FUNCTIONAL INTERFACES - DESCRIPTION AND OPERATION

** ON A/C NOT FOR ALL

1. General

General Arrangement of A/C ECU - A/C Interfaces/T/R Interface ** ON A/C NOT FOR ALL

The FADEC unit interfaces with the following aircraft functional elements:

Air data computer which transmits air data signals to the engine control system.
Engine interface unit which : concentrates airframe signals and transmits them to the ECU, Receives information from engine and dispatches them to other systems.
Cockpit system display which furnishes engine parameters indication to the crew.
Throttle control system which translates the crew commands for engine throttle level into a command signal to the ECU.
The thrust reverser system.
The AIDS interface which records engine data for maintenance purposes.
Electrical power supply from airframe to power FADEC system while engines are not running.

** ON A/C NOT FOR ALL

2. System Description

A. FADEC Inputs/Outputs

General Arrangement of A/C ECU - A/C Interfaces/T/R Interface ** ON A/C NOT FOR ALL

Engine Fuel and Control Functional Interfaces ** ON A/C NOT FOR ALL

(1) Digital Input
Inputs of each channel are isolated in order to prevent failure propagation between channel A and B and/or between both engines.
Each channel of the ECU has input ports for both ADIRU and EIU plus an input port for a spare.

(2) Digital Output

(a) General
Bit transmission rate is nominally 12.5 kHz. Each channel of the ECU has two output ports and each bus has separate line drivers.
Outputs are isolated in such a way that propagation of failures is prevented.
Information contained on FADEC output buses includes the following general items:

Engine Rating Parameter Information
Parameters used for Engine Control
FADEC System Maintenance Data
Engine Condition Monitoring Parameters
ECU Status and Fault Indication.

A detailed list of the specific data items on the output data buses is shown in Tables 1 to 20.

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

! ! ! Nominal !Binary!Significant! Operating ! !

!Parameter !label!transmit ! ! ! range ! units !

! ! !interval !Range ! Bits ! Min.! Max. ! +/- 5%!

! ! ! (msec) ! ! ! ! ! !

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

!ENG SERIAL ! ! ! ! ! ! ! !

!NUMBER ! 046 ! 960 ! BCD ! N/A ! N/A ! N/A ! LSD'S !

!ENG SERIAL ! ! ! ! ! ! ! !

!NUMBER ! 047 ! 960 ! BCD ! N/A ! N/A ! N/A ! MSD'S !

!ENG ON TIME! 050 ! 960 !65635 ! 17 ! 0 !65,535! HOURS !

!TM DEMAND, ! ! ! ! ! ! ! !

!VBV ! 052 ! 240 ! 512 ! 12 ! -300! 300 ! MA !

!TM DEMAND, ! ! ! ! ! ! ! !

!RAC ! 054 ! 480 ! 512 ! 12 ! -300! 300 ! MA !

!POSITION, ! ! ! ! ! ! ! !

!RACSB SEL. ! 055 ! 480 ! 128 ! 12 ! 0 ! 100 !PERCENT!

!DEMND RACSB! 057 ! 480 ! 128 ! 12 ! 0 ! 100 !PERCENT!

!DEMAND FMV ! 060 ! 120 ! 128 ! 12 ! 0 ! 100 !PERCENT!

!DEMAND VSV ! 061 ! 240 ! 64 ! 12 ! -5.8!38.71 ! DEG. !

!DEMAND VBV ! 062 ! 240 ! 64 ! 12 ! 0 ! 40 ! DEG. !

!DEMAND HPTC! 063 ! 480 ! 128 ! 12 ! 0 ! 100 !PERCENT!

!DEMAND LPTC! 064 ! 480 ! 128 ! 12 ! 0 ! 100 !PERCENT!

!POSITION, ! ! ! ! ! ! ! !

!VBV SLCTD ! 071 ! 240 ! 64 ! 12 ! 0 ! 40 ! DEG. !

!POSITION, ! ! ! ! ! ! ! !

!VSV SLCTD ! 072 ! 120 ! 64 ! 12 ! -5.8!38.71 ! DEG. !

!P0 SELECTED! 114 ! 240 ! 32 ! 12 ! 2 ! 20 ! PSIA !

!HPTC SLCT ! ! ! ! ! ! ! !

!TEMP. ! 116 ! 480 ! 1024 ! 12 ! -55 ! 850 ! DEG.C !

!PS13 ! 127 ! 240 ! 32 ! 12 ! 2 ! 30 ! PSIA !

!T12 ! 130 ! 240 ! 128 ! 11 ! -55 ! 85 ! DEG.C !

!PT2 ! 131 ! 240 ! 32 ! 12 ! 1.75! 22 ! PSIA !

!TLA ! ! ! ! ! ! ! !

!FILTERED ! 133 ! 120 ! 1 ! 12 !-25.0! 55.0 !DEG/180!

! ! ! ! ! ! /180! /180 ! !

!N1 REF ! 166 ! 120 ! 256 ! 12 ! 0 ! 108 !% RPM !

!A/C M0 ! 205 ! 240 ! 4.096! 12 ! 0 ! 1 ! MACH !

!A/C TAT ! ! ! ! ! ! ! !

!SELECTED ! 211 ! 240 ! 512 ! 11 ! -60 ! 99 ! DEG.C !

!T FLEX ! 214 ! 240 ! 128 ! 16 ! -55 ! 85 ! DEG.C !

!A/C PRESS ! ! ! ! ! ! ! !

!IMPACT ! 215 ! 240 ! 512 ! 12 ! 0 ! 450 ! MB. !

!A/C PT ! ! ! ! ! ! ! !

!SELECTED ! 242 ! 240 ! 2048 ! 12 ! 135 ! 1,379! MB. !

!WFM ! 244 ! 480 !32768 ! 16 ! 0 !15,000! PPH !

!T5 ! 260 ! 240 ! 1024 ! 12 ! -55 ! 850 ! DEG.C !

!P25 ! 262 ! 240 ! 64 ! 12 ! 2 ! 50 ! PSIA !

!T25 ! ! ! ! ! ! ! !

!ESTIMATED ! 263 ! 240 ! 256 ! 12 ! -55 ! 120 ! DEG.C !

!PS3 SLCTD ! 264 ! 120 ! 512 ! 12 ! 2 ! 450 ! PSIA !

!T3 SELECTED! 265 ! 240 ! 1024 ! 12 ! -55 ! 850 ! DEG.C !

!TM DEMAND, ! ! ! ! ! ! ! !

!FMV ! 300 ! 60 ! 512 ! 12 !-300 ! -300! MA. !

!TM DEMAND, ! ! ! ! ! ! ! !

!LPTC ! 301 ! 480 ! 512 ! 12 !-300 ! -300! MA. !

!TM DEMAND, ! ! ! ! ! ! ! !

!VSV ! 302 ! 120 ! 512 ! 12 !-300 ! -300! MA. !

!A/C BLEED, ! ! ! ! ! ! ! !

!CALCULATED ! 303 ! 240 ! 64 ! 12 ! 0 ! 20 ! PPS. !

!ECU TEMP. ! 304 ! 960 ! 256 ! 12 ! -55 ! 125 ! DEG.C !

!POS., HPTC ! ! ! ! ! ! ! !

!SELECTED ! 306 ! 480 ! 128 ! 12 ! 0 ! 100 !PERCENT!

!POS., LPTC ! ! ! ! ! ! ! !

!SELECTED ! 307 ! 480 ! 128 ! 12 ! 0 ! 100 !PERCENT!

!TEO SLCTD ! 316 ! 960 ! 2048 ! 12 ! -55 ! 170 ! DEG.C !

!N1 LIMIT ! 337 ! 120 ! 256 ! 14 ! 0 ! 102 ! % RPM !

!N1 COMMAND ! 341 ! 120 ! 256 ! 14 ! 0 ! 102 ! % RPM !

!N1 MAXIMUM ! 342 ! 240 ! 256 ! 14 ! 0 ! 102 ! % RPM !

!N1 TARGET ! 343 ! 120 ! 256 ! 14 ! 0 ! 102 ! % RPM !

!N2 ACTUAL ! ! ! ! ! ! ! !

!SELECTED ! 344 ! 60 ! 256 ! 13 ! 0 ! 120 ! % RPM !

!T495 SLCTD ! 345 ! 120 ! 2048 ! 12 ! -55 ! 1,200! DEG.C !

!N1 ACTUAL ! ! ! ! ! ! ! !

!SELECTED ! 346 ! 60 ! 256 ! 13 ! 0 ! 120 ! % RPM !

!POSITION, ! ! ! ! ! ! ! !

!FMV SLCTD ! 347 ! 30 ! 128 ! 12 ! 0 ! 100 !PERCENT!

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

ECU ARINC Output Bus (BCD, Binary Data)

Table 1

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

! ! ! Nominal !

! Parameter ! label ! Transmit !

! ! ! Interval !

! ! ! (msec) !

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

! ECU Status Word 1 ! 270 ! 240 !

! Engine Rating Word ! 271 ! 960 !

! ECU Status Word 2 ! 272 ! 240 !

! ECU Status Word 3 ! 273 ! 120 !

! ECU Status Word 4 ! 274 ! 120 !

! ECU Status Word 5 ! 275 ! 120 !

! ECU Status Word 6 ! 011 ! 960 !

! ECU Status Word 7 ! 066 ! 960 !

! Maintenance Word 1 ! 350 ! 480 !

! Maintenance Word 2 ! 351 ! 480 !

! Maintenance Word 3 ! 352 ! 480 !

! Maintenance Word 4 ! 353 ! 480 !

! Maintenance Word 5 ! 354 ! 240 !

! Maintenance Word 6 ! 355 ! 240 !

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

NOTES:

1. ARINC transmit interval tolerance is +/- 5 percent.

2. Each label and bit is updated at the nominal transmit interval rate

ECU ARINC Output Bus (Discrete Data)

Table 2

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

! Bit ! Description (Bit = 1) ! 0 ! Failure !

! No. ! ! ! Class !

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

! 11 ! Ignition 1 Primary Selected ! ! !

! 12 ! Starter Air Valve Switch Fault-Latched ! ! !

! 13 ! Starter Air Valve Open-Local Switch ! Closed ! !

! 14 ! HP Fuel Valve Closed - Local Switch ! Not Closed ! !

! 15 ! SAV Position Fault ! ! Class 1* !

! 16 ! HPSOV Position Fault ! ! !

! 17 ! Start - EGT Overtemperature Detected ! ! Class 1* !

! 18 ! Start - Stall Detected ! ! Class 1* !

! 19 ! No/ Low Fan Speed for Core Speed ! ! Class 1* !

! 20 ! No Engine Lightoff Detected ! ! Class 1* !

! 21 ! Starter Time Limit Exceeded ! ! * !

! 22 ! Fuel Schedule Derich Active ! ! !

! 23 ! TLA Not At Idle for Start Initiation ! ! !

! 24 ! Channel in Control ! ! !

! 25 ! Low Sap - (Slow Start) detected ! ! Class 3 !

! 26 ! Start Abort Active ! ! Class 1* !

! 27 ! New Start in Progress ! ! !

! 28 ! 50 Percent Thrust Limit Active ! ! !

! 29 ! HP Fuel Valve Switch Fault - Latched ! ! !

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

* Immediate message on the ECAM

ECU Status Word 1 - Label 270

ECU ARINC Output Bus Data (Discrete)

Table 3

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

! Bit ! Description (Bit = 1) !

! No. ! !

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

! 11 ! SAV Position Fault - Latched !

! 12 ! HPSOV Position Fault - Latched !

! 13 ! TRPV Position Fault - Latched !

! 14 ! Oil Temp Fault - Latched !

! 15 ! TLA Sensor Fault - Latched !

! 16 ! TRDV Solenoid Fault - Latched !

! 17 ! Engine Family Least Significant Bit !

! 18 ! Engine Family Middle Bit !

! 19 ! Engine Family Most Significant Bit !

! 20 ! Bump Selection Status LSB !

! 21 ! Bump Selection Status Middle Bit !

! 22 ! Bump Selection Status MSB !

! 23 ! Wing Anti-ice Commanded !

! 24 ! Bleed Constant K1 Commanded and Latched !

! 25 ! Bleed Constant K2 Commanded and Latched !

! 26 ! Bleed Constant K3 Commanded and Latched !

! 27 ! Bleed Constant K4 Commanded and Latched !

! 28 ! Bleed Constant K5 Commanded and Latched !

! 29 ! Bleed Constant K6 Commanded and Latched !

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

Engine Rating Word - Label 271

Table 4

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

! Bit ! Description (Bit = 1) ! Failure !

! No. ! ! Class !

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

! 11 ! Master Lever "Off" ! !

! 12 ! Spare ! !

! 13 ! Spare ! !

! 14 ! Spare ! !

! 15 ! Max Reverse Limit Mode Selected ! !

! 16 ! TLA MCT set to FTO ! !

! 17 ! BSV Position Fault Latched ! !

! 18 ! Bump/Overboost Active ! !

! 19 ! Auto Thrust Active ! !

! 20 ! Approach Idle Commanded ! !

! 21 ! Alpha Floor Protection Commanded ! !

! 22 ! MTO. GA Limit Mode Selected ! !

! 23 ! Flex TO Limit mode Selected ! !

! 24 ! MCT Limit Mode Selected ! !

! 25 ! MCL Limit Mode Selected ! !

! 26 ! Engine Interface Unit ARINC Fault ! !

! 27 ! Autothrust Disconnect Commanded ! !

! 28 ! Aircraft on Ground ! !

! 29 ! Minimum Power Active ! !

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

ECU Status Word 2 - Label 272

Table 5

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

! Bit ! Description-ARINC LABEL 273 !

! No. ! !

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

! 11 ! Manual Air Start N2 Less Than 10% !

! 12 ! Four T/R Doors not Stowed !

! 13 ! HP Fuel Valve Commanded Open !

! 14 ! RAC Position Fault - Latched !

! 15 ! Category 2 Fault(s) - Latched !

! 16 ! LPTC Position Fault - Latched !

! 17 ! Core Speed Below 15 Percent !

! 18 ! Core Speed at or Above 50 Percent !

! 19 ! Auto-Start Sequence in Progress !

! 20 ! Manual Start in Progress !

! 21 ! Wet Crank in Progress !

! 22 ! Dry Crank in Progress !

! 23 ! Continuous Ignition Active !

! 24 ! Blow Out Recovery Active !

! 25 ! Four T/R Doors Fully Stowed and Locked !

! 26 ! Four T/R Doors Fully Deployed !

! 27 ! 1, 2, or 3 T/R Doors Not Stowed !

! 28 ! Thrust Reverser System Pressurized !

! 29 ! Start Assist Fail - EMER W/M Start SEL !

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

NOTE: - Iteration time is 120 ms.
- Set bits 30 and 31 (SM bits) to zero.

ECU Status Word 3 - Label 273

ECU ARINC Output Bus Data (Discrete)

Table 6

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

! Bit ! Description-ARINC LABEL 275 !

! No. ! !

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

! 11 ! TRPV Position Fault - Latched !

! 12 ! T/R Pressure Switch Fault - Latched !

! 13 ! 115 VAC to Ignitor 1 Commanded !

! 14 ! Ignition System 1 Fault !

! 15 ! 115 VAC to Ignitor 2 Commanded !

! 16 ! Ignition System 2 Fault !

! 17 ! SAV Open Commanded !

! 18 ! Burner Staging on 10 Nozzles Commanded !

! 19 ! BSV Closed Position Fault !

! 20 ! BSV Switch Fault - Latched !

! 21 ! RAC Position Fault !

! 22 ! T/R Stow Switch Circuit Failure - Latched !

! 23 ! Engine Oil Temp High Fault !

! 24 ! T/R Deploy Switch Circuit Failure - Latched !

! 25 ! T/R Indeterminable SW Circuit Failure - Latched !

! 26 ! T/R Deploy Commanded !

! 27 ! T/R Pressurize Commanded !

! 28 ! T/R Auto Restow Commanded !

! 29 ! LPTC Position Fault !

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

NOTE: - Iteration time is 120 ms.
- Set bits 30 and 31 (SM bits) to zero.

ECU Status Word 4 - Label 274

ECU ARINC Output Bus Data (Discrete)

Table 7

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

! Bit ! Description-ARINC LABEL 275 !

! No. ! !

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

! 11 ! ECU Cooling Commanded !

! 12 ! Reserved for Flight Warning Computer !

! ! Logic Panel: 77980 !

! 13 ! Spare !

! 14 ! FMV Position Fault or Overthrust !

! 15 ! N1/N2 Control Active !

! 16 ! FMV Position Fault - Latched !

! 17 ! VBV Position Fault - Latched !

! 18 ! VBV Position Fault !

! 19 ! VSV Position Fault - Latched !

! 20 ! VSV Position Fault !

! 21 ! HPTC in Bleed Position Fault - Latched !

! 22 ! HPTC in Bleed Position Fault !

! 23 ! ECU Designation Discretes Invalid !

! 24 ! Engine ID Plug Fault - Latched !

! 25 ! Fuel Return to A/C Commanded !

! 26 ! Channel "A" Active !

! 27 ! Channel "B" Active !

! 28 ! All Channel Controls Active !

! 29 ! HPTC Position Fault !

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

NOTE: - Iteration time is 120 ms.
- Set bits 30 and 31 (SM) to zero.

ECU Status Word 5 - Label 275

ECU ARINC Output Bus Data (Dicretes)

Table 8

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

! Bit ! Description-ARINC LABEL 011 !

! No. ! !

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

! 11 ! Burner Staging Valve Position Status !

! 12 ! Regulator, bit 1 !

! 13 ! Regulator, bit 2 !

! 14 ! Regulator, bit 3 !

! 15 ! Regulator, bit 4 !

! 16 ! Regulator, bit 5 !

! 17 ! Reserved for CFM56-5B !

! 18 ! Reserved for CFM56-5B !

! 19 ! Reserved for CFM56-5B !

! 20 ! Reserved for CFM56-5B !

! 21 ! ENGPNLMD Indicator Bit 1 !

! 22 ! ENGPNLMD Indicator Bit 2 !

! 23 ! ENGPNLMD Indicator Bit 3 !

! 24 ! ENGPNLMD Indicator Bit 4 !

! 25 ! Reserved for CFM56-5B Dual Annular C. !

! 26 ! Reserved for CFM56-5B Dual Annular C. !

! 27 ! Spare !

! 28 ! Spare !

! 29 ! Menu Mode Active !

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

NOTE: - Iteration time is 960 ms.
- Set bits 30 and 31 (SM) to zero.

ECU Status Word 6 - Label 011

ECU ARINC Output Bus Data (Discrete)

Table 9

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

! Bit ! Description-ARINC LABEL 066 !

! No. ! !

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

! 11 ! A/C Type Bit 1 !

! 12 ! A/C Type Bit 2 !

! 13 ! Idle Commanded by TLA Fault !

! 14 ! Bleed Latched by ECU !

! 15 ! Engine Type = 5B (False = 5A) !

! 16 ! Reserved for CFM56-5B !

! 17 ! Reserved for CFM56-5B !

! 18 ! Spare !

! 19 ! Spare !

! 20 ! Spare !

! 21 ! Spare !

! 22 ! Spare !

! 23 ! Spare !

! 24 ! Spare !

! 25 ! Spare !

! 26 ! Spare !

! 27 ! Spare !

! 28 ! T/R Shut Off Valve Installed !

! 29 ! T/R Shut Off Valve Failed Open !

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

NOTE: - Iteration time is 960 ms.
- Set bits 30 and 31 (SM) to zero.

ECU Status Word 7 - Label 066

ECU ARINC Output Bus Data (Discrete)

Table 10

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

! Bit ! Description-ARINC LABEL 350 !

! No. ! !

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

! 11 ! TAT ADC1 Input Not Used !

! 12 ! P0 ADC1 Input Not Used !

! 13 ! PT ADC1 Input Not Used !

! 14 ! HPTC Position Fault - Latched !

! 15 ! TAT ADC2 Input Not Used !

! 16 ! P0 ADC2 Input Not Used !

! 17 ! PT ADC2 Input Not Used !

! 18 ! Cross Channel TLA Input Fault - Latched !

! 19 ! Local Channel TLA Input Fault - Latched !

! 20 ! TLA Input Inequality Fault !

! 21 ! TRDV Aircraft Switch Fault !

! 22 ! Thrust Reverser Position Fault !

! 23 ! TRPV SOL Wrap Fault/HCU CLOG Detection !

! 24 ! T/R Directional VLV Solenoid Wrap Fault !

! 25 ! ECU Overtemperature Fault - Latched !

! 26 ! Airframe 28 VDC Power Unavailable !

! 27 ! Instinctive Disconect Fault - Latched !

! 28 ! 115 VAC to Ignitor 1 Unavaible !

! 29 ! 115 VAC to Ignitor 2 Unavaible !

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

NOTE: -Iteration time is 480 ms.
-Set bits 30 and 31 (SM bits) to zero.

ECU Maintenance Word 1 - Label 350

ECU ARINC Output Bus Data (Discrete)

Table 11

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

! Bit ! Description-ARINC LABEL 351 !

! No. ! !

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

! 11 ! FLEX Temperature Input Invalid !

! 12 ! A/T N1 Target Input Invalid !

! 13 ! ECS MOD Idle Input Invalid !

! 14 ! Bleed Const. - 030 EIU Input Invalid !

! 15 ! A/C Discrete - 031 EIU Input Invalid !

! 16 ! Autothrust - 034 EIU Input Invalid !

! 17 ! CFDS Signal - 227 EIU Input Invalid !

! 18 ! FMV Sensor Inequality Fault !

! 19 ! VSV Sensor Inequality Fault !

! 20 ! VBV Sensor Inequality Fault !

! 21 ! HPTC Sensor Inequality Fault !

! 22 ! Flight Number Input Invalid !

! 23 ! Date Input Invalid !

! 24 ! GMT Input Invalid !

! 25 ! RAC Sensor Inequality Fault !

! 26 ! LPTC Sensor Inequality Fault !

! 27 ! PS13 Sensor Fault - Latched !

! 28 ! TECU Sensor Fault - Latched !

! 29 ! Fuel Flow Sensor Fault - Latched !

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

NOTE: - Iteration time is 480 ms.
- Set bits 30 and 31 (SM bits) to zero.

ECU Maintenance Word 2 - Label 351

ECU ARINC Output Bus Data (Discrete)

Table 12

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

! Bit ! Description-ARINC LABEL 352 !

! No. ! !

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

! 11 ! T12 Sensor Fault !

! 12 ! T25 Sensor Fault !

! 13 ! T495 Sensor Fault - Latched !

! 14 ! HPTC T/C Sensor Fault - Latched !

! 15 ! Logic 0 - Reserved for A/C T25 Fault Use !

! 16 ! P0 Sensor Fault !

! 17 ! PT2 Sensor Fault !

! 18 ! PS3 Sensor Fault !

! 19 ! PS3 Local/Model Disagree !

! 20 ! N1 and N2 Sensor Fault !

! 21 ! N1 Sensor Fault !

! 22 ! N2 Sensor Fault !

! 23 ! T3 Sensor Fault !

! 24 ! T5 Sensor Fault - Latched !

! 25 ! Logic 0-Reserved for A/C N1 Fault Use !

! 26 ! TE0 Sensor Fault - Latched !

! 27 ! P25 Sensor Fault - Latched !

! 28 ! Reserved for A/C N2 Fault Use !

! 29 ! Reserved for A/C T3 Fault Use !

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

NOTE: - Iteration time is 480 ms.
- Set bits 30 and 31 (SM bits) to zero.

ECU Maintenance Word 3 - Label 352

ECU ARINC Output Bus Data (Discrete)

Table 13

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

! Bit ! Description-ARINC LABEL 353 !

! No. ! !

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

! 11 ! FMV Sensor Fault !

! 12 ! FMV Torque Motor Wrap Fault !

! 13 ! VBV Sensor Fault !

! 14 ! VBV Torque Motor Wrap Fault !

! 15 ! VSV Sensor Fault !

! 16 ! VSV Torque Motor Wrap Fault !

! 17 ! HPTC Sensor Fault - Latched !

! 18 ! HPTC Torque Motor Wrap Fault - Latched !

! 19 ! SAV Solenoid Wrap Fault - Latched !

! 20 ! T495 Sensor Inequality Fault !

! 21 ! LPTC Sensor Fault - Latched !

! 22 ! LPTC Torque Motor Wrap Fault - Latched !

! 23 ! BSV Solenoid Wrap Fault - Latched !

! 24 ! TC Sensor Inequality Fault !

! 25 ! TEO Sensor Inequality Fault !

! 26 ! RAC Sensor Fault - Latched !

! 27 ! RAC Torque Motor Wrap Fault - Latched !

! 28 ! OSG Fault !

! 29 ! Alternator Fault !

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

NOTE: - Iteration time is 480 ms.
- Set bits 30 and 31 (SM bits) to zero.

ECU Maintenance Word 4 - Label 353

ECU ARINC Output Bus Data (Discrete)

Table 14

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

! Bit ! Description-ARINC LABEL 354 !

! No. ! !

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

! 11 ! Reserved for Flight Warning Computer !

! ! Logic Panel: 77980 !

! 12 ! X Channel Data Link Serial Bus Fault !

! 13 ! NVM Fault !

! 14 ! X Channel Data Link Parallel Disc Fault !

! 15 ! ECU Temperature Warning Exceeded !

! 16 ! ECUCV Solenoid Wrap Fault - Latched !

! 17 ! FRV Solenoid Wrap Fault - Latched !

! 18 ! WOW Inputs Disagree !

! 19 ! Signal Conversion Fault - Latched !

! 20 ! Spare !

! 21 ! Local Channel Major Internal Fault !

! 22 ! T/C Cold Junction Compensation Fault !

! 23 ! Local Channel Major Internal Fault !

! 24 ! Cross Channel Major Internal Fault !

! 25 ! ECU Local Channel Fault !

! 26 ! ECU Temperature Limit Exceeded !

! 27 ! Autothrust Inoperative !

! 28 ! Burner Staging Valve Position Status !

! 29 ! 28 VDC Disconnect Command !

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

NOTE: - Iteration time is 240 ms.
- Set bits 30 and 31 (SM bits) to zero.

ECU Maintenance Word 5 - Label 354

ECU ARINC Output Bus Data (Discrete)

Table 15

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

! Bit ! Description-ARINC LABEL 355 !

! No. ! !

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

! 11 ! Core Speed at or above N2IDL !

! 12 ! Autothrust Memo Thrust Mode Active !

! 13 ! Idle Selected Due to T/R Inadvertently Deployed !

! 14 ! Voluntary Autothrust Logic Active !

! 15 ! 28 VDC Fault - Latched !

! 16 ! 28 VDC Fault Due to EIU - Latched !

! 17 ! Reserved for CFM56-5B Compatibility !

! 18 ! Reserved for CFM56-5B Compatibility !

! 19 ! Reserved for CFM56-5B Compatibility !

! 20 ! Reserved for CFM56-5B Compatibility !

! 21 ! Reserved for CFM56-5B Compatibility !

! 22 ! Reserved for CFM56-5B Compatibility !

! 23 ! Reserved for CFM56-5B Compatibility !

! 24 ! Reserved for CFM56-5B Compatibility !

! 25 ! Reserved for CFM56-5B Compatibility !

! 26 ! Reserved for CFM56-5B Compatibility !

! 27 ! Reserved for CFM56-5B Compatibility !

! 28 ! Reserved for CFM56-5B Compatibility !

! 29 ! Spare !

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

NOTE: - Iteration time is 240 ms.
- Set bits 30 and 31 (SM bits) to zero.

ECU Maintenance Word 6 - Label 355

ECU ARINC Output Bus Data (Discrete)

Table 16

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

! Bit ! Description !

! No. ! Condition True = Bit at 1 !

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

! 11 ! Logic 1 - Indicates CFMI Engine Is Installed (For Aircraft Use) !

! 12 ! Logic 0 - Indicates CFMI Engine Is Installed (For Aircraft Use) !

! 13 ! Logic 0 !

! 14 ! Logic 0 !

! 15 ! LSB of - Digit 1 of ENG S/N --! !

! 16 ! Bit 2 - Digit 1 of ENG S/N ! 1's !

! 17 ! Bit 3 - Digit 1 of ENG S/N ! !

! 18 ! MSB of - Digit 1 of ENG S/N --! !

! 19 ! LSB of - Digit 2 of ENG S/N --! !

! 20 ! Bit 2 - Digit 2 of ENG S/N ! 10's !

! 21 ! Bit 3 - Digit 2 of ENG S/N ! !

! 22 ! MSB of - Digit 2 of ENG S/N --! !

! 23 ! LSB of - Digit 3 of ENG S/N --! !

! 24 ! Bit 2 - Digit 3 of ENG S/N ! 100's !

! 25 ! Bit 3 - Digit 3 of ENG S/N ! !

! 26 ! MSB of - Digit 3 of ENG S/N --! !

! 27 ! Logic 0 !

! 28 ! Logic 0 !

! 29 ! Logic 0 !

! 30 ! Logic 0 (SM Bit) !

! 31 ! Logic 0 (SM Bit) !

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

ARINC Label 046

FADEC Engine Serial No. BCD Output Word

Table 17

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

! Bit ! Description !

! No. ! Condition True = Bit at 1 !

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

! 11 ! Logic 1 - Indicates CFMI Engine Is Installed (For Aircraft Use) !

! 11 ! Logic 0 - Indicates CFMI Engine Is Installed (For Aircraft Use) !

! 13 ! Logic 0 !

! 14 ! Logic 0 !

! 15 ! LSB of - Digit 4 of ENG S/N --! !

! 16 ! Bit 2 - Digit 4 of ENG S/N ! 1,000's !

! 17 ! Bit 3 - Digit 4 of ENG S/N ! !

! 18 ! MSB of - Digit 4 of ENG S/N --! !

! 19 ! LSB of - Digit 5 of ENG S/N --! !

! 20 ! Bit 2 - Digit 5 of ENG S/N ! 10,000's !

! 21 ! Bit 3 - Digit 5 of ENG S/N ! !

! 22 ! MSB of - Digit 5 of ENG S/N --! !

! 23 ! LSB of - Digit 6 of ENG S/N --! !

! 24 ! Bit 2 - Digit 6 of ENG S/N ! 100,000's !

! 25 ! Bit 3 - Digit 6 of ENG S/N ! !

! 26 ! MSB of - Digit 6 of ENG S/N --! !

! 27 ! Logic 0 !

! 28 ! Logic 0 !

! 29 ! Logic 0 !

! 30 ! Logic 0 (SM Bit) !

! 31 ! Logic 0 (SM Bit) !

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

ARINC Label 047

FADEC Engine Serial No. BCD Output Word

Table 18

The ARINC 429 Output Data is transmitted in sequence as shown on

Tables 19 and 20.

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

! ARINC WORD ! Label Sequence !

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

! 1-10 ! 300 347 275 344 072 133 071 114 116 356 !

! 11-20 ! 060 347 346 264 273 274 127 130 131 244 !

! 21-30 ! 300 347 166 344 302 337 205 211 214 011 !

! 31-40 ! 061 347 346 341 343 345 215 242 260 306 !

! 41-50 ! 300 347 275 344 072 133 052 262 263 356 !

! 51-60 ! 060 347 346 264 273 274 265 270 350 355 !

! 61-70 ! 300 347 166 344 302 337 272 301 351 054 !

! 71-80 ! 062 347 346 341 343 345 303 342 354 352 !

! 81-90 ! 300 347 275 344 072 133 071 114 353 356 !

! 91-100 ! 060 347 346 264 273 274 127 130 131 046 !

! 101-110 ! 300 347 166 344 302 337 205 211 214 316 !

! 111-120 ! 061 347 346 341 343 345 215 242 260 271 !

! 121-130 ! 300 347 275 344 072 133 052 262 263 356 !

! 131-140 ! 060 347 346 264 273 274 265 270 063 355 !

! 141-150 ! 300 347 166 344 302 337 272 307 064 055 !

! 151-160 ! 062 347 346 341 343 345 303 342 354 057 !

! 161-170 ! 300 347 275 344 072 133 071 114 116 356 !

! 171-180 ! 060 347 346 264 273 274 127 130 131 244 !

! 181-190 ! 300 347 275 344 302 337 205 211 214 066 !

! 191-200 ! 061 347 346 341 343 345 215 242 260 306 !

! 201-210 ! 300 347 275 344 072 133 052 262 263 356 !

! 211-220 ! 060 347 346 264 273 274 265 270 350 355 !

! 221-230 ! 300 347 166 344 302 337 272 301 351 054 !

! 231-240 ! 062 347 346 341 343 345 303 342 354 352 !

! 241-250 ! 300 347 275 344 072 133 071 114 353 356 !

! 251-260 ! 060 347 346 264 273 274 127 130 131 047 !

! 261-270 ! 300 347 166 344 302 337 205 211 214 304 !

! 271-280 ! 061 347 346 341 343 345 215 242 260 050 !

! 281-290 ! 300 347 275 344 072 133 052 262 263 356 !

! 291-300 ! 060 347 346 264 273 274 265 270 063 355 !

! 301-310 ! 300 347 166 344 302 337 272 307 064 055 !

! 311-320 ! 062 347 346 341 343 345 303 342 354 057 !

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

ECU ARINC Output Transmission Sequence

Normal Mode Transmission

Table 19

NOTE: Five labels are transmitted every 15 ms.

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

! ARINC WORD ! Label Sequence !

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

! 1-10 ! 300 347 275 344 072 133 071 114 116 356 !

! 11-20 ! 060 347 346 264 273 274 127 130 131 244 !

! 21-30 ! 300 347 166 344 302 205 211 214 011 356 !

! 31-40 ! 061 347 346 341 343 345 215 242 260 306 !

! 41-50 ! 300 347 275 344 072 133 052 262 263 356 !

! 51-60 ! 060 347 346 264 273 274 265 270 350 355 !

! 61-70 ! 300 347 166 344 302 272 301 351 054 356 !

! 71-80 ! 062 347 346 341 343 345 303 342 354 352 !

! 81-90 ! 300 347 275 344 072 133 071 114 353 356 !

! 91-100 ! 060 347 346 264 273 274 127 130 131 046 !

! 101-110 ! 300 347 166 344 302 205 211 214 304 356 !

! 111-120 ! 061 347 346 341 343 345 215 242 260 271 !

! 121-130 ! 300 347 275 344 072 133 052 262 263 356 !

! 131-140 ! 060 347 346 264 273 274 265 270 063 355 !

! 141-150 ! 300 347 166 344 302 272 307 064 055 356 !

! 151-160 ! 062 347 346 341 343 345 303 342 354 057 !

! 161-170 ! 300 347 275 344 072 133 071 114 116 356 !

! 171-180 ! 060 347 346 264 273 274 127 130 131 244 !

! 181-190 ! 300 347 275 344 302 205 211 214 066 356 !

! 191-200 ! 061 347 346 341 343 345 215 242 260 306 !

! 201-210 ! 300 347 275 344 072 133 052 262 263 356 !

! 211-220 ! 060 347 346 264 273 274 265 270 350 355 !

! 221-230 ! 300 347 166 344 302 272 301 351 054 356 !

! 231-240 ! 062 347 346 341 343 345 303 342 354 352 !

! 241-250 ! 300 347 275 344 072 133 071 114 353 356 !

! 251-260 ! 060 347 346 264 273 274 127 130 131 047 !

! 261-270 ! 300 347 166 344 302 205 211 214 304 356 !

! 271-280 ! 061 347 346 341 343 345 215 242 260 050 !

! 281-290 ! 300 347 275 344 072 133 052 262 263 356 !

! 291-300 ! 060 347 346 264 273 274 265 270 063 355 !

! 301-310 ! 300 347 166 344 302 272 307 064 055 356 !

! 311-320 ! 062 347 346 341 343 345 303 342 354 057 !

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

ECU ARINC Output Transmission Sequence

Normal Mode Transmission

Table 20

(b) Specification
Additional characteristics of the ECU digital output data buses are as follows:

1 Continuity
The ECU transmission is continuous on all the output buses in normal operation irrespective of which channel is in control. The data transmission is inhibited when the processor in the applicable channel is not functioning, during power-up or power-down transients, and during channel initialization.
After initialization, the ECU tranmits all the labels continuously, including when in maintenace menu mode. The ECU initialization is completed within 3 seconds when N2 is less than 890 rpm. Above 890 N2 rpm, the initialization is accomplished in less than or equal to 750 ms. The normal ECU ARINC transmission will begin as soon as initialization has been completed.
Following a power interruption/transient greater than 5 ms or a commanded reset when above 890 N2 rpm, the ECU ARINC outputs resume normal transmission in less than 750 ms following the interruption, transient or reset.

2 Synchronization
The two ARINC output buses on a given ECU channel are not synchronized. The same set of ARINC labels are transmitted in the same order but are not synchronized to the same frame. Channel to channel ARINC bus synchronization may not be possible due to initialization constraints.

3 Output Differences
No output differences exist in the two buses on each channel unless an ARINC tansmitter is incorrect. In most cases, parameter values from sensors output by the two separate ECU channels will be slightly different but will be within signal tolerance requirements. Data which is specific to a channel, such as fault and maintenance data, may differ from channel to channel.

4 Channel Switchover Effect
Channel switchover does not affect the output data of the ECU with the exception of the status indication for the channel in control, items specific to channel in control (such as some ARINC output bits) and whatever faults caused the switchover.

5 ARINC Wrap Around Data Verification
The aircraft ARINC output data bus 1 is verified for data integrity by means of looping the output data bus to an internal, dedicated ARINC input port within each ECU channel. Specified output data is read by the ECU and compared with the corresponding software buffer. Each channel reads the SDI, SM, data and parity for the following output labels every 240 ms.

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

! LABEL PARAMETER !

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

! 061 VSV Demand !

! 341 N1 Command !

! 343 N1 Target !

! 346 Selected N1 Actual !

! 347 Selected FMV Position !

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

6 Parametric Data
There are three types of parametric data output on the ARINC 429 data bus. The first is local channel data (calculated or sensed). This data is output to the ARINC bus with no cross-channel communication of parameters. Examples of this type of data include the following:
T12, TECU, solenoid and torque motor commands.
The second type of data is calculated from multiple sources and is called selected data. This data depends on inputs from the local and cross-channel and may be influenced from Air Data Computer 1 or 2 inputs. If the cross-channel communication bus is not functioning, the output parameters will be identical in both channels. If either single sensor faults occur, or the cross-channel is not functioning, the output parameters may be different due to the different resources available to each channel. Parameters of this type used by the aircraft are N1, N2, T495, TEO and thrust reverser position.
The third type of data is from signals with only one sensing element. When the cross-channel communication bus is functioning, the ARINC 429 output bus contains identical values for this type of parameter. When the cross-channel is not functioning, the channel without the direct access to the sensing element will output the last value before the cross-channel communication failure.
There are two ARINC 429 data buses per channel to transmit engine data to the aircraft.

7 Status matrix
The status matrix for the ARINC paramaters is based on the following criteria:

a Discrete words

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

! 31 ! 30 ! !

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

! 0 ! 0 ! Normal Operation !

! 0 ! 1 ! No Computed Data !

! 1 ! 0 ! Functional Test !

! 1 ! 1 ! Failure Warning !

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

b Binary words

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

! 31 ! 30 ! !

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

! 0 ! 0 ! Failure Warning !

! 0 ! 1 ! No Computed Data !

! 1 ! 0 ! Functional Test !

! 1 ! 1 ! Normal Operation !

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

c BCD words (engine serial number labels 046,047)

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

! 31 ! 30 ! !

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

! 0 ! 0 ! Normal Operation !

! 0 ! 1 ! No Computed Data or Failure Warning !

! 1 ! 0 ! Functional Test !

! 1 ! 1 ! Not Used !

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

The status matrix of parameters affected by the requested test will be 1.0 during ground test. Parameters and data unaffected by the test will be set valid/invalid according to normal criteria.

8 Source/destination Identifier (SDI)
The SDI for the ARINC output words will be assigned based on the Engine Designation Discretes from the Airframe and the channel designation. The assignment matrix is as shown below.
Engine 1 channel A ECU sends a SDI 01 (BIT 10 - BIT 9)
Engine 1 channel B ECU sends a SDI 11 (BIT 10 - BIT 9)
Engine 2 channel A ECU sends a SDI 10 (BIT 10 - BIT 9)
Engine 2 channel B ECU sends a SDI 00 (BIT 10 - BIT 9)

(3) Discrete and Analog Signals
The ECU also receives discretes and analog signals from the airframe and from local engine sensors.
From airframe it receives:

(a) TLA signals
TLA validation logic is given in paragraph ECU/Throttle system interfaces.

(b) ECU reset: The ECU reset is associated to the ENG MASTER 1(2) lever switching. When lever is moved from ON to OFF position the ECU is reseted.

ECU Reset ** ON A/C NOT FOR ALL

All the engine sensors signals are validated by the ECU - Basically The ECU checks the range limits, the rate limits and performs an interface fault detection.

B. ADIRU/ECU Interface

(1) General
ADIRU send air data parameters to the ECU through ARINC 429 buses. One output ARINC 429 buses of each ADIRU is dedicated to one engine control only

Interwiring ECU-ADIRU ** ON A/C NOT FOR ALL

(2) Input Data to ECU
Data is provided from ADIRU to the ECU at "LOW BIT RATE" defined by ARINC 429 (12 - 14.5 kilobits per second). Air data transmitted to the FADEC will be in accordance with TABLE 21.

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

! ! ! MAX ARINC ! Binary !Significant! Operating ! !

! Parameter !label! Update ! ! ! range !units!

! ! !Time (ms) ! Range ! Bits ! Min.* ! Max.* ! !

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

!Altitude ! 203 ! 66 ! 131.072! 17 !-2000 ! 50.000 ! feet!

!Total Air Temp.! 211 ! 500 ! 512 ! 11 ! -60.0! 99.0 !deg.C!

!Total Pressure ! 242 ! 126 ! 2.048! 16 ! 100 ! 1400 ! mb !

!Mach Number ! 205 ! 126 !4096 ! 16 ! 0.1! 1 ! Mach!

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

NOTE: - ADC 1 sends SDI 0 1 (BIT 10 - BIT 9)
- ADC 2 sends SDI 1 0 (BIT 10 - BIT 9)

ADIRU Data to FADEC

Table 21

(3) Data Validation and Selection Logic
The ECU performs validation test and selection logic between data coming from ADIRU and data from engine sensor, with the requirement that ADIRU inputs are preferred over engine sensor inputs, and used for rating calculations, otherwise engine sensor values will be used.
As an exception to that rule and only for operational purpose, it is acceptable that in case of complete loss of FADEC air data sensor, the corresponding value from the remaining ADIRU will be used.
The involved air data parameters used to validate Po, PT, TAT and calculate Mo, altitude, ambient temperature used in power management and engine control are:

Total Air Temperature !

Total Air Pressure ! from ADIRU1 and ADIRU2

Altitude -!

PS12 Air Inlet Pressure ! from local and Cross-channel

T12 Total Air Inlet Temperature _!

General arrangement of validation and selection logic are referenced

ADC Parameters Validation and Selection Logic ** ON A/C NOT FOR ALL

ARINC validation and sensor validations are given on TABLE 22.

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

! WORD LABEL ! ALTITUDE !TOTAL AIR ! TOTAL ! Mach !

! ! ! TEMP ! PRESSURE ! Number !

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

! BINARY DATA ! 203 ! 211 ! 242 ! 205 !

! WORD LABEL ! ! ! ! !

! FUNCTION ITERATION ! 240 ! 240 ! 240 ! 240 !

! TIME (ms) ! ! ! ! !

! ARINC UPDATE TIME ! 720 ! 1440 ! 720 ! 720 !

! LIMIT (ms) ! ! ! ! !

! VALID SDI CODE(S) ! 01,10 ! 01,10 ! 01,10 ! 01,10 !

! Bit 10, Bit 9 ! ! ! ! !

! VALID SM CODE(S) ! 11 ! 11 ! 11 ! !

! INPUT CONVERSION ! (Note 1) ! (Note 2) ! (Note 3) ! (Note 4) !

! FUNCTION ! ! ! ! !

!RANGE FAULT - Min ! -2.000 ! -60.0 ! 120.66 ! 0.0 !

!LIMIT - Max ! 50.000 ! +99.0 ! 1516.82 ! 1.0 !

!PARAMETER DEFAULT ! 0.0 ! 15.0 ! 1013.25 ! 0.0 !

!VALUE ! ! ! ! !

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

NOTE: 1 POADCn = 14.696 (1-6.8756 x 10exp.-6 (Data Field)) exp.5.25588 psia
2 TATADCn = (Data Field) deg. C
3 PTADCn = 0.014504 (Data Field) psia
4 MOADC1 = (Data Field) Mach. Available from ADC1 only.

ADIRU Data Validation

Table 22

C. EIU/ECU Interface

(1) General

(a) EIU Presentation
Two EIU's are fitted on each aircraft, one for engine 1, one for engine 2. Each EIU located in the electronics bay is an interface concentrator between the airframe and the corresponding ECU located on the engine, reducing thus the number of wires. EIU's are active at least from engine starting to engine shutdown, they are essential to start the engine.
The main functions of the EIU are:

to concentrate data from cockpit panels and different electronic boxes to the associated ECU on each engine,
to insure the segregation of the two engines,
to select the airframe electrical supplies for the FADEC,
to give to the airframe the necessary logic and information from engine to other systems (APU, ECS, Bleed Air, Maintenance).

(b) EIU/ECU Interface
Data link arrangement between EIU and ECU is shown in

ECU - EIU Digital Data Unit ** ON A/C NOT FOR ALL

1 EIU input from the ECU
The EIU acquires two ARINC 429 output data buses from the associated ECU (one from each channel) and it reads data from the channel in control. When some data are not available on the channel in control, data from the other channel are used.
The EIU will use Label 275 bit 26 and 27 on the ECU ARINC output buses to determine which channel is in control.
In the case where EIU is not able to identify the channel in control because of wrong setting of these bits, it will assume Channel A as in control.
The EIU will look at particular engine data on the ECU digital data flow to interface them with other aircraft computers and with engine cockpit panels.

2 EIU output to the ECU
Through its output ARINC 429 data bus, the EIU transmits data coming from all the A/C computers which have to communicate with the ECU, except from ADIRU's and throttle which communicate directly the ECU.
There is no data flow during EIU internal test or initialization.
The specific data outputs from EIU to ECU are given on tables 24 to 26.
The ECU performs the EIU data validation according to table 23.

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

! ! ! ! Function ! Maximum !

! Parameter Definition ! Mnemonic ! Label ! Iteration ! Update !

! ! ! ! Time (ms) ! Interval (ms) !

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

!A/C BLEED CONFIG. ! LABEL 030 ! 030 ! 240 ! 1440 !

!A/C STATUS/START ! LABEL 031 ! 031 ! 240 ! 720 !

!AUTO THROTTLE STATUS ! LABEL 034 ! 034 ! 240 ! 720 !

!GMT ! GMT ! 125 ! 240 ! 2880 !

!FLIGHT PHASE ! FLGTPH ! 126 ! 240 ! 2880 !

!A/C PRINTER STATUS ! LABEL 155 ! 155 ! 240 ! 2880 !

!FLEXIBLE TEMP ! TFLEXEIU ! 214 ! 240 ! 720 !

!ECS MIN PRESS DEMAND ! ECSDEIU ! 222 ! 60 ! 480 !

!BITE COMMAND ! LABEL 227 ! 227 ! 60 ! 720 !

!FLIGHT NUMBER, CH 1, 2 ! FLGTnCHR ! 233 ! Note 1 ! 12000 !

!FLIGHT NUMBER, CH 3, 4 ! FLGTnCHR ! 234 ! Note 1 ! 12000 !

!FLIGHT NUMBER, CH 5, 6 ! FLGTnCHR ! 235 ! Note 1 ! 12000 !

!FLIGHT NUMBER, CH 7, 8 ! FLGTnCHR ! 236 ! Note 1 ! 12000 !

!DATE ! DATE ! 260 ! 240 ! 2880 !

!A/C ID, CH 1, 2, 3 ! AIRIDnCHR ! 301 ! Note 2 ! 12000 !

!A/C ID, CH 4, 5, 6 ! AIRIDnCHR ! 302 ! Note 2 ! 12000 !

!A/C ID, CH 7 ! AIRIDnCHR ! 303 ! Note 2 ! 12000 !

!A/C ID, FLEET ID, ! Various ! 304 ! Note 2 ! 12000 !

!RECORD ! ! ! ! !

!AUTOTHR. N1 TARGET ! ATN1EIU ! 343 ! 60 ! 180 !

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

! Label ! Valid SM ! Valid SDI ! Conversion Function !

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

! 030 ! 00 ! 00, 01, 10, 11 ! Note 4 !

! 031 ! 00 ! 00, 01, 10, 11 ! Note 5 !

! 034 ! 00 ! 00, 01, 10, 11 ! Note 6 !

! 125 ! 00, 11 ! 00, 01, 10, 11 ! Note 7 !

! 126 ! 00, 11 ! 00, 01, 10, 11 ! Note 8 !

! 155 ! 00, 01, 10, 11 ! 00, 01, 10, 11 ! Note 9 !

! 214 ! 11 ! 00, 01, 10, 11 ! Note 10 !

! 222 ! 11 ! 00, 01, 10, 11 ! Note 11 !

! 227 ! 00, 01, 10, 11 ! Note 3 ! Note 12 !

! 233 ! 00, 01, 10, 11 ! 00 ! Note 13 !

! 234 ! 00, 01, 10, 11 ! 00 ! Note 14 !

! 235 ! 00, 01, 10, 11 ! 00 ! Note 15 !

! 236 ! 00, 01, 10, 11 ! 00 ! Note 16 !

! 260 ! 00, 11 ! 00, 01, 10, 11 ! Note 17 !

! 301 ! 00, 01, 10, 11 ! 00 ! Note 18 !

! 302 ! 00, 01, 10, 11 ! 00 ! Note 19 !

! 303 ! 00, 01, 10, 11 ! 00 ! Note 20 !

! 304 ! 00, 01, 10, 11 ! 00 ! Note 21 !

! 343 ! 11 ! 00, 01, 10, 11 ! Note 22 !

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

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

! ! Range Fault Limit ! Parameter ! Parameter !

! Label !____________________! Default ! Initialize !

! ! Min ! Max ! Value ! Value !

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

! 030 ! N/A ! N/A ! 0 ! 0 !

! 031 ! N/A ! N/A ! Table 24 ! Table 24 !

! 034 ! N/A ! N/A ! 0 ! 0 !

! 125 ! 00:00.0 ! 23:59.9 ! 00:00.0 ! 00:00.0 !

! 126 ! 0 ! 9.999 ! 0 ! 0 !

! 155 ! N/A ! N/A ! 0 ! 0 !

! 214 ! -99.0 ! 99.0 ! 0 ! 0 !

! 222 ! -1.0 ! 101.0 ! 100.0 ! 100 !

! 227 ! N/A ! N/A ! 0 ! 0 !

! 233 ! N/A ! N/A ! PRIOR VAL ! ISO5 0'S !

! 234 ! N/A ! N/A ! PRIOR VAL ! ISO5 0'S !

! 235 ! N/A ! N/A ! PRIOR VAL ! ISO5 0'S !

! 236 ! N/A ! N/A ! PRIOR VAL ! ISO5 0'S !

! 260 ! 01/01 ! 12/31 ! 00/00/00 ! 00/00/00 !

! 301 ! N/A ! N/A ! PRIOR VAL ! ISO5 0'S !

! 302 ! N/A ! N/A ! PRIOR VAL ! ISO5 0'S !

! 303 ! N/A ! N/A ! PRIOR VAL ! ISO5 0'S !

! 304 ! N/A ! N/A ! PRIOR VAL ! ISO5 0'S !

! 343 ! 0.0 ! 108.68 ! 200 RPM ! 200 RPM !

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

NOTES:

1 The EIU transmission rate of each of these parameters is 4000 ms.

The label is processed until two consecutive samples are equal.

The processingis started on a transition of Ground to flight. The decoding

of the label is stored in reserved RAM.

2 The EIU transmission rate of each of these parameters is 4000 ms. The label

is processed until two consecutive samples are equal. The processing is

started on a transition of Ground to Flight. The decoding of the label is

stored in the non-volatile memory (NVM).

3 Validation SDI for ENGINE 1 designation is 01 or 00 (Bits 10 and 9

respectively) and for ENGINE 2 designation is 01 or 00 (Bits 10 and 9

respectively). All other SDI and ECUDSG combinations are invalid.

4 Label 030 discrete assignments per Table 24.

5 Label 031 discrete assignments per Table 24.

6 Label 034 discrete assignments per Table 25.

7 GMT = (BCD Data Field) hours: minute per ARINC 429.

8 FLGTPH = (Binary Data Field).

9 Label 155 discrete assignments per Table 25.

10 TFLXEIU = (Binary Data Field) deg. c.

11 ECSDEIU = (Binary Data Field) percent.

12 Label 227 discrete assignments as follows:

. READY = Bit 11.

. HEC1 = Bits 13-16 Hexadecimal Equipment Code 1 (LSD).

. HEC2 = Bits 17-20 Hexadecimal Equipment Code 2.

. HEC3 = Bits 21-24 Hexadecimal Equipment Code 3 (MSD).

. 227CC = Bits 25-31 Command Code (ISO5). Unused bit 12 is zero.

The initialization state for all bits is zero, except for the following bits

in which the initialization state is one: 227CC = ISO5 null.

13 FLGT1CHR = ISO5 Bits 11-17 of Label 233 Flight Number Character 1 (MSC).

FLGT2CHR = ISO5 Bits 19-25 of Label 233 Flight Number Character 2.

Unused bits 9, 10, 18, 26-29 are zero.

14 FLGT3CHR = ISO5 Bits 11-17 of Label 234 Flight Number Character 3.

FLGT4CHR = ISO5 Bits 19-25 of Label 234 Flight Number Character 4.

Unused bits 9, 10, 18, 26-29 are zero.

15 FLGT5CHR = ISO5 Bits 11-17 of Label 235 Flight Number Character 5.

FLGT6CHR = ISO5 Bits 19-25 of Label 235 Flight Number Character 6.

Unused bits 9, 10, 18, 26-29 are zero.

16 FLGT7CHR = ISO5 Bits 11-17 of Label 236 Flight Number Character 7.

FLGT8CHR = ISO5 Bits 19-25 of Label 236 Flight Number Character 8 (LSC).

Unused bits 9, 10, 18, 26-29 are zero.

The FLGTnCHR labels are processed until two consecutive samples are equal.

THE processing is started on a transition of ESFLGTIND =

Ground to ESFLGTIND = Flight.

17 DATE = (BCD Data Field) per ARINC 429.

18 AIRID1CHR = ISO5 Bits 11-17 of Label 301 Aircraft Identification Character 1

(MSC).

AIRID2CHR = ISO5 Bits 18-24 of Label 301 Aircraft Identification Character 2

AIRID3CHR = ISO5 Bits 25-31 of Label 301 Aircraft Identification Character 3

19 AIRID4CHR = ISO5 Bits 11-17 of Label 302 Aircraft Identification

Character 4.

AIRID5CHR = ISO5 Bits 18-24 of Label 302 Aircraft Identification

Character 5.

AIRID6CHR = ISO5 Bits 25-31 of Label 302 Aircraft Identification

Character 6.

20 AIRID7CHR = ISO5 Bits 11-17 of Label 303 Aircraft Identification

Character 7 (LSC).

Unused Bits 18-31 are zero.

The Aircraft Identification labels is processed until two consecutive

samples are equal. The processing is started on a transition of

ESFLGTIND = Ground to ESFLGTIND = Flight.

21 AIRIDTYPE = ISO5 Bits 11-16 of Label 304 Aircraft Type Code Label 304

Bit 17 is spare (Logic Zero).

AIRIDFLID = ISO5 Bits 18-21 of Label 304 Aircraft Fleet Identification

Label 304 Bit 22 is spare (Logic Zero).

AIRIDREC = ISO5 Bits 23-24 of Label 304 Aircraft Record Version Label 304

Bit 22 is spare (Logic Zero).

22 ATN1EIU = 50.0 * (Binary Data Field) rpm.

EIU DATA VALIDATION PARAMETERS

Table 23

EIU Label 030 Discretes

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

! BIT ! ECU ! Parameter Definition ! Initialization !

! No ! Mnemonic ! Condition True = Bit at 1 ! Value !

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

! 11 ! - ! RESERVED ! !

! 12 ! BCK1 ! Bleed Config. K1 On ! 0 !

! 13 ! BCK2 ! Bleed Config. K2 On ! 0 !

! 14 ! BCK3 ! Bleed Config. K3 On ! 0 !

! 15 ! BCK4 ! Bleed Config. K4 On ! 0 !

! 16 ! BCK5 ! Bleed Config. K5 On ! 0 !

! 17 ! BCK6 ! Bleed Config. K6 On ! 0 !

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

Label 030 Bits 18 through 29 are reserved

EIU Label 031 Discretes

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

! BIT ! ECU ! Parameter Definition ! Initialization !

! No ! Mnemonic ! Condition True = Bit at 1 ! Value !

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

! 11 ! IGON ! Ignition On Selected ! 0 !

! 12 ! AUTO ! Automatic Start Selected ! 0 !

! 13 ! CRNK ! Crank Selected ! 0 !

! 14 ! MLON ! Master Lever "On" ! 0 !

! 15 ! MLOF ! Master Lever "Off" ! 1 !

! 16 ! MSTR ! Manual Start Selected ! 0 !

! 17 ! LHMLG ! LH Main Landing Gear Compressed ! 0 !

! 18 ! RHMLG ! RH Main Landing Gear Compressed ! 0 !

! 19 ! SLIN ! Slat Lever "In" ! 0 !

! 20 ! MIDL ! Modulated Idle Selected ! 0 !

! 21 ! - ! RESERVED ! !

! 22 ! FRSOV ! FRV Demand to Close ! 0 !

! 23 ! - ! RESERVED ! !

! 24 ! BRSF ! Bump Rating Select False ! 1 !

! 25 ! BRST ! Bump Rating Select True ! 0 !

! 26 ! - ! RESERVED ! !

! 27 ! VDCA ! 28 VDC Aircraft Supply ! 0 !

! 28 ! - ! RESERVED ! !

! 29 ! WAINS ! Wing Anti-Ice Not Selected ! 0 !

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

NOTE: APIL = Complement of MIDL.

Bit Definition of EIU Discrete Labels 30 and 31 to ECU

Table 24

EIU Label 034 Discretes

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

! BIT ! ECU ! Parameter Definition ! Initialization !

! No ! Mnemonic ! Condition True = Bit at 1 ! Value !

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

! 11 ! - ! RESERVED ! 0 !

! 12 ! - ! RESERVED ! 0 !

! 13 ! ATEN ! Auto Throttle Engaged ! 0 !

! 14 ! ATON ! Auto Throttle Active ! See Note !

! 15 ! ATVOLINSTAL ! Voluntary A/T Disconnect ! !

! ! ! Logic Installed ! 0 !

! 16 ! ATVOLDISENG ! Voluntary A/T Disconnect ! 0 !

! ! ! Command by FMGC ! !

! 17 ! - ! RESERVED ! !

! 18 ! - ! RESERVED ! !

! 19 ! - ! RESERVED ! !

! 20 ! - ! RESERVED ! !

! 21 ! - ! RESERVED ! !

! 22 ! - ! RESERVED ! !

! 23 ! AFPS ! Alpha Floor Protect ! 0 !

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

Bits 24 through 29 are reserved.

NOTE: Label 034 bit 15 (ATVOLINSTAL) is read continuously as long as the label is valid. If the label is not valid, the last valid value is retained except during engine start. During engine start (when the label is not valid), bit 15 is considered false.

EIU Label 155 Discretes

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

! BIT ! ECU ! Parameter Definition ! Initialization !

! No ! Mnemonic ! Condition True = Bit at 1 ! Value !

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

! 11 ! PRNT ! Printer is available ! 0 !

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

Bits 12 through 29 are reserved.

Bit Definition of EIU Di1crete Labels 34 and 155 to ECU

Table 25

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

! Parameter ! ECU ! ! !

! Definition ! Mnemonic ! Label ! Units !

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

! A/C BLEED CONFIG. ! LABEL 030 ! 030 ! N/A !

! A/C STATUS/START ! LABEL 031 ! 031 ! N/A !

! AUTO THROTTLE STATUS ! LABEL 034 ! 034 ! N/A !

! GMT ! GMT ! 125 ! HH:MM.M !

! FLIGHT PHASE ! FLGTPH ! 126 ! N/A !

! A/C PRINTER STATUS ! LABEL 155 ! 155 ! N/A !

! FLEXIBLE TEMP. ! TFLXEIU ! 214 ! deg.C !

! ECS MIN PRESS DEMAND ! ECSDEIU ! 222 ! % !

! BITE COMMAND ! LABEL 227 ! 227 ! N/A !

! FLIGHT NUMBER, CH 1, 2 ! FLGTnCHR ! 233 ! N/A !

! FLIGHT NUMBER, CH 3, 4 ! FLGTnCHR ! 234 ! N/A !

! FLIGHT NUMBER, CH 5, 6 ! FLGTnCHR ! 235 ! N/A !

! FLIGHT NUMBER, CH 7, 8 ! FLGTnCHR ! 236 ! N/A !

! DATE ! DATE ! 260 ! DD:MM:YY !

! A/C ID, CH 1, 2, 3 ! AIRIDnCHR ! 301 ! N/A !

! A/C ID, CH 4, 5, 6 ! AIRIDnCHR ! 302 ! N/A !

! A/C ID, CH 7 ! AIRIDnCHR ! 303 ! N/A !

! A/C ID, FLEET ID, RECORD ! Various ! 304 ! N/A !

! AUTOTHR. N1 TARGET ! ATN1EIU ! 343 ! rpm !

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

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

! ! Operating Range ! Binary ! Significant ! Approximate !

! Label !---------------------! Range ! Bits ! Resolution !

! ! Min ! Max ! ! ! !

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

! 030 ! N/A ! N/A ! N/A ! N/A ! N/A !

! 031 ! N/A ! N/A ! N/A ! N/A ! N/A !

! 034 ! N/A ! N/A ! N/A ! N/A ! N/A !

! 125 ! OO:OO.O ! 99:99.9 ! N/A ! N/A ! 0.1 MIN. !

! 126 ! 0 ! 9,999 ! 16 ! 4 ! N/A !

! 155 ! N/A ! N/A ! N/A ! N/A ! N/A !

! 214 ! -99.0 ! 99.0 ! 128 ! 7 ! 1.0 !

! 222 ! 0.0 ! 100.0 ! 256 ! 10 ! 0.25 !

! 227 ! N/A ! N/A ! ISO5 ! N/A ! N/A !

! 233 ! N/A ! N/A ! ISO5 ! N/A ! N/A !

! 234 ! N/A ! N/A ! ISO5 ! N/A ! N/A !

! 235 ! N/A ! N/A ! ISO5 ! N/A ! N/A !

! 236 ! N/A ! N/A ! ISO5 ! N/A ! N/A !

! 260 ! N/A ! N/A ! N/A ! N/A ! 1 DAY !

! 301 ! N/A ! N/A ! ISO5 ! N/A ! N/A !

! 302 ! N/A ! N/A ! ISO5 ! N/A ! N/A !

! 303 ! N/A ! N/A ! ISO5 ! N/A ! N/A !

! 304 ! N/A ! N/A ! ISO5 ! N/A ! N/A !

! 343 ! 0.0 ! 105.0 ! 256 ! 14 ! 0.015625 !

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

EIU Parameters to ECU

Table 26

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

! ITEM ! PIN ! PARAMETER DEFINITION ! Nature when !

! ! NUMBER ! ! active ! inactive !

! ! ! ! (1) ! (0) !

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

! D 1 ! A.A3 ! Engine 1 Side ! ground ! open circuit !

! D 2 ! A.B3 ! Provision ! ground ! open circuit !

! D 3 ! A.C3 ! Provision ! ground ! open circuit !

! D 4 ! A.B4 ! Engine 2 Side ! ground ! open circuit !

! D 5 ! A.D4 ! Full Provision, DISCRETE 1 ! ground ! open circuit !

! D 6 ! A.F2 ! Full Provision, DISCRETE 2 ! ground ! open circuit !

! D 7 ! A.D3 ! Provision ! ground ! open circuit !

! D 8 ! A.E3 ! (used by IAE) ! ground ! open circuit !

! D 9 ! A.A1 ! Engine Selector on "AUTO" Position ! ground ! open circuit !

! D 10 ! A.B1 ! Engine Selector on "IGNITION" ! ! !

! ! ! Position ! ground ! open circuit !

! D 11 ! A.C1 ! Engine Selector on "CRANK" Position ! ground ! open circuit !

! D 12 ! A.D1 ! Aiframe FADEC Supply on "ON ! ! !

! ! ! Position ! ground ! open circuit !

! D 13 ! A.E1 ! Wing Anti-ice Switch on "OFF" ! ! !

! ! ! Position ! ground ! open circuit !

! D 14 ! A.F1 ! "MAN" Engine Start Selected ! ground ! open circuit !

! D 15 ! A.B2 ! Flaps and Slats Lever in Retracted ! ! !

! ! ! Position ! ground ! open circuit !

! D 16 ! A.C2 ! Bump/Overboost "OFF" ! ground ! open circuit !

! D 17 ! A.E4 ! Master Lever "ON" ! ground ! open circuit !

! D 18 ! A.A5 ! Master Lever "OFF" ! ground ! open circuit !

! D 19 ! A.B5 ! Fire "ON" ! ground ! open circuit !

! D 20 ! A.C5 ! Nacelle Anti-ice Switch "OFF" ! ! !

! ! ! Position ! ground ! open circuit !

! D 21 ! A.D5 ! LH Main Landing Gear Compressed ! ground ! open circuit !

! D 22 ! A.E5 ! RH Main Landing Gear Compressed ! ground ! open circuit !

! D 23 ! A.C4 ! TLA Below Minus 3 Degrees ! ground ! open circuit !

! D 24 ! A.A2 ! FRSOV Selected "OFF" ! ! !

! ! ! (Aircraft Control) ! ground ! open circuit !

! D 25 ! A.A7 ! Oil Low Press Detected ! ground ! open circuit !

! D 26 ! A.E7 ! Provision ! ground ! open circuit !

! D 27 ! A.G7 ! Provision ! ground ! open circuit !

! D 28 ! A.C7 ! Provision (used by IAE) ! ground ! open circuit !

! D 29 ! A.D2 ! Bump/Overboost ON ! ground ! open circuit !

! D 30 ! A.E2 ! Provision ! ground ! open circuit !

! D 31 ! A.F3 ! Nose Wheel Landing Gear Compressed ! ground ! open circuit !

! D 32 ! A.A4 ! TLA Below Minus 3 Degrees ! ground ! open circuit !

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

NOTES:

- All the discrete inputs are low pass filtered (time constant = 12ms plus or

minus 20%).

- In case of one detected EIU failure, corresponding outputs are open circuit

for discrete outputs or have status 0 for digital bits.

Discrete Input Signals

Table 27

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

! ITEM ! PIN ! PARAMETER ! RANGE ! TIME ! TYPE !

! ! NUMBER ! DEFINITION ! ! CONSTANT ! !

! ! ! ! ! (s) ! !

! ! ! ! ! (Note 1)!!

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

! V1 ! A.J5 ! Provision !-! ! ! !

! ! ! (+) ! ! 0 to 10V ! 1.5 ! Analog !

! V1 ! A.K5 ! Provision !-! ! ! Voltage !

! ! ! (-) ! ! ! !

! ! ! ! ! ! !

! V2 ! A.B8 ! Oil Pressure !-! 0.7V to 9.1V ! 1.5 ! Analog !

! ! ! (+) ! ! ! ! Voltage !

! V2 ! A.D8 ! Oil Pressure !-! for 0 to 100 PSID ! ! !

! ! ! (-) ! ! ! !

! ! ! ! ! ! !

! V3 ! A.F8 ! oil Quantity !-! 1.3V to 9V ! ! !

! ! ! (+) ! ! ! 6 ! Analog !

! V3 ! A.H8 ! Oil Quantity !-! for 0 to 21.8 QTS ! ! Voltage !

! ! ! (-) ! ! ! !

! ! ! ! ! ! !

! V4 ! A.J7 ! Provision !-! ! ! !

! ! ! (+) ! ! 0 to 10V ! 1.5 ! Analog !

! V4 ! A.K8 ! Provision !-! ! ! Voltage !

! ! ! (-) ! ! ! !

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

! P1 ! A.E9 ! Provision + !-! ! ! !

! ! ! (supply) ! ! ! !Potentiometer!

! P1 ! A.G9 ! Provision + ! ! 0 to 10V ! 6 !300 Ohms < R !

! ! ! (signal) ! ! ! !< 2500 Ohms !

! P1 ! A.J9 ! Provision - ! ! ! ! !

! ! ! (supply) !-! ! ! !

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

! R1 ! A.D10 ! Nacelle ! ! ! !

! ! ! Temperature ! ! ! !

! ! ! (see Note 2) ! - 55 deg. C to ! 1.5 ! DIN 43760 !

! R1 ! A.B10 ! Nacelle ! + 300 deg. C ! ! !

! ! ! Temperature ! ! ! !

! ! ! (see Note 2) ! ! ! !

! R2 ! A.H10 ! Oil ! ! ! !

! ! ! temperature ! ! ! !

! ! ! (see Note 3) ! - 50 deg. C to ! 1.5 ! MIL SPEC T !

! ! ! ! + 200 deg. C ! ! 7990B !

! R2 ! A.F10 ! Oil ! ! ! !

! ! ! temperature ! ! ! !

! ! ! (see Note 3) ! ! ! !

! R3 ! A.C9 ! Provision ! ! 1.5 ! MIL SPEC !

! R3 ! A.A9 ! Provision ! ! ! T 7990B OR !

! ! ! ! ! ! DIN 43760 !

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

NOTES:

1 The time constant is inhibited if 2 successive readings differ by

more than 10%.

2 Resistance of one wire: 1.8 Ohm plus or minus 20%.

3 Resistance of one wire: 2.0 Ohm plus or minus 20%.

Analog Input Signals

Table 28

(2) EIU Description

(a) EIU inputs/outputs definition
The general EIU inputs/outputs layout is shown in

Engine Interface Unit ** ON A/C NOT FOR ALL

1 Inputs
The EIU receives a discrete signal, ARINC 429 lines, analog voltage and electrical supplies and is able to process data from resistor sensors.
The discrete signals which are of the ground/open circuit type are listed in tables 27.
The analog voltages which are of a differential type with a working range of 1 to 9 volts, include a filter with a time constant.
These inputs are listed in table 28.
The EIU receives several ARINC 429 lines and seeks specific information.
The selected information from the A/C computers is shown in

ARINC 429 Numerical Input Words ** ON A/C NOT FOR ALL

for numerical words and

ARINC 429 Discrete Input Words ** ON A/C NOT FOR ALL

for discretes.
The data flowpath from the ECU is described in tables 24 to 26. The selected EIU word information is shown in

ARINC 429 Numerical Input Words ** ON A/C NOT FOR ALL

ARINC 429 Discrete Input Words ** ON A/C NOT FOR ALL

2 Outputs
The EIU sends discrete outputs and ARINC 429 line outputs ; one ARINC line is dedicated to the ECU and the other to the A/C systems.
The discrete signals which are of the +28V/open circuit or ground/open circuit types are listed in

Discrete Output Signals ** ON A/C NOT FOR ALL

ARINC 429 Discrete Output Words ** ON A/C NOT FOR ALL

The EIU sends two ARINC 429 buses, on these bus lines the EIU sends information to the ECU and to the A/C system. The data flow is shown in

ARINC 429 Numerical Output Words ** ON A/C NOT FOR ALL

for numerical words and

ARINC 429 Discrete Output Words ** ON A/C NOT FOR ALL

for discretes.

3 Functions of the EIU

a Input data validation
The EIU has to acquire all information available on the inputs without losses.
Transmitted messages must not be modified, except messages with bad parity.
EIU receives two input buses (channel A and channel B) from the ECU, and reads data from in-control channel. When some data is not available on in-control channel, data from the other channel is used.
EIU receives two input buses (primary and secondary) from ECS, and reads data from primary channel, if they are not available secondary channel is used.
Some input signals are used to create output data ; when data is not available or in conflict with other sources, the correponding outputs are:

"open circuit" for discretes
"failure warning" for internal faults and "NCD" for external faults for ARINC data.

b Logics to be performed
The EIU has to perform the following logics with the acquired data:

discrete output: oil low press and ground, light fault on

discrete output and digital output: APU boost command 1 and 2 valve closure for engine start, TLA in TAKE-OFF position

- digital output: Modulated idle

28VDC airframe FADEC supply off

ECU BUS or N1 relay fault

Engine 1, engine 2

APU boost fault

Flight memory storage allowed

Nacelle high temp (real and latched signal)

Oil low press inop

Thrust reverser inhibition

Bump/overboost selection

Valve closure for engine start inop

Master level fault

Crank/auto/ignition fault

FADEC supply auto shut-down

Nacelle anti-ice and wing de-icing selection

FRSOV OFF selected

These logics are referenced

Processed Logics ** ON A/C NOT FOR ALL

c Fault logics
The EIU incorporates an internal BITE allowing efficient fault detection. The result of that fault detection shall be contained in status and maintenance words available on the output data bus:

external faults - label 350
internal minor faults - label 351
internal major faults - label 352

d Power-up tests
Power-up tests are accomplished only on the ground and if pressure switch indicates continuity to ground, in other cases initialization time is less than 20 ms.

D. EIU Power-up Test

(1) EIU/A/C Interface

(a) General environment
The EIU concentrates data from cockpit panels and different aircraft systems to send them to the FADEC unit and gives selected FADEC information to the A/C systems. The EIU communicates with a lot of A/C systems through analog and digital interfaces.
The general architecture of the EIU/AC interfaces is shown in

General Architecture ** ON A/C NOT FOR ALL

(2) AFCS interface - General
AFCS is part of the ATS function described in 73-20-00.
The automatic flight system provides the following functions related to engine power management.

compilation of N1 target
selection of autothrust modes
alpha floor protection
selection of flex T/O temperature

(3) AFCS interface - Input AFS to the ECU
Input from AFS to the ECU is the Flight Control Unit of the AFS and is linked to the EIU via an ARINC 429 low speed bus. The EIU then transmits this information to the ECU via the EIU/ECU digital data link.
The data link layout is shown in

AFS to ECU via EIU Wiring ** ON A/C NOT FOR ALL

Specific information from AFS is:

flex T/O temperature
auto-thrust active signal
auto-thrust demand : N1 target
alpha floor protection signal
auto thrust engagement signal.

(4) AFCS interface - Output to the AFS
The ECU sends directly some specific outputs to the AFS via the ARINC 429 output bus via directly via the FMGC which is part of AFS system. The data link arrangement is shown in

AFS to ECU via EIU Wiring ** ON A/C NOT FOR ALL

The EIU also receives these data from FADEC but does not transmit them to the AFS.
The following data are sent to the AFS:

- Throttle lever position - Engine set at min power

- N1 command - N1 throttle

- N1 actual - Fuel flow

- N1 target (feedback) - Bleed configuration

- N1 limit selected - Engine rating

- Thrust mode - Flex T/O temp

- N1 max

(5) ECS interface
The Environmental Control System (ECS) provides the following function related to the engine control :

Engine bleed port pressure demand
A/C and engine bleed configuration

Engine bleed part pressure demand : The compatibility between ECS and A/C performance necessitates a modulation of the engine idle during the descent.
This modulation is obtained by controlling the bleed pressure at the high pressure port.
The ECS sends a signal representing a coefficient K which has to be used as follows.
(curve 2) + K (curve 1 - curve 2) = pressure demand
Bleed configuration shall be generated by the ECS with respect of the actual position of the various values

General Schematics of Air Bleeds ** ON A/C NOT FOR ALL

Through the logic

General Schematics of Air Bleeds ** ON A/C NOT FOR ALL

ECS determines multipliers for the various air bleed configurations.
The FADEC takes these multipliers into account for computation of thrust corrections.
The ECS demand for idle setting and multipliers corresponding to the bleed configuration is sent through ARINC 429 data bus via EIU to the ECU. Data link arrangement is referenced

Interface between ECS Computer via EIU and ECU ** ON A/C NOT FOR ALL

EIU receives two input buses (primary and secondary) from ECS and reads data from primary channel ; if they are not available, secondary channel is used.
Characteristics of these signals are described in

EIU Input from ECS ** ON A/C NOT FOR ALL

(6) Engine starting control panel interface
The engine control panel is controlled from engine panel located on the center pedestal which provides:

the selector position,
the master lever position,

and receives the fault announcement
In addition, an engine manual start panel located on the overhead panel provides the "MAN start" signal to the ECU.
Input from engine starting control panel to the EIU are discrete input signal

Discrete Input Output from EIU to A/C Starting Control ** ON A/C NOT FOR ALL

General arrangement is shown in

Inputs from A/C Starting Control to ECU ** ON A/C NOT FOR ALL

Output from EIU to engine starting panel is a discrete output signal

Discrete Input Output from EIU to A/C Starting Control ** ON A/C NOT FOR ALL

General arrangement is shown in

Outputs from ECU to A/C Starting Control ** ON A/C NOT FOR ALL

The electrical circuit diagram is shown in

Engine Control Power Supply for Ignition and Starting Systems ** ON A/C NOT FOR ALL

(7) CFDS interface
The centralized fault data system is a means of accessing the systems to obtain maintenance information and initiate tests through the BITE of the system.
The communication is established through the existing ARINC 429 bus arrangement

Centralized Fault Display System ** ON A/C NOT FOR ALL

The FADEC and EIU menu function is requested by the CFDS system through the label 227. The EIU depending on the equipment code, the EIU will work in menu mode or transmit the request to the ECU.

(8) CFDS interface - ECU transmission

(a) Normal mode
The ECU transmits the messages as per the communication protocol defined in chapter 31-30-00.

(b) Menu mode
The following functions can be selected:

LAST LEG REPORT,
PREVIOUS LEGS REPORT,
LRU IDENTIFICATION,
TROUBLE SHOOTING REPORT,
SCHEDULED MAINTENANCE REPORT,
FADEC TEST,
IGNITION TEST,
THRUST REVERSER TEST.

(9) CFDS interface - EIU transmission

(a) Normal mode
The EIU transmits the messages as per to the communication protocol defined in chapter 31-30-00.

Text Transmission to CFDS ** ON A/C NOT FOR ALL

(b) Menu mode
The EIU deals only with the standard items of the menu which are:

LAST LEG REPORT,
PREVIOUS LEG REPORT,
LRU IDENTIFICATION.

(10) Other interfaces
The EIU receives other signals from various aircraft systems listed below:

nacelle A/I switch "OFF" position from cockpit panel,
wing A/I switch "OFF" position from cockpit panel,
airframe FADEC supply "ON" position from cockpit panel,
fuel recirculation shut-off valve selected "OFF" from the fuel system,
LH and RH landing gear compressed from LGCIU,
nose wheel landing gear compressed from LGCIU,
Engine 1 side from pin programming,
Engine 2 side from pin programming,
oil pressure, quantity, temperature from engine sensor,
nacelle temperature from engine sensor,
flaps and slats lever in retracted position from SFCC,
bump/overboost "OFF" position and "ON" position from pushbutton on throttle,
fire "ON" position from cockpit panel,
TLA below -3 deg. from SEC,
oil low press detected from engine switch.

All these inputs are shown in

Various EIU Inputs ** ON A/C NOT FOR ALL

The EIU sends some specific signals to various aircraft systems listed below:

APU boost command 1 and 2 - to the ECB,
2 "Oil low press and ground" signals to airframe systems and panels,
value closure to air valves,
HP fuel shut-off valve closed to the ECS,
T/A in T/O position,
core speed at or above idle,
throttle control interlock,
thrust reverser inhibition.

All these outputs are shown in

Discrete Output Signals ** ON A/C NOT FOR ALL

E. Cockpit Engine Fault Indication and Warning

(1) General
The ECU is closely integrated into the aircraft Electronic Centralized Aircraft Monitoring (ECAM) system to provide the cockpit fault indication and warning display. The propulsion system survey parameters are directly displayed on the dedicated Engine/Warning Display (upper ECAM Display Unit) and System Display (lower ECAM Display Unit).

(2) Cockpit Display System Definition
The engine information display data is processed by the ECAM system. This ECAM system includes:

two Display Units (DUs),
three Display Management Computers (DMCs),
two Flight Warning Computers (FWCs).

The general architecture is shown in

Interwiring from FADEC to Cockpit Indications ** ON A/C NOT FOR ALL

Each DMC and FWC receives one ARINC 429 bus from each ECU channel.

(a) Aircraft Display Units
The upper ECAM Display Unit (E/WD) and the lower ECAM Display Unit (SD) both receive data from the DMC. The E/WD is dedicated to the primary engine parameters and engine warning messages, and the SD is dedicated to the propulsion system parameters when the engine system page is called either automatically or manually.

Lower ECAM Display Unit ** ON A/C NOT FOR ALL

(b) Aircraft Display Management Computer
Each ECAM Display Management Computer (DMC) interfaces with the engine through ARINC 429 data buses to access current engine system status information. In normal operation, DMC1 drives the E/WD and DMC2 drives the SD. The DMCs utilize engine information from the ECU channel in control. Parameters which are not available (not refreshed or with invalid SSM) in the channel in control are picked up from the other channel. The DMCs utilize an ARINC update time limit of either 500 ms or three times the nominal transmit interval for all ECU system parameters, whichever is the longer. When the DMC1 is lost, it can be replaced by the DMC3 after a manual transfer; DMC3 can also replace the DMC2.

(c) Aircraft Flight Warning Computers
The ECAM Flight Warning Computers (FWCs) annunciate engine warning messages and their associated pilot action recommendation on the E/WD via the DMC based on engine status information. The two FWCs have the same engine monitoring capability.

(3) Cockpit Propulsion System Indications
The ECU ARINC output data is utilized in several ways by the ECAM system to provide the cockpit engine fault indications and warnings. The ECAM system displays the propulsion system survey parameters directly on the Engine/Warning and System Displays. There is also DMC processing performed for some of this E/WD data. The ECAM FWCs utilize ECU ARINC output data on a current faults basis to determine the cockpit propulsion system warnings for presentation on the E/WD display.

(a) Propulsion System Survey Parameters
The propulsion system survey parameters are displayed to the crew on the E/WD and SD. The DMCs use data from the ECU ARINC 429 output bus to display the propulsion system parameters as shown

Upper ECAM Display Unit ** ON A/C NOT FOR ALL

(b) DMC Processing
The DMC perform the following functions:

in case of invalid ECU ARINC data, the DMC indicates the failed status until valid data is received. An exception to this is N1 peak, N2 peak, EGT peak when greater than redline which is memorized as long as there is no DMC power interrupt; and fuel used is memorized at the engine power interrupt,
the Status Matrix "Functional Test" is considered invalid, except when ECU menu mode test is enabled,
some parameters limits are memorized in the DMC,
the Status Matrix "Non-computed Data" is considered by the DMC as non valid for all the parameters.

(4) Cockpit Propulsion System Warnings and Status
The propulsion system warnings and status are generated by the FWC. Class 1 and 2 faults are displayed by the FWC.
Detailed FWC logic is provided by the A/C manufacturer, for each FWC logic evolution; furthermore the FWC logic gives the inhibit phases. The warnings and the status are generated by the FWC based on current fault statuses transmitted from the ECU to the FWC, on the ARINC 429 data bus.
The warning activation leads to the display of the alarm.
All other procedure messages are qualified by the warning activation condition, and are not displayed unless the activation is present even if the conditions are satisfied.

(a) Centralized Fault Display System (CFDS)
The ECAM and CFDS apply different criteria for the display and report generation of fault data depending on the fault class.
For all class 1 (2) faults, the FWCs transmit the corresponding warnings and cautions (maintenance status) (displayed on the ECAM Display Units) to the CFDS for immediate transmission to the ACARS, and for the composition of the current leg or last leg ECAM report.
For scheduled maintenance faults, the faults are transmitted to the CFDS in menu mode only.

(b) FWC Flight Phase Inhibition
The FWC calculates an aircraft flight phase for use in the warning message logic. This is applied as an inhibit during specific phases. This flight phase calculation is similar to that performed by the CFDIU, but is entirely independent. Consequently, there may be differences between the FWC flight phase state and the CFDIU state that is input to the ECU on the EIU label 126.

F. Throttle Control System/ECU Interface

(1) General
Throttle control system is fully electrical, each throttle lever shall drive two resolvers, located in the cockpit center pedestal, these resolvers are dedicated to the FADEC, one for each engine

Inputs from Throttle Lever Transducers to ECU ** ON A/C NOT FOR ALL

The FADEC excites and demodulates these resolvers.
Each throttle lever is fitted with one pushbutton which is used to generate the autothrust disconnect discrete signal to the ECU.

(2) Interface

(a) Throttle Lever Angle (TLA) signal
TLA signals are sensed from resolvers rotated as a function of throttle lever positions.
Electrical characteristics are as follows:

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

! PARAMETER ! VALUE !

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

! Excitation: Voltage ! 7.07 + or - 0.14 V rms !

! Frequency ! 3,000 + or - 300 Hz !

! Current ! 6 mA rms nominal !

! Power ! 23.5 mW nominal !

! Zso. Stator Impedance, Rotor Open (0 deg.) ! 215 + j395 Ohms + or - 20% !

! Zso. Stator Impedance, Rotor Open (90 deg.) ! 56 + j104 Ohms + or - 20% !

! Zro, Rotor Impedance, Stator Open ! 650 + j980 Ohms + or - 20% !

! Zss, Stator Impedance, Rotor Shorted ! 54 + j128 Ohms + or - 20% !

! Transformation Ratio ! 0.492 + or - 0.025 !

! Phase Shift (output to input voltage) ! 0.5 deg. + or - 2.0 deg. !

! Total Null Voltage ! 20 mV rms max !

! Fundamental Null Voltage ! 15 mV rms max !

! Electrical Error on Transmitter ! + or - 5 minutes max !

! Electrical Error on Transmitter ! !

! (peak-to-peak) ! 6 minutes !

! Rotor DC Resistance ! 29.5 Ohms + or - 10% !

! Stator DC Resistance ! 15.5 Ohms + or - 10% !

! Cable DC Resistance Ch. A Including ! 10.8 Ohms nominal !

! Return Path ! !

! Cable DC Resistance Ch. B Including ! 6.1 Ohms nominal !

! Return Path ! !

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

NOTE: - resolver has copper windings.

the wire is gauge 24 in the aircraft and gauge 20 in the nacelle.
all characteristics must be met over the entire operating temperature range of the resolver.

There are two throttle resolvers per throttle lever, each dedicated to one channel of the ECU. Electrical excitation is provided by the ECU (one excitation output per channel).
The TLA resolver is a dual quadrant resolver which works in the first quadrant for positive angles and in the fourth quadrant for negative angles.
Therefore the TLA sine and cosine winding outputs are in phase with the excitation for resolver angle within 0 deg. to 90 deg. range of angle.
In the -90 deg. to 0 deg. range of angles the cosine output and the excitation are in phase and the sine output out of phase.
The TLA wiring between resolver unit and ECU is shown on

TLA Electrical Harness ** ON A/C NOT FOR ALL

(b) Instinctive autothrust disconnect signal
The ECU receives a signal directly issued by either the throttle 1 or throttle 2 pushbutton through an aircraft wiring when the instinctive disconnect pushbutton is pressed. The minimum pulse duration must not be less than 50 ms.

Autothrust Instinctive Disconnect ** ON A/C NOT FOR ALL

(3) TLA signal fault

(a) Fault detection
The TLA fault detection and validation logic are based on the following basic tests:

conversion range (Trigonometric Identity Test)
range tests (max and min limits)
rate check (in both increase or decrease directions)
TLA comparison (channel A to channel B has to be in 0.25 degree)

Detailed logic and values are given in

TLA Resolver Signal Processing ** ON A/C NOT FOR ALL

(b) Fault accommodation
The accommodation strategy is based on:

the objective to keep engine operational
the ECU capability to memorize value at the time of fault detection
the principle of using a throttle configuration allowing identification of the faulty value of TLA in case of disagreement between both channels

The accomodation strategy is described in

TLA Selection ** ON A/C NOT FOR ALL

The operationnal impact is given in

TLA Fault Accommodation Operational Impact ** ON A/C NOT FOR ALL

G. Thrust Reverser Interface

(1) General
The ECU controls the deployment and stowing sequence of the thrust reversers. The logic which is implemented in the ECU is based on TLA signals, flight ground signals, thrust reverser position feedback.
The general interwiring diagram is given in

Thrust Reverser - FADEC Interwiring Diagram ** ON A/C NOT FOR ALL

(2) Thrust reverser directional valve solenoid
The ECU interfaces with the thrust reverser directional valve (TRDV) solenoid. The solenoid contains two electrically isolated, independent windings, one dedicated to channel A and the other to channel B. Each of these windings conforms to the following characteristics (conditions measured at 20 deg. C ambient temperature):

(a) Actuation current 300 mA Minimum

(b) Actuation voltage 17.75 volts DC max. at 300 mA

(d) DC resistance 18 Ohm min.

(e) Sense

Energized T/R deploy (valve open)

Deenergized T/R stow (valve closed)

(f) Inductance (below 300 Hz) 500 millihenries nominal

(g) ECU Update time capability 50 milliseconds min.

(3) Thrust Reverser Pressurizing Valve (TRPV) solenoid
Each channel within the ECU interfaces with the TRPV solenoid. The solenoid contains two electrically isolated, independent windings. One dedicated to channel A and the other to channel B. Each of these windings conforms to the following characteristics:

(a) Actuation current 300 mA Minimum

(b) Actuation voltage 18.24 volts DC max. at 300 mA.

(d) DC resistance 18 Ohm min.

(e) Sense

Energized Shutoff valve open

Deenergized Shutoff valve closed

(f) Inductance (below 300 Hz) 500 millihenries nominal

(g) ECU Update time capability 50 milliseconds min.

(4) Thrust reverser switches
Each channel of the FADEC interfaces with:

the 4 deployed switches, one on each door, fitted in series
the 4 stow switches, one on each door, fitted in parallel
the hydraulic pressure switch.

Each switch has the following electrical characteristics:

open circuit voltage rating 50 VDC maximum

open circuit resistance 0.1 x 10exp.6 Ohms min.

current 2 to 10 mA

closed circuit resistance 5 Ohms max

** ON A/C NOT FOR ALL

3. Power Supply

A. 28VDC Power Supply
The ECU is designed to operate with the engine not running, the ECU is operational 2 to 3 seconds after it is electrically powered by A/C 28VDC. The ECU is electrically powered by the A/C through the EIU.
This A/C 28VDC permits:

automatic ground check of the FADEC before engine running,
engine starting,
powering the ECU while engine is running below 12 % N2.

As soon as the engine runs above 12 % N2 the FADEC automatically switches from A/C power to the engine alternator power supply.
After engine shutdown the ECU is powered by A/C 28VDC for 5 minutes to allow engine parameters monitoring.
Channel A and B 28VDC power inputs are isolated. Faults propagation between 28VDC and FADEC alternator inputs within each channel is prevented by design.
General schematic of 28VDC power is shown in

Electrical Power Supplies to FADEC ** ON A/C NOT FOR ALL

The total FADEC system 28VDC power requirement is shown in

28VDC Electrical Power Requirement ** ON A/C NOT FOR ALL

B. 115VAC Power Supply
The 115VAC power supply is dedicated to the ignitors.
General schematic of 115VAC power supply is shown in

Electrical Power Supplies to FADEC ** ON A/C NOT FOR ALL

** ON A/C NOT FOR ALL

4. FADEC Interfaces
All interfaces between ECU and engine sensors, LVDTS feedback and HMU are detailed in the chapter "ECU description" ATA 73-20-00

[Rev.10 from 2021] 2026.04.01 04:51:49 UTC