC Filter Select ! Open/GND ! Type A/Type B !

! CFDS Message Select ! Open/GND ! Active/ Not Active !

! SDI LSB (Middle Insert) ! Open/GND ! 0/1 !

! SDI MSB (Middle Insert) ! Open/GND ! 0/1 !

! Pitot Probe Ht Disc ! Open/GND ! No Fault/Fault !

! Right Static Ht Disc ! Open/GND ! No Fault/Fault !

! Left Static Ht Disc ! Open/GND ! No Fault/Fault !

! TAT Ht Disc ! Open/GND ! Off/On !

! AOA 1 Ht Disc ! Open/GND ! No Fault/Fault !

! AOA Average/Unique ! Open/GND ! Average/Unique !

! VMO/MMO Disc 1 ! Open/GND ! No/Yes !

! VMO/MMO Disc 2 ! Open/GND ! No/Yes !

! VMO/MMO Disc 3 ! Open/GND ! No/Yes !

! VMO/MMO Disc 4 ! Open/GND ! No/Yes !

! SSEC Alternate Disc A ! Open/GND ! No/Yes !

! SSEC Alternate Disc B ! Open/GND ! N0/Yes !

! AOA Alternate Disc 1A ! Open/GND ! Off/On !

! AOA Alternate Disc 1B ! Open/GND ! Off/On !

! AOA Alternate Disc 2A ! Open/GND ! Off/On !

! AOA Alternate Disc 2B ! Open/GND ! Off/On !

! Baro Port "A" ! Open/GND ! Port B/Port A !

! Zero MACH SSEC ! Open/GND ! Use SSEC/Ignore SSEC !

! Zero AOA SSEC ! Open/GND ! Use SSEC/Ignore SSEC !

! AIR FRM ID Code 1/0 ! Open/GND ! No/Yes !

! AIR FRM ID Code 2/0 ! Open/GND ! No/Yes !

! AIR FRM ID Code 4/0 ! Open/GND ! No/Yes !

! AIR FRM ID Code 8/0 ! Open/GND ! No/Yes !

! AIR FRM ID Code 16/0 ! Open/GND ! No/Yes !

! AIR FRM ID Code 32/0 ! Open/GND ! No/Yes !

! AIR FRM ID Code 64/0 ! Open/GND ! No/Yes !

! AIR FRM ID Code Parity ! Open/GND ! No/Yes !

! ADR Remote Test ! Open/GND ! No Test/Test !

! ADR OFF DISCR Input ! Open/GND ! Released/Pressed !

! Dual Baro ! Open/GND ! Sgl Port/Dual Port !

! Baro Analog/Digital Sel.! Open/GND ! Digital/Analog !

! Baro Corr. 3 Active ! Open/GND ! Not Active/Active !

----------------------------------------------------------------

Table 3 - Discrete Input Signal

NOTE: "Open" means either a high logic voltage level or the "binary zero" state.
"GND" means either a low logic voltage level or the "binary one" state.

(1) ADR ARINC Filter Select discrete
This discrete is used to select the characteristics of the ADR output filter.
Two sets of characteristics are available:
Open/Ground = Type A/Type B
Type A : No filtering except for the Altitude Rate (3dB filter bandwidth : 0.17 Hz)
The A/C is defined with the ADR ARINC filter select discrete open.

(2) CFDS Message Select discrete
Open = CFDS message.
When open, this discrete is used to select and display fault messages.

(3) Source Data Identifier (SDI) program pins
These discretes code the installation side of the ADIRU. This item of information is used to choose the appropriate correction laws (for Static Source Error Correction (SSEC) and corrected angle of attack).
The following table gives the ADR side according to the SDI:

--------------------------------------------------------

! DEBOUNCED STATUS ! ! !

!-----------------------------! SDI ! ADIRU !

! SDI-MSB ! SDI-LSB ! CODE ! NUMBER !

!------------------------------------------------------!

! OPEN ! GND ! 01 ! 1 !

! GND ! OPEN ! 10 ! 2 !

! GND ! GND ! 11 ! 3 !

--------------------------------------------------------

Table 4 - ADR SDI Code

(4) sensor heat status discretes
These discrete inputs are used to provide the sensors heat status to the ADR.
These discretes are of the open/ground type.
When the TAT HEAT DISC is grounded, the TAT sensor is heated.
When one of the STATIC, PITOT or AOA HEAT discretes is grounded, it means that the output of the Probe Heat Computer (PHC) heating power supply is faulty and that the concerned probe is no longer heated.
In this case, the ADR operates as a relay which sends these information signals to the FWC for warning purposes.

(5) AOA Average/Unique program pin
The ADR uses the AOA Average/Unique program pin to determine whether one or two angle of attack resolver inputs are used for angle of attack computations. When this program pin indicates "Unique", the ADR uses only a single angle of attack input.
If this first AOA input fails, the ADR uses the opposite AOA input, as shown in table 5 below. When this program pin indicates "Average", the ADR calculates angle of attack based on the average of the angle of attack inputs 1 and 2.

-------------------------------------------------------

! SYSTEM ! INITIAL NON-FAULT ! INPUT TO ADR !

! NUMBER ! INPUT TO ADR ! AFTER FAULT !

-------------------------------------------------------

! 1 ! input number 1 ! input number 2 !

! 2 ! input number 2 ! input number 1 !

! 3 ! input number 1 ! input number 2 !

-------------------------------------------------------

Table 5 - AOA Resolver Input

The characteristics of these discretes are OPEN/GROUND = AVERAGE/UNIQUE.
The A/C is defined with the AOA average/unique discrete grounded.

(6) VMO/MMO Program Discretes 1 through 4
These discretes are used to select alternate VMO/MMO levels. There are four alternates and a basic VMO/MMO for each aircraft type. Table 6 below defines VMO/MMO versus state of the VMO/MMO program discretes.
With no VMO/MMO discretes in the ground state (yes) the ADR defaults to the BASIC LAW values for VMO/MMO.
Only one of the four VMO/MMO program discretes can be in the ground state at any one time.
If more than one VMO/MMO program discrete is in the ground state at any one time, the ADR defaults to the lowest available alternate condition.

(7) on the A/C only the VMO/MMO DISC 2 is available and is provided by the L/G DOWN VMO/MMO SELECTION switch 22FP.
The normal position of this switch is open and it is grounded after crew action for particular flights (ferry flight for example).
Table 6 below defines VMO/MMO state according to the position of the switch 22FP.

----------------------------------------------------------

! ! VMO ! MMO ! SWITCH !

! LAW ! (kts) ! (Mach) ! 22FP !

----------------------------------------------------------

! BASIC ! 350 ! 0.82 ! OPEN !

! ALT 1 * ! 235 ! 0.60 ! N/A !

! ALT 2 ! 235 ! 0.60 ! GROUND !

! ALT 3 * ! 235 ! 0.60 ! N/A !

! ALT 4 * ! 235 ! 0.60 ! N/A !

----------------------------------------------------------

* Spare. Default value included for safety and BITE purpose.

Table 6 - VMO/MMO Selection

(8) SSEC Alternate discrete
The ADR is provided with two Static Source Error Correction (SSEC) data sets to be stored in the computer, for each SDI and each aircraft type, one for use in "normal" conditions and one for use in "alternate" conditions.
With the two SSEC selection discretes open (no), the ADR employs the "normal" SSEC curve for the aircraft type in which it is installed. With the two SSEC selection discretes grounded (yes), the ADR employs the "alternate" condition curve.

(9) AOA Alternate discrete
The ADR uses the alternate discrete inputs from the two redundant SFCCs to select the angle of attack correction which is appropriate for the current slat and flap settings.
Three laws are available for each aircraft type and SDI:

the normal law is activated when all the discretes are open,
the alternate 1 law is activated when discretes 1A and 2A are grounded,
the alternate 2 law is activated when discretes 1A, 2A, 1B and 2B are grounded.

(10) Baro Port A discrete
The ADR uses this discrete to select which ARINC 429 port is used as a source for all baro-correction input data.
If this discrete is grounded, the baro port A is selected.
If this discrete is open, the baro port B is selected.
The A/c is wired with this discrete grounded (Ref. Dual Baro discrete).

(11) Dual Baro discrete
The ADR uses this discrete to select which ARINC 429 port is used as a source for all baro-correction input data.
If this discrete is grounded, the baro port A and the baro port B are selected and the baro port A discrete selection is overriden. If this discrete is open, the baro port A or the baro port B is selected depending on the baro port A discrete selection. The A/C is wired with this discrete open.

(12) Zero MACH SSEC discrete
The ADR uses this discrete to select the SSEC as a function of Mach. When this program pin indicates Use SSEC (open), the SSEC as a function of Mach is computed. When this program pin indicates Ignore SSEC (ground), the ADR uses zero correction.
The A/C is wired with this discrete open.

(13) 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.

(14) 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.

(15) 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 CFDIU (Ref. AMM D/O 34-18-00-00).

(16) ADR OFF DISCR input discrete
The ADR uses this discrete input to toggle its state between ON and OFF at each press on the momentary contact switch. When the ADR is OFF, the output buses are disabled and the ADR FAULT annunciator is inhibited (reset if already set).

(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.

F. ADR Operation - Acquisition and Processing of the Sensor Inputs

Pressure Computation - Block Diagram ** ON A/C NOT FOR ALL

CAS/Mach Computation - Block Diagram ** ON A/C NOT FOR ALL

(1) Pressure computation
Based on pressure data received from the ADM (Ref. para. 2.A.(2)(a)1), the software converts the pressure inputs into corrected pressure data.
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 19 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.
During correction of total pressure, the software calculates the limited total pressure in a range of 100 to 1400hPa from the ADM inputs.
From the measured total pressure (Ptm) and the measured static pressure (Psm), the software calculates a corrected total pressure:

(Ptm + Psm)

Pt = Ptm + --------------- X 0.38

Psm

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

(2) Temperature computation
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:

- -

! 3!

Rt ! (TAT ) (TAT ) (TAT ) (TAT) !

-- = 1 + a ! TAT - d (--- -1) (--- ) - b (--- -1) (---) !

Ro ! (100 ) (100 ) (100 ) (100) !

- -

TAT = temperature in deg.C

Rt = Resistance at temperature TAT

Ro = Resistance at 0 deg.C = 500 ohm

a = 0.003832

d = 1.81

b = 0.1 for temperature below 0 deg.C

b = 0 for temperature above 0 deg.C

The computation also compensates the TAT value for heating effect. The ADR knows when the sensor is heated by the state of the TAT Heat input discrete from the PHC. The heating compensation law is provided by the TAT sensor supplier and is function of Mach and air density.
The PHC 1 controls the heating of the TAT sensor 1 and the PHC 2 controls the heating of the TAT sensor 2. On the ground, the sensors are not heated (Ref. 30-31-00 for more details).
The result of the above computation is available on the following output labels:

label 211 Total Air Temperature (BNR)
label 231 Total Air Temperature (BCD).

(3) AOA computation
The A/C is wired in the AOA unique selection, so the ADR computes the AOA with the reading of one resolver. The second resolver is used as a back-up. The monitoring function is described in 34-18.
The ADR determines the corrected angle of attack value which depends on the system number and the slat/flap position.
For a CAS less than 60 kts: AOAc is still computed but coded NCD.
The corrected angle of attack is calculated as follows:

AOA ind

AOAc = ------- + I

where:

AOA ind = Indicated Angle of Attack (Ref. 34-11-00 for the

relation between resolver and AOA indication)

K, I = Correction coefficients which depend on system

number, slat and flap configuration and magnitude

AOA indication.

The configuration is defined by the status of four input discretes (Ref. 2.A.(2)(c)).
The results of the above computation is available on the labels:

label 221 = Indicated Angle of Attack
label 241 = Corrected Angle of Attack

G. ADR Operation - Parameter Computation

(1) General
The operational software of the ADR performs the following computations:

pressure altitude and pressure altitude rate function (ALT)
Mach function (M)
airspeed function (CAS/TAS)
temperature function (SAT/TAT)
maximum operating speed function (VMO/MMO).

(2) Altitude computation
The ADR software computes these different parameters:

label 203 Altitude

label 212 Altitude Rate (BNR)

label 204 Baro Corrected Altitude 1 (CAPT)

label 220 Baro Corrected Altitude 2 (F/O)

label 232 Altitude rate (BCD)

(a) Altitude and altitude rate computation
The altitude is derived from the corrected static pressure.
Standard altitude is computed as :

* For Ps graeter or equal to 226,323 hPa

0,190263

Altitude = 145442,156 * (1- (Ps / Po) )

* For Ps < 226,323 hPa

Altitude = 148897,4 - 47907,18 * Log (Ps)

with Ps = Corrected Static Pressure

Po = Standard day sea level pressure (1013,25 hPa)

The accepted range is (-2000 ft, +50.000 ft).
The altitude rate is calculated by multiplying the rate of change of the corrected static pressure by the derivative of altitude with respect to corrected static pressure:

dH d Ps dH

-- = ---- x ----

dt dt d Ps

(b) Corrected altitude computation
The ADR receives the baro correction introduced on the FCU by each crew member. The ADR uses the values in hPa (labels 234 and 236 from the FCU).
The corrected altitude is calculated by a shift of the pressure altitude to a value corresponding to the entered baro correction. The result is sent on label 204 for CAPT baro corrected altitude and label 220 for F/O baro corrected altitude.

(3) CAS/Mach computation
The ADR software computes these different parameters:
label 206 Computed Airspeed
label 205 Mach
label 207 Maximum Allowable Airspeed.
The CAS and Mach computation is based on the conversion of the impact pressure:
impact pressure = Pt - Ps.

the CAS computation converts input of impact pressure to output corresponding to computed airspeed with:

_______________________

/ Qc 2/7

CAS = Cso X V 5 X ((-- + 1) - 1)

CAS = Computed Airspeed in knots

Cso = Speed of sound under standard day sea level

conditions = 661.4746 kts

Qc = Impact pressure in hPa

Po = Standard day sea level pressure = 1013.25 hPa

For accuracy reason, the CAS is output with a valid (NO) SSM only after 30 kts. If the CAS is below 30 kts, the label 206 indicates 0 kt with SSM = NCD.

the Mach computation converts Qc/Ps to Mach, with:

_______________________

/ Qc 2/7

MACH = V 5 ((-- + 1) - 1)

MACH = Mach number

Qc/Ps = Ratio of impact pressure to static pressure

If Mach is below 0.1, the label 205 indicates 0 with SSM = NCD.

(4) SAT/TAS computation
The ADR software calculates these different parameters:
label 213 BNR Static Air Temperature (SAT)
label 233 BCD Static Air Temperature (SAT)
label 210 BNR True Airspeed (TAS)
label 230 BCD True Airspeed (TAS).

the calculation of the BNR SAT converts TAT to SAT with:

TAT

SAT = --------- - 273.15

1 + 0.2M

SAT = Static Air Temperature (in deg. C)

TAT = Total Air Temperature (in deg. Kelvin)

M = Mach number (corrected for static source error)

the calculation converts Static Air Temperature from BNR to BCD format.

the calculation of the BNR TAS converts Mach and SAT to TAS with:

___

TAS = 38.96695 x M x V SAT

TAS = True Airspeed (in knots)

M = Mach Number (corrected for Static Source Error)

SAT = Static Air Temperature (in deg. Kelvin)

the calculation converts True Airspeed from BNR to BCD format.
For accuracy reason, the TAS is output with a valid (NO) SSM only after 60 kts. If TAS is below 60 kts, the label 210 indicates 0 kt with SSM = NCD.

(5) VMO/MM0 computation
The software determines the normal or alternate VMO/MMO law selected by the VM0/MM0 input 2 discrete state; then it computes the label 207 Maximum Allowable Airspeed.
This airspeed is based on the Maximum Allowable Airspeed under a certain altitude and on the Maximum Allowable Mach above this altitude. It is always indicated in knots and decreases when the altitude increases.

NOTE: At a constant Mach, the Vc value decreases when the altitude increases.

H. ADR Operation - ADR Data Outputs
The ADR data outputs are transmitted in two forms: digital and discrete.

(1) Digital form
The table below contains all the output parameters in the digital form.
They are sorted as per the numerical order of their output label.
The following table gives:

EQ.SYS.LAB.SDI : (SDAC, FWC, DMC...) output label for which the parameter is available
PARAMETER DEFINITION: parameter name
RANGE ACCURACY : measurement range maximum value transmitted. When the digital value changes, the change step is equal to the accuracy
UNIT : unit in which the digital value is transmitted
SIG BIT : indicates whether a sign bit is available
BITS : number of bits used by the parameter in the label
UPD/MSEC : output transmission interval. The refresh rate is given in milliseconds.
CODE:
BNR: binary data word
BCD: binary coded decimal data word
ISO: data word coded in ISO5 code
DIS: discrete data word
HEX: hexadecimal coded
HYB: mixed code.
ALPHA CODE: indicates the parameter mnemonic code
SOURCE ORIGIN: parameter source computer or system.

(2) Digital form - Labels table (Part 1)

-------------------------------------------------------------------------------

| PARAMETER LIST PARAMETER CHARACTERISTICS (NUMERIC) |

-------------------------------------------------------------------------------

-------------------------------------------------------------------------------

! 047 !S/W IDENT ! ! ! ! !1000!BCD ! ! !

!--------------!----------!------------!----!----!----!----!----!-----!-------!

! 176 !L STATIC !W2048 !hPa ! ! 18 !125 !BNR ! ! !

! !PRESSURE !100 to 1100 ! ! ! ! ! ! ! !

! ! !R 0.0078 ! ! ! ! ! ! ! !

! ! !+/- 0.30 ! ! ! ! ! ! ! !

!--------------!----------!------------!----!----!----!----!----!-----!-------!

! 177 !R STATIC !W2048 !hPa ! ! 18 !125 !BNR ! ! !

! !PRESSURE !100 to 1100 ! ! ! ! ! ! ! !

! ! !R 0.0078 ! ! ! ! ! ! ! !

! ! !+/- 0.30 ! ! ! ! ! ! ! !

!--------------!----------!------------!----!----!----!----!----!-----!-------!

! 203 !STANDARD !W+/- 131072 ! ft ! 29 ! 17 ! 62 !BNR ! ALT ! !

! !ALTITUDE !-2000 to ! ! ! ! ! ! ! !

! ! ! 50000 ! ! ! ! ! ! ! !

! ! !R 1 ! ! ! ! ! ! ! !

! ! !+/-40 ! ! ! ! ! ! ! !

! ! !(30,000) ! ! ! ! ! ! ! !

!--------------!----------!------------!----!----!----!----!----!-----!-------!

! 204 !BARO CORR !W+/- 131072 ! ft ! 29 ! 17 ! 62 !BNR ! ! !

! !ALT 1 !-2000 to ! ! ! ! ! ! ! !

! ! ! 50000 ! ! ! ! ! ! ! !

! ! !R 1 ! ! ! ! ! ! ! !

! ! !+/-47 ! ! ! ! ! ! ! !

! ! !(30,000) ! ! ! ! ! ! ! !

!--------------!----------!------------!----!----!----!----!----!-----!-------!

! 205 !MACH !W4096 !Mach! ! 16 !125 !BNR ! MN ! !

! ! !0.1 to 1.00 ! ! ! ! ! ! ! !

! ! !R 6.25 E-5 ! ! ! ! ! ! ! !

! ! !+/-0.015 ! ! ! ! ! ! ! !

! ! !(0.1) ! ! ! ! ! ! ! !

!--------------!----------!------------!----!----!----!----!----!-----!-------!

! 206 !COMPUTED !W1024 !Kts ! ! 14 !125 !BNR ! CAS ! !

! !AIRSPEED !30 to 450 ! ! ! ! ! ! ! !

! ! !R 0.0625 ! ! ! ! ! ! ! !

! ! !2 (100) ! ! ! ! ! ! ! !

!--------------!----------!------------!----!----!----!----!----!-----!-------!

! 207 !MAXIMUM !W1024 !Kts ! ! 12 !125 !BNR ! ! !

! !ALLOWABLE !150 to 450 ! ! ! ! ! ! ! !

! !AIRSPEED !R 0.25 ! ! ! ! ! ! ! !

! ! !+/- 1 ! ! ! ! ! ! ! !

!--------------!----------!------------!----!----!----!----!----!-----!-------!

! 210 !TRUE !W2048 !Kts ! ! 15 !125 !BNR ! ! !

! !AIRSPEED !60 to 599 ! ! ! ! ! ! ! !

! ! !R 0.0625 ! ! ! ! ! ! ! !

! ! !+/- 4 ! ! ! ! ! ! ! !

!--------------!----------!------------!----!----!----!----!----!-----!-------!

! 211 !TOTAL AIR !W +/- 512 !Deg.! 29 ! 11 !500 !BNR ! TAT ! !

! !TEMP !-60 to +100 !C ! ! ! ! ! ! !

! ! !R 0.25 ! ! ! ! ! ! ! !

! ! !+/- 0.5 ! ! ! ! ! ! ! !

!--------------!----------!------------!----!----!----!----!----!-----!-------!

! 212 !ALTITUDE !W+/- 32768 !ft/ ! 29 ! 11 ! 62 !BNR ! ! !

! !RATE !+/- 20000 !mn ! ! ! ! ! ! !

! ! !R 2 ! ! ! ! ! ! ! !

! ! !+/- 30 ! ! ! ! ! ! ! !

!--------------!----------!------------!----!----!----!----!----!-----!-------!

! 213 !STATIC AIR!W+/- 512 !Deg.! 29 ! 11 !500 !BNR ! SAT ! !

! !TEMP !-99 to +80 !C ! ! ! ! ! ! !

! ! !R 0.25 ! ! ! ! ! ! ! !

! ! !+/- 1 ! ! ! ! ! ! ! !

!--------------!----------!------------!----!----!----!----!----!-----!-------!

! 215 !IMPACT !W512 !hPa ! ! 16 !125 !BNR ! ! !

! !PRESSURE !0 to 372.5 ! ! ! ! ! ! ! !

! ! !R 0.0078 ! ! ! ! ! ! ! !

! ! !+/- 0.25 ! ! ! ! ! ! ! !

!--------------!----------!------------!----!----!----!----!----!-----!-------!

! 220 !BARO CORR !W +/- 131072! ft ! 29 ! 17 ! 62 !BNR ! ! !

! !ALT 2 !-2000 to ! ! ! ! ! ! ! !

! ! ! 50000 ! ! ! ! ! ! ! !

! ! !R 1 ! ! ! ! ! ! ! !

! ! !47 (30,000) ! ! ! ! ! ! ! !

!--------------!----------!------------!----!----!----!----!----!-----!-------!

! 221 !IND ANGLE !W +/- 180 !Deg.! 29 ! 12 ! 62 !BNR ! ! !

! !OF ATTACK !-40 to +90 ! ! ! ! ! ! ! !

! ! !R 0.0439 ! ! ! ! ! ! ! !

! ! !+/- 0.25 ! ! ! ! ! ! ! !

!--------------!----------!------------!----!----!----!----!----!-----!-------!

! 230 !TRUE !W +/- 799 !Kts ! ! 3 !500 !BCD ! ! !

! !AIRSPEED !60 to 599 ! ! ! ! ! ! ! !

! ! !R 1 ! ! ! ! ! ! ! !

! ! !+/- 4 ! ! ! ! ! ! ! !

!--------------!----------!------------!----!----!----!----!----!-----!-------!

! 231 !TOTAL AIR !W +/- 799 !Deg.! ! 2 !500 !BCD ! ! !

! !TEMP !-60 to +100 !C ! ! ! ! ! ! !

! ! !R 1 ! ! ! ! ! ! ! !

! ! !+/- 0.5 ! ! ! ! ! ! ! !

!--------------!----------!------------!----!----!----!----!----!-----!-------!

! 232 !ALTITUDE !W +/- 79999 !ft/ ! ! 5 !500 !BCD ! ! !

! !RATE !0 TO !mn ! ! ! ! ! ! !

! ! !+/- 20,000 ! ! ! ! ! ! ! !

! ! !R 1 ! ! ! ! ! ! ! !

! ! !+/- 30 ! ! ! ! ! ! ! !

!--------------!----------!------------!----!----!----!----!----!-----!-------!

! 233 !STATIC AIR!W +/- 799 !Deg.! ! 2 !500 !BCD ! ! !

! !TEMP !-99 to +80 !C ! ! ! ! ! ! !

! ! !R 1 ! ! ! ! ! ! ! !

! ! !+/- 1 ! ! ! ! ! ! ! !

!--------------!----------!------------!----!----!----!----!----!-----!-------!

! 234 !BARO !W +/- 7999.9!hPa ! ! 5 !500 !BCD ! ! !

! !CORRECT 1 !745 to 1100 ! ! ! ! ! ! ! !

! ! !R 0.1 ! ! ! ! ! ! ! !

! ! !+/- 0.25 ! ! ! ! ! ! ! !

!--------------!----------!------------!----!----!----!----!----!-----!-------!

! 235 !BARO !W +/- 79.999!inHg! ! 5 !500 !BCD ! ! !

! !CORRECT 1 !22.0 to 32.5! ! ! ! ! ! ! !

! ! !R 0.001 ! ! ! ! ! ! ! !

! ! !+/- 0.0074 ! ! ! ! ! ! ! !

!--------------!----------!------------!----!----!----!----!----!-----!-------!

! 236 !BARO !W +/- 7999.9!hPa ! ! 5 !500 !BCD ! ! !

! !CORRECT 2 !745 to 1100 ! ! ! ! ! ! ! !

! ! !R 0.1 ! ! ! ! ! ! ! !

! ! !+/- 0.25 ! ! ! ! ! ! ! !

!--------------!----------!------------!----!----!----!----!----!-----!-------!

! 237 !BARO !W +/- 79.999!inHg! ! 5 !500 !BCD ! ! !

! !CORRECT 2 !22.0 to 32.5! ! ! ! ! ! ! !

! ! !R 0.001 ! ! ! ! ! ! ! !

! ! !+/- 0.0074 ! ! ! ! ! ! ! !

!--------------!----------!------------!----!----!----!----!----!-----!-------!

! 240 !VMO/MMO ! ! ! ! !500 !BCD ! ! !

!--------------!----------!------------!----!----!----!----!----!-----!-------!

! 241 !CORRECTED !W +/- 180 !Deg.! 29 ! 12 ! 62 !BNR ! AOA ! !

! !ANGLE OF !-40 to +90 ! ! ! ! ! ! ! !

! !ATTACK !R 0.0439 ! ! ! ! ! ! ! !

! ! !+/- 0.25 ! ! ! ! ! ! ! !

!--------------!----------!------------!----!----!----!----!----!-----!-------!

! 242 !TOTAL !W2048 !hPa ! ! 18 !125 !BNR ! ! !

! !PRESSURE !100 to 1400 ! ! ! ! ! ! ! !

! ! !R 0.0078 ! ! ! ! ! ! ! !

! ! !+/- 0.30 ! ! ! ! ! ! ! !

!--------------!----------!------------!----!----!----!----!----!-----!-------!

! 245 !UNCRCTD !W2048 !hPa ! ! 18 !125 !BNR ! ! !

! !AVG STAT !100 to 1100 ! ! ! ! ! ! ! !

! !PRESSURE !R 0.0078 ! ! ! ! ! ! ! !

! ! !+/- 0.30 ! ! ! ! ! ! ! !

!--------------!----------!------------!----!----!----!----!----!-----!-------!

! 246 !CORCTD !W2048 !hPa ! ! 18 !125 !BNR ! ! !

! !AVG STAT !100 to 1100 ! ! ! ! ! ! ! !

! !PRESSURE !R 0.0078 ! ! ! ! ! ! ! !

! ! !+/- 0.30 ! ! ! ! ! ! ! !

!--------------!----------!------------!----!----!----!----!----!-----!-------!

! 270 !DSCT WORD ! ! ! ! !500 !DIS ! ! !

! ! 1 ! ! ! ! ! ! ! ! !

!--------------!----------!------------!----!----!----!----!----!-----!-------!

! 271 !DSCT WORD ! ! ! ! !500 !DIS ! ! !

! ! 2 ! ! ! ! ! ! ! ! !

!--------------!----------!------------!----!----!----!----!----!-----!-------!

! 272 !DSCT WORD ! ! ! ! !500 !DIS ! ! !

! ! 3 ! ! ! ! ! ! ! ! !

!--------------!----------!------------!----!----!----!----!----!-----!-------!

! 277 !ADR TEST ! ! ! ! !1000!DIS ! ! !

!--------------!----------!------------!----!----!----!----!----!-----!-------!

! 352 !DSCT WORD ! ! ! ! !1000!DIS ! ! !

! ! 4 ! ! ! ! ! ! ! ! !

!--------------!----------!------------!----!----!----!----!----!-----!-------!

! 354 !LRU IDENT ! ! ! ! !500 !ISO ! ! !

!--------------!----------!------------!----!----!----!----!----!-----!-------!

! 356 ! CFDIU ! ! ! ! ! !ISO ! ! !

! !INTFC WORD! ! ! ! ! ! ! ! !

!--------------!----------!------------!----!----!----!----!----!-----!-------!

! 377 !EQPT IDENT! ! ! ! !1000!HEX ! ! !

-------------------------------------------------------------------------------

Table 7 - Output Label

(3) Digital form - Labels table (Part 2)

-------------------------------------------------------------------------

! BIT N° ! FUNCTION !

-------------------------------------------------------------------------

! 11 !--- !

! 12 ! ! LSD --- !

! 13 ! ! ! !

! 14 !--- ! Program Modification xx !

! 15 !--- ! !

! 16 ! ! MSD --- !

! 17 ! ! !

! 18 !--- !

! 19 !--- !

! 20 ! ! LSD ----- !

! 21 ! ! ! !

! 22 !--- ! !

! 23 !--- ! !

! 24 ! ! MSD --! Program Version xx !

! 25 ! ! !

! 26 !--- !

! 27 ! 0 !

! 28 ! 0 !

! 29 ! 0 !

-------------------------------------------------------------------------

Table 8 : Label 047 - S/W Ident

-------------------------------------------------------------------------

! BIT N° ! FUNCTION !

-------------------------------------------------------------------------

! 11 !--- !

! 12 ! ! Least significant (Hundredths) digit of MMO !

! 13 ! ! !

! 14 !--- !

! 15 !--- !

! 16 ! ! Most significant (Tenths) digit of MMO !

! 17 ! ! !

! 18 !--- !

! 19 !--- !

! 20 ! ! Least significant (Units) BCD digit of VMO !

! 21 ! ! !

! 22 !--- !

! 23 !--- !

! 24 ! ! Middle (Tens) BCD digit of VMO !

! 25 ! ! !

! 26 !--- !

! 27-28 !--- Most significant (Hundreds) BCD digit of VMO !

-------------------------------------------------------------------------

Table 9 : Label 240 - VMO/MMO

--------------------------------------------------------------------------

! BIT N° ! FUNCTION ! 1 = GND ! 0 = OPEN !

--------------------------------------------------------------------------

! 11 ! Icing Detector Heat ! NO FAULT ! FAULT !

! 12 ! Pitot Probe Heat ! NO FAULT ! FAULT !

! 13 ! ADR FAULT ! FAULT ! NO FAULT !

! 14 ! Right Static Heat ! NO FAULT ! FAULT !

! 15 ! Left Static Heat ! NO FAULT ! FAULT !

! 16 ! TAT Heat ! HEAT ! NO HEAT !

! 17 ! AOA 1 Heat ! NO FAULT ! FAULT !

! 18 ! AOA 2 Heat ! NO FAULT ! FAULT !

! 19 ! Overspeed Warning ! WARN ! NO WARN !

! 20 ! Spare (Primary AOA Fault) ! ! !

! 21 ! AOA Average/Unique ! UNIQUE ! AVERAGE !

! 22 ! VMO/MMO 1 ! YES ! NO !

! 23 ! VMO/MMO 2 ! YES ! NO !

! 24 ! VMO/MMO 3 ! YES ! NO !

! 25 ! VMO/MMO 4 ! YES ! NO !

! 26 ! SSEC Alternate Select 1 ! YES ! NO !

! 27 ! SSEC Alternate Select 2 ! YES ! NO !

! 28 ! Baro Port A Select ! Port A ! Port B !

! 29 ! Zero Mach SSEC Select ! YES ! NO !

--------------------------------------------------------------------------

Table 10 : Label 270 - Discrete Word 1

--------------------------------------------------------------------------

! BIT N° ! FUNCTION ! 1 = GND ! 0 = OPEN !

--------------------------------------------------------------------------

! 11 ! Zero AOA SSEC Select ! YES ! NO !

! 12 ! AOA Test Active ! ACTIVE ! NOT !

! 13 ! Low Speed Warning 1 ! FAST ! SLOW !

! 14 ! Low Speed Warning 2 ! FAST ! SLOW !

! 15 ! Low Speed Warning 3 ! FAST ! SLOW !

! 16 ! Low Speed Warning 4 ! SLOW ! FAST !

! 17 ! Spare ! ! !

! 18 ! Spare ! ! !

! 19 ! Spare ! ! !

! 20 ! AOA Correction 1A ! YES ! NO !

! 21 ! AOA Correction 1B ! YES ! NO !

! 22 ! AOA Correction 2A ! YES ! NO !

! 23 ! AOA Correction 2B ! YES ! NO !

!24 to 29! Spare ! ! !

--------------------------------------------------------------------------

Table 11 : Label 271 - Discrete Word 2

--------------------------------------------------------------------------

! BIT N° ! FUNCTION ! 1 = GND ! 0 = OPEN !

--------------------------------------------------------------------------

! 11 ! SDI 2 ! GROUND ! OPEN !

! 12 ! SDI 1 ! GROUND ! OPEN !

! 13 ! Dual Baro Select ! INPUT A ! INPUT B !

! 14 ! Analog Baro Select ! YES ! NO !

! 15 ! Spare IDSC 1 ! GROUND ! OPEN !

! 16 ! Spare IDSC 2 ! GROUND ! OPEN !

! 17 ! Spare IDSC 3 ! GROUND ! OPEN !

! 18 ! Baro 3 Present ! PRESENT ! ABSENT !

! 19 ! Spare IDSC 4 ! GROUND ! OPEN !

! 20 ! CFDS Select ! NOT ACTI.! ACTIVE !

! 21 ! ADR Filter Select ! FILTERED ! NOT !

! 22 ! BITE Memory Clear Enable ! ENABLE ! DISABLE !

! 23 ! BITE Write Inhibit ! INHIBIT ! ENABLE !

! 24 ! ADR Interface Test ! TEST ! NORMAL !

! 25 ! ADR Off Command ! GROUND ! OPEN !

! 26 ! Reserved ! ! !

! 27 ! ADR On/Off Status ! On ! Off !

! 28 ! Spare ! ! !

! 29 ! Spare ! ! !

--------------------------------------------------------------------------

Table 12 : Label 272 - Discrete Word 3

-------------------------------------------------------------------------

! ! Test Pattern ! !

! BIT N° ! 0 ! 1 ! FT ! !

-------------------------------------------------------------------------

! 11 ! 0 ! 1 ! 1 ! !

! 12 ! 1 ! 0 ! 1 ! !

! 13 ! 0 ! 1 ! 1 ! !

! 14 ! 1 ! 0 ! 1 ! !

! 15 ! 0 ! 1 ! 1 ! !

! 16 ! 1 ! 0 ! 1 ! !

! 17 ! 0 ! 1 ! 1 ! !

! 18 ! 1 ! 0 ! 1 ! !

! 19 ! 0 ! 1 ! 1 ! !

! 20 ! 1 ! 0 ! 1 ! Test patterns 0 and 1 alternate !

! 21 ! 0 ! 1 ! 1 ! every other transmission. The FT !

! 22 ! 1 ! 0 ! 1 ! test pattern is used when the !

! 23 ! 0 ! 1 ! 1 ! interface test discrete is set. !

! 24 ! 1 ! 0 ! 1 ! !

! 25 ! 0 ! 1 ! 1 ! !

! 26 ! 1 ! 0 ! 1 ! !

! 27 ! 0 ! 1 ! 1 ! !

! 28 ! 1 ! 0 ! 1 ! !

! 29 ! 0 ! 1 ! 1 ! !

! 30 ! 0 ! 1 ! 0 ! !

! 31 ! 0 ! 1 ! 1 ! !

! 32 ! P ! ! ! !

-------------------------------------------------------------------------

Table 13 : Label 277 - ADR test word

-------------------------------------------------------------------------

! BIT N° ! FUNCTION ! 1 = GND ! 0 = OPEN !

-------------------------------------------------------------------------

! 11 ! A/C ID Code 32/0 ! GROUND ! OPEN !

! 12 ! A/C ID Code 64/0 ! GROUND ! OPEN !

!13 to 23! Spare ! ! !

! 24 ! A/C ID Code 1/0 ! GROUND ! OPEN !

! 25 ! A/C ID Code 2/0 ! GROUND ! OPEN !

! 26 ! A/C ID Code 4/0 ! GROUND ! OPEN !

! 27 ! A/C ID Code 8/0 ! GROUND ! OPEN !

! 28 ! A/C ID Code 16/0 ! GROUND ! OPEN !

! 29 ! A/C ID Parity ! GROUND ! OPEN !

-------------------------------------------------------------------------

Table 14 : Label 352 - Discrete Word 4

-------------------------------------------------------------------------

! BIT N° ! FUNCTION !

-------------------------------------------------------------------------

! 11 ! = 0 -- !

! 12 ! = 1 ! LSD = 6 !

! 13 ! = 1 ! !

! 14 ! = 0 -- !

! 15 ! = 0 -- !

! 16 ! = 0 ! MSD = 0 !

! 17 ! = 0 ! !

! 18 ! = 0 -- !

!19 to 29! Spare !

-------------------------------------------------------------------------

Table 15 : Label 377 - Equipment Ident

(4) Digital form - Labels table (on ground)

On the ground the output labels are in the following state:

------------------------------------------------------------------------------

! LABEL ! PARAMETER DEFINITION ! SSM ! ON GND CRITERION !

------------------------------------------------------------------------------

! 047 ! S/W Ident ! NO ! !

! 203 ! Altitude ! NO ! !

! 204 ! Baro Corr Alt 1 ! NO ! !

! 220 ! Baro Corr Alt 2 ! NO ! !

! 251 ! Baro Corr Alt 3 ! NO ! !

! 205 ! Mach ! NCD ! 0 Mach less than 0.1 !

! 206 ! Computed Airspeed ! NCD ! 0 kt CAS less than 30 kts !

! 207 ! Max Allowable Airspeed ! NO ! !

! 210 ! True Airspeed ! NCD ! 0 kt CAS less than 60 kts !

! 211 ! Total Air Temp ! NO ! !

! 212 ! Altitude Rate ! NO ! !

! 213 ! Static Air Temp ! NO ! !

! 215 ! Impact Pressure ! NO ! !

! 221 ! Indicated AOA ! NCD ! NOTE CAS less than 60 kts !

! 230 ! True Airspeed ! NCD ! 0 kt CAS less than 60 kts !

! 231 ! Total Air Temp ! NO ! !

! 232 ! Altitude Rate ! NO ! !

! 233 ! Static Air Temp ! NO ! !

! 234 ! Baro Corr (hPa) 1 ! NO ! !

! 236 ! Baro Corr (hPa) 2 ! NO ! !

! 235 ! Baro Corr (in.Hg) 1 ! NO ! !

! 237 ! Baro Corr (in.Hg) 2 ! NO ! !

! 240 ! VMO/MMO ! NO ! !

! 241 ! Corrected AOA ! NCD ! Cmptd value CAS less than 60Kts !

! 242 ! Total Pressure ! NO ! !

! 176 ! L. Static Pressure ! NO ! !

! 177 ! R. Static Pressure ! NO ! !

! 245 ! Uncrctd Avg Stat Pressure! NO ! !

! 246 ! Corctd Avg Stat Pressure ! NO ! !

! 270 ! Discrete word 1 ! NO ! !

! 271 ! Discrete word 2 ! NO ! !

! 272 ! Discrete word 3 ! NO ! !

! 277 ! ADR test ! NO ! !

! 352 ! Discrete word 4 ! NO ! !

! 354 ! LRU ident ! NO ! !

! 377 ! Equipement ident ! NO ! !

! 356 ! CFDIU interface word ! N/A ! N/A !

------------------------------------------------------------------------------

Table 16 - Output Label Value on Ground

(5) Discrete form
The ADR provides seven standard OPEN/GROUND output discretes (Ref. table 17).

--------------------------------------------------------------------------

! SIGNAL ! PIN ! OUTPUT ! DEFINITION !

!------------------------------!------------!-------------!--------------!

! ADR OFF Status ! TP- 4E ! OPEN/GROUND ! ON/OFF !

! ADR FAULT ! TP- 4D ! OPEN/GROUND ! NO/FAULT !

! Low Speed Warning Discrete 1 ! TP- 2F ! OPEN/GROUND ! SLOW/FAST !

! Low Speed Warning Discrete 2 ! TP- 2G ! OPEN/GROUND ! SLOW/FAST !

! Low Speed Warning Discrete 3 ! TP- 6F ! OPEN/GROUND ! SLOW/FAST !

! Low Speed Warning Discrete 4 ! TP-13H ! OPEN/GROUND ! FAST/SLOW !

! AOA Special Test ! TP-12G ! OPEN/28VDC ! NO/TEST !

--------------------------------------------------------------------------

Table 17 - ADR - Discrete Output Signals

(a) ADR OFF Status
When the ADR is commanded OFF, it issues a ground state to the ADR OFF light discrete to enable the legend to come on.

(b) ADR FAULT
When an ADR FAULT is detected, the ADR issues a ground state to the ADR FAULT discrete to enable the legend to come on.

(c) Low speed warning discretes 1, 2, 3, 4
The ADR provides four standard Open/Ground low speed-warning output discretes.

Airspeed conditions
Airspeed decreasing
Discrete 1 = OPEN for Airspeed less than or equal to 100 knots
Discrete 2 = OPEN for Airspeed less than or equal to 50 knots
Discrete 3 = OPEN for Airspeed less than or equal to 155 knots
Discrete 4 = GROUND for Airspeed less than or equal to 260 knots
Airspeed increasing
Discrete 1 = GROUND for Airspeed greater than 104 knots
Discrete 2 = GROUND for Airspeed greater than 54 knots
Discrete 3 = GROUND for Airspeed greater than 159 knots
Discrete 4 = OPEN for Airspeed greater than 264 knots
Power off conditions
Discrete 1 = OPEN
Discrete 2 = OPEN
Discrete 3 = OPEN
Discrete 4 = OPEN
CAS detected failure condition
Discrete 1 = previous state
Discrete 2 = previous state
Discrete 3 = previous state
Discrete 4 = OPEN

(d) AOA special test
The ADR provides an OPEN/GROUND output discrete to drive the AOA self-test.
The AOA self-test is commanded via the CFDS interface bus. When the AOA test is active, the AOA sensor is offset to +15 deg. (plus or minus 1 deg.). All AOA dependent parameters reflect this offset and their SSMs indicate Functional Test (FT).
The RETURN command from the MCDU results in the discrete output set to OPEN.
Ref. 34-18-00 for more details.

** ON A/C NOT FOR ALL

3. Operation/Control and Indicating

A. Control

(1) ADIRS Mode Selector Unit (MSU)

ADR Control on MSU ** ON A/C NOT FOR ALL

The ADIRS MSU provides the control and warning of the three ADRs by means of three ADR illuminated pushbutton switches:

The pushbutton switch is used to disable the ADR output buses. It is a momentary action pushbutton switch.
When the ADR output buses are disabled, the ADR controls the activation of the ADR OFF legend by its output discrete: ADR OFF status.
When an ADR failure is detected, the ADR controls the activation of the ADR FAULT legend by its output discrete: ADR FAULT.
Each ADR is de-energized when the associated OFF/NAV/ATT selector switch is set to OFF.
When the associated OFF/NAV/ATT selector switch is set to NAV or ATT, each ADR is switched on independently of the previous selection on the ADR pushbutton switch.

(2) ADIRS Mode Selector Unit (CDU)

ADR Control on CDU ** ON A/C NOT FOR ALL

The ADIRS MSU provides the control and warning of the three ADRs by means of three ADR illuminated pushbutton switches:

The pushbutton switch is used to disable the ADR output buses. It is a momentary action pushbutton switch.
When the ADR output buses are disabled, the ADR controls the activation of the ADR OFF legend by its output discrete: ADR OFF status.
When an ADR failure is detected, the ADR controls the activation of the ADR FAULT legend by its output discrete: ADR FAULT.
Each ADR is de-energized when the associated OFF/NAV/ATT selector switch is set to OFF.
When the associated OFF/NAV/ATT selector switch is set to NAV or ATT, each ADR is switched on independently of the previous selection on the ADR pushbutton switch.

B. Indicating
Altitude (ALT), Computed Airspeed (CAS), Mach number (M) and Vertical Speed (V/S) are computed by the ADIRU (ADR portion), processed by the associated DMC and displayed on the PFDs.
True Airspeed (TAS) is supplied in the same way but is displayed on the NDs.
In normal configuration, with the AIR DATA selector switch in NORM position, the ADR 1 displays information on CAPT PFD and ND. The ADR 2 displays information on F/O PFD and ND.
Static Air Temperature (SAT) and Total Air Temperature (TAT) are also supplied in the same way but are permanently displayed on the lower part of the lower ECAM DU.
These items of information are displayed by the ADR 2 when EIS 1 is installed, by ADR 1 when EIS 2 is installed.

(1) PFD display
For further details concerning speed, altitude or vertical speed scale, Ref. 31-64-00.

(a) Computed Airspeed (CAS)

Computed Airspeed and Mach Indication Display ** ON A/C NOT FOR ALL

The CAS indication is displayed in analog form by means of a white tape with graduations every 10 kts and digital values every 20 kts. This tape moves up and down so as to indicate the A/C actual speed value in front of a fixed yellow reference line.
The displayed part of the scale represents an 84 kts range. The scale is graduated from 30 kts to 520 kts and the digital values from 40 to 520 kts (item A).
In no case can the displayed CAS be lower than 30 kts.
In case of computed airspeed failure, the speed scale goes out of view and is replaced by a red SPD flag (item B).

(b) Mach number (M)
When the Mach number is above 0.5, it is displayed just below the speed scale.
In case of failure, a red MACH flag is presented.

Altitude Indication Display ** ON A/C NOT FOR ALL

The baro altitude indication is provided by means of a tape which moves up and down behind a window within which the A/C actual altitude is displayed.
The tape of the scale is graduated every 100 ft and digital values are displayed every 500 ft in hundreds.
The A/C actual altitude is provided by a counter located at the middle of the scale in which the actual value is displayed in green digits.
The hundreds of feet are written in a large size whereas the tens and units are displayed by a drum operating as a classical mechanical altimeter.
Small white marks are positioned in front of each number on the tape (item A).
If the altitude is negative, a NEG white indication is added at the left of the digital value. The digital value is limited to minus 1500 ft (item B).
Different displays are presented depending on the baro setting reference (standard or baro corrected), Ref. 31-64-00.
In case of baro altitude failure, the scale goes out of view and a red ALT flag flashes for a few seconds in the altitude window then remains steady (item C).
In case of discrepancy between the altitude given by the CAPT air data source and the altitude given by the F/O air data source, a CHECK ALT amber flag is presented on the right side of the altitude scale (item D).

(d) Vertical Speed (V/S)

Vertical Speed Indication Display ** ON A/C NOT FOR ALL

The baro vertical speed is automatically displayed in the right side of the PFD when the inertial vertical speed is not available (item A).
It is a degraded mode.
The vertical speed scale consists of:

a trapezoidal grey background colored surface
a fixed white scale with 500 ft/mn spaced marks from -2000 ft/mn to +2000 ft/mn
a needle giving in analog form the actual vertical speed value
a number in a moving amber window. This window accompanies the needle (above the needle if V/S > 0, below if V/S < 0).
The number gives the V/S value in hundreds of ft/mn.
Between -200 ft/mn and +200 ft/mn, both the window and the number disappear.
above +6000 ft/mn (or below -6000 ft/mn), the needle remains stopped where it is.

When the vertical speed exceeds +6000 ft/mn or -6000 ft/mn, the digital indication and the analog needle change from green to amber.
In addition, those indications change to amber in approach, in the following cases:

V/S less than -2000 ft/mn below 2500 ft RA
V/S less than -1200 ft/mn below 1000 ft RA.

In case of a failure warning, the vertical speed scale is removed and replaced by a red V/S flag which flashes for a few seconds then remains steady (item B).

(2) ND display

True Airspeed Indication Display ** ON A/C NOT FOR ALL

The true airspeed (TAS) is displayed on the ND in ROSE, ARC and PLAN mode (item A).
The TAS information is displayed by a numerical indication of three digits preceded by TAS indication. This information is displayed in the left upper corner of the ND for speed higher than 100 kts. Below this value TAS indication remains visible but is followed by three dashes (item B).

(3) Display on the lower ECAM DU

TAT/SAT Indication Display ** ON A/C NOT FOR ALL

The Static Air Temperature (SAT) and the Total Air Temperature (TAT) are permanently displayed on the lower part of the lower ECAM DU by a numerical indication of two digits preceded by the plus or minus sign (item A).
These data are delivered by the ADR 2 when EIS 1 is installed, by ADR 1 when EIS 2 is installed.
In case of failure or when NCD information is received from the ADR 1, these data are replaced by crosses (item B).

(4) Reconfiguration display
In case of loss of AIR DATA parameters on CAPT or F/O PFD and ND, the ADR 3 can be used as a back up source by placing the AIR DATA selector switch in CAPT/3 position for EFIS 1 and F/O/3 position for EFIS 2.
In case of loss of TAT/SAT parameters on the lower ECAM DU, the ADR 3 can be used as a back up source by placing the AIR DATA selector switch in F/O/3 position when EIS 1 is installed, in CAPT/3 position when EIS 2 is installed.

C. Warnings
In addition to the AIR DATA flags displayed on the PFDs and NDs, warning messages are displayed on the lower part of the upper ECAM DU.
Two kinds of warning messages can be displayed:

failure warning messages in case of loss of AIR DATA parameters
configuration warning messages in case of dangerous configuration of the aircraft.

When the CLR key is pushed on the ECAM control panel, a STATUS page is displayed on the lower ECAM DU and indicates the STATUS and INOP SYS (systems).
In addition to the AIR DATA flags displayed on the PFDs and NDs and On the CDU, warning messages are displayed on the lower part of the upper ECAM DU.
Two kinds of warning messages can be displayed:

failure warning messages in case of loss of AIR DATA parameters
configuration warning messages in case of dangerous configuration of the aircraft.

When the CLR key is pushed on the ECAM control panel, a STATUS page is displayed on the lower ECAM DU and indicates the STATUS and INOP SYS (systems).

(1) Failure warning messages

NAV ADR 1(2)(3) FAULT Message ** ON A/C NOT FOR ALL

NAV ADR 1+3(2+3) FAULT Message ** ON A/C NOT FOR ALL

NAV ADR 1 + 2 FAULT Message ** ON A/C NOT FOR ALL

(a) NAV ADR 1(2)(3) FAULT
NAV ADR 1(2) + 2(3) FAULT
When these messages are displayed:

the MASTER CAUT lights on the glareshield come on
the Single Chime (SC) sounds
the FAULT legend of the ADR pushbutton switch on the MSU comes on.

(b) NAV ALTI DISCREPANCY

NAV ALTI DISCREPANCY Message ** ON A/C NOT FOR ALL

This message is displayed when a difference higher than plus or minus 250 ft is detected by the external comparison inside the FWCs between the baro-corrected altitude (or plus or minus 500 ft for the standard altitude) provided by two ADRs.
When it is displayed:

the MASTER CAUT lights on the glareshield come on
the Single Chime (SC) sounds
the CHECK ALT message appears on the PFD.

(2) Failure warning messages

NAV ADR 1(2)(3) FAULT Message ** ON A/C NOT FOR ALL

NAV ADR 1+3(2+3) FAULT Message ** ON A/C NOT FOR ALL

NAV ADR 1 + 2 FAULT Message ** ON A/C NOT FOR ALL

(a) NAV ADR 1(2)(3) FAULT
NAV ADR 1(2) + 2(3) FAULT
When these messages are displayed:

the MASTER CAUT lights on the glareshield come on
the Single Chime (SC) sounds
the FAULT legend of the ADR pushbutton switch on the CDU comes on.

(b) NAV ALTI DISCREPANCY

NAV ALTI DISCREPANCY Message ** ON A/C NOT FOR ALL

the MASTER CAUT lights on the glareshield come on
the Single Chime (SC) sounds
the CHECK ALT message appears on the PFD.

(3) Configuration warning messages

OVERSPEED VMO/MMO Message ** ON A/C NOT FOR ALL

OVERSPEED VFE/VLE Message ** ON A/C NOT FOR ALL

(a) OVERSPEED VM0/MM0
OVERSPEED VFE/VLE
When these messages are displayed:

the MASTER WARN lights on the glareshield flash
the Continuous Repetitive Chime (CRC) sounds.

OVERSPEED VMO/MMO warning processed by the FWC is triggered when the CAS/Mach calculated by the ADR exceed the VMO/MMO threshold by more than 4 kts/0.006 Mach.
OVERSPEED VFE/VLE processed by the FWC is a function of CAS and depends on slat/flap position for the VFE and landing gear position for the VLE.
For overspeed VLE, the warning is triggered at 284 knots.

(b) Stall warning

Stall Warning Message ** ON A/C NOT FOR ALL

When this warning is activated:

the MASTER WARN lights on the glareshield flash
the cricket and the voice STALL sound.

This warning is processed by the FWC and is a function of angle of attack value and slat position following these conditions:

normal law:
if corrected angle of attack exceeds 23° or if corrected angle of attack exceeds 15° and slat < 15° and aircraft in clean configuration
alternate law
if corrected angle of attack exceeds 13° or if corrected angle of attack exceeds 8° and slat < 15°.

[Rev.10 from 2021] 2026.04.02 06:23:07 UTC